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@AIRBUSA350-900

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 01/13 Rev: Apr 01/15

@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

HIGHLIGHTS

Revision No. 2 - Apr 01/15

LOCATIONS CHGCODE

DESCRIPTIONS OF CHANGE

CHAPTER 2

Section 2-1

Subject 2-1-0 R

General Aircraft Characteristics Data R DESCRIPTION TITLE UPDATED

Section 2-3

Subject 2-3-0

Ground Clearances R

FIGURE Ground Clearances R

FIGURE Ground Clearances N ILLUSTRATION ADDED





FIGURE Flap Tracks - Retracted N ILLUSTRATION ADDED


Section 2-7

Subject 2-7-0

FIGURE Forward Passenger/Crew Doors R

FIGURE Aft Passenger/Crew Doors R

FIGURE Nose Landing Gear Doors R

FIGURE Main Landing Gear Doors R

Section 2-8

Subject 2-8-0

Escape Slides R

FIGURE Escape Slides N ILLUSTRATION ADDED

Section 2-9 R

Subject 2-9-0

Landing Gear R

FIGURE Main Landing Gear R

HIGHLIGHTSPage 1

Apr 01/15


LOCATIONS CHGCODE


FIGURE Nose Landing Gear R

Subject 2-9-1 N

Landing Gear Maintenance Pits N

FIGURE Maintenance Pit Envelopes N ILLUSTRATION ADDED

FIGURE NLG/MLG Extension/RetractionPit

N ILLUSTRATION ADDED

FIGURE NLG/MLG Shock AbsorberRemoval Pit


FIGURE NLG/MLG Removal Pit N ILLUSTRATION ADDED

Section 2-14

Subject 2-14-1

Jacking for Maintenance R

FIGURE Jacking for Maintenance R

Subject 2-14-2 R

CHAPTER 3 N

Section 3-1 N

Subject 3-1-0 N

General Information N

Section 3-3 N

Subject 3-3-0 N

Take-Off Weight Limitation N

FIGURE ISA Conditions N ILLUSTRATION ADDED

FIGURE ISA + 15 ˚C (+59 ˚F)Conditions


Section 3-4 N

Subject 3-4-0 N

Landing Field Length N

FIGURE Landing Field Length N ILLUSTRATION ADDED

Section 3-5 N

Subject 3-5-0 N

Final Approach Speed N

HIGHLIGHTSPage 2

Apr 01/15


LOCATIONS CHGCODE


CHAPTER 5

Section 5-4 R

Subject 5-4-1

Grounding (Earthing) Points R

Subject 5-4-2

Hydraulic System R

Subject 5-4-3

Electrical System R

Subject 5-4-10 N

Cargo Control Panels N

FIGURE Forward Cargo Control Panels N ILLUSTRATION ADDED

FIGURE Aft Cargo Control Panels N ILLUSTRATION ADDED

Section 5-6

Subject 5-6-0

Ground Pneumatic Power Requirements R NOTE AMENDED

Section 5-8

Subject 5-8-0 R

Ground Towing Requirements R DESCRIPTION TITLE UPDATEDCROSS REFERENCED MANUAL(S)ADDED/REVISED/DELETED

FIGURE Ground Towing Requirements R ILLUSTRATION REVISED

CHAPTER 6 R

Section 6-1 N

Subject 6-1-0 N

Engine Exhaust Velocities andTemperatures

N

Subject 6-1-1 N

Engine Exhaust Velocities - Ground IdlePower

N

FIGURE Ground Idle Power - TRENTXWB Engine


Subject 6-1-2 N

HIGHLIGHTSPage 3

Apr 01/15


LOCATIONS CHGCODE


Engine Exhaust Temperatures - GroundIdle Power

N

FIGURE Ground Idle Power - TRENTXWB-84 Engine


Subject 6-1-3 N

Engine Exhaust Velocities - BreakawayPower

N

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




Subject 6-1-4 N

Engine Exhaust Temperatures -Breakaway Power

N





Subject 6-1-5 N

Engine Exhaust Velocities - Max Take-OffPower

N

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


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


Subject 6-1-6 N

Engine Exhaust Temperatures - MaxTake-Off Power

N

FIGURE Max Take-Off Power - TRENTXWB-84 Engine


Section 6-3 N

Subject 6-3-1 N

Danger Areas of the Engines - Ground IdlePower

N

HIGHLIGHTSPage 4

Apr 01/15


LOCATIONS CHGCODE


FIGURE Ground Idle Power - TRENTXWB-84 Engine


Subject 6-3-3 N

Danger Areas of the Engines - Max Take-Off Power

N

FIGURE Max Take-Off Power - TRENTXWB-84 Engine


CHAPTER 7

Section 7-1

Subject 7-1-0

General Information R

Section 7-2

Subject 7-2-0

Landing Gear Footprint R

FIGURE Landing Gear Footprint R

Section 7-3

Subject 7-3-0

Maximum Pavement Loads R

FIGURE Maximum Pavement Loads R

Section 7-4

Subject 7-4-0

Landing Gear Loading on Pavement R NOTE AMENDED

FIGURE Landing Gear Loading onPavement

R

FIGURE Landing Gear Loading onPavement


Section 7-5

Subject 7-5-0 R

Flexible Pavement Requirements - USArmy Corps of Engineers Design Method

R DESCRIPTION TITLE UPDATEDNOTE AMENDED

FIGURE Flexible Pavement Requirements R

FIGURE Flexible Pavement Requirements N ILLUSTRATION ADDED

Section 7-6

HIGHLIGHTSPage 5

Apr 01/15


LOCATIONS CHGCODE


Subject 7-6-0

Flexible Pavement Requirements - LCNConversion

R

Section 7-7

Subject 7-7-0

Rigid Pavement Requirements - PortlandCement Association Design Method

R NOTE AMENDED

FIGURE Rigid Pavement Requirements R

FIGURE Rigid Pavement Requirements N ILLUSTRATION ADDED

Section 7-8 R

Subject 7-8-0

Rigid Pavement Requirements - LCNConversion

R

Subject 07-08-01 D

Subject 07-08-02 D

Section 7-9 R

Subject 7-9-0 R

ACN/PCN Reporting System - Flexibleand Rigid Pavements

R DESCRIPTION TITLE UPDATEDNOTE AMENDED

FIGURE ACN/PCN Reporting System -WV000, MRW 268 900 kg, CG 33%

R ILLUSTRATION REVISED

FIGURE ACN/PCN Reporting System -WV001, MRW 275 900 kg, CG 33.2%


FIGURE ACN Table N ILLUSTRATION ADDED

Subject 07-09-01 D

CHAPTER 10

Section 10-0

Subject 10-0-0

Aircraft Rescue and Fire Fighting R

FIGURE Front Page R

FIGURE Highly Flammable and HazardousMaterials and Components

R

HIGHLIGHTSPage 6

Apr 01/15


LOCATIONS CHGCODE


FIGURE Emergency Evacuation Devices R

FIGURE FWD and AFT Lower DeckCargo Doors

R

FIGURE APU Compartment Access R

FIGURE Batteries Location and Access R

HIGHLIGHTSPage 7

Apr 01/15


LIST OF EFFECTIVE CONTENT

Revision No. 2 - Apr 01/15

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Introduction Jun 01/13

Subject 1-2-0

Glossary Jun 01/13

CHAPTER 2

Subject 2-1-0

General Aircraft Characteristics Data R Apr 01/15

Subject 2-2-0

General Aircraft Dimensions Jun 01/13

FIGURE General Aircraft Dimensions Sep 01/14

Subject 2-3-0

Ground Clearances R Apr 01/15

FIGURE Ground Clearances R Apr 01/15

FIGURE Ground Clearances N Apr 01/15





FIGURE Flap Tracks - Retracted N Apr 01/15


Subject 2-4-0

Interior Arrangements - Plan View Jun 01/13

FIGURE Standard Configuration Jun 01/13

Subject 2-5-0

Interior Arrangements - Cross Section Jun 01/13

L.E.C.Page 1

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Typical Configuration Jun 01/13

Subject 2-6-0

Cargo Compartments Jun 01/13

FIGURE Cargo Compartments Jun 01/13

Subject 2-7-0

Door Clearances and Location Sep 01/14

FIGURE Door Identification and Location Sep 01/14

FIGURE Forward Passenger/Crew Doors R Apr 01/15

FIGURE Aft Passenger/Crew Doors R Apr 01/15

FIGURE Forward Cargo Compartment Door Sep 01/14

FIGURE Aft Cargo Compartment Door Sep 01/14

FIGURE Bulk Cargo Compartment Door Sep 01/14

FIGURE Nose Landing Gear Doors R Apr 01/15

FIGURE Main Landing Gear Doors R Apr 01/15

Subject 2-8-0

Escape Slides R Apr 01/15

FIGURE Escape Slides N Apr 01/15

Subject 2-9-0

Landing Gear R Apr 01/15

FIGURE Main Landing Gear R Apr 01/15

FIGURE Nose Landing Gear R Apr 01/15

Subject 2-9-1

Landing Gear Maintenance Pits N Apr 01/15

FIGURE Maintenance Pit Envelopes N Apr 01/15

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

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

FIGURE NLG/MLG Removal Pit N Apr 01/15

Subject 2-10-0

Exterior Lighting Jun 01/13

L.E.C.Page 2

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Exterior Lighting Jun 01/13





Subject 2-11-0

Antennas and Probes Location Jun 01/13

FIGURE Antennas and Probes Location Jun 01/13

Subject 2-12-0

Engine and Nacelle Jun 01/13

FIGURE Engine and Nacelle Jun 01/13

Subject 2-12-1

APU Jun 01/13

FIGURE APU Jun 01/13

Subject 2-13-0

Levelling, Symmetry and Alignement Jun 01/13

FIGURE Location of Leveling Points Jun 01/13

Subject 2-14-1

Jacking for Maintenance R Apr 01/15

FIGURE Jacking for Maintenance R Apr 01/15

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 N Apr 01/15

Subject 3-3-0

Take-Off Weight Limitation N Apr 01/15

L.E.C.Page 3

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE ISA Conditions N Apr 01/15

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

Subject 3-4-0

Landing Field Length N Apr 01/15

FIGURE Landing Field Length N Apr 01/15

Subject 3-5-0

Final Approach Speed N Apr 01/15

CHAPTER 4

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 Jun 01/13

FIGURE Visibility from Cockpit in Static Position Jun 01/13

Subject 4-5-0

Introduction Jun 01/13

Subject 4-5-1

90˚ Turn - Runway to Taxiway Jun 01/13

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

Subject 4-5-2

135˚ Turn - Runway to Taxiway Jun 01/13

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

Subject 4-5-3

180˚ Turn on a Runway Jun 01/13

FIGURE 180˚ Turn on a Runway Jun 01/13

Subject 4-5-4

L.E.C.Page 4

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

90˚ Turn - Taxiway to Taxiway Jun 01/13

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

Subject 4-5-5

135˚ Turn - Taxiway to Taxiway Jun 01/13

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

Subject 4-6-0

Runway Holding Bay (Apron) Jun 01/13

FIGURE Runway Holding Bay (Apron) Jun 01/13

Subject 4-7-0

Minimum Line-Up Distance Corrections Sep 01/14

FIGURE 90˚ Turn on Runway Entry Sep 01/14

FIGURE 180˚ Turn on Runway Turn Pad Sep 01/14

FIGURE 180˚ Turn on Runway Width Sep 01/14

Subject 4-8-0

Aircraft Mooring Jun 01/13

FIGURE Aircraft Mooring Sep 01/14

CHAPTER 5

Subject 5-1-0

Aircraft Servicing Arrangements Jun 01/13

Subject 5-1-1

Typical Ramp Layout (Open Apron) Sep 01/14

FIGURE Typical Ramp Layout (Open Apron) Sep 01/14

Subject 5-1-2

Typical Ramp Layout (Gate) Sep 01/14

FIGURE Typical Ramp Layout (Gate) Sep 01/14

Subject 5-2-0

Terminal Operations - Full Servicing Turn Round Time Sep 01/14

FIGURE Full Servicing Turn Round Time Chart Sep 01/14

Subject 5-3-0

L.E.C.Page 5

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

Terminal Operations - Transit Turn Round Time Sep 01/14

FIGURE Transit Turn Round Time Chart Sep 01/14

Subject 5-4-0

Ground Service Connections Layout Sep 01/14

FIGURE Ground Service Connections Layout Sep 01/14

Subject 5-4-1

Grounding (Earthing) Points R Apr 01/15

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

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

Subject 5-4-2

Hydraulic System R Apr 01/15

FIGURE Green Ground Service Panel Sep 01/14

FIGURE Yellow Ground Service Panel Sep 01/14

Subject 5-4-3

Electrical System R Apr 01/15

FIGURE Electrical Service Panel Jun 01/13

FIGURE RAT Sep 01/14

Subject 5-4-4

Oxygen System Sep 01/14

FIGURE Oxygen System Jun 01/13

FIGURE Crew Oxygen Storage - Location Sep 01/14

Subject 5-4-5

Fuel System Sep 01/14

FIGURE Refuel/Defuel Control Panel Sep 01/14

FIGURE Refuel/Defuel Couplings Sep 01/14

FIGURE Overpressure Protectors and NACA Vent Intake Sep 01/14

Subject 5-4-6

Pneumatic System Sep 01/14

FIGURE Low Pressure Ground Connectors Sep 01/14

L.E.C.Page 6

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE High Pressure Ground Connectors Sep 01/14

Subject 5-4-7

Engine Oil Servicing Sep 01/14

FIGURE Engine Oil Servicing Sep 01/14

VFG Oil Servicing Sep 01/14

FIGURE VFG Oil Servicing Sep 01/14

Starter Oil Servicing Sep 01/14

FIGURE Starter Oil Servicing Sep 01/14

APU Oil Servicing Sep 01/14

FIGURE APU Oil Servicing Sep 01/14

Subject 5-4-8

Potable Water System Sep 01/14

FIGURE Potable-Water Ground Service Panel Sep 01/14

FIGURE Forward Drain Port Sep 01/14

FIGURE Potable-Water Tanks Location Sep 01/14

Subject 5-4-9

Waste Water System Sep 01/14

FIGURE Waste-Water Ground Service Panel Sep 01/14

FIGURE Waste Tanks Location Jun 01/13

Subject 5-4-10

Cargo Control Panels N Apr 01/15

FIGURE Forward Cargo Control Panels N Apr 01/15

FIGURE Aft Cargo Control Panels N Apr 01/15

Subject 5-5-0

Engine Starting Pneumatic Requirements Sep 01/14

FIGURE Example for Use of the Charts Sep 01/14

FIGURE Engine Starting Pneumatic Requirements Sep 01/14

Subject 5-6-0

Ground Pneumatic Power Requirements R Apr 01/15

L.E.C.Page 7

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Ground Pneumatic Power Requirements Jun 01/13

Subject 5-7-0

Preconditioned Airflow Requirements Jun 01/13

FIGURE Preconditioned Airflow Requirements Jun 01/13

Subject 5-8-0

Ground Towing Requirements R Apr 01/15

FIGURE Ground Towing Requirements R Apr 01/15

Subject 5-9-0

De-icing and External cleaning Jun 01/13

CHAPTER 6

Subject 6-1-0

Engine Exhaust Velocities and Temperatures N Apr 01/15

Subject 6-1-1

Engine Exhaust Velocities - Ground Idle Power N Apr 01/15

FIGURE Ground Idle Power - TRENT XWB Engine N Apr 01/15

Subject 6-1-2

Engine Exhaust Temperatures - Ground Idle Power N Apr 01/15

FIGURE Ground Idle Power - TRENT XWB-84 Engine N Apr 01/15

Subject 6-1-3

Engine Exhaust Velocities - Breakaway Power N Apr 01/15

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

N Apr 01/15


N Apr 01/15

Subject 6-1-4

Engine Exhaust Temperatures - Breakaway Power N Apr 01/15


N Apr 01/15


N Apr 01/15

L.E.C.Page 8

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

Subject 6-1-5

Engine Exhaust Velocities - Max Take-Off Power N Apr 01/15

FIGURE Max Take-Off Power - TRENT XWB-84 Engine (Single) N Apr 01/15

FIGURE Max Take-Off Power - TRENT XWB-84 Engine (Twin) N Apr 01/15

Subject 6-1-6

Engine Exhaust Temperatures - Max Take-Off Power N Apr 01/15

FIGURE Max Take-Off Power - TRENT XWB-84 Engine N Apr 01/15

Subject 6-3-1

Danger Areas of the Engines - Ground Idle Power N Apr 01/15

FIGURE Ground Idle Power - TRENT XWB-84 Engine N Apr 01/15

Subject 6-3-3

Danger Areas of the Engines - Max Take-Off Power N Apr 01/15

FIGURE Max Take-Off Power - TRENT XWB-84 Engine N Apr 01/15

Subject 6-4-0

APU Exhaust Velocities and Temperatures Jun 01/13

FIGURE APU Exhaust Velocities and Temperatures Jun 01/13

CHAPTER 7

Subject 7-1-0

General Information R Apr 01/15

Subject 7-2-0

Landing Gear Footprint R Apr 01/15

FIGURE Landing Gear Footprint R Apr 01/15

Subject 7-3-0

Maximum Pavement Loads R Apr 01/15

FIGURE Maximum Pavement Loads R Apr 01/15

Subject 7-4-0

Landing Gear Loading on Pavement R Apr 01/15

FIGURE Landing Gear Loading on Pavement R Apr 01/15

FIGURE Landing Gear Loading on Pavement N Apr 01/15

L.E.C.Page 9

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

Subject 7-5-0

Flexible Pavement Requirements - US Army Corps of EngineersDesign Method

R Apr 01/15

FIGURE Flexible Pavement Requirements R Apr 01/15

FIGURE Flexible Pavement Requirements N Apr 01/15

Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion R Apr 01/15

Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

R Apr 01/15

FIGURE Rigid Pavement Requirements R Apr 01/15

FIGURE Rigid Pavement Requirements N Apr 01/15

Subject 7-8-0

Rigid Pavement Requirements - LCN Conversion R Apr 01/15

Subject 7-9-0

ACN/PCN Reporting System - Flexible and Rigid Pavements R Apr 01/15

FIGURE ACN/PCN Reporting System - WV000, MRW 268 900 kg,CG 33%

R Apr 01/15

FIGURE ACN/PCN Reporting System - WV001, MRW 275 900 kg,CG 33.2%

N Apr 01/15

FIGURE ACN Table N Apr 01/15

CHAPTER 8

Subject 8-0-0

Scaled Drawings Jun 01/13

FIGURE Scaled Drawings Jun 01/13

CHAPTER 10

Subject 10-0-0

Aircraft Rescue and Fire Fighting R Apr 01/15

FIGURE Front Page R Apr 01/15

FIGURE Highly Flammable and Hazardous Materials and Components R Apr 01/15

L.E.C.Page 10

Apr 01/15


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Crew Rest Compartments Location Jun 01/13

FIGURE Wheel/Brake Overheat Jun 01/13

FIGURE Composite Materials Location Jun 01/13

FIGURE Ground Lock Safety Devices Jun 01/13

FIGURE Emergency Evacuation Devices R Apr 01/15

FIGURE Pax/Crew Doors and Emergency Exits Jun 01/13

FIGURE Cockpit Emergency Exit Jun 01/13

FIGURE FWD and AFT Lower Deck Cargo Doors R Apr 01/15

FIGURE Control Panels Jun 01/13

FIGURE APU Compartment Access R Apr 01/15

FIGURE Aircraft Ground Clearances Jun 01/13

FIGURE Structural Break-in Points Jun 01/13

FIGURE Batteries Location and Access R Apr 01/15

L.E.C.Page 11

Apr 01/15


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 APU

2-13-0 Levelling, Symmetry and Alignement

2-14-1 Jacking for Maintenance

2-14-2 Jacking of the Landing Gear

3 AIRCRAFT PERFORMANCE

3-1-0 General Information

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

4-5-0 Runway and Taxiway Turn Paths

4-5-1 90˚ Turn - Runway to Taxiway

T.O.C.Page 1

Apr 01/15



4-5-3 180˚ Turn on a Runway

4-5-4 90˚ Turn - Taxiway to Taxiway


4-6-0 Runway Holding Bay (Apron)

4-7-0 Minimum Line-Up Distance Corrections

4-8-0 Aircraft Mooring

5 TERMINAL SERVICING

5-1-0 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 System

5-4-3 Electrical System

5-4-4 Oxygen System

5-4-5 Fuel System

5-4-6 Pneumatic System

5-4-7 Oil System

5-4-8 Potable Water System

5-4-9 Waste Water System

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 - Ground Idle Power

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

6-1-3 Engine Exhaust Velocities - Breakaway Power

6-1-4 Engine Exhaust Temperatures - Breakaway Power

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

T.O.C.Page 2

Apr 01/15


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

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

Apr 01/15


SCOPE

1-1-0 INTRODUCTION

**ON A/C A350-900

Introduction

1. General

The A350 AIRCRAFT CHARACTERISTICS AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A350-900 series aircraft to provide necessary data to airport operators andairlines for airport facilities 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

Apr 01/15


1-2-0 Glossary

**ON A/C A350-900

Glossary

1. List of Abbreviations

A/C Aircraft

ACN Aircraft Classification NumberAPU Auxiliary Power Unit

B/C Business Class

CBR California Bearing Ratio

CC Cargo Compartment

CG Center of Gravity

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

PAX Passenger

PBB Passenger Boarding Bridge

1-2-0Page 1

Apr 01/15


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

Apr 01/15


AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics Data

**ON A/C A350-900

General Aircraft Characteristics Data

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

Aircraft CharacteristicsWV000 WV001 WV002

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

268900 kg(592824 lb)

275900 kg(608256 lb)

272900 kg(601642 lb)

Maximum Take-OffWeight (MTOW)

268000 kg(590839 lb)

275000 kg(606272 lb)

272000 kg(599658 lb)

Maximum LandingWeight (MLW)

205000 kg(451948 lb)

207000 kg(456357 lb)

207000 kg(456357 lb)

Maximum Zero FuelWeight (MZFW)

192000 kg(423288 lb)

195700 kg(431445 lb)

194000 kg(427697 lb)

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)

138000 l(36456.4 USgal)Usable Fuel Capacity

(density = 0.785 kg/l) 108330 kg(238827.0 lb)

Pressurized Fuselage Volume971 m3(34291.0 ft.3)

Cockpit Volume8.23 m3(291.0 ft.3)

Passenger Compartment Volume473.7 m3(16729.0 ft.3)

Usable Volume, FWD CC(Based on LD3)

89.4 m3(3157.0 ft.3)

Usable Volume, AFT CC(Based on LD3)

71.5 m3(2525.0 ft.3)

2-1-0Page 1

Apr 01/15


Aircraft Characteristics

Usable Volume, Bulk CC9.12 m3(322.07 ft.3)

Water Volume, FWD CC113.4 m3(4004.7 ft.3)

Water Volume, AFT CC95.8 m3(3383.16 ft.3)

Water Volume, Bulk CC11.4 m3(402.59 ft.3)

2-1-0Page 2

Apr 01/15


2-2-0 General Aircraft Dimensions

**ON A/C A350-900

General Aircraft Dimensions

1. This section provides general aircraft dimensions.

2-2-0Page 1

Apr 01/15


**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_02

General Aircraft Dimensions(Sheet 1 of 2)

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

2-2-0Page 2

Apr 01/15


**ON A/C A350-900

66.80 m(219.16 ft)

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)

NOTE:RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.

13.47 m(44.19 ft)

6.21 m(20.37 ft)

2.88 m(9.45 ft)

P_AC_020200_1_0010001_02_02

General Aircraft Dimensions(Sheet 2 of 2)

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

2-2-0Page 3

Apr 01/15


2-3-0 Ground Clearances

**ON A/C 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 FWD CG and a AFT CG,- An aircraft at MRW with a FWD CG and a 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

Apr 01/15


**ON A/C A350-900

m ft m ft m ft m ft

A/C JACKEDFDL = 6.5 m

(21.33 ft)

ft16.6016.74

10.677.928.3027.9027.60

6.34

5.11

3.21

8.38

1.93

5.13

2.452.508.54

16.7616.82

10.548.058.2228.0227.50

6.34

5.165.22

3.432.522.708.618.59

2.08

8.85

16.9317.14

8.27

28.2628.17

6.81 2.08

2.59

5.385.34

3.262.71

8.788.45

8.48

17.6517.51

10.708.88

28.8227.71

6.82

6.376.37

4.41

3.713.71

9.809.58

3.16

20.9120.91

14.4712.1812.1832.1431.45

10.37

11.25

16.96 5.16 16.91 5.33 17.47 5.27 17.28 6.37 20.91

22.9025.1621.7156.34

1.93

6.967.606.55

17.10

0.60

22.8324.9221.4856.11

1.97

7.147.886.82

17.38

0.72

23.4425.8422.3857.03

2.36

7.057.566.52

17.06

0.78

23.1224.8021.3855.99

2.55

8.178.777.72

1.84

26.8028.7725.3459.96

6.02

18.27

8.2719.1913.0630.85

2.505.914.049.37

8.2019.3813.2630.74

2.685.944.079.57

8.8019.4913.3531.41

2.596.214.359.44

8.5120.3614.2730.96

3.717.185.32

10.57

12.1823.5517.4534.69

A/C CONFIGURATION

mD1D2

C3F1F2F3F4

BF2

2.53

5.065.10

3.252.41

8.508.41

1.93

D3 5.17

W2HTAPVT

6.987.676.62

17.17

0.59

BF3CP1RD1W1

2.525.853.989.40

2.43 0.76 2.48 0.87 2.87 0.94 3.08 6.541.99N1 0.74

23.7910.15

7.313.13

23.9810.27

7.333.20

24.0510.50

7.613.38

24.9711.08

8.594.39

28.1814.40

10.68 3.22 10.58 3.43 11.25 3.29 10.78 4.43 14.52

D5C1

7.253.09

C2 3.26

17.13 5.18 16.98 5.40 17.73 5.21 17.10 6.37 20.90D4 5.22

8.03 2.47 8.09 2.57 8.44 2.67 8.75 3.71 12.17BF1 2.45

140 000 kg (308 647 lb)

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

DOORS

FUSELAGE

WINGS

TAILPLANE

ENGINE/NACELLE N1 WITH

DRAIN MAST

VT C2HT C1 F1BF1BF3 D5F2F4 BF2 F3

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

AFT CG (33.2%)

MRW

FWD CG (26%)

P_AC_020300_1_0010001_01_03

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

2-3-0Page 2

Apr 01/15


**ON A/C A350-900

NOTE:* DN − DROOP NOSE

A B C D E F G H J

m ft m ft m ftft11.2015.01

3.434.58

11.2515.03

3.554.71

11.6315.47

3.614.74

11.8515.56

15.10 4.61 15.12 4.74 15.56 4.77 15.64

DESCRIPTION

mAB

3.414.58

C 4.60

DN* INBDDN* OUTBDSLAT 1 INBD

LEADING EDGE SLATS EXTENDED

SLAT 1/2 16.33 4.98 16.33 5.12 5.13 16.82D 4.98 16.80SLAT 2/3 17.48 5.33 17.47 5.48 5.46 17.93E 5.33 17.97SLAT 3/4 18.59 5.66 18.57 5.82 5.79 18.99F 5.67 19.09SLAT 4/5 19.63 5.97 19.59 6.14 6.09 19.97G 5.98 20.13SLAT 5/6 20.61 6.27 20.56 6.44 6.37 20.91H 6.28 21.13

SLAT 6 OUTBD 21.71 6.60 21.64 6.78 6.69 21.95J 6.62 22.24

140 000 kg (308 647 lb)

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

MRW

FWD CG (26%)

P_AC_020300_1_0020001_01_00

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

2-3-0Page 3

Apr 01/15


**ON A/C A350-900

G F E D C B A


2.533.25

8.2910.67

2.693.42

8.8211.21

2.653.37

8.6911.07

13.34 4.05 13.30 4.22 13.84 4.17 13.69

DESCRIPTION

mAB

2.543.26

C 4.06

FLAP 1 INBDFLAP 1/2

FLAP 2 OUTBD

FLAPS EXTENDED

13.51 4.11 13.47 4.27 14.01 4.23 13.86D 4.12FLAP 3 INBD15.96 4.85 15.91 5.02 16.47 4.96 16.28E 4.86FLAP 3/417.72 5.38 17.67 5.56 18.24 5.49 18.01F 5.40FLAP 4/518.52 5.63 18.46 5.81 19.05 5.73 18.79G 5.65FLAP 5 OUTBD

MRW

FWD CG (26%) AFT CG (33.2%)

140 000 kg (308 647 lb)


P_AC_020300_1_0030001_01_00

Ground ClearancesTrailing Edge Flaps - Extended

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

2-3-0Page 4

Apr 01/15


**ON A/C A350-900

J


4.995.45

16.3717.89

5.155.61

16.8918.41

5.125.58

16.7818.30

19.40 5.91 19.38 6.07 19.90 6.03 19.79

DESCRIPTION

mAB

5.005.46

C 5.91

SPOILER 1 INBDSPOILER 1/2

SPOILER 2 OUTBD

SPOILERS EXTENDED

19.87 6.05 19.84 6.21 20.36 6.17 20.26D 6.06SPOILER 3 INBD20.66 6.29 20.63 6.45 21.16 6.41 21.03E 6.30SPOILER 3/421.34 6.49 21.31 6.66 21.85 6.61 21.70F 6.51SPOILER 4/521.96 6.68 21.92 6.85 22.47 6.80 22.30G 6.69SPOILER 5/622.54 6.86 22.49 7.03 23.05 6.97 22.86H 6.87SPOILER 6/723.11 7.03 23.06 7.20 23.63 7.13 23.40J 7.04SPOILER 7 OUTBD

H G F E D C B A

MRW

FWD CG (26%) AFT CG (33.2%)

140 000 kg (308 647 lb)


P_AC_020300_1_0040001_01_00

Ground ClearancesSpoilers - Extended

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

2-3-0Page 5

Apr 01/15


**ON A/C A350-900


5.896.30

19.3220.66

6.076.48

19.9121.27

5.996.39

19.6520.97

20.69 6.29 20.62 6.47 21.23 6.38 20.93

DESCRIPTION

mAB

5.916.32

C 6.31

AILERON 1 INBDAILERON 1 OUTBD

AILERON 2 INBD

AILERONS DOWN

B AC

AILERON 2 OUTBD 22.30 6.77 22.22 6.96 6.85 22.49D 6.80 22.84

D

140 000 kg (308 647 lb)


MRW

FWD CG (26%)

P_AC_020300_1_0050001_01_00

Ground ClearancesAilerons - Down

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

2-3-0Page 6

Apr 01/15


**ON A/C A350-900


6.917.14

22.6623.43

7.087.33

23.2424.04

7.017.23

22.9923.74

23.54 7.15 23.47 7.34 24.07 7.24 23.77

DESCRIPTION

mAB

6.927.16

C 7.17

AILERON 1 INBDAILERON 1 OUTBD

AILERON 2 INBD

AILERONS UP

B AC

AILERON 2 OUTBD 24.43 7.42 24.35 7.61 7.50 24.62D 7.45 24.98

D

140 000 kg (308 647 lb)


MRW

FWD CG (26%)

P_AC_020300_1_0060001_01_00

Ground ClearancesAilerons - Up

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

2-3-0Page 7

Apr 01/15


**ON A/C A350-900

B A


3.724.52

12.1914.84

3.874.68

12.7115.37

3.844.64

12.6115.24

16.96 5.16 16.92 5.33 17.47 5.27 17.30

DESCRIPTION

mAB

3.724.53

C 5.17

FLAP TRACK 1FLAP TRACK 2FLAP TRACK 3

FLAP TRACKS RETRACTED

C

FWD CG (26%)

MRW

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

140 000 kg (308 647 lb)

AFT CG (40%)

P_AC_020300_1_0070001_01_00

Flap Tracks - RetractedFIGURE-2-3-0-991-007-A01

2-3-0Page 8

Apr 01/15


**ON A/C A350-900

B A


2.813.32

9.2310.90

2.983.49

9.7711.46

2.933.43

9.6211.27

13.11 3.98 13.06 4.16 13.63 4.08 13.40

DESCRIPTION

mAB

2.823.34

C 4.00

FLAP TRACK 1FLAP TRACK 2FLAP TRACK 3

FLAP TRACKS EXTENDED

C

MRW

FWD CG (26%) AFT CG (33.2%)

140 000 kg (308 647 lb)


P_AC_020300_1_0080001_01_00

Ground ClearancesFlap Tracks - Extended

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

2-3-0Page 9

Apr 01/15


2-4-0 Interior Arrangements - Plan View

**ON A/C A350-900

Interior Arrangements - Plan View

1. This section gives the standard configuration.

2-4-0Page 1

Apr 01/15


**ON A/C A350-900

48 B

US

INE

SS

CLA

SS

(6−

AB

RE

AS

T)

267

EC

ON

OM

Y C

LAS

S (

9−A

BR

EA

ST

)

PA

SS

EN

GE

R S

EA

TS

(31

5 T

OT

AL)

ITE

MD

ES

IGN

AT

ION

GG

ALL

EY

(12)

LLA

VA

TO

RY

(9)

AA

TT

EN

DA

NT

SE

AT

(8)

SS

TO

WA

GE

(1)

PA

SS

EN

GE

RD

OO

R 1

LH

PA

SS

EN

GE

RD

OO

R 2

LH

PA

SS

EN

GE

RD

OO

R 3

LH

PA

SS

EN

GE

RD

OO

R 4

LH

PA

SS

EN

GE

RD

OO

R 1

RH

PA

SS

EN

GE

RD

OO

R 2

RH

PA

SS

EN

GE

RD

OO

R 3

RH

PA

SS

EN

GE

RD

OO

R 4

RH

SE

AT

PIT

CH

ES

: EC

ON

OM

Y 3

2 in

.

BU

SIN

ES

S 6

0 in

.

A

A

G

G

GG G

GG

GG

AAA A

L LLL

AA

SL L

LLG

L

P_AC_020400_1_0010001_01_01

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

2-4-0Page 2

Apr 01/15


2-5-0 Interior Arrangements - Cross Section

**ON A/C A350-900

Interior Arrangements - Cross Section

1. This section gives the typical configuration.

2-5-0Page 1

Apr 01/15


**ON A/C 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

Apr 01/15


2-6-0 Cargo Compartments

**ON A/C A350-900

Cargo Compartments

1. This section gives cargo compartments :- Locations and dimensions,- Loading combinations.

2-6-0Page 1

Apr 01/15


**ON A/C A350-900

P_AC_020600_1_0020001_01_00

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(1

14.5

5 in

)

16.2

21 m

(638

.62

in)

0.95

m(3

7.4

in)

2.85

m(1

12.3

4 in

)

1.91

m(7

5.20

in)

13.5

78 m

(535

.57

in)

Cargo CompartmentsLocations and Dimensions (Sheet 1 of 2)

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

2-6-0Page 2

Apr 01/15


**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

Apr 01/15


2-7-0 Door Clearances and Location

**ON A/C A350-900

Door Clearances and Location

1. This section provides door clearances and location.

2-7-0Page 1

Apr 01/15


**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_02

Door Identification and Location(Sheet 1 of 2)

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

2-7-0Page 2

Apr 01/15


**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_02

Door Identification and Location(Sheet 2 of 2)

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

2-7-0Page 3

Apr 01/15


**ON A/C 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 4

Apr 01/15


**ON A/C 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 5

Apr 01/15


**ON A/C 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 6

Apr 01/15


**ON A/C 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 7

Apr 01/15


**ON A/C 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 8

Apr 01/15


**ON A/C 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 9

Apr 01/15


**ON A/C 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 10

Apr 01/15


**ON A/C 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

B

A

P_AC_020700_1_0070001_01_01

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

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

2-7-0Page 11

Apr 01/15


**ON A/C 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 12

Apr 01/15


**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 13

Apr 01/15


2-8-0 Escape Slides

**ON A/C A350-900

Escape Slides

1. GeneralThis section provides location of 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 slide-raft at each passenger/crew door (total eight).

2-8-0Page 1

Apr 01/15


**ON A/C A350-900

COCKPITESCAPE ROPE

CABIN DUAL−LANESLIDE/RAFT

CABIN SINGLE−LANESLIDE/RAFT



NOTE:RH SHOWN, LH SYMMETRICAL P_AC_020800_1_0020001_01_00

Escape Slides(Sheet 1 of 2)

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

2-8-0Page 2

Apr 01/15


**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

:R

H S

HO

WN

, LH

SY

MM

ET

RIC

AL

P_AC_020800_1_0020001_02_00

Escape Slides(Sheet 2 of 2)

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

2-8-0Page 3

Apr 01/15


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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


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

Apr 01/15


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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


2-10-0 Exterior Lighting

**ON A/C A350-900

Exterior Lighting

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

EXTERIOR LIGHTINGITEM DESCRIPTION

1 RIGHT NAVIGATION LIGHT (GREEN)

2 LEFT NAVIGATION LIGHT (RED)

3 TAIL NAVIGATION LIGHT (WHITE)

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

Apr 01/15


**ON A/C A350-900

P_AC_021000_1_0010002_01_00

3

6

6

92

1

9

12

5 12

10

8

11

7

8

7

4

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

2-10-0Page 2

Apr 01/15


**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

Apr 01/15


**ON A/C A350-900

21

3

11 11

14

8

15

14

5

7

P_AC_021000_1_0030002_01_00

4

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

2-10-0Page 4

Apr 01/15


**ON A/C A350-900

99

1313

16

10

1212

P_AC_021000_1_0040001_01_00


2-10-0Page 5

Apr 01/15


**ON A/C A350-900

17 17

CEILING LIGHT

18 18

SPOT LIGHT

EXAMPLE FOR LIGHT N° 17

P_AC_021000_1_0050001_01_00


2-10-0Page 6

Apr 01/15


2-11-0 Antennas and Probes Location

**ON A/C A350-900

Antennas and Probes Location

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

2-11-0Page 1

Apr 01/15


**ON A/C A350-900

P_AC_021100_1_0010001_01_00

12

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

15

16

17

1819202122

2324

25262728

29

30 3132

34353637383940

1 − LOC2 − SSA 13 − TAT PROBE 1, 24 − ICE PROBE5 − GNSS 16 − GNSS 27 − TCAS 2 (TOP)8 − WACS9 − SATCOM

10 − VHF 111 − ADF 112 − ADF 213 − VHF 314 − ELT15 − HF16 − MARKER17 − ISP LH18 − DME 219 − RADIO ALT R2

21 − DME 122 − TCAS 1 (BOTTOM)23 − PITOT24 − MFP 125 − AOA26− ICE PROBE DETECTOR27 − GLIDE28 − WEATHER RADAR29 − VOR30 − ISP RH31 − TCAS 1 (TOP)32 − SSA 2, 333 − ICE PROBE PROTECTOR34 − MFP 2, 335 − RADIO ALT E136 − RADIO ALT R137 − RADIO ALT R338 − RADIO ALT E339 − TCAS 2 (BOTTOM)

33

40 − VHF 220 − RADIO ALT E2NOTE:LOCATION DEPENDING OF AIRCRAFT CONFIGURATION

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

2-11-0Page 2

Apr 01/15


2-12-0 Engine and Nacelle

**ON A/C A350-900

Engine and Nacelle

1. Power PlantThe A350--900 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

Apr 01/15


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

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C 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

Apr 01/15


2-12-1 APU

**ON A/C A350-900

APU

1. The APU is installed at the rear part of the fuselage in the tail cone.An air intake system with a flap-type door is installed in the top right area of the tail cone.The exhaust gases pass overboard at the end of the fuselage cone.

2-12-1Page 1

Apr 01/15


**ON A/C A350-900

, Z315 Z316

A

FR104

FR112

ENGINE

ENGINE FUELAND

CONTROLSYSTEM

EXHAUSTSYSTEM

AIR SYSTEM

IGNITIONAND

STARTINGSYSTEM

AIR SYSTEM

OILSYSTEM

FR109

FR104

A

B

B

P_AC_021201_1_0010001_01_00

APUFIGURE-2-12-1-991-001-A01

2-12-1Page 2

Apr 01/15


2-13-0 Levelling, Symmetry and Alignement

**ON A/C A350-900

Levelling, Symmetry and Alignement

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 the reference marks on the sighting rods are alignedin the sighting plane (aircraft level).

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

2-13-0Page 1

Apr 01/15


**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

Apr 01/15


2-14-1 Jacking for Maintenance

**ON A/C A350-900

Jacking for Maintenance

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.

2. Jacks and Safety Stay

A. Jack Design- The maximum eligible static load given in table (FIGURE 2-14-1-991-001-A) are the

maximum loads applicable on jack fittings.- In fully retracted position (jack stroke at minimum), the height of the jacks is such that the

jack 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 1

Apr 01/15


**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

18630

daN

YX

76600

76600

7650

m ft

NOTE:SAFETY STAY IS NOT USED FOR JACKING.

P_AC_021401_1_0010001_01_00

Jacking for MaintenanceJacking Points Location (Sheet 1 of 5)

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

2-14-1Page 2

Apr 01/15


**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

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

MAIN LANDING GEAR = 1 400 x 530 R23

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,

P_AC_021401_1_0010001_02_01

Jacking for MaintenanceJacking Dimensions (Sheet 2 of 5)

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

2-14-1Page 3

Apr 01/15


**ON A/C A350-900

FR12

FR13

FR14

FR11

NOSE JACKADAPTOR

A

FR12FR13

Z120

A

P_AC_021401_1_0010001_03_00

Jacking for MaintenanceForward Jacking Point (Sheet 3 of 5)

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

2-14-1Page 4

Apr 01/15


**ON A/C A350-900

A

A

A

A A

REAR SPAR

RIB9

Z571 (Z671)

571FB (671FB)

PLATE COVERPROTECTOR

WING JACKADAPTOR

A

P_AC_021401_1_0010001_04_01

Jacking for MaintenanceWing Jacking Point (Sheet 4 of 5)

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

2-14-1Page 5

Apr 01/15


**ON A/C A350-900

FR98

FR98

BEAM5

FR98

A

A

FWD

B

Z310

B

AFT JACKADAPTOR

P_AC_021401_1_0010001_05_01

Jacking for MaintenanceAuxiliary Jacking Point - Safety (Sheet 5 of 5)

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

2-14-1Page 6

Apr 01/15


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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


AIRCRAFT PERFORMANCE


**ON A/C A350-900

General Information

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

Standard Day Temperatures for the Altitudes

Altitude Standard Day Temperature

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

3-1-0Page 1

Apr 01/15


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

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


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

Apr 01/15


**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

Apr 01/15


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

Apr 01/15


GROUND MANEUVERING

4-2-0 Turning Radii

**ON A/C A350-900

Turning Radii

1. This section gives the turning radii.

4-2-0Page 1

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


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

Apr 01/15


**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

Apr 01/15


4-4-0 Visibility from Cockpit in Static Position

**ON A/C A350-900

Visibility from Cockpit in Static Position

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

4-4-0Page 1

Apr 01/15


**ON A/C 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

Apr 01/15


4-5-0 Runway and Taxiway Turn Paths

**ON A/C A350-900

Introduction

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

4-5-0Page 1

Apr 01/15



**ON A/C A350-900

90˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15



**ON A/C A350-900

135˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Apr 01/15


**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

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

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

4-5-2Page 2

Apr 01/15


**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

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

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

4-5-2Page 3

Apr 01/15


4-5-3 180˚ Turn on a Runway

**ON A/C A350-900

180˚ Turn on a Runway

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

4-5-3Page 1

Apr 01/15


**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

Apr 01/15



**ON A/C A350-900

90˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Apr 01/15


**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

Apr 01/15


**ON A/C A350-900

TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY



APPROX 3.9 m(13 ft)

(75 ft)23 m


NLG PATH

MLG PATH

P_AC_040504_1_0010001_02_02

CENTERLINE

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

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

4-5-4Page 3

Apr 01/15



**ON A/C A350-900

135˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Apr 01/15


**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

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

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

4-5-5Page 2

Apr 01/15


**ON A/C A350-900

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY

23 m(75 ft)



TURN R = 45 m(150 ft)

APPROX2.5 m (8 ft)

NLG PATH

MLG PATH


P_AC_040505_1_0010002_02_02

CENTERLINE

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

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

4-5-5Page 3

Apr 01/15


4-6-0 Runway Holding Bay (Apron)

**ON A/C A350-900

Runway Holding Bay (Apron)

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

4-6-0Page 1

Apr 01/15


**ON A/C 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 Bay (Apron)FIGURE-4-6-0-991-001-A01

4-6-0Page 2

Apr 01/15


4-7-0 Minimum Line-Up Distance Corrections

**ON A/C 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 gives the minimum line-up distance correction for a 90˚ turn on runway entry.This maneuver consists in a 90˚ turn at minimum turn radius. It starts with the edge of the MLG ata distance of 4.5 m (15 ft.) from the taxiway edge, and finishes with the aircraft aligned on thecenterline of the runway.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 gives the minimum line-up distance correction for a 180˚ turn on the runway turn pad.This maneuver consists in a 180˚ turn at minimum turn radius on a runway turn pad with standardICAO geometry.It starts with the edge of the MLG at a distance of 4.5 m (15 ft.) from the pavement edge, and itfinishes with the aircraft aligned on the centerline of the runway.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 gives the minimum line-up distance correction for a 180˚ turn on the runway width.For this maneuver, the pavement width is considered to be the runway width, which is a frozenparameter (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.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

Apr 01/15


**ON A/C 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 m

P_AC_040700_1_0010001_01_01

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

4-7-0Page 2

Apr 01/15


**ON A/C 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)




P_AC_040700_1_0020001_01_01

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

4-7-0Page 3

Apr 01/15


**ON A/C 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

25°

P_AC_040700_1_0030001_01_01

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

4-7-0Page 4

Apr 01/15


4-8-0 Aircraft Mooring

**ON A/C A350-900

Aircraft Mooring

1. This section provides information on aircraft mooring.

4-8-0Page 1

Apr 01/15


**ON A/C 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

Apr 01/15


TERMINAL SERVICING

5-1-0 Aircraft Servicing Arrangements

**ON A/C 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 the positioning and operation on the ramp.

This table gives the symbols used on servicing diagrams.

Ground Support Equipment

AC AIR CONDITIONING UNITAS AIR START UNIT

BULK BULK TRAINCAT CATERING TRUCK

CB CONVEYOR BELTCLEAN CLEANING TRUCK

FUEL FUEL HYDRANT DISPENSER or TANKERGPU GROUND POWER UNIT

LDCL LOWER DECK CARGO LOADERLV LAVATORY VEHICLE

PBB PASSENGER BOARDING BRIDGEPS PASSENGER STAIRS

TOW TOW TRACTORULD ULD TRAINWV POTABLE WATER VEHICLE

5-1-0Page 1

Apr 01/15


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

**ON A/C 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 (25 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

Apr 01/15


**ON A/C A350-900

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

ULD

TOW

GPU

LDCL

CAT

FUEL

BULK

WV

LV

ULD

CAT

CBLDCL

AC

CAT

CLEAN

AS

PS

PS

STAND SAFETY LINE

P_AC_050101_1_0010001_01_02

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

5-1-1Page 2

Apr 01/15


5-1-2 Typical Ramp Layout (Gate)

**ON A/C 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 7.5 m (25 ft.) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-2Page 1

Apr 01/15


**ON A/C A350-900

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

ULD

TOW

GPU

LDCL

CAT

FUEL

BULK

WV

LV

ULD

CAT

CBLDCL

AC

CAT

CLEAN

AS

PBB

PBB

STAND SAFETY LINE

P_AC_050102_1_0010001_01_02

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

5-1-2Page 2

Apr 01/15


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

**ON A/C 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.

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/4 pallets- AFT cargo compartment: 4 containers/4 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:

5-2-0Page 1

Apr 01/15


- 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 psig (2.76 bars-rel).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 + rinsing.

5-2-0Page 2

Apr 01/15


**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_02

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

5-2-0Page 3

Apr 01/15


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

**ON A/C 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.

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/2 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

5-3-0Page 1

Apr 01/15


- Loading = 2.6 min/pallet.

C. REFUELINGNo refueling.

D. CLEANINGCleaning is performed in available time.

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.

5-3-0Page 2

Apr 01/15


**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

GSE POSITIONING/REMOVAL

P_AC_050300_1_0010002_01_02

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

5-3-0Page 3

Apr 01/15


5-4-0 Ground Service Connections Layout

**ON A/C A350-900

Ground Service Connections Layout

1. This section provides the ground service connections layout.

5-4-0Page 1

Apr 01/15


**ON A/C A350-900

12

4

7

89

10

111415

11

10 7 89 6

13

1617

18

12

12

5

3

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 SERVICING PANEL17 − WASTE WATER SERVICING PANEL18 − APU OIL SERVICING

1 − NLG GROUNDING (EARTHING) POINT2 − GROUND ELECTRICAL POWER CONNECTORS3 − OXYGEN SYSTEM4 − LOW PRESSURE AIR PRE−CONDITIONING5 − HIGH PRESSURE AIR PRE−CONDITIONING6 − YELLOW HYDRAULIC−SYSTEM SERVICE PANEL7 − ENGINE OIL SERVICING8 − STARTER OIL SERVICING9 − VFG OIL SERVICING

P_AC_050400_1_0010001_01_02

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

5-4-0Page 2

Apr 01/15


5-4-1 Grounding (Earthing) Points

**ON A/C A350-900

Grounding (Earthing) Points

1. Grounding (Earthing) Point Locations

DISTANCEFROM AIRCRAFT CENTERLINE

AFT OF NOSELH SIDE RH SIDE

MEAN HEIGHTFROM GROUND

On Nose LandingGear leg

4.42 m(14.5 ft.)

0.07 m(0.23 ft.)

1.06 m(3.48 ft.)

On left MainLanding Gear leg

32.95 m(108.1 ft.)

5.59 m(18.34 ft.)

1.55 m(5.09 ft.)

On right MainLanding Gear leg

32.95 m(108.1 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.

5-4-1Page 1

Apr 01/15


**ON A/C A350-900

A

A

B

C

B

GROUNDING (EARTHING) POINT

C

P_AC_050401_1_0010001_01_00

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

5-4-1Page 2

Apr 01/15


**ON A/C A350-900

A

A

A

B

C

LH SHOWN

GROUNDING (EARTHING) POINT

B

C

RH SYMMETRICAL

P_AC_050401_1_0020001_01_00

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

5-4-1Page 3

Apr 01/15


5-4-2 Hydraulic System

**ON A/C A350-900

Hydraulic System

1. Hydraulic SystemThe nominal operating pressure is 5000 psi (345 bar).

A. Access

DISTANCEFROM AIRCRAFT CENTERLINEACCESS



Green HydraulicSystem:Access Door 197LB

36.37 m(119.32 ft.)

0.61 m(2.0 ft.)

2.39 m(7.84 ft.)

Yellow HydraulicSystem: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).

2. 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 and 5.0 bar (29.0 psi and 72.51 psi).

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

5-4-2Page 1

Apr 01/15


**ON A/C 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 2

Apr 01/15


**ON A/C 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 3

Apr 01/15


5-4-3 Electrical System

**ON A/C A350-900

Electrical System

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. 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.)

5-4-3Page 1

Apr 01/15


**ON A/C 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 2

Apr 01/15


**ON A/C 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 3

Apr 01/15


5-4-4 Oxygen System

**ON A/C A350-900

Oxygen System

1. GeneralThe crew oxygen system has two isolated subsystems:- The left-hand side oxygen subsystem supplies oxygen to the captain and one observer.- The right-hand side oxygen subsystem supplies oxygen to the F/O and one observer.Each subsystem has a compartment with a HP gaseous cylinder assembly (one more cylinderassembly for each oxygen compartment is optional).

2. AccessGet access to the forward lower-deck cargo-compartment.The access panel to the crew oxygen servicing point is located on the rear triangular area of the FWDcargo door.

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

5-4-4Page 1

Apr 01/15


**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

Apr 01/15


**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

Apr 01/15


5-4-5 Fuel System

**ON A/C A350-900

Fuel System

1. Refuel/Defuel Control Panel




Refuel/DefuelControl Panel:Access Door 197KB

36.2 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.)

-5.5 m

(18.04 ft.)

Refuel/DefuelCoupling, Right:

Access Door 623EB

32.57 m(106.86 ft.)

-15.83 m(51.94 ft.)

5.5 m(18.04 ft.)

A. Refuel/defuel couplings:

(1) Two standard ISO 45, 2.5 in. on right wing.

(2) Two standard ISO 45, 2.5 in. on left wing (optional).

B. Refuel pressure:

(1) Max. pressure: 3.45 bar (50 psi).

3. Overpressure Protector and NACA Intake for Vent Tank

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 Intake forVent Tank

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

Apr 01/15


**ON A/C 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 2

Apr 01/15


**ON A/C 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 3

Apr 01/15


**ON A/C 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 Vent IntakeFIGURE-5-4-5-991-003-A01

5-4-5Page 4

Apr 01/15


5-4-6 Pneumatic System

**ON A/C A350-900

Pneumatic System

1. Low Pressure Connectors




Low PressureConnector:Access Door 193CB

23.58 m(77.36 ft.)

-1.05 m(3.44 ft.)

2.59 m(8.5 ft.)

Low PressureConnector:Access Door 194CR

23.58 m(77.36 ft.)

- 1.87 m(6.14 ft.)

2.87 m(9.42 ft.)

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

2. High Pressure Connectors




High PressureConnectors:Access Door 193KB


2.06 m(6.76 ft.)

A. Connectors: Two standard ISO 2026, 3 in.

5-4-6Page 1

Apr 01/15


**ON A/C 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 2

Apr 01/15


**ON A/C 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 3

Apr 01/15


5-4-7 Oil System

**ON A/C A350-900

Engine Oil Servicing

1. Engine Oil Servicing




Engine 1:Access Door 415BR

24.7 m(81.04 ft.)

8.6 m(28.22 ft.)

-3.23 m(10.6 ft.)

Engine 2:Access Door 425BR

24.7 m(81.04 ft.)

-12.29 m(40.32 ft.)

3.23 m(10.6 ft.)

5-4-7Page 1

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C A350-900

VFG Oil Servicing

1. VFG Oil Servicing




Engine 1:Fan Cowl 415AL

24.3 m(79.72 ft.)

11.02 m(36.15 ft.)

-1.22 m(4.0 ft.)


24.3 m(79.72 ft.)

-9.86 m(32.35 ft.)

1.22 m(4.0 ft.)

5-4-7Page 3

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C A350-900

Starter Oil Servicing

1. Starter Oil Servicing





24.6 m(80.71 ft.)

10.57 m(34.68 ft.)

-1.08 m(3.54 ft.)


24.6 m(80.71 ft.)

-10.31 m(33.83 ft.)

1.08 m(3.54 ft.)

5-4-7Page 5

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C A350-900

APU Oil Servicing

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.)

5-4-7Page 7

Apr 01/15


**ON A/C A350-900

A

Z310

SIGHT GLASS

PRESSURE FILLPORT

FILL CAP

FR104

B

A

CB

FWD

316BR

C

PRESSUREOVERFILL

PORT

P_AC_050407_1_0110001_01_00

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

5-4-7Page 8

Apr 01/15


5-4-8 Potable Water System

**ON A/C A350-900

Potable Water System

1. Potable Water System




Potable-WaterGround ServicePanel:Access Door 164AR

50.2 m(164.7 ft.)

-1.6 m(5.25 ft.)

3.3 m(10.83 ft.)


A. Connectors:

(1) Fill/drain nipple 3/4 in. (ISO 17775).

B. Capacity:

(1) Standard configuration - two tanks (530 l (140 USgal) each): 1060 l (280 USgal).

(2) Optional - two tanks (750 l (198 USgal) each): 1500 l (396 USgal).

C. Filling pressure:

(1) Max filling pressure: 8.6 bar (125 psi).

5-4-8Page 1

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C 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

Apr 01/15


5-4-9 Waste Water System

**ON A/C A350-900

Waste Water System

1. Waste Water System




Waste-WaterGround ServicePanel:Access Door 171AL


3.69 m(12.11 ft.)


A. Connectors:

(1) Draining - 4 in. (ISO 17775).

(2) Flushing and Filling - 1 in. (ISO 17775).

B. Usable waste tank capacity:

(1) Two tanks (595 l (157 USgal) each): 1190 l (314 USgal).

C. Waste tank - Rinsing:

(1) Operating pressure: 3.45 bar (50 psi).

D. Waste tank - Precharge:

(1) Precharge per tank (two tanks): 23 l (6 USgal).

5-4-9Page 1

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C A350-900

Z170

A

A

WASTE TANK

FR86

FR89

FR93

P_AC_050409_1_0020001_01_00

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

5-4-9Page 3

Apr 01/15


5-4-10 Cargo Control Panels

**ON A/C A350-900

Cargo Control Panels

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

5-4-10Page 1

Apr 01/15


**ON A/C 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

Apr 01/15


**ON A/C 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

Apr 01/15


5-5-0 Engine Starting Pneumatic Requirements

**ON A/C 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 UnitHPGC High Pressure Ground Connection

OAT Outside Air Temperature

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

B. For the requirements below, the configuration with two HPGC is used. Using one connector only(for a given mass flow rate and discharge pressure from the ASU) will increase the pressure lossin the ducts of the bleed system and therefore lower the performances at the engine starter.

C. For a given OAT the following charts are used to determine an acceptable combination for airdata: discharge temperature, absolute discharge pressure and mass flow rate at the HPGC.

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

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

5-5-0Page 1

Apr 01/15


**ON A/C 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 1000/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_00

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

5-5-0Page 2

Apr 01/15


**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 1000/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_00

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

5-5-0Page 3

Apr 01/15


5-6-0 Ground Pneumatic Power Requirements

**ON A/C 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 (80.6 deg.F) for the cooling or 21 deg.C (69.8 deg.F) for the 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 capacity of the equipment (kW) is only indicative and is not sufficient byitself to ensure the performance (outlet temperature and flow rate combinations arethe requirements needed for ground power). An example of cooling capacitycalculation is given in Section 5.7.

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 ground connection.

C. For temperature at ground connection below 2 deg.C (35.6 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.

2. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for:

5-6-0Page 1

Apr 01/15


- Heating (pull up) the cabin, initially at OAT, up to 21 deg.C (69.8 deg.F) (FIGURE5-6-0-991-001-A --- Sheet 1).

- Cooling (pull down) the cabin, initially at OAT, down to 27 deg.C (80.6 deg.F) (FIGURE5-6-0-991-001-A --- Sheet 2).

5-6-0Page 2

Apr 01/15


**ON A/C A350-900

PU

LL U

P P

ER

FO

RM

AN

CE

(+

70°

C (

+15

8°F

) G

C O

UT

LET

)

AIR FLOW AT GC (kg/s)

TIM

E T

O H

EA

T C

AB

IN T

O +

21°

C (

+69

.8°

F)

ON

GR

OU

ND

(m

in)

PU

1: O

AT

ISA

−38

°C

(−

36.4

°F

); G

C O

UT

LET

+70

°C

(+

158°

F);

A/C

EM

PT

Y; I

FE

OF

F; N

O S

OLA

R L

OA

D; L

IGH

TS

ON

;R

EC

IRC

ULA

TIO

N F

AN

S O

N

MA

X A

IR F

LOW

PU

1 "I

SA

−38

°C

(−

36.4

°F

)"

PU

2 "I

SA

−45

°C

(−

49°

F )

"

3035

4045

5055

6065

2.5

2.7

2.9

3.1

3.3

3.5

3.7

3.9

4.1

4.3

4.5

PU

LL U

P C

AS

ES

:

PU

2: O

AT

ISA

−45

°C

(−

49°

F);

GC

OU

TLE

T +

70°

C (

+15

8°F

); A

/C E

MP

TY

; IF

E O

FF

; NO

SO

LAR

LO

AD

; LIG

HT

S O

N;

RE

CIR

CU

LAT

ION

FA

NS

ON

P_AC_050600_1_0010001_01_02

Ground Pneumatic Power RequirementsHeating (Sheet 1 of 2)

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

5-6-0Page 3

Apr 01/15


**ON A/C A350-900

PU

LL D

OW

N P

ER

FO

RM

AN

CE

TIM

E T

O C

OO

L C

AB

IN T

O +

27°

C (

+80

.6°

F)

ON

GR

OU

ND

(m

in)

AIR FLOW AT GC (kg/s)M

AX

AIR

FLO

W

PD

1 "I

SA

+23

°C

(+

73.4

°F

) / G

C O

UT

LET

+2°

C (

+35

.6°

F)"

PD

2 "I

SA

+23

°C

(+

73.4

°F

) / G

C O

UT

LET

−10

°C

(+

14°

F)"

PD

3 "I

SA

+23

°C

(+

73.4

°F

) / G

C O

UT

LET

−20

°C

(−

4°F

)"

1020

3040

5060

7080

902.

5

2.7

2.9

3.1

3.3

3.5

3.7

3.9

4.1

4.3

4.5

PD

1: O

AT

ISA

+23

°C

(+

73.4

°F

); G

C O

UT

LET

+ 2

°C

(+

35.6

°F

); A

/C E

MP

TY

; IF

E O

FF

; SO

LAR

LO

AD

; LIG

HT

S O

N;

RE

CIR

CU

LAT

ION

FA

NS

ON

PU

LL D

OW

N C

AS

ES

:

PD

2: O

AT

ISA

+23

°C

(+

73.4

°F

); G

C O

UT

LET

−10

°C

(+

14°

F);

A/C

EM

PT

Y; I

FE

OF

F; S

OLA

R L

OA

D; L

IGH

TS

ON

;R

EC

IRC

ULA

TIO

N F

AN

S O

NP

D3:

OA

T IS

A +

23°

C (

+73

.4°

F);

GC

OU

TLE

T −

20°

C (−

4°F

); A

/C E

MP

TY

; IF

E O

FF

; SO

LAR

LO

AD

; LIG

HT

S O

N;

RE

CIR

CU

LAT

ION

FA

NS

ON

P_AC_050600_1_0010001_02_01

Ground Pneumatic Power RequirementsCooling (Sheet 2 of 2)

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

5-6-0Page 4

Apr 01/15


5-7-0 Preconditioned Airflow Requirements

**ON A/C A350-900

Preconditioned Airflow Requirements

1. This section provides the necessary information for the design of a ground unit; it gives the air flowrate and temperature combinations needed to maintain the cabin temperature at 27 deg.C (80.6deg.F).These settings are not intended to be used for operation (they don’t substitute to the settings givenin the AMM):They are issued from theoretical simulations and give the picture of a real steady state.For the air conditioning operation, Airlines will refer to the AMM that details the procedure and thePCA settings to maintain the cabin temperature below 27 deg.C (80.6 deg.F) during boarding(therefore it is not a steady state).

5-7-0Page 1

Apr 01/15


**ON A/C A350-900

1,8

2,3

2,8

3,3

3,8

4,3

05

1015

2025

3035

4045

5055

AIRFLOW FROM GC (kg/s)

CO

OL

ING

/HE

AT

ING

PE

RF

OR

MA

NC

E

GC

OU

TLE

T T

EM

PE

RA

TU

RE

(°

C)

CO

OLI

NG

CA

PA

CIT

Y C

ALC

ULA

TIO

N:

4,8

FO

R T

HE

CO

ND

ITIO

NS

C3,

TH

E C

OO

LIN

G C

AP

AC

ITY

OF

4.2

5 kg

/s x

1kJ

/(kg

.°C

) X

(27−

2) =

106

kW

IS N

EE

DE

DT

O M

AIN

TA

IN T

HE

CA

BIN

TE

MP

ER

AT

UR

E B

ELO

W 2

7°C

(86

°F

) (4

.25

kg/s

AT

GC

OU

TLE

T O

F 2

°C

(35

.6°

F))

.

OA

T IS

A+

30°

C (

86°

F);

446

PA

SS

EN

GE

RS

AN

D C

RE

W; I

FE

ON

; LIG

HT

S O

N; S

OLA

R L

OA

D; R

EC

IRC

ULA

TIO

N F

AN

S O

NO

AT

ISA

+23

°C

(73

.4°

F);

446

PA

SS

EN

GE

RS

AN

D C

RE

W; I

FE

ON

; LIG

HT

S O

N; S

OLA

R L

OA

D; R

EC

IRC

ULA

TIO

N F

AN

S O

NO

AT

ISA

; 446

PA

SS

EN

GE

RS

AN

D C

RE

W; I

FE

ON

; LIG

HT

S O

N; S

OLA

R L

OA

D; R

EC

IRC

ULA

TIO

N F

AN

S O

N

OA

T IS

A−

38°

C (−

36.4

°F

); A

/C E

MP

TY

; IF

E O

FF

; NO

SO

LAR

LO

AD

; LIG

HT

S O

N; R

EC

IRC

ULA

TIO

N F

AN

S O

NO

AT

ISA−

45°

C (−

49°

F);

A/C

EM

PT

Y; I

FE

OF

F; N

O S

OLA

R L

OA

D; L

IGH

TS

ON

; RE

CIR

CU

LAT

ION

FA

NS

ON

O

AT

ISA−

55°

C (−

67°

F);

A/C

EM

PT

Y; I

FE

OF

F; N

O S

OLA

R L

OA

D; L

IGH

TS

ON

; RE

CIR

CU

LAT

ION

FA

NS

ON

MA

X A

IR F

LOW

C1 C

2

C3

H1

H2

H3

EX

AM

PL

E:

P_AC_050700_1_0010001_01_01

−5

−10

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

5-7-0Page 2

Apr 01/15


5-8-0 Ground Towing Requirements

**ON A/C 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.

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 (27 7028 lbf.in).The towing head is designed according to ISO 8267--1, cat. III.

5-8-0Page 1

Apr 01/15


**ON A/C A350-900

25

20

15

10

5

00 10 20 30 40 50 60 70 80 0 1 2 0 0.5 1.0 1.5 2.0

TOTAL TRACTION WHEEL LOAD ( x 1000 kg ) No. OF ENGINES SLOPE ( % )

DRAWBAR PULL ( x 1000 kg )

ICE = 0.05

A/C WEIGHT ( x 1000 kg )

EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A350 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 (17 000 kg),− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE. THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (29 800 kg).

AT IDLE

P_AC_050800_1_0010001_01_00

29.8

17.0

280

255

230

205

180

155

130

2% SLOPE

HARD SNOW = 0.2

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

1 ENGINE ON

WET

CO

NC

RET

E

= 0

.57

DR

Y C

ON

CR

ETE

= 0.

8250

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

5-8-0Page 2

Apr 01/15


5-9-0 De-icing and External cleaning

**ON A/C A350-900

De-icing and External cleaning

1. De-Icing and External Cleaning on Ground.The 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 TYPE Wing Top Surface(Both Sides)

Wingtip Devices(Both Inside and

(Outside Surfaces)(Both Sides)

HTP Top Surface(Both Sides)

VTP(Both Sides)

A350--900 354 m2(3810 ft.2)

25 m2(269 ft.2)

69 m2(743 ft.2)

102 m2(1098 ft.2)

AIRCRAFT TYPE Fuselage Top Surface(Top Third - 120? Arc)

Nacelle and Pylon(Top Third - 120? Arc)

(All Engines)

Total De-Iced Area

A350--900 357 m2(3843 ft.2)

56 m2(603 ft.2)

962 m2(10355 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

and(OutsideSurfaces)

(Both Sides)

HTP TopSurface

(Both Sides)

HTP LowerSurface

(Both Sides)

A350--900 354 m2(3810 ft.2)

384 m2(4133 ft.2)

25 m2(269 ft.2)

69 m2(743 ft.2)

69 m2(743 ft.2)

AIRCRAFT TYPE VTP(Both Sides)

Fuselage andBelly Fairing

Nacelle and Pylon(All Engines)

Total Cleaned Area

A350--900 102 m2(1098 ft.2)

1073 m2(11550 ft.2)

166 m2(1787 ft.2)

2242 m2(24133 ft.2)

NOTE : Dimensions are approximate

5-9-0Page 1

Apr 01/15


OPERATING CONDITIONS

6-1-0 Engine Exhaust Velocities and Temperatures

**ON A/C A350-900

Engine Exhaust Velocities and Temperatures

1. GeneralThis section provides the estimated engine exhaust-efflux velocity and temperature contours forMaximum Take-Off (MTO), Breakaway 11% MTO, Breakaway 22% MTO and Ground Idleconditions for the A350 engines.The contours are available for the Rolls-Royce Trent XWB-84 engine.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 A350-900 at its maximum ramp weight, from a staticposition or when on an uphill surface with a slope of 1.5%. Breakaway thrust corresponds to 11%MTO when applied on both engines and 22% MTO when applied on a single engine (Idle thrust onthe other engine).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

Apr 01/15


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

**ON A/C A350-900

Engine Exhaust Velocities - Ground Idle Power

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

6-1-1Page 1

Apr 01/15


**ON A/C A350-900

020

4060

8010

012

014

016

018

020

0

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

VE

LOC

ITY

CO

NT

OU

RS

AT

GR

OU

ND

IDLE

AX

ISY

MM

ET

RIC

VIE

W

220

40 20 0

−20

−40

−60

−80

−10

0

RADIAL CO−ORDINATE (ft)

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2140−A

−001−0

1

P_AC_060101_1_0020001_01_00

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

6-1-1Page 2

Apr 01/15


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

**ON A/C A350-900

Engine Exhaust Temperatures - Ground Idle Power

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

6-1-2Page 1

Apr 01/15


**ON A/C A350-900

Tam

b +

30K

Tam

b +

20K

Tam

b +

10K

020

4060

8010

012

014

016

018

020

0

−40040

VERTICAL CO−ORDINATE (ft)

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

SA

T G

RO

UN

D ID

LE S

IDE

VIE

W

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2294−A

−001−0

1

P_AC_060102_1_0010001_01_00

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

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

6-1-2Page 2

Apr 01/15


**ON A/C A350-900

020

4060

8010

012

014

016

0

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

SA

T G

RO

UN

D ID

LE A

XIS

YM

ME

TR

IC V

IEW

40 20 0

−20

−40

−60

−80

−10

0


ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2141−A

−001−0

1

P_AC_060102_1_0010001_02_00

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

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

6-1-2Page 3

Apr 01/15


6-1-3 Engine Exhaust Velocities - Breakaway Power

**ON A/C A350-900

Engine Exhaust Velocities - Breakaway Power

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

6-1-3Page 1

Apr 01/15


**ON A/C A350-900

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2138−A

−001−0

1

50 ft

/sec

100

ft/se

c15

0 ft/

sec

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

VE

LOC

ITY

CO

NT

OU

RS

AT

11%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

060

140

200

280

340

400

2040

8010

012

016

018

022

024

026

030

036

038

032

0

RADIAL CO−ORDINATE (ft)40 20 0

−20

−40

−60

−80

−10

0

P_AC_060103_1_0010001_01_00

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

6-1-3Page 2

Apr 01/15


**ON A/C A350-900

50 ft

/sec

100

ft/se

c15

0 ft/

sec

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

VE

LOC

ITY

CO

NT

OU

RS

AT

22%

MT

O T

HR

US

T A

XIS

YM

ME

TR

IC V

IEW

010

020

030

040

050

060

0

40 20 0

−20

−40

−60

−80

−10

0


ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2136−A

−001−0

1

P_AC_060103_1_0020001_01_00

Breakaway Power (22% MTO Thrust) - TRENT XWB-84 EngineFIGURE-6-1-3-991-002-A01

6-1-3Page 3

Apr 01/15


6-1-4 Engine Exhaust Temperatures - Breakaway Power

**ON A/C A350-900

Engine Exhaust Temperatures - Breakaway Power

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

6-1-4Page 1

Apr 01/15


**ON A/C A350-900

Tam

b +

10K

Tam

b +

20K

Tam

b +

30K

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

SA

T 1

1% M

TO

TH

RU

ST

SID

E V

IEW

060

140

200

2040

8010

012

016

018

0


40 0

−40

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2292−A

−001−0

1

P_AC_060104_1_0010001_01_00

Breakaway Power (11% MTO Thrust) - TRENT XWB-84 Engine(Sheet 1 of 2)

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

6-1-4Page 2

Apr 01/15


**ON A/C A350-900

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2139−A

−001−0

1

Tam

b +

10K

Tam

b +

20K

Tam

b +

30K

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

SA

T 1

1% M

TO

TH

RU

ST

AX

ISY

MM

ET

RIC

VIE

W

060

140

200

2040

8010

012

016

018

0


40 20 0

−20

−40

−60

−80

−10

0

P_AC_060104_1_0010001_02_00


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

6-1-4Page 3

Apr 01/15


**ON A/C A350-900

Tam

b +

30K

Tam

b +

20K

Tam

b +

10K


−40040

020

4060

8010

012

014

016

018

020

0

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

SA

T 2

2% M

TO

TH

RU

ST

SID

E V

IEW

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2290−A

−001−0

1

P_AC_060104_1_0020001_01_00


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

6-1-4Page 4

Apr 01/15


**ON A/C A350-900

40 20 0

−20

−40

−60

−80

−10

0

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

SA

T 2

2% M

TO

TH

RU

ST

AX

ISY

MM

ET

RIC

VIE

W

020

4060

8010

012

014

016

018

020

0

Tam

b +

30K

Tam

b +

20K

Tam

b +

10K


ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2137−A

−001−0

1

P_AC_060104_1_0020001_02_00


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

6-1-4Page 5

Apr 01/15


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

**ON A/C A350-900

Engine Exhaust Velocities - Max Take-Off Power

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

6-1-5Page 1

Apr 01/15


**ON A/C A350-900

50 ft

/sec

100

ft/se

c15

0 ft/

sec

AX

IAL

CO−

OR

DIN

AT

E (

ft)

020

040

060

080

010

0012

0014

00

100 0

−10

0


ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2134−A

−001−0

1

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

VE

LOC

ITY

CO

NT

OU

RS

AT

MT

OA

XIS

YM

ME

TR

IC V

IEW

FO

R S

ING

LE E

NG

INE

OP

ER

AT

ION

P_AC_060105_1_0030001_01_00

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

6-1-5Page 2

Apr 01/15


**ON A/C A350-900


50 ft

/sec

100

ft/se

c15

0 ft/

sec

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

VE

LOC

ITY

CO

NT

OU

RS

AT

MT

OS

IDE

VIE

W F

OR

TW

IN−

EN

GIN

E O

PE

RA

TIO

N

020

040

060

080

010

0012

0014

00

40 0

−40

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2133−A

−001−0

1

P_AC_060105_1_0040001_01_00

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

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

6-1-5Page 3

Apr 01/15


**ON A/C A350-900

LATERAL CO−ORDINATE (ft)

020

040

060

080

010

0012

0014

00

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

VE

LOC

ITY

CO

NT

OU

RS

AT

MT

OP

LAN

VIE

W F

OR

TW

IN −

EN

GIN

E O

PE

RA

TIO

N

100 0

−10

0

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2132−A

−001−0

1

P_AC_060105_1_0040001_02_00

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

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

6-1-5Page 4

Apr 01/15


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

**ON A/C A350-900

Engine Exhaust Temperatures - Max Take-Off Power

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

6-1-6Page 1

Apr 01/15


**ON A/C A350-900

Tam

b +

10K

Tam

b +

20K

Tam

b +

30K

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

S A

T M

TO

SID

E V

IEW

010

020

030

040

050

0


40 0

−40

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2288−A

−001−0

1

P_AC_060106_1_0030001_01_00

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

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

6-1-6Page 2

Apr 01/15


**ON A/C A350-900

ICN−T

RE

NTX

WB−A

−710

000−

R−K

0680−0

2135−A

−001−0

1

Tam

b +

10K

Tam

b +

20K

Tam

b +

30K

AX

IAL

CO−

OR

DIN

AT

E (

ft)

TR

EN

T X

WB

840

00 lb

f TH

RU

ST

EN

GIN

E −

ES

TIM

AT

ED

EX

HA

US

T E

FF

LUX

TE

MP

ER

AT

UR

E C

ON

TO

UR

S A

T M

TO

AX

ISY

MM

ET

RIC

VIE

W

010

020

030

040

050

0

40 20 0

−20

−40

−60

−80

−10

0


P_AC_060106_1_0030001_02_00

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

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

6-1-6Page 3

Apr 01/15


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

**ON A/C 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

Apr 01/15


**ON A/C A350-900

45°

1.6 m(5 ft)

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

P_AC_060301_1_0010001_01_00

Ground Idle Power - TRENT XWB-84 EngineFIGURE-6-3-1-991-001-A01

6-3-1Page 2

Apr 01/15


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

**ON A/C A350-900

Danger Areas of the Engines - Max Take-Off Power

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

6-3-3Page 1

Apr 01/15


**ON A/C A350-900

30°

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

INTAKE SUCTION DANGER AREA

EXHAUST DANGER AREA

R 9.1 m(30 ft)

P_AC_060303_1_0010001_01_00

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

6-3-3Page 2

Apr 01/15


6-4-0 APU Exhaust Velocities and Temperatures

**ON A/C A350-900

APU Exhaust Velocities and Temperatures

1. This section gives APU exhaust velocities and temperatures.

6-4-0Page 1

Apr 01/15


**ON A/C A350-900

P_AC_060400_1_0010001_01_00

0 5 10 15 200

5

10

0

0 10

0 5 10 15 200

5

10

0

FD

FD

[m]

[ft]

[m] [ft]

[m]

[ft]

0

[m] [ft]

15 m/s30.5 m/s46 m/s61 m/s

93°C

149°C204°C

315.5°C427°C

260°C

20 30 40 50 60

10

20

30

40

10

20

30

40

10 20 30 40 50 60

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

6-4-0Page 2

Apr 01/15


PAVEMENT DATA


**ON A/C 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 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 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

Apr 01/15


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 referred to 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 andS-77-1 for 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 - Medium X - High pressure limitedto 1.75 MPa (254 psi)

U - Using Aircraft

7-1-0Page 2

Apr 01/15


PCN

PAVEMENT TYPESUBGRADECATEGORY

TIRE PRESSURECATEGORY

EVALUATIONMETHOD

C - Low Y - Medium pressurelimited to 1.25 MPa (181psi)

D - Ultra Low Z - 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/m 3 (550 pci)

- B. Medium Strength k = 80 MN/m 3 (300 pci)

- C. Low Strength k = 40 MN/m 3 (150 pci)

- D. Ultra Low Strength k = 20 MN/m 3 (75 pci)

7-1-0Page 3

Apr 01/15


7-2-0 Landing Gear Footprint

**ON A/C A350-900

Landing Gear Footprint

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

7-2-0Page 1

Apr 01/15


**ON A/C A350-900

268 900 kg(592 825 lb) 93.7% 1050x395R16 28PR 1400x530R23 42PR

93.7% 1050x395R16 28PR 1400x530R23 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

WING GEAR TIRESIZE

WING GEARTIRE

PRESSURE

94.8% 1050x395R16 28PR 1400x530R23 42PRA350−900WV002

272 900 kg(601 650 lb)

12.2 bar(177 psi)

16.6 bar(241 psi)

P_AC_070200_1_0010001_01_02

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

7-2-0Page 2

Apr 01/15


7-3-0 Maximum Pavement Loads

**ON A/C 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

Apr 01/15


**ON A/C A350-900

V(NG)

MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT FORWARD CG

V(MG)

H

MAXIMUM VERTICAL MAIN GEAR GROUND LOAD AT AFT CG

MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING

1 2 3 4 5

(PER STRUT)

V(MG) H (PER STRUT)

WEIGHTVARIANT

MAXIMUMRAMP

WEIGHTAT

STATIC LOAD

FWD CG AT 10 ft/s²DECELERATION

BRAKINGSTATIC

BRAKINGCOEFFICIENT = 0.8

INSTANTANEOUSAT

268 900 kg(592 825 lb)

125 960 kg(277 700 lb)

129 330 kg(285 125 lb)

23.4 %MAC(b)

33 %MAC(a)

23.4 %MAC(b)

33.2 %MAC(a)

275 900 kg(608 250 lb)

23 450 kg(51 700 lb)

23 450 kg(51 700 lb)

37 500 kg(82 675 lb)

37 500 kg(82 675 lb)

ATSTATIC LOAD

AFT CG AT 10 ft/s²DECELERATION

BRAKINGSTEADY

6

42 880 kg(94 525 lb)

41 790 kg(92 125 lb)

(c)

(c)

42 410 kg(93 500 lb)

(c)

(c)103 460 kg(228 100 lb)

(c)100 770 kg(222 150 lb)

(c)103 450 kg(228 075 lb)

A350−900WV000

A350−900WV001

(b) LOADS CALCULATED USING AIRCRAFT AT 250 200 kg (551 600 lb)(c) BRAKED MAIN GEAR

NOTE:(a) LOADS CALCULATED USING AIRCRAFT AT MRW

V(NG)

H

V(MG)

V(NG)

129 310 kg(285 075 lb)

23.4 %MAC(b)

36.39 %MAC(a)

272 900 kg(601 650 lb)

23 450 kg(51 700 lb)

37 500 kg(82 675 lb)

A350−900WV002

P_AC_070300_1_0010001_01_02

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

7-3-0Page 2

Apr 01/15


7-4-0 Landing Gear Loading on Pavement

**ON A/C 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, see FIGURE 7-4-0-991-001-A, calculation of the total weight on the MLG for:- An aircraft with a MRW of 268 900 kg (592 825 lb),- The aircraft gross weight is 210 000 kg (462 975 lb),- A percentage of weight on the MLG of 93.68 % (percentage of weight on the MLG at MRW and

maximum aft CG).The total weight on the MLG group is 196 730 kg (433 725 lb).

NOTE : The CG in the figure title is the CG used for ACN/LCN calculation.

7-4-0Page 1

Apr 01/15


**ON A/C A350-900

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

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

CG FOR ACN/LCNCALCULATION

33% MACMTOW − 268 000 kg

25.46% MAC

TAKE OFF

LANDING

MZFW

MLW

P_AC_070400_1_0010001_01_01

Landing Gear Loading on PavementWV000, MRW 268 900 kg, CG 33%

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

7-4-0Page 2

Apr 01/15


**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

PERCENTAGE OF WEIGHT ON MAIN GEAR

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

Apr 01/15


7-5-0 Flexible Pavement Requirements - US Army Corps of Engineers Design Method

**ON A/C A350-900

Flexible Pavement Requirements - US Army Corps of Engineers Design Method

1. This section provides data about the flexible pavement requirements.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 the highest ACN for each typeof aircraft.They are calculated with the US Army Corps of Engineers Design Method.To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annualdeparture level and the weight on one MLG.The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).The procedure that follows is used to develop flexible pavement design curves:- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random

line is made to show 10 000 coverages,- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shown

on the graph.Example, see FIGURE 7-5-0-991-001-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MRW of 268 900 kg (592 825 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

Apr 01/15


**ON A/C A350-900

LANDING GEARWEIGHT ON ONE MAIN

125 960 kg110 000 kg100 000 kg

90 000 kg80 000 kg

(277 700 lb)(242 500 lb)(220 450 lb)(198 425 lb)(176 375 lb)

SUBGRADE STRENGTH − CBR

8060403020151063

8060403020151063

FLEXIBLE PAVEMENT THICKNESS

10 15 20 30 40 60 80 100 120 150 180(cm)

(in)

10 000 COVERAGES USEDFOR ACN CALCULATIONSALPHA FACTOR = 0.8

1400x530R23 42PR TIRES

TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)

1 2003 0006 00015 000

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE25 000

MAXIMUM POSSIBLEMAIN GEAR LOADAT MAXIMUM RAMPWEIGHT AND AFT CG

P_AC_070500_1_0010001_01_02

Flexible Pavement RequirementsWV000, MRW 268 900 kg, CG 33%

FIGURE-7-5-0-991-001-A01

7-5-0Page 2

Apr 01/15


**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)

10 000 COVERAGES USEDFOR ACN CALCULATIONSALPHA FACTOR = 0.8

MAXIMUM POSSIBLEMAIN GEAR LOADAT MAXIMUM RAMPWEIGHT AND AFT CG

1 2003 0006 00015 000

ANNUAL DEPARTURES*

*20 YEAR PAVEMENT LIFE25 000

SUBGRADE STRENGTH − CBR

FLEXIBLE PAVEMENT THICKNESS

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

Apr 01/15


7-6-0 Flexible Pavement Requirements - LCN Conversion

**ON A/C 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

Apr 01/15


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

**ON A/C 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 MLG loading on pavement graphs are given for the weight variants that produce (at the MRWand maximum aft CG and standards tire pressure) the lowest ACN and the highest ACN for eachtype 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 weight on the MLG are made based on the curve for

k = 80 MN/m3 , already shown on the graph.Example, see FIGURE 7-7-0-991-001-A, calculation of the thickness of the rigid pavement for:- An aircraft with a MRW of 268 900 kg (592 825 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

Apr 01/15


**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)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

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.

125 960 kg110 000 kg100 000 kg

90 000 kg80 000 kg

(277 700 lb)(242 500 lb)(220 450 lb)(198 425 lb)(176 375 lb)

P_AC_070700_1_0010001_01_01

Rigid Pavement RequirementsWV000, MRW 268 900 kg, CG 33%

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

7-7-0Page 2

Apr 01/15


**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

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.

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

Apr 01/15


7-8-0 Rigid Pavement Requirements - LCN Conversion

**ON A/C 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

Apr 01/15


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

**ON A/C 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 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 the highest ACN for each typeof 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 DesignManual Part 3 Chapter 1 Second Edition 1983).

For example, see FIGURE 7-9-0-991-001-A (sheet 1), calculation of the ACN for flexible pavementfor:- An aircraft with a MRW of 268 900 kg (592 825 lb)- An aircraft gross weight of 210 000 kg (462 975 lb)- A medium subgrade strength (code B).The ACN for flexible pavement is 51.For example, see FIGURE 7-9-0-991-001-A (sheet 2), calculation of the ACN for rigid pavement for:- An aircraft with a MRW of 268 900 kg (592 825 lb)- An aircraft gross weight of 210 000 kg (462 975 lb)- A medium subgrade strength (code B).The ACN for rigid pavement is 52.

2. Aircraft Classification Number - ACN TableThe table (FIGURE 7-9-0-991-003-A) provides ACN data in tabular format similar to the one used byICAO in the ”Aerodrome Design Manual Part 3, Pavements - Edition 1983” for all the operationalweight 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)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)With ACN max: ACN calculated at the MRW in the table and with ACN min: ACN calculated at 142000 kg.


7-9-0Page 1

Apr 01/15


**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.

6 ba

r (2

41 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.

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

P_AC_070900_1_0010001_01_01

ACN/PCN Reporting System - WV000, MRW 268 900 kg, CG 33%Flexible Pavement (Sheet 1 of 2)

FIGURE-7-9-0-991-001-A01

7-9-0Page 2

Apr 01/15


**ON A/C A350-900

1400

x530

R23

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 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)

(x 1

000

lb)

P_AC_070900_1_0010001_02_00

ACN/PCN Reporting System - WV000, MRW 268 900 kg, CG 33%Rigid Pavement (Sheet 2 of 2)FIGURE-7-9-0-991-001-A01

7-9-0Page 3

Apr 01/15


**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

ACN/PCN Reporting System - WV001, MRW 275 900 kg, CG 33.2%Flexible Pavement (Sheet 1 of 2)

FIGURE-7-9-0-991-002-A01

7-9-0Page 4

Apr 01/15


**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

ACN/PCN Reporting System - WV001, MRW 275 900 kg, CG 33.2%Rigid Pavement (Sheet 2 of 2)FIGURE-7-9-0-991-002-A01

7-9-0Page 5

Apr 01/15


**ON A/C A350-900

63 70 82 95 65 69 79 109

33 36 41 31 3232 34 41

65 73 85 98 68 72 82 113

33 36 41 31 3232 34 41

65 73 85 98 67 72 82 113

33 36 41 31 3233 34 42

LOADON ONE

MAINGEAR

LEG (%) MEDIUM10

HIGH15

ULTRA−LOW20

LOW40

MEDIUM80

HIGH150

LOW6

ULTRA−LOW3

ACN FORFLEXIBLE PAVEMENTSUBGRADES − CBR

ACN FORRIGID PAVEMENT

SUBGRADES − MN/m³TIREPRESSURE

(MPa)

ALL UPMASS

(kg)

WEIGHTVARIANT

A350−900WV000

A350−900WV001

A350−900WV002

268 900

142 000

275 900

142 000

272 900

142 000

46.8

46.9

47.4

1.66

1.68

1.66

P_AC_070900_1_0030001_01_00

ACN TableFIGURE-7-9-0-991-003-A01

7-9-0Page 6

Apr 01/15


SCALED DRAWINGS

8-0-0 Scaled Drawings

**ON A/C 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

Apr 01/15


**ON A/C A350-900

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

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

010

2030

4050

60F

EE

T

04

812

1620

ME

TE

RS

NOTE:

P_AC_080000_1_0010001_01_00

Scaled DrawingsFIGURE-8-0-0-991-001-A01

8-0-0Page 2

Apr 01/15


AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 Aircraft Rescue and Fire Fighting

**ON A/C A350-900

Aircraft Rescue and Fire Fighting

1. This 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

Apr 01/15


**ON A/C A350-900

RE

FE

RE

NC

E

:

AP

RIL

201

5A

IRB

US

S.A

.SC

US

TO

ME

R S

ER

VIC

ES

TE

CH

NIC

AL

DA

TA

SU

PP

OR

T A

ND

SE

RV

ICE

S31

707

BLA

GN

AC

CE

DE

XF

RA

NC

E

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_03

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

10-0-0Page 2

Apr 01/15


**ON A/C A350-900

P_AC_100000_1_0030001_01_02

Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-003-A01

10-0-0Page 3

Apr 01/15


**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 4

Apr 01/15


**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 5

Apr 01/15


**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 6

Apr 01/15


**ON A/C A350-900

ALU

ALL

OY

CF

RP

MO

NO

LIT

HIC

CF

RP

SA

ND

WIC

H

QU

AR

TZ

, GLA

SS

TIT

AN

IUM

CO

MP

OS

ITE

MA

TE

RIA

LS

P_AC_100000_1_0060001_01_00

Composite Materials LocationFIGURE-10-0-0-991-006-A01

10-0-0Page 7

Apr 01/15


**ON A/C A350-900

P_AC_100000_1_0070001_01_00

NO

SE

LA

ND

ING

GE

AR

MA

IN L

AN

DIN

G G

EA

R

TY

PIC

AL

INS

TA

LLA

TIO

N

Ground Lock Safety DevicesFIGURE-10-0-0-991-007-A01

10-0-0Page 8

Apr 01/15


**ON A/C A350-900

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

EN

OT

E:

03691215

− R

H S

HO

WN

, LH

SY

MM

ET

RIC

AL.

− D

IME

NS

ION

S A

RE

AP

PR

OX

IMA

TE

.

GR

ID E

QU

ALS

1 m

(3.

28 ft

) IN

RE

ALI

TY

CA

BIN

DU

AL−

LAN

ES

LID

E/R

AF

T9.

43 m

(30

.94

ft)

CA

BIN

DU

AL−

LAN

ES

LID

E/R

AF

T9.

38 m

(30

.77

ft)

CA

BIN

SIN

GLE

−LA

NE

SLI

DE

/RA

FT

10.2

5 m

(33

.63

ft)C

OC

KP

ITE

SC

AP

E R

OP

E

CA

BIN

DU

AL−

LAN

ES

LID

E/R

AF

T9.

35 m

(30

.68

ft)

P_AC_100000_1_0080001_01_02

Emergency Evacuation DevicesFIGURE-10-0-0-991-008-A01

10-0-0Page 9

Apr 01/15


**ON A/C A350-900

PA

SS

EN

GE

R/C

RE

W D

OO

RS

AN

D E

ME

RG

EN

CY

EX

ITS

EX

TE

RIO

R C

ON

TR

OL

HA

ND

LE

SR

ES

IDU

AL

CA

BIN−

PR

ES

SU

RE

WA

RN

ING−

LIG

HT

SLI

DE

AR

ME

D W

AR

NIN

G−

LIG

HT

AN

D B

UZ

ZE

R(S

LID

E W

ILL

BE

DIS

AR

ME

D A

UT

OM

AT

ICA

LLY

IFD

OO

R IS

OP

EN

FR

OM

OU

TS

IDE

)

OU

TE

R H

AN

DLE

ME

CH

AN

ICA

LD

OO

R−

LOC

KIN

G IN

DIC

AT

OR

S

TO O

PE

N:

1 −

MA

KE

SU

RE

TH

AT

RE

SID

UA

L C

AB

IN−P

RE

SS

UR

E W

AR

NIN

G L

IGH

TS D

OE

S N

OT

FLA

SH

.2 −

PU

SH

FLA

P T

O G

RA

SP

HA

ND

LE.

3 −

LIFT

HA

ND

LE F

ULL

Y U

P T

O H

OR

IZO

NTA

L P

OS

ITIO

N (G

RE

EN

LIN

E).

4 −

PU

LL T

HE

DO

OR

OU

T A

ND

MO

VE

IT F

OR

WA

RD

.

P_AC_100000_1_0090001_01_00

Pax/Crew Doors and Emergency ExitsFIGURE-10-0-0-991-009-A01

10-0-0Page 10

Apr 01/15


**ON A/C A350-900

ES

CA

PE

RO

PE

TH

E E

SC

AP

E H

AT

CH

IS T

HE

CO

CK

PIT

EM

ER

GE

NC

Y E

XIT

.

TO

OP

EN

:1 −

PU

SH

ON

TH

E H

AN

DLE

. TH

E H

AN

DLE

IS E

JEC

TE

D F

RO

M IT

S H

OU

SIN

G.

2 −

TU

RN

TH

E H

AN

DLE

CO

UN

TE

RC

LOC

KW

ISE

TO

DE

SE

NG

AG

E T

HE

LA

TC

HE

S.

3 −

PU

SH

ON

TH

E E

SC

AP

E H

AT

CH

. IT

OP

EN

S IN

SID

E T

HE

CO

CK

PIT

.

NO

TE

:

MA

KE

SU

RE

TH

AT

NO

PE

RS

ON

IN T

HE

CO

CK

PIT

IS B

ELO

W T

HE

ES

CA

PE

HA

TC

H.

P_AC_100000_1_0100001_01_00

Cockpit Emergency ExitFIGURE-10-0-0-991-010-A01

10-0-0Page 11

Apr 01/15


**ON A/C A350-900

FW

D A

ND

AF

T C

AR

GO−C

OM

PA

RT

ME

NT

DO

OR−C

ON

TR

OL

S

HY

DR

AU

LIC

AU

XIL

IAR

YP

UM

P

LOC

K H

AN

DLE

HA

ND

LE

DR

ILLI

NG

MA

CH

INE

HY

DR

AU

LIC

AU

XIL

IAR

Y−

PU

MP

GE

AR

BO

X

IND

ICA

TO

R W

IND

OW

S

IND

ICA

TO

R F

LAG

EX

TE

NS

ION

HA

ND

LE

YE

LLO

WG

RO

UN

DS

ER

VIC

E−

PA

NE

L

LAT

CH

HA

ND

LE

CA

RG

O C

OM

PA

RT

ME

NT

DO

OR

MA

NU

AL

OP

ER

AT

ING

DE

VIC

E

TO

GG

LE S

WIT

CH

GR

EE

NIN

DIC

AT

OR

LIG

HT

197L

B

194K

B

194K

B

EN

SU

RE

TH

AT

ALL

PE

RS

ON

NE

L A

ND

EQ

UIP

ME

NT

AR

EW

AR

NIN

G: M

AK

E S

UR

E T

HA

T T

HE

RE

SID

UA

L P

RE

SS

UR

EW

AR

NIN

G:

CLE

AR

OF

CA

RG

O D

OO

R A

RE

A.

WA

RN

ING−

LIG

HT

DO

ES

NO

T F

LAS

H.

MA

NU

AL

OP

ER

AT

ION

NO

TE

:

TW

O O

PE

RA

TO

RS

AR

E N

EC

ES

SA

RY

FO

R T

HIS

OP

ER

AT

ION

.1 −

DO

OP

ER

AT

ION

S 1

AN

D 2

OF

TH

E "

NO

RM

AL

OP

ER

AT

ION

" P

RO

CE

DU

RE

.2 −

ON

TH

E Y

ELL

OW

GR

OU

ND

SE

RV

ICE−

PA

NE

L, D

O S

TE

P (

A)

OR

(B

):(A

) C

ON

NE

CT

A D

RIL

LIN

G M

AC

HIN

E (

WIT

H S

OC

KE

T D

IA 1

/2 in

(12

.7 m

m))

.(B

) A

TT

AC

H T

HE

HY

DR

AU

LIC

AU

XIL

IAR

Y−

PU

MP

GE

AR

BO

X T

O T

HE

HY

DR

AU

LIC

AU

XIL

IAR

Y P

UM

P. C

ON

NE

CT

TH

E H

AN

DLE

(S

TO

RE

D O

N

) A

ND

TH

E E

XT

EN

SIO

N H

AN

DLE

(S

TO

RE

D O

N

) W

ITH

TH

E H

YD

RA

ULI

C A

UX

ILIA

RY−

PU

MP

GE

AR

BO

X.

3 −

OP

ER

AT

E T

HE

HY

DR

AU

LIC

AU

XIL

IAR

Y−

PU

MP

GE

AR

BO

X(A

T N

OT

MO

RE

TH

AN

100

RP

M).

4 −

TU

RN

TH

E M

AN

UA

L O

PE

RA

TIN

G D

EV

ICE

TO

TH

E "

OP

EN

" P

OS

ITIO

N(C

LOC

KW

ISE

) A

ND

HO

LD IT

UN

TIL

TH

E G

RE

EN

IND

ICA

TO

R L

IGH

TC

OM

ES

ON

(C

AR

GO

DO

OR

FU

LLY

OP

EN

AN

D L

OC

KE

D).

5 −

RE

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TH

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LL T

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OR

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DIC

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TH

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TO

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4 −

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ND

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TH

E T

OG

GLE

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ITC

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SID

UA

LP

RE

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AR

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194K

B19

7LB

P_AC_100000_1_0110001_01_01

FWD and AFT Lower Deck Cargo DoorsFIGURE-10-0-0-991-011-A01

10-0-0Page 12

Apr 01/15


**ON A/C A350-900

INS

TA

LLE

D O

N N

LG

P_AC_100000_1_0120001_01_00

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

10-0-0Page 13

Apr 01/15


**ON A/C A350-900

AP

U A

CC

ES

S D

OO

RS

OP

ER

AT

ION

:

1 −

OP

EN

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RP

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2 −

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TH

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AF

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TH

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AC

CE

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AT

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IN L

AT

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(F

OR

WA

RD

AN

D A

FT

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OP

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CE

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P_AC_100000_1_0150001_01_01

APU Compartment AccessFIGURE-10-0-0-991-015-A01

10-0-0Page 14

Apr 01/15


**ON A/C A350-900

P_AC_100000_1_0160001_01_01

mft

5.33

6.52

2.66

6.20

5.37

5.27

5.21

17.4

9

21.3

98.

73

20.3

417

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917

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2.08

6.82

CO

NF

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RA

TIO

NA

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BF

1

CP

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1D

2D

3D

4

BF

2

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3.29

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610

.79

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10.7

0

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C2

C3

2.59

8.50

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3

7.61

24.9

7D

5

(142

000

kg)

AF

T C

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40%

)

DIM

EN

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NS

AR

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RA

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ND

CG

CO

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mft

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8.86

4.64

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79.

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04

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217

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030

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3.84

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28.8

127

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12.6

0

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2F

T3

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WL1

WL2F2

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(142

000

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RA

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T1.

254.

10

Aircraft Ground ClearancesFIGURE-10-0-0-991-016-A01

10-0-0Page 15

Apr 01/15


**ON A/C A350-900

= =

CO

LOR

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NO

T M

AR

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DO

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LL A

IRC

RA

FT

==

CU

T H

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E IN

EM

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GE

NC

Y

P_AC_100000_1_0170001_01_01

Structural Break-in PointsFIGURE-10-0-0-991-017-A01

10-0-0Page 16

Apr 01/15


**ON A/C A350-900

TH

E B

AT

TE

RY

CA

SE

AN

D T

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EX

HA

US

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:

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A

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B

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BA

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SS

VIA

FW

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CO

MP

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TM

EN

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BA

T 1BA

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AC

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SS

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811

A

C

P_AC_100000_1_0180001_01_01

Batteries Location and AccessFIGURE-10-0-0-991-018-A01

10-0-0Page 17

Apr 01/15

Documents

A350-900 AIRCRAFT CHARACTERISTICS AIRPORT AND MAINTENANCE ...com.airbus-fenice.customers.artful.net/fileadmin/media_gallery/... · @a350-900 aircraft characteristics - airport and