AIRCRAFT CHARACTERISTICS AIRPORT AND …com.airbus-fenice.customers.artful.net/.../files/...A350XWB-Jun16.pdf · @a350 aircraft characteristics - airport and maintenance planning

@AIRBUSA350

AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING

AC

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

AIRBUS S.A.S.Customer Services

Technical Data Support and Services31707 Blagnac Cedex

FRANCE

Issue: Jun 01/16 Rev: Jun 01/16

@A350AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 3 - Jun 01/16

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 1

Section 1-1

Subject 1-1-0 R

Introduction R PART EFFECTIVITYADDED/REVISED/DELETED

Section 1-2

Subject 1-2-0

Glossary R PART EFFECTIVITYADDED/REVISED/DELETED

CHAPTER 2

Section 2-1

Subject 2-1-0

General Aircraft Characteristics Data R PART EFFECTIVITYADDED/REVISED/DELETED

Section 2-2

Subject 2-2-0

General Aircraft Dimensions R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE General Aircraft Dimensions R

FIGURE General Aircraft Dimensions N ILLUSTRATION ADDED

Section 2-3

Subject 2-3-0

Ground Clearances R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Clearances R






HIGHLIGHTSPage 1

Jun 01/16


LOCATIONS CHGCODE


FIGURE Ground Clearances R ILLUSTRATION REVISED


FIGURE Ground Clearances N ILLUSTRATION ADDED








Section 2-4

Subject 2-4-0

Interior Arrangements - Plan View R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Standard Configuration R

FIGURE Standard Configuration N ILLUSTRATION ADDED

Section 2-5

Subject 2-5-0

Interior Arrangements - Cross Section R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Typical Configuration R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Section 2-6

Subject 2-6-0

Cargo Compartments R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Cargo Compartments R

FIGURE Cargo Compartments N ILLUSTRATION ADDED

Section 2-7

Subject 2-7-0

Door Clearances and Location R PART EFFECTIVITYADDED/REVISED/DELETED

HIGHLIGHTSPage 2

Jun 01/16


LOCATIONS CHGCODE


FIGURE Door Identification and Location R

FIGURE Door Identification and Location N ILLUSTRATION ADDED

FIGURE Forward Passenger/Crew Doors R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Aft Passenger/Crew Doors R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Forward Cargo CompartmentDoor

R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Aft Cargo Compartment Door R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Bulk Cargo Compartment Door R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Nose Landing Gear Doors R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Main Landing Gear Doors N ILLUSTRATION ADDED

Section 2-8

Subject 2-8-0

Escape Slides R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Escape Slides R

FIGURE Escape Slides N ILLUSTRATION ADDED

Section 2-10

Subject 2-10-0

Exterior Lighting R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Exterior Lighting R



HIGHLIGHTSPage 3

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LOCATIONS CHGCODE



FIGURE Exterior Lighting N ILLUSTRATION ADDED





Section 2-11

Subject 2-11-0

Antennas and Probes Location R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Antennas and Probes Location R

FIGURE Antennas and Probes Location N ILLUSTRATION ADDED

Section 2-12

Subject 2-12-0

Engine and Nacelle R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Engine and Nacelle R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 2-12-1 R

Auxiliary Power Unit R DESCRIPTION TITLE UPDATED

FIGURE Auxiliary Power Unit R ILLUSTRATION REVISED

Section 2-13

Subject 2-13-0 R

Leveling, Symmetry and Alignment R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Location of Leveling Points N ILLUSTRATION ADDED

Section 2-14

Subject 2-14-1

Jacking for Maintenance R PART EFFECTIVITYADDED/REVISED/DELETED

HIGHLIGHTSPage 4

Jun 01/16


LOCATIONS CHGCODE


FIGURE Jacking Points Location N ILLUSTRATION ADDED

FIGURE Jacking Points Location N ILLUSTRATION ADDED

FIGURE Jacking Dimensions N ILLUSTRATION ADDED

FIGURE Jacking Dimensions N ILLUSTRATION ADDED

FIGURE Forward Jacking Point N ILLUSTRATION ADDED

FIGURE Wing Jacking Point N ILLUSTRATION ADDED

FIGURE Auxiliary Jacking Point - Safety N ILLUSTRATION ADDED

CHAPTER 3 R

Section 3-1

Subject 3-1-0

General Information R PART EFFECTIVITYADDED/REVISED/DELETED

Section 3-2 N

Subject 3-2-0 N

Payload/Range - ISA Conditions N

FIGURE Payload/Range - ISA Conditions N ILLUSTRATION ADDED

FIGURE Payload/Range - ISA Conditions N ILLUSTRATION ADDED

CHAPTER 4 R

Section 4-1 N

Subject 4-1-0 N

General Information N

Section 4-4

Subject 4-4-0

Visibility from Cockpit in Static Position R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Visibility from Cockpit in StaticPosition


Section 4-5

Subject 4-5-0

HIGHLIGHTSPage 5

Jun 01/16


LOCATIONS CHGCODE


Introduction R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 4-5-1

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

FIGURE 90˚ Turn - Runway to Taxiway N ILLUSTRATION ADDED

Subject 4-5-2

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

FIGURE 135˚ Turn - Runway to Taxiway N ILLUSTRATION ADDED

Subject 4-5-3

180˚ Turn on a Runway R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE 180˚ Turn on a Runway N ILLUSTRATION ADDED

Subject 4-5-4

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

FIGURE 90˚ Turn - Taxiway to Taxiway R

FIGURE 90˚ Turn - Taxiway to Taxiway N ILLUSTRATION ADDED

Subject 4-5-5

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

FIGURE 135˚ Turn - Taxiway to Taxiway R

FIGURE 135˚ Turn - Taxiway to Taxiway N ILLUSTRATION ADDED

Section 4-6

Subject 4-6-0 R

Runway Holding Bay R DESCRIPTION TITLE UPDATED

FIGURE Runway Holding Bay R ILLUSTRATION REVISED

Section 4-7

Subject 4-7-0

Minimum Line-Up Distance Corrections R PART EFFECTIVITYADDED/REVISED/DELETED

HIGHLIGHTSPage 6

Jun 01/16


LOCATIONS CHGCODE


FIGURE 90˚ Turn on Runway Entry R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE 180˚ Turn on Runway Turn Pad R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE 180˚ Turn on Runway Width R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Section 4-8

Subject 4-8-0

Aircraft Mooring R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Aircraft Mooring R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

CHAPTER 5

Section 5-1

Subject 5-1-0

Aircraft Servicing Arrangements R PART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-1-1

Typical Ramp Layout (Open Apron) R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Typical Ramp Layout (OpenApron)

R

FIGURE Typical Ramp Layout (OpenApron)

N ILLUSTRATION ADDED

Subject 5-1-2

Typical Ramp Layout (Gate) R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Typical Ramp Layout (Gate) R

FIGURE Typical Ramp Layout (Gate) N ILLUSTRATION ADDED

HIGHLIGHTSPage 7

Jun 01/16


LOCATIONS CHGCODE


Section 5-2

Subject 5-2-0

Terminal Operations - Full Servicing TurnRound Time

R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Full Servicing Turn Round TimeChart

R

FIGURE Full Servicing Turn Round TimeChart


Section 5-3

Subject 5-3-0

Terminal Operations - Transit TurnRound Time


FIGURE Transit Turn Round Time Chart N ILLUSTRATION ADDED

Section 5-4

Subject 5-4-0

Ground Service Connections Layout R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Ground Service ConnectionsLayout

R

FIGURE Ground Service ConnectionsLayout


Subject 5-4-1

Grounding (Earthing) Points R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Grounding (Earthing) Point -NLG


FIGURE Grounding (Earthing) Point -MLG


Subject 5-4-2 R

Hydraulic Servicing R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

HIGHLIGHTSPage 8

Jun 01/16


LOCATIONS CHGCODE


FIGURE Green Ground Service Panel R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Yellow Ground Service Panel R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-3 R

Electrical Servicing R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Electrical Service Panel R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE RAT R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-4 R

Oxygen Servicing R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-5 R

Fuel Servicing R DESCRIPTION TITLE UPDATED

FIGURE Refuel/Defuel Control Panel R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Refuel/Defuel Couplings R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Overpressure Protectors andNACA Flame Arrestor

R ILLUSTRATION REVISED

Subject 5-4-6 R

Pneumatic Servicing R DESCRIPTION TITLE UPDATED

HIGHLIGHTSPage 9

Jun 01/16


LOCATIONS CHGCODE


FIGURE Low Pressure Ground Connectors R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE High Pressure GroundConnectors


Subject 5-4-7 R

Engine Oil Servicing R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Engine Oil Servicing R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

VFG Oil Servicing R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE VFG Oil Servicing R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Starter Oil Servicing R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Starter Oil Servicing R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

APU Oil Servicing R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE APU Oil Servicing R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-8 R

Potable Water Servicing R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Potable-Water Ground ServicePanel


HIGHLIGHTSPage 10

Jun 01/16


LOCATIONS CHGCODE


FIGURE Forward Drain Port R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Potable-Water Tanks Location R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-9 R

Waste Water Servicing R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Waste-Water Ground ServicePanel


FIGURE Waste Tanks Location R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Subject 5-4-10

Cargo Control Panels R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Forward Cargo Control Panels R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Aft Cargo Control Panels R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

Section 5-5

Subject 5-5-0

Engine Starting Pneumatic Requirements R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Example for Use of the Charts R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Engine Starting PneumaticRequirements

R

HIGHLIGHTSPage 11

Jun 01/16


LOCATIONS CHGCODE


FIGURE Engine Starting PneumaticRequirements


Section 5-6

Subject 5-6-0

Ground Pneumatic Power Requirements R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Ground Pneumatic PowerRequirements

R

FIGURE Ground Pneumatic PowerRequirements


Section 5-7

Subject 5-7-0

Preconditioned Airflow Requirements R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Preconditioned AirflowRequirements

R

FIGURE Preconditioned AirflowRequirements


Section 5-8

Subject 5-8-0

Ground Towing Requirements R PART EFFECTIVITYADDED/REVISED/DELETED

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

Section 5-9

Subject 5-9-0 R

De-Icing and External Cleaning R DESCRIPTION TITLE UPDATEDPART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

CHAPTER 6

Section 6-1

HIGHLIGHTSPage 12

Jun 01/16


LOCATIONS CHGCODE


Subject 6-1-0

Engine Exhaust Velocities andTemperatures


Subject 6-1-1 R

Engine Exhaust Velocities Contours -Ground Idle Power

R DESCRIPTION TITLE UPDATED

FIGURE Ground Idle Power - TRENTXWB-84 Engine




Subject 6-1-2 R

Engine Exhaust Temperatures Contours -Ground Idle Power



R



Subject 6-1-3 R

Engine Exhaust Velocities Contours -Breakaway Power


FIGURE Breakaway Power (11% MTOThrust) - TRENT XWB-84 Engine

R


R





Subject 6-1-4 R

Engine Exhaust Temperatures Contours -Breakaway Power



R

HIGHLIGHTSPage 13

Jun 01/16


LOCATIONS CHGCODE



R





Subject 6-1-5 R

Engine Exhaust Velocities Contours - MaxTake-Off Power


FIGURE Max Take-Off Power - TRENTXWB-84 Engine (Single)

R

FIGURE Max Take-Off Power - TRENTXWB-84 Engine (Twin)

R

FIGURE Max Take-Off Power - TRENTXWB-97 Engine (Single)


FIGURE Max Take-Off Power - TRENTXWB-97 Engine (Twin)


Subject 6-1-6 R

Engine Exhaust Temperatures Contours -Max Take-Off Power


FIGURE Max Take-Off Power - TRENTXWB-84 Engine

R



Section 6-3 R

Subject 6-3-0 N

Danger Areas of the Engines N

Subject 6-3-1

Danger Areas of the Engines - Ground IdlePower



R



HIGHLIGHTSPage 14

Jun 01/16


LOCATIONS CHGCODE


Subject 6-3-3

Danger Areas of the Engines - Max Take-Off Power



R



Section 6-4

Subject 6-4-0

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

FIGURE APU Exhaust Velocities andTemperatures


CHAPTER 7

Section 7-1

Subject 7-1-0

General Information R PART EFFECTIVITYADDED/REVISED/DELETED

Section 7-2

Subject 7-2-0

Landing Gear Footprint R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Landing Gear Footprint R

FIGURE Landing Gear Footprint N ILLUSTRATION ADDED

Section 7-3

Subject 7-3-0

Maximum Pavement Loads R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Maximum Pavement Loads R

FIGURE Maximum Pavement Loads N ILLUSTRATION ADDED

Section 7-4

Subject 7-4-0

HIGHLIGHTSPage 15

Jun 01/16


LOCATIONS CHGCODE


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

FIGURE Landing Gear Loading onPavement

R

FIGURE Landing Gear Loading onPavement


Section 7-5

Subject 7-5-0

Flexible Pavement Requirements - USArmy Corps of Engineers Design Method


FIGURE Flexible Pavement Requirements R

FIGURE Flexible Pavement Requirements N ILLUSTRATION ADDED

Section 7-6

Subject 7-6-0

Flexible Pavement Requirements - LCNConversion


Section 7-7

Subject 7-7-0

Rigid Pavement Requirements - PortlandCement Association Design Method


FIGURE Rigid Pavement Requirements R

FIGURE Rigid Pavement Requirements N ILLUSTRATION ADDED

Section 7-8

Subject 7-8-0

Rigid Pavement Requirements - LCNConversion


Section 7-9

Subject 7-9-0

ACN/PCN Reporting System - Flexibleand Rigid Pavements

R PART EFFECTIVITYADDED/REVISED/DELETEDNOTE AMENDED

FIGURE Aircraft Classification Number -WV005, MRW 250 900 kg, CG 40.86%


HIGHLIGHTSPage 16

Jun 01/16


LOCATIONS CHGCODE


FIGURE Aircraft Classification Number -WV001, MRW 275 900 kg, CG 33.2%


FIGURE ACN Table R

FIGURE Aircraft Classification Number -WV000, MRW 308 900 kg, CG 34%


FIGURE ACN Table N ILLUSTRATION ADDED

CHAPTER 8

Section 8-0

Subject 8-0-0

Scaled Drawings R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Scaled Drawings R

FIGURE Scaled Drawings N ILLUSTRATION ADDED

CHAPTER 10

Section 10-0

Subject 10-0-0

Aircraft Rescue and Fire Fighting R PART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Front Page R

FIGURE Front Page N ILLUSTRATION ADDED

FIGURE Highly Flammable and HazardousMaterials and Components

R

FIGURE Highly Flammable and HazardousMaterials and Components


FIGURE Crew Rest CompartmentsLocation


FIGURE Wheel/Brake Overheat N ILLUSTRATION ADDED

FIGURE Composite Materials Location N ILLUSTRATION ADDED

FIGURE Ground Lock Safety Devices N ILLUSTRATION ADDED

FIGURE Emergency Evacuation Devices R

FIGURE Emergency Evacuation Devices N ILLUSTRATION ADDED

HIGHLIGHTSPage 17

Jun 01/16


LOCATIONS CHGCODE


FIGURE Pax/Crew Doors and EmergencyExits


FIGURE Cockpit Emergency Exit R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE FWD and AFT Lower DeckCargo Doors


FIGURE Control Panels R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE APU Compartment Access R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Aircraft Ground Clearances R

FIGURE Aircraft Ground Clearances N ILLUSTRATION ADDED

FIGURE Structural Break-in Points R ILLUSTRATION REVISEDPART EFFECTIVITYADDED/REVISED/DELETED

FIGURE Batteries Location and Access N ILLUSTRATION ADDED

HIGHLIGHTSPage 18

Jun 01/16


LIST OF EFFECTIVE CONTENT

Revision No. 3 - Jun 01/16

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Introduction R Jun 01/16

Subject 1-2-0

Glossary R Jun 01/16

CHAPTER 2

Subject 2-1-0

General Aircraft Characteristics Data R Jun 01/16

Subject 2-2-0

General Aircraft Dimensions R Jun 01/16

FIGURE General Aircraft Dimensions R Jun 01/16

FIGURE General Aircraft Dimensions N Jun 01/16

Subject 2-3-0

Ground Clearances R Jun 01/16

FIGURE Ground Clearances R Jun 01/16








FIGURE Ground Clearances N Jun 01/16




L.E.C.Page 1

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE





Subject 2-4-0

Interior Arrangements - Plan View R Jun 01/16

FIGURE Standard Configuration R Jun 01/16

FIGURE Standard Configuration N Jun 01/16

Subject 2-5-0

Interior Arrangements - Cross Section R Jun 01/16

FIGURE Typical Configuration R Jun 01/16

Subject 2-6-0

Cargo Compartments R Jun 01/16

FIGURE Cargo Compartments R Jun 01/16

FIGURE Cargo Compartments N Jun 01/16

Subject 2-7-0

Door Clearances and Location R Jun 01/16

FIGURE Door Identification and Location R Jun 01/16

FIGURE Door Identification and Location N Jun 01/16

FIGURE Forward Passenger/Crew Doors R Jun 01/16

FIGURE Aft Passenger/Crew Doors R Jun 01/16

FIGURE Forward Cargo Compartment Door R Jun 01/16

FIGURE Aft Cargo Compartment Door R Jun 01/16

FIGURE Bulk Cargo Compartment Door R Jun 01/16

FIGURE Nose Landing Gear Doors R Jun 01/16

FIGURE Main Landing Gear Doors Apr 01/15

FIGURE Main Landing Gear Doors N Jun 01/16

Subject 2-8-0

Escape Slides R Jun 01/16

L.E.C.Page 2

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Escape Slides R Jun 01/16

FIGURE Escape Slides N Jun 01/16

Subject 2-9-0

Landing Gear Apr 01/15

FIGURE Main Landing Gear Apr 01/15

FIGURE Nose Landing Gear Apr 01/15

Subject 2-9-1

Landing Gear Maintenance Pits Apr 01/15

FIGURE Maintenance Pit Envelopes Apr 01/15

FIGURE NLG/MLG Extension/Retraction Pit Apr 01/15

FIGURE NLG/MLG Shock Absorber Removal Pit Apr 01/15

FIGURE NLG/MLG Removal Pit Apr 01/15

Subject 2-10-0

Exterior Lighting R Jun 01/16

FIGURE Exterior Lighting R Jun 01/16

FIGURE Exterior Lighting Jun 01/13




FIGURE Exterior Lighting N Jun 01/16





Subject 2-11-0

Antennas and Probes Location R Jun 01/16

FIGURE Antennas and Probes Location R Jun 01/16

FIGURE Antennas and Probes Location N Jun 01/16

Subject 2-12-0

L.E.C.Page 3

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Engine and Nacelle R Jun 01/16

FIGURE Engine and Nacelle R Jun 01/16

Subject 2-12-1

Auxiliary Power Unit R Jun 01/16

FIGURE Auxiliary Power Unit R Jun 01/16

Subject 2-13-0

Leveling, Symmetry and Alignment R Jun 01/16

FIGURE Location of Leveling Points Jun 01/13

FIGURE Location of Leveling Points N Jun 01/16

Subject 2-14-1

Jacking for Maintenance R Jun 01/16

FIGURE Jacking Points Location N Jun 01/16

FIGURE Jacking Points Location N Jun 01/16

FIGURE Jacking Dimensions N Jun 01/16

FIGURE Jacking Dimensions N Jun 01/16

FIGURE Forward Jacking Point N Jun 01/16

FIGURE Wing Jacking Point N Jun 01/16

FIGURE Auxiliary Jacking Point - Safety N Jun 01/16

Subject 2-14-2

Jacking for wheel change Jun 01/13

FIGURE Nose Landing Gear Jacking Point Heights Jun 01/13

FIGURE Main Landing Gear Jacking Point Heights Jun 01/13

CHAPTER 3

Subject 3-1-0

General Information R Jun 01/16

Subject 3-2-0

Payload/Range - ISA Conditions N Jun 01/16

FIGURE Payload/Range - ISA Conditions N Jun 01/16

FIGURE Payload/Range - ISA Conditions N Jun 01/16

L.E.C.Page 4

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Subject 3-3-0

Take-Off Weight Limitation Apr 01/15

FIGURE ISA Conditions Apr 01/15

FIGURE ISA + 15 ˚C (+59 ˚F) Conditions Apr 01/15

Subject 3-4-0

Landing Field Length Apr 01/15

FIGURE Landing Field Length Apr 01/15

Subject 3-5-0

Final Approach Speed Apr 01/15

CHAPTER 4

Subject 4-1-0

General Information N Jun 01/16

Subject 4-2-0

Turning Radii Jun 01/13

FIGURE Turning Radii Jun 01/13

Subject 4-3-0

Minimum Turning Radii Jun 01/13

FIGURE Minimum Turning Radii Jun 01/13

Subject 4-4-0

Visibility from Cockpit in Static Position R Jun 01/16

FIGURE Visibility from Cockpit in Static Position R Jun 01/16

Subject 4-5-0

Introduction R Jun 01/16

Subject 4-5-1

90˚ Turn - Runway to Taxiway R Jun 01/16

FIGURE 90˚ Turn - Runway to Taxiway Jun 01/13

FIGURE 90˚ Turn - Runway to Taxiway N Jun 01/16

Subject 4-5-2

135˚ Turn - Runway to Taxiway R Jun 01/16

L.E.C.Page 5

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE 135˚ Turn - Runway to Taxiway Jun 01/13

FIGURE 135˚ Turn - Runway to Taxiway N Jun 01/16

Subject 4-5-3

180˚ Turn on a Runway R Jun 01/16

FIGURE 180˚ Turn on a Runway Jun 01/13

FIGURE 180˚ Turn on a Runway N Jun 01/16

Subject 4-5-4

90˚ Turn - Taxiway to Taxiway R Jun 01/16

FIGURE 90˚ Turn - Taxiway to Taxiway R Jun 01/16

FIGURE 90˚ Turn - Taxiway to Taxiway N Jun 01/16

Subject 4-5-5

135˚ Turn - Taxiway to Taxiway R Jun 01/16

FIGURE 135˚ Turn - Taxiway to Taxiway R Jun 01/16

FIGURE 135˚ Turn - Taxiway to Taxiway N Jun 01/16

Subject 4-6-0

Runway Holding Bay R Jun 01/16

FIGURE Runway Holding Bay R Jun 01/16

Subject 4-7-0

Minimum Line-Up Distance Corrections R Jun 01/16

FIGURE 90˚ Turn on Runway Entry R Jun 01/16

FIGURE 180˚ Turn on Runway Turn Pad R Jun 01/16

FIGURE 180˚ Turn on Runway Width R Jun 01/16

Subject 4-8-0

Aircraft Mooring R Jun 01/16

FIGURE Aircraft Mooring R Jun 01/16

CHAPTER 5

Subject 5-1-0

Aircraft Servicing Arrangements R Jun 01/16

Subject 5-1-1

L.E.C.Page 6

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Typical Ramp Layout (Open Apron) R Jun 01/16

FIGURE Typical Ramp Layout (Open Apron) R Jun 01/16

FIGURE Typical Ramp Layout (Open Apron) N Jun 01/16

Subject 5-1-2

Typical Ramp Layout (Gate) R Jun 01/16

FIGURE Typical Ramp Layout (Gate) R Jun 01/16

FIGURE Typical Ramp Layout (Gate) N Jun 01/16

Subject 5-2-0

Terminal Operations - Full Servicing Turn Round Time R Jun 01/16

FIGURE Full Servicing Turn Round Time Chart R Jun 01/16

FIGURE Full Servicing Turn Round Time Chart N Jun 01/16

Subject 5-3-0

Terminal Operations - Transit Turn Round Time R Jun 01/16

FIGURE Transit Turn Round Time Chart Sep 01/14

FIGURE Transit Turn Round Time Chart N Jun 01/16

Subject 5-4-0

Ground Service Connections Layout R Jun 01/16

FIGURE Ground Service Connections Layout R Jun 01/16

FIGURE Ground Service Connections Layout N Jun 01/16

Subject 5-4-1

Grounding (Earthing) Points R Jun 01/16

FIGURE Grounding (Earthing) Point - NLG R Jun 01/16

FIGURE Grounding (Earthing) Point - MLG Sep 01/14

FIGURE Grounding (Earthing) Point - MLG N Jun 01/16

Subject 5-4-2

Hydraulic Servicing R Jun 01/16

FIGURE Green Ground Service Panel R Jun 01/16

FIGURE Yellow Ground Service Panel R Jun 01/16

Subject 5-4-3

L.E.C.Page 7

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Electrical Servicing R Jun 01/16

FIGURE Electrical Service Panel R Jun 01/16

FIGURE RAT R Jun 01/16

Subject 5-4-4

Oxygen Servicing R Jun 01/16

FIGURE Oxygen System Jun 01/13

FIGURE Crew Oxygen Storage - Location Sep 01/14

Subject 5-4-5

Fuel Servicing R Jun 01/16

FIGURE Refuel/Defuel Control Panel R Jun 01/16

FIGURE Refuel/Defuel Couplings R Jun 01/16

FIGURE Overpressure Protectors and NACA Flame Arrestor R Jun 01/16

Subject 5-4-6

Pneumatic Servicing R Jun 01/16

FIGURE Low Pressure Ground Connectors R Jun 01/16

FIGURE High Pressure Ground Connectors R Jun 01/16

Subject 5-4-7

Engine Oil Servicing R Jun 01/16

FIGURE Engine Oil Servicing R Jun 01/16

VFG Oil Servicing R Jun 01/16

FIGURE VFG Oil Servicing R Jun 01/16

Starter Oil Servicing R Jun 01/16

FIGURE Starter Oil Servicing R Jun 01/16

APU Oil Servicing R Jun 01/16

FIGURE APU Oil Servicing R Jun 01/16

Subject 5-4-8

Potable Water Servicing R Jun 01/16

FIGURE Potable-Water Ground Service Panel R Jun 01/16

FIGURE Forward Drain Port R Jun 01/16

L.E.C.Page 8

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Potable-Water Tanks Location R Jun 01/16

Subject 5-4-9

Waste Water Servicing R Jun 01/16

FIGURE Waste-Water Ground Service Panel R Jun 01/16

FIGURE Waste Tanks Location R Jun 01/16

Subject 5-4-10

Cargo Control Panels R Jun 01/16

FIGURE Forward Cargo Control Panels R Jun 01/16

FIGURE Aft Cargo Control Panels R Jun 01/16

Subject 5-5-0

Engine Starting Pneumatic Requirements R Jun 01/16

FIGURE Example for Use of the Charts R Jun 01/16

FIGURE Engine Starting Pneumatic Requirements R Jun 01/16

FIGURE Engine Starting Pneumatic Requirements N Jun 01/16

Subject 5-6-0

Ground Pneumatic Power Requirements R Jun 01/16

FIGURE Ground Pneumatic Power Requirements R Jun 01/16

FIGURE Ground Pneumatic Power Requirements N Jun 01/16

Subject 5-7-0

Preconditioned Airflow Requirements R Jun 01/16

FIGURE Preconditioned Airflow Requirements R Jun 01/16

FIGURE Preconditioned Airflow Requirements N Jun 01/16

Subject 5-8-0

Ground Towing Requirements R Jun 01/16

FIGURE Ground Towing Requirements R Jun 01/16

Subject 5-9-0

De-Icing and External Cleaning R Jun 01/16

CHAPTER 6

Subject 6-1-0

L.E.C.Page 9

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Engine Exhaust Velocities and Temperatures R Jun 01/16

Subject 6-1-1

Engine Exhaust Velocities Contours - Ground Idle Power R Jun 01/16

FIGURE Ground Idle Power - TRENT XWB-84 Engine R Jun 01/16

FIGURE Ground Idle Power - TRENT XWB-97 Engine N Jun 01/16

Subject 6-1-2

Engine Exhaust Temperatures Contours - Ground Idle Power R Jun 01/16



Subject 6-1-3

Engine Exhaust Velocities Contours - Breakaway Power R Jun 01/16

FIGURE Breakaway Power (11% MTO Thrust) - TRENT XWB-84Engine

R Jun 01/16


R Jun 01/16


N Jun 01/16


N Jun 01/16

Subject 6-1-4

Engine Exhaust Temperatures Contours - Breakaway Power R Jun 01/16


R Jun 01/16


R Jun 01/16


N Jun 01/16


N Jun 01/16

Subject 6-1-5

Engine Exhaust Velocities Contours - Max Take-Off Power R Jun 01/16

L.E.C.Page 10

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Max Take-Off Power - TRENT XWB-84 Engine (Single) R Jun 01/16

FIGURE Max Take-Off Power - TRENT XWB-84 Engine (Twin) R Jun 01/16

FIGURE Max Take-Off Power - TRENT XWB-97 Engine (Single) N Jun 01/16

FIGURE Max Take-Off Power - TRENT XWB-97 Engine (Twin) N Jun 01/16

Subject 6-1-6

Engine Exhaust Temperatures Contours - Max Take-Off Power R Jun 01/16

FIGURE Max Take-Off Power - TRENT XWB-84 Engine R Jun 01/16

FIGURE Max Take-Off Power - TRENT XWB-97 Engine N Jun 01/16

Subject 6-3-0

Danger Areas of the Engines N Jun 01/16

Subject 6-3-1

Danger Areas of the Engines - Ground Idle Power R Jun 01/16



Subject 6-3-3

Danger Areas of the Engines - Max Take-Off Power R Jun 01/16

FIGURE Max Take-Off Power - TRENT XWB-84 Engine R Jun 01/16

FIGURE Max Take-Off Power - TRENT XWB-97 Engine N Jun 01/16

Subject 6-4-0

APU Exhaust Velocities and Temperatures R Jun 01/16

FIGURE APU Exhaust Velocities and Temperatures R Jun 01/16

CHAPTER 7

Subject 7-1-0

General Information R Jun 01/16

Subject 7-2-0

Landing Gear Footprint R Jun 01/16

FIGURE Landing Gear Footprint R Jun 01/16

FIGURE Landing Gear Footprint N Jun 01/16

Subject 7-3-0

L.E.C.Page 11

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

Maximum Pavement Loads R Jun 01/16

FIGURE Maximum Pavement Loads R Jun 01/16

FIGURE Maximum Pavement Loads N Jun 01/16

Subject 7-4-0

Landing Gear Loading on Pavement R Jun 01/16

FIGURE Landing Gear Loading on Pavement R Jun 01/16

FIGURE Landing Gear Loading on Pavement Apr 01/15

FIGURE Landing Gear Loading on Pavement N Jun 01/16

Subject 7-5-0

Flexible Pavement Requirements - US Army Corps of EngineersDesign Method

R Jun 01/16

FIGURE Flexible Pavement Requirements R Jun 01/16

FIGURE Flexible Pavement Requirements Apr 01/15

FIGURE Flexible Pavement Requirements N Jun 01/16

Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion R Jun 01/16

Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Jun 01/16

FIGURE Rigid Pavement Requirements R Jun 01/16

FIGURE Rigid Pavement Requirements Apr 01/15

FIGURE Rigid Pavement Requirements N Jun 01/16

Subject 7-8-0

Rigid Pavement Requirements - LCN Conversion R Jun 01/16

Subject 7-9-0

ACN/PCN Reporting System - Flexible and Rigid Pavements R Jun 01/16

FIGURE Aircraft Classification Number - WV005, MRW 250 900 kg,CG 40.86%

R Jun 01/16

FIGURE Aircraft Classification Number - WV001, MRW 275 900 kg,CG 33.2%

R Jun 01/16

L.E.C.Page 12

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE ACN Table R Jun 01/16

FIGURE Aircraft Classification Number - WV000, MRW 308 900 kg,CG 34%

N Jun 01/16

FIGURE ACN Table N Jun 01/16

CHAPTER 8

Subject 8-0-0

Scaled Drawings R Jun 01/16

FIGURE Scaled Drawings R Jun 01/16

FIGURE Scaled Drawings N Jun 01/16

CHAPTER 10

Subject 10-0-0

Aircraft Rescue and Fire Fighting R Jun 01/16

FIGURE Front Page R Jun 01/16

FIGURE Front Page N Jun 01/16

FIGURE Highly Flammable and Hazardous Materials and Components R Jun 01/16

FIGURE Highly Flammable and Hazardous Materials and Components N Jun 01/16

FIGURE Crew Rest Compartments Location Jun 01/13

FIGURE Crew Rest Compartments Location N Jun 01/16

FIGURE Wheel/Brake Overheat Jun 01/13

FIGURE Wheel/Brake Overheat N Jun 01/16

FIGURE Composite Materials Location Jun 01/13

FIGURE Composite Materials Location N Jun 01/16

FIGURE Ground Lock Safety Devices Jun 01/13

FIGURE Ground Lock Safety Devices N Jun 01/16

FIGURE Emergency Evacuation Devices R Jun 01/16

FIGURE Emergency Evacuation Devices N Jun 01/16

FIGURE Pax/Crew Doors and Emergency Exits R Jun 01/16

FIGURE Cockpit Emergency Exit R Jun 01/16

FIGURE FWD and AFT Lower Deck Cargo Doors R Jun 01/16

L.E.C.Page 13

Jun 01/16


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Control Panels R Jun 01/16

FIGURE APU Compartment Access R Jun 01/16

FIGURE Aircraft Ground Clearances R Jun 01/16

FIGURE Aircraft Ground Clearances N Jun 01/16

FIGURE Structural Break-in Points R Jun 01/16

FIGURE Batteries Location and Access Apr 01/15

FIGURE Batteries Location and Access N Jun 01/16

L.E.C.Page 14

Jun 01/16


TABLE OF CONTENTS

1 SCOPE

1-1-0 Introduction

1-2-0 Glossary

2 AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics Data

2-2-0 General Aircraft Dimensions

2-3-0 Ground Clearances

2-4-0 Interior Arrangements - Plan View

2-5-0 Interior Arrangements - Cross Section

2-6-0 Cargo Compartments

2-7-0 Door Clearances and Location

2-8-0 Escape Slides

2-9-0 Landing Gear

2-9-1 Landing Gear Maintenance Pits

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 Leveling, Symmetry and Alignment

2-14-1 Jacking for Maintenance

2-14-2 Jacking of the Landing Gear

3 AIRCRAFT PERFORMANCE

3-1-0 General Information

3-2-0 Payload/Range - ISA Conditions

3-3-0 Take-Off Weight Limitation

3-4-0 Landing Field Length

3-5-0 Final Approach Speed

4 GROUND MANEUVERING


4-2-0 Turning Radii

4-3-0 Minimum Turning Radii

4-4-0 Visibility from Cockpit in Static Position

T.O.C.Page 1

Jun 01/16


4-5-0 Runway and Taxiway Turn Paths

4-5-1 90˚ Turn - Runway to Taxiway


4-5-3 180˚ Turn on a Runway

4-5-4 90˚ Turn - Taxiway to Taxiway


4-6-0 Runway Holding Bay

4-7-0 Minimum Line-Up Distance Corrections

4-8-0 Aircraft Mooring

5 TERMINAL SERVICING

5-1-0 Aircraft Servicing Arrangements

5-1-1 Typical Ramp Layout (Open Apron)

5-1-2 Typical Ramp Layout (Gate)

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

5-3-0 Terminal Operations - Transit Turn Round Time

5-4-0 Ground Service Connections Layout

5-4-1 Grounding (Earthing) Points

5-4-2 Hydraulic Servicing

5-4-3 Electrical Servicing

5-4-4 Oxygen Servicing

5-4-5 Fuel Servicing

5-4-6 Pneumatic Servicing

5-4-7 Oil Servicing

5-4-8 Potable Water Servicing

5-4-9 Waste Water Servicing

5-4-10 Cargo Control Panels

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

T.O.C.Page 2

Jun 01/16


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

6-1-5 Engine Exhaust Velocities Contours - Max Take-Off Power

6-1-6 Engine Exhaust Temperatures Contours - Max Take-Off Power

6-3-0 Danger Areas of the Engines

6-3-1 Danger Areas of the Engines - Ground Idle Power

6-3-3 Danger Areas of the Engines - Max Take-Off Power

6-4-0 APU Exhaust Velocities and Temperatures

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 - US Army Corps of Engineers Design Method

7-6-0 Flexible Pavement Requirements - LCN Conversion

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

7-8-0 Rigid Pavement Requirements - LCN Conversion

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

8 SCALED DRAWINGS

8-0-0 Scaled Drawings

10 AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 Aircraft Rescue and Fire Fighting

T.O.C.Page 3

Jun 01/16


SCOPE

1-1-0 Introduction

**ON A/C A350-1000 A350-900

Introduction

1. General

The A350 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A350-900 and A350-1000 series aircraft to provide necessary data to airportoperators, airlines and Maintenance/Repair Organizations (MRO) for airport and maintenancefacilities planning.

The data given in this issue of the A350 AIRCRAFT CHARACTERISTICS - AIRPORT ANDMAINTENANCE PLANNING (AC) can be subject to change pending completion of the design andflight test phase. It is given for guidance only and does not constitute a contractual commitment.

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

The A350 XWB is a new family of mid-size medium to long range new technology aircraft that willdeliver superior fuel efficiency, passenger comfort, environmental characteristics and economics, witha global market coverage.The aircraft is designed to offer multiple payload capabilities with a consistant range ability acrossthe family.The A350 XWB is equipped with two Rolls-Royce Trent XWB engines.This engine will incorporate the most advanced technologies to provide the best aircraft performance,maintainability, lowest fuel consumption and environmental impact.Reflecting market needs, the A350 XWB offers a high level of cargo hold capability and flexibility.Two wide cargo doors and a Cargo Loading System (CLS) compatible with most lower deck cargocontainers and pallet standards, allowing interlining operations, ease the loading.The A350 XWB provides easy and cost effective ground handling minimizing aircraft turn round time.The innovative A350 XWB design increases planning flexibility to perform maintenance during theaircraft scheduled downtime.

Correspondence concerning this publication should be directed to:

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

1-1-0Page 1

Jun 01/16


1-2-0 Glossary

**ON A/C A350-1000 A350-900

Glossary

1. List of Abbreviations

A/C Aircraft

ACN Aircraft Classification NumberAMM Aircraft Maintenance ManualAPU Auxiliary Power Unit

B/C Business Class

CBR California Bearing Ratio

CC Cargo Compartment

CG Center of Gravity

CLS Cargo Loading System

E Young’s Modulus

ESWL Equivalent Single Wheel Load

FAA Federal Aviation AdministrationFDL Fuselage Datum Line

FR FrameFSTE Full Size Trolley Equivalent

FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment

ICAO International Civil Aviation Organisation

ISA International Standard Atmosphere

L Radius of relative stiffnessLCN Load Classification NumberLD Load DeviceLD Lower DeckLH Left HandLP Low PressureLPS Last Pax Seating

MAC Mean Aerodynamic Chord

MAX MaximumMIN MinimumMLG Main Landing Gear

NLG Nose Landing Gear

OAT Outside Air Temperature

1-2-0Page 1

Jun 01/16


PAX Passenger

PBB Passenger Boarding Bridge

PCA Portland Cement AssociationPCN Pavement Classification NumberPRM Passenger with Reduced Mobility

RH Right Hand

ULD Unit Load DeviceUS United StatesVFG Variable Frequency Generator

WV Weight Variant

Y/C Economic Class

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

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

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

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

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

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

Water Volume:Maximum volume of cargo compartment.

Usable Fuel:Fuel available for aircraft propulsion.

1-2-0Page 2

Jun 01/16


AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics Data

**ON A/C A350-1000 A350-900

General Aircraft Characteristics Data

**ON A/C A350-900

1. The following table provides characteristics of A350--900 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000 WV001 WV002 WV003

Maximum TaxiWeight (MTW)Maximum RampWeight (MRW)

268 900 kg(592 824 lb)

275 900 kg(608 256 lb)

272 900 kg(601 642 lb)

268 900 kg(592 824 lb)

Maximum Take-OffWeight (MTOW)

268 000 kg(590 839 lb)

275 000 kg(606 272 lb)

272 000 kg(599 658 lb)

268 000 kg(590 839 lb)

Maximum LandingWeight (MLW)

205 000 kg(451 948 lb)

207 000 kg(456 357 lb)

207 000 kg(456 357 lb)

207 000 kg(456 357 lb)

Maximum Zero FuelWeight (MZFW)

192 000 kg(423 288 lb)

195 700 kg(431 445 lb)

194 000 kg(427 697 lb)

195 700 kg(431 445 lb)

Aircraft CharacteristicsWV004 WV005 WV006

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

260 900 kg(575 187 lb)

250 900 kg(553 140 lb)

272 900 kg(601 642 lb)

Maximum Take-OffWeight (MTOW)

260 000 kg(573 202 lb)

250 000 kg(551 156 lb)

272 000 kg(599 658 lb)

Maximum LandingWeight (MLW)

207 000 kg(456 357 lb)

205 000 kg(451 948 lb)

207 000 kg(456 357 lb)

Maximum Zero FuelWeight (MZFW)

195 700 kg(431 445 lb)

192 000 kg(423 288 lb)

195 700 kg(431 445 lb)

2-1-0Page 1

Jun 01/16


2. The following table provides characteristics of A350--900 Models, these data are common to eachWeight Variant:

Aircraft Characteristics

Standard Seating Capacity 315 (2 class)

138 000 L(36 456 USgal)Usable Fuel Capacity

(density = 0.785 kg/l) 108 330 kg(238 827 lb)

Pressurized Fuselage Volume971 m3(34 291 ft.3)

Cockpit Volume8.23 m3(291 ft.3)

Passenger Compartment Volume473.7 m3(16 729 ft.3)

Usable Volume, FWD CC(Based on LD3)

86.7 m3(3 062 ft.3)

Usable Volume, AFT CC(Based on LD3)

69.3 m3(2 447 ft.3)

Usable Volume, Bulk CC11.4 m3(403 ft.3)

Water Volume, FWD CC113.4 m3(4 005 ft.3)

Water Volume, AFT CC95.8 m3(3 383 ft.3)

Water Volume, Bulk CC13.4 m3(473 ft.3)

**ON A/C A350-1000

3. The following table provides characteristics of A350--1000 Models, these data are specific to eachWeight Variant:

Aircraft CharacteristicsWV000

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

308 900 kg(681 008 lb)

Maximum Take-Off Weight (MTOW)308 000 kg(679 024 lb)

Maximum Landing Weight (MLW)233 000 kg(513 677 lb)

2-1-0Page 2

Jun 01/16


Aircraft CharacteristicsWV000

Maximum Zero Fuel Weight (MZFW)220 000 kg(485 017 lb)

4. The following table provides characteristics of A350--1000 Models, these data are common to eachWeight Variant:

Aircraft Characteristics

Standard Seating Capacity 440 (2 class)

156 000 L(41 212 USgal)Usable Fuel Capacity

(density = 0.785 kg/l) 122 460 kg(269 978 lb)

Pressurized Fuselage Volume

Cockpit Volume8.23 m3(291 ft.3)

Passenger Compartment Volume

Usable Volume, FWD CC(Based on LD3)

104 m3(3 673 ft.3)

Usable Volume, AFT CC(Based on LD3)

86.7 m3(3 062 ft.3)

Usable Volume, Bulk CC11.4 m3(403 ft.3)

Water Volume, FWD CC138 m3

(4 873 ft.3)

Water Volume, AFT CC113 m3

(3 991 ft.3)

Water Volume, Bulk CC13.4 m3(473 ft.3)

2-1-0Page 3

Jun 01/16


2-2-0 General Aircraft Dimensions

**ON A/C A350-1000 A350-900

General Aircraft Dimensions

1. This section provides general aircraft dimensions.

2-2-0Page 1

Jun 01/16


**ON A/C A350-900

3.04 m(9.97 ft)

10.60 m(34.78 ft)

4.63 m(15.19 ft)

1.74 m(5.71 ft)

0.75 m(2.46 ft)

12.87 m(42.22 ft)

6.09 m(19.98 ft)

65.26 m(214.11 ft)

64.75 m(212.43 ft)

18.79 m(61.65 ft)

28.66 m(94.03 ft)

66.61 m(218.54 ft)

9.42 m(30.91 ft)

NOTE:RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.

7.79 m(25.56 ft)

9.09 m(29.82 ft)

P_AC_020200_1_0010001_01_03

General Aircraft Dimensions(Sheet 1 of 2)

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

2-2-0Page 2

Jun 01/16


**ON A/C A350-900

2.46 m(8.07 ft)

7.86 m(25.79 ft)

9.62 m(31.56 ft)

21.97 m(72.08 ft)

46.68 m(153.15 ft)

5.18 m(16.99 ft)

10.50 m(34.45 ft)

12.75 m(41.83 ft)

17.02 m(55.84 ft)

5.96 m(19.55 ft)


13.47 m(44.19 ft)

6.21 m(20.37 ft)

2.88 m(9.45 ft)

66.80 m(219.16 ft)

P_AC_020200_1_0010001_02_03


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

2-2-0Page 3

Jun 01/16


**ON A/C A350-1000


CENTRE AXLE02

FWD & AFT AXLE01

3.04 m(9.97 ft)

10.73 m(35.20 ft)

4.63 m(15.19 ft)

12.84 m(42.13 ft)

6.09 m(19.98 ft)

72.25 m(237.04 ft)

64.75 m(212.43 ft)

18.79 m(61.65 ft)

32.48 m(106.56 ft)

73.59 m(241.44 ft)

9.42 m(30.91 ft)

7.79 m(25.56 ft)

9.09 m(29.82 ft)

1.40 m (4.59 ft)

1.47 m (4.82 ft)

0.75 m(2.46 ft)

01

02

P_AC_020200_1_0020003_01_00


FIGURE-2-2-0-991-002-C01

2-2-0Page 4

Jun 01/16


**ON A/C A350-1000

73.79 m(242.09 ft)

2.46 m(8.07 ft)

9.62 m

25.78 m(84.58 ft)

50.58 m(165.94 ft)

5.27 m(17.29 ft)

12.75 m

17.02 m(55.84 ft)

5.96 m(19.55 ft)


13.47 m(44.19 ft)

6.21 m(20.37 ft)

2.88 m(9.45 ft)

(41.83 ft)

(31.56 ft)

7.86 m(25.79 ft)

10.50 m(34.45 ft)

P_AC_020200_1_0020003_02_00


FIGURE-2-2-0-991-002-C01

2-2-0Page 5

Jun 01/16


2-3-0 Ground Clearances

**ON A/C A350-1000 A350-900

Ground Clearances

1. This section provides the heights of various points of the aircraft, above the ground, for differentaircraft configurations.Dimensions in the tables are approximate and will vary with tire type, weight and balance and otherspecial conditions.

The dimensions are given for:- A light weight, for an A/C in maintenance configuration with a FWD CG and an AFT CG,- An aircraft at MRW with a FWD CG and an AFT CG,- Aircraft on jacks, FDL at 6.50 m (21.33 ft.).

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

2-3-0Page 1

Jun 01/16


**ON A/C A350-900

m ft m ft m ft m ft

AC JACKEDFDL = 6.5 m

(21.33 ft)

ft16.5416.75

10.857.888.4627.8827.77

6.42

5.08

3.27

8.44

1.96

5.13

2.442.558.53

16.6816.82

10.747.998.3827.9827.68

6.42

5.135.22

3.482.502.748.608.64

2.10

9.00

16.8417.13

8.20

28.2128.33

6.88 2.10

2.63

5.365.34

3.312.70

8.788.49

8.62

17.6017.52

10.878.85

28.8027.87

6.90

6.376.37

4.41

3.713.71

9.809.58

3.16

20.9120.91

14.4712.1812.1832.1431.45

10.37

11.43

17.08 5.19 17.04 5.36 17.58 5.30 17.39 6.37 20.91

23.0525.4421.9856.63

1.97

7.007.696.6417.20

0.61

22.9825.2321.7856.42

2.00

7.197.966.91

17.47

0.73

23.5826.1322.6657.31

2.39

7.097.646.59

17.14

0.79

23.2525.0521.6356.24

2.59

8.178.777.72

1.84

26.8028.7725.3459.96

6.02

18.27

8.4119.1112.9631.01

2.545.874.009.42

8.3519.2713.1430.92

2.725.904.039.62

8.9419.3713.2231.57

2.636.184.329.48

8.6320.2814.1831.11

3.717.185.32

10.57

12.1823.5517.4534.69

A/C CONFIGURATION

mD1D2

C3F1F2F3F4

BF2

2.58

5.045.11

3.312.40

8.508.46

1.96

D3 5.21

W2HTAPVT

7.027.756.70

17.26

0.60

BF3CP1RD1W1

2.565.823.959.45

2.48 0.77 2.51 0.88 2.89 0.95 3.11 6.541.99N1 0.76

23.7910.12

7.313.12

23.9810.22

7.333.18

24.0510.45

7.613.37

24.9711.06

8.594.39

28.1814.40

10.86 3.28 10.76 3.48 11.42 3.33 10.94 4.43 14.52

D5C1

7.253.08

C2 3.31

17.33 5.24 17.20 5.46 17.93 5.27 17.29 6.37 20.90D4 5.28

8.05 2.47 8.10 2.57 8.44 2.67 8.77 3.71 12.17BF1 2.45

140 000 kg (308 647 lb)

DOORS

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE

MRW

N1 WITHDRAIN MAST

FWD CG (26.2%) AFT CG (33.2%) FWD CG (20%) AFT CG (40%)

VT C2HT C1 F1BF1BF3 D5F2F4 BF2 F3

RD1CP1 D1 D2N1

D3 W2 W1C3 D4 AP

OF THE DOOR SILL AND FROM FLOOR LEVEL.

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

P_AC_020300_1_0010001_01_04

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

2-3-0Page 2

Jun 01/16


**ON A/C A350-900

NOTE:* DN − DROOP NOSE

A B C D E F G H J

m ft m ft m ftft11.2415.08

3.444.60

11.2815.09

3.554.73

11.6615.51

3.624.76

11.8815.62

15.17 4.63 15.18 4.76 15.61 4.79 15.70

DESCRIPTION

mAB

3.434.60

C 4.62

DN* INBDDN* OUTBDSLAT 1 INBD

LEADING EDGE SLATS EXTENDED

SLAT 1/2 16.41 5.00 16.41 5.14 5.15 16.89D 5.00 16.86SLAT 2/3 17.57 5.35 17.56 5.50 5.49 18.01E 5.36 18.04SLAT 3/4 18.70 5.69 18.67 5.85 5.82 19.08F 5.70 19.18SLAT 4/5 19.74 6.01 19.71 6.17 6.12 20.08G 6.02 20.24SLAT 5/6 20.73 6.31 20.69 6.47 6.41 21.02H 6.32 21.24

SLAT 6 OUTBD 21.85 6.64 21.79 6.82 6.73 22.08J 6.66 22.37

140 000 kg (308 647 lb)

FWD CG (20%) AFT CG (40%)AFT CG (33.2%)

MRW

FWD CG (26.2%)

P_AC_020300_1_0020001_01_01

Ground ClearancesLeading Edge Slats - ExtendedFIGURE-2-3-0-991-002-A01

2-3-0Page 3

Jun 01/16


**ON A/C A350-900

G F E D C B A


2.563.29

8.4010.79

2.723.45

8.9211.31

2.683.40

8.7911.17

13.45 4.09 13.41 4.25 13.94 4.20 13.79

DESCRIPTION

mAB

2.573.30

C 4.10

FLAP 1 INBDFLAP 1/2

FLAP 2 OUTBD

FLAPS EXTENDED

13.62 4.14 13.58 4.30 14.11 4.26 13.96D 4.15FLAP 3 INBD16.07 4.89 16.03 5.05 16.57 4.99 16.39E 4.90FLAP 3/417.85 5.42 17.80 5.60 18.36 5.52 18.12F 5.44FLAP 4/518.65 5.67 18.60 5.84 19.17 5.76 18.91G 5.69FLAP 5 OUTBD

MRW

FWD CG (26.2%) AFT CG (33.2%)

140 000 kg (308 647 lb)

FWD CG (20%) AFT CG (40%)

P_AC_020300_1_0030001_01_01

Ground ClearancesTrailing Edge Flaps - Extended

FIGURE-2-3-0-991-003-A01

2-3-0Page 4

Jun 01/16


**ON A/C A350-900

J


5.025.48

16.4717.99

5.175.64

16.9818.50

5.145.61

16.8818.40

19.51 5.94 19.48 6.09 19.99 6.06 19.88

DESCRIPTION

mAB

5.035.49

C 5.95

SPOILER 1 INBDSPOILER 1/2

SPOILER 2 OUTBD

SPOILERS EXTENDED

19.97 6.08 19.95 6.23 20.45 6.20 20.35D 6.09SPOILER 3 INBD20.77 6.32 20.74 6.48 21.26 6.44 21.13E 6.33SPOILER 3/421.46 6.53 21.42 6.69 21.95 6.64 21.80F 6.54SPOILER 4/522.08 6.72 22.04 6.88 22.58 6.83 22.40G 6.73SPOILER 5/622.66 6.89 22.62 7.06 23.16 7.00 22.96H 6.91SPOILER 6/723.23 7.07 23.19 7.24 23.74 7.17 23.52J 7.08SPOILER 7 OUTBD

MRW

FWD CG (26.2%) AFT CG (33.2%)

140 000 kg (308 647 lb)


H G F E D C B A

P_AC_020300_1_0040001_01_01

Ground ClearancesSpoilers - Extended

FIGURE-2-3-0-991-004-A01

2-3-0Page 5

Jun 01/16


**ON A/C A350-900


5.936.34

19.4620.81

6.106.52

20.0321.40

6.036.43

19.7721.09

20.83 6.33 20.77 6.51 21.36 6.42 21.05

DESCRIPTION

mAB

5.956.36

C 6.35

AILERON 1 INBDAILERON 1 OUTBDAILERON 2 INBD

AILERONS DOWN

AILERON 2 OUTBD 22.45 6.82 22.38 7.01 6.90 22.62D 6.84 22.99

140 000 kg (308 647 lb)


MRW

FWD CG (26.2%)

B ACD

P_AC_020300_1_0050001_01_01

Ground ClearancesAilerons - Down

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

2-3-0Page 6

Jun 01/16


**ON A/C A350-900


6.957.19

22.8023.58

7.127.37

23.3624.17

7.047.27

23.1123.86

23.68 7.20 23.61 7.38 24.20 7.28 23.90

DESCRIPTION

mAB

6.967.21

C 7.22


AILERONS UP

AILERON 2 OUTBD 24.59 7.47 24.51 7.66 7.55 24.76D 7.49 25.12

140 000 kg (308 647 lb)


MRW

FWD CG (26.2%)

B ACD

P_AC_020300_1_0060001_01_01

Ground ClearancesAilerons - Up

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

2-3-0Page 7

Jun 01/16


**ON A/C A350-900

B A


3.754.56

12.3014.95

3.904.71

12.8015.46

3.874.67

12.7115.34

17.08 5.19 17.04 5.36 17.58 5.30 17.40

DESCRIPTION

mAB

3.754.56

C 5.21

FLAP TRACK 1FLAP TRACK 2FLAP TRACK 3

FLAPS TRACKS RETRACTED

FWD CG (26.2%)

MRW

AFT CG (33.2%) FWD CG (20%)

140 000 kg (308 647 lb)

AFT CG (40%)

C

P_AC_020300_1_0070001_01_01

Ground ClearancesFlap Tracks - Retracted

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

2-3-0Page 8

Jun 01/16


**ON A/C A350-900

B A

m ft m ft m ftft9.38

11.072.853.36

9.3411.02

3.013.53

9.8711.57

2.963.47

9.7211.37

13.24 4.02 13.19 4.19 13.75 4.12 13.51

DESCRIPTION

mAB

2.863.37

C 4.04


FLAPS TRACKS EXTENDED

MRW

FWD CG (26.2%) AFT CG (33.2%)

140 000 kg (308 647 lb)


C

P_AC_020300_1_0080001_01_01

Ground ClearancesFlap Tracks - Extended

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

2-3-0Page 9

Jun 01/16


**ON A/C A350-1000

VT C2HT C1 F1BF1BF3 D5F2F4 BF2

RD1CP1 D1 D2N1

D3 W2 W1 C3 D4 AP

OF THE DOOR SILL AND FROM FLOOR LEVEL.

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

F3

m ft m ft m ft m ft

AC JACKEDFDL = 6.5 m

(21.33 ft)

ft16.5516.80

10.897.888.50

27.8827.81

6.44

5.09

3.28

8.44

1.96

5.14

2.452.568.54

16.7216.87

10.768.028.4028.0127.70

6.44

5.135.23

3.462.502.728.598.61

2.08

8.94

16.8417.15

8.19

28.1928.26

6.83 2.09

2.60

5.365.32

3.292.69

8.778.47

8.54

17.5917.47

10.798.84

28.7927.79

6.85

6.376.37

4.41

3.713.71

9.809.58

3.16

20.9120.91

14.4712.1812.1832.1431.45

10.37

11.35

17.09 5.20 17.05 5.34 17.51 5.28 17.33 6.37 20.91

23.0425.4321.9856.62

2.00

7.007.686.63

17.19

0.62

22.9825.2121.7656.39

2.04

7.157.916.8517.41

0.72

23.4725.9522.4957.14

2.37

7.077.616.5717.11

0.78

23.1924.9621.5456.15

2.55

8.178.777.72

1.84

26.8028.7725.3459.96

6.02

18.27

8.4119.1312.9931.00

2.545.894.029.42

8.3519.3213.1930.91

2.695.914.049.58

8.8319.4013.2631.44

2.616.184.329.46

8.5820.2714.1831.05

3.717.185.32

10.57

12.1823.5517.4534.69

A/C CONFIGURATION

mD1D2

C3F1F2F3F4

BF2

2.59

5.055.12

3.322.40

8.508.47

1.96

D3 5.21

W2HTAPVT

7.027.756.70

17.26

0.61

BF3CP1RD1W1

2.565.833.969.45

2.51 0.78 2.55 0.88 2.87 0.93 3.07 6.541.99N1 0.76

23.8210.12

7.303.12

23.9510.25

7.323.18

24.0210.42

7.553.37

24.7711.05

8.564.39

28.0814.40

10.89 3.28 10.78 3.46 11.34 3.31 10.86 4.43 14.52

D5C1

7.263.08

C2 3.32

17.35 5.24 17.21 5.43 17.82 5.24 17.20 6.37 20.90D4 5.29

8.09 2.48 8.15 2.57 8.44 2.66 8.73 3.71 12.17BF1 2.46

160 000 kg (352 739 lb)


DOORS

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE

AFT CG (34%)

MRW

FWD CG (25%)

N1 WITHDRAIN MAST

P_AC_020300_1_0090002_01_00

Ground ClearancesFIGURE-2-3-0-991-009-B01

2-3-0Page 10

Jun 01/16


**ON A/C A350-1000

NOTE:* DN − DROOP NOSE

A B C D E F G H J


3.454.61

11.3215.12

3.554.72

11.6415.48

3.614.75

11.8415.57

15.19 4.63 15.21 4.75 15.57 4.77 15.65

DESCRIPTION

mAB

3.444.60

C 4.63

DN* INBDDN* OUTBDSLAT 1 INBD

LEADING EDGE SLATS EXTENDED

SLAT 1/2 16.43 5.01 16.43 5.12 5.13 16.84D 5.01 16.81SLAT 2/3 17.59 5.36 17.58 5.48 5.47 17.96E 5.36 17.98SLAT 3/4 18.71 5.69 18.68 5.82 5.80 19.03F 5.70 19.11SLAT 4/5 19.75 6.01 19.71 6.14 6.10 20.02G 6.02 20.15SLAT 5/6 20.74 6.31 20.69 6.45 6.39 20.97H 6.32 21.15

SLAT 6 OUTBD 21.84 6.64 21.78 6.79 6.71 22.02J 6.66 22.26

160 000 kg (352 739 lb)

FWD CG (20%) AFT CG (40%)AFT CG (34%)

MRW

FWD CG (25%)

P_AC_020300_1_0100001_01_00

Ground ClearancesLeading Edge Slats - ExtendedFIGURE-2-3-0-991-010-A01

2-3-0Page 11

Jun 01/16


**ON A/C A350-1000

G F E D C B A


2.563.29

8.4110.80

2.693.42

8.8411.23

2.663.39

8.7311.12

13.45 4.09 13.42 4.22 13.86 4.19 13.74

DESCRIPTION

mAB

2.573.30

C 4.10

FLAPS EXTENDED

13.63 4.14 13.59 4.28 14.03 4.24 13.91D 4.1516.08 4.89 16.04 5.03 16.49 4.98 16.33E 4.9017.85 5.43 17.80 5.57 18.26 5.51 18.07F 5.4418.65 5.67 18.60 5.81 19.07 5.75 18.86G 5.69

MRW


160 000 kg (352 739 lb)


FLAP 1 INBDFLAP 1/2

FLAP 2 OUTBDFLAP 3 INBD

FLAP 3/4FLAP 4/5

FLAP 5 OUTBD

P_AC_020300_1_0110001_01_00

Ground ClearancesTrailing Edge Flaps - Extended

FIGURE-2-3-0-991-011-A01

2-3-0Page 12

Jun 01/16


**ON A/C A350-1000

J H D C B A


5.025.49

16.4818.00

5.155.62

16.9118.43

5.135.59

16.8318.34

19.52 5.94 19.49 6.07 19.92 6.04 19.83

DESCRIPTION

mAB

5.035.49

C 5.95

SPOILER 1 INBDSPOILER 1/2

SPOILER 2 OUTBD

SPOILERS EXTENDED

19.98 6.08 19.96 6.21 20.38 6.19 20.30D 6.09SPOILER 3 INBD20.78 6.32 20.75 6.46 21.18 6.42 21.08E 6.33SPOILER 3/421.46 6.53 21.43 6.67 21.87 6.63 21.74F 6.54SPOILER 4/522.09 6.72 22.05 6.86 22.49 6.81 22.35G 6.73SPOILER 5/622.67 6.90 22.62 7.03 23.08 6.98 22.91H 6.91SPOILER 6/723.24 7.07 23.19 7.21 23.65 7.15 23.46J 7.08SPOILER 7 OUTBD

MRW


160 000 kg (352 739 lb)


G F E

P_AC_020300_1_0120001_01_00

Ground ClearancesSpoilers - Extended

FIGURE-2-3-0-991-012-A01

2-3-0Page 13

Jun 01/16


**ON A/C A350-1000

B AD


5.936.34

19.4620.81

6.076.49

19.9321.29

6.016.41

19.7221.04

20.83 6.33 20.77 6.48 21.25 6.40 21.00

DESCRIPTION

m5.956.366.35


AILERONS DOWN

AILERON 2 OUTBD 22.44 6.82 22.37 6.97 6.88 22.576.84 22.87

160 000 kg (352 739 lb)


MRW

FWD CG (25%)

C

ABCD

P_AC_020300_1_0130001_01_00

Ground ClearancesAilerons - Down

FIGURE-2-3-0-991-013-A01

2-3-0Page 14

Jun 01/16


**ON A/C A350-1000

B ACD


6.957.19

22.8023.58

7.097.33

23.2724.06

7.037.26

23.0623.81

23.67 7.20 23.61 7.34 24.09 7.27 23.84

DESCRIPTION

mAB

6.967.20

C 7.21


AILERONS UP

AILERON 2 OUTBD 24.58 7.47 24.50 7.62 7.53 24.70D 7.49 25.01

160 000 kg (352 739 lb)


MRW

FWD CG (25%)

P_AC_020300_1_0140001_01_00

Ground ClearancesAilerons - Up

FIGURE-2-3-0-991-014-A01

2-3-0Page 15

Jun 01/16


**ON A/C A350-1000

B AC


3.754.56

12.3114.96

3.884.69

12.7315.39

3.864.66

12.6515.28

17.09 5.20 17.05 5.33 17.49 5.29 17.35

DESCRIPTION

mAB

3.764.57

C 5.21


FLAPS TRACKS RETRACTED

FWD CG (25%)

MRW

AFT CG (34%) FWD CG (20%)

160 000 kg (352 739 lb)

AFT CG (40%)

P_AC_020300_1_0150001_01_00

Ground ClearancesFlap Tracks - Retracted

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

2-3-0Page 16

Jun 01/16


**ON A/C A350-1000

B AC

m ft m ft m ftft9.38

11.072.853.36

9.3511.03

2.983.50

9.7911.48

2.953.45

9.6611.32

13.24 4.02 13.19 4.16 13.66 4.10 13.46

DESCRIPTION

m2.863.374.04

FLAPS TRACKS EXTENDED

MRW


160 000 kg (352 739 lb)


ABC


P_AC_020300_1_0160001_01_00

Ground ClearancesFlap Tracks - Extended

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

2-3-0Page 17

Jun 01/16


2-4-0 Interior Arrangements - Plan View

**ON A/C A350-1000 A350-900

Interior Arrangements - Plan View

1. This section provides the standard configuration.

2-4-0Page 1

Jun 01/16


**ON A/C A350-900

GALLEY

PASSENGER DOOR 4 LH

LAVATORYGALLEY

ATTENDANT SEATATTENDANT SEAT

PASSENGER DOOR 4 RH

ECONOMYCLASS SEATS

ECONOMYCLASS SEATS

LAVATORYLAVATORY

PASSENGER DOOR 3 LHPASSENGER DOOR 3 RHATTENDANT SEATATTENDANT SEAT

LAVATORYGALLEY

BUSINESSCLASS SEATS

GALLEYPASSENGER DOOR 2 LH

BUSINESSCLASS SEATS

PASSENGER DOOR 2 RH

PASSENGER DOOR 1 LHPASSENGER DOOR 1 RH

LAVATORY

LAVATORYATTENDANT SEAT

ATTENDANT SEAT

GALLEY

LAVATORYSTOWAGE

GALLEY

ATTENDANT SEAT ATTENDANT SEAT

PASSENGER SEATS (315 TOTAL)

267 ECONOMY CLASS SEATS(9 ABREAST − 32 in PITCH)

48 BUSINESS CLASS SEATS(6 ABREAST − 60 in PITCH)

ATTENDANT SEATS 8

GALLEYS 12

LAVATORIES 9

STOWAGE 1

P_AC_020400_1_0010001_01_02

Standard ConfigurationFIGURE-2-4-0-991-001-A01

2-4-0Page 2

Jun 01/16


**ON A/C A350-1000

ATTENDANT SEATGALLEY

GALLEY

ATTENDANT SEAT

LAVATORYLAVATORY


ECONOMYCLASS SEATS

PASSENGER DOOR 3 LHPASSENGER DOOR 3 RHGALLEY

ATTENDANT SEAT ATTENDANT SEAT

LAVATORY LAVATORY

ECONOMYCLASS SEATS

BUSINESSCLASS SEATS

LAVATORYATTENDANT SEAT


PASSENGER DOOR 2 RH

ATTENDANT SEAT

PASSENGER DOOR 2 LHATTENDANT SEAT

GALLEYGALLEY

LAVATORY

ATTENDANT SEATGALLEY

GALLEY

LAVATORY

GALLEY

STOWAGE

PASSENGER SEATS (369 TOTAL)

315 ECONOMY CLASS SEATS(9 ABREAST − 32 in PITCH)

54 BUSINESS CLASS SEATS(6 ABREAST − 60 in PITCH)

ATTENDANT SEATS 8

GALLEYS 12

LAVATORIES 11

STOWAGE 1

P_AC_020400_1_0020001_01_00

Standard ConfigurationFIGURE-2-4-0-991-002-A01

2-4-0Page 3

Jun 01/16


2-5-0 Interior Arrangements - Cross Section

**ON A/C A350-1000 A350-900

Interior Arrangements - Cross Section

1. This section provides the typical configuration.

2-5-0Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

BUSINESS CLASS / FIRST CLASS 6 ABREAST

BASELINE ECONOMY CLASS 9 ABREAST

1.50 m(59 in)

0.55 m(21.5 in)

0.18 m(7 in)

0.09 m(3.5 in)

0.57 m(22.5 in)

1.53 m(60.11 in)

0.46 m(18.1in)

0.04 m(1.5 in)

0.46 m(18 in)

NOTE:AISLE WIDTH MAY VARY DEPENDING ON ACTUAL CABINCONFIGURATION SELECTED BY CUSTOMER P_AC_020500_1_0010001_01_01

Typical ConfigurationFIGURE-2-5-0-991-001-A01

2-5-0Page 2

Jun 01/16


2-6-0 Cargo Compartments

**ON A/C A350-1000 A350-900

Cargo Compartments

1. This section provides the following data about cargo compartments:- Locations and dimensions,- Loading combinations.

2-6-0Page 1

Jun 01/16


**ON A/C A350-900

FR

19F

R44

FR

61F

R82

FR

85

LOW

ER

DE

CK

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

AF

T C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

2.90

m(9

.51

ft)

0.95

m(3

.12

ft)

1.91

m(6

.27

ft)

2.85

m(9

.35

ft)

(53.

22 ft

)16

.22

m13

.58

m(4

4.55

ft)

P_AC_020600_1_0020001_01_01

Cargo CompartmentsLocations and Dimensions (Sheet 1 of 2)

FIGURE-2-6-0-991-002-A01

2-6-0Page 2

Jun 01/16


**ON A/C A350-900

ST

AN

DA

RD

: 20

LD3

CO

NT

AIN

ER

SS

TA

ND

AR

D: 1

6 LD

3 C

ON

TA

INE

RS

ST

AN

DA

RD

: 6 P

ALL

ET

S 8

8 in

/ 96

in X

125

inS

TA

ND

AR

D: 5

PA

LLE

TS

88

in /

96 in

X 1

25 in

P_AC_020600_1_0020001_02_00

Cargo CompartmentsLoading Combinations (Sheet 2 of 2)

FIGURE-2-6-0-991-002-A01

2-6-0Page 3

Jun 01/16


**ON A/C A350-1000

LOW

ER

DE

CK

FO

RW

AR

D C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

AF

T C

AR

GO

CO

MP

AR

TM

EN

T

LOW

ER

DE

CK

BU

LK C

AR

GO

CO

MP

AR

TM

EN

T

FR

19F

R44

FR

62F

R82

FR

85

2.90

m(9

.51

ft)2.

85 m

(9.3

5 ft)

20.0

3 m

(65.

72 ft

)16

.12

m(5

2.89

ft)

0.95

m(3

.12

ft)

1.91

m(6

.27

ft)

P_AC_020600_1_0030001_01_00

Cargo CompartmentsLocations and Dimensions (Sheet 1 of 2)

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

2-6-0Page 4

Jun 01/16


**ON A/C A350-1000

ST

AN

DA

RD

: 24

LD3

CO

NT

AIN

ER

SS

TA

ND

AR

D: 2

0 LD

3 C

ON

TA

INE

RS

ST

AN

DA

RD

: 8 P

ALL

ET

S 9

6 in

X 1

25 in

ST

AN

DA

RD

: 6 P

ALL

ET

S 9

6 in

X 1

25 in

P_AC_020600_1_0030001_02_00

Cargo CompartmentsLoading Combinations (Sheet 2 of 2)

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

2-6-0Page 5

Jun 01/16


2-7-0 Door Clearances and Location

**ON A/C A350-1000 A350-900

Door Clearances and Location

1. This section provides door clearances and location.

2-7-0Page 1

Jun 01/16


**ON A/C A350-900

DOOR1L

BULK CARGO DOOR

COCKPIT ESCAPEHATCH

AFT CARGO DOOR FWD CARGO DOOR

DOOR2L

DOOR3L

DOOR4L

DOOR1R

DOOR2R

DOOR3R

DOOR4R

P_AC_020700_1_0010001_01_03

Door Identification and Location(Sheet 1 of 2)

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

2-7-0Page 2

Jun 01/16


**ON A/C A350-900

4.12 m(13.52 ft)

11.68 m(38.32 ft)

6.82 m(22.38 ft)

18.86 m(61.88 ft)

37.93 m(124.44 ft)

52.55 m(172.41 ft)

49.99 m(164.01 ft)

47.30 m(155.18 ft)

P_AC_020700_1_0010001_02_03


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

2-7-0Page 3

Jun 01/16


**ON A/C A350-1000

DOOR1L

BULK CARGO DOOR

COCKPIT ESCAPEHATCH

AFT CARGO DOOR FWD CARGO DOOR

DOOR2L

DOOR3L

DOOR4L

DOOR1R

DOOR2R

DOOR3R

DOOR4R

P_AC_020700_1_0010004_01_00


FIGURE-2-7-0-991-001-D01

2-7-0Page 4

Jun 01/16


**ON A/C A350-1000

4.12 m(13.52 ft)

11.68 m(38.32 ft)

6.82 m(22.38 ft)

23.30 m(76.44 ft)

42.38 m(139.04 ft)

59.53 m(195.31 ft)

56.89 m(186.65 ft)

54.28 m(178.08 ft)

P_AC_020700_1_0010004_02_00


FIGURE-2-7-0-991-001-D01

2-7-0Page 5

Jun 01/16


**ON A/C A350-1000 A350-900

2.16 m(7.09 ft)

0.06 m(0.20 ft)

FWD

0.86 m(2.82 ft)

0.73 m(2.40 ft)

FWD

2.46 m(8.07 ft)

1.26 m(4.13 ft)

PASSENGER/CREW DOOR1LH, 1RH

SEE CHAPTER2−3

P_AC_020700_1_0020003_01_01

Forward Passenger/Crew Doors(Sheet 1 of 2)

FIGURE-2-7-0-991-002-C01

2-7-0Page 6

Jun 01/16


**ON A/C A350-1000 A350-900

0.69 m(2.26 ft)

0.84 m(2.76 ft)

2.47 m(8.10 ft)

2.16 m(7.09 ft)

0.06 m(0.20 ft)

FWD

FWD

1.26 m(4.13 ft)


SEE CHAPTER2−3

P_AC_020700_1_0020003_02_01

Forward Passenger/Crew Doors(Sheet 2 of 2)

FIGURE-2-7-0-991-002-C01

2-7-0Page 7

Jun 01/16


**ON A/C A350-1000 A350-900

2.47 m(8.10 ft)

0.84 m(2.76 ft)

2.11 m(6.92 ft)

FWD

FWD

0.69 m(2.26 ft)

1.26 m(4.13 ft)


SEE CHAPTER2−3

0.06 m(0.20 ft)

P_AC_020700_1_0030001_01_01

Aft Passenger/Crew Doors(Sheet 1 of 2)

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

2-7-0Page 8

Jun 01/16


**ON A/C A350-1000 A350-900

2.39 m(7.84 ft)

0.87 m(2.85 ft)

2.16 m(7.09 ft)

0.06 m(0.20 ft)

FWD

FWD

1.26 m(4.13 ft)


SEE CHAPTER2−3

0.74 m(2.43 ft)

P_AC_020700_1_0030001_02_01

Aft Passenger/Crew Doors(Sheet 2 of 2)

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

2-7-0Page 9

Jun 01/16


**ON A/C A350-1000 A350-900

A A

1.76 m(5.77 ft)

2.55 m(8.37 ft)

2.40 m(7.87 ft)

SEE CHAPTER 2−3

FWD

0.27 m(0.89 ft)

2.91 m(9.55 ft)

0.74 m(2.43 ft)

A

A

P_AC_020700_1_0040001_01_00

Forward Cargo Compartment DoorFIGURE-2-7-0-991-004-A01

2-7-0Page 10

Jun 01/16


**ON A/C A350-1000 A350-900

SEE CHAPTER 2−3 0.27 m(0.89 ft)

1.75 m(5.74 ft)

2.53 m(8.30 ft)

2.40 m(7.87 ft)

FWD

A

A

A A

0.75 m(2.46 ft)

2.85 m(9.35 ft)

P_AC_020700_1_0050001_01_00

Aft Cargo Compartment DoorFIGURE-2-7-0-991-005-A01

2-7-0Page 11

Jun 01/16


**ON A/C A350-1000 A350-900

0.95 m(3.12 ft)

1.76 m(5.77 ft) SEE CHAPTER 2−3

FWD

A A

0.76 m(2.49 ft)

A

A

P_AC_020700_1_0060001_01_00

Bulk Cargo Compartment DoorFIGURE-2-7-0-991-006-A01

2-7-0Page 12

Jun 01/16


**ON A/C A350-1000 A350-900

R 0.78 m(2.56 ft)

1.06 m(3.48 ft)

61.8°

0.77 m(2.53 ft)

R 1.06 m(3.48 ft)

2.93 m(9.61 ft)

2.00 m(6.56 ft)

A

A

B

P_AC_020700_1_0070001_01_02

Nose Landing Gear DoorsForward Nose Landing Gear Doors (Sheet 1 of 2)

FIGURE-2-7-0-991-007-A01

2-7-0Page 13

Jun 01/16


**ON A/C A350-1000 A350-900

0.76 m(2.49 ft)

0.59 m(1.94 ft)

(2.36 ft)R 0.72 m

69.8°

2.03 m(6.66 ft)

B

2.15 m(7.05 ft)

R 0.71 m(2.33 ft)

P_AC_020700_1_0070001_02_01

Nose Landing Gear DoorsAft Nose Landing Gear Doors (Sheet 2 of 2)

FIGURE-2-7-0-991-007-A01

2-7-0Page 14

Jun 01/16


**ON A/C A350-900

81.3°

A

A

2.75 m(9.02 ft)

R 2.43 m(7.97 ft)

1.63 m(5.35 ft)

0.13 m(0.43 ft)

0.19 m(0.62 ft)

P_AC_020700_1_0080001_01_01

Main Landing Gear DoorsFIGURE-2-7-0-991-008-A01

2-7-0Page 15

Jun 01/16


**ON A/C A350-1000

INTENTIONALLY LEFT BLANK

P_AC_020700_1_0080002_01_00

Main Landing Gear DoorsFIGURE-2-7-0-991-008-B01

2-7-0Page 16

Jun 01/16


2-8-0 Escape Slides

**ON A/C A350-1000 A350-900

Escape Slides

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

2. LocationEscape facilities are provided at the following locations:- One cockpit escape rope is kept in a dedicated stowage compartment adjacent to the escape

hatch.- One escape slide-raft at each passenger/crew door (total eight).

2-8-0Page 1

Jun 01/16


**ON A/C A350-900

MID CABIN DUAL−LANEESCAPE SLIDE/RAFT


NOTE:RH SHOWN, LH SYMMETRICAL.

AFT CABIN DUAL−LANEESCAPE SLIDE/RAFT

FWD CABIN SINGLE−LANEESCAPE SLIDE/RAFT

COCKPITESCAPE ROPE

9.35 m (30.68 ft)

9.43 m (30.94 ft)

9.38 m (30.77 ft)

10.25 m (33.63 ft)

P_AC_020800_1_0020001_01_01

Escape SlidesEscape Slides - Location (Sheet 1 of 2)

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

2-8-0Page 2

Jun 01/16


**ON A/C A350-900

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

03691215182124273033

EM

ER

GE

NC

Y D

ES

CE

NT

TH

RO

UG

H T

HE

ES

CA

PE

HA

TC

H W

ITH

TH

E E

SC

AP

E R

OP

E

NO

TE

:−

RH

SH

OW

N, L

H S

YM

ME

TR

ICA

L.−

DIM

EN

SIO

NS

AR

E A

PP

RO

XIM

AT

E.

P_AC_020800_1_0020001_02_01

Escape SlidesEscape Slides - Dimensions (Sheet 2 of 2)

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

2-8-0Page 3

Jun 01/16


**ON A/C A350-1000

NOTE:RH SHOWN, LH SYMMETRICAL.



AFT CABIN DUAL−LANEESCAPE SLIDE/RAFT

FWD CABIN SINGLE−LANEESCAPE SLIDE/RAFT

COCKPITESCAPE ROPE

9.35 m (30.68 ft)

9.43 m (30.94 ft)

9.38 m (30.77 ft)

10.25 m (33.63 ft)

P_AC_020800_1_0030004_01_00

Escape SlidesEscape Slides - Location (Sheet 1 of 2)

FIGURE-2-8-0-991-003-D01

2-8-0Page 4

Jun 01/16


**ON A/C A350-1000

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

03691215182124273033

EM

ER

GE

NC

Y D

ES

CE

NT

TH

RO

UG

H T

HE

ES

CA

PE

HA

TC

H W

ITH

TH

E E

SC

AP

E R

OP

E

NO

TE

:−

RH

SH

OW

N, L

H S

YM

ME

TR

ICA

L.−

DIM

EN

SIO

NS

AR

E A

PP

RO

XIM

AT

E.

P_AC_020800_1_0030004_02_00

Escape SlidesEscape Slides - Dimensions (Sheet 2 of 2)

FIGURE-2-8-0-991-003-D01

2-8-0Page 5

Jun 01/16


2-9-0 Landing Gear

**ON A/C A350-900

Landing Gear

1. MLG System DescriptionThe two MLGs are mounted in the LH and RH wing just outboard of the wing root within thetrailing edge.The MLGs retract sideways into bays in the fuselage. Each MLG has a four wheel twin-tandem bogie.Each MLG has one related main door operated by a single door actuator.Each MLG has a gear uplock and a door uplock.The MLG has a double side stay arrangement to improve load distribution on the composite wing.Each side stay has a separate lock stay assembly to provide a positive means to lock the landing gearin the extended position for landing and ground manoeuvres.Each MLG leg contains a single-stage oleo shock strut consisting of a sliding piston and a main fittingthat is supported by the two folding side stays and pivots on the top of the main fitting forextension/retraction.In flight, the MLGs are retracted and locked up.The MLG doors are closed and locked to enclose the MLG bay in flight and on the ground, onlyopening when the landing gear is extending or retracting.Hydraulic power for the MLG extension/retraction comes from the Green Hydraulic System.

2. NLG System DescriptionThe NLG is located in the forward lower fuselage on the aircraft centerline below the cockpit.It is forward retracting and consists of a twin wheel axle mounted on a main fitting that incorporatesa single-stage oleo shock strut supported by a forward drag stay.The NLG main fitting accommodates the steering assembly for the NWS system.In flight, the NLG is retracted and locked up while the four sideways opening NLG Doors are closedand locked to enclose the NLG bay.The two forward doors are each operated by two independent door actuators.When retracted, the NLG is held by an uplock and the two main NLG doors are held by a single dooruplock assembly, containing an uplock hook for each door.The hydraulically powered Forward NLG Doors are also closed after the NLG is extended.The aft doors are mechanically driven and remain open when the NLG is extended.Hydraulic power for the NLG extension/retraction comes from the Yellow hydraulic system.

3. Landing Gear Extension and Retraction SystemThe Landing Gear Extension and Retraction System is made up of three sub-systems:- Normal extension and retraction system, for normal extension and retraction- Alternate extension system, for extension in flight if the normal system is unavailable- Ground door opening system, to allow on-ground access to the landing gear bays for maintenance

purposes.

2-9-0Page 1

Jun 01/16


**ON A/C A350-900

HINGE DOOR

MAIN DOOR

A

B

C

LH SHOWNRH SYMMETRICAL

B

FIXED FAIRINGDOOR

C

D

F

ACTUATOR

HINGE

FREE−FALLRAMP

FREE−FALLROD

HINGE

UP−LOCKFITTING

MECHANICALLINKAGE

FREE−FALLRAMP

A

P_AC_020900_1_0010001_01_01

Main Landing GearDoors Overview (Sheet 1 of 3)FIGURE-2-9-0-991-001-A01

2-9-0Page 2

Jun 01/16


**ON A/C A350-900

RETRACTIONACTUATOR

MAIN FITTING

FORWARDLOCK STAY

FORWARDSIDE STAY

SLIDINGPISTON

BOGIE

AFT LOCKSTAY ACTUATORAFT

LOCK STAY

AFT SIDE STAY

AFT DOWNLOCKSPRINGS

UPPERTORQUE LINK

LOWERTORQUE LINK

D

E

BOGIE PITCHTRIMMER

ACTUATOR

FORWARDDOWNLOCK

SPRINGS

FORWARD LOCKSTAY ACTUATOR

G

G

E

P_AC_020900_1_0010001_02_01

Main Landing GearOverview (Sheet 2 of 3)

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

2-9-0Page 3

Jun 01/16


**ON A/C A350-900

SAFETY

SAFETYPIN

TYPICAL

SAFETYPIN

COLLAR

SAFETYPIN

LOCK STAY

WARNINGFLAG

F

WARNINGFLAG

NOTE:FORWARD LOCK STAY SHOWN, AFT SIMILAR01

01G

P_AC_020900_1_0010001_03_01

Main Landing GearSafety Devices (Sheet 3 of 3)FIGURE-2-9-0-991-001-A01

2-9-0Page 4

Jun 01/16


**ON A/C A350-900

A

A

B

HINGE

HINGE

PROTECTIVEPLATE

DOOR STOP

ROD FITTING

FORWARDDOOR

AFT DOOR

RH SHOWNLH SYMMETRICAL

CE

ACTUATOR

INTERDOOR STOP

B

P_AC_020900_1_0020001_01_01

Nose Landing GearDoors Overview (Sheet 1 of 4)FIGURE-2-9-0-991-002-A01

2-9-0Page 5

Jun 01/16


**ON A/C A350-900

RETRACTION ACTUATOR

LOCK STAY ACTUATOR

MAIN FITTING

UPPER DRAGSTAY

LOWER DRAGSTAY

DOWNLOCKSPRINGS

STEERINGASSEMBLY

TOWINGFITTING

UPPERTORQUE LINK

LOWERTORQUE LINK

SLIDINGPISTON

C

D

F

FORWARD/ AFTLOCK STAYS

G D

P_AC_020900_1_0020001_02_01

Nose Landing GearOverview (Sheet 2 of 4)

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

2-9-0Page 6

Jun 01/16


**ON A/C A350-900

SAFETYCOLLAR

WARNINGFLAG

E

F

SAFETY PIN

WARNING FLAG

LOCK STAY

SAFETYPIN

P_AC_020900_1_0020001_03_01

Nose Landing GearSafety Devices (Sheet 3 of 4)FIGURE-2-9-0-991-002-A01

2-9-0Page 7

Jun 01/16


**ON A/C A350-900

2GN

FWD

FWD

1GN

HJ

G

H

J

WARNINGFLAG

P_AC_020900_1_0020001_04_01

Nose Landing GearService Panels (Sheet 4 of 4)FIGURE-2-9-0-991-002-A01

2-9-0Page 8

Jun 01/16


2-9-1 Landing Gear Maintenance Pits

**ON A/C A350-900

Landing Gear Maintenance Pits

1. GeneralThe minimum maintenance pit envelopes for landing gear shock absorber maintenance are shown inFigures FIGURE 2-9-1-991-001-A, FIGURE 2-9-1-991-002-A, FIGURE 2-9-1-991-003-A and FIGURE2-9-1-991-004-A.The landing gears are shown with simplified gear structure.

The three envelopes show the minimum dimensions for these maintenance operations:- Extension and retraction- Gear removal- Piston removal.

Pit envelopes shown represent minimum sizing required to accommodate landing gear tires andremoval tooling. Dimensions for the below cases are to be added in the shown envelopes:- Clearance allowances for working area- Operator access- Functional clearances- Tooling- Civil engineering considerations.

The maintenance pits are symmetrical about the aircraft centerline and all dimensions shown areminimum dimensions with zero clearances.The dimensions for the pits have been determined as follows:- The aircraft starting condition is with weight on wheels supported by jacks over the pits.- The pit depths are then based on the shock absorbers lowering to the fully extended position plus

allowances for tooling.- The length and width of the pits allow the gear to rotate after the weight is taken off the landing

gear- The landing gear tires are in the maximum grown condition- The MLG wheels, brakes and bogie beams are removed before the piston is removed- The NLG wheels are removed before the piston is removed- Both the MLG and the NLG pistons are removed vertically.The pit depth for the MLG piston removal is based on the removal pallet support leg being installedat its maximum length (upper pin hole position).The landing gear piston trolley for MLG and NLG may be positioned FWD or AFT of the landinggears depending on the chosen removal orientation (rotation FWD or AFT).

Dimensions for elevators and associated mechanisms must be added to those in Figures FIGURE2-9-1-991-001-A, FIGURE 2-9-1-991-002-A, FIGURE 2-9-1-991-003-A and FIGURE 2-9-1-991-004-A.

2-9-1Page 1

Jun 01/16


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

B. JackingThe aircraft must be in position over the pits to put the gear on the elevators. The jack must beinstalled and engaged with all the jacking points, AC 2-14-1 for aircraft maintenance jacking.When lowering the elevators, the aircraft weight will be transferred from the wheels to the jacks.The landing gears must not be in contact with the elevators during retraction/extension tests.The aircraft must not bend when it is jacked and when its weight is off the wheels.When tripod support jacks are used, the tripod-base circle radius must be limited because thelocations required for positioning the columns are close to the sides of the pits.

2-9-1Page 2

Jun 01/16


**ON A/C A350-900

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.

AIR

CR

AF

T C

EN

TE

R L

INE

1.16

m(3

.81

ft)

1.52

m(4

.99

ft)

NLG

RE

MO

VA

L P

IT O

UT

LIN

E

1.63

m(5

.35

ft)1.

73 m

(5.6

8 ft)

2.22

m(7

.28

ft) 8.71

m(2

8.58

ft)

MLG

RE

MO

VA

L P

IT O

UT

LIN

E

MLG

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

WIN

G J

AC

KIN

G P

OIN

T

3.41

m(1

1.19

ft)

3.50

m(1

1.48

ft)

3.85

m(1

2.63

ft)

4.16

m(1

3.65

ft)

38.5

6 m

(126

.51

ft)

MLG

SH

OC

K A

BS

OR

BE

RR

EM

OV

AL

PIT

NLG

EX

TE

NS

ION

/RE

TR

AC

TIO

NP

IT O

UT

LIN

E

NLG

SH

OC

K A

BS

OR

BE

RR

EM

OV

AL

PIT

OU

TLI

NE

FW

D

A/C DATUM X = 0

1.84

m(6

.04

ft)

10.1

1 m

(33.

17 ft

)

0.38

m(1

.25

ft)

3.14

m(1

0.30

ft)

2.05

m(6

.73

ft)2.

57 m

(8.4

3 ft)

2.26

m(7

.42

ft)

2.30

m(7

.55

ft)W

ING

JAC

KIN

GP

OIN

T

0.91

m(2

.99

ft)

FW

DJA

CK

ING

PO

INT

1.14

m(3

.74

ft)

P_AC_020901_1_0010001_01_00

Maintenance Pit EnvelopesFIGURE-2-9-1-991-001-A01

2-9-1Page 3

Jun 01/16


**ON A/C A350-900

AIR

CR

AF

T J

AC

KE

D A

T 2

0% M

AC

0.38

° R

EF

NLG WEIGHT ON WHEELS

NLG TIRES RETRACTIONSWEEP

NLG EXTENSION/RETRACTIONPIT 2.25 m

(7.38 ft)

AIR

CR

AF

T J

AC

KE

D A

T 4

1% M

AC

0.11

° R

EF

MLG WEIGHT ON WHEELS

MLG FULLY EXTENDED

0.90 m(2.95 ft)

NLG FULLY EXTENDED

MLG TIRESRETRACTION SWEEPS

FUSELAGE DATUM LINE

GROUND PLANE

FUSELAGE DATUM LINE

GROUND PLANE

0.44 m(1.44 ft)

MLG EXTENSION/RETRACTIONPIT

FWD

FWD

P_AC_020901_1_0020001_01_00

NLG/MLG Extension/Retraction PitFIGURE-2-9-1-991-002-A01

2-9-1Page 4

Jun 01/16


**ON A/C A350-900

FUSELAGE DATUM LINE

AIR

CR

AF

T J

AC

KE

D A

T 2

0% M

AC

0.38

° R

EF NLG FULLY EXTENDED

CLEARANCE BETWEENBOTTOM OF MAIN FITTINGAND TOP OF PISTON SLIDING TUBE

GROUND PLANE

NLG SHOCK ABSORBERREMOVAL TROLLEY

NLG SHOCK ABSORBERREMOVAL PIT

0.09 m(0.30 ft)

1.85 m(6.07 ft)

2.03 m(6.66 ft)

FUSELAGE DATUM LINE

AIR

CR

AF

T J

AC

KE

D A

T 4

1% M

AC

0.11

° R

EF


MLG FULLY EXTENDED

EXTENT OF PIT TO ALLOWROTATION OF THE SLIDER

FWD OF MLG

MLG SHOCK ABSORBERREMOVAL PIT MLG SLIDER

TRANSPORTATION PALLETMLG REMOVAL TOOL

TRANSPORTATION PALLET 2.40 m(7.87 ft)

2.80 m(9.19 ft)

2.25 m(7.38 ft)

2.03 m(6.66 ft)

GROUND PLANE

CLEARANCE BETWEENBOTTOM OF MAIN FITTINGAND TOP OF PISTON

0.09 m(0.30 ft)

EXTENT OF PIT TO ALLOWREMOVAL OF THE NLG

SHOCK ABSORBER WITHTROLLEY POSITIONED

AFT OF NLGNLG WEIGHTON WHEELS

FWD

FWD

P_AC_020901_1_0030001_01_00

NLG/MLG Shock Absorber Removal PitFIGURE-2-9-1-991-003-A01

2-9-1Page 5

Jun 01/16


**ON A/C A350-900

NLG TROLLEY

GROUND PLANE

NLG REMOVAL PIT

FUSELAGE DATUM LINE

AIR

CR

AF

T J

AC

KE

D A

T 4

1% M

AC

0.11

° R

EF

MLG PISTON

MLG REMOVAL PIT

MLG TROLLEY


GROUND PLANE

NLG LOWERED UNTIL ZEROCLEARANCE BETWEEN TOP OF

NLG AND NOSE FUSELAGE PROFILEA

IRC

RA

FT

JA

CK

ED

AT

20%

MA

C0.

38°

RE

F

EXTENT OF PIT TOALLOW REMOVAL OF

THE NLG AND TROLLEYTO GROUND LEVEL WITH

ZERO CLEARANCE TOTHE NOSE FUSELAGE

0.63 m(2.07 ft)

0.94 m(3.08 ft)

EXTENT OF PITWITH NLG TROLLEY

TOWING HANDLEEXTENDED

8.74 m(28.67 ft)

1.12 m(3.67 ft)

EXTENT OF PITWITH MLG TROLLEYTOWING HANDLEEXTENDED

1.36 m(4.46 ft)

NLG WEIGHTON WHEELS

FUSELAGE DATUM LINE

4.06 m(13.32 ft)

3.52 m(11.55 ft)

7.66 m(25.13 ft)

NLG PISTON

FWD

FWD

MLG LOWEREDUNTIL ZEROCLEARANCE

BETWEEN TOP OFMLG AND LOWER

WING O/S SKIN LINE

4.60 m(15.09 ft)

5.55 m(18.21 ft)

P_AC_020901_1_0040001_01_00

NLG/MLG Removal PitFIGURE-2-9-1-991-004-A01

2-9-1Page 6

Jun 01/16


2-10-0 Exterior Lighting

**ON A/C A350-1000 A350-900

Exterior Lighting

1. This section provides 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)

4UPPER ANTI-COLLISION LIGHT/BEACON(RED)

5LOWER ANTI-COLLISION LIGHT/BEACON(RED)

6 LOGO LIGHTS7 ENGINE SCAN LIGHTS8 WING SCAN LIGHTS

9WING STROBE LIGHT (HIGH INTENSITY,WHITE)

10TAIL STROBE LIGHT (HIGH INTENSITY,WHITE)

11 TAXI CAMERA LIGHTS (NLG)

12 TAXI CAMERA LIGHTS (MLG)

13 LANDING LIGHTS14 RUNWAY TURN-OFF LIGHTS15 TAXI LIGHTS16 TAKE-OFF LIGHTS17 CARGO COMPARTMENT FLOOD LIGHTS

18 LANDING GEAR BAY/WELL LIGHTS (DOME)

2-10-0Page 1

Jun 01/16


**ON A/C A350-900

3

6

6

12

12

8

7

8

7

11

10

4

1

2 9

9

5

P_AC_021000_1_0010002_01_01

Exterior LightingFIGURE-2-10-0-991-001-B01

2-10-0Page 2

Jun 01/16


**ON A/C A350-900

15

13

6

6

16

16

13

14

P_AC_021000_1_0020001_01_00

Exterior LightingFIGURE-2-10-0-991-002-A01

2-10-0Page 3

Jun 01/16


**ON A/C A350-900

21

3

11 11

14

8

15

14

5

7

4

P_AC_021000_1_0030002_01_01

Exterior LightingFIGURE-2-10-0-991-003-B01

2-10-0Page 4

Jun 01/16


**ON A/C A350-900

99

16

10

1212

1313

P_AC_021000_1_0040001_01_01


2-10-0Page 5

Jun 01/16


**ON A/C A350-900

17 1718 18

EXAMPLE FOR LIGHT N° 17

CEILING LIGHT SPOT LIGHT

P_AC_021000_1_0050001_01_01


2-10-0Page 6

Jun 01/16


**ON A/C A350-1000

3

6

6

12

512

10

7

8

7

1

2 9

11

8

9

4

P_AC_021000_1_0060001_01_00


2-10-0Page 7

Jun 01/16


**ON A/C A350-1000

13

6

6

16

13

1615

14

P_AC_021000_1_0070001_01_00


2-10-0Page 8

Jun 01/16


**ON A/C A350-1000

21

11 11

5

7

3

8

1414

15

4

P_AC_021000_1_0080001_01_00


2-10-0Page 9

Jun 01/16


**ON A/C A350-1000

99

16

10

1212

1313

P_AC_021000_1_0090001_01_00


2-10-0Page 10

Jun 01/16


**ON A/C A350-1000

17 17

CEILING LIGHT

18 18

SPOT LIGHT

EXAMPLE FOR LIGHT N° 17

P_AC_021000_1_0100001_01_00


2-10-0Page 11

Jun 01/16


2-11-0 Antennas and Probes Location

**ON A/C A350-1000 A350-900

Antennas and Probes Location

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

2-11-0Page 1

Jun 01/16


**ON A/C A350-900

WACSSATCOM

VHF 1

ADF 2VHF 3 ELT

GNSS 1

RADIO ALTIMETER E2RADIO ALTIMETER R2

DME 2 MARKER

TCAS 1 (TOP)

VHF 2

GNSS 2

ADF 1

TCAS 2 (TOP)

ISP LH

ISP RH

AOA

MFP 1

PITOT

LOCALIZER

SSA 1

MFP 2, 3

HF

ICE PROBE

TATPROBE

1, 2

WEATHER RADAR

GLIDE

ICE PROBE DETECTOR

TCAS 1 (BOTTOM)DME 1

ICE PROBE PROTECTOR

TCAS 2 (BOTTOM)

RADIO ALTIMETER E1

RADIO ALTIMETER R3RADIO ALTIMETER E3

RADIO ALTIMETER R1

VORSSA 2, 3

P_AC_021100_1_0010001_01_01

Antennas and Probes LocationFIGURE-2-11-0-991-001-A01

2-11-0Page 2

Jun 01/16


**ON A/C A350-1000

WACSSATCOM

VHF 1ADF 2

VHF 3 ELT

GNSS 1

RADIO ALTIMETER E2RADIO ALTIMETER R2

DME 2 MARKER

TCAS 1 (TOP)

VHF 2

GNSS 2

ADF 1

TCAS 2 (TOP)

ISP LH

ISP RH

AOAMFP 1

PITOT

LOCALIZER

SSA 1

MFP 2, 3

HF

ICE PROBE

WEATHER RADARGLIDEICE PROBE DETECTOR

TCAS 1 (BOTTOM)DME 1

VORSSA 2, 3

TCAS 2 (BOTTOM)

RADIO ALTIMETER E1

RADIO ALTIMETER R3RADIO ALTIMETER E3

RADIO ALTIMETER R1

ICE PROBE PROTECTOR

TATPROBE

1, 2

P_AC_021100_1_0020001_01_00

Antennas and Probes LocationFIGURE-2-11-0-991-002-A01

2-11-0Page 3

Jun 01/16


2-12-0 Engine and Nacelle

**ON A/C A350-1000 A350-900

Engine and Nacelle

1. Power PlantThe A350--900 and A350--1000 has two main power plants, one installed under each wing on a pylon.Each power plant can be lowered for removal from its pylon.The power plant comprises the:- Nacelle,- Engine.

2. NacelleThe nacelle comprises the following assemblies:- Air intake,- Fan cowls,- Thrust reverser,- Exhaust system.

A. Fan CowlA power door opening system is installed to assist in opening the cowls.The cowls have access doors for fan case-mounted components.

B. Thrust ReverserThe engine thrust reverser consists primarily of a inner fixed structure and an outer translatingsleeve.The fan exhaust stream is reversed by the cascades and blocker doors, which form part of thetranslating sleeve actuated by an electrical Thrust Reverser Actuation System (TRAS).A power door opening system is used to assist thrust reverser cowl opening.The thrust reverser latching system is designed so that the remote latches close only when thehooks are engaged.Means are provided to latch and secure a thrust reverser in the stowed position.Means are provided to permit actuation of the thrust reversers without engine operation, formaintenance purposes, either using the TRAS powered by the aircraft or by manual drive withexternal Ground Support Equipment (GSE).

C. Exhaust SystemThe exhaust system consists of a primary nozzle and a center body plug.The exhaust system is designed to optimize aerodynamics and acoustic performance.

3. Engine

A. IgnitionEach engine is equipped with a dual ignition system controlled by the FADEC.Each engine is equipped with an automatic flame-out protection.

2-12-0Page 1

Jun 01/16


B. Cooling SystemA nacelle cooling and ventilating system automatically provides the airflow required for coolingengine and nacelle accessories and associated structure.

C. Power ControlForward thrust of each engine is controlled by a throttle control lever mounted on the centerpedestal in the cockpit.Thrust reverser control is by means of a separate lever for each engine.

D. Engine Master ControlEngine fuel shutoff is controlled by switches installed on the center pedestal.

E. Emergency ShutdownActuation of the fire controls closes the associated LP valves.

F. IndicatingIndications for each engine are displayed on the Control and Display System (CDS).

G. OilThe propulsion system has an independent integral oil system that is able to provide theappropriate quantity of oil, at the temperature necessary for continuous propulsion systemoperation, for all achievable conditions within the propulsion system operating envelope.Means are provided for gravity filling.It is possible to visually check and replenish the engine oil level without opening the fan cowldoor.Magnetic chip detectors are installed in the lubrication system.

H. StartingThe engine is equipped with a pneumatic air turbine starter.The starter can be supplied with air either from the APU, or the other engine, or an Air StartUnit (AS).Standard types of GSE can be used.

2-12-0Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

P_AC_021200_1_0010001_01_00

1.53 m(5.02 ft)

5.09 m(16.70 ft)

2.03 m(6.66 ft)

0.72 m(2.39 ft)

1.65 m(5.41 ft)

1.94 m(6.36 ft)

3.17 m(10.40 ft)3.52 m

(11.55 ft)

1.48 m(4.86 ft) 0.89 m

(2.92 ft)REFER

APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATIONNOTE:

3.94 m(12.93 ft)

11.10 m(36.42 ft)

2.09 m(6.86 ft)

1.68 m(5.51 ft)

6.40 m(21 ft)

1.40 m(4.59 ft)

TO SECTION2−3−0

Engine and Nacelle(Sheet 1 of 3)

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

2-12-0Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

P_AC_021200_1_0010001_02_00

APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION.NOTE:

B

C

5.50 m(18.04 ft)

1.01 m(3.31 ft)

A B

6.39 m(20.96 ft)

1.28 m(4.20 ft)

C D

D

A

TRFC

FC: FAN COWL AND TR: THRUST REVERSER


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

2-12-0Page 4

Jun 01/16


**ON A/C A350-1000 A350-900

P_AC_021200_1_0010001_03_00

B

C

6.42 m(21.06 ft)

1.51 m(4.95 ft)

A B

7.13 m(23.40 ft)

1.81 m(5.94 ft)

C D

D

A

TRFC

TR=45° FC=50°

APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION.NOTE:

FC: FAN COWL AND TR: THRUST REVERSER


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

2-12-0Page 5

Jun 01/16


2-12-1 Auxiliary Power Unit

**ON A/C A350-1000 A350-900

Auxiliary Power Unit

1. GeneralThe Auxiliary Power Unit (APU) is installed at the rear part of the fuselage in the tail cone. An airintake system with a flap-type door is installed on the top right area of the tail cone. The exhaustgases pass overboard at the end of the fuselage cone.

2-12-1Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

, Z315 Z316

A

FR104

FR112

ENGINE

ENGINE FUEL ANDCONTROL SYSTEM

EXHAUSTSYSTEM

AIR SYSTEM

IGNITION ANDSTARTING SYSTEM

AIR SYSTEM

OILSYSTEM

FR109

FR104

A

B

B

P_AC_021201_1_0010001_01_01

Auxiliary Power UnitFIGURE-2-12-1-991-001-A01

2-12-1Page 2

Jun 01/16


2-13-0 Leveling, Symmetry and Alignment

**ON A/C A350-1000 A350-900

Leveling, Symmetry and Alignment

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.

2. Precise LevelingFor precise leveling, it is necessary to install sighting rods in the receptacles located under thefuselage (points 10 and 17 for longitudinal leveling) and under the wings (points 1 LH and 1 RH forlateral leveling) and use a sighting tube. With the aircraft on jacks, adjust the jacks until thereference marks on the sighting rods are aligned in the sighting plane (aircraft level).

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

2-13-0Page 1

Jun 01/16


**ON A/C A350-900

P_AC_021300_1_0010001_01_00

FR22FR23

FR92

10

17

1RH

1LH

RIB4

RIB5

RIB5

RIB4

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

2-13-0Page 2

Jun 01/16


**ON A/C A350-1000

FR22FR23

FR89

10

17

1RH

1LH

RIB4

RIB5

RIB5

RIB4

P_AC_021300_1_0020001_01_00

Location of Leveling PointsFIGURE-2-13-0-991-002-A01

2-13-0Page 3

Jun 01/16


2-14-1 Jacking for Maintenance

**ON A/C A350-1000 A350-900

Jacking for Maintenance

**ON A/C A350-900

1. Aircraft Jacking Points for Maintenance

A. The A350-900 can be jacked:- At not more than 164000 kg (361558 lb),- Within the limits of the permissible wind speed when the aircraft is jacked outside a closed

environment.

B. Primary Jacking PointsThe aircraft is provided with three primary jacking points:- One located on the forward lower left fuselage (FR12),- Two located under the wings (one under each wing, RIB9).

C. Auxiliary Jacking Point (Safety Stay)- When the aircraft is on jacks, a safety stay is placed under the fuselage at FR98 to prevent

tail tipping caused by accidental displacement of the aircraft center of gravity.- The safety point must not be used for lifting the aircraft.

**ON A/C A350-1000

2. Aircraft Jacking Points for Maintenance

A. The A350-1000 can be jacked:- At not more than 186000 kg (410060 lb),- Within the limits of the permissible wind speed when the aircraft is jacked outside a closed

environment.

B. Primary Jacking PointsThe aircraft is provided with three primary jacking points:- One located on the forward lower left fuselage (FR12),- Two located under the wings (one under each wing, RIB9).

C. Auxiliary Jacking Point (Safety Stay)- When the aircraft is on jacks, a safety stay is placed under the fuselage at FR98 to prevent

tail tipping caused by accidental displacement of the aircraft center of gravity.- The safety point must not be used for lifting the aircraft.

**ON A/C A350-1000 A350-900

3. Jacks and Safety Stay

A. Jack Design- The maximum eligible static load given in table (FIGURE 2-14-1-991-002-AFIGURE

2-14-1-991-002-B) are the maximum loads applicable on jack fittings.

2-14-1Page 1

Jun 01/16


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

- The jacks stroke enables the aircraft to be jacked up so that the Fuselage Datum Line(FDL) may be positioned up to 7.30 m (23.95 ft.) from the ground to allow all requiredmaintenance procedure and in particular, the removal/installation of the landing-gear shockabsorbers.

B. Safety StayThe stay stroke enables the aircraft tail to be supported up to the Fuselage Datum Line (FDL)positioned at 7.30 m (23.95 ft.) from the ground.

2-14-1Page 2

Jun 01/16


**ON A/C A350-900

FUSELAGE DATUM LINE

X

FR12

FWD JACKING POINT

RIB9

RIB9

WING JACKING POINT

WING JACKING POINT

SAFETY POINTFR98

Y

A

B

B’

C

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

4.77

33.22

33.22

58.75

15.65

108.99

108.99

192.75

−1.72

8.71

−8.71

0

−5.64

28.58

−28.58

0

MAXIMUMLOAD ELIGIBLE

m ft

18 630

daN

YX

76 600

76 600

7 650

m ft

NOTE:SAFETY STAY IS NOT USED FOR JACKING.

P_AC_021401_1_0020001_01_00

Jacking Points LocationFIGURE-2-14-1-991-002-A01

2-14-1Page 3

Jun 01/16


**ON A/C A350-1000

FUSELAGE DATUM LINE

X

FR12

FWD JACKING POINT

RIB9

RIB9

WING JACKING POINT

WING JACKING POINT

SAFETY POINTFR98

Y

A

B

B’

C

SAFETY STAY

WING JACKINGPOINT

C

B’

B

FORWARD FUSELAGEJACKING POINT A

4.77

37

37

65.74

15.65

121.39

121.39

215.68

−1.72

8.71

−8.71

0

−5.64

28.58

−28.58

0

MAXIMUMLOAD ELIGIBLE

m ft

18 630

daN

YX

90 000

90 000

7 652

m ft

NOTE:SAFETY STAY IS NOT USED FOR JACKING.

P_AC_021401_1_0020002_01_00

Jacking Points LocationFIGURE-2-14-1-991-002-B01

2-14-1Page 4

Jun 01/16


**ON A/C A350-900

FUSELAGE DATUM LINE

NL M

POSITIONCG

(% MAC)

AIRCRAFT ON WHEELS, SHOCK−ABSORBERDEFLATED, TIRES DEFLATED (RH)

A/C ON JACKS, FDL AT 6.50 m (21.33 ft),

SHOCK−ABSORBER RELAXED, CLEARANCEOF MAIN GEAR WHEELS = 1.17 m (3.84 ft)(STANDARD TIRES *), CLEARANCE OFNOSE GEAR WHEELS = 1.38 m (4.53 ft)(STANDARD TIRES *)

AIRCRAFT ON WHEELS (STANDARD TIRES *)MAXIMUM JACKING WEIGHT= 164 000 kg (361 558 lb)

AIRCRAFT ON WHEELS (STANDARD TIRES *)A/C WEIGHT = 142 000 kg (313 056 lb)

3.122015.42 LH

4.00 RH4.71

41 3.364.68 LH

4.00 RH4.48

20 4.32 6.125.66

41

20 3.06 16.904.58

41 3.29 4.914.57

20 3.09 17.034.62

41 3.34 4.934.60

HEIGHT

L M N

4.32 5.66

CONFIGURATION

10.24

11.02

14.17

14.17

10.04

10.79

10.14

10.96

4.70 LH

13.12 RH

15.35 LH

13.12 RH

18.57

18.57

15.03

14.99

15.16

15.09

15.45

14.70

20.08

6.12 20.08

5.15

16.11

5.19

16.18

m ft m mft ft

A/C FUSELAGE PARALLEL TO THE GROUND,

NOTE:* STANDARD TIRES: NOSE LANDING GEAR = 1 050 x 395 R16

MAIN LANDING GEAR = 1 400 x 530 R23P_AC_021401_1_0030001_01_00

Jacking DimensionsFIGURE-2-14-1-991-003-A01

2-14-1Page 5

Jun 01/16


**ON A/C A350-1000

FUSELAGE DATUM LINE

NL M

POSITIONCG

(% MAC)

AIRCRAFT ON WHEELS, SHOCK−ABSORBERDEFLATED, TIRES DEFLATED (RH)

A/C ON JACKS, FDL AT 6.50 m (21.33 ft),

SHOCK−ABSORBER RELAXED, CLEARANCEOF MAIN GEAR WHEELS = 1.17 m (3.84 ft)(STANDARD TIRES *), CLEARANCE OFNOSE GEAR WHEELS = 1.38 m (4.53 ft)(STANDARD TIRES *)

A/C FUSELAGE PARALLEL TO THE GROUND,

AIRCRAFT ON WHEELS (STANDARD TIRES *)MAXIMUM JACKING WEIGHT= 186 000 kg (410 060 lb)

AIRCRAFT ON WHEELS (STANDARD TIRES *)A/C WEIGHT = 155 000 kg (341 717 lb)

3.1217.515.45 LH

4.08 RH4.79

40 3.414.69 LH

4.08 RH4.53

17.5 4.32 6.125.69

40

17.5 3.06 16.994.61

40 3.34 4.914.59

17.5 3.10 17.164.65

40 3.41 4.934.63

HEIGHT

L M N

4.32 5.69

CONFIGURATION

10.24

11.19

14.17

14.17

10.04

10.96

10.17

11.19

4.71 LH

13.39 RH

15.39 LH

13.39 RH

18.67

18.67

15.12

15.06

15.26

15.19

15.72

14.86

20.08

6.12 20.08

5.18

16.11

5.23

16.17

m ft m mft ft

NOTE:* STANDARD TIRES: NOSE LANDING GEAR = 1 050 x 395 R16

MAIN LANDING GEAR = 1 400 x 530 R23P_AC_021401_1_0030002_01_00

Jacking DimensionsFIGURE-2-14-1-991-003-B01

2-14-1Page 6

Jun 01/16


**ON A/C A350-1000 A350-900

FR12

FR13

FR14

FR11

NOSE JACKADAPTOR

A

FR12FR13

Z120

A

P_AC_021401_1_0040002_01_00

Forward Jacking PointFIGURE-2-14-1-991-004-B01

2-14-1Page 7

Jun 01/16


**ON A/C A350-1000 A350-900

A

A

A

A A

REAR SPAR

RIB9

Z571 (Z671)

571FB (671FB)

PLATE COVERPROTECTOR

WING JACKADAPTOR

A

P_AC_021401_1_0050001_01_00

Wing Jacking PointFIGURE-2-14-1-991-005-A01

2-14-1Page 8

Jun 01/16


**ON A/C A350-1000 A350-900

FR98

FR98

BEAM5

FR98

A

A

FWD

B

Z310

B

AFT JACKADAPTOR

P_AC_021401_1_0060001_01_00

Auxiliary Jacking Point - SafetyFIGURE-2-14-1-991-006-A01

2-14-1Page 9

Jun 01/16


2-14-2 Jacking of the Landing Gear

**ON A/C A350-900

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.

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

2. Nose Landing Gear (NLG)To lift the NLG axle with a jack, a dome shaped pad is installed between the wheels.The reaction loads at the jacking position are shown in FIGURE 2-14-2-991-002-A.

NOTE : The maximum load at NLG jacking point is 33758 daN.

3. Main Landing Gear (MLG)To lift the MLG bogie with jacks, a dome shaped pad is installed below the FWD and AFT ends ofeach bogie beam.Each pair of wheels and brake units can be replaced on the end 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 reaction loads at the jacking position are shown in FIGURE 2-14-2-991-003-A.

NOTE : The maximum load at each MLG jacking point is 83892.5 daN.

2-14-2Page 1

Jun 01/16


**ON A/C A350-900

FWD

CONFIGURATION (ASSUMEALL OTHER TYRES ONTHE A/C ARE INTACT)

WEIGHT (T)CG

(% MAC)DIM A DIM B

2 TYRES (NORMAL)

1 FLAT TYRE

2 FLAT TYRES & 50% RIMFLANGE DAMAGE

2 FLAT TYRES & NO RIMFLANGE DAMAGE

MRW

MRW

MLW

MLW

26.2

26.2

20

20

291

227

75

97

10.27

8.42

7.51

7.51

11.45

8.93

2.95

3.81

261

214

191

191

mm in mm in

DOME HEIGHT− A : DISTANCE BETWEEN TYRES− B :

A350−900 NLG (1 050 x 395 R16)

B

A

A

A

P_AC_021402_1_0020001_01_00

Nose Landing Gear Jacking Point HeightsFIGURE-2-14-2-991-002-A01

2-14-2Page 2

Jun 01/16


**ON A/C A350-900

4 TYRES (NORMAL) MRW 33.2 378 378 1 029 1 036 267 267

AFTDIM A

AFTDIM B

AFTDIM C

MRW 33.2 304 381 981 1 041 194 271

MRW 33.2 285 374 974 1 033 175 264

MRW 33.2 381 304 1 032 983 271 193AFT INNER TYREUNSERVICEABLE 15.00 11.96 40.62 38.70 10.66 7.59

MRW 33.2 374 285 1 025 975 264 175AFT OUTER TYREUNSERVICEABLE 14.72 11.22 40.35 38.38 10.39 6.88

MLW 42 129 404 967 1 071 18 2932 FLAT FWD TYRES& 50% RIM DAMAGE 5.07 15.90 38.07 42.16 0.70 11.53

MLW 42 404 129 1 060 967 293 182 FLAT AFT TYRES& 50% RIM DAMAGE 15.90 5.07 41.73 38.07 11.53 0.70

MLW 42 136 136 967 967 26 264 FLAT TYRES &50% RIM DAMAGE 5.35 5.35 38.07 38.07 1.02 1.02

MLW 42 159 403 967 1 071 48 2932 FLAT FWD TYRES& NO RIM DAMAGE 6.25 15.86 38.07 42.16 1.88 11.53

MLW 42 403 159 1 059 967 293 482 FLAT AFT TYRES& NO RIM DAMAGE 15.86 6.25 41.69 38.07 11.53 1.88

MLW 42 166 166 967 967 55 554 FLAT TYRES &NO RIM DAMAGE 6.53 6.53 38.07 38.07 2.16 2.16

MRW 33.2 541 378 1 113 1 029 431 268FWD MAX GROWN

TYRE 25 mmFROM GROUND

21.29 14.88 43.81 40.51 16.96 10.55

MRW 33.2 378 541 1 029 1 113 268 43014.88 21.29 40.51 43.81 10.55 16.92AFT MAX GROWN

TYRE 25 mmFROM GROUND

MRW 26.2 118 118 967 967 7 74.64 4.64 38.07 38.07 0.27 0.27

MRW 26.2 149 149 967 967 39 395.86 5.86 38.07 38.07 1.53 1.53

FWD INNER TYREUNSERVICEABLE

FWD OUTER TYREUNSERVICEABLE

8 FLAT TYRES &50% RIM DAMAGE8 FLAT TYRES &NO RIM DAMAGE

(ASSUME ALL OTHERTYRES ON THE A/C

CONFIGURATION

ARE INTACT)

TYRE CHANGE

WEIGHT(T)

CG(% MAC)

14.88

11.96

11.22

15.00

14.72

14.88 40.51

38.62

38.34

40.78

40.98

40.66

10.51

7.63

6.88

10.66

10.39

10.51

mm in mm in mm in mm in mm in mm in

DOME HEIGHT− A : DISTANCE BETWEEN TYRES− B : DISTANCE BETWEEN BRAKE RODS AND GROUND − C :

DIM AFWD

DIM BFWD

DIM CFWD

A350−900 MLG (1 400 x 530 R23)

A

FWD

A

A

C

B

P_AC_021402_1_0030001_01_00

Main Landing Gear Jacking Point HeightsFIGURE-2-14-2-991-003-A01

2-14-2Page 3

Jun 01/16


AIRCRAFT PERFORMANCE


**ON A/C A350-1000 A350-900

General Information

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

STANDARD DAY TEMPERATURES FOR THE ALTITUDESALTITUDE STANDARD DAY TEMPERATURE

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

3-1-0Page 1

Jun 01/16


3-2-0 Payload/Range - ISA Conditions

**ON A/C A350-1000 A350-900

Payload/Range - ISA Conditions

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

3-2-0Page 1

Jun 01/16


**ON A/C A350-900

0

10203040

RA

NG

E (

nm)

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY. T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

NO

TE

:

IN T

HE

"O

PE

RA

TIN

G M

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

5060

0

RA

NG

E (

km)

MA

XIM

UM

ST

RU

CT

UR

AL

PA

YLO

AD

1 50

050

02

500

3 50

04

500

5 50

06

500

7 50

08

500

9 50

010

500

ST

AN

DA

RD

DA

Y C

ON

DIT

ION

ST

YP

ICA

L IN

TE

RN

AT

ION

AL

FLI

GH

T P

RO

FIL

E95

kg

PE

R P

AS

SE

NG

ER

INC

LUD

ING

BA

GG

AG

EB

AS

IC C

ON

FIG

UR

AT

ION

WIT

H C

RE

W R

ES

T C

OM

PA

RT

ME

NT

S

AN

D O

TH

ER

OP

TIO

NA

L F

EA

TU

RE

S

70

20406080100

120

140

2 00

04

000

6 00

08

000

10 0

0012

000

14 0

0016

000

18 0

00

325

PA

SS

EN

GE

RS

PAYLOAD (x 1 000 kg)

PAYLOAD (x 1 000 lb)P_AC_030200_1_0010001_01_01

Payload/Range - ISA ConditionsFIGURE-3-2-0-991-001-A01

3-2-0Page 2

Jun 01/16


**ON A/C A350-1000

0

10203040

RA

NG

E (

nm)

5060

0

RA

NG

E (

km)

1 50

050

02

500

3 50

04

500

5 50

06

500

7 50

08

500

9 50

010

500

ST

AN

DA

RD

DA

Y C

ON

DIT

ION

ST

YP

ICA

L IN

TE

RN

AT

ION

AL

FLI

GH

T P

RO

FIL

E95

kg

PE

R P

AS

SE

NG

ER

INC

LUD

ING

BA

GG

AG

EB

AS

IC C

ON

FIG

UR

AT

ION

WIT

H C

RE

W R

ES

T C

OM

PA

RT

ME

NT

S

AN

D O

TH

ER

OP

TIO

NA

L F

EA

TU

RE

S

366

PA

SS

EN

GE

RS

70

20406080100

120

140

2 00

04

000

6 00

08

000

10 0

0012

000

14 0

0016

000

18 0

00

MA

XIM

UM

ST

RU

CT

UR

AL

PA

YLO

AD

TH

ES

E C

UR

VE

S A

RE

GIV

EN

FO

R IN

FO

RM

AT

ION

ON

LY. T

HE

AP

PR

OV

ED

VA

LUE

S A

RE

ST

AT

ED

NO

TE

:

IN T

HE

"O

PE

RA

TIN

G M

AN

UA

LS"

SP

EC

IFIC

TO

TH

E A

IRLI

NE

OP

ER

AT

ING

TH

E A

IRC

RA

FT

.

PAYLOAD (x 1 000 kg)

PAYLOAD (x 1 000 lb)P_AC_030200_1_0020001_01_00

Payload/Range - ISA ConditionsFIGURE-3-2-0-991-002-A01

3-2-0Page 3

Jun 01/16


3-3-0 Take-Off Weight Limitation

**ON A/C A350-900

Take-Off Weight Limitation

1. This section provides the take-off weight limitation at ISA conditions and ISA + 15 ˚C (+59 ˚F)conditions on a dry runway.

3-3-0Page 1

Jun 01/16


**ON A/C A350-900

RU

NW

AY

LE

NG

TH

(ft)

TAKE−OFF WEIGHT (x 1 000 kg)

4 92

06

920

8 92

010

920

12 9

2014

920

290

270

250

230

210

190

170

150

RU

NW

AY

LE

NG

TH

(m

)

1 50

02

000

2 50

03

000

3 50

04

000

4 50

05

000

130

TAKE−OFF WEIGHT (x 1 000 lb)

0 ft

2 00

0 ft

4 00

0 ft

6 00

0 ft

8 00

0 ft

586.

6

536.

6

486.

6

436.

6

386.

6

336.

6

286.

6

636.

6

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

DIN

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.

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

MT

OW

P_AC_030300_1_0010001_01_01

ISA ConditionsFIGURE-3-3-0-991-001-A01

3-3-0Page 2

Jun 01/16


**ON A/C A350-900

RU

NW

AY

LE

NG

TH

(ft)

TAKE−OFF WEIGHT (x 1 000 kg)

4 92

06

920

8 92

010

920

12 9

2014

920

290

270

250

230

210

190

170

150

RU

NW

AY

LE

NG

TH

(m

)

1 50

02

000

2 50

03

000

3 50

04

000

4 50

05

000

130

586.

6

536.

6

486.

6

436.

6

386.

6

336.

6

286.

6

TAKE−OFF WEIGHT (x 1 000 lb)

636.

6

0 ft

2 00

0 ft

4 00

0 ft

6 00

0 ft

8 00

0 ft

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

DIN

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.

AIR

PO

RT

PR

ES

SU

RE

ALT

ITU

DE

MT

OW

P_AC_030300_1_0020001_01_01

ISA + 15 ˚C (+59 ˚F) ConditionsFIGURE-3-3-0-991-002-A01

3-3-0Page 3

Jun 01/16


3-4-0 Landing Field Length

**ON A/C A350-900

Landing Field Length

1. This section provides the landing field length on a dry runway.

3-4-0Page 1

Jun 01/16


**ON A/C A350-900

8 00

0 ft

6 00

0 ft

4 00

0 ft

2 00

0 ft

0 ft

2 60

0

REQUIRED LANDING DISTANCE (m)

REQUIRED LANDING DISTANCE (ft)

130

140

150

160

170

180

190

200

210

286.

630

6.6

326.

634

6.6

366.

638

6.6

406.

642

6.6

446.

6

LAN

DIN

G W

EIG

HT

(x

1 00

0 lb

)

LAN

DIN

G W

EIG

HT

(x

1 00

0 kg

)

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

DIN

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.

VA

LID

FO

R A

LL T

EM

PE

RA

TU

RE

S

1 20

0

1 40

0

1 60

0

1 80

0

2 00

0

2 20

0

2 40

0

4 28

0

4 78

0

5 28

0

5 78

0

6 28

0

6 78

0

7 28

0

7 78

0

8 28

0

AIR

FIE

LD E

LEV

AT

ION

P_AC_030400_1_0010001_01_01

Landing Field LengthFIGURE-3-4-0-991-001-A01

3-4-0Page 2

Jun 01/16


3-5-0 Final Approach Speed

**ON A/C A350-900

Final Approach Speed

1. This section provides the final approach speed. It is defined as the indicated airspeed at threshold inthe landing configuration, at the certificated maximum flap setting and maximum landing weight, instandard atmospheric conditions. The approach speed is used to classify the aircraft into an AircraftApproach Category, a grouping of aircraft based on the indicated airspeed at threshold.

2. The final approach speed is 140 kt at a MLW of 205000 kg (451948 lb) and classifies the aircraftinto the Aircraft Approach Category C.

NOTE : This value is given for information only.

3-5-0Page 1

Jun 01/16


GROUND MANEUVERING


**ON A/C A350-1000 A350-900

General Information

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

4-1-0Page 1

Jun 01/16


4-2-0 Turning Radii

**ON A/C A350-900

Turning Radii

1. This section gives the turning radii.

4-2-0Page 1

Jun 01/16


**ON A/C A350-900

P_AC_040200_1_0010001_01_00

R5

R3

R4

R6

R2

60°65°70°

R1

NOTE:FOR TURNING RADII VALUES, REFER TO SHEET 2

Turning Radii(Sheet 1 of 2)

FIGURE-4-2-0-991-001-A01

4-2-0Page 2

Jun 01/16


**ON A/C A350-900

P_AC_040200_1_0010001_02_00

19.620

TYPE OFTURN

2

EFFECTIVESTEERING ANGLE (deg)

STEERINGANGLE (deg)

76.3250

A350−900 TURNING RADII

mft

86.9285

86.0282

R4

113.6373

R5

87.1286

R6

96.0315

WING NOSE TAIL

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

R1 R2 R3RMLG LMLG NLG

24.525258.7193

69.3227

69.6228

96.2316

71.2233

79.7262

29.430246.7153

57.3188

58.9193

84.3277

60.8199

69.0226

34.235238.0125

48.6159

51.5169

75.7248

53.7176

61.5202

39.140231.1102

41.7137

45.9151

68.9226

48.5159

55.9183

43.845225.784

36.3119

41.8137

63.7209

44.7147

51.7170

48.650221.169

31.7104

38.6127

59.2194

41.8137

48.3158

53.155217.457

28.092

36.2119

55.5182

39.6130

45.7150

57.560214.146

24.781

34.3113

52.4172

38.0125

43.5143

61.565211.437

22.072

32.9108

49.8163

36.7121

41.9137

65.07029.230

19.865

31.9105

47.7156

35.9118

40.6133

49.350120.567

31.1102

38.2125

58.6192

41.4136

47.8157

54.155116.654

27.289

35.7117

54.8180

39.2129

45.1148

58.760113.343

23.978

33.8111

51.6169

37.6123

43.0141

63.265110.334

20.969

32.4106

48.7160

36.3119

41.2135

67.57017.725

18.360

31.2103

46.2152

35.3116

39.8130

mftmftmftmftmftmftmftmftmftmft

mftmftmftmftmft

FROM TYPE 1 BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN.

66.172 (MAX)28.528

19.163

31.6104

47.0154

35.6117

40.2132

mft

69.272 (MAX)16.722

17.357

30.9101

45.3149

35.0115

39.2129

mft

Turning Radii(Sheet 2 of 2)

FIGURE-4-2-0-991-001-A01

4-2-0Page 3

Jun 01/16


4-3-0 Minimum Turning Radii

**ON A/C A350-900

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0Page 1

Jun 01/16


**ON A/C A350-900

P_AC_040300_1_0010001_01_00

69.272 (MAX)

TYPE OFTURN

1

EFFECTIVESTEERING ANGLE (deg)

STEERINGANGLE (deg)

28.794

A350−900 MINIMUM TURNING RADII

mft

48.5159

30.9101

R4

45.3149

R5

35.0115

R6

39.2129

WING NOSE TAILX A

66.172 (MAX)228.794

51.1168

31.6104

47.0154

35.6117

40.2132

mft

YR3

NLG

10.936

12.742

NOTE:TYPE 1 TURNS USE: ASYMMETRIC THRUST DURING THE WHOLE TURN; AND DIFFERENTIAL BRAKING

TYPE 2 TURNS USE: SYMMETRIC THRUST DURING THE WHOLE TURN; AND NO DIFFERENTIAL BRAKING AT ALL

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

TO INITIATE THE TURN ONLY

A(MINIMUM TURNING WIDTH)

X

Y

R5

R3

R6

R4

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

4-3-0Page 2

Jun 01/16


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A350-1000 A350-900

Visibility from Cockpit in Static Position

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

4-4-0Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

P_AC_040400_1_0010001_01_00

27°

20°

14.20 m(46.59 ft)

4.63 m(15.19 ft)

VISUAL ANGLES IN VERTICAL

DIMENSIONS ARE APPROXIMATE

105.5°

CAPTAIN FIELD OF VIEW

0.53 m(1 ft 8.88 in)

32°

15° 15°

32°

120°

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 SEEN

PLANE THROUGH PILOTEYE POSITION.

3.04 m(9.97 ft)

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

VISUAL ANGLES IN PLANEPERPENDICULAR TOLONGITUDINAL AXIS.

120°105.5°

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

4-4-0Page 2

Jun 01/16


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A350-1000 A350-900

Introduction

1. This section provides the runway and taxiway turn paths for the following configurations:- 90˚ Turn --- Runway to Taxiway- 135˚ Turn --- Runway to Taxiway- 180˚ Turn on a Runway- 90˚ Turn --- Taxiway to Taxiway- 135˚ Turn --- Taxiway to Taxiway.The turn paths Runway to Taxiway and Taxiway to Taxiway are defined using 2 methods:- Oversteering method,- Cockpit over centerline method.The 180˚ Turn on runway is defined using the following method:- 180˚ Turn using edge of runway method.

4-5-0Page 1

Jun 01/16



**ON A/C A350-1000 A350-900

90˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Jun 01/16


**ON A/C A350-900

P_AC_040501_1_0010001_01_02

APPROX 13.3 m(44 ft)

FILLET R = 25.5 m(85 ft)

TURN R = 45 m(150 ft)

(75 ft)23 m


TAXIWAY

RUNWAY CENTERLINE

NLG PATH

MLG PATH

FAA LEAD−IN FILLETL=75 m (250 ft)

(150 ft)45 m

CENTERLINE

90˚ Turn - Runway to TaxiwayOversteering Method (Sheet 1 of 2)

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

4-5-1Page 2

Jun 01/16


**ON A/C A350-900

P_AC_040501_1_0010001_02_02

APPROX 5 m(16 ft)


TURN R = 45 m(150 ft)

(75 ft)23 m

TAXIWAY CENTERLINE

RUNWAY CENTERLINE

NLG PATH

MLG PATH


(150 ft)45 m

90˚ Turn - Runway to TaxiwayCockpit over Centerline Method (Sheet 2 of 2)

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

4-5-1Page 3

Jun 01/16


**ON A/C A350-1000

APPROX 14 m(45 ft)


TURN R = 45 m(150 ft)

(75 ft)23 m

APPROX 8.5 m(28 ft)

TAXIWAY

RUNWAY CENTERLINE

NLG PATH

MLG PATH

FAA LEAD−IN FILLETL = 75 m (250 ft)

CENTERLINE

(150 ft)45 m

P_AC_040501_1_0020001_01_00


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

4-5-1Page 4

Jun 01/16


**ON A/C A350-1000

APPROX 3 m(10 ft)


TURN R = 45 m(150 ft)

(75 ft)23 m

TAXIWAY CENTERLINE

RUNWAY CENTERLINE

NLG PATH

MLG PATH


(150 ft)45 m

ADDITIONAL FILLETTO MEET 4.5 m (15 ft)EDGE CLEARANCE

P_AC_040501_1_0020001_02_00


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

4-5-1Page 5

Jun 01/16



**ON A/C A350-1000 A350-900

135˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Jun 01/16


**ON A/C A350-900

P_AC_040502_1_0010002_01_02

23 m(75 ft)

TAXIWAY

RUNWAY CENTERLINE

(150 ft)45 m

TURN R = 45 m(150 ft)


APPROX 5.8 m(19 ft)

APPROX 7.6 m(25 ft)

NLG PATH

MLG PATH


CENTERLINE


FIGURE-4-5-2-991-001-B01

4-5-2Page 2

Jun 01/16


**ON A/C A350-900

P_AC_040502_1_0010002_02_02

RUNWAY

TAXIWAY23 m(75 ft)


4.5 m (15 ft) EDGE CLEARANCEADDITIONAL FILLET TO MEET

TURN R = 45 m(150 ft)

APPROX1.6 m (5 ft)

(150 ft)45 m

NLG PATH

MLG PATH


CENTERLINE

CENTERLINE


FIGURE-4-5-2-991-001-B01

4-5-2Page 3

Jun 01/16


**ON A/C A350-1000

23 m(75 ft)

RUNWAY CENTERLINE

(150 ft)45 m

TURN R = 45 m(150 ft)


APPROX 5.5 m(18 ft)

APPROX 6.1 m(20 ft)

NLG PATH

MLG PATH


TAXIWAYCENTERLINE

P_AC_040502_1_0020002_01_00


FIGURE-4-5-2-991-002-B01

4-5-2Page 4

Jun 01/16


**ON A/C A350-1000

RUNWAY

TAXIWAY

23 m(75 ft)


TURN R = 45 m(150 ft)

APPROX1.3 m (5 ft)

(150 ft)45 m

NLG PATH

MLG PATH


CENTERLINE

CENTERLINE


P_AC_040502_1_0020002_02_00


FIGURE-4-5-2-991-002-B01

4-5-2Page 5

Jun 01/16


4-5-3 180˚ Turn on a Runway

**ON A/C A350-1000 A350-900

180˚ Turn on a Runway

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

4-5-3Page 1

Jun 01/16


**ON A/C A350-900

P_AC_040503_1_0010001_01_01

APPROX 48.5 m(159.12 ft)

R4 = 45.3 m(149 ft)

R3 = 30.9 m(101 ft)

R5 = 35 m(115 ft)

4.5 m(15 ft)

4.5 m(15 ft)

RUNWAY CENTERLINE

MLG PATH

WING TIP PATH

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

NOSE TIP PATH

NLG PATH

180˚ Turn on a RunwayFIGURE-4-5-3-991-001-A01

4-5-3Page 2

Jun 01/16


**ON A/C A350-1000


P_AC_040503_1_0020002_01_00

180˚ Turn on a RunwayFIGURE-4-5-3-991-002-B01

4-5-3Page 3

Jun 01/16



**ON A/C A350-1000 A350-900

90˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Jun 01/16


**ON A/C A350-900

P_AC_040504_1_0010001_01_02

TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY





(75 ft)23 m

NLG PATH

MLG PATH

CENTERLINE

90˚ Turn - Taxiway to TaxiwayOversteering Method (Sheet 1 of 2)

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

4-5-4Page 2

Jun 01/16


**ON A/C A350-900

(75 ft)23 m


APPROX 3.9 m(13 ft)

(75 ft)23 m

NLG PATH

MLG PATH



TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

TAXIWAYCENTERLINE

P_AC_040504_1_0010001_02_03

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

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

4-5-4Page 3

Jun 01/16


**ON A/C A350-1000

TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY


APPROX 8.2 m(27 ft)


(75 ft)23 m

NLG PATH

MLG PATH

CENTERLINE


P_AC_040504_1_0020001_01_00


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

4-5-4Page 4

Jun 01/16


**ON A/C A350-1000

TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

TAXIWAY

NLG PATH

MLG PATH

CENTERLINE



(75 ft)23 m


APPROX 1.8 m(6 ft)

(75 ft)23 m

P_AC_040504_1_0020001_02_00


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

4-5-4Page 5

Jun 01/16



**ON A/C A350-1000 A350-900

135˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Jun 01/16


**ON A/C A350-900

TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY

23 m(75 ft)

APPROX 6.9 m(23 ft)


APPROX 8.8 m(29 ft)

NLG PATH

MLG PATH


P_AC_040505_1_0010002_01_02

CENTERLINE


FIGURE-4-5-5-991-001-B01

4-5-5Page 2

Jun 01/16


**ON A/C A350-900

(75 ft)23 m

TAXIWAY

23 m(75 ft)

NLG PATH

MLG PATH

CENTERLINE

APPROX2.5 m (8 ft)



TURN R = 45 m(150 ft)


TAXIWAY CENTERLINE

P_AC_040505_1_0010002_02_03


FIGURE-4-5-5-991-001-B01

4-5-5Page 3

Jun 01/16


**ON A/C A350-1000

TURN R = 45 m(150 ft)

APPROX 4.7 m(15 ft)

APPROX 8.2 m(27 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY

23 m(75 ft)

CENTERLINE



NLG PATH

MLG PATH

P_AC_040505_1_0020001_01_00


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

4-5-5Page 4

Jun 01/16


**ON A/C A350-1000

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY


TURN R = 45 m(150 ft)

APPROX0.5 m (2 ft)

NLG PATH

MLG PATH

CENTERLINE



23 m(75 ft)

P_AC_040505_1_0020001_02_00


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

4-5-5Page 5

Jun 01/16


4-6-0 Runway Holding Bay

**ON A/C A350-1000 A350-900

Runway Holding Bay

1. This section provides the runway holding bay.

4-6-0Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

P_AC_040600_1_0010001_01_00

45 m(150 ft)

23 m(75 ft)

190 m(625 ft)

6.1 m(20 ft)

90 m(300 ft)102 m

(335 ft)

6.1 m(20 ft)

12.2 m(40 ft)

TAXIWAYCENTERLINE

RUNWAYCENTERLINE

MAIN LANDINGGEAR PATH

HOLDINGPOINT

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

Runway Holding BayFIGURE-4-6-0-991-001-A01

4-6-0Page 2

Jun 01/16


4-7-0 Minimum Line-Up Distance Corrections

**ON A/C A350-1000 A350-900

Minimum Line-Up Distance Corrections

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

2. 90˚ Turn on Runway EntryThis section provides the minimum line-up distance correction for a 90˚ turn on runway entry.This maneuver consists in a 90˚ turn at minimum turn radius. It starts with the edge of the MLG ata distance of 4.5 m (15 ft.) from the taxiway edge, and finishes with the aircraft aligned on thecenterline of the runway, FIGURE 4-7-0-991-001-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft.) for this categoryof aircraft as recommended in ICAO Annex 14.

3. 180˚ Turn on Runway Turn PadThis section provides the minimum line-up distance correction for a 180˚ turn on the runway turnpad.This maneuver consists in a 180˚ turn at minimum turn radius on a runway turn pad with standardICAO geometry.It starts with the edge of the MLG at a distance of 4.5 m (15 ft.) from the pavement edge, and itfinishes with the aircraft aligned on the centerline of the runway, FIGURE 4-7-0-991-002-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft.) for this categoryof aircraft as recommended in ICAO Annex 14.

4. 180˚ Turn on Runway WidthThis section provides the minimum line-up distance correction for a 180˚ turn on the runway width.For this maneuver, the pavement width is considered to be the runway width, which is a frozenparameter (45 m (150 ft) and 60 m (200 ft)).As per the standard operating procedures for the ”180˚ turn on runway” (described in the FlightCrew Operating Manual), the aircraft is initially angled with respect to the runway centerline whenstarting the 180˚ turn, FIGURE 4-7-0-991-003-A.The value of this angle depends on the aircraft type and is mentioned in the FCOM.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft.) for this categoryof aircraft as recommended in ICAO Annex 14.

4-7-0Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

ASDA

4.5 m(15 ft)

TAXIWAYCENTERLINE

4.5 m(15 ft)

TODA

90° TURN ON RUNWAY ENTRY

AIRCRAFTTYPE

MAXSTEERING

ANGLE MINIMUM LINE−UPDISTANCE CORRECTIONON TODA ON ASDA

MINIMUM LINE−UPDISTANCE CORRECTION

72°A350−900 72 ft21.8 m 166 ft50.5 mON TODA ON ASDA

45 m (150 ft)WIDE RUNWAY


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

RUNWAY CENTERLINE

84 ft25.7 m 178 ft54.3 m75°A350−1000 72 ft21.8 m 179 ft54.4 m106 ft32.2 m 212 ft64.7 m

P_AC_040700_1_0010001_01_02

90˚ Turn on Runway EntryFIGURE-4-7-0-991-001-A01

4-7-0Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

180° TURN ON RUNWAY TURN PAD

AIRCRAFTTYPE

MAXSTEERING



72°A350−900 122 ft37.2 m 216 ft65.9 m 117 ft35.7 m 211 ft64.4 mON TODA ON ASDA

REQUIRED MINIMUMPAVEMENT WIDTH

206 ft62.9 m



MINIMUM PAVEMENT WIDTH

TODA

ASDA

RUNWAY CENTERLINE

4.5 m(15 ft)

4.5 m(15 ft)

4.5 m(15 ft)


75°A350−1000 144 ft43.9 m 250 ft76.3 m 129 ft39.4 m 236 ft71.9 m

P_AC_040700_1_0020001_01_02

180˚ Turn on Runway Turn PadFIGURE-4-7-0-991-002-A01

4-7-0Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

ASDA

4.5 m(15 ft)

> 4.5 m(15 ft)

4.5 m(15 ft)

TODA

180° TURN ON RUNWAY WIDTH

AIRCRAFTTYPE

MAXSTEERING



72°A350−900 156 ft47.5 m 250 ft76.2 mON TODA ON ASDA



NOT POSSIBLE


RUNWAY CENTERLINE

75°A350−1000 NOT POSSIBLE

25°

P_AC_040700_1_0030001_01_02

180˚ Turn on Runway WidthFIGURE-4-7-0-991-003-A01

4-7-0Page 4

Jun 01/16


4-8-0 Aircraft Mooring

**ON A/C A350-1000 A350-900

Aircraft Mooring

1. This section provides information on aircraft mooring.

4-8-0Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

TOWING FITTING

STRAP

MOORING KIT

SAFETY LEVER

MOORING POINT

HOOKWARNING FLAG

TENSIONER

A

QUICK RELEASEPIN

A

P_AC_040800_1_0010001_01_01

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

4-8-0Page 2

Jun 01/16


TERMINAL SERVICING

5-1-0 Aircraft Servicing Arrangements

**ON A/C A350-1000 A350-900

Aircraft Servicing Arrangements

1. This section provides typical ramp layouts, showing the various GSE items in position during typicalturn-round scenarios.These ramp layouts show typical arrangements only. Each operator will have its own specificrequirements/regulations for positioning and operation on the ramp.

This table provides the symbols used on servicing diagrams.

GROUND SUPPORT EQUIPMENT

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

5-1-0Page 1

Jun 01/16


5-1-1 Typical Ramp Layout (Open Apron)

**ON A/C A350-1000 A350-900

Typical Ramp Layout (Open Apron)

1. This section provides the typical ramp layout (Open Apron).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).

5-1-1Page 1

Jun 01/16


**ON A/C A350-900

ULD

TOW

GPU

LDCL

CAT

FUEL

BULK

WV

ULD

CAT

CB

LDCL

AC

CAT

CLEAN

AS

PS

PS

STAND SAFETY LINE LV

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

P_AC_050101_1_0010001_01_03

Typical Ramp Layout (Open Apron)FIGURE-5-1-1-991-001-A01

5-1-1Page 2

Jun 01/16


**ON A/C A350-1000

ULD

TOWGPU

LDCL

CAT

FUEL

BULK

WV

LV

ULD

CAT

CB

LDCL

AC

CAT

CLEAN

AS

PS

PS

STAND SAFETY LINE

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

P_AC_050101_1_0030001_01_00

Typical Ramp Layout (Open Apron)FIGURE-5-1-1-991-003-A01

5-1-1Page 3

Jun 01/16


5-1-2 Typical Ramp Layout (Gate)

**ON A/C A350-1000 A350-900

Typical Ramp Layout (Gate)

1. This section provides the baseline ramp layout (gate).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.50 m (24.61 ft.)from the 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

Jun 01/16


**ON A/C A350-900

ULD

GPU

LDCL

CAT

FUEL

BULK

LV

ULDCB

CAT

CLEAN

PBB

PBB

STAND SAFETY LINE

ASTOW

AC

LDCL

WV CAT

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

P_AC_050102_1_0010001_01_03

Typical Ramp Layout (Gate)FIGURE-5-1-2-991-001-A01

5-1-2Page 2

Jun 01/16


**ON A/C A350-1000

ULD

TOWGPU

LDCL

CAT

FUEL

BULK

WV

LV

ULD

CAT

CB

LDCL

CAT

CLEAN

AS

PBB

PBB

STAND SAFETY LINE

AC

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

P_AC_050102_1_0030001_01_00

Typical Ramp Layout (Gate)FIGURE-5-1-2-991-003-A01

5-1-2Page 3

Jun 01/16


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

**ON A/C A350-1000 A350-900

Terminal Operations - Full Servicing Turn Round Time

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

**ON A/C A350-900

2. Assumptions used for full servicing turn round time chart

A. PASSENGER HANDLING315 pax: 48 B/C + 267 Y/C.All passengers deplane and board the aircraft.2 Passenger Boarding Bridges (PBB) used at doors L1 and L2.Equipment positioning + opening door = +3 min.Closing door + equipment removal = +3 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 158 pax at door L1- 157 pax at door L2- Deplaning rate = 25 pax/min per door- Priority deplaning for premium passengers.Boarding:- 158 pax at door L1- 157 pax at door L2- Boarding rate = 15 pax/min per door- Last Pax Seated allowance (LPS) + headcounting = +4 min.

B. CARGO2 cargo loaders + 1 belt loader.Opening door + equipment positioning = +2.5 min.Equipment removal + closing door = +2.5 min.100% cargo exchange:- FWD cargo compartment: 8 containers (LD3) + 4 (96 in) pallets- AFT cargo compartment: 4 containers (LD3) + 4 (96 in) pallets- Bulk compartment: 1000 kg (2205 lb).Container unloading/loading times:- Unloading = 1.2 min/container- Loading = 1.4 min/container.

5-2-0Page 1

Jun 01/16


Bulk unloading/loading times:- Unloading = 110 kg/min (243 lb/min)- Loading = 95 kg/min (209 lb/min).Pallet unloading/loading times:- Unloading = 2.4 min/pallet- Loading = 2.8 min/pallet.

C. REFUELLING100000 L (26418 USgal), 4 hoses, 40 psi (2.76 bar).Dispenser positioning + connection = +8 min.Disconnection + dispenser removal = +8 min.

D. CLEANINGCleaning is performed in available time.

E. CATERING3 catering trucks for servicing galleys simultaneously at doors R1, R2 and R4.Equipment positioning + opening door = +5 min.Closing door + equipment removal = +3 min.Full Size Trolley Equivalent (FSTE) to unload and load: 40 FSTE- 10 FSTE at door R1- 7 FSTE at door R2- 23 FSTE at door R4.Time for trolley exchange = 1.5 min per FSTE.

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges/Stairs: t0=0- Other equipment: t = t0 +1 min.Ground Power Unit (GPU): up to 2 × 90 kVA.Air Conditioning: up to 2 hoses.Potable water servicing: 100% uplift, 1060 L (280 USgal).Waste water servicing: draining and rinsing.

**ON A/C A350-1000

3. Assumptions used for full servicing turn round time chart.

A. PASSENGER HANDLING369 pax: 54 B/C + 315 Y/C.All passengers deplane and board the aircraft.

5-2-0Page 2

Jun 01/16


2 Passenger Boarding Bridges (PBB) used at doors L1 and L2.Equipment positioning + opening door = +3 min.Closing door + equipment removal = +3 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 184 pax at door L1- 185 pax at door L2- Deplaning rate = 25 pax/min per door- Priority deplaning for premium passengers.Boarding:- 54 pax at door L1- 315 pax at door L2- Boarding rate = 15 pax/min per door- Last Pax Seated allowance (LPS) + headcounting = +4 min.

B. CARGO2 cargo loaders + 1 belt loader.Opening door + equipment positioning = +2.5 min.Equipment removal + closing door = +2.5 min.100% cargo exchange:- FWD cargo compartment: 6 containers (LD3) + 6 (96 in) pallets- AFT cargo compartment: 14 containers (LD3) + 2 (96 in) pallets- Bulk compartment 1000 kg (2205 lb).Container unloading/loading times:- Unloading = 1.2 min/container- Loading = 1.4 min/container.Bulk unloading/loading times:- Unloading = 110 kg/min (243 lb/min).- Loading = 95 kg/min (209 lb/min).Pallet unloading/loading times:- Unloading = 2.4 min/pallet- Loading = 2.8 min/pallet.

C. REFUELLING100000 L (26418 USgal), 4 hoses, 40 psi (2.76 bar).Dispenser positioning + connection = +8 min.Disconnection + dispenser removal = +8 min.


5-2-0Page 3

Jun 01/16


E. CATERINGcatering trucks for servicing galleys simultaneously at doors R1, R2 and R4.Equipment positioning + opening door = +5 min.Closing door + equipment removal = +3 min.Full Size Trolley Equivalent (FSTE) to unload and load: 45 FSTE- 12 FSTE at door R1- 8 FSTE at door R2- 4 FSTE at door R3 (Stowage area)- 21 FSTE at door R4.Time for trolley exchange = 1.5 min per FSTE.

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges/Stairs: t0=0- Other equipment: t = t0 +1 min.Ground Power Unit (GPU): up to 2 × 90 kVA.Air Conditioning: up to 2 hoses.Potable water servicing: 100% uplift, 1060 L (280 USgal).Waste water servicing: draining and rinsing.

5-2-0Page 4

Jun 01/16


**ON A/C A350-900

0 10 20 30 40 50 60 70

DEPLANING/BOARDING AT L1

HEADCOUNTING

CATERING AT R1

CLEANING

CARGO FWD CC

BULK

REFUELING

POTABLE WATER SERVICING

WASTE WATER SERVICING


CATERING AT R2

CATERING AT R4

CARGO AFT CC

TRT: 61 min

GSE POSITIONING/REMOVAL

ACTIVITY

CRITICAL PATH

AVAILABLE TIME

P_AC_050200_1_0010001_01_03

Full Servicing Turn Round Time ChartFIGURE-5-2-0-991-001-A01

5-2-0Page 5

Jun 01/16


**ON A/C A350-1000


HEADCOUNTING

CATERING AT R1

CLEANING

CARGO FWD CC

BULK

REFUELING




CATERING AT R2

CATERING AT R4

CARGO AFT CC

AVAILABLE TIME

0 10 20 30 40 50 60 70 80

TRT: 70 min


ACTIVITY

CRITICAL PATH

P_AC_050200_1_0040001_01_00

Full Servicing Turn Round Time ChartFIGURE-5-2-0-991-004-A01

5-2-0Page 6

Jun 01/16


5-3-0 Terminal Operations - Transit Turn Round Time

**ON A/C A350-1000 A350-900

Terminal Operations - Transit Turn Round Time

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

**ON A/C A350-900

2. Assumptions used for transit turn round time chart

A. PASSENGER HANDLING315 pax: 48 B/C + 267 Y/C.50% passengers deplane and board the aircraft.1 Passenger Boarding Bridge (PBB) used at door L1.Equipment positioning + opening door = +3 min.Closing door + equipment removal = +3 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 158 pax at door L1- Deplaning rate = 25 pax/min per door.Boarding:- 158 pax at door L1- Boarding rate = 15 pax/min per door- Last Pax Seated allowance (LPS) + headcounting = + 4 min.

B. CARGO1 cargo loader + 1 belt loader.Opening door + equipment positioning = +2.5 min.Equipment removal + closing door = +2.5 min.50% cargo exchange:- AFT cargo compartment: 2 containers (LD3) + 2 (96 in) pallets- Bulk compartment: 500 kg (1102 lb).Container unloading/loading times:- Unloading = 1.2 min/container- Loading = 1.4 min/container.Bulk unloading/loading times:- Unloading = 110 kg/min (243 lb/min)- Loading = 95 kg/min (209 lb/min).

5-3-0Page 1

Jun 01/16


Pallet unloading/loading times:- Unloading = 2.4 min/pallet- Loading = 2.6 min/pallet.

C. REFUELINGNo refueling.


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

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges: t0 = 0- Other equipment: t = t0 + 1 min.Ground Power Unit (GPU): up to 2 × 90 kVA.Air conditioning: up to 2 hoses.No potable water servicing.No waste water servicing.

**ON A/C A350-1000

3. Assumptions used for transit turn round time char

A. PASSENGER HANDLING369 pax: 54 B/C + 315 Y/C.50% passengers deplane and board the aircraft.1 Passenger Boarding Bridge (PBB) used at door L1.Equipment positioning + opening door = +3 min.Closing door + equipment removal = +3 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 184 pax at door L1- Deplaning rate = 25 pax/min per door.Boarding:- 184 pax at door L1- Boarding rate = 15 pax/min per door- Last Pax Seated allowance (LPS) + headcounting = + 4 min.

5-3-0Page 2

Jun 01/16


B. CARGO1 cargo loader + 1 belt loader.Opening door + equipment positioning = +2.5 min.Equipment removal + closing door = +2.5 min.50% cargo exchange:- FWD cargo compartment: 3 containers (LD3) + 3 (96 in) pallets- AFT cargo compartment: 7 containers (LD3) + 1 (96 in) pallets- Bulk compartment: 500 kg (1102 lb).Container unloading/loading times:- Unloading = 1.2 min/container- Loading = 1.4 min/container.Bulk unloading/loading times:- Unloading = 110 kg/min (243 lb/min).- Loading = 95 kg/min (209 lb/min).Pallet unloading/loading times:- Unloading = 2.4 min/pallet- Loading = 2.6 min/pallet.

C. REFUELINGNo refueling.


E. CATERINGcatering trucks for servicing galleys simultaneously at doors R1, R2 and R4.Equipment positioning + opening door = +5 min.Closing door + equipment removal = +3 min.Full Size Trolley Equivalent (FSTE) to unload and load: 22.5 FSTE- 6 FSTE at door R1- 4 FSTE at door R2- 2 FSTE at door R3 (Stowage area)- 10.5 FSTE at door R4.Time for trolley exchange = 1.5 min per FSTE.

F. GROUND HANDLING/GENERAL SERVICINGStart of operations:- Bridges: t0 = 0- Other equipment: t = t0 + 1 min.Ground Power Unit (GPU): up to 2 × 90 kVA.Air conditioning: up to 2 hoses.

5-3-0Page 3

Jun 01/16


Potable water servicing: 25% uplift, 265 L (70 USgal).Waste water servicing: draining and rinsing.

5-3-0Page 4

Jun 01/16


**ON A/C A350-900

0 5 10 15 20 25 30 35


CATERING

BULK

HEADCOUNTING

CLEANING

CARGO AFT CC

TRT: 30 min

AVAILABLE TIME

AVAILABLE TIME

ACTIVITY


P_AC_050300_1_0010002_01_02

Transit Turn Round Time ChartFIGURE-5-3-0-991-001-B01

5-3-0Page 5

Jun 01/16


**ON A/C A350-1000


CATERING AT R1

CATERING AT R2

CARGO FWD CC

CARGO AFT CC



HEADCOUNTING

CATERING AT R4

CLEANING

BULK

0 5 10 15 20 25 30 35 40 45 50

AVAILABLE TIME

TRT: 46 min


ACTIVITY

CRITICAL PATH

P_AC_050300_1_0020001_01_00

Transit Turn Round Time ChartFIGURE-5-3-0-991-002-A01

5-3-0Page 6

Jun 01/16


5-4-0 Ground Service Connections Layout

**ON A/C A350-1000 A350-900

Ground Service Connections Layout

1. This section provides the ground service connections layout.

5-4-0Page 1

Jun 01/16


**ON A/C A350-900

10 − REFUEL/DEFUEL COUPLINGS(OPTIONAL−LH WING)

11 − OVERPRESSURE PROTECTOR12 − NACA FLAME ARRESTOR13 − MLG GROUNDING (EARTHING) POINT14 − GREEN HYDRAULIC−SYSTEM SERVICE PANEL15 − REFUEL/DEFUEL CONTROL PANEL16 − POTABLE WATER SERVICE PANEL17 − WASTE WATER SERVICE PANEL18 − APU OIL SERVICING

1 − NLG GROUNDING (EARTHING) POINT2 − GROUND ELECTRICAL POWER CONNECTORS3 − OXYGEN SERVICING4 − LOW PRESSURE AIR PRE−CONDITIONING5 − HIGH PRESSURE AIR PRE−CONDITIONING6 − YELLOW HYDRAULIC−SYSTEM SERVICE PANEL7 − ENGINE OIL SERVICING8 − STARTER OIL SERVICING9 − VFG OIL SERVICING

12

4

7

89

10

111415

11

10 7 89 6

13

1617

18

12

12

5

3

P_AC_050400_1_0010001_01_03

Ground Service Connections LayoutFIGURE-5-4-0-991-001-A01

5-4-0Page 2

Jun 01/16


**ON A/C A350-1000

10 − REFUEL/DEFUEL COUPLINGS(OPTIONAL−LH WING)

11 − OVERPRESSURE PROTECTOR12 − NACA FLAME ARRESTOR13 − MLG GROUNDING (EARTHING) POINT14 − GREEN HYDRAULIC−SYSTEM SERVICE PANEL15 − REFUEL/DEFUEL CONTROL PANEL16 − POTABLE WATER SERVICE PANEL17 − WASTE WATER SERVICE PANEL18 − APU OIL SERVICING

1 − NLG GROUNDING (EARTHING) POINT2 − GROUND ELECTRICAL POWER CONNECTORS3 − OXYGEN SERVICING4 − LOW PRESSURE AIR PRE−CONDITIONING5 − HIGH PRESSURE AIR PRE−CONDITIONING6 − YELLOW HYDRAULIC−SYSTEM SERVICE PANEL7 − ENGINE OIL SERVICING8 − STARTER OIL SERVICING9 − VFG OIL SERVICING

12

4

7

89

10

111415

11

10 7 89 6

13

18

12

12

5

3

1617

P_AC_050400_1_0020001_01_00

Ground Service Connections LayoutFIGURE-5-4-0-991-002-A01

5-4-0Page 3

Jun 01/16


5-4-1 Grounding (Earthing) Points

**ON A/C A350-1000 A350-900

Grounding (Earthing) Points

**ON A/C A350-900

1. Grounding (Earthing) Point Locations

DISTANCEFROM AIRCRAFT CENTERLINE

AFT OF NOSELH SIDE RH SIDE

MEAN HEIGHTFROM GROUND

On Nose LandingGear leg

4.42 m(14.50 ft.)

0.07 m(0.23 ft.)

1.06 m(3.48 ft.)

On left MainLanding Gear leg

32.95 m(108.10 ft.)

5.59 m(18.34 ft.)

1.55 m(5.09 ft.)

On right MainLanding Gear leg

32.95 m(108.10 ft.)

5.59 m(18.34 ft.)

1.55 m(5.09 ft.)

A. The grounding (earthing) stud on each landing gear leg is designed for use with a clip-onconnector (such as an Appleton TGR).

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

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

**ON A/C A350-1000

2. Grounding (Earthing) Point Locations

DISTANCEFROM AIRCRAFT CENTERLINE



On Nose LandingGear leg

4.42 m(14.50 ft.)

0.07 m(0.23 ft.)

1.80 m(5.91 ft.)

On left MainLanding Gear leg

36.75 m(120.57 ft.)

5.59 m(18.34 ft.)

1.55 m(5.09 ft.)

On right MainLanding Gear leg

36.75 m(120.57 ft.)

5.59 m(18.34 ft.)

1.55 m(5.09 ft.)

5-4-1Page 1

Jun 01/16


A. The grounding (earthing) stud on each landing gear leg is designed for use with a clip-onconnector (such as an Appleton TGR).

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

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

5-4-1Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

A

B

C

B

GROUNDING (EARTHING) POINT

C

A

P_AC_050401_1_0010001_01_01

Grounding (Earthing) Point - NLGFIGURE-5-4-1-991-001-A01

5-4-1Page 3

Jun 01/16


**ON A/C A350-900

A

A

A

B

C

LH SHOWN


B

C

RH SYMMETRICAL

P_AC_050401_1_0020001_01_00

Grounding (Earthing) Point - MLGFIGURE-5-4-1-991-002-A01

5-4-1Page 4

Jun 01/16


**ON A/C A350-1000

A

B

C

LH SHOWN


RH SYMMETRICAL

A

A

B

C

P_AC_050401_1_0030001_01_00

Grounding (Earthing) Point - MLGFIGURE-5-4-1-991-003-A01

5-4-1Page 5

Jun 01/16


5-4-2 Hydraulic Servicing

**ON A/C A350-1000 A350-900

Hydraulic Servicing

**ON A/C A350-900

1. Hydraulic ServicingThe nominal operating pressure is 344.75 bar (5000 psi).

A. Access

DISTANCEFROM AIRCRAFT CENTERLINEACCESS



Green GroundService Panel:Access Door 197LB

36.37 m(119.32 ft.)

0.61 m(2.00 ft.)

2.39 m(7.84 ft.)

Yellow GroundService Panel:Access Door 194KB

30.35 m(99.57 ft.)

1.51 m(4.95 ft.)

2.24 m(7.35 ft.)

B. Reservoir Pressurization- One 1/4 in. ISO 4570 connector.

C. Reservoir FillingCentralized filling capability is on the Green ground service panel.Filling: Ground pressurized supply or hand pump.

D. Ground TestOn each ground service panel:- One self-sealing connector (suction)- One self-sealing connector (delivery).

**ON A/C A350-1000

2. Hydraulic ServicingThe nominal operating pressure is 344.74 bar (5000 psi).

A. Access




Green GroundService Panel:Access Door197LB

40.18 m(131.82 ft.)

0.61 m(2.00 ft.)

2.24 m(7.35 ft.)

5-4-2Page 1

Jun 01/16





Yellow GroundService Panel:Access Door194KB

34.15 m(112.04 ft.)

1.51 m(4.95 ft.)

2.12 m(6.96 ft.)

B. Reservoir Pressurization- One 1/4 in. ISO 4570 connector.

C. Reservoir FillingCentralized filling capability is on the Green ground service panel.Filling: Ground pressurized supply or hand pump.

D. Ground TestOn each ground service panel:- One self-sealing connector (suction)- One self-sealing connector (delivery).

**ON A/C A350-1000 A350-900

3. Technical Specifications

A. The hydraulic ground equipment must be able to start with the aircraft hydraulic circuit notpressurized.

B. The hydraulic ground equipment must be able to permanently operate with the aircraft reservoirpressures varying between 2.0 bar (29 psi) and 5 bar (73 psi).

C. After ground equipment shutdown, no further fluid exchange must occur between the aircraftreservoir and the ground equipment.

5-4-2Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

GROUND SUPPLY

Z190

GROUND TEST PRESSURECONNECTION

GROUND TEST SUCTIONCONNECTION

A

197LBA

P_AC_050402_1_0010001_01_01

Green Ground Service PanelFIGURE-5-4-2-991-001-A01

5-4-2Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

GROUND TEST PRESSURECONNECTION GROUND TEST SUCTION

CONNECTION

A

194KB

A

Z190

P_AC_050402_1_0020001_01_01

Yellow Ground Service PanelFIGURE-5-4-2-991-002-A01

5-4-2Page 4

Jun 01/16


5-4-3 Electrical Servicing

**ON A/C A350-1000 A350-900

Electrical Servicing

1. A/C External Power




A/C ExternalPower:Access Door 122AR

6.63 m(21.75 ft.)

0.91 m(2.99 ft.)

2.58 m(8.46 ft.)


A. External Power Receptacle:- Two standard ISO 461 Style3 -- 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.

3. Tow Truck Power




NLG Service Panel:2GN

4.35 m(14.27 ft.)

0.15 m(0.49 ft.)

1.8 m(5.91 ft.)


A. Power Supply:- Two-Phase, 115 V, 400 Hz- 28V DC.

B. Electrical Connector for Servicing:- Bernier, 22--11--10--13 Connector.

C. Pin Allocation:

Pin IdentificationA 28V DCB 0V DCD 115V AC

5-4-3Page 1

Jun 01/16


Pin IdentificationE 0V ACG PWR SPLYH INT LOCK

NOTE : The power cable should be extendable in order to guarantee fit and non-interferencewith nose gear nor tow vehicle during the pick-up and the towing process. Theconnector shall be secured against pull-out by means of straps against the nose gear.

**ON A/C A350-900

5. A/C Emergency Generation




RAT Safety-PinInstallation:Access Panel198VR

39.48 m(129.53 ft.)

2.50 m(8.2 ft.)

2.91 m(9.55 ft.)

**ON A/C A350-1000

6. A/C Emergency Generation




RAT Safety-PinInstallation:Access Panel198VR

44.00 m(144.36 ft.)

2.50 m(8.2 ft.)

2.91 m(9.55 ft.)

5-4-3Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

122AR

A

925VU

FWD

A

ELECTRICAL POWERRECEPTACLES

P_AC_050403_1_0010001_01_01

Electrical Service PanelFIGURE-5-4-3-991-001-A01

5-4-3Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

198VR

198QR

198PR

A

B

SAFETY PIN

A

B

RAT RETRACTED

RAT EXTENDED

Z190

P_AC_050403_1_0030001_01_01

RATFIGURE-5-4-3-991-003-A01

5-4-3Page 4

Jun 01/16


5-4-4 Oxygen Servicing

**ON A/C A350-1000 A350-900

Oxygen Servicing

1. GeneralThe A350 XWB oxygen servicing is designed to supply oxygen to the cockpit and the cabin.

2. Technical Specifications- Refilling of the oxygen sources is accomplished by the replacement of the units.- An optional filling port and associated devices can be installed at the rear triangular area of the

FWD cargo door to allow in-situ flight crew oxygen replenishment.

5-4-4Page 1

Jun 01/16


**ON A/C A350-900

Z130

FR20

FR30

B

A

A

B

CREW OXYGEN

CREW OXYGENFILLING PORT

FILLING GAGE

FR28

FR29

P_AC_050404_1_0010001_01_00

Oxygen SystemFIGURE-5-4-4-991-001-A01

5-4-4Page 2

Jun 01/16


**ON A/C A350-900

B

OXYGENCOMPARTMENT−CAPT

OXYGENCOMPARTMENT−F/O

C

A

A

Z130

FR21FR20

FR32 FR33

C

B

P_AC_050404_1_0020001_01_00

Crew Oxygen Storage - LocationFIGURE-5-4-4-991-002-A01

5-4-4Page 3

Jun 01/16


5-4-5 Fuel Servicing

**ON A/C A350-1000 A350-900

Fuel Servicing

**ON A/C A350-900

1. Refuel/Defuel Control Panel




Refuel/DefuelControl Panel:Access Door 197KB

36.20 m(118.77 ft.) On centerline

2.18 m(7.15 ft.)

2. Refuel/Defuel Connectors




Refuel/DefuelCoupling, Left(Optional):Access Door 523EB

32.57 m(106.86 ft.)

15.83 m(51.94 ft.)

5.50 m(18.04 ft.)

Refuel/DefuelCoupling, Right:Access Door 623EB

32.57 m(106.86 ft.)

15.83 m(51.94 ft.)

5.50 m(18.04 ft.)

A. Refuel/Defuel couplings:- Two standard 2.5 in. ISO 45 connections on the right wing,- Two standard 2.5 in. ISO 45 connections on the left wing (optional).

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

3. Overpressure Protector and NACA Flame Arrestor

FROM AIRCRAFT CENTERLINEACCESS AFT OF NOSE

LH SIDE RH SIDEMEAN HEIGHTFROM GROUND

OverpressureProtector

38.24 m(125.46 ft.)

22.33 m(73.26 ft.)

22.33 m(73.26 ft.)

6.13 m(20.11 ft.)

NACA FlameArrestor

38.69 m(126.94 ft.)

23.07 m(75.69 ft.)

23.07 m(75.69 ft.)

6.19 m(20.31 ft.)

5-4-5Page 1

Jun 01/16


**ON A/C A350-1000

4. Refuel/Defuel Control Panel




Refuel/DefuelControl Panel:Access Door 197KB


2.18 m(7.15 ft.)

5. Refuel/Defuel Connectors




Refuel/DefuelCoupling, Left(Optional):Access Door 523EB

36.49 m(119.72 ft.)

15.83 m(51.94 ft.)

5.50 m(18.04 ft.)

Refuel/DefuelCoupling, Right:Access Door 623EB

36.49 m(119.72 ft.)

15.83 m(51.94 ft.)

5.50 m(18.04 ft.)

A. Refuel/Defuel couplings:- Two standard 2.5 in. ISO 45 connections on the right wing,- Two standard 2.5 in. ISO 45 connections on the left wing (optional).

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

6. Overpressure Protector and NACA Flame Arrestor

FROM AIRCRAFT CENTERLINEACCESS AFT OF NOSE

LH SIDE RH SIDEMEAN HEIGHTFROM GROUND

OverpressureProtector

42.05 m(137.96 ft.)

22.33 m(73.26 ft.)

22.33 m(73.26 ft.)

6.13 m(20.11 ft.)

NACA FlameArrestor

42.50 m(139.44 ft.)

23.07 m(75.69 ft.)

23.07 m(75.69 ft.)

6.19 m(20.31 ft.)

5-4-5Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

A

A

TYPICAL LAYOUT11QU

197KB

Z190

P_AC_050405_1_0010001_01_01

Refuel/Defuel Control PanelFIGURE-5-4-5-991-001-A01

5-4-5Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

523EB623EB

A

Z500Z600

ARH SHOWN

LH SYMMETRICAL

01

NOTE:01 LH OPTIONAL

REFUEL/DEFUEL COUPLING

RIB15RIB16

P_AC_050405_1_0020002_01_01

Refuel/Defuel CouplingsFIGURE-5-4-5-991-002-B01

5-4-5Page 4

Jun 01/16


**ON A/C A350-1000 A350-900

NACA INTAKE

NACA DUCT PANEL

543CB (643CB)

Z500 (Z600)

A

A

TANK OVERPRESSUREDISC

OVERPRESSURE PANEL

LH SHOWNRH SYMMETRICAL

RIB27

543DB (643DB)

RIB25

P_AC_050405_1_0030001_01_01

Overpressure Protectors and NACA Flame ArrestorFIGURE-5-4-5-991-003-A01

5-4-5Page 5

Jun 01/16


5-4-6 Pneumatic Servicing

**ON A/C A350-1000 A350-900

Pneumatic Servicing

**ON A/C A350-900

1. Low Pressure Connectors




Access Door 193CB23.58 m(77.36 ft.)

1.05 m(3.44 ft.)

2.59 m(8.50 ft.)

Access Door 194CR23.58 m(77.36 ft.)

1.87 m(6.14 ft.)

2.87 m(9.42 ft.)

A. Connectors:- Two standard 8 in. SAE AS4262 type B connections.

2. High Pressure Connectors




Access Door 193KB26.81 m(87.96 ft.) On Centerline

2.06 m(6.76 ft.)

A. Connectors:- Two standard 3 in. ISO 2026 connections.

**ON A/C A350-1000

3. Low Pressure Connectors




Access Door 193CB27.39 m(89.86 ft.)

1.05 m(3.44 ft.)

2.44 m(8.01 ft.)

Access Door 194CR27.39 m(89.86 ft.)

1.86 m(6.10 ft.)

2.57 m(8.43 ft.)

A. Connectors:- Two standard 8 in. SAE AS4262 type B connections.

5-4-6Page 1

Jun 01/16


4. High Pressure Connectors




Access Door 193KB30.77 m(100.95 ft.) On Centerline

2.06 m(6.76 ft.)

A. Connectors:- Two standard 3 in. ISO 2026 connections.

5-4-6Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

LP CONNECTOR

193CB

A

Z190

194CRA

P_AC_050406_1_0010001_01_01

Low Pressure Ground ConnectorsFIGURE-5-4-6-991-001-A01

5-4-6Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

HP CONNECTOR

A

Z190

193KB

A

P_AC_050406_1_0020001_01_01

High Pressure Ground ConnectorsFIGURE-5-4-6-991-002-A01

5-4-6Page 4

Jun 01/16


5-4-7 Oil Servicing

**ON A/C A350-1000 A350-900

Engine Oil Servicing

**ON A/C A350-900

1. Engine Oil Servicing




Engine 1:Access Door 415BR

24.75 m(81.20 ft.)

8.60 m(28.22 ft.)

3.23 m(10.60 ft.)


24.68 m(80.97 ft.)

12.29 m(40.32 ft.)

3.23 m(10.60 ft.)

**ON A/C A350-1000

2. Engine Oil Servicing





28.56 m(93.70 ft.)

8.60 m(28.22 ft.)

3.23 m(10.60 ft.)


28.49 m(93.47 ft.)

12.29 m(40.32 ft.)

3.23 m(10.60 ft.)

5-4-7Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

OIL LEVEL SIGHTGLASS

A

OIL FILLER CAP

OIL TANK

A

(ENGINE 2)(ENGINE 1)

TYPICAL

425BR415BR

P_AC_050407_1_0040001_01_00

Engine Oil ServicingFIGURE-5-4-7-991-004-A01

5-4-7Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

VFG Oil Servicing

**ON A/C A350-900

1. VFG Oil Servicing




Engine 1:Fan Cowl 415AL

24.32 m(79.79 ft.)

11.02 m(36.15 ft.)

1.22 m(4.00 ft.)


24.34 m(79.86 ft.)

9.86 m(32.35 ft.)

1.22 m(4.00 ft.)

**ON A/C A350-1000

2. VFG Oil Servicing





28.13 m(92.29 ft.)

11.02 m(36.15 ft.)

1.22 m(4.00 ft.)


28.15 m(92.36 ft.)

9.86 m(32.35 ft.)

1.22 m(4.00 ft.)

5-4-7Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

OVERFLOW/STANDPIPE

DISCONNECTRESET HANDLE

DRAINFILTER BOWL

PRESSURE FILL

AB

B

C

A

C

SIGHT GLASS

BTYPICAL

P_AC_050407_1_0090001_01_00

VFG Oil ServicingFIGURE-5-4-7-991-009-A01

5-4-7Page 4

Jun 01/16


**ON A/C A350-1000 A350-900

Starter Oil Servicing

**ON A/C A350-900

1. Starter Oil Servicing





24.60 m(80.71 ft.)

10.57 m(34.68 ft.)

1.08 m(3.54 ft.)


24.60 m(80.71 ft.)

10.31 m(33.83 ft.)

1.08 m(3.54 ft.)

**ON A/C A350-1000

2. Starter Oil Servicing





28.41 m(93.21 ft.)

10.57 m(34.68 ft.)

1.08 m(3.54 ft.)


28.41 m(93.21 ft.)

10.31 m(33.83 ft.)

1.08 m(3.54 ft.)

5-4-7Page 5

Jun 01/16


**ON A/C A350-1000 A350-900

PRESSUREFILL PORT

PRESSURE SPILLPORT

A

A

OIL DRAIN PLUG/MAGNETIC CHIP DETECTOR

P_AC_050407_1_0100001_01_00

Starter Oil ServicingFIGURE-5-4-7-991-010-A01

5-4-7Page 6

Jun 01/16


**ON A/C A350-1000 A350-900

APU Oil Servicing

**ON A/C A350-900

1. APU Oil Servicing




APU:Access Door 316BR

62.52 m(205.12 ft.)

0.48 m(1.57 ft.)

6.45 m(21.16 ft.)

**ON A/C A350-1000

2. APU Oil Servicing




APU:Access Door 316BR

69.51 m(228.05 ft.)

0.48 m(1.57 ft.)

6.45 m(21.16 ft.)

5-4-7Page 7

Jun 01/16


**ON A/C A350-1000 A350-900

SIGHT GLASS

PRESSURE FILLPORT

FILL CAP

CB

FWD

C

PRESSUREOVERFILL

PORT

FR104

316BR

BZ310

A

A

P_AC_050407_1_0110001_01_01

APU Oil ServicingFIGURE-5-4-7-991-011-A01

5-4-7Page 8

Jun 01/16


5-4-8 Potable Water Servicing

**ON A/C A350-1000 A350-900

Potable Water Servicing

**ON A/C A350-900

1. Potable Water Servicing




Potable-WaterGround ServicePanel:Access Door 164AR

50.20 m(164.70 ft.)

1.60 m(5.25 ft.)

3.30 m(10.83 ft.)

**ON A/C A350-1000

2. Potable Water Servicing




Potable-WaterGround ServicePanel:Access Door 164AR

57.16 m(187.53 ft.)

1.60 m(5.25 ft.)

3.30 m(10.83 ft.)

**ON A/C A350-1000 A350-900


A. Connectors:- Fill/drain nipple 3/4 in. (ISO 17775).

B. Capacity:- Standard configuration - two tanks (530 L (140 USgal) each): 1060 L (280 USgal),- Optional - two tanks (750 L (198 USgal) each): 1500 L (396 USgal).

C. Filling pressure:- Max filling pressure: 8.6 bar (125 psi).

5-4-8Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

FR86FR85

FR84

FR71

AFILL/DRAIN PORT

INDICATION PANELPOTABLE WATER

NIPPLEOVERFLOW

FILL STOP DRAIN

FWD

Z160

164AR

A

P_AC_050408_1_0050001_01_00

Potable-Water Ground Service PanelFIGURE-5-4-8-991-005-A01

5-4-8Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

FR12FR13

Z120

DRAIN PORT

A

A

P_AC_050408_1_0060002_01_00

Forward Drain PortFIGURE-5-4-8-991-006-B01

5-4-8Page 3

Jun 01/16


**ON A/C A350-1000 A350-900

A

Z170

FR89

FR93

FR86

POTABLE WATER TANKS

A

P_AC_050408_1_0070001_01_00

Potable-Water Tanks LocationFIGURE-5-4-8-991-007-A01

5-4-8Page 4

Jun 01/16


5-4-9 Waste Water Servicing

**ON A/C A350-1000 A350-900

Waste Water Servicing

**ON A/C A350-900

1. Waste Water Servicing




Waste-WaterGround ServicePanel:Access Door 171AL


3.69 m(12.11 ft.)

**ON A/C A350-1000

2. Waste Water Servicing




Waste-WaterGround ServicePanel:Access Door 171AL


3.69 m(12.11 ft.)

**ON A/C A350-1000 A350-900


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

B. Usable waste tank capacity:- Standard configuration - two tanks (615 L (162 USgal) each): 1230 L (325 USgal).

C. Waste tank - Rinsing:- Operating pressure: 3.5 bar (50 psi).

D. Waste tank - Precharge:- No precharge required.

5-4-9Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

P_AC_050409_1_0010001_01_00

WASTE DRAINCONNECTION

FILL AND RINSECONNECTION

CONTROLLEVER

Waste-Water Ground Service PanelFIGURE-5-4-9-991-001-A01

5-4-9Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

Z170

A

WASTE TANK

FR86

FR89

FR93

A

FR84

P_AC_050409_1_0020001_01_01

Waste Tanks LocationFIGURE-5-4-9-991-002-A01

5-4-9Page 3

Jun 01/16


5-4-10 Cargo Control Panels

**ON A/C A350-1000 A350-900

Cargo Control Panels

**ON A/C A350-900

1. Cargo Control Panels




FWD Cargo DoorControl Panel:Access Door 132AR

9.59 m(31.46 ft.)

2.48 m(8.14 ft.)

3.87 m(12.7 ft.)

FWD CLS* Panel:Access Door 132BR

9.59 m(31.46 ft.)

2.77 m(9.09 ft.)

4.50 m(14.76 ft.)

AFT Cargo DoorControl Panel:Access Door 152AR

45.18 m(148.23 ft.)

2.46 m(8.07 ft.)

3.80 m(12.47 ft.)

AFT CLS* Panel:Access Door 152BR

45.37 m(148.85 ft.)

2.84 m(9.32 ft.)

4.71 m(15.45 ft.)

NOTE : * CLS - CARGO LOADING SYSTEMS

**ON A/C A350-1000

2. Cargo Control Panels




FWD Cargo DoorControl Panel:Access Door 132AR

9.59 m(31.46 ft.)

2.48 m(8.14 ft.)

3.87 m(12.70 ft.)

FWD CLS* Panel:Access Door 132BR

9.59 m(31.46 ft.)

2.77 m(9.09 ft.)

4.50 m(14.76 ft.)

AFT Cargo DoorControl Panel:Access Door 152AR

52.17 m(171.16 ft.)

2.46 m(8.07 ft.)

3.80 m(12.47 ft.)

AFT CLS* Panel:Access Door 152BR

52.36 m(171.78 ft.)

2.84 m(9.32 ft.)

4.71 m(15.45 ft.)

NOTE : * CLS - CARGO LOADING SYSTEMS

5-4-10Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

FR21

FR22

132BRPWR ON/OFF

SWITCHSYST ON

LAMP

JOYSTICK

TOGGLE SWITCHOPEN OR CLOSE

CARGO DOOR

MANUALOPERATING

132AR

OUTSIDE CARGO LOADING SYSTEM CONTROL PANEL01

CARGO DOOR CONTROL PANEL02

NOTE:

FWD

FWD

DEVICE

01

02

INDICATOR LIGHT"CARGO DOOR

FULLY OPEN ANDARRESTED"

B

C

A

B

C

A

Z130

FWD CARGODOOR

P_AC_050410_1_0030001_01_00

Forward Cargo Control PanelsFIGURE-5-4-10-991-003-A01

5-4-10Page 2

Jun 01/16


**ON A/C A350-1000 A350-900

AFT CARGO DOOR

152BR

PWR ON/OFFSWITCH

SYST ONLAMP

JOYSTICK

OUTSIDE CARGO LOADING SYSTEM CONTROL PANEL01

CARGO DOOR CONTROL PANEL02

NOTE:

FWD

FWD

01

02

FR77

FR76

TOGGLE SWITCHOPEN OR CLOSE

CARGO DOOR

MANUALOPERATING

DEVICE

INDICATOR LIGHT"CARGO DOOR

FULLY OPEN ANDARRESTED"

152AR

A

A

B

C

B

C

Z150

P_AC_050410_1_0040001_01_00

Aft Cargo Control PanelsFIGURE-5-4-10-991-004-A01

5-4-10Page 3

Jun 01/16


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C A350-1000 A350-900

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 Unit

HPGC 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 airdata: discharge temperature, absolute discharge pressure and mass flow rate at the HPGC.

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

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

Jun 01/16


**ON A/C A350-1000 A350-900

AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

5 15 25 35 45 55

ROLLS ROYCE TRENT XWB/SEA LEVELSTARTING TIME: LESS THAN 90 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)

OUTSIDE AIR TEMPERATURE OAT (° C)

OUTSIDE AIR TEMPERATURE OAT (° F)

−5−15−25−35−45

0 20 40 60 80 100 120−20−40

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 260° C (500° F)AT HPGC:− THE REQUIRED PRESSURE AT HPGC IS 41 psia− THE REQUIRED AIRFLOW AT HPGC IS 102 kg/min.

EXAMPLE:FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 200° C (392° F) AT HPGC, INTERPOLATING BETWEEN THE LINES 140° C (284° F) AND 260° C (500° F) RESULTS IN:− A REQUIRED PRESSURE AT HPGC OF 42.5 psia− A REQUIRED AIRFLOW AT HPGC OF 114 kg/min.

55

50

45

40

35

50 55

100

110

120

130

140

150

180

4540ABSOLUTE PRESSURE (psia)

260° C (500° F) MAX140° C (284° F)70° C (158° F)

ASU DISCHARGE TEMPERATURE:

170

160

90210

230

250

270

290

310

330

350

370

390

P_AC_050500_1_0010001_01_01

Example for Use of the ChartsFIGURE-5-5-0-991-001-A01

5-5-0Page 2

Jun 01/16


**ON A/C A350-900

260° C (500° F) MAX140° C (284° F)70° C (158° F)

ASU DISCHARGE TEMPERATURE:

−40 −20 0 20 40 60 80 100 120

OUTSIDE AIR TEMPERATURE OAT (° F)

−45 −35 −25 −15 −5

OUTSIDE AIR TEMPERATURE OAT (° C)

AB

SO

LUT

E P

RE

SS

UR

E (

psia

)

45

ABSOLUTE PRESSURE (psia)

AIR

FLO

W (

kg/m

in)

AIR

FLO

W (

lb/m

in)

35

40

40

45

50

50 5590

100

110

120

130

140

150

160

170

180

5 15 25 35 45 55

55

ROLLS ROYCE TRENT XWB/SEA LEVELSTARTING TIME: LESS THAN 90 s

AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)

210

230

250

270

290

310

330

350

370

390

P_AC_050500_1_0020001_01_01

Engine Starting Pneumatic RequirementsFIGURE-5-5-0-991-002-A01

5-5-0Page 3

Jun 01/16


**ON A/C A350-1000


P_AC_050500_1_0030001_01_00

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

5-5-0Page 4

Jun 01/16


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A350-1000 A350-900

Ground Pneumatic Power Requirements

1. GeneralThis section describes the required performance for the ground equipment to maintain the cabintemperature at 27 deg.C (80.60 deg.F) for the cooling or 21 deg.C (69.80 deg.F) for heating casesafter boarding (Section 5.7 - steady state), and provides the time needed to cool down or heat up theaircraft cabin to the required temperature (Section 5.6 - dynamic cases 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

PCA Pre-Conditioned Air

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

NOTE : The cooling capability of a vapour-compression refrigeration system is frequentlyexpressed on the basis of tons of refrigeration (1 ton ≡ 3.5 kW), which is the rate ofheat transfer in the evaporator (or the rate of heat transfer to the air passing throughthe evaporator). The cooling capability of the equipment (kW) is only indicative andis not sufficient by itself to make sure of the performance. The air temperature andflow rate combinations at A/C inlet are the requirements that the equipment mustcomply to ensure this performance.

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

C. For temperatures at ground connection below 2 deg.C (35.60 deg.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.

5-6-0Page 1

Jun 01/16


**ON A/C A350-900

2. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for:- Heating (pull up) the cabin, initially at OAT, up to 21 deg.C (69.80 deg.F) (FIGURE

5-6-0-991-001-A -- Sheet 1).- Cooling (pull down) the cabin, initially at OAT, down to 27 deg.C (80.60 deg.F) (FIGURE

5-6-0-991-001-A -- Sheet 2).

**ON A/C A350-1000

3. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for heating (pull up) and cooling(pull down) the cabin, FIGURE 5-6-0-991-002-A.

5-6-0Page 2

Jun 01/16


**ON A/C A350-900

30 45 502.5

3.0

3.5

4.0

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 SOLARLOAD; LIGHTS ON; RECIRCULATION FANS ON

OAT ISA −45° C (−49° F); GC OUTLET +70° C (+158° F); EMPTY CABIN; IFE OFF; NO SOLARLOAD; LIGHTS ON; RECIRCULATION FANS ON

35 40 55

7.0

6.0

60 65

8.0

8.5

7.5

6.5

P_AC_050600_1_0010001_01_03

Ground Pneumatic Power RequirementsHeating (Sheet 1 of 2)

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

5-6-0Page 3

Jun 01/16


**ON A/C A350-900

10 40 502.5

3.0

3.5

4.0

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 −10° C (+14° F); EMPTY CABIN; IFE OFF; SOLARLOAD; LIGHTS ON; RECIRCULATION FANS ON

OAT ISA +23° C (+73.4° F); GC OUTLET +2° C (+35.6° F); EMPTY CABIN; IFE OFF; SOLARLOAD; LIGHTS ON; RECIRCULATION FANS ON

20 30 60 70 80 90

7.0

6.0

8.0

8.5

7.5

6.5

P_AC_050600_1_0010001_02_02

Ground Pneumatic Power RequirementsCooling (Sheet 2 of 2)

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

5-6-0Page 4

Jun 01/16


**ON A/C A350-1000


P_AC_050600_1_0020001_01_00

Ground Pneumatic Power RequirementsHeating (Sheet 1 of 2)

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

5-6-0Page 5

Jun 01/16


**ON A/C A350-1000


P_AC_050600_1_0020001_02_00

Ground Pneumatic Power RequirementsCooling (Sheet 2 of 2)

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

5-6-0Page 6

Jun 01/16


5-7-0 Preconditioned Airflow Requirements

**ON A/C A350-1000 A350-900

Preconditioned Airflow Requirements

1. This section provides the preconditioned airflow rate and temperature needed to maintain the cabintemperature at 24 deg.C (75.20 deg.F) for the cooling or 21 deg.C (69.80 deg.F) for the heatingcases.These settings are not intended to be used for operation (they are not a substitute for the settingsgiven in the AMM). They are based on theoretical simulations and give the picture of a real steadystate.The purpose of the air conditioning (cooling) operation (described in the AMM) is to maintain thecabin temperature below 24 deg.C (75.20 deg.F) during boarding (therefore it is not a steady state).

5-7-0Page 1

Jun 01/16


**ON A/C A350-900

AIR

FLO

W A

T G

C (

kg/s

)

−101.5

AIR

FLO

W A

T G

C (

lb/s

)

2.0

2.5

3.0

3.5

4.0

−5 0 5 10 15 20 25 30 55

20 30 60 70 80 100

GC OUTLET TEMPERATURE (° C)

GC OUTLET TEMPERATURE (° F)

MAXIMUM AIRFLOW (RECIRCULATION FANS OFF)

COOLING/HEATING PERFORMANCE

SETTINGS NOTINTENDED TO BE USED

FOR OPERATION

OAT ISA +30° C (86° F); 446 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD;

OAT ISA +23° C (73.4° F); 446 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD;RECIRCULATION FANS ON

RECIRCULATION FANS ONOAT ISA; 446 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATIONFANS ONOAT ISA −38° C (−36.4° F); EMPTY CABIN; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATIONFANS ON

FANS ONOAT ISA −45° C (−49° F); EMPTY CABIN; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATION

FANS ONOAT ISA −55° C (−67° F); EMPTY CABIN; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATION

C1

110

3.5

C2

7 35 40 45 50

C3

H1 H2 H34.5

5.5

6.5

7.5

8.5

MAXIMUM AIRFLOW (RECIRCULATION FANS ON)

40 50 90 120 130

COOLING CAPACITY CALCULATION:FOR THE CONDITIONS "C3", THE COOLING CAPACITY OF 4 kg/s x 1 kJ/(kg.° C) x (24 − 2) = 88 kW IS NEEDEDTO MAINTAIN THE CABIN TEMPERATURE BELOW 24° C (75.2° F) (4 kg/s AT GC OUTLET OF 2° C (35.6° F)).

EXAMPLE:

P_AC_050700_1_0010001_01_02

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

5-7-0Page 2

Jun 01/16


**ON A/C A350-1000


P_AC_050700_1_0020002_01_00

Preconditioned Airflow RequirementsFIGURE-5-7-0-991-002-B01

5-7-0Page 3

Jun 01/16


5-8-0 Ground Towing Requirements

**ON A/C A350-1000 A350-900

Ground Towing Requirements

1. This section provides information on aircraft towing.

The A350 is designed with means for conventional or towbarless towing. Information/procedures canbe found in chapter 9 of the Aircraft Maintenance Manual.Status on towbarless towing equipment qualification can be found in ISI 09.11.00001.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 NLG.One towbar fitting is installed at the front of the leg (optional towing fitting for towing from the rearof the NLG available).The main landing gears have attachment points for towing or debogging (for details, ARM 7).

This section shows the chart to determine the drawbar pull and tow tractor mass requirements as afunction of the following physical characteristics:- Aircraft weight,- Number of engines at idle,- Slope.The chart is based on the A350 engine type with the highest idle thrust. The chart is therefore validfor all A350 models.

2. Towbar design guidelines

The A350 towbar requirements are identical to the towbar requirements of the long range aircraft.- 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 NLG 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 (277 028 lbf.in).The towing head is designed according to ISO 8267--1, cat. III.

5-8-0Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

100

5

10

15

20

20 30 40 50 60 70 800 0 1 2 0 0.5 1.0 1.5 2.0

TOTAL TRACTION WHEEL LOAD (x 1 000 kg) No. OF ENGINESAT IDLE

SLOPE ( % )

330

300

270

240

210

180

150

2% SLOPE

19.4

15.8

DR

AW

BA

R P

ULL

(x

1 00

0 kg

)

A/C

WE

IGH

T (

x 1

000

kg)

310

250

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A350−900 AT 250 000 kg,AT 2% SLOPE, 1 ENGINE AT IDLE AND FOR WET TARMAC CONDITIONS:

ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (250 000 kg),FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (2%),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 (15 800 kg),

−THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (27 770 kg).

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A350−1000 AT 310 000 kg,AT 2% SLOPE, 1 ENGINE AT IDLE AND FOR WET TARMAC CONDITIONS:

ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (310 000 kg),FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (2%),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 (19 400 kg),SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE.THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (34 080 kg).

ICE = 0.05

HARD SNOW

= 0.2

WE

T C

ON

CR

ETE

= 0.

57

BREAKWAY RESISTANCE 4%# OF ENGINES ON FOR PB: 1ENGINE THRUST 811 daN

1 ENGINE ON

27.7

7

34.0

8

DR

Y C

ON

CR

ETE

= 0.

8

SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE.−−−−−−

−−−−−−−

A350−900A350−1000

P_AC_050800_1_0010001_01_01

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

5-8-0Page 2

Jun 01/16


5-9-0 De-Icing and External Cleaning

**ON A/C A350-1000 A350-900

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.).

2. De-Icing

AIRCRAFT TYPEWing Top Surface

(Both Sides)

Wingtip Devices(Both Inside andOutside Surfaces)

(Both Sides)

HTP Top Surface(Both Sides)

VTP(Both Sides)

A350--900354 m2(3 810 ft.2)

25 m2(269 ft.2)

72 m2(775 ft.2)

102 m2(1 098 ft.2)

A350--1000370 m2(3 983 ft.2)

30 m2(323 ft.2)

72 m2(775 ft.2)

102 m2(1 098 ft.2)

AIRCRAFT TYPEFuselage Top Surface

(Top Third - 120� Arc)

Nacelle and Pylon(Top Third - 120� Arc)

(All Engines)Total De-Iced Area

A350--900357 m2(3 843 ft.2)

56 m2(603 ft.2)

966 m2(10 398 ft.2)

A350--1000395 m2(4 252 ft.2)

56 m2(603 ft.2)

1 024 m2(11 022 ft.2)

NOTE : Dimensions are approximate.

3. External Cleaning

AIRCRAFTTYPE

Wing TopSurface

(Both Sides)

Wing LowerSurface

(Including FlapTrack Fairing)(Both Sides)

Wingtip Devices(Both Inside

andOutsideSurfaces)

(Both Sides)

HTP TopSurface

(Both Sides)

HTP LowerSurface

(Both Sides)

A350--900354 m2(3 810 ft.2)

384 m2(4 133 ft.2)

25 m2(269 ft.2)

72 m2(775 ft.2)

72 m2(775 ft.2)

A350--1000370 m2(3 983 ft.2)

399 m2(4 295 ft.2)

30 m2(323 ft.2)

72 m2(775 ft.2)

72 m2(775 ft.2)

5-9-0Page 1

Jun 01/16


AIRCRAFT TYPEVTP

(Both Sides)Fuselage andBelly Fairing

Nacelle and Pylon(All Engines) Total Cleaned Area

A350--900102 m2(1 098 ft.2)

1 073 m2(11 550 ft.2)

166 m2(1 787 ft.2)

2 242 m2(24 133 ft.2)

A350--1000102 m2(1 098 ft.2)

1 187 m2(12 777 ft.2)

166 m2(1 787 ft.2)

2 392 m2(25 747 ft.2)

NOTE : Dimensions are approximate.

5-9-0Page 2

Jun 01/16


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A350-1000 A350-900

Engine Exhaust Velocities and Temperatures

1. GeneralThis section provides the estimated engine exhaust-efflux velocity and temperature contours forGround Idle, Breakaway 11% MTO, Breakaway 22% MTO and Maximum Take-Off (MTO)conditions for the A350 engines.The contours are available for the Rolls-Royce Trent XWB-84 and Trent XWB-97 engines.The Maximum Take-Off data are presented at the maximum thrust rating.The Breakaway data are presented at a rating that corresponds to the minimum thrust levelnecessary to start the movement of the A350 at its maximum ramp weight, from a static position orwhen on an uphill surface with a slope of 1.5%. Breakaway thrust corresponds to 11% MTO whenapplied on both engines and 22% MTO when applied on a single engine (Idle thrust on the otherengine).The Idle data are directly provided by the engine manufacturer.In the charts, the longitudinal distances are measured from the inboard engine core-nozzle exitsection. The lateral distances are measured from the aircraft fuselage centerline.The estimated efflux data are shown at ISA +15K (+15˚C), Sea Level Static and no headwindconditions.The analysis assumes that the core and the bypass streams are fully mixed by the nozzle exit plane.The effects of on-wing installation or ground proximity are not taken into account and the ambientair is assumed to be still.The velocity contours are presented at 50 ft/s (15 m/s), 100 ft/s (30 m/s) and 150 ft/s (46 m/s).The temperature contours are shown at ambient temperature +10K (+10˚C), ambient temperature+20K (+20˚C) and ambient temperature +30K (+30˚C).In the case of the velocity contours for the Maximum Take-Off operating condition, there is somecoalescence of the jet plumes from the port and starboard engines, hence the contours are presentedwith both a plan view and a side view for twin-engine operation.An axisymmetric view is also provided for this case, to be applied only for single engine operation. Forthe other figures, there is no interference between the two engine plumes in the operating conditionsstudied and hence the efflux can be adequately described by the axisymmetric contours of a singleplume.

6-1-0Page 1

Jun 01/16


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

**ON A/C A350-1000 A350-900

Engine Exhaust Velocities Contours - Ground Idle Power

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

6-1-1Page 1

Jun 01/16


**ON A/C A350-900

mft

3

3040

69121550

040

8012

016

020

0

100

3050

6020

40

01020

240

70

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

0−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

50 (15)

100

(30)

150

(46)

FE

ET

ME

TE

RS

0P

LAN

AIR

CR

AF

T

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T G

RO

UN

D ID

LE A

XIS

YM

ME

TR

IC V

IEW

P_AC_060101_1_0020001_01_01

Ground Idle Power - TRENT XWB-84 EngineFIGURE-6-1-1-991-002-A01

6-1-1Page 2

Jun 01/16


**ON A/C A350-1000

50 (15)

100

(30)

150

(46)ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0215

0−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

ft

304050

040

8012

016

020

0

100

3050

6020

40

01020

240

70

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T G

RO

UN

D ID

LE A

XIS

YM

ME

TR

IC V

IEW

FE

ET

ME

TE

RS

m

3691215 0P

LAN

AIR

CR

AF

T

P_AC_060101_1_0030001_01_00


6-1-1Page 3

Jun 01/16


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

**ON A/C A350-1000 A350-900

Engine Exhaust Temperatures Contours - Ground Idle Power

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

6-1-2Page 1

Jun 01/16


**ON A/C A350-900

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0229

4−A−

001−

01

mft

00

10203040

369121550

040

8012

016

020

0

100

3050

6020

40

FE

ET

ME

TE

RS

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

GR

OU

ND

IDLE

SID

E V

IEW

P_AC_060102_1_0010001_01_01

Ground Idle Power - TRENT XWB-84 Engine(Sheet 1 of 2)

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

6-1-2Page 2

Jun 01/16


**ON A/C A350-900

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

GR

OU

ND

IDLE

AX

ISY

MM

ET

RIC

VIE

W

040

8012

016

020

0

100

3050

6020

40

FE

ET

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

1−A−

001−

01

mft

00

10203040

369121550

PLA

NA

IRC

RA

FT

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

P_AC_060102_1_0010001_02_01


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

6-1-2Page 3

Jun 01/16


**ON A/C A350-1000

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

040

8012

016

020

0

100

3050

6020

40

FE

ET

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0230

2−A−

001−

01

mft

00

10203040

369121550

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

GR

OU

ND

IDLE

SID

E V

IEW

P_AC_060102_1_0020001_01_00


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

6-1-2Page 4

Jun 01/16


**ON A/C A350-1000

040

8012

016

020

0

100

3050

6020

40

FE

ET

ME

TE

RS

mft

00

10203040

369121550

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0215

1−A−

001−

01

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

GR

OU

ND

IDLE

AX

ISY

MM

ET

RIC

VIE

W

PLA

NA

IRC

RA

FT

P_AC_060102_1_0020001_02_00


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

6-1-2Page 5

Jun 01/16


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

**ON A/C A350-1000 A350-900

Engine Exhaust Velocities Contours - Breakaway Power

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

6-1-3Page 1

Jun 01/16


**ON A/C A350-900

50 (15)

100

(30)

150

(46)

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

8−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

040

8016

020

0

100

3050

6020

40

240

70

280

320

360

400

8090

100

110

120

120

mft

3

3040

69121550

001020

FE

ET

ME

TE

RS

PLA

NA

IRC

RA

FT

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T 1

1% M

TO

TH

RU

ST

AX

ISY

MM

ET

RIC

VIE

W

P_AC_060103_1_0010001_01_01

Breakaway Power (11% MTO Thrust) - TRENT XWB-84 EngineFIGURE-6-1-3-991-001-A01

6-1-3Page 2

Jun 01/16


**ON A/C A350-900

040

8012

016

020

024

028

032

036

040

044

048

052

056

0

100

3050

6020

4070

8090

100

110

120

130

140

150

160

170

50 (15)

100

(30)

150

(46)

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

6−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

mft

3

3040

69121550

001020

FE

ET

ME

TE

RS

PLA

NA

IRC

RA

FT

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T 2

2% M

TO

TH

RU

ST

AX

ISY

MM

ET

RIC

VIE

W

P_AC_060103_1_0020001_01_01


6-1-3Page 3

Jun 01/16


**ON A/C A350-1000

mft

3

3040

69121550

001020

040

8016

020

0

100

3050

6020

40

240

70

280

320

360

400

8090

100

110

120

50 (15)

100

(30)

150

(46)

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0229

9−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

120

FE

ET

ME

TE

RS

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T 1

1% M

TO

TH

RU

ST

SID

E V

IEW

FO

R T

WIN

EN

GIN

E O

PE

RA

TIO

N

P_AC_060103_1_0030001_01_00

Breakaway Power (11% MTO Thrust) - TRENT XWB-97 Engine(Sheet 1 of 2)

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

6-1-3Page 4

Jun 01/16


**ON A/C A350-1000

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

8−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

50 (15)

100

(30)

150

(46)

040

8016

020

0

100

3050

6020

40

240

70

280

320

360

400

8090

100

110

120

120

mft

3

3040

69121550

001020

FE

ET

ME

TE

RS

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

S

PLA

NA

IRC

RA

FT

AT

11%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

FO

R T

WIN

EN

GIN

E O

PE

RA

TIO

N

P_AC_060103_1_0030001_02_00


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

6-1-3Page 5

Jun 01/16


**ON A/C A350-1000

50 (15)

100

(30)

150

(46)

040

8012

016

020

024

028

032

036

040

044

048

052

056

0

100

3050

6020

4070

8090

100

110

120

130

140

150

160

170

mft

3

3040

69121550

001020

FE

ET

ME

TE

RS

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

S

PLA

NA

IRC

RA

FT

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

6−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

AT

22%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

FO

R T

WIN

EN

GIN

E O

PE

RA

TIO

N

P_AC_060103_1_0040001_01_00


6-1-3Page 6

Jun 01/16


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

**ON A/C A350-1000 A350-900

Engine Exhaust Temperatures Contours - Breakaway Power

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

6-1-4Page 1

Jun 01/16


**ON A/C A350-900

040

8012

016

020

0

100

3050

6020

40

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

FE

ET

ME

TE

RS

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

11%

MT

O T

HR

US

T S

IDE

VIE

W

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0229

2−A−

001−

01

ELE

VA

TIO

N

mft

00

10203040

369121550

GR

OU

ND

PLA

NE

P_AC_060104_1_0010001_01_01


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

6-1-4Page 2

Jun 01/16


**ON A/C A350-900

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

040

8012

016

020

0

100

3050

6020

40

mft

00

10203040

369121550

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

9−A−

001−

01

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

11%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

PLA

NA

IRC

RA

FT

FE

ET

ME

TE

RS

P_AC_060104_1_0010001_02_01


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

6-1-4Page 3

Jun 01/16


**ON A/C A350-900

040

8012

016

020

0

100

3050

6020

40

GR

OU

ND

PLA

NE

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0229

0−A−

001−

01

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

22%

MT

O T

HR

US

T S

IDE

VIE

W

mft

00

10203040

369121550

ELE

VA

TIO

N

FE

ET

ME

TE

RS

P_AC_060104_1_0020001_01_01


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

6-1-4Page 4

Jun 01/16


**ON A/C A350-900

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

040

8012

016

020

0

100

3050

6020

40

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

22%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

mft

00

10203040

369121550

FE

ET

ME

TE

RS

PLA

NA

IRC

RA

FT

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

7−A−

001−

01

P_AC_060104_1_0020001_02_01


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

6-1-4Page 5

Jun 01/16


**ON A/C A350-1000

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

040

8012

016

020

0

100

3050

6020

40

GR

OU

ND

PLA

NE

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

11%

MT

O T

HR

US

T S

IDE

VIE

W

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0230

0−A−

001−

01

mft

00

10203040

369121550

FE

ET

ME

TE

RS

ELE

VA

TIO

N

P_AC_060104_1_0030001_01_00


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

6-1-4Page 6

Jun 01/16


**ON A/C A350-1000

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

040

8012

016

020

0

100

3050

6020

40

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

11%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

9−A−

001−

01

mft

00

10203040

369121550

FE

ET

ME

TE

RS

PLA

NA

IRC

RA

FT

P_AC_060104_1_0030001_02_00


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

6-1-4Page 7

Jun 01/16


**ON A/C A350-1000

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

040

8012

016

020

0

100

3050

6020

40

GR

OU

ND

PLA

NE

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0229

8−A−

001−

01

mft

00

10203040

369121550

FE

ET

ME

TE

RS

ELE

VA

TIO

N

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

22%

MT

O T

HR

US

T S

IDE

VIE

W

P_AC_060104_1_0040001_01_00


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

6-1-4Page 8

Jun 01/16


**ON A/C A350-1000

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

040

8012

016

020

0

100

3050

6020

40

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

7−A−

001−

01

mft

00

10203040

369121550

FE

ET

ME

TE

RS

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

22%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

PLA

NA

IRC

RA

FT

P_AC_060104_1_0040001_02_00


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

6-1-4Page 9

Jun 01/16


6-1-5 Engine Exhaust Velocities Contours - Max Take-Off Power

**ON A/C A350-1000 A350-900

Engine Exhaust Velocities Contours - Max Take-Off Power

1. This section provides engine exhaust velocities contours at max take-off power.

6-1-5Page 1

Jun 01/16


**ON A/C A350-900

mft

00

501530

100

VE

LOC

ITY

= ft

/s (

m/s

)

020

040

060

080

01

000

1 40

0

060

120

180

240

300

360

420

150

(46)

100

(30)

50 (15)

PLA

NA

IRC

RA

FT

FE

ET

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

4−A−

001−

01

1 20

0

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T M

TO

AX

ISY

MM

ET

RIC

VIE

W F

OR

SIN

GLE

EN

GIN

E O

PE

RA

TIO

N

P_AC_060105_1_0030001_01_01

Max Take-Off Power - TRENT XWB-84 Engine (Single)FIGURE-6-1-5-991-003-A01

6-1-5Page 2

Jun 01/16


**ON A/C A350-900

mft

00

501530

100

020

040

060

080

01

000

1 20

01

400

060

120

180

240

300

360

420

150

(46)

100

(30)

50 (15)

FE

ET

ME

TE

RS

VE

LOC

ITY

= ft

/s (

m/s

)

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

3−A−

001−

01

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T M

TO

SID

E V

IEW

FO

R T

WIN

EN

GIN

E O

PE

RA

TIO

N

P_AC_060105_1_0040001_01_01

Max Take-Off Power - TRENT XWB-84 Engine (Twin)(Sheet 1 of 2)

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

6-1-5Page 3

Jun 01/16


**ON A/C A350-900

020

040

060

080

01

000

1 20

01

400

060

120

180

240

300

360

420

mft

00

501530

100

VE

LOC

ITY

= ft

/s (

m/s

)

150

(46)

100

(30)

50 (15)

FE

ET

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

2−A−

001−

01

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T M

TO

PLA

N V

IEW

FO

R T

WIN

EN

GIN

E O

PE

RA

TIO

N

P_AC_060105_1_0040001_02_01


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

6-1-5Page 4

Jun 01/16


**ON A/C A350-1000

mft

00

501530

100

VE

LOC

ITY

= ft

/s (

m/s

)

060

120

180

240

300

360

420

150

(46)

100

(30)

50 (15)

020

040

060

080

01

000

1 20

01

400

FE

ET

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0229

5−A−

001−

01

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T M

TO

SID

E V

IEW

FO

R S

ING

LE E

NG

INE

OP

ER

AT

ION

P_AC_060105_1_0050001_01_00

Max Take-Off Power - TRENT XWB-97 Engine (Single)(Sheet 1 of 2)

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

6-1-5Page 5

Jun 01/16


**ON A/C A350-1000

mft

00

501530

100

VE

LOC

ITY

= ft

/s (

m/s

)

020

040

060

080

01

000

1 20

01

400

060

120

180

240

300

360

420

150

(46)

100

(30)

50 (15)

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

4−A−

001−

01

PLA

NA

IRC

RA

FT

FE

ET

ME

TE

RS

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T M

TO

AX

ISY

MM

ET

RIC

VIE

W F

OR

SIN

GLE

EN

GIN

E O

PE

RA

TIO

N

P_AC_060105_1_0050001_02_00

Max Take-Off Power - TRENT XWB-97 Engine (Single)(Sheet 2 of 2)

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

6-1-5Page 6

Jun 01/16


**ON A/C A350-1000

mft

00

501530

100

VE

LOC

ITY

= ft

/s (

m/s

)

020

040

080

01

000

1 20

0

600

180

300

360

120

240

600

1 40

0

420

1 60

0

480

150

(46)

100

(30)

50 (15)

FE

ET

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

3−A−

001−

01

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T M

TO

SID

E V

IEW

FO

R T

WIN

EN

GIN

E O

PE

RA

TIO

N

P_AC_060105_1_0060001_01_00


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

6-1-5Page 7

Jun 01/16


**ON A/C A350-1000

mft

00

501530

100

020

040

080

01

000

1 20

0

600

180

300

360

120

240

600

1 40

0

420

1 60

0

480

150

(46)

100

(30)

50 (15)

FE

ET

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

2−A−

001−

01

VE

LOC

ITY

= ft

/s (

m/s

)

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X V

ELO

CIT

Y C

ON

TO

UR

SA

T M

TO

PLA

N V

IEW

FO

R T

WIN

EN

GIN

E O

PE

RA

TIO

N

P_AC_060105_1_0060001_02_00


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

6-1-5Page 8

Jun 01/16


6-1-6 Engine Exhaust Temperatures Contours - Max Take-Off Power

**ON A/C A350-1000 A350-900

Engine Exhaust Temperatures Contours - Max Take-Off Power

1. This section provides engine exhaust temperatures contours at max take-off power.

6-1-6Page 1

Jun 01/16


**ON A/C A350-900

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

0612 3915

01020304050

ftm

010

2030

4060

7080

9010

011

012

013

014

015

016

050

ME

TE

RS

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0228

8−A−

001−

01

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

MT

O S

IDE

VIE

W

040

8012

020

024

028

032

036

040

044

048

052

016

0F

EE

T

P_AC_060106_1_0030001_01_01

Max Take-Off Power - TRENT XWB-84 Engine(Sheet 1 of 2)

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

6-1-6Page 2

Jun 01/16


**ON A/C A350-900

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

0612 3915

01020304050

ftm

0 0

4080

120

200

240

280

320

360

400

440

480

520

1020

3040

6070

8090

100

110

120

130

140

150

160

160 50

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0213

5−A−

001−

01

ME

TE

RS

FE

ET

TR

EN

T X

WB

84

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

MT

O A

XIS

YM

ME

TR

IC V

IEW

PLA

NA

IRC

RA

FT

P_AC_060106_1_0030001_02_01


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

6-1-6Page 3

Jun 01/16


**ON A/C A350-1000

0612 3915

01020304050

ftm

0 0

4080

120

200

240

280

320

360

400

440

480

520

1020

3040

6070

8090

100

110

120

130

140

150

160

160 50

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0229

6−A−

001−

01

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

ME

TE

RS

FE

ET

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

MT

O S

IDE

VIE

W

ELE

VA

TIO

NG

RO

UN

D P

LAN

E

P_AC_060106_1_0040003_01_00


FIGURE-6-1-6-991-004-C01

6-1-6Page 4

Jun 01/16


**ON A/C A350-1000

0612 3915

01020304050

ftm

0 0

4080

120

200

240

280

320

360

400

440

480

520

1020

3040

6070

8090

100

110

120

130

140

150

160

160 50

ICN−

TR

EN

TX

WB−

A−

7100

00−

R−

K06

80−

0214

5−A−

001−

01

Tam

b +

30 K

Tam

b +

20 K

Tam

b +

10 K

ME

TE

RS

FE

ET

TR

EN

T X

WB

97

000

lbf T

HR

US

T E

NG

INE

− E

ST

IMA

TE

D E

XH

AU

ST

EF

FLU

X T

EM

PE

RA

TU

RE

CO

NT

OU

RS

AT

MT

O A

XIS

YM

ME

TR

IC V

IEW

PLA

NA

IRC

RA

FT

P_AC_060106_1_0040003_02_00


FIGURE-6-1-6-991-004-C01

6-1-6Page 5

Jun 01/16


6-3-0 Danger Areas of the Engines

**ON A/C A350-1000 A350-900

Danger Areas of the Engines

1. Danger Areas of the EnginesThe intake suction danger areas, which are plotted in this chapter, correspond to very low suctionvelocities in order to prevent very low density objects (hat, handkerchief) from ingestion by engines.The primary aim of those danger areas is to protect the people working around the engines.

6-3-0Page 1

Jun 01/16


6-3-1 Danger Areas of the Engines - Ground Idle Power

**ON A/C A350-1000 A350-900

Danger Areas of the Engines - Ground Idle Power

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

6-3-1Page 1

Jun 01/16


**ON A/C A350-900

45°

R 4.6 m

30°

UPTO 67 m (220 ft) AFT OF EXHAUST NOZZLES

INTAKE SUCTION DANGER AREA

EXHAUST DANGER AREA

(15 ft)

ENTRY CORRIDOR

1.6 m(5 ft)

P_AC_060301_1_0010001_01_01


6-3-1Page 2

Jun 01/16


**ON A/C A350-1000

45°

R 4.6 m

30°


EXHAUST DANGER AREA

(15 ft)

ENTRY CORRIDOR

1.6 m(5 ft)

UPTO 67 m (220 ft) AFT OF EXHAUST NOZZLES

P_AC_060301_1_0020001_01_00


6-3-1Page 3

Jun 01/16


6-3-3 Danger Areas of the Engines - Max Take-Off Power

**ON A/C A350-1000 A350-900

Danger Areas of the Engines - Max Take-Off Power

1. This section provides danger areas of the engines at maximum take-off power conditions.

6-3-3Page 1

Jun 01/16


**ON A/C A350-900

UPTO 442 m (1 450 ft) AFT OF EXHAUST NOZZLES


EXHAUST DANGER AREA

30°

R 9.1 m(30 ft)

P_AC_060303_1_0010001_01_01

Max Take-Off Power - TRENT XWB-84 EngineFIGURE-6-3-3-991-001-A01

6-3-3Page 2

Jun 01/16


**ON A/C A350-1000


EXHAUST DANGER AREA

30°

R 9.1 m(30 ft)

UPTO 488 m (1 600 ft) AFT OF EXHAUST NOZZLES

P_AC_060303_1_0020001_01_00

Max Take-Off Power - TRENT XWB-97 EngineFIGURE-6-3-3-991-002-A01

6-3-3Page 3

Jun 01/16


6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A350-1000 A350-900

APU Exhaust Velocities and Temperatures

1. This section provides APU exhaust velocities and temperatures.

6-4-0Page 1

Jun 01/16


**ON A/C A350-1000 A350-900

0

5

10

15

0

10

20

30

40

20151050

0 10 20 30 40 50 60

METERS

FEET

50METERS FEET

FD

0

5

10

15

0

10

20

30

40

20151050

0 10 20 30 40 50 60

METERS

FEET

50METERS FEET

FD

427° C(800° F)

315.5° C(600° F)

260° C(500° F)

204° C(400° F)

149° C(300° F)

93° C(200° F)

61 m/s(200 ft/s)

46 m/s(150 ft/s)

30.5 m/s(100 ft/s)

15 m/s(50 ft/s)

P_AC_060400_1_0010001_01_01

APU Exhaust Velocities and TemperaturesFIGURE-6-4-0-991-001-A01

6-4-0Page 2

Jun 01/16


PAVEMENT DATA


**ON A/C A350-1000 A350-900

General Information

1. A brief description of the pavement charts that follow will help in airport planning.

To aid in the interpolation between the discrete values shown, each aircraft configuration is shownwith a minimum range of five loads on the Main Landing Gear (MLG).

All curves on the charts represent data at a constant specified tire pressure with:- The aircraft loaded to the Maximum Ramp Weight (MRW),- The CG at its maximum permissible aft position.Pavement requirements for commercial aircraft are derived from the static analysis of loads imposedon the MLG struts.

Landing Gear Footprint:Section 7-2-0 presents basic data on the landing gear footprint configuration, MRW and tire sizes andpressures.

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

Landing Gear Loading on Pavement:Section 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 Method:Section 7-5-0 uses the procedures in Instruction Report No. S-77-1 ”Procedures for Development ofCBR Design Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3. Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by the ICAO in October 2007.The report was prepared by the ”U.S. Army Corps Engineers Waterways Experiment Station, Soilsand Pavement Laboratory, Vicksburg, Mississippi”.The line showing 10 000 coverages is used to calculate Aircraft Classification Number (ACN).

Flexible Pavement Requirements - LCN Conversion Method:

7-1-0Page 1

Jun 01/16


The Load Classification Number (LCN) curves are no longer provided in section 7-6-0 since the LCNsystem for reporting pavement strength is obsolete, having been replaced by the ICAO recommendedACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

Rigid Pavement Requirements - PCA (Portland Cement Association) Design Method:Section 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 Conversion:The Load Classification Number (LCN) curves are no longer provided in section 7-8-0 since the LCNsystem for reporting pavement strength is obsolete, having been replaced by the ICAO recommendedACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

ACN/PCN Reporting System:Section 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 with an ACN less than or equal to the PCN can operate without restriction on thepavement.Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.The derived single wheel load is defined as the load on a single tire inflated to 1.25 MPa (181 psi)that would have the same pavement requirements as the aircraft.Computationally the ACN/PCN system uses the PCA program PDILB for rigid pavements and S-77-1for flexible pavements to calculate ACN values.The Airport Authority must decide on the method of pavement analysis and the results of theirevaluation shown as follows:

PCN

PAVEMENT TYPESUBGRADECATEGORY

TIRE PRESSURECATEGORY

EVALUATIONMETHOD

R - Rigid A - High W - No pressure limit T - Technical

F - Flexible B - MediumX - High pressure limitedto 1.75 MPa (254 psi)

U - Using Aircraft

7-1-0Page 2

Jun 01/16


PCN

PAVEMENT TYPESUBGRADECATEGORY

TIRE PRESSURECATEGORY

EVALUATIONMETHOD

C - Low

Y - Medium pressurelimited to 1.25 MPa (181psi)

D - Ultra LowZ - Low pressure limitedto 0.5 MPa (73 psi)

For flexible pavements, the four subgrade categories (CBR) are:

- A. High Strength CBR 15

- B. Medium Strength CBR 10

- C. Low Strength CBR 6

- D. Ultra Low Strength CBR 3

For rigid pavements, the four subgrade categories (k) are:

- A. High Strength k = 150 MN/m3 (550 pci)

- B. Medium Strength k = 80 MN/m3 (300 pci)

- C. Low Strength k = 40 MN/m3 (150 pci)

- D. Ultra Low Strength k = 20 MN/m3 (75 pci)

7-1-0Page 3

Jun 01/16


7-2-0 Landing Gear Footprint

**ON A/C A350-1000 A350-900

Landing Gear Footprint

1. This section provides data about the landing gear footprint in relation to the aircraft MRW and tiresizes and pressures.The landing-gear footprint information is given for all the operational weight variants of the aircraft.

7-2-0Page 1

Jun 01/16


**ON A/C A350-900

268 900 kg(592 825 lb) 93.7% 1 050x395R16 28PR 1 400x530R23 42PR

93.7% 1 400x530R23 42PR

28.665 m(94.045 ft)

0.748 m(2.454 ft)

1.735 m(5.692 ft)

2.040 m(6.693 ft)

10.600 m(34.777 ft)

A350−900WV000

A350−900WV001

275 900 kg(608 250 lb)

12.2 bar(177 psi)

12.2 bar(177 psi)

16.6 bar(241 psi)

16.8 bar(244 psi)

WEIGHTVARIANT

MAXIMUMRAMP

WEIGHT

PERCENTAGEOF WEIGHT

ON MAINGEAR GROUP

NOSE GEAR TIRESIZE

NOSE GEARTIRE

PRESSURE

MAIN GEAR TIRESIZE

MAIN GEARTIRE

PRESSURE

94.8% 1 400x530R23 42PRA350−900WV002

272 900 kg(601 650 lb)

12.2 bar(177 psi)

16.6 bar(241 psi)

95.3% 1 400x530R23 42PRA350−900WV003

268 900 kg(592 825 lb)

12.2 bar(177 psi)

16.6 bar(241 psi)

95.7% 1 400x530R23 42PRA350−900WV004

260 900 kg(575 175 lb)

12.2 bar(177 psi)

16.6 bar(241 psi)

96.2% 1 400x530R23 42PRA350−900WV005

250 900 kg(553 150 lb)

12.2 bar(177 psi)

16.6 bar(241 psi)

94.8% 1 400x530R23 42PRA350−900WV006

272 900 kg(601 650 lb)

12.2 bar(177 psi)

16.6 bar(241 psi)

1 050x395R16 28PR

1 050x395R16 28PR

1 050x395R16 28PR

1 050x395R16 28PR

1 050x395R16 28PR

1 050x395R16 28PR

P_AC_070200_1_0010001_01_03

Landing Gear FootprintFIGURE-7-2-0-991-001-A01

7-2-0Page 2

Jun 01/16


**ON A/C A350-1000

308 900 kg(681 000 lb) 94.2% 1 050x395R16 28PR 50x20R22 34PR

32.484 m(106.575 ft)

0.748 m(2.454 ft)

1.397 m(4.583 ft)

1.400 m(4.593 ft)

10.734 m(35.217 ft)

A350−1000WV000

12 bar(174 psi)

15.2 bar(220 psi)

WEIGHTVARIANT

MAXIMUMRAMP

WEIGHT

PERCENTAGEOF WEIGHT

ON MAINGEAR GROUP

NOSE GEAR TIRESIZE

NOSE GEARTIRE

PRESSURE

MAIN GEAR TIRESIZE

MAIN GEARTIRE

PRESSURE

1.400 m(4.593 ft)

1.474 m(4.836 ft)

1.397 m(4.583 ft)

P_AC_070200_1_0020001_01_00

Landing Gear FootprintFIGURE-7-2-0-991-002-A01

7-2-0Page 3

Jun 01/16


7-3-0 Maximum Pavement Loads

**ON A/C A350-1000 A350-900

Maximum Pavement Loads

1. This section provides maximum vertical and horizontal pavement loads for some critical conditions atthe tire-ground interfaces.The maximum pavement loads are given for all the operational weight variants of the aircraft.

7-3-0Page 1

Jun 01/16


**ON A/C A350-900

NO

TE

:(a

) LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

AT

MR

W.

(c)

BR

AK

ED

MA

IN G

EA

R.

1

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

T

2

A35

0−90

0W

V00

026

8 90

0 kg

(592

825

lb)

FW

D C

GS

TA

TIC

LO

AD

AT

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

AT

IC B

RA

KIN

G

34

V(N

G)

23.4

%M

AC

(b)

AF

T C

GS

TA

TIC

LO

AD

AT

5(P

ER

ST

RU

T)

V(M

G)

33%

MA

C (

a)

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

AT

INS

TA

NT

AN

EO

US

6H

(P

ER

ST

RU

T)

23 4

50 k

g(5

1 70

0 lb

)37

500

kg

(82

675

lb)

125

960

kg(2

77 7

00 lb

)41

790

kg

(92

125

lb)

42 8

80 k

g(9

4 52

5 lb

)

42 4

10 k

g(9

3 50

0 lb

)

41 7

90 k

g(9

2 12

5 lb

)

40 5

50 k

g(8

9 40

0 lb

)

38 9

90 k

g(8

5 95

0 lb

)

42 4

10 k

g(9

3 50

0 lb

)

(c)

(c)

(c)

(c)

(c)

(c)

(c)

100

770

kg(2

22 1

50 lb

)

103

460

kg(2

28 1

00 lb

)

103

450

kg(2

28 0

75 lb

)

102

520

kg(2

26 0

25 lb

)

99 8

70 k

g(2

20 1

75 lb

)

96 5

50 k

g(2

12 8

50 lb

)

103

430

kg(2

28 0

25 lb

)

(c)

(c)

(c)

(c)

(c)

(c)

(c)

275

900

kg(6

08 2

50 lb

)33

.2%

MA

C (

a)23

450

kg

(51

700

lb)

37 5

00 k

g(8

2 67

5 lb

)12

9 33

0 kg

(285

125

lb)

272

900

kg(6

01 6

50 lb

)36

.39%

MA

C (

a)23

450

kg

(51

700

lb)

37 5

00 k

g(8

2 67

5 lb

)12

9 31

0 kg

(285

075

lb)

268

900

kg(5

92 8

25 lb

)38

.1%

MA

C (

a)23

450

kg

(51

700

lb)

37 5

00 k

g(8

2 67

5 lb

)12

8 15

0 kg

(282

525

lb)

260

900

kg(5

75 1

75 lb

)39

.28%

MA

C (

a)23

480

kg

(51

775

lb)

38 1

30 k

g(8

4 05

0 lb

)12

4 83

0 kg

(275

200

lb)

A35

0−90

0W

V00

1

A35

0−90

0W

V00

4

23.4

%M

AC

(b)

23.4

%M

AC

(b)

23.4

%M

AC

(b)

24.5

7%M

AC

(a)

A35

0−90

0W

V00

2

A35

0−90

0W

V00

3

250

900

kg(5

53 1

50 lb

)40

.86%

MA

C (

a)23

520

kg

(51

850

lb)

37 6

20 k

g(8

2 95

0 lb

)12

0 69

0 kg

(266

075

lb)

A35

0−90

0W

V00

523

.39%

MA

C (

a)

272

900

kg(6

01 6

50 lb

)36

.34%

MA

C (

a)23

450

kg

(51

700

lb)

37 5

00 k

g(8

2 67

5 lb

)12

9 29

0 kg

(285

025

lb)

A35

0−90

0W

V00

623

.4%

MA

C (

b)

(b)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T 2

50 2

00 k

g (5

51 6

00 lb

).

V(N

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T F

WD

CG

V(M

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

AF

T C

G

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

H

V(M

G)

V(N

G)

P_AC_070300_1_0010001_01_03

Maximum Pavement LoadsFIGURE-7-3-0-991-001-A01

7-3-0Page 2

Jun 01/16


**ON A/C A350-1000

NO

TE

:(a

) LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

AT

MR

W.

(c)

BR

AK

ED

MA

IN G

EA

R.

1

WE

IGH

TV

AR

IAN

T

MA

XIM

UM

RA

MP

WE

IGH

T

2

A35

0−10

00W

V00

030

8 90

0 kg

(681

000

lb)

FW

D C

GS

TA

TIC

LO

AD

AT

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

AT

IC B

RA

KIN

G

34

V(N

G)

24.1

%M

AC

(b)

5(P

ER

ST

RU

T)

V(M

G)

34%

MA

C (

a)

AT

10

ft/s²

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

AT

INS

TA

NT

AN

EO

US

6H

(P

ER

ST

RU

T)

26 4

70 k

g(5

8 35

0 lb

)T

BD

145

430

kg(3

20 6

25 lb

)48

000

kg

(105

825

lb)

(c)

116

340

kg(2

56 4

75 lb

)(c

)

(b)

LOA

DS

CA

LCU

LAT

ED

US

ING

AIR

CR

AF

T A

T 3

07 3

00 k

g (6

77 4

75 lb

).

V(N

G)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T F

WD

CG

V(M

G)

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

AF

T C

G

HM

AX

IMU

M H

OR

IZO

NT

AL

GR

OU

ND

LO

AD

FR

OM

BR

AK

ING

H

V(M

G)

V(N

G)

AF

T C

GS

TA

TIC

LO

AD

AT

P_AC_070300_1_0020001_01_00

Maximum Pavement LoadsFIGURE-7-3-0-991-002-A01

7-3-0Page 3

Jun 01/16


7-4-0 Landing Gear Loading on Pavement

**ON A/C A350-1000 A350-900

Landing Gear Loading on Pavement

1. This section provides data about the landing gear loading on pavement.The MLG loading on pavement graphs are given for the weight variants that produce (at the MRWand maximum aft CG and standard tire pressure) the lowest ACN (and LCN) and the highest ACN(and LCN) for each type of aircraft.

Example, FIGURE 7-4-0-991-001-A, calculation of the total weight on the MLG for:- An aircraft with a MRW of 250 900 kg (553 150 lb),- The aircraft gross weight is 210 000 kg (462 975 lb),- A percentage of weight on the MLG of 96.21 % (percentage of weight on the MLG at MRW and

maximum aft CG at MRW).The total weight on the MLG group is 202 030 kg (445 400 lb).

NOTE : The CG in the figure title is the CG used for ACN/LCN calculation.

7-4-0Page 1

Jun 01/16


**ON A/C A350-900

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

lb)

650

600

550

500

450

400

300

350

(x 1

000

kg)

84

PERCENTAGE OF WEIGHT ON MAIN GEAR

10086 88 90 92 94 96 98

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

MLW

MZFW

TAKE OFF

LANDING

23.39% MAC

CG FOR ACN/LCNCALCULATION40.86% MAC

MTOW − 250 000 kg

P_AC_070400_1_0010001_01_02

Landing Gear Loading on PavementWV005, MRW 250 900 kg, CG 40.86%

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

7-4-0Page 2

Jun 01/16


**ON A/C A350-900

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

120

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

(x 1

000

lb)

650

600

550

500

450

400

300

350

(x 1

000

kg)

84


10086 88 90 92 94 96 98

AIR

CR

AF

T G

RO

SS

WE

IGH

T

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)

MLW

CG FOR ACN/LCNCALCULATION

33.2% MACMTOW − 275 000 kg

26.2% MAC

MZFW

TAKE OFF

LANDING

P_AC_070400_1_0020001_01_00

Landing Gear Loading on PavementWV001, MRW 275 900 kg, CG 33.2%

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

7-4-0Page 3

Jun 01/16


**ON A/C A350-1000

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1 00

0 kg

)


350

450

500

550

600

650

700

750

400

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

lb)

(x 1

000

kg)

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

84 10086 88 90 92 94 96 98

310

320

330

340

350

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

25% MAC

CG FOR ACN/LCNCALCULATION

34% MAC

LANDING

TAKE OFF

MLW

MZFW

300

MTOW − 308 000 kg

P_AC_070400_1_0030001_01_00

Landing Gear Loading on PavementWV000, MRW 308 900 kg, CG 34%

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

7-4-0Page 4

Jun 01/16


7-5-0 Flexible Pavement Requirements - US Army Corps of Engineers Design Method

**ON A/C A350-1000 A350-900

Flexible Pavement Requirements - US Army Corps of Engineers Design Method

1. This section provides data about the flexible pavement requirements.The flexible pavement requirement graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load foreach type of aircraft.They are calculated with the US Army Corps of Engineers Design Method.To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annualdeparture level and the weight on one MLG.The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).The procedure that follows is used to develop flexible pavement design curves:- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random

line is made to show 10 000 coverages,- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shown

on the graph.Example, FIGURE 7-5-0-991-001-A, calculation of the thickness of the flexible pavement for theMLG:- An aircraft with a MRW of 250 900 kg (553 150 lb),- A ”CBR” value of 10,- An annual departure level of 3 000,- The load on one MLG of 110 000 kg (242 500 lb).The required flexible pavement thickness is 711 mm (28 in.).

NOTE : The CG in the figure title is the CG used for ACN calculation.

7-5-0Page 1

Jun 01/16


**ON A/C A350-900

SUBGRADE STRENGTH − CBR

8060403020151063

8060403020151063

FLEXIBLE PAVEMENT THICKNESS

(cm)

(in)

1 400x530R23 42PR TIRES

TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE

10 000 COVERAGES USEDFOR ACN CALCULATIONSALPHA FACTOR = 0.8

MAXIMUM POSSIBLEMAIN GEAR LOADAT MAXIMUM RAMPWEIGHT AND AFT CG

LANDING GEARWEIGHT ON ONE MAIN

120 690 kg110 000 kg100 000 kg

90 000 kg80 000 kg

(266 075 lb)(242 500 lb)(220 450 lb)(198 425 lb)(176 375 lb)

1 2003 0006 00015 00025 000

10 15 20 30 40 60 80 100 120 150 180

P_AC_070500_1_0010001_01_03

Flexible Pavement RequirementsWV005, MRW 250 900 kg, CG 40.86%

FIGURE-7-5-0-991-001-A01

7-5-0Page 2

Jun 01/16


**ON A/C A350-900


129 330 kg110 000 kg100 000 kg

90 000 kg80 000 kg

(285 125 lb)(242 500 lb)(220 450 lb)(198 425 lb)(176 375 lb)

8060403020151063

8060403020151063

10 15 20 30 40 60 80 100 120 150 180(cm)

(in)



1 2003 0006 00015 000

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE25 000



1400x530R23 42PR TIRES

TIRE PRESSURE CONSTANT AT 16.8 bar (244 psi)P_AC_070500_1_0020001_01_00

Flexible Pavement RequirementsWV001, MRW 275 900 kg, CG 33.2%

FIGURE-7-5-0-991-002-A01

7-5-0Page 3

Jun 01/16


**ON A/C A350-1000


8060403020151063


(cm)

(in)

50x20R22 34PR TIRES

TIRE PRESSURE CONSTANT AT 15.2 bar (220 psi)



1 2003 0006 00015 000

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE25 000


145 430 kg130 000 kg120 000 kg

(320 625 lb)(286 600 lb)(264 550 lb)(242 500 lb)(220 450 lb)

110 000 kg100 000 kg

8060403020151063

10 15 20 30 40 60 80 100 120 150 180

P_AC_070500_1_0030002_01_00

Flexible Pavement RequirementsWV000, MRW 308 900 kg, CG 34%

FIGURE-7-5-0-991-003-B01

7-5-0Page 4

Jun 01/16


7-6-0 Flexible Pavement Requirements - LCN Conversion

**ON A/C A350-1000 A350-900

Flexible Pavement Requirements - LCN Conversion

1. The Load Classification Number (LCN) curves are no longer provided in section 7-6-0 since the LCNsystem for reporting pavement strength is obsolete, having been replaced by the ICAO recommendedACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

7-6-0Page 1

Jun 01/16


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

**ON A/C A350-1000 A350-900

Rigid Pavement Requirements - Portland Cement Association Design Method

1. This section provides data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.The rigid pavement requirement graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load foreach type of aircraft.They are calculated with the PCA design method.To find a rigid pavement thickness, you must know the Subgrade Modulus (k), the permitted workingstress and the weight on one MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on

the right, a random load line is made. This represents the MLG maximum weight to be shown,- A plot is then made of all values of the subgrade modulus (k values),- More load lines for the incremental values of the weight on the MLG are made based on the

curve for k = 80 MN/m3 , which is already shown on the graph.Example, FIGURE 7-7-0-991-001-A, calculation of the thickness of the rigid pavement for the MLG:- An aircraft with a MRW of 250 900 kg (553 150 lb),

- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 35.15 kg/cm2 (500 lb/in2),- The load on one MLG of 110 000 kg (242 500 lb).The required rigid pavement thickness is 290 mm (11 in.).


7-7-0Page 1

Jun 01/16


**ON A/C A350-900

38

36

34

32

30

28

26

24

22

20

70

65

60

55

50

45

40

35

30

25

20

1518

TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)1 400x530R23 42PR TIRES

(cm

)R

IGID

PA

VE

ME

NT

TH

ICK

NE

SS

(in)

(lb/in

²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S(k

g/cm

²)

15

14

13

12

11

10

9

8

7

1 000

900

800

700

600

500

400

300

200

REFERENCE:"DESIGN OF CONCRETE AIRPORT PAVEMENTS" AND "COMPUTER PROGRAM FOR AIRPORT PAVEMENTDESIGN − PROGRAM PDILB" PORTLAND CEMENT ASSOCIATION.

THE VALUES OBTAINED BY USING THE MAXIMUM LOAD REFERENCE LINE AND ANY VALUES FOR k ARENOTE:

EXACT. FOR LOADS LESS THAN MAXIMUM, THE CURVES ARE EXACT FOR k = 80 MN/m³ BUT DEVIATESLIGHTLY FOR ANY OTHER VALUES OF k.

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUM

RAMP WEIGHT AND AFT CG

k = 20 MN/m³k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³


120 690 kg110 000 kg100 000 kg

90 000 kg80 000 kg

(266 075 lb)(242 500 lb)(220 450 lb)(198 425 lb)(176 375 lb)

P_AC_070700_1_0010001_01_02

Rigid Pavement RequirementsWV005, MRW 250 900 kg, CG 40.86%

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

7-7-0Page 2

Jun 01/16


**ON A/C A350-900


110 000 kg100 000 kg

90 000 kg80 000 kg

(285 075 lb)(242 500 lb)(220 450 lb)(198 425 lb)(176 375 lb)

38

36

34

32

30

28

26

24

22

20

70

65

60

55

50

45

40

35

30

25

20

1518

TIRE PRESSURE CONSTANT AT 16.8 bar (244 psi)1400x530R23 42PR TIRES

(cm

)R

IGID

PA

VE

ME

NT

TH

ICK

NE

SS

(in)

(lb/in

²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S(k

g/cm

²)

15

14

13

12

11

10

9

8

7

1000

900

800

700

600

500

400

300

200

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT AND AFT CG

k = 20 MN/m³

k = 80 MN/m³

k = 150 MN/m³

k = 40 MN/m³




129 310 kg

P_AC_070700_1_0020001_01_00

Rigid Pavement RequirementsWV001, MRW 275 900 kg, CG 33.2%

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

7-7-0Page 3

Jun 01/16


**ON A/C A350-1000

38

36

34

32

30

28

26

24

22

20

70

65

60

55

50

45

40

35

30

25

20

1518

TIRE PRESSURE CONSTANT AT 15.2 bar (220 psi)1 400x530R23 42PR TIRES

(cm

)R

IGID

PA

VE

ME

NT

TH

ICK

NE

SS

(in)

(lb/in

²)

ALL

OW

AB

LE W

OR

KIN

G S

TR

ES

S(k

g/cm

²)

15

14

13

12

11

10

9

8

7

1 000

900

800

700

600

500

400

300

200


MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUM

RAMP WEIGHT AND AFT CG




145 430 kg130 000 kg120 000 kg110 000 kg100 000 kg

(320 625 lb)(286 600 lb)(264 550 lb)(242 500 lb)(220 450 lb)

k = 20 MN/m³k = 40 MN/m³k = 80 MN/m³k = 150 MN/m³

P_AC_070700_1_0030001_01_00

Rigid Pavement RequirementsWV000, MRW 308 900 kg, CG 34%

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

7-7-0Page 4

Jun 01/16


7-8-0 Rigid Pavement Requirements - LCN Conversion

**ON A/C A350-1000 A350-900

Rigid Pavement Requirements - LCN Conversion

1. The Load Classification Number (LCN) curves are no longer provided in section 7-8-0 since the LCNsystem for reporting pavement strength is obsolete, having been replaced by the ICAO recommendedACN/PCN system in 1983.For questions regarding the LCN system, contact Airbus.

7-8-0Page 1

Jun 01/16


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

**ON A/C A350-1000 A350-900

ACN/PCN Reporting System - Flexible and Rigid Pavements

1. This section provides data about the Aircraft Classification Number (ACN) for an aircraft grossweight in relation to a subgrade strength value for flexible and rigid pavement.The flexible and rigid pavement requirement graphs are given at standard tire pressure for the weightvariants producing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLGload for each type of aircraft.To find the ACN of an aircraft on flexible and rigid pavement, you must know the aircraft grossweight and the subgrade strength.

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

Example, FIGURE 7-9-0-991-001-A (sheet 1), calculation of the ACN for flexible pavement for:- An aircraft with a MRW of 250 900 kg (553 150 lb),- An aircraft gross weight of 210 000 kg (462 975 lb),- A medium subgrade strength (code B).The ACN for flexible pavement is 53.Example, FIGURE 7-9-0-991-001-A (sheet 2), calculation of the ACN for rigid pavement for:- An aircraft with a MRW of 250 900 kg (553 150 lb),- An aircraft gross weight of 210 000 kg (462 975 lb),- A medium subgrade strength (code B).The ACN for rigid pavement is 53.

2. Aircraft Classification Number - ACN tableThe tables in figures (FIGURE 7-9-0-991-003-A and FIGURE 7-9-0-991-005-A) provide ACN data intabular format similar to the one used by ICAO in the ”Aerodrome Design Manual Part 3, Pavements- Edition 1983” for all the operational weight variants of the aircraft.As an approximation, use a linear interpolation in order to get the ACN at the required operatingweight using the following equation:- ACN = ACN min + (ACN max - ACN min) x (Operating weight - 142 000 kg)/(MRW - 142 000

kg) for the A350-900,- ACN = ACN min + (ACN max - ACN min) x (Operating Weight - 160 000 kg)/(MRW - 160

000 kg) for the A350-1000.As an approximation, also use a linear interpolation in order to get the aircraft weight at thepavement PCN using the following equation:- Operating weight = 142 000 kg + (MRW - 142 000 kg) x (PCN - ACN min)/(ACN max - ACN

min) for the A350-900,- Operating weight = 160 000 kg + (MRW - 160 000 kg) x (PCN - ACN min)/(ACN max - ACN

min) for the A350-1000.

7-9-0Page 1

Jun 01/16


With ACN max = ACN calculated at the MRW in the table and with ACN min = ACN calculated at142 000 kg for the A350-900 and 160 000 kg for the A350-1000.


7-9-0Page 2

Jun 01/16


**ON A/C A350-900

1 40

0x53

0R23

42P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

6 ba

r (2

41 p

si)

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

300

400

500

600

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

AIRCRAFT CLASSIFICATION NUMBER (ACN)

280

120

130

140

150

160

170

180

190

200

210

230

240

250

260

270

220

120

110

100 90 80 70 60 50 40 30 20

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

)

ALP

HA

FA

CT

OR

= 0

.8

(x 1

000

lb)

P_AC_070900_1_0010001_01_02

Aircraft Classification Number - WV005, MRW 250 900 kg, CG 40.86%Flexible Pavement (Sheet 1 of 2)

FIGURE-7-9-0-991-001-A01

7-9-0Page 3

Jun 01/16


**ON A/C A350-900

1 40

0x53

0R23

42P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

6 ba

r (2

41 p

si)

300

400

500

600

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.


280

120

130

140

150

160

170

180

190

200

210

230

240

250

260

270

220

120

110

100 90 80 70 60 50 40 30 20

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

A −

k =

150

MN

/m³

(HIG

H)

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

lb)

P_AC_070900_1_0010001_02_01

Aircraft Classification Number - WV005, MRW 250 900 kg, CG 40.86%Rigid Pavement (Sheet 2 of 2)FIGURE-7-9-0-991-001-A01

7-9-0Page 4

Jun 01/16


**ON A/C A350-900

1400

x530

R23

42P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

8 ba

r (2

44 p

si) (x

1 0

00 k

g)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

300

400

500

600

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.


280

120

130

140

150

160

170

180

190

200

210

230

240

250

260

270

220

120

110

100 90 80 70 60 50 40 30 20

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

)

ALP

HA

FA

CT

OR

= 0

.8

(x 1

000

lb)

P_AC_070900_1_0020001_01_00

Aircraft Classification Number - WV001, MRW 275 900 kg, CG 33.2%Flexible Pavement (Sheet 1 of 2)

FIGURE-7-9-0-991-002-A01

7-9-0Page 5

Jun 01/16


**ON A/C A350-900

(x 1

000

lb)

1400

x530

R23

42P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

16.

8 ba

r (2

44 p

si) (x

1 0

00 k

g)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

300

400

500

600

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.


280

120

130

140

150

160

170

180

190

200

210

230

240

250

260

270

220

120

110

100 90 80 70 60 50 40 30 20

SU

BG

RA

DE

ST

RE

NG

TH

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

A −

k =

150

MN

/m³

(HIG

H)

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

P_AC_070900_1_0020001_02_00

Aircraft Classification Number - WV001, MRW 275 900 kg, CG 33.2%Rigid Pavement (Sheet 2 of 2)FIGURE-7-9-0-991-002-A01

7-9-0Page 6

Jun 01/16


**ON A/C A350-900

6332653265326432633360336532

7033733373337233693366347333

8235853685368436813677378536

9540984098419741944189419841

6530683067316731653162316731

6931723172327132683266327232

7933823382348134783474358234

10940113401134111141

107421024211341

ALL UPMASS (kg)

LOAD ONONE MAINGEAR LEG

(%)

TIREPRESSURE

(MPa)

ACN FORRIGID PAVEMENT

SUBGRADES − MN/m³

HIGH150

MEDIUM80

LOW40

20

ULTRA−LOW

20

ACN FORFLEXIBLE PAVEMENTSUBGRADES − CBR

15HIGH

10MEDIUM

6LOW

3

ULTRA−LOW

WEIGHTVARIANT

A350−900WV000

268 900140 000

46.846.8

1.66

A350−900WV001

46.946.947.447.4

1.66

1.66

1.66

1.66

1.68

1.66

A350−900WV002

A350−900WV003

A350−900WV004

A350−900WV005

A350−900WV006

260 900140 000

272 900140 000

47.847.948.148.147.447.4

275 900140 000272 900140 000268 900140 000

250 900140 000

47.747.7

P_AC_070900_1_0030001_01_01

ACN TableFIGURE-7-9-0-991-003-A01

7-9-0Page 7

Jun 01/16


**ON A/C A350-1000

50x2

0R22

34P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15.

2 ba

r (2

20 p

si)

400

500

600

700

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.


320

130

140

150

160

170

180

190

200

210

220

240

250

260

270

280

230

120

110

100 90 80 70 60 50 40 30 10

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

)

ALP

HA

FA

CT

OR

= 0

.72

290

300

310

300

20

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

lb)

P_AC_070900_1_0040001_01_00

Aircraft Classification Number - WV000, MRW 308 900 kg, CG 34%Flexible Pavement (Sheet 1 of 2)

FIGURE-7-9-0-991-004-A01

7-9-0Page 8

Jun 01/16


**ON A/C A350-1000

50x2

0R22

34P

R T

IRE

ST

IRE

PR

ES

SU

RE

CO

NS

TA

NT

AT

15.

2 ba

r (2

20 p

si)

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.


400

500

600

700 32

013

014

015

016

017

018

019

020

021

022

024

025

026

027

028

023

0

120

110

100 90 80 70 60 50 40 30 10

290

300

310

300

20

D −

k =

20

MN

/m³

(ULT

RA

LO

W)

SU

BG

RA

DE

ST

RE

NG

TH

C −

k =

40

MN

/m³

(LO

W)

B −

k =

80

MN

/m³

(ME

DIU

M)

A −

k =

150

MN

/m³

(HIG

H)

(x 1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

(x 1

000

lb)

P_AC_070900_1_0040001_02_00

Aircraft Classification Number - WV000, MRW 308 900 kg, CG 34%Rigid Pavement (Sheet 2 of 2)FIGURE-7-9-0-991-004-A01

7-9-0Page 9

Jun 01/16


**ON A/C A350-1000

57 72 92 111 55 61 75 10427 33 42 23 2527 28 38

ALL UPMASS (kg)

LOAD ONONE MAINGEAR LEG

(%)

TIREPRESSURE

(MPa)

ACN FORRIGID PAVEMENT

SUBGRADES − MN/m³

HIGH150

MEDIUM80

LOW40

20

ULTRA−LOW

20

ACN FORFLEXIBLE PAVEMENTSUBGRADES − CBR

15HIGH

10MEDIUM

6LOW

3

ULTRA−LOW

WEIGHTVARIANT

A350−1000WV000

308 900160 000

47.147.1

1.52

P_AC_070900_1_0050001_01_00

ACN TableFIGURE-7-9-0-991-005-A01

7-9-0Page 10

Jun 01/16


SCALED DRAWINGS

8-0-0 Scaled Drawings

**ON A/C A350-1000 A350-900

Scaled Drawings

1. This section provides the scaled drawings.

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

8-0-0Page 1

Jun 01/16


**ON A/C A350-900

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

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

P_AC_080000_1_0010001_01_01

Scaled DrawingsFIGURE-8-0-0-991-001-A01

8-0-0Page 2

Jun 01/16


**ON A/C A350-1000

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

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

P_AC_080000_1_0020001_01_00

Scaled DrawingsFIGURE-8-0-0-991-002-A01

8-0-0Page 3

Jun 01/16


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 Aircraft Rescue and Fire Fighting

**ON A/C A350-1000 A350-900

Aircraft Rescue and Fire Fighting

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

10-0-0Page 1

Jun 01/16


**ON A/C A350-900

RE

FE

RE

NC

E

:

JUN

E 2

016

AIR

BU

S S

.A.S

CU

ST

OM

ER

SE

RV

ICE

ST

EC

HN

ICA

L D

AT

A S

UP

PO

RT

AN

D S

ER

VIC

ES

3170

7 B

LAG

NA

C C

ED

EX

FR

AN

CE

RE

VIS

ION

DA

TE

:

SH

EE

T 1

/2P

_RF

_000

000_

1_A

3509

00

AIR

BU

S S

.A.S

. 201

2 . A

ll rig

hts

rese

rved

.

TH

IS C

HA

RT

GIV

ES

TH

E G

EN

ER

AL

LA

YO

UT

OF

TH

E A

350−

900

ST

AN

DA

RD

VE

RS

ION

.T

HE

NU

MB

ER

AN

D A

RR

AN

GE

ME

NT

OF

TH

E IN

DIV

IDU

AL

ITE

MS

VA

RY

WIT

H T

HE

CU

ST

OM

ER

S.

FIG

UR

ES

CO

NT

AIN

ED

IN T

HIS

PO

ST

ER

AR

E A

VA

ILA

BL

E S

EP

AR

AT

EL

Y IN

TH

E C

HA

PT

ER

10

OF

TH

E"A

IRC

RA

FT

CH

AR

AC

TE

RIS

TIC

S −

AIR

PO

RT

AN

D M

AIN

TE

NA

NC

E P

LA

NN

ING

" D

OC

UM

EN

T.

P_AC_100000_1_0010001_01_04

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

10-0-0Page 2

Jun 01/16


**ON A/C A350-1000

RE

FE

RE

NC

E

:

JUN

E 2

016

AIR

BU

S S

.A.S

CU

ST

OM

ER

SE

RV

ICE

ST

EC

HN

ICA

L D

AT

A S

UP

PO

RT

AN

D S

ER

VIC

ES

3170

7 B

LAG

NA

C C

ED

EX

FR

AN

CE

RE

VIS

ION

DA

TE

:

SH

EE

T 1

/2P

_RF

_000

000_

1_A

3501

000

TH

IS C

HA

RT

GIV

ES

TH

E G

EN

ER

AL

LA

YO

UT

OF

TH

E A

350−

1000

ST

AN

DA

RD

VE

RS

ION

.T

HE

NU

MB

ER

AN

D A

RR

AN

GE

ME

NT

OF

TH

E IN

DIV

IDU

AL

ITE

MS

VA

RY

WIT

H T

HE

CU

ST

OM

ER

S.

FIG

UR

ES

CO

NT

AIN

ED

IN T

HIS

PO

ST

ER

AR

E A

VA

ILA

BL

E S

EP

AR

AT

EL

Y IN

TH

E C

HA

PT

ER

10

OF

TH

E"A

IRC

RA

FT

CH

AR

AC

TE

RIS

TIC

S −

AIR

PO

RT

AN

D M

AIN

TE

NA

NC

E P

LA

NN

ING

" D

OC

UM

EN

T.

AIR

BU

S S

.A.S

. 201

2 . A

ll rig

hts

rese

rved

.

P_AC_100000_1_0010003_01_00

Front PageFIGURE-10-0-0-991-001-C01

10-0-0Page 3

Jun 01/16


**ON A/C A350-900

P_AC_100000_1_0030001_01_03

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-003-A01

10-0-0Page 4

Jun 01/16


**ON A/C A350-1000

P_AC_100000_1_0030002_01_00

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-003-B01

10-0-0Page 5

Jun 01/16


**ON A/C A350-900

NO

TE

:T

HE

CR

EW

RE

ST

CO

MP

AR

TM

EN

T IN

ST

ALL

AT

ION

IS O

PT

ION

AL

AN

D R

ELA

TE

D T

O A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N.

FLI

GH

T C

RE

W

CA

BIN

CR

EW

RE

ST

CO

MP

AR

TM

EN

T

RE

ST

CO

MP

AR

TM

EN

T

EM

ER

GE

NC

Y E

XIT

EM

ER

GE

NC

Y E

XIT

AC

CE

SS

DO

OR

AC

CE

SS

DO

OR

P_AC_100000_1_0040001_01_01

Crew Rest Compartments LocationFIGURE-10-0-0-991-004-A01

10-0-0Page 6

Jun 01/16


**ON A/C A350-1000

NO

TE

:T

HE

CR

EW

RE

ST

CO

MP

AR

TM

EN

T IN

ST

ALL

AT

ION

IS O

PT

ION

AL

AN

D R

ELA

TE

D T

O A

IRC

RA

FT

CO

NF

IGU

RA

TIO

N.

FLI

GH

T C

RE

W

CA

BIN

CR

EW

RE

ST

CO

MP

AR

TM

EN

T

RE

ST

CO

MP

AR

TM

EN

T

EM

ER

GE

NC

Y E

XIT

EM

ER

GE

NC

Y E

XIT

AC

CE

SS

DO

OR

AC

CE

SS

DO

OR

P_AC_100000_1_0040002_01_00

Crew Rest Compartments LocationFIGURE-10-0-0-991-004-B01

10-0-0Page 7

Jun 01/16


**ON A/C A350-900

P_AC_100000_1_0050001_01_00

Wheel/Brake OverheatWheel Safety Area (Sheet 1 of 2)

FIGURE-10-0-0-991-005-A01

10-0-0Page 8

Jun 01/16


**ON A/C A350-900

P_AC_100000_1_0050001_02_00

Wheel/Brake OverheatRecommendations (Sheet 2 of 2)

FIGURE-10-0-0-991-005-A01

10-0-0Page 9

Jun 01/16


**ON A/C A350-1000

P_AC_100000_1_0050002_01_00

Wheel/Brake OverheatWheel Safety Area (Sheet 1 of 2)

FIGURE-10-0-0-991-005-B01

10-0-0Page 10

Jun 01/16


**ON A/C A350-1000

NO

TE

:

CA

UT

ION

:

BR

AK

E O

VE

RH

EA

T A

ND

LA

ND

ING

GE

AR

FIR

E

WA

RN

ING

:B

E V

ER

Y C

AR

EF

UL

WH

EN

TH

ER

E IS

A B

RA

KE

OV

ER

HE

AT

AN

D/O

R L

AN

DIN

G G

EA

R F

IRE

.T

HE

RE

IS A

RIS

K O

F T

IRE

EX

PLO

SIO

N A

ND

/OR

WH

EE

L R

IM B

UR

ST

TH

AT

CA

N C

AU

SE

DE

AT

H O

R IN

JUR

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PR

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AU

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NO

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FIGURE-10-0-0-991-005-B01

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Jun 01/16


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Jun 01/16


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10-0-0Page 13

Jun 01/16


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Jun 01/16


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Ground Lock Safety DevicesFIGURE-10-0-0-991-007-B01

10-0-0Page 15

Jun 01/16


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Emergency Evacuation DevicesFIGURE-10-0-0-991-008-A01

10-0-0Page 16

Jun 01/16


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Emergency Evacuation DevicesFIGURE-10-0-0-991-008-B01

10-0-0Page 17

Jun 01/16


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P_AC_100000_1_0090001_01_00

Pax/Crew Doors and Emergency ExitsFIGURE-10-0-0-991-009-A01

10-0-0Page 18

Jun 01/16


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P_AC_100000_1_0100001_01_00

Cockpit Emergency ExitFIGURE-10-0-0-991-010-A01

10-0-0Page 19

Jun 01/16


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P_AC_100000_1_0110001_01_01

FWD and AFT Lower Deck Cargo DoorsFIGURE-10-0-0-991-011-A01

10-0-0Page 20

Jun 01/16


**ON A/C A350-1000 A350-900

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P_AC_100000_1_0120001_01_00

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

10-0-0Page 21

Jun 01/16


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APU Compartment AccessFIGURE-10-0-0-991-015-A01

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P_AC_100000_1_0160001_01_02

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**ON A/C A350-1000

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P_AC_100000_1_0160002_01_00

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**ON A/C A350-1000 A350-900

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Structural Break-in PointsFIGURE-10-0-0-991-017-A01

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Jun 01/16


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P_AC_100000_1_0180001_01_01

Batteries Location and AccessFIGURE-10-0-0-991-018-A01

10-0-0Page 26

Jun 01/16


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P_AC_100000_1_0180002_01_00

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Documents

AIRCRAFT CHARACTERISTICS AIRPORT AND …com.airbus-fenice.customers.artful.net/.../files/...A350XWB-Jun16.pdf · @a350 aircraft characteristics - airport and maintenance planning