airbus a350-900 booklet

@AIRBUSA350-900

AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING

AC

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

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

AIRBUS S.A.S.Customer Services

Technical Data Support and Services31707 Blagnac Cedex

FRANCE

Issue: Jun 01/13 Rev: Jun 01/13

@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

LIST OF EFFECTIVE CONTENT

Revision No. 0 - Jun 01/13

CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 1

Subject 1-1-0

Introduction N Jun 01/13

Subject 1-2-0

Glossary N Jun 01/13

CHAPTER 2

Subject 2-1-0

General Aircraft Characteristics N Jun 01/13

Subject 2-2-0

General Aircraft Dimensions N Jun 01/13

FIGURE General Aircraft Dimensions N Jun 01/13

Subject 2-3-0

Ground Clearances N Jun 01/13

FIGURE Ground Clearances N Jun 01/13

Subject 2-4-0

Interior Arrangements - Plan View N Jun 01/13

FIGURE Standard Configuration N Jun 01/13

Subject 2-5-0

Interior Arrangements - Cross Section N Jun 01/13

FIGURE Typical Configuration N Jun 01/13

Subject 2-6-0

Cargo Compartments N Jun 01/13

FIGURE Cargo Compartments N Jun 01/13

Subject 2-7-0

Door Clearances and Location N Jun 01/13

FIGURE Door Location N Jun 01/13

L.E.C.Page 1

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Subject 2-7-1

Forward Doors N Jun 01/13

FIGURE Forward Doors N Jun 01/13

FIGURE Forward Doors N Jun 01/13

Subject 2-7-3

Aft Doors N Jun 01/13

FIGURE Aft Doors N Jun 01/13

FIGURE Aft Doors N Jun 01/13

Subject 2-7-4

Forward Cargo Compartment Door N Jun 01/13

FIGURE Forward Cargo Compartment Door N Jun 01/13

Subject 2-7-5

Aft Cargo Compartment Door N Jun 01/13

FIGURE Aft Cargo Compartment Door N Jun 01/13

Subject 2-7-6

Bulk Cargo Compartment Door N Jun 01/13

FIGURE Bulk Cargo Compartment Door N Jun 01/13

Subject 2-7-7

Nose Landing Gear Doors N Jun 01/13

FIGURE Nose Landing Gear Doors N Jun 01/13

Subject 2-7-8

Main Landing Gear Doors N Jun 01/13

FIGURE Main Landing Gear Doors N Jun 01/13

Subject 2-8-0

Escape Slides N Jun 01/13

FIGURE Escape Slides N Jun 01/13

Subject 2-9-0

Landing Gear N Jun 01/13

FIGURE Main Landing Gear N Jun 01/13

L.E.C.Page 2

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Nose Landing Gear N Jun 01/13

Subject 2-10-0

Exterior Lighting N Jun 01/13

FIGURE Exterior Lighting N Jun 01/13





Subject 2-11-0

Antennas and Probes Location N Jun 01/13

FIGURE Antennas and Probes Location N Jun 01/13

Subject 2-12-0

Engine and Nacelle N Jun 01/13

FIGURE Engine and Nacelle N Jun 01/13

Subject 2-12-1

APU N Jun 01/13

FIGURE APU N Jun 01/13

Subject 2-13-0

Levelling, Symmetry and Alignement N Jun 01/13

FIGURE Location of Leveling Points N Jun 01/13

Subject 2-14-1

Jacking for Maintenance N Jun 01/13

FIGURE Jacking for Maintenance N Jun 01/13

Subject 2-14-2

Jacking for wheel change N Jun 01/13

FIGURE Nose Landing Gear Jacking Point Heights N Jun 01/13

FIGURE Main Landing Gear Jacking Point Heights N Jun 01/13

CHAPTER 4

Subject 4-2-0

L.E.C.Page 3

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Turning Radii N Jun 01/13

FIGURE Turning Radii N Jun 01/13

Subject 4-3-0

Minimum Turning Radii N Jun 01/13

FIGURE Minimum Turning Radii N Jun 01/13

Subject 4-4-0

Visibility from Cockpit in Static Position N Jun 01/13

FIGURE Visibility from Cockpit in Static Position N Jun 01/13

Subject 4-5-0

Introduction N Jun 01/13

Subject 4-5-1

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

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

Subject 4-5-2

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

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

Subject 4-5-3

180˚ Turn on a Runway N Jun 01/13

FIGURE 180˚ Turn on a Runway N Jun 01/13

Subject 4-5-4

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

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

Subject 4-5-5

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

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

Subject 4-6-0

Runway Holding Bay (Apron) N Jun 01/13

FIGURE Runway Holding Bay (Apron) N Jun 01/13

Subject 4-7-0

L.E.C.Page 4

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Minimum Line-Up Distance Corrections N Jun 01/13

FIGURE 90˚ Turn on Runway Entry N Jun 01/13

FIGURE 180˚ Turn on Runway Turn Pad N Jun 01/13

FIGURE 180˚ Turn on Runway Width N Jun 01/13

Subject 4-8-0

Aircraft Mooring N Jun 01/13

FIGURE Aircraft Mooring N Jun 01/13

CHAPTER 5

Subject 5-1-0

Aircraft Servicing Arrangements N Jun 01/13

Subject 5-1-1

Typical Ramp Layout (Open Apron) N Jun 01/13

FIGURE Typical Ramp Layout (Open Apron) N Jun 01/13

Subject 5-1-2

Typical Ramp Layout (Gate) N Jun 01/13

FIGURE Typical Ramp Layout (Gate) N Jun 01/13

Subject 5-2-0

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

FIGURE Full Servicing Turn Round Time Chart N Jun 01/13

Subject 5-3-0

Terminal Operations - Transit Turn Round Time N Jun 01/13

FIGURE Transit Turn Round Time N Jun 01/13

Subject 5-4-0

Ground Service Connections layout N Jun 01/13

FIGURE Ground Service Connections layout N Jun 01/13

Subject 5-4-1

Grounding Points N Jun 01/13

FIGURE Ground Point NLG N Jun 01/13

FIGURE Ground Point MLG N Jun 01/13

L.E.C.Page 5

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

Subject 5-4-2

Hydraulic System N Jun 01/13

FIGURE Green Ground Service Panel N Jun 01/13

FIGURE Yellow Ground Service Panel N Jun 01/13

Subject 5-4-3

Electrical System N Jun 01/13

FIGURE Electrical Service Panel N Jun 01/13

FIGURE RAT N Jun 01/13

Subject 5-4-4

Oxygen System N Jun 01/13

FIGURE Oxygen System N Jun 01/13

Subject 5-4-5

Fuel System N Jun 01/13

FIGURE Refuel/Defuel Control Panel N Jun 01/13

FIGURE Ground Service Connections N Jun 01/13

FIGURE NACA and Overpressure Locations N Jun 01/13

Subject 5-4-6

Pneumatic System N Jun 01/13

FIGURE Low Pressure Preconditioned Air N Jun 01/13

FIGURE High Pressure Preconditioned Air N Jun 01/13

Subject 5-4-7

Potable Water System N Jun 01/13

FIGURE Potable Water Ground Service Panel N Jun 01/13

FIGURE Forward Drain panel N Jun 01/13

FIGURE Potable Water Tanks Location N Jun 01/13

Subject 5-4-8

Oil System N Jun 01/13

FIGURE Engine Oil Servicing N Jun 01/13

FIGURE VFG Oil Servicing N Jun 01/13

L.E.C.Page 6

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Starter Oil Servicing N Jun 01/13

FIGURE APU Oil Servicing N Jun 01/13

Subject 5-4-9

Vacuum Toilet System N Jun 01/13

FIGURE Ground Service Panel N Jun 01/13

FIGURE Waste Tanks Location N Jun 01/13

Subject 5-6-0

Ground Pneumatic Power Requirements N Jun 01/13

FIGURE Ground Pneumatic Power Requirements N Jun 01/13

Subject 5-7-0

Preconditioned Airflow Requirements N Jun 01/13

FIGURE Preconditioned Airflow Requirements N Jun 01/13

Subject 5-8-0

Towing Requirements N Jun 01/13

FIGURE Towing Requirements N Jun 01/13

Subject 5-9-0

De-icing and External cleaning N Jun 01/13

CHAPTER 6

Subject 6-4-0

APU Exhaust Velocities and Temperatures N Jun 01/13

FIGURE APU Exhaust Velocities and Temperatures N Jun 01/13

CHAPTER 7

Subject 7-1-0

General Information N Jun 01/13

Subject 7-2-0

Landing Gear Footprint N Jun 01/13

FIGURE Landing Gear Footprint N Jun 01/13

Subject 7-3-0

Maximum Pavement Loads N Jun 01/13

L.E.C.Page 7

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

FIGURE Maximum Pavement Loads N Jun 01/13

Subject 7-4-0

Landing Gear Loading on Pavement N Jun 01/13

FIGURE Landing Gear Loading on Pavement N Jun 01/13

Subject 7-5-0

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

N Jun 01/13

FIGURE Flexible Pavement Requirements N Jun 01/13

Subject 7-6-0

Flexible Pavement Requirements - LCN Conversion N Jun 01/13

FIGURE Flexible Pavement Requirements - LCN N Jun 01/13

Subject 7-7-0

Rigid Pavement Requirements - Portland Cement Association DesignMethod

N Jun 01/13

FIGURE Rigid Pavement Requirements N Jun 01/13

Subject 7-8-0

Rigid Pavement Requirements - LCN Conversion N Jun 01/13

FIGURE Rigid Pavement Requirements - LCN N Jun 01/13

Subject 7-8-1

Radius of Relative Stiffness (L) N Jun 01/13

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

Subject 7-8-2

Radius of Relative Stiffness (Other values of E and µ) N Jun 01/13

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

Subject 7-9-0

Aircraft Classification Number - Flexible Pavement N Jun 01/13

FIGURE Aircraft Classification Number - Flexible Pavement N Jun 01/13

Subject 7-9-1

Aircraft Classification Number - Rigid Pavement N Jun 01/13

FIGURE Aircraft Classification Number - Rigid Pavement N Jun 01/13

L.E.C.Page 8

Jun 01/13


CONTENT CHGCODE

LAST REVISIONDATE

CHAPTER 8

Subject 8-0-0

Scaled Drawings N Jun 01/13

FIGURE Scaled Drawings N Jun 01/13

CHAPTER 10

Subject 10-0-0

Aircraft Rescue and Fire Fighting N Jun 01/13

FIGURE Front Page N Jun 01/13

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

FIGURE Crew Rest Compartments Location N Jun 01/13

FIGURE Wheel/Brake Overheat N Jun 01/13

FIGURE Composite Materials Location N Jun 01/13

FIGURE Ground Lock Safety Devices N Jun 01/13

FIGURE Emergency Evacuation Devices N Jun 01/13

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

FIGURE Cockpit Emergency Exit N Jun 01/13

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

FIGURE Control Panels N Jun 01/13

FIGURE APU Compartment Access N Jun 01/13

FIGURE Aircraft Ground Clearances N Jun 01/13

FIGURE Structural Break-in Points N Jun 01/13

FIGURE Batteries Location and Access N Jun 01/13

L.E.C.Page 9

Jun 01/13


TABLE OF CONTENTS

1 SCOPE

1-1-0 INTRODUCTION

1-2-0 Glossary

2 AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics

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

2-7-1 Forward Doors

2-7-3 Aft Doors

2-7-4 Forward Cargo Compartment Door

2-7-5 Aft Cargo Compartment Door

2-7-6 Bulk Cargo Compartment Door

2-7-7 Nose Landing Gear Doors

2-7-8 Main Landing Gear Doors

2-8-0 Escape Slides

2-9-0 Landing Gear

2-10-0 Exterior Lighting

2-11-0 Antennas and Probes Location

2-12-0 Engine and Nacelle

2-12-1 APU

2-13-0 Levelling, Symmetry and Alignement

2-14-1 Jacking for Maintenance

2-14-2 Jacking for wheel change

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

Jun 01/13



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 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 Potable Water System

5-4-8 Oil System

5-4-9 Vacuum Toilet System

5-6-0 Ground Pneumatic Power Requirements

5-7-0 Preconditioned Airflow Requirements

5-8-0 Towing Requirements

5-9-0 De-icing and External cleaning

6 OPERATING CONDITIONS

6-4-0 APU Exhaust Velocities and Temperatures

7 PAVEMENT DATA

7-1-0 General Information

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 S-77-1

T.O.C.Page 2

Jun 01/13


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

7-8-1 Radius of Relative Stiffness (L)

7-8-2 Radius of Relative Stiffness (Other values of E and µ)

7-9-0 Aircraft Classification Number - Flexible Pavement

7-9-1 Aircraft Classification Number - Rigid Pavement

8 SCALED DRAWINGS

8-0-0 Scaled Drawings

10 AIRCRAFT RESCUE AND FIRE FIGHTING

10-0-0 Aircraft Rescue and Fire Fighting

T.O.C.Page 3

Jun 01/13


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

Jun 01/13


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

Jun 01/13


PCA Portland Cement AssociationPCN Pavement Classification NumberPRM Passenger with Reduced Mobility

RH Right Hand

ULD Unit Load DeviceUS United StatesVFG Variable Frequency Generator

WV Weight Variant

Y/C Economic Class

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

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

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

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

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

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

Water Volume:Maximum volume of cargo compartment.

Usable Fuel:Fuel available for aircraft propulsion.

1-2-0Page 2

Jun 01/13


AIRCRAFT DESCRIPTION

2-1-0 General Aircraft Characteristics

**ON A/C A350-900

General Aircraft Characteristics

1. The following table provides characteristics of the A350--900.

Aircraft CharacteristicsBasic Weights

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

268900 kg(592824.0 lb)

Maximum Take Off Weight (MTOW) 268000 kg(590839.0 lb)

Maximum Landing Weight (MLW) 205000 kg(451948.0 lb)

Maximum Zero Fuel Weight (MZFW) 192000 kg(423288.0 lb)

Aircraft CharacteristicsStandard 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 Volume 971 m3(34291.0 ft.3)

Cockpit Volume 8.23 m3(291.0 ft.3)

Passenger Compartment Volume 473.7 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)

Usable Volume, Bulk CC 9.12 m3(322.07 ft.3)

Water Volume, FWD CC 113.4 m3(4004.7 ft.3)

2-1-0Page 1

Jun 01/13


Aircraft CharacteristicsWater Volume, AFT CC 95.8 m3

(3383.16 ft.3)

Water Volume, Bulk CC 11.4 m3(402.59 ft.3)

2-1-0Page 2

Jun 01/13


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

Jun 01/13


**ON A/C A350-900

66.61 m(218.54 ft)

3.04 m(9.97 ft)

65.26 m(214.11 ft)

4.63 m(15.19 ft)

9.42 m(30.90 ft)

18.79 m(61.65 ft)

1.74 m(5.71 ft)

12.87 m(42.22 ft)

10.60 m(34.77 ft)

0.75 m(2.46 ft)

64.75 m(212.43 ft)

28.66 m(94.03 ft)

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

6.09 m(19.98 ft)

P_AC_020200_1_0010001_01_01

General Aircraft Dimensions(Sheet 1 of 2)

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

2-2-0Page 2

Jun 01/13


**ON A/C A350-900

10.50 m(34.45 ft)

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

21.97 m(72.08 ft)

46.68 m(153.15 ft)

66.80 m(219.16 ft)

2.46 m(8.07 ft)

9.62 m(31.56 ft)

7.86 m(25.79 ft) 12.75 m

(41.83 ft)

17.02 m(55.84 ft)

5.96 m(19.55 ft)

5.18 m(16.99 ft)

P_AC_020200_1_0010001_02_01

General Aircraft Dimensions(Sheet 2 of 2)

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

2-2-0Page 3

Jun 01/13


2-3-0 Ground Clearances

**ON A/C A350-900

Ground Clearances

1. This section gives the height of various points of the aircraft, above the ground, for different aircraftconfigurations.Dimensions in the tables are approximate and will vary with tire type, weight and balance and otherspecial conditions.The dimensions are given for:- A light weight, for an A/C in maintenance configuration with 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

Jun 01/13


**ON A/C A350-900

P_AC_020300_1_0010001_01_02

m ft m ft m ft m ft

A/C JACKEDFDL = 6.5 m

(21.33 ft)

ft21.698.01

19.1616.5716.7316.9217.13

7.91

6.55

5.90

5.18

2.45

2.46

5.105.125.15

21.498.07

19.3616.7316.8016.9017.00

8.04

6.832.56

5.935.155.225.325.41

2.51

17.13

22.418.40

16.90

17.4517.75

8.23 2.70

5.33

6.522.66

6.205.37

5.275.21

17.49

21.398.73

20.3417.62

17.2917.09

8.86

7.723.71

7.18

6.376.37

6.376.37

3.71

25.3312.17

23.5620.9020.9020.9020.90

12.17

19.46

6.33 1.93 6.33 2.07 6.79 2.08 6.82 3.16 10.37

14.8616.9625.16

2.43

56.3330.8422.90

4.525.167.600.75

17.109.376.96

14.8316.9324.932.46

56.1030.7422.84

4.685.327.880.87

17.399.577.14

15.3517.4525.852.85

57.0531.4023.43

4.645.277.560.93

17.079.447.04

15.2217.2924.803.05

56.0030.9723.10

5.746.388.77

18.2710.57

8.17

18.8320.9328.776.53

59.9434.6826.80

1.99

8.3027.8927.5912.21

2.508.548.383.71

8.2028.0227.4912.17

2.708.618.593.87

8.8628.2528.1812.70

2.588.788.453.84

8.4628.8127.7212.60

3.719.809.584.94

12.1732.1531.4316.21

CONFIGURATIONA/C

mAPBF1

CP1D1D2D3D4

F1

5.10

6.612.44

5.845.05

5.175.22

2.41

BF2 1.93

FT2FT3HTN1

VTWL1WL2

4.535.177.670.74

17.179.406.98

F2F3F4FT1

2.538.508.413.72

13.06 4.04 13.26 4.06 13.32 4.34 14.24 17.455.32RD1 3.98

10.1410.66

3.133.22

10.2710.56

3.193.43

10.4711.25

3.373.29

11.0610.79

4.394.43

14.4014.53

10.66 3.21 10.53 3.43 11.25 3.26 10.70 4.41 14.47

C1C2

3.093.25

C3 3.25

8.27 2.50 8.20 2.68 8.79 2.59 8.50 3.71 12.17BF3 2.52

23.79 7.31 23.98 7.33 24.05 7.61 24.97 8.59 28.18D5 7.25

N1

VT D4 C2 D3 RD1

FT1FT2FT3

AP

HT

D2 D1 CP1

WL1 WL2

C1F1

F3BF2 BF1BF3

D5

NOTE: PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED

MRWFWD CG (26%)

MRWAFT CG (33.1%)

(142 000 kg)FWD CG (20%)

(142 000 kg)AFT CG (40%)

F2 F4C3

FROM THE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.

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

2-3-0Page 2

Jun 01/13


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

Jun 01/13


**ON A/C A350-900

48 B

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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

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

ST

AN

DA

RD

: 20

LD3

CO

NT

AIN

ER

SS

TA

ND

AR

D: 1

6 LD

3 C

ON

TA

INE

RS

ST

AN

DA

RD

: 6 P

ALL

ET

S 8

8 in

/ 96

in X

125

inS

TA

ND

AR

D: 5

PA

LLE

TS

88

in /

96 in

X 1

25 in

P_AC_020600_1_0020001_02_00

Cargo CompartmentsLoading Combinations (Sheet 2 of 2)

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

2-6-0Page 3

Jun 01/13


2-7-0 Door Clearances and Location

**ON A/C A350-900

Door Clearances and Location

1. This section gives door clearances and location.

2-7-0Page 1

Jun 01/13


**ON A/C A350-900

PAX DOOR 1 LH PAX DOOR 2 LH PAX DOOR 3 LH PAX DOOR 4 LH

BULK CARGO DOOR

AFT CARGO DOOR FORWARD CARGO DOOR

PAX DOOR 4 RH PAX DOOR 3 RH PAX DOOR 2 RH PAX DOOR 1 RH

COCKPIT ESCAPE HATCH

P_AC_020700_1_0010001_01_01

Door Location(Sheet 1 of 2)

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

2-7-0Page 2

Jun 01/13


**ON A/C A350-900

52.55 m(172.41 ft)

6.85 m(22.47 ft)

18.85 m(61.84 ft)

37.93 m(124.44 ft)

49.99 m(164.01 ft)

11.69 m(38.35 ft)

47.30 m(155.18 ft)

4.12 m(13.52 ft)

P_AC_020700_1_0010001_02_01

Door Location(Sheet 2 of 2)

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

2-7-0Page 3

Jun 01/13


2-7-1 Forward Doors

**ON A/C A350-900

Forward Doors

1. This section gives forward door clearances.

2-7-1Page 1

Jun 01/13


**ON A/C A350-900

0.06 m(0.20 ft)

2.16 m(7.09 ft)

0.73 m(2.40 ft)

2.46 m(8.07 ft)

0.82 m(2.69 ft)

FWD

FWD

P_AC_020701_1_0010001_01_00

Forward DoorsFIGURE-2-7-1-991-001-A01

2-7-1Page 2

Jun 01/13


**ON A/C A350-900

0.06 m(0.20 ft)

FWD

FWD0.70 m(2.30 ft)

2.46 m(8.07 ft)

0.84 m(2.76 ft)

2.16 m(7.09 ft)

P_AC_020701_1_0020001_01_00

Forward DoorsFIGURE-2-7-1-991-002-A01

2-7-1Page 3

Jun 01/13


2-7-3 Aft Doors

**ON A/C A350-900

Aft Doors

1. This section gives aft door clearances.

2-7-3Page 1

Jun 01/13


**ON A/C A350-900

FWD

FWD0.70 m(2.30 ft)

2.46 m(8.07 ft)

0.06 m(0.20 ft)

2.11 m(6.92 ft)

0.84 m(2.76 ft)

P_AC_020703_1_0010002_01_00

Aft DoorsFIGURE-2-7-3-991-001-B01

2-7-3Page 2

Jun 01/13


**ON A/C A350-900

FWD

FWD

2.16 m(7.09 ft)

0.06 m(0.20 ft)

2.45 m(8.04 ft)

0.75 m(2.46 in)

0.80 m(2.62 ft)

P_AC_020703_1_0020001_01_00

Aft DoorsFIGURE-2-7-3-991-002-A01

2-7-3Page 3

Jun 01/13


2-7-4 Forward Cargo Compartment Door

**ON A/C A350-900

Forward Cargo Compartment Door

1. This section gives forward cargo compartment door clearances.

2-7-4Page 1

Jun 01/13


**ON A/C A350-900

1.90 m(6.23 ft)

2.59 m(8.50 ft)

2.51 m(8.23 ft)

0.08 m(0.26 ft)

SEE CHAPTER2−3

A A

FWD

A

A

P_AC_020704_1_0010001_01_00

Forward Cargo Compartment DoorFIGURE-2-7-4-991-001-A01

2-7-4Page 2

Jun 01/13


2-7-5 Aft Cargo Compartment Door

**ON A/C A350-900

Aft Cargo Compartment Door

1. This section gives aft cargo compartment door clearances.

2-7-5Page 1

Jun 01/13


**ON A/C A350-900

A

AFWD

2.53 m(8.30 ft)

1.91 m(6.27 ft)

2.57 m(8.43 ft)

0.10 m(0.33 ft)

SEE CHAPTER2−3

A A

P_AC_020705_1_0010001_01_00

Aft Cargo Compartment DoorFIGURE-2-7-5-991-001-A01

2-7-5Page 2

Jun 01/13


2-7-6 Bulk Cargo Compartment Door

**ON A/C A350-900

Bulk Cargo Compartment Door

1. This section gives the bulk cargo compartment door clearances.

2-7-6Page 1

Jun 01/13


**ON A/C A350-900

AA

SEE CHAPTER2−3

1.75 m(5.74 ft)

A

A

0.77 m(2.53 ft)

FWD

P_AC_020706_1_0010001_01_00

Bulk Cargo Compartment DoorFIGURE-2-7-6-991-001-A01

2-7-6Page 2

Jun 01/13


2-7-7 Nose Landing Gear Doors

**ON A/C A350-900

Nose Landing Gear Doors

1. This section gives nose landing gear (NLG) door clearances.

2-7-7Page 1

Jun 01/13


**ON A/C A350-900

A

A

1.06 m(3.48 ft)

2 m(6.56 ft)

61.8 °

R 0.78 m(2.56 ft)

2.93 m(9.61 ft)

R 1.06 m(3.48 ft)

0.77 m(2.53 ft)

P_AC_020707_1_0010001_01_00

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

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

2-7-7Page 2

Jun 01/13


**ON A/C A350-900

0.76 m(2.49 ft)

2.03 m(6.66 ft)

69.8 °

2.15 m(7.05 ft)

0.59 m(1.94 ft)

A

A

R 0.72 m(2.36 ft)

R 0.71 m(2.33 ft)

P_AC_020707_1_0010001_02_00

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

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

2-7-7Page 3

Jun 01/13


2-7-8 Main Landing Gear Doors

**ON A/C A350-900

Main Landing Gear Doors

1. This section gives main landing gear (MLG) door clearances.

2-7-8Page 1

Jun 01/13


**ON A/C A350-900

2.75 m(9.02 ft)

R 2.43 m(7.97 ft)

0.19 m(0.62 ft)

81.3 °

1.63 m(5.35 ft)

0.13 m(0.43 ft)

A

A

P_AC_020708_1_0010001_01_00

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

2-7-8Page 2

Jun 01/13


2-8-0 Escape Slides

**ON A/C A350-900

Escape Slides

1. GeneralThis section gives 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

Jun 01/13


**ON A/C A350-900

P_AC_020800_1_0010001_01_01

COCKPITESCAPE ROPE

CABIN DUAL−LANESLIDE/RAFT

CABIN SINGLE−LANESLIDE/RAFT



Escape SlidesLocation (Sheet 1 of 2)

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

2-8-0Page 2

Jun 01/13


**ON A/C A350-900

P_AC_020800_1_0010001_02_00

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

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

2-8-0Page 3

Jun 01/13


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 associated 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 landing gear inthe 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 is 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 brace.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 normal system is unavailable,- Ground door opening system, to allow on ground access to the landing gear bays for maintenance

purposes.

2-9-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_020900_1_0010001_01_00

AA

HINGE DOOR

FIXEDFAIRINGDOOR

MAIN DOOR B

C

D

A

HINGE

GUIDE

GUIDE ROLLER RAMP

B

MECHANICAL LINKAGE

C

F

LH SHOWNRH SYMMETRICAL

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

2-9-0Page 2

Jun 01/13


**ON A/C A350-900

P_AC_020900_1_0010001_02_00

RETRACTIONACTUATOR

MAIN FITTING

FORWARD LOCKSTAY ACTUATOR

FORWARDLOCK STAY

FORWARDSIDE STAY

FORWARDDOWNLOCK

SPRINGSSLIDINGPISTON

BOGIE

AFT LOCKSTAY ACTUATOR

AFTLOCK STAY

AFTSIDE STAY

AFTDOWNLOCKSPRINGS

UPPERTORQUE LINK

LOWERTORQUE LINK

BOGIE PITCHTRIMMER ACTUATOR

E

D

E

H

H

Main Landing GearOverview (Sheet 2 of 3)

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

2-9-0Page 3

Jun 01/13


**ON A/C A350-900

P_AC_020900_1_0010001_03_00

SAFETY

SAFETYPIN

F

TYPICAL INSTALLATION

SAFETYPIN

COLLAR

SAFETYPIN

ACTUATOR

LOCK STAY

HINGE

G

G

H

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

2-9-0Page 4

Jun 01/13


**ON A/C A350-900

P_AC_020900_1_0020001_01_00

A

B

C

A

B

HINGE

HINGEFREE FALL

NLG Z−STOP

DRIVEN

RAMP

LINKAGE ROD

FORWARDDOOR

AFTDOOR

RH SHOWNLH SYMMETRICAL

E

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

2-9-0Page 5

Jun 01/13


**ON A/C A350-900

P_AC_020900_1_0020001_02_00

RETRACTION ACTUATOR

LOCK STAY ACTUATOR

MAIN FITTING

UPPER DRAGBRACE

LOWER DRAGBRACE

FORWARD/ AFT LOCK STAYS

DOWNLOCKSPRINGS

STEERINGASSEMBLY

JACKINGDOME

UPPERTORQUE LINK

LOWERTORQUE LINK

SLIDINGPISTON

C

D

D

G

H

Nose Landing GearOverview (Sheet 2 of 4)

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

2-9-0Page 6

Jun 01/13


**ON A/C A350-900

P_AC_020900_1_0020001_03_00

E

SAFETY

SAFETYPIN

SAFETYPIN

SAFETYPIN

COLLAR

ACTUATOR

LOCK STAY

F

G

F

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

2-9-0Page 7

Jun 01/13


**ON A/C A350-900

P_AC_020900_1_0020001_04_00

1GN2GN

H

J

JK

K

FWD

FWD

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

2-9-0Page 8

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

15

13

6

6

16

16

13

14

P_AC_021000_1_0020001_01_00

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

2-10-0Page 3

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

99

1313

16

10

1212

P_AC_021000_1_0040001_01_00


2-10-0Page 5

Jun 01/13


**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

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


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

Jun 01/13


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

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

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

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

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

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

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

2-12-0Page 2

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


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

Jun 01/13


**ON A/C A350-900

P_AC_021300_1_0010001_01_00

FR22FR23

FR92

10

17

1RH

1LH

RIB4

RIB5

RIB5

RIB4

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

2-13-0Page 2

Jun 01/13


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 163000 kg (359354 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 tailtipping 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 DesignThe Maximum Eligible Static Load given in table FIGURE 2-14-1-991-001-A are the maximumloads applicable on jack fittings.

(1) In fully retracted position (jack stroke at minimum), the height of the jacks is such thatthey may be placed beneath the aircraft under the most adverse conditions, namely, tiresdeflated and shock absorbers depressurized and, in addition, with a sufficient clearancebetween the aircraft jacking point and the jack upper end.

(2) 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 landing gear shock absorbersremoval/installation.

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

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

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= 163 000 kg (359 353 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

NML

FUSELAGE DATUM LINE

A/C FUSELAGE PARALLEL TO THE GROUND,

P_AC_021401_1_0010001_02_00

Jacking for MaintenanceJacking Dimensions (Sheet 2 of 5)

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

2-14-1Page 3

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

A

A

1

2

3

4

A

A

A A

REAR SPAR

RIB9

Z571 (Z671)

WING JACKADAPTOR

PLATE COVERPROTECTOR

571FB (671FB)

P_AC_021401_1_0010001_04_00

Jacking for MaintenanceWing Jacking Point (Sheet 4 of 5)

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

2-14-1Page 5

Jun 01/13


**ON A/C A350-900

FR98

FR98

BEAM5

FR98

5

A

B

A

FWD

B

Z310

AFT JACKADAPTOR

P_AC_021401_1_0010001_05_00

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

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

2-14-1Page 6

Jun 01/13


2-14-2 Jacking for wheel change

**ON A/C A350-900

Jacking for wheel change

1. GeneralTo replace either the wheel or brake unit assemblies on any of the landing gears, it is necessary to liftthe landing gear with a jack.The landing gear can be lifted by a pillar jack or with a cantilever jack.

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

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

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

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

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

2-14-2Page 1

Jun 01/13


**ON A/C A350-900

FWD

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

WEIGHT (T)CG

(% MAC)DIM A DIM B

2 TYRES (NORMAL)

1 FLAT TYRE

2 FLAT TYRES & 50% RIMFLANGE DAMAGE

2 FLAT TYRES & NO RIMFLANGE DAMAGE

MRW

MRW

MLW

MLW

26.2

26.2

20

20

291

227

75

97

10.27

8.42

7.51

7.51

11.45

8.93

2.95

3.81

261

214

191

191

mm in mm in

DOME HEIGHT− A : DISTANCE BETWEEN TYRES− B :

A350−900 NLG (1 050 x 395 R16)

B

A

A

A

P_AC_021402_1_0020001_01_00

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

2-14-2Page 2

Jun 01/13


**ON A/C A350-900

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

AFTDIM A

AFTDIM B

AFTDIM C

MRW 33.2 304 381 981 1 041 194 271

MRW 33.2 285 374 974 1 033 175 264

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

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

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

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

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

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

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

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

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

TYRE 25 mmFROM GROUND

21.29 14.88 43.81 40.51 16.96 10.55

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

TYRE 25 mmFROM GROUND

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

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

FWD INNER TYREUNSERVICEABLE

FWD OUTER TYREUNSERVICEABLE

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

(ASSUME ALL OTHERTYRES ON THE A/C

CONFIGURATION

ARE INTACT)

TYRE CHANGE

WEIGHT(T)

CG(% MAC)

14.88

11.96

11.22

15.00

14.72

14.88 40.51

38.62

38.34

40.78

40.98

40.66

10.51

7.63

6.88

10.66

10.39

10.51

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

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

DIM AFWD

DIM BFWD

DIM CFWD

A350−900 MLG (1 400 x 530 R23)

A

FWD

A

A

C

B

P_AC_021402_1_0030001_01_00

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

2-14-2Page 3

Jun 01/13


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

Jun 01/13


**ON A/C A350-900

P_AC_040200_1_0010001_01_00

R5

R3

R4

R6

R2

60°65°70°

R1

NOTE:FOR TURNING RADII VALUES, REFER TO SHEET 2

Turning Radii(Sheet 1 of 2)

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

4-2-0Page 2

Jun 01/13


**ON A/C A350-900

P_AC_040200_1_0010001_02_00

19.620

TYPE OFTURN

2

EFFECTIVESTEERING ANGLE (deg)

STEERINGANGLE (deg)

76.3250

A350−900 TURNING RADII

mft

86.9285

86.0282

R4

113.6373

R5

87.1286

R6

96.0315

WING NOSE TAIL

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

R1 R2 R3RMLG LMLG NLG

24.525258.7193

69.3227

69.6228

96.2316

71.2233

79.7262

29.430246.7153

57.3188

58.9193

84.3277

60.8199

69.0226

34.235238.0125

48.6159

51.5169

75.7248

53.7176

61.5202

39.140231.1102

41.7137

45.9151

68.9226

48.5159

55.9183

43.845225.784

36.3119

41.8137

63.7209

44.7147

51.7170

48.650221.169

31.7104

38.6127

59.2194

41.8137

48.3158

53.155217.457

28.092

36.2119

55.5182

39.6130

45.7150

57.560214.146

24.781

34.3113

52.4172

38.0125

43.5143

61.565211.437

22.072

32.9108

49.8163

36.7121

41.9137

65.07029.230

19.865

31.9105

47.7156

35.9118

40.6133

49.350120.567

31.1102

38.2125

58.6192

41.4136

47.8157

54.155116.654

27.289

35.7117

54.8180

39.2129

45.1148

58.760113.343

23.978

33.8111

51.6169

37.6123

43.0141

63.265110.334

20.969

32.4106

48.7160

36.3119

41.2135

67.57017.725

18.360

31.2103

46.2152

35.3116

39.8130

mftmftmftmftmftmftmftmftmftmft

mftmftmftmftmft

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

66.172 (MAX)28.528

19.163

31.6104

47.0154

35.6117

40.2132

mft

69.272 (MAX)16.722

17.357

30.9101

45.3149

35.0115

39.2129

mft

Turning Radii(Sheet 2 of 2)

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

4-2-0Page 3

Jun 01/13


4-3-0 Minimum Turning Radii

**ON A/C A350-900

Minimum Turning Radii

1. This section gives the minimum turning radii.

4-3-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_040300_1_0010001_01_00

69.272 (MAX)

TYPE OFTURN

1

EFFECTIVESTEERING ANGLE (deg)

STEERINGANGLE (deg)

28.794

A350−900 MINIMUM TURNING RADII

mft

48.5159

30.9101

R4

45.3149

R5

35.0115

R6

39.2129

WING NOSE TAILX A

66.172 (MAX)228.794

51.1168

31.6104

47.0154

35.6117

40.2132

mft

YR3

NLG

10.936

12.742

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

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

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

TO INITIATE THE TURN ONLY

A(MINIMUM TURNING WIDTH)

X

Y

R5

R3

R6

R4

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

4-3-0Page 2

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


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

Jun 01/13



**ON A/C A350-900

90˚ Turn - Runway to Taxiway

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

4-5-1Page 1

Jun 01/13


**ON A/C A350-900

P_AC_040501_1_0010001_01_02

APPROX 13.3 m(44 ft)

FILLET R = 25.5 m(85 ft)

TURN R = 45 m(150 ft)

(75 ft)23 m


TAXIWAY

RUNWAY CENTERLINE

NLG PATH

MLG PATH

FAA LEAD−IN FILLETL=75 m (250 ft)

(150 ft)45 m

CENTERLINE

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

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

4-5-1Page 2

Jun 01/13


**ON A/C A350-900

P_AC_040501_1_0010001_02_02

APPROX 5 m(16 ft)


TURN R = 45 m(150 ft)

(75 ft)23 m

TAXIWAY CENTERLINE

RUNWAY CENTERLINE

NLG PATH

MLG PATH


(150 ft)45 m

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

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

4-5-1Page 3

Jun 01/13



**ON A/C A350-900

135˚ Turn - Runway to Taxiway

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

4-5-2Page 1

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


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

Jun 01/13


**ON A/C A350-900

P_AC_040503_1_0010001_01_01

APPROX 48.5 m(159.12 ft)

R4 = 45.3 m(149 ft)

R3 = 30.9 m(101 ft)

R5 = 35 m(115 ft)

4.5 m(15 ft)

4.5 m(15 ft)

RUNWAY CENTERLINE

MLG PATH

WING TIP PATH

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

NOSE TIP PATH

NLG PATH

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

4-5-3Page 2

Jun 01/13



**ON A/C A350-900

90˚ Turn - Taxiway to Taxiway

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

4-5-4Page 1

Jun 01/13


**ON A/C A350-900

P_AC_040504_1_0010001_01_02

TURN R = 45 m(150 ft)

TAXIWAY CENTERLINE

(75 ft)23 m

TAXIWAY





(75 ft)23 m

NLG PATH

MLG PATH

CENTERLINE

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

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

4-5-4Page 2

Jun 01/13


**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

Jun 01/13



**ON A/C A350-900

135˚ Turn - Taxiway to Taxiway

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

4-5-5Page 1

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


4-7-0 Minimum Line-Up Distance Corrections

**ON A/C A350-900

Minimum Line-Up Distance Corrections

1. The ground manoeuvres were performed using asymmetric thrust and differential only braking toinitiate the turn.TODA: Take-Off Available DistanceASDA: 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 manoeuvre consists in a 90˚ turn at minimum turn radius starting with the edge of the MLG ata distance of 4.5 m from taxiway edge, and finishing with the aircraft aligned on the centerline of therunway.During the turn, all the clearances must meet the minimum value of 4.5 m for this category ofaircraft as recommended in ICAO Annex 14.

3. 180˚ Turn on Runway Turn PadThis section gives the minimum line-up distance correction for a 180˚ turn on runway turn pad.

This manoeuvre consists in a 180˚ turn at minimum turn radius on a standard ICAO runway turnpad geometry.It starts with the edge of the MLG at 4.5 m from pavement edge, and it finishes with the aircraftaligned on the centerline of the runway.During the turn, all the clearances must meet the minimum value of 4.5 m for this category ofaircraft as recommended in ICAO Annex 14.

4. 180˚ Turn on Runway WidthThis section gives the minimum line-up distance correction for a 180˚ turn on runway width.

For this manoeuvre, the pavement width is considered to be the runway width, which is a frozenparameter (45 m and 60 m).As per the ”180˚ turn on runway” standard operating procedures described in the Flight CrewOperating Manual, the aircraft is initially angled with respect to runway centerline when starting the180˚ 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 for this category ofaircraft as recommended in ICAO Annex 14.

4-7-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_040700_1_0010001_01_00

TODA

ASDA4.5 m(15 ft)

4.5 m(15 ft)

90° TURN ON RUNWAY ENTRY

AIRCRAFTTYPE

MAXSTEERING

ANGLE

45 m WIDE RUNWAY

(STANDARD WIDTH)

60 m WIDE RUNWAY

(STANDARD WIDTH)

MINIMUM LINE−UPDISTANCE CORRECTION

ON TODA ON ASDA ON TODA ON ASDA


72°A350−900 84 ft 25.7 m 178 ft 54.3 m 72 ft 21.8 m 166 ft 50.5 m

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

TAXIWAYCENTERLINE

RUNWAYCENTERLINE

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

4-7-0Page 2

Jun 01/13


**ON A/C A350-900

P_AC_040700_1_0020001_01_00

180° TURN ON RUNWAY TURNPAD

AIRCRAFTTYPE

MAXSTEERING

ANGLE

45 m WIDE RUNWAY

(STANDARD WIDTH)

60 m WIDE RUNWAY

(STANDARD WIDTH)

MINIMUM LINE−UPDISTANCE CORRECTIONON TODA ON ASDA


72°A350−900 122 ft 37.2 m


216 ft 65.9 m 117 ft 35.7 m 211 ft 64.4 mON TODA ON ASDA

REQUIRED MINIMUMPAVEMENT WIDTH

206 ft 62.9 m

4.5 m(15 ft)

4.5 m(15 ft)

MINIMUM PAVEMENT WIDTH

TODA

ASDA

4.5 m(15 ft)

RUNWAYCENTERLINE

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

4-7-0Page 3

Jun 01/13


**ON A/C A350-900

P_AC_040700_1_0030001_01_00

180° TURN ON RUNWAY WIDTH

AIRCRAFTTYPE

MAXSTEERING

ANGLE

45 m WIDE RUNWAY

(STANDARD WIDTH)

60 m WIDE RUNWAY

(STANDARD WIDTH)


ON TODA ON ASDA ON TODA ON ASDA


72°A350−900 NOT POSSIBLE 156 ft 47.5 m 250 ft 76.2 m


RUNWAYCENTERLINE

> 4.5 m(15 ft)

4.5 m(15 ft)

4.5 m(15 ft)

TODA

ASDA

25°

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

4-7-0Page 4

Jun 01/13


4-8-0 Aircraft Mooring

**ON A/C A350-900

Aircraft Mooring

1. This section provides information on aircraft mooring.

4-8-0Page 1

Jun 01/13


**ON A/C A350-900

TOWING FITTING

A

B

B

FLAG

MOORING

A

POINT

TOWINGFITTING

SLING

HOOK

HOOK PIN

MOVABLEPIN

REMOVE BEFORE FLIGHT

P_AC_040800_1_0010001_01_00

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

4-8-0Page 2

Jun 01/13


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

Jun 01/13


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

**ON A/C A350-900

Typical Ramp Layout (Open Apron)

1. This section gives the typical ramp layout (open apron).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.50 m (24.61 ft.)from the aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-1Page 1

Jun 01/13


**ON A/C A350-900

P_AC_050101_1_0010001_01_01

ULD

TOW

GPU

LDCL

CAT

FUEL

BULK

WV

LV

ULD

CAT

CBLDCL

AC

CAT

CLEAN

AS

PS

PS

STAND SAFETY LINE

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

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

5-1-1Page 2

Jun 01/13


5-1-2 Typical Ramp Layout (Gate)

**ON A/C A350-900

Typical Ramp Layout (Gate)

1. This section gives the baseline ramp layout (gate).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.50 m (24.61 ft.)from the aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).

5-1-2Page 1

Jun 01/13


**ON A/C A350-900

P_AC_050102_1_0010001_01_01

ULD

TOW

GPU

LDCL

CAT

FUEL

BULK

WV

LV

ULD

CAT

CBLDCL

AC

CAT

CLEAN

AS

PS

PS

STAND SAFETY LINE

0 10 20 30 40 50 60FEET

0 4 8 12 16 20METERS

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

5-1-2Page 2

Jun 01/13


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 practice, 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/removal + opening/closing door = + 3 min.No Passenger with Reduced Mobility (PRM) on boardDeplaning:- 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 and 1 belt loader.Equipment positioning/removal + opening/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:- Unloading = 110 kg/min (243 lb/min),- Loading = 95 kg/min (210 lb/min).Pallet unloading/loading times:- Unloading = 2.4 min/pallet,

5-2-0Page 1

Jun 01/13


- Loading = 2.8 min/pallet.

C. REFUELLING81000 l (21398 US gal) at 50 psig (3.45 bars-rel).Dispenser positioning/removal = + 3 min.

D. CLEANINGCleaning is performed in available time.

E. CATERING3 catering trucks for servicing galleys simultaneously at doors R1, R2 and R4.Equipment positioning + door opening = + 5 min.Closing door + equipment removal = + 3 min.Full Size Trolley Equivalent (FSTE) to unload and load: 42 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 / SERVICING. GENERAL.Start 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 US gal).Toilet servicing: draining + rinsing.

5-2-0Page 2

Jun 01/13


**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

REFUELLING

POTABLE WATER SERVICING

TOILET SERVICING


CATERING AT R2

CATERING AT R4

CARGO AFT CC

TRT : 61 min

POSITIONING/REMOVAL

ACTIVITY

AVAILABLE TIME

CRITICAL PATH

P_AC_050200_1_0010001_01_01

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

5-2-0Page 3

Jun 01/13


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 practice, 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 L2.Equipment positioning/removal + opening/closing door = + 3 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 158 pax at door L2,- Deplaning rate = 25 pax/min per door.Boarding:- 158 pax at door L2,- Boarding rate = 15 pax/min per door,- Last Pax Seated Allowance (LPS) + headcounting = + 4 min.

B. CARGO1 cargo loader + 1 belt loader.Equipment positioning/removal + opening/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 (210 lb/min).Pallet unloading/loading times:- Unloading = 2.4 min/pallet,- Loading = 2.6 min/pallet.

C. REFUELLINGNo refuelling.

5-3-0Page 1

Jun 01/13


D. CLEANINGCleaning is performed in available time.

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

F. GROUND HANDLING / SERVICING. GENERALStart 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 toilet servicing.

5-3-0Page 2

Jun 01/13


**ON A/C A350-900

0 5 15 20 25 30 35


TRT : 30 min

POSITIONING/REMOVAL

ACTIVITY

10

P_AC_050300_1_0010002_01_01

HEADCOUNTING

CATERING

CLEANING

CARGO AFT CC

BULK

AVAILABLE TIME

AVAILABLE TIME

Transit Turn Round TimeFIGURE-5-3-0-991-001-B01

5-3-0Page 3

Jun 01/13


5-4-0 Ground Service Connections layout

**ON A/C A350-900

Ground Service Connections layout

1. This section gives the ground service connections layout.

5-4-0Page 1

Jun 01/13


**ON A/C A350-900

1 − GROUNDING POINT NLG2 − GROUND ELECTRICAL POWER CONNECTORS

4 − VFG OIL SERVICING5 − STARTER OIL SERVICING6 − ENGINE OIL SERVICING7 − AIR START UNIT CONNECTORS

10 − PRESSURE REFUEL CONNECTORS (LH WING) − OPTION11 − GROUNDING POINT MLG12 − REFUEL/DEFUEL CONTROL PANEL13 − HYDRAULIC SERVICING PANEL14 − GREEN HYDRAULIC GROUND CONNECTOR

3 − PRE CONDITIONNED AIR CONNECTORS

15 − NACA AND OVERPRESSURE PANEL

13

127

6

15

1714

82

10

1

5

4

3

11

9

6

15

11

1816

8 − YELLOW HYDRAULIC GROUND CONNECTOR9 − PRESSURE REFUEL CONNECTORS (RH WING)

16 − POTABLE WATER SERVICING PANEL17 − WASTE WATER SERVICING PANEL18 − APU OIL SERVICING

1 2 4−5 8 11 12−14 16 17 18

1510

P_AC_050400_1_0010001_01_01

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

5-4-0Page 2

Jun 01/13


5-4-1 Grounding Points

**ON A/C A350-900

Grounding Points

1. Grounding (Earthing) Point Locations

DISTANCEFROM AIRCRAFT CENTERLINE

AFT OF NOSER SIDE L SIDE

MEAN HEIGHTFROM GROUND

On Nose LandingGear

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 is designed for use with a clip-on connector,such as an Appleton TGR.

B. The grounding studs are used to connect the aircraft to approved ground connection on theramp or in the hangar for:

(1) Refuel/defuel operations

(2) Maintenance operations

(3) Bad weather conditions.

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

5-4-1Page 1

Jun 01/13


**ON A/C A350-900

A

A

B

C

B

GROUNDING (EARTHING) POINT

C

P_AC_050401_1_0010001_01_00

Ground Point NLGFIGURE-5-4-1-991-001-A01

5-4-1Page 2

Jun 01/13


**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

Ground Point MLGFIGURE-5-4-1-991-002-A01

5-4-1Page 3

Jun 01/13


5-4-2 Hydraulic System

**ON A/C A350-900

Hydraulic System

1. Ground Service Panel




Green HydraulicGroundAccess Door:197 LB

36.37 m(119.32 ft.)

0.61 m(2.0 ft.)

2.39 m(7.84 ft.)

Yellow HydraulicGroundAccess Door:194 KB

30.35 m(99.57 ft.)

1.51 m(4.95 ft.)

2.24 m(7.35 ft.)

Hydraulic ReservoirServicingAccess Door:197 LB

36.42 m(119.49 ft.)

0.87 m(2.85 ft.)

2.51 m(8.23 ft.)

A. Reservoir pressurization

(1) One connector ISO 4570, 1/4 in.

B. Reservoir filling

(1) One connector AE96993E, 1/4 in.

5-4-2Page 1

Jun 01/13


**ON A/C A350-900

RESERVOIR FILLINGCONNECTOR

LOW PRESSURE CONNECTOR

HIGH PRESSURE CONNECTOR

P_AC_050402_1_0010001_01_00

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

5-4-2Page 2

Jun 01/13


**ON A/C A350-900

HIGH PRESSURE CONNECTORLOW PRESSURE CONNECTOR

P_AC_050402_1_0020001_01_00

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

5-4-2Page 3

Jun 01/13


5-4-3 Electrical System

**ON A/C A350-900

Electrical System

1. Electrical System




A/C ExternalPowerAccess Door:122 AR

6.63 m(21.75 ft.)

0.91 m(2.99 ft.)

2.58 m(8.46 ft.)

A. External power receptacle :

(1) Two standard ISO 461 Style3 --- 90 kVA each.

B. Power supply :

(1) Three-phase, 115 V, 400 Hz.

C. Electrical connectors for servicing :

(1) AC outlets : HUBBELL 5258

(2) DC outlets : HUBBELL 7472

5-4-3Page 1

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

A

B

C

Z190

B

C

A 198QR

198PR

198VR

SAFETY PIN

P_AC_050403_1_0030001_01_00

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

5-4-3Page 3

Jun 01/13


5-4-4 Oxygen System

**ON A/C A350-900

Oxygen System

1. Oxygen systemGet 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.

5-4-4Page 1

Jun 01/13


**ON A/C A350-900

Z130

FR20

FR30

B

A

A

B

CREW OXYGEN

CREW OXYGENFILLING PORT

FILLING GAGE

FR28

FR29

P_AC_050404_1_0010001_01_00

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

5-4-4Page 2

Jun 01/13


5-4-5 Fuel System

**ON A/C A350-900

Fuel System

1. Refuel/Defuel Control Panel and Connectors




Refuel/DefuelControl PanelAccess Door:197 KB

36.30 m(119.09 ft.) on centerline

2.18 m(7.15 ft.)

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

32.57 m(106.86 ft.)

15.83 m(51.94 ft.)

5.50 m(18.04 ft.)

Refuel/DefuelConnectors, RightAccess Door:623 EB

32.57 m(106.86 ft.)

15.83 m(51.94 ft.)

5.50 m(18.04 ft.)

A. Refuel/defuel connectors:

(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).

2. Overpressure Protector and NACA Intake for Vent Tank

POSITION FROM AIRCRAFTCENTERLINEACCESS AFT OF NOSE

RH SIDE LH SIDE


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

Jun 01/13


**ON A/C A350-900

P_AC_050405_1_0010001_01_00

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

5-4-5Page 2

Jun 01/13


**ON A/C A350-900

P_AC_050405_1_0020002_01_00

LH SIDE SHOWNRH SIDE SYMMETRICAL

REFUEL/DEFUEL COUPLINGS

Ground Service ConnectionsFIGURE-5-4-5-991-002-B01

5-4-5Page 3

Jun 01/13


**ON A/C A350-900

P_AC_050405_1_0030001_01_00

LH SIDE SHOWNRH SIDE SYMMETRICAL

TANK OVER PRESSURE DISC

NACA INTAKE

NACA DUCT PANEL

OVER PRESSURE PANEL

NACA and Overpressure LocationsFIGURE-5-4-5-991-003-A01

5-4-5Page 4

Jun 01/13


5-4-6 Pneumatic System

**ON A/C A350-900

Pneumatic System

1. Low Pressure Connectors




Low PressureConnectorAccess Door:193 CB

23.58 m(77.36 ft.)

1.05 m(3.44 ft.)

2.59 m(8.5 ft.)

Low PressureConnectorAccess Door:194 CR

23.58 m(77.36 ft.)

1.87 m(6.14 ft.)

2.87 m(9.42 ft.)

A. Connectors : Two standard ISO 1034, 8 in.

2. High Pressure Connectors




High PressureConnectorsAccess door:193 KB


2.06 m(6.76 ft.)

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

5-4-6Page 1

Jun 01/13


**ON A/C A350-900

P_AC_050406_1_0010001_01_00

LOW PRESSURE AIR CONNECTORS

Low Pressure Preconditioned AirFIGURE-5-4-6-991-001-A01

5-4-6Page 2

Jun 01/13


**ON A/C A350-900

P_AC_050406_1_0020001_01_00

HIGH PRESSURE AIR CONNECTORS

High Pressure Preconditioned AirFIGURE-5-4-6-991-002-A01

5-4-6Page 3

Jun 01/13


5-4-7 Potable Water System

**ON A/C A350-900

Potable Water System

1. Potable Water System




Potable WaterGround ServiceAccess Door:164 AR

50.2 m(164.7 ft.)

1.6 m(5.25 ft.)

3.3 m(10.83 ft.)

A. Technical SpecificationsConnectors :

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

(2) Overflow, SAE AS5132-16

B. Capacity :

(1) Standard configuration --- 2 tanks: 1060 l (280 USgal)

(2) Optional --- 2 tanks: 1500 l (396 USgal)

C. Filling pressure :

(1) Max filling pressure: 8.60 bar (125 psi)

5-4-7Page 1

Jun 01/13


**ON A/C A350-900

FR86FR85

FR84

FR71

164AR

A

Z160

A

FWD

FILL/DRAIN PORT

PANELINDICATION

WATERPOTABLE

NIPPLEOVERFLOW

FILL STOP DRAIN

P_AC_050407_1_0010001_01_00

Potable Water Ground Service PanelFIGURE-5-4-7-991-001-A01

5-4-7Page 2

Jun 01/13


**ON A/C A350-900

FR12FR13

Z120

DRAIN PORT

A

A

P_AC_050407_1_0020001_01_00

Forward Drain panelFIGURE-5-4-7-991-002-A01

5-4-7Page 3

Jun 01/13


**ON A/C A350-900

Z170

A

A

POTABLEWATER TANK

FR86

FR89

FR93

P_AC_050407_1_0030001_01_00

Potable Water Tanks LocationFIGURE-5-4-7-991-003-A01

5-4-7Page 4

Jun 01/13


5-4-8 Oil System

**ON A/C A350-900

Oil System

1. Engine Oil Servicing




Oil Engine 1Access Door:415 BR

24.75 m(81.2 ft.)

8.6 m(28.22 ft.)

3.23 m(10.6 ft.)

Oil Engine 2Access Door:425 BR

24.68 m(80.97 ft.)

12.29 m(40.32 ft.)

3.23 m(10.6 ft.)

2. VFG Oil Servicing




2 VFG on Engine 1Fan Cowl:415 AL

24.32 m(79.79 ft.)

11.02 m(36.15 ft.)

1.22 m(4.0 ft.)

2 VFG on Engine 2Fan Cowl:425 AL

24.34 m(79.86 ft.)

9.86 m(32.35 ft.)

1.22 m(4.0 ft.)

3. Starter Oil Servicing




Starter Engine 1Fan Cowl:415 AL

24.6 m(80.71 ft.)

10.57 m(34.68 ft.)

1.08 m(3.54 ft.)

Starter Engine 2Fan Cowl:425 AL

24.6 m(80.71 ft.)

10.31 m(33.83 ft.)

1.08 m(3.54 ft.)

5-4-8Page 1

Jun 01/13


4. APU Oil Servicing




APUAccess Door316 BR

62.52 m(205.12 ft.)

0.48 m(1.57 ft.)

6.45 m(21.16 ft.)

5-4-8Page 2

Jun 01/13


**ON A/C A350-900

P_AC_050408_1_0010001_01_00

OIL FILLER CAP

OIL LEVELSIGHT GLASS

OIL TANK

Engine Oil ServicingFIGURE-5-4-8-991-001-A01

5-4-8Page 3

Jun 01/13


**ON A/C A350-900

P_AC_050408_1_0020001_01_00

PRESSURE FILL

FILTER BOWL

OVERFLOW/STANDPIPE

DISCONNECT RESET HANDLE

SIGHT GLASS

DRAIN

TYPICAL

VFG Oil ServicingFIGURE-5-4-8-991-002-A01

5-4-8Page 4

Jun 01/13


**ON A/C A350-900

OIL DRAIN PLUG

MAGNETIC CHIP DETECTOR

PRESSURE FILL PORT

PRESSURE SPILL PORT

A

A

P_AC_050408_1_0030001_01_01

Starter Oil ServicingFIGURE-5-4-8-991-003-A01

5-4-8Page 5

Jun 01/13


**ON A/C A350-900

P_AC_050408_1_0040001_01_00

FILL CAP

SIGHT GLASS

APU Oil ServicingFIGURE-5-4-8-991-004-A01

5-4-8Page 6

Jun 01/13


5-4-9 Vacuum Toilet System

**ON A/C A350-900

Vacuum Toilet System

1. Waste Water System




Waste WaterGround ServiceAccess Door:171 AL


3.69 m(12.11 ft.)

A. Connectors :

(1) Draining, ISO 17775, 4 in

(2) Flushing and Filling, ISO 17775, 1 in

B. Capacity per tank (two tanks), 595 l (157.19 USgal)

C. Waste tank --- rinsing :

(1) Operating pressure, 3.45 bar (50.04 psi)

D. Waste precharge per tank (two tanks), 23 l (6.08 USgal)

5-4-9Page 1

Jun 01/13


**ON A/C A350-900

P_AC_050409_1_0010001_01_00

WASTE DRAINCONNECTION

FILL AND RINSECONNECTION

CONTROLLEVER

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

5-4-9Page 2

Jun 01/13


**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

Jun 01/13


5-6-0 Ground Pneumatic Power Requirements

**ON A/C A350-900

Ground Pneumatic Power Requirements

1. This document describes the required performance for the ground equipment to maintain the cabintemperature at 27 deg.C (80.6 deg.F) after boarding (Section 5.7 - steady state), and provides thetime needed to cool down or heat up the aircraft 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 Preconditioned 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 the limitation on pressure at ground connection.

C. For temperature below 2 deg.C (35.6 deg.F), the ground equipment shall be compliant with theAirbus document ”Subfreezing PCA Carts -- Compliance Document for Suppliers” (contactAirbus to obtain this document) defining all the requirements to which Subfreezing Pre-Conditioning Air equipment needs to comply to allow its use on Airbus aircraft.These requirements come in addition to the functional specifications included in the IATAAHM997.

2. Ground Pneumatic Power Requirements - HeatingThis section provides the ground pneumatic power requirements for heating (pull up) the cabin,initially at OAT, up to 21 deg.C (69.8 deg.F) FIGURE 5-6-0-991-001-A Sheet 1.

3. Ground Pneumatic Power Requirements - CoolingThis section provides the ground pneumatic power requirements for cooling (pull down) the cabin,initially at OAT, down to 27 deg.C (80.6 deg.F) FIGURE 5-6-0-991-001-A Sheet 2.

5-6-0Page 1

Jun 01/13


**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 2

Jun 01/13


**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

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

N

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 3

Jun 01/13


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

Jun 01/13


**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)

= 1

06 k

W IS

NE

ED

ED

TO

MA

INT

AIN

TH

E C

AB

IN T

EM

PE

RA

TU

RE

BE

LOW

27°

C (

86°

F)

(4.2

5 kg

/s A

T G

C O

UT

LET

OF

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

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

OA

T IS

A−

45°

C (

−49

°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

N

OA

T IS

A−

55°

C (

−67

°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

N

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

Jun 01/13


5-8-0 Towing Requirements

**ON A/C A350-900

Towing Requirements

1. This section provides information on aircraft towing.

The A350 is designed with means for conventional or towbarless towing.

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 first part of this section shows the chart to determine the draw bar pull and tow tractor massrequirements as function of the following physical characteristics:- Aircraft weight,- Slope,- Number of engines at idle.

2. Towbar design guidelines

The A350 towbar requirements are identical to the towbar requirements for 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 (Aircraft Weight Category III)..

5-8-0Page 1

Jun 01/13


**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

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

5-8-0Page 2

Jun 01/13


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

Jun 01/13


OPERATING CONDITIONS

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

Jun 01/13


**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

Jun 01/13


PAVEMENT DATA

7-1-0 General Information

**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,- 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, maximum rampweights and tire sizes and pressures.

Maximum Pavement Loads.Section 7-3-0, shows maximum vertical and horizontal pavement loads for certain critical conditionsat the 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 procedures in Instruction Report No S-77-1 ”Procedures for Development of CBRDesign Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3.Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007. The report wasprepared by the U.S. Army Corps Engineers Waterways Experiment Station, Soils and PavementLaboratory, Vicksburg, Mississippi”.The line showing 10 000 coverages is used to calculate Aircraft Classification Number (ACN).

Flexible Pavement Requirements - LCN Conversion Method.

7-1-0Page 1

Jun 01/13


The flexible pavement charts in Section 7-6-0 show LCN against Equivalent Single Wheel Load(ESWL), and ESWL against pavement thickness.All LCN curves shown in ’Flexible Pavement Requirements’ were developed from a computer programbased on data in International Civil Aviation Organisation (ICAO) document 7920-AN/865/2,Aerodrome manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.

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.Section 7-8-0 gives the rigid pavement requirements.All LCN curves shown in ’Rigid Pavement Requirements - Radius of Relative Stiffness (other valuesof E and µ) - were developed from a computer program based on data in International Civil AviationOrganisation (ICAO) document 7920-AN/865/2, Aerodrome manual, Part 2, ”Aerodrome PhysicalCharacteristics”, Second Edition, 1965.The rigid pavement charts in Section 7-8-0 show LCN against ESWL, and ESWL against radius ofrelative stiffness.

Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness.Section 7-8-1 allow to find the radius of relative stiffness based on other values of E and µ.

Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness (other values of E andµ).The rigid pavement charts show LCN in Section 7-8-2 against ESWL and ESWL against radius ofrelative stiffness affected by the other values of E and µ.

ACN/PCN Reporting System.Section 7-9 provides ACN data prepared according to the ACN/PCN system as referenced in ICAOAnnex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations.” Fourth Edition July 2004,incorporating Amendments 1 to 6.Fourth Edition July 2004, incorporating Amendments 1 to 6. The ACN/PCN system provides astandardized international aircraft / pavement rating system replacing the various S, T, TT, LCN,AUW, ISWL, etc., rating systems used throughout the world.ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.An aircraft having an ACN equal to or less than the PCN can operate without restriction on thepavement.Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.

7-1-0Page 2

Jun 01/13


The derived single wheel load is defined as the load on a single tire inflated to 1.25 Mpa (181 psi)that would have the same pavement requirements as the aircraft.Computationally the ACN/PCN system uses PCA program PDILB for rigid pavements and S-77-1 forflexible pavements to calculate ACN values.The Airport Authority must decide on the method of pavement analysis and the results of theirevaluation shown as follows:

PCN

PAVEMENT TYPESUBGRADECATEGORY

TIRE PRESSURECATEGORY

EVALUATIONMETHOD

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

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

U - Using Aircraft

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

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

Section 7-9-0 shows the aircraft ACN values for flexible pavements.The four subgrade categories are:- A . High Strength CBR 15- B . Medium Strength CBR 10- C . Low Strength CBR 6- D . Ultra Low Strength CBR 3

Section 7-9-1 shows the aircraft ACN values for rigid pavements.The four subgrade categories are:- A . High Strength Subgrade k = 150 MN/m3 (550 pci )- B . Medium Strength Subgrade k = 80 MN/m3 (300 pci )- C . Low Strength Subgrade k = 40 MN/m3 (150 pci )- D . Ultra Low Strength Subgrade k = 20 MN/m3 (75 pci )

7-1-0Page 3

Jun 01/13


7-2-0 Landing Gear Footprint

**ON A/C A350-900

Landing Gear Footprint

1. This section gives data about the landing gear footprint in relation with the aircraft MRW and tiresizes and pressures.

7-2-0Page 1

Jun 01/13


**ON A/C A350-900

MAXIMUM RAMP WEIGHT

PERCENTAGE OF WEIGHTON MAIN GEAR GROUP

NOSE GEAR TIRE SIZE

NOSE GEAR TIRE PRESSURE

MAIN GEAR TIRE SIZE

MAIN GEAR TIRE PRESSURE

268 900 kg(592 825 lb)

SEE SECTION 7−4−0

1050x395R16 28PR

12.2 bar (177 psi)

1400x530R23 42PR

16.6 bar (241 psi)

10.600 m(34.777 ft)

28.665 m(94.050 ft)

1.735 m(5.692 ft) 2.040 m

(6.693 ft)

0.748 m(2.454 ft)

P_AC_070200_1_0010001_01_01

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

7-2-0Page 2

Jun 01/13


7-3-0 Maximum Pavement Loads

**ON A/C A350-900

Maximum Pavement Loads

1. This section shows maximum vertical and horizontal pavement loads for some critical conditions atthe tire-ground interfaces.

7-3-0Page 1

Jun 01/13


**ON A/C A350-900

H

V(M

G)

(1)

(2)

NO

TE

:

MR

W =

2

68 9

00 k

g

F

WD

CG

= 2

5.5

% M

AC

AT

A/C

WE

IGH

T=

268

900

kg

ALL

LO

AD

S C

ALC

ULA

TE

D U

SIN

G A

IRC

RA

FT

MA

XIM

UM

RA

MP

WE

IGH

T

V(N

G)

V(M

G)

H

MA

XIM

UM

VE

RT

ICA

L M

AIN

GE

AR

GR

OU

ND

LO

AD

AT

MO

ST

AF

T C

G

MA

XIM

UM

HO

RIZ

ON

TA

L G

RO

UN

D L

OA

D F

RO

M B

RA

KIN

G

12

34

56

MO

DE

L

lbkg

lbkg

VN

G

kglb

lbkg

lbkg

lbkg

AT

INS

TA

NT

AN

EO

US

BR

AK

ING

CO

EF

FIC

IEN

T =

0.8

VM

G (

PE

R S

TR

UT

)H

(P

ER

ST

RU

T)

ST

AT

IC L

OA

DA

T M

AX

AF

TC

.G. (

2)

MA

XIM

UM

RA

MP

WE

IGH

T

ST

AT

IC L

OA

DA

T M

OS

T F

WD

C.G

. (1)

MA

XIM

UM

VE

RT

ICA

L N

OS

E G

EA

R G

RO

UN

D L

OA

D A

T M

OS

T F

OR

WA

RD

CG

592

825

268

900

51 5

7523

400

85 5

0038

780

277

700

125

960

ST

AT

IC B

RA

KIN

G

DE

CE

LER

AT

ION

ST

EA

DY

BR

AK

ING

@ 1

0 ft/

DE

CE

LER

AT

ION

s²@

10

ft/s²

V(N

G)

92 1

2541

790

222

150

100

770

MR

W =

2

68 9

00 k

g

A

FT

CG

= 3

3 %

MA

C A

T A

/C W

EIG

HT

=26

8 90

0 kg

−90

0

P_AC_070300_1_0010001_01_01

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

7-3-0Page 2

Jun 01/13


7-4-0 Landing Gear Loading on Pavement

**ON A/C A350-900

Landing Gear Loading on Pavement

1. This section gives data about the landing gear loading on pavement.

Example, see FIGURE 7-4-0-991-001-A, calculation of the total weight on the MLG for:- An aircraft with a MTOW of 268000 kg (590839 lb)- The aircraft gross weight is 190000 kg (418879 lb)- A percentage of weight on the MLG of 93.68 %.The total weight on the MLG group is 178000 kg (392423 lb).

7-4-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070400_1_0010001_01_00

5 10 15 20 25 30 35 40 45 50

120 120

125

130

135

140

145

150

155

160

165

170

175

180

185

190

195

200

205

210

215

220

225

230

235

240

245

250

255

260

265

270

84

125

130

135

140

145

150

155

160

165

170

175

180

185

190

195

200

205

210

215

220

225

230

235

240

245

250

255

260

265

270

86 88 90 92 94 96 98 100

AIR

CR

AF

T G

RO

SS

WE

IGH

T (

x 10

00 k

g)

PERCENTAGE OF WEIGHT ON MAIN GEAR

PERCENTAGE MAC

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(x

1000

kg)

MTOW − 268 000 kg CG FOR ACNCALCULATION

MLW − 205 000 kg

MZFW − 192 000 kg

LANDING

TAKE OFF

Landing Gear Loading on PavementMTOW 268 000 kg

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

7-4-0Page 2

Jun 01/13


7-5-0 Flexible Pavement Requirements - US Army Corps of Engineers Design Method S-77-1

**ON A/C A350-900

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

1. This section gives data about the flexible pavement requirements.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 MTOW of 268000 kg (590839 lb),- A CBR value of 10,- An annual departure level of 3 000,- The load on one MLG of 110000 kg (242509 lb).The required flexible pavement thickness is 593 mm (23 in.).

7-5-0Page 1

Jun 01/13


**ON A/C A350-900

SUBGRADE STRENGTH − CBR

3 6 10 15 20 30 40 60 80

[in]

[cm]

FLEXIBLE PAVEMENT THICKNESS

1400x530R23 42PR TIRESTIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)

10 15 20 30 40 60 80 100 120 150 180

3 6 10 15 20 30 40 60 80

WEIGHT ON ONE MAIN LANDING GEAR 125 960 kg (277 700 lb) 110 000 kg (242 500 lb)

90 000 kg (198 425 lb) 80 000 kg (176 375 lb)

10 000 COVERAGESUSED FOR ACNCALCULATIONS

ANNUALDEPARTURES*1 2003 0006 00015 00025 000*20 YEARPAVEMENT LIFE

ALPHA FACTOR = 0.8

P_AC_070500_1_0010001_01_01

100 000 kg (220 450 lb)

MAXIMUM POSSIBLE MAIN GEAR LOAD AT

MAXIMUM RAMPWEIGHT AND AFT CG

Flexible Pavement RequirementsMTOW 268 000 kg

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

7-5-0Page 2

Jun 01/13


7-6-0 Flexible Pavement Requirements - LCN Conversion

**ON A/C A350-900

Flexible Pavement Requirements - LCN Conversion

1. This section gives data about the flexible pavement requirements for Load Classification Number(LCN) conversion.They are calculated with the LCN conversion method.To find the aircraft weight that a flexible pavement can support, you must know the LCN of thepavement and the thickness.Example, see FIGURE 7-6-0-991-001-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb)- The flexible pavement thickness is 1397 mm (55 in.) with a related LCN of 154.The weight on one MLG is 110000 kg (242509 lb).

The following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”.In order to use the system accurately you should know the total pavement thickness for flexiblepavement.However, the pavement thickness for a particular runway are not frequently published in the standardairport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard thickness (20 inches) when determining the LCNand the ESWL of the aircraft.

If the LCN for an intermediate weight between MRW and the empty weight of the aircraft is requiredor if the real thickness is known, refer to charts in FIGURE 7-6-0-991-001-A.

FLEXIBLE PAVEMENTESWLAIRCRAFT

TYPEWEIGHT

LOAD ONONE MLGLEG (%)

TIREPRESSURE

(Mpa) x 1000 kg x 1000 lbLCN

h =510 mm(20 in.)

A350--900268900 kg(592824 lb) 46.8 31 69.4 116

A350--900142000 kg(313057 lb) 46.8

1.66

17 36.7 68

7-6-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070600_1_0010001_01_00

40708090100

110

120

130

EQUIVALENT SINGLE WHEEL LOAD (1000 lb)

230

70

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQUIVALENT SINGLE WHEEL LOAD (1000 kg)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

EC

ON

D E

DIT

ION

196

5

1400

x 5

30R

23 4

2PR

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.6

bar

(241

psi

)F

LEX

IBLE

PA

VE

ME

NT

TH

ICK

NE

SS

(m

m)

500

750

1000

1500

2500

70

1020

3040

100

8060

50

FLE

XIB

LE P

AV

EM

EN

T T

HIC

KN

ES

S (

in)

60 50150

140

160

2000

200

150

120

100

80

60 50 40 30 20

L

AN

DIN

G G

EA

R 1

25 9

60 k

g (2

77 7

00 lb

) 1

10

00

0 k

g

(2

42

50

0 lb

) 100 0

00 k

g (2

20 4

50 lb

)

90

00

0 k

g

(1

98

42

5 lb

)

80

00

0 k

g

(1

76

37

5 lb

)

WE

IGH

T O

N O

NE

MA

IN

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

RLO

AD

AT

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

NO

TE

:

Flexible Pavement Requirements - LCNMTOW 268 000 kg

FIGURE-7-6-0-991-001-A01

7-6-0Page 2

Jun 01/13


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 gives data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.They are calculated with the PCA design method.To find a rigid pavement thickness, you must know the Subgrade Modulus (K), the permittedworking stress and the weight on MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on

the right, a random load line is made. This represents the MLG maximum weight to be shown,- A plot is then made of all values of the subgrade modulus (k values),- More load lines for the incremental values of weight on the MLG are made based on the curve for

k= 80MN/m3 already shown on the graph.Example, see FIGURE 7-7-0-991-001-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MTOW of 268000 kg (590839 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 110000 kg (242509 lb).The required rigid pavement thickness is 290 mm (11 in.).

7-7-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070700_1_0010001_01_00

THE VALUES OBTAINED BY USING

FOR LOADS LESS THAN MAXIMUM,

15

14

13

12

11

10

9

8

7

1000

900

800

700

600

500

400

300

200

38

36

34

32

30

28

26

24

22

20

70

65

60

55

50

45

40

35

30

25

20

1518

LANDING GEAR 125 960 kg (277 700 lb) 110 000 kg (242 500 lb)

100 000 kg (220 450 lb) 90 000 kg (198 425 lb) 80 000 kg (176 375 lb)

WEIGHT ON ONE MAIN

NOTES:

THE MAXIMUM LOAD REFERENCELINE AND ANY VALUES FOR K ARE EXACT.

THE CURVES ARE EXACT FOR K = 80 MN/m³BUT DEVIATE SLIGHTLY FOR ANY OTHER VALUES OF K

"DESIGN OF CONCRETE AIRPORT

PAVEMENT DESIGN − PROGRAM

REFERENCE:

PAVEMENTS" AND "COMPUTERPROGRAM FOR AIRPORT

PDILB" PORTLAND CEMENTASSOCIATION

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)

MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT AND AFT CG

K = 20 MN/m³

K = 40 MN/m³

K = 80 MN/m³

K = 150 MN/m³

Rigid Pavement RequirementsMTOW 268 000 kg

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

7-7-0Page 2

Jun 01/13


7-8-0 Rigid Pavement Requirements - LCN Conversion

**ON A/C A350-900

Rigid Pavement Requirements - LCN Conversion

1. This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness).- For the radius of relative stiffness, see Section 7--8--1,- For the radius of relative stiffness (other values of E and µ), see Section 7--8--2.Example, see FIGURE 7-8-0-991-001-A, calculation of the aircraft weight with the thickness of therigid pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- The radius of relative stiffness is shown at1143 mm (45 in.) with a related LCN of 119.The weight on one MLG is 110000 kg (242509 lb).

The following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”.In order to use the system accurately you should know the total pavement radius of relative stiffness(L-value) for rigid pavement.However, the pavement radius of relative stiffness for a particular runway are not frequently publishedin the standard airport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard radius of relative stiffness (30 inches) whendetermining the LCN and the ESWL of the aircraft.If the LCN for an intermediate weight between maximum ramp weight and the empty weight of theaircraft is required or if the real thickness is known, refer to charts FIGURE 7-8-0-991-001-A.

RIGID PAVEMENTESWL LCN

AIRCRAFTTYPE

WEIGHT


TIREPRESSURE

(Mpa) x 1000 kg x 1000 lb

L =760 mm(30 in.)

A350--900268900 kg(592824 lb) 46.8 28 62 107

A350--900142000 kg(313057 lb) 46.8

1.66

15 33 59

7-8-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070800_1_0010001_01_00

2030405060708090100

110

120

EQUIVALENT SINGLE WHEEL LOAD (1000 lb)

190

5060

7080

40

LOA

D C

LAS

SIF

ICA

TIO

N N

UM

BE

R (

LCN

)

EQUIVALENT SINGLE WHEEL LOAD (1000 kg)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

S A

RE

DE

RIV

ED

BY

ME

TH

OD

S S

HO

WN

INIC

AO

AE

RO

DR

OM

E M

AN

UA

L P

AR

T 2

PA

R 4

.1.3

S

EC

ON

D E

DIT

ION

196

5

1400

x 5

30R

23 4

2PR

TIR

ES

TIR

E P

RE

SS

UR

E C

ON

ST

AN

T A

T 1

6.6

bar

(241

psi

)R

AD

IUS

OF

RE

LAT

IVE

ST

IFF

NE

SS

(m

m)

750

1000

1250

1500

2000

2500

150

120

100

905141924293439444954

2030

4050

100

9080

7060

RA

DIU

S O

F R

ELA

TIV

E S

TIF

FN

ES

S (

inch

es)

WE

IGH

T O

N O

NE

MA

IN L

AN

DIN

G G

EA

R 1

25 9

60 k

g (2

77 7

00 lb

) 1

10

00

0 k

g

(2

42

50

0 lb

) 100 0

00 k

g (2

20 4

50 lb

) 90 0

00 k

g (1

98 4

25 lb

)

80

00

0 k

g

(1

76

37

5 lb

)

MA

XIM

UM

PO

SS

IBLE

MA

IN G

EA

RLO

AD

AT

MA

XIM

UM

RA

MP

WE

IGH

T A

ND

AF

T C

G

NO

TE

:

Rigid Pavement Requirements - LCNMTOW 268 000 kg

FIGURE-7-8-0-991-001-A01

7-8-0Page 2

Jun 01/13


7-8-1 Radius of Relative Stiffness (L)

**ON A/C A350-900

Radius of Relative Stiffness (L)

1. This section gives the radius of relative stiffness.

7-8-1Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070801_1_0010001_01_00

WHERE

=

E

k

d

Ed4

=

=

=

dk

= 24.1652 4

RIGID PAVEMENT THICKNESS, (in)

YOUNG’S MODULUS = 4 x 10 psi

RADIUS OF RELATIVE STIFFNESS VALUES IN INCHES

L

SUBGRADE MODULUS, lb/in

= POISSON’S RATIO = 0.15

6.06.57.07.5

31.4833.4335.3437.22

29.3031.1132.8934.63

26.4728.1129.7231.29

24.6326.1627.6529.12

23.3024.7426.1527.54

22.2623.6424.9926.32

21.4222.7424.0425.32

20.7222.0023.2524.49

19.1320.3121.4722.61

8.08.59.09.5

39.0640.8842.6744.43

36.3538.0439.7141.35

32.8534.3735.8837.36

30.5731.9933.3934.77

28.9130.2531.5832.89

27.6228.9130.1731.42

26.5827.8129.0330.23

25.7026.9028.0829.24

23.7424.8425.9327.00

10.010.511.011.5

46.1847.9049.6051.28

38.8340.2841.7143.12

36.1437.4838.8140.13

34.1735.4536.7137.95

32.6533.8735.0736.26

31.4232.5933.7534.89

30.3931.5232.6433.74

28.0629.1130.1431.16

12.012.513.013.5

52.9454.5956.2257.83

49.2750.8052.3253.82

44.5245.9047.2748.63

41.4342.7243.9945.26

39.1840.4041.6142.80

37.4438.6039.7540.89

36.0237.1438.2539.35

34.8435.9236.9938.06

32.1733.1734.1635.14

14.014.515.015.5

16.016.517.017.5

55.3156.7858.2559.70

65.6967.2368.7570.26

61.1362.5663.9865.38

49.9851.3152.6353.94

46.5147.7548.9850.20

43.9845.1646.3247.47

55.2456.5357.8159.08

51.4152.6153.8054.98

48.6249.7550.8852.00

42.0243.1544.2645.36

40.4441.5142.5843.64

39.1140.1541.1942.21

36.1237.0838.0338.98

46.4547.5448.6149.68

44.7045.7446.7747.80

43.2344.2445.2446.23

39.9240.8541.7842.70

18.019.020.021.0

22.023.024.025.0

71.7674.7377.6680.55

83.4186.2489.0491.81

66.7869.5472.2774.96

77.6380.2682.8685.44

60.3462.8465.3067.74

70.1472.5274.8777.20

56.1558.4860.7763.04

65.2867.4969.6871.84

53.1155.3157.4759.62

61.7363.8365.9067.95

50.7452.8454.9156.96

58.9860.9862.9664.92

48.8250.8452.8454.81

56.7558.6860.5862.46

54.8956.7558.5960.41

47.2249.1751.1053.01

43.6145.4147.1948.95

50.6952.4154.1155.79

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

59.4361.0262.5964.15

42.9744.5746.1647.72

( )L

12 (1 − ) k

REFERENCE: PORTLAND CEMENT ASSOCIATION

Radius of Relative Stiffness (L)FIGURE-7-8-1-991-001-A01

7-8-1Page 2

Jun 01/13


7-8-2 Radius of Relative Stiffness (Other values of E and µ)

**ON A/C A350-900

Radius of Relative Stiffness (Other values of E and µ)

1. The table of Section 7--8--1 radius of relative stiffness, presents L values based on young’s modulus(E) of 4 000 000 psi and poisson’s ratio (µ) of 0.15.

To find L values based on other values of E and µ, see FIGURE 7-8-2-991-001-B.

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

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

7-8-2Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070802_1_0010002_01_00

0 1 2 3 4 50.80

0.85

0.90

0.95

1.00

1.05

1.10EFFECT OF E ON VALUESL

E F

AC

TO

R

0.00 0.05 0.10 0.15 0.20 0.250.995

1.000

1.005

1.010

1.015EFFECT OF L

FA

CT

OR

, POISSON’S RATIO

NOTE: BOTH CURVES ON THIS PAGE ARE USED TO ADJUSTTHE VALUES OF TABLE 7−8−1L

E, YOUNG’S MODULUS (10 psi)

ON VALUES

Radius of Relative Stiffness (Effect E and µ ON ”L” values)FIGURE-7-8-2-991-001-B01

7-8-2Page 2

Jun 01/13


7-9-0 Aircraft Classification Number - Flexible Pavement

**ON A/C A350-900

Aircraft Classification Number - Flexible Pavement

1. This section gives data about the Aircraft Classification Number (ACN) for flexible pavement for anaircraft gross weight in relation with a subgrade strength value.To find the ACN of an aircraft on flexible pavement, you must know the aircraft gross weight andthe 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).

Example, see FIGURE 7-9-0-991-001-A, calculation of the ACN for flexible pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- An aircraft gross weight of 210000 kg (462971 lb),- A medium subgrade strength (code B).The ACN for flexible pavement is 51.

2. Aircraft Classification Number - ACN TableThe following table provides ACN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1983”. If the ACN for an intermediateweight between maximum ramp weight and the empty weight of the aircraft is required, refer tochart FIGURE 7-9-0-991-001-A.

ACN FOR FLEXIBLE PAVEMENT SUBGRADES -CBRAIRCRAFT

TYPEWEIGHT


TIREPRESSURE

(Mpa) High15

Medium10

Low6

Ultral-low3

A350--900

268900 kg(592824

lb)46.8 66 70 80 110

A350--900

142000 kg(313057

lb)46.8

1.66

31 32 34 41

7-9-0Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070900_1_0010001_01_00

ALP

HA

FA

CT

OR

= 0

.8

SU

BG

RA

DE

ST

RE

NG

TH

B −

CB

R 1

0 (M

ED

IUM

)A

− C

BR

15

(HIG

H)

280

310

340

370

400

430

460

490

520

550

580

610

( x1

000

lb)

120

110

100 90 80 70 60 50 40 30 2012

014

016

018

020

022

024

026

028

0

AIRCRAFT CLASSIFICATION NUMBER (ACN)

( x1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

3% M

AC

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)

SE

E S

EC

TIO

N 7

−4−

0

C −

CB

R63

(LO

W)

(ULT

RA

LO

W)

D −

CB

R

Aircraft Classification Number - Flexible PavementMTOW 268 000 kg

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

7-9-0Page 2

Jun 01/13


7-9-1 Aircraft Classification Number - Rigid Pavement

**ON A/C A350-900

Aircraft Classification Number - Rigid Pavement

1. This section gives data about the Aircraft Classification Number (ACN) for rigid pavement for anaircraft gross weight in relation with a subgrade strength value.To find the ACN of an aircraft on rigid pavement, you must know the aircraft gross weight and thesubgrade 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).

Example, see FIGURE 7-9-1-991-001-A, calculation of the ACN for rigid pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- An aircraft gross weight of 210000 kg (462971 lb),- A medium subgrade strength (code B).The ACN for rigid pavement is 52.

2. Aircraft Classification Number - ACN TableThe following table provides ACN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1983”. If the ACN for an intermediateweight between maximum ramp weight and the empty weight of the aircraft is required, refer tochart FIGURE 7-9-1-991-001-A.

ACN FOR RIGID PAVEMENT SUBGRADES -MN/m3AIRCRAFT

TYPEWEIGHT


TIREPRESSURE

(Mpa) High150

Medium80

Low40

Ultral-low20

A350--900

268900 kg(592824

lb)46.8 64 71 83 96

A350--900

142000 kg(313057

lb)46.8

1.66

32 33 36 41

7-9-1Page 1

Jun 01/13


**ON A/C A350-900

P_AC_070901_1_0010001_01_00

280

310

340

370

400

430

460

490

520

550

580

610

( x1

000

lb)

120

110

100 90 80 70 60 50 40 30 2012

014

016

018

020

022

024

026

028

0

AIRCRAFT CLASSIFICATION NUMBER (ACN)

( x1

000

kg)

AIR

CR

AF

T G

RO

SS

WE

IGH

T

AC

N W

AS

DE

TE

RM

INE

D A

S R

EF

ER

EN

CE

D IN

ICA

O A

ER

OD

RO

ME

DE

SIG

N M

AN

UA

L P

AR

T 3

CH

AP

TE

R 1

. SE

CO

ND

ED

ITIO

N 1

983.

CG

US

ED

FO

R A

CN

CA

LCU

LAT

ION

S: 3

3% M

AC

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)

SE

E S

EC

TIO

N 7

−4−

0

SU

BG

RA

DE

ST

RE

NG

TH

D −

K =

20

MN

/m³(

ULT

RA

LO

W)

C −

K =

40

MN

/m³

B −

K =

80

MN

/m³

A −

K =

150

MN

/m³(L

OW

)

(ME

DIU

M)

(HIG

H)

Aircraft Classification Number - Rigid PavementMTOW 268 000 kg

FIGURE-7-9-1-991-001-A01

7-9-1Page 2

Jun 01/13


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

Jun 01/13


**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

Jun 01/13


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

10-0-0Page 1

Jun 01/13


**ON A/C A350-900

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

.

RE

FE

RE

NC

E

:

JUN

E 2

013

P_AC_100000_1_0010001_01_01

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

10-0-0Page 2

Jun 01/13


**ON A/C A350-900

P_AC_100000_1_0030001_01_01

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

10-0-0Page 3

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

P_AC_100000_1_0080001_01_01

CO

CK

PIT

ES

CA

PE

RO

PE

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)

CA

BIN

DU

AL−

LAN

ES

LID

E/R

AF

T

CA

BIN

DU

AL−

LAN

ES

LID

E/R

AF

T9.

35 m

(30

.68

ft)

9.43

m (

30.9

4 ft)

03691215

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

DIM

EN

SIO

NS

AR

E A

PP

RO

XIM

AT

EN

OT

E:

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

10-0-0Page 9

Jun 01/13


**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

−P

RE

SS

UR

EW

AR

NIN

G−

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

− P

US

H F

LAP

TO

GR

AS

P H

AN

DLE

.3

− LI

FT H

AN

DLE

FU

LLY

UP

TO

HO

RIZ

ON

TAL

PO

SIT

ION

(GR

EE

N L

INE

).4

− P

ULL

TH

E D

OO

R O

UT

AN

D M

OV

E IT

FO

RW

AR

D.

P_AC_100000_1_0090001_01_00

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

10-0-0Page 10

Jun 01/13


**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

− P

US

H O

N T

HE

HA

ND

LE. T

HE

HA

ND

LE IS

EJE

CT

ED

FR

OM

ITS

HO

US

ING

.2

− T

UR

N T

HE

HA

ND

LE C

OU

NT

ER

CLO

CK

WIS

E T

O D

ES

EN

GA

GE

TH

E L

AT

CH

ES

.3

− P

US

H O

N T

HE

ES

CA

PE

HA

TC

H. I

T O

PE

NS

INS

IDE

TH

E C

OC

KP

IT.

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

Jun 01/13


**ON A/C A350-900

FW

D A

ND

AF

T C

AR

GO

CO

MP

AR

TM

EN

T D

OO

R C

ON

TR

OL

S

EN

SU

RE

TH

AT

ALL

PE

RS

ON

NE

L A

ND

EQ

UIP

ME

NT

AR

E C

LEA

R O

F C

AR

GO

DO

OR

AR

EA

.

PR

ES

SU

RE

WA

RN

ING

−LI

GH

T D

OE

S N

OT

FLA

SH

.M

AK

E S

UR

E T

HA

T T

HE

RE

SID

UA

L

NO

RM

AL

OP

ER

AT

ION

1− P

US

H T

HE

LO

CK

ING

HA

ND

LE F

LAP

IN A

ND

PU

LL T

HE

LOC

KIN

G H

AN

DLE

TO

TH

E "

UN

LOC

KE

D"

PO

SIT

ION

(OU

TW

AR

D A

ND

UP

WA

RD

). M

AK

E S

UR

E T

HA

T Y

OU

SE

E A

LL T

HE

IND

ICA

TO

R F

LAG

S (

EIG

HT

FLA

GS

).

2 −

QU

ICK

LY A

ND

FU

LLY

PU

LL T

HE

LA

TC

HIN

G H

AN

DLE

DO

WN

WIT

H A

CO

NT

INU

OU

S M

OV

EM

EN

T

(O

UT

AN

D D

OW

N).

4 −

RE

LEA

SE

TH

E T

OG

GLE

SW

ITC

H.

PA

NE

L T

O T

HE

"O

PE

N"

PO

SIT

ION

AN

D H

OLD

IT U

NT

IL

T

HE

GR

EE

N IN

DIC

AT

OR

LIG

HT

CO

ME

S O

N

(C

AR

GO

DO

OR

FU

LLY

OP

EN

AN

D L

OC

KE

D).

3 −

PU

SH

TH

E T

OG

GLE

SW

ITC

H O

N T

HE

DO

OR

OP

ER

AT

ION

MA

NU

AL

OP

ER

AT

ION

TW

O O

PE

RA

TO

RS

AR

E R

EQ

UIR

ED

FO

R T

HIS

OP

ER

AT

ION

.

1− D

O T

HE

OP

ER

AT

ION

S 1

AN

D 2

AS

FO

R "

NO

RM

AL

O

PE

RA

TIO

N".

2 −

TU

RN

TH

E M

AN

UA

L O

PE

RA

TIN

G D

EV

ICE

CLO

CK

WIS

E

TO

TH

E "

OP

EN

" P

OS

ITIO

N A

ND

HO

LD IT

.

T

HE

HY

DR

AU

LIC

AU

XIL

IAR

Y−

PU

MP

GE

AR

BO

X IN

T

HE

PO

SIT

ION

ON

TH

E H

YD

RA

ULI

C A

UX

ILIA

RY

−P

UM

P

AN

D T

IGH

TE

N T

HE

BO

LTS

.

3 −

ON

TH

E Y

ELL

OW

GR

OU

ND

−S

ER

VIC

E P

AN

EL;

PU

T

TO

OP

ER

AT

E T

HE

HY

DR

AU

LIC

AU

XIL

IAR

Y−

PU

MP

UN

TIL

TH

E G

RE

EN

IND

ICA

TO

R L

IGH

T C

OM

ES

ON

4 −

CO

NN

EC

T A

PO

WE

R H

AN

D T

OO

L O

R T

HE

HA

ND

LE

(CA

RG

O D

OO

R F

ULL

Y O

PE

N A

ND

LO

CK

ED

).

5 −

RE

LEA

SE

TH

E M

AN

UA

L O

PE

RA

TIN

G D

EV

ICE

.

WA

RN

ING

:

WA

RN

ING

:

NO

TE

:

A P

OW

ER

HA

ND

TO

OL

(MIN

IMU

M 6

00 R

PM

,E

LEC

TR

IC O

R P

NE

UM

AT

IC)

OR

TH

E H

AN

DLE

(O

N T

HE

YE

LLO

W G

RO

UN

D−

SE

RV

ICE

PA

NE

L) IS

RE

QU

IRE

DF

OR

TH

IS O

PE

RA

TIO

N.

LAT

CH

ING

PR

ES

SU

RE

WA

RN

ING

LIG

HT

HA

ND

LE

TO

GG

LES

WIT

CH

GR

EE

NIN

DIC

AT

OR

LIG

HT

OP

ER

AT

ING

DE

VIC

E

HY

DR

AU

LIC

AU

XIL

IAR

Y−

GE

AR

BO

X

HA

ND

LE

HY

DR

AU

LIC

AU

XIL

IAR

Y−

PU

MP

PU

MP

YE

LLO

WG

RO

UN

D−

SE

RV

ICE

PA

NE

L

MA

NU

AL

LOC

KIN

GH

AN

DLE

194K

B

P_AC_100000_1_0110001_01_00

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

10-0-0Page 12

Jun 01/13


**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

Jun 01/13


**ON A/C A350-900

AP

U A

CC

ES

S D

OO

RS

P_AC_100000_1_0150001_01_00

OP

ER

AT

ION

:

1 −

OP

EN

TH

E O

VE

RP

RE

SS

UR

E D

OO

R 3

16B

R T

O R

ELE

AS

E U

NW

AN

TE

D A

IR P

RE

SS

UR

E.

2 −

TU

RN

TH

E M

EC

HA

NIS

M L

EV

ER

AN

D B

LOC

K IT

.3

− R

ELE

AS

E T

HE

HO

OK

LA

TC

HE

S O

N R

IGH

T A

CC

ES

S D

OO

R 3

16A

R.

4 −

OP

ER

AT

E P

IN L

AT

CH

ES

(F

OR

WA

RD

AN

D A

FT

).5

− O

PE

N R

IGH

T A

CC

ES

S D

OO

R 3

16A

R A

ND

LO

CK

MA

NU

ALL

Y T

HE

FIX

ED

RO

D W

HE

N D

OO

R IS

FU

LLY

OP

EN

.6

− O

PE

RA

TE

PIN

LA

TC

HE

S (

FO

RW

AR

D A

ND

AF

T)

ON

LE

FT

AC

CE

SS

DO

OR

315

AL.

7 −

OP

EN

LE

FT

AC

CE

SS

DO

OR

315

AL

AN

D L

OC

K M

AN

UA

LLY

TH

E F

IXE

D R

OD

WH

EN

DO

OR

IS F

ULL

Y O

PE

N.

PIN

LA

TC

HE

S

HO

OK

LA

TC

HE

SP

IN L

AT

CH

ES

316A

R

316A

L

316B

R

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

10-0-0Page 14

Jun 01/13


**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

.62

17.2

917

.09

2.08

6.82

CO

NF

IGU

RA

TIO

NA

/C AP

BF

1

CP

1D

1D

2D

3D

4

BF

2

3.37

3.29

11.0

610

.79

3.26

10.7

0

C1

C2

C3

2.59

8.50

BF

3

7.61

24.9

7D

5

(142

000

kg)

AF

T C

G (

40%

)

DIM

EN

SIO

NS

AR

E R

ELA

TE

D T

O A

IRC

RA

FT

WE

IGH

T A

ND

CG

CO

NF

IGU

RA

TIO

N

mft

2.70

8.86

4.64

5.27

7.56

0.93

17.0

79.

447.

04

15.2

217

.29

24.8

03.

05

56.0

030

.97

23.1

0

2.58

8.78

8.45

3.84

8.46

28.8

127

.72

12.6

0

CO

NF

IGU

RA

TIO

NA

/C F1

FT

2F

T3

HT

N1

VT

WL1

WL2F2

F3

F4

FT

1

4.34

14.2

4R

D1

(142

000

kg)

AF

T C

G (

40%

)

NO

TE

:P

AS

SE

NG

ER

AN

D C

AR

GO

DO

OR

GR

OU

ND

CLE

AR

AN

CE

S A

RE

ME

AS

UR

ED

FR

OM

TH

E C

EN

TE

R O

F T

HE

DO

OR

SIL

L A

ND

FR

OM

FLO

OR

LE

VE

L.

N1

VT

D4

C2

D3

RD

1

FT

1F

T2

FT

3

AP

HT

D2

D1

CP

1

WL1

WL2

C1

F1

F3

BF

2B

F1

BF

3

D5

F2

F4

C3

RA

T

RA

T1.

254.

10

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

10-0-0Page 15

Jun 01/13


**ON A/C A350-900

= =

CO

LOR

ED

NO

T M

AR

KE

DO

N A

LL A

IRC

RA

FT

==

CU

T H

ER

E IN

EM

ER

GE

NC

Y

P_AC_100000_1_0170001_01_01

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

10-0-0Page 16

Jun 01/13


**ON A/C A350-900

BA

T 2

BA

T E

ME

R 2

AC

CE

SS

VIA

FW

DC

AR

GO

CO

MP

AR

TM

EN

T D

OO

R

BA

T 1

BA

T E

ME

R 1

811

AC

CE

SS

VIA

AC

CE

SS

DO

OR

811

P_AC_100000_1_0180001_01_00

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

10-0-0Page 17

Jun 01/13

airbus a350-900 booklet

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