Airbus A350-900 Booklet

A350-900

AIRCRAFT CHARACTERISTICS

AIRPORT AND MAINTENANCE PLANNING

AC

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

AIRBUS S.A.S. Customer Services

Technical Data Support and Services 31707 Blagnac Cedex

LIST OF EFFECTIVE CONTENT Revision No. 0 - Jun 01/13

CONTENT CHG CODE LAST REVISION DATE 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 CHG CODE

LAST REVISION DATE

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

CONTENT CHG CODE

LAST REVISION DATE

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 FIGURE Exterior Lighting N Jun 01/13 FIGURE Exterior Lighting N Jun 01/13 FIGURE 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 CHG CODE

LAST REVISION DATE

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

CONTENT CHG CODE

LAST REVISION DATE

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 CHG CODE

LAST REVISION DATE

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

CONTENT CHG CODE

LAST REVISION DATE

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 CHG CODE

LAST REVISION DATE

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 Engineers Design 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 Design Method

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

CONTENT CHG CODE LAST REVISION DATE 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

4-5-2 135˚ Turn - Runway to Taxiway 4-5-3 180˚ Turn on a Runway

4-5-4 90˚ Turn - Taxiway to Taxiway 4-5-5 135˚ 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

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 and airlines for airport facilities planning.

The data given in this issue of the A350 AIRCRAFT CHARACTERISTICS AIRPORT AND

MAINTENANCE PLANNING (AC) can be subject to change pending completion of the design and flight 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 will deliver superior fuel efficiency, passenger comfort, environmental characteristics and economics, with a global market coverage.

The aircraft is designed to offer multiple payload capabilities with a consistant range ability across the 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 cargo containers 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 the aircraft scheduled downtime.

Correspondence concerning this publication should be directed to:

AIRBUS S.A.S. Customer Services

Technical Data Support and Services 1 Rond Point Maurice BELLONTE 31707 BLAGNAC CEDEX

FRANCE

1-2-0 Glossary **ON A/C A350-900

Glossary

1. List of Abbreviations A/C Aircraft

ACN Aircraft Classification Number APU 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 Administration FDL Fuselage Datum Line

FR Frame

FSTE Full Size Trolley Equivalent FWD Forward

GPU Ground Power Unit

GSE Ground Support Equipment

ICAO International Civil Aviation Organisation ISA International Standard Atmosphere L Radius of relative stiffness

LCN Load Classification Number LD Load Device

LD Lower Deck LH Left Hand LP Low Pressure LPS Last Pax Seating

MAC Mean Aerodynamic Chord MAX Maximum

MIN Minimum

MLG Main Landing Gear NLG Nose Landing Gear OAT Outside Air Temperature PAX Passenger

PCA Portland Cement Association PCN Pavement Classification Number PRM Passenger with Reduced Mobility RH Right Hand

ULD Unit Load Device US United States

VFG Variable Frequency Generator WV Weight Variant

Y/C Economic Class 2. Design Weight Terminology

Maximum Design Ramp Weight (MRW):

Maximum weight for ground maneuver (including weight of taxi and run-up fuel) as limited by aircraft 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 is the maximum weight at start of the take-off run).

Maximum Design Zero Fuel Weight (MZFW):

Maximum permissible weight of the aircraft without usable fuel.

Maximum Seating Capacity:

Maximum number of passengers specifically certified or anticipated for certification.

Usable Volume:

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.

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 Characteristics

Basic 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 Characteristics

Standard Seating Capacity 315 (2 class) 138000 l (36456.4 USgal) Usable Fuel Capacity

(density = 0.785 kg/l)

108330 kg (238827.0 lb) Pressurized Fuselage 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

Aircraft Characteristics

Water Volume, AFT CC 95.8 m3 (3383.16 ft.3) Water Volume, Bulk CC 11.4 m3

(402.59 ft.3)

2-2-0 General Aircraft Dimensions **ON A/C A350-900

General Aircraft Dimensions

**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

**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

2-3-0 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 aircraft configurations.

Dimensions in the tables are approximate and will vary with tire type, weight and balance and other special 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 sill and from floor level.

**ON A/C A350-900 P_AC_020300_1_0010001_01_02 m ft m ft m ft m ft A/C JACKED FDL = 6.5 m (21.33 ft) ft 21.69 8.01 19.16 16.57 16.73 16.92 17.13 7.91 6.55 5.90 5.18 2.45 2.46 5.10 5.12 5.15 21.49 8.07 19.36 16.73 16.80 16.90 17.00 8.04 6.83 2.56 5.93 5.15 5.22 5.32 5.41 2.51 17.13 22.41 8.40 16.90 17.45 17.75 8.23 2.70 5.33 6.52 2.66 6.20 5.37 5.27 5.21 17.49 21.39 8.73 20.34 17.62 17.29 17.09 8.86 7.72 3.71 7.18 6.37 6.37 6.37 6.37 3.71 25.33 12.17 23.56 20.90 20.90 20.90 20.90 12.17 19.46 6.33 1.93 6.33 2.07 6.79 2.08 6.82 3.16 10.37 14.86 16.96 25.16 2.43 56.33 30.84 22.90 4.52 5.16 7.60 0.75 17.10 9.37 6.96 14.83 16.93 24.93 2.46 56.10 30.74 22.84 4.68 5.32 7.88 0.87 17.39 9.57 7.14 15.35 17.45 25.85 2.85 57.05 31.40 23.43 4.64 5.27 7.56 0.93 17.07 9.44 7.04 15.22 17.29 24.80 3.05 56.00 30.97 23.10 5.74 6.38 8.77 18.27 10.57 8.17 18.83 20.93 28.77 6.53 59.94 34.68 26.80 1.99 8.30 27.89 27.59 12.21 2.50 8.54 8.38 3.71 8.20 28.02 27.49 12.17 2.70 8.61 8.59 3.87 8.86 28.25 28.18 12.70 2.58 8.78 8.45 3.84 8.46 28.81 27.72 12.60 3.71 9.80 9.58 4.94 12.17 32.15 31.43 16.21 CONFIGURATION A/C m AP BF1 CP1 D1 D2 D3 D4 F1 5.10 6.61 2.44 5.84 5.05 5.17 5.22 2.41 BF2 1.93 FT2 FT3 HT N1 VT WL1 WL2 4.53 5.17 7.67 0.74 17.17 9.40 6.98 F2 F3 F4 FT1 2.53 8.50 8.41 3.72 13.06 4.04 13.26 4.06 13.32 4.34 14.24 5.32 17.45 RD1 3.98 10.14 10.66 3.13 3.22 10.27 10.56 3.19 3.43 10.47 11.25 3.37 3.29 11.06 10.79 4.39 4.43 14.40 14.53 10.66 3.21 10.53 3.43 11.25 3.26 10.70 4.41 14.47 C1 C2 3.09 3.25 C3 3.25 8.27 2.50 8.20 2.68 8.79 2.59 8.50 3.71 12.17 BF3 2.52 23.79 7.31 23.98 7.33 24.05 7.61 24.97 8.59 28.18 D5 7.25 N1 VT D4 C2 D3 RD1 FT1 FT2 FT3 AP HT D2 D1 CP1 WL1 WL2 C1 F1 F3 BF2 BF1 BF3 D5

NOTE: PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED MRW FWD CG (26%)AFT CG (33.1%)MRW FWD CG (20%)(142 000 kg) (142 000 kg) AFT CG (40%) F2 F4 C3

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

Ground Clearances FIGURE-2-3-0-991-001-A01

2-4-0 Interior Arrangements - Plan View **ON A/C A350-900

Interior Arrangements - Plan View

1. This section gives the standard configuration.

**ON A/C A350-900

48 BUSINESS CLASS (6−ABREAST) 267 ECONOMY CLASS (9−ABREAST)

PASSENGER SEATS (315 TOTAL)

ITEM DESIGNATION G GALLEY (12) L LAVATORY (9) A ATTENDANT SEAT (8) S STOWAGE (1) PASSENGER DOOR 1 LH PASSENGER DOOR 2 LH PASSENGER DOOR 3 LH PASSENGER DOOR 4 LH PASSENGER DOOR 1 RH PASSENGER DOOR 2 RH PASSENGER DOOR 3 RH PASSENGER DOOR 4 RH

SEAT PITCHES: ECONOMY 32 in. BUSINESS 60 in.

A A G G G G G G G G G A A A A L L L L A A S L L L L G L P_AC_020400_1_0010001_01_01 Standard Configuration FIGURE-2-4-0-991-001-A01

2-5-0 Interior Arrangements - Cross Section **ON A/C A350-900

Interior Arrangements - Cross Section

1. This section gives the typical configuration.

**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 CABIN

CONFIGURATION SELECTED BY CUSTOMER _{P_AC_020500_1_0010001_01_01}

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

2-6-0 Cargo Compartments **ON A/C A350-900

Cargo Compartments

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

- Loading combinations.

**ON A/C A350-900 P_AC_020600_1_0020001_01_00 FR19 FR44 FR61 FR82 FR85 LOWER DECK

FORWARD CARGO COMPARTMENT LOWER DECK AFT CARGO

COMPARTMENT

LOWER DECK BULK CARGO

COMPARTMENT 2.90 m (114.55 in) 16.221 m _{(638.62 in)} 0.95 m _{(37.4 in)} 2.85 m (112.34 in) 1.91 m _{(75.20 in)} 13.578 m _{(535.57 in)} Cargo Compartments

Locations and Dimensions (Sheet 1 of 2) FIGURE-2-6-0-991-002-A01

**ON A/C A350-900 STANDARD: 20 LD3 CONTAINERS STANDARD: 16 LD3 CONTAINERS STANDARD: 6 PALLETS 88 in / 96 in X 125 in STANDARD: 5 PALLETS 88 in / 96 in X 125 in P_AC_020600_1_0020001_02_00 Cargo Compartments

Loading Combinations (Sheet 2 of 2) FIGURE-2-6-0-991-002-A01

2-7-0 Door Clearances and Location **ON A/C A350-900

Door Clearances and Location

**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

**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

2-7-1 Forward Doors **ON A/C A350-900

Forward Doors

1. This section gives forward door clearances.

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

**ON A/C A350-900 0.06 m (0.20 ft) FWD FWD 0.70 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 Doors FIGURE-2-7-1-991-002-A01

2-7-1

2-7-3 Aft Doors **ON A/C A350-900

Aft Doors

**ON A/C A350-900 FWD FWD 0.70 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 Doors FIGURE-2-7-3-991-001-B01

2-7-3

**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 Doors FIGURE-2-7-3-991-002-A01

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.

**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 CHAPTER 2−3

A A

Forward Cargo Compartment Door FIGURE-2-7-4-991-001-A01

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.

**ON A/C A350-900 A A FWD 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 CHAPTER 2−3

A A

Aft Cargo Compartment Door FIGURE-2-7-5-991-001-A01

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.

**ON A/C A350-900

A

A

Bulk Cargo Compartment Door FIGURE-2-7-6-991-001-A01

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.

**ON A/C A350-900 A

A

Nose Landing Gear Doors

Forward Nose Landing Gear Doors (Sheet 1 of 2) FIGURE-2-7-7-991-001-A01

**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

Nose Landing Gear Doors

Aft Nose Landing Gear Doors (Sheet 2 of 2) FIGURE-2-7-7-991-001-A01

2-7-8 Main Landing Gear Doors **ON A/C A350-900

Main Landing Gear Doors

**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

Main Landing Gear Doors FIGURE-2-7-8-991-001-A01

2-8-0 Escape Slides **ON A/C A350-900

Escape Slides 1. General

This section gives location of escape facilities and related clearances. 2. Location

Escape facilities are provided at the following locations:

- One cockpit escape rope is kept in a dedicated stowage compartment adjacent to the escape hatch,

**ON A/C A350-900 P_AC_020800_1_0010001_01_01 COCKPIT ESCAPE ROPE CABIN DUAL−LANE SLIDE/RAFT CABIN SINGLE−LANE SLIDE/RAFT CABIN DUAL−LANE SLIDE/RAFT CABIN DUAL−LANE SLIDE/RAFT Escape Slides Location (Sheet 1 of 2) FIGURE-2-8-0-991-001-A01

2-8-0

**ON A/C A350-900

P_AC_020800_1_0010001_02_00

GRID EQUALS 1 m (3.28 ft) IN REALITY

0 3 6 9 12 15 18 21 24 27 30 33

EMERGENCY DESCENT THROUGH THE ESCAPE HATCH WITH THE ESCAPE ROPE

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

2-9-0 Landing Gear **ON A/C A350-900

Landing Gear

1. MLG System Description

The two MLGs are mounted in the LH and RH wing just outboard of the wing root within the trailing 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 in the extended position for landing and ground manoeuvres.

Each MLG leg contains a single stage oleo shock strut consisting of a sliding piston and a main fitting that is supported by the two folding side stays and pivots on the top of the main fitting for

extension/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, only opening when the landing gear is extending or retracting.

Hydraulic power for the MLG extension/retraction is from the green hydraulic system. 2. NLG System Description

The 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 incorporates a 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 closed and 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 door uplock 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 System

The 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.

**ON A/C A350-900 P_AC_020900_1_0010001_01_00 A A HINGE DOOR FIXED FAIRING DOOR MAIN DOOR _B C D

A

GUIDE ROLLER RAMP

B

C

Main Landing Gear Doors overview (Sheet 1 of 3)

**ON A/C A350-900 P_AC_020900_1_0010001_02_00 RETRACTION ACTUATOR MAIN FITTING FORWARD LOCK STAY ACTUATOR FORWARD LOCK STAY FORWARD SIDE STAY FORWARD DOWNLOCK SPRINGS SLIDING PISTON BOGIE AFT LOCK STAY ACTUATOR AFT LOCK STAY AFT SIDE STAY AFT DOWNLOCK SPRINGS UPPER TORQUE LINK LOWER TORQUE LINK BOGIE PITCH TRIMMER ACTUATOR E

D

E

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

**ON A/C A350-900 P_AC_020900_1_0010001_03_00 SAFETY SAFETY PIN

F

G

H

Main Landing Gear Safety Devices (Sheet 3 of 3)

**ON A/C A350-900 P_AC_020900_1_0020001_01_00 A B C

A

B

Nose Landing Gear Doors overview (Sheet 1 of 4)

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

**ON A/C A350-900

P_AC_020900_1_0020001_02_00 RETRACTION ACTUATOR

LOCK STAY ACTUATOR

MAIN FITTING UPPER DRAG

BRACE LOWER DRAG

BRACE

FORWARD/ AFT LOCK STAYS

DOWNLOCK SPRINGS STEERING ASSEMBLY JACKING DOME UPPER TORQUE LINK LOWER TORQUE LINK SLIDING PISTON

C

D

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

**ON A/C A350-900 P_AC_020900_1_0020001_03_00

E

F

G

Nose Landing Gear Safety Devices (Sheet 3 of 4)

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

**ON A/C A350-900 P_AC_020900_1_0020001_04_00 1GN 2GN

H

J

K

Nose Landing Gear Service Panels (Sheet 4 of 4)

2-10-0 Exterior Lighting **ON A/C A350-900

Exterior Lighting

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

ITEM DESCRIPTION 1 RIGHT NAVIGATION LIGHT (GREEN) 2 LEFT NAVIGATION LIGHT (RED) 3 TAIL NAVIGATION LIGHT (WHITE)

4 UPPER ANTI-COLLISION LIGHT/BEACON (RED)

5 LOWER ANTI-COLLISION LIGHT/BEACON (RED)

6 LOGO LIGHTS

7 ENGINE SCAN LIGHTS 8 WING SCAN LIGHTS

9 WING STROBE LIGHT (HIGH INTENSITY, WHITE)

10 TAIL STROBE LIGHT (HIGH INTENSITY, WHITE)

11 TAXI CAMERA LIGHTS (NLG) 12 TAXI CAMERA LIGHTS (MLG) 13 LANDING LIGHTS

14 RUNWAY TURN-OFF LIGHTS

15 TAXI LIGHTS

16 TAKE-OFF LIGHTS

17 CARGO COMPARTMENT FLOOD LIGHTS 18 LANDING GEAR BAY/WELL LIGHTS (DOME)

**ON A/C A350-900 P_AC_021000_1_0010002_01_00 3 6 6 9 2 1 9 12 5 12 10 8 11 7 8 7 4 Exterior Lighting FIGURE-2-10-0-991-001-B01

**ON A/C A350-900 15 13 6 6 16 16 13 14 P_AC_021000_1_0020001_01_00 Exterior Lighting FIGURE-2-10-0-991-002-A01

2-10-0

**ON A/C A350-900 2 1 3 11 11 14 8 15 14 5 7 P_AC_021000_1_0030002_01_00 4 Exterior Lighting FIGURE-2-10-0-991-003-B01

**ON A/C A350-900 9 9 13 13 16 10 12 12 P_AC_021000_1_0040001_01_00 Exterior Lighting FIGURE-2-10-0-991-004-A01

2-10-0

**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

Exterior Lighting FIGURE-2-10-0-991-005-A01

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.

**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 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 34 35 36 37 38 39 40 1 − LOC 2 − SSA 1 3 − TAT PROBE 1, 2 4 − ICE PROBE 5 − GNSS 1 6 − GNSS 2 7 − TCAS 2 (TOP) 8 − WACS 9 − SATCOM 10 − VHF 1 11 − ADF 1 12 − ADF 2 13 − VHF 3 14 − ELT 15 − HF 16 − MARKER 17 − ISP LH 18 − DME 2 19 − RADIO ALT R2 21 − DME 1 22 − TCAS 1 (BOTTOM) 23 − PITOT 24 − MFP 1 25 − AOA

26− ICE PROBE DETECTOR 27 − GLIDE 28 − WEATHER RADAR 29 − VOR 30 − ISP RH 31 − TCAS 1 (TOP) 32 − SSA 2, 3

33 − ICE PROBE PROTECTOR 34 − MFP 2, 3 35 − RADIO ALT E1 36 − RADIO ALT R1 37 − RADIO ALT R3 38 − RADIO ALT E3 39 − TCAS 2 (BOTTOM) 33 40 − VHF 2 20 − RADIO ALT E2 NOTE:

LOCATION DEPENDING OF AIRCRAFT CONFIGURATION

Antennas and Probes Location FIGURE-2-11-0-991-001-A01

2-12-0 Engine and Nacelle **ON A/C A350-900

Engine and Nacelle 1. Power Plant

The 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. Nacelle

The nacelle comprises the following assemblies: - Air intake,

- Fan cowls, - Thrust reverser, - Exhaust system. A. Fan Cowl

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

B. Thrust Reverser

The engine thrust reverser consists primarily of a inner fixed structure and an outer translating sleeve.

The fan exhaust stream is reversed by the cascades and blocker doors, which form part of the translating 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 the hooks 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, for maintenance purposes, either using the TRAS powered by the aircraft or by manual drive with external Ground Support Equipment (GSE).

C. Exhaust System

The 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. Ignition

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

B. Cooling System

A nacelle cooling and ventilating system automatically provides the airflow required for cooling engine and nacelle accessories and associated structure.

C. Power Control

Forward thrust of each engine is controlled by a throttle control lever mounted on the center pedestal in the cockpit.

Thrust reverser control is by means of a separate lever for each engine. D. Engine Master Control

Engine fuel shutoff is controlled by switches installed on the center pedestal. E. Emergency Shutdown

Actuation of the fire controls closes the associated LP valves. F. Indicating

Indications for each engine are displayed on the Control and Display System (CDS). G. Oil

The propulsion system has an independent integral oil system that is able to provide the appropriate quantity of oil, at the temperature necessary for continuous propulsion system operation, 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 cowl door.

Magnetic chip detectors are installed in the lubrication system. H. Starting

The 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 Start Unit (AS).

**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 CONFIGURATION NOTE: 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 SECTION 2−3−0

Engine and Nacelle (Sheet 1 of 3) FIGURE-2-12-0-991-001-A01

**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 TR FC

FC: FAN COWL AND TR: THRUST REVERSER

Engine and Nacelle (Sheet 2 of 3) FIGURE-2-12-0-991-001-A01

**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 TR FC TR=45° FC=50°

APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION. NOTE:

FC: FAN COWL AND TR: THRUST REVERSER

Engine and Nacelle (Sheet 3 of 3) FIGURE-2-12-0-991-001-A01

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.

**ON A/C A350-900 , Z315 Z316 A FR104 FR112 ENGINE ENGINE FUEL AND CONTROL SYSTEM EXHAUST SYSTEM AIR SYSTEM IGNITION AND STARTING SYSTEM AIR SYSTEM OIL SYSTEM FR109 FR104

A

B

2-12-1

2-13-0 Levelling, Symmetry and Alignement **ON A/C A350-900

Levelling, Symmetry and Alignement 1. Quick Leveling

There 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 Leveling

For precise leveling, it is necessary to install sighting rods in the receptacles located under the fuselage (points 10 and 17 for longitudinal leveling) and under the wings (points 1 LH and 1 RH for lateral leveling) and use a sighting tube.

With the aircraft on jacks, adjust the jacks until the reference marks on the sighting rods are aligned in the sighting plane (aircraft level).

3. Symmetry and Alignment Check

**ON A/C A350-900 P_AC_021300_1_0010001_01_00 FR22 FR23 FR92 10 17 1RH 1LH RIB4 RIB5 RIB5 RIB4

Location of Leveling Points FIGURE-2-13-0-991-001-A01

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 Points

The aircraft is provided with three primary jacking points: - One located on the forward lower left fuselage (FR12), - Two located under the wings (one under each wing, RIB9). C. Auxiliary Jacking Point (Safety Stay)

When the aircraft is on jacks, a safety stay is placed under the fuselage at FR98 to prevent tail tipping caused by accidental displacement of the aircraft center of gravity.

The safety point must not be used for lifting the aircraft. 2. Jacks and Safety Stay

A. Jack Design

The Maximum Eligible Static Load given in table FIGURE 2-14-1-991-001-A are the maximum loads applicable on jack fittings.

(1) In fully retracted position (jack stroke at minimum), the height of the jacks is such that they may be placed beneath the aircraft under the most adverse conditions, namely, tires deflated and shock absorbers depressurized and, in addition, with a sufficient clearance between 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 required maintenance procedure and in particular, the landing gear shock absorbers

removal/installation. B. Safety Stay

The 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.

**ON A/C A350-900

FUSELAGE DATUM LINE

X FR12

FWD JACKING POINT

RIB9

RIB9

WING JACKING POINT WING JACKING POINT

SAFETY POINT FR98 Y A B B’ C SAFETY STAY WING JACKING POINT C B’ B FORWARD FUSELAGE JACKING 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 MAXIMUM LOAD ELIGIBLE m ft 18630 daN Y X 76600 76600 7650 m ft NOTE:

SAFETY STAY IS NOT USED FOR JACKING.

P_AC_021401_1_0010001_01_00

Jacking for Maintenance Jacking Points Location (Sheet 1 of 5)

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

**ON A/C A350-900

POSITION CG (% MAC)

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

A/C ON JACKS, FDL AT 6.50 m (21.33 ft), SHOCK−ABSORBER RELAXED, CLEARANCE OF MAIN GEAR WHEELS = 1.17 m (3.84 ft) (STANDARD TIRES *), CLEARANCE OF NOSE 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) 3.12 20 15.42 LH 4.00 RH 4.71 41 3.36 4.68 LH 4.00 RH 4.48 20 4.32 5.66 6.12 41 20 3.06 4.58 16.90 41 3.29 4.57 4.91 20 3.09 4.62 17.03 41 3.34 4.60 4.93 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 ft m ft N M L

FUSELAGE DATUM LINE

A/C FUSELAGE PARALLEL TO THE GROUND,

P_AC_021401_1_0010001_02_00

Jacking for Maintenance Jacking Dimensions (Sheet 2 of 5)

**ON A/C A350-900 FR12 FR13 FR14 FR11 NOSE JACK ADAPTOR

A

Jacking for Maintenance Forward Jacking Point (Sheet 3 of 5)

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

**ON A/C A350-900 A

A

Jacking for Maintenance Wing Jacking Point (Sheet 4 of 5)

**ON A/C A350-900 FR98 FR98 BEAM5 FR98 5 A B

A

B

Jacking for Maintenance

Auxiliary Jacking Point - Safety (Sheet 5 of 5) FIGURE-2-14-1-991-001-A01

2-14-2 Jacking for wheel change **ON A/C A350-900

Jacking for wheel change 1. General

To replace either the wheel or brake unit assemblies on any of the landing gears, it is necessary to lift the 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 of each 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 kept level 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.

**ON A/C A350-900

FWD

CONFIGURATION (ASSUME ALL OTHER TYRES ON

THE A/C ARE INTACT)

WEIGHT (T) CG

(% MAC)

DIM A DIM B

2 TYRES (NORMAL) 1 FLAT TYRE 2 FLAT TYRES & 50% RIM

FLANGE DAMAGE 2 FLAT TYRES & NO RIM

FLANGE 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

Nose Landing Gear Jacking Point Heights FIGURE-2-14-2-991-002-A01

**ON A/C A350-900 4 TYRES (NORMAL) MRW 33.2 378 378 1 029 1 036 267 267 AFT DIM A AFT DIM B AFT DIM 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 1 032 983 271 193

AFT INNER TYRE

UNSERVICEABLE 15.00 11.96 40.62 38.70 10.66 7.59

MRW 33.2 374 285 1 025 975 264 175

AFT OUTER TYRE

UNSERVICEABLE 14.72 11.22 40.35 38.38 10.39 6.88

MLW 42 129 404 967 1 071 18 293

2 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 18

2 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 26

4 FLAT TYRES &

50% RIM DAMAGE 5.35 5.35 38.07 38.07 1.02 1.02

MLW 42 159 403 967 1 071 48 293

2 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 48

2 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 55

4 FLAT TYRES &

NO RIM DAMAGE 6.53 6.53 38.07 38.07 2.16 2.16 MRW 33.2 541 378 1 113 1 029 431 268 FWD MAX GROWN TYRE 25 mm FROM GROUND 21.29 14.88 43.81 40.51 16.96 10.55 MRW 33.2 378 14.88 541 21.291 02940.511 11343.81 268 10.55 430 16.92

AFT MAX GROWN TYRE 25 mm FROM GROUND MRW 26.2 118 4.64 118 4.64 967 38.07 967 38.07 7 0.27 7 0.27 MRW 26.2 149 5.86 149 5.86 967 38.07 967 38.07 39 1.53 39 1.53 FWD INNER TYRE UNSERVICEABLE FWD OUTER TYRE UNSERVICEABLE

8 FLAT TYRES & 50% RIM DAMAGE

8 FLAT TYRES & NO RIM DAMAGE (ASSUME ALL OTHER

TYRES 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 A FWD DIM B FWD DIM C FWD A350−900 MLG (1 400 x 530 R23) A FWD A

A

Main Landing Gear Jacking Point Heights FIGURE-2-14-2-991-003-A01

GROUND MANEUVERING

4-2-0 Turning Radii

**ON A/C A350-900

Turning Radii

1. This section gives the turning radii.

**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

**ON A/C A350-900 P_AC_040200_1_0010001_02_00 19.6 20 TYPE OF TURN 2 EFFECTIVE STEERING ANGLE (deg) STEERING

ANGLE (deg)

76.3 250 A350−900 TURNING RADII

m ft 86.9 285 86.0 282 R4 113.6 373 R5 87.1 286 R6 96.0 315

WING NOSE TAIL

NOTE:

ABOVE 50°, AIRLINES MAY USE TYPE 1 OR TYPE 2 TURNS DEPENDING ON THE SITUATION TYPE 1 TURNS USE: ASYMMETRIC THRUST DURING THE WHOLE TURN;

AND DIFFERENTIAL BRAKING TO INITIATE THE TURN ONLY

TYPE 2 TURNS USE: SYMMETRIC THRUST DURING THE WHOLE TURN;

AND NO DIFFERENTIAL BRAKING AT ALL IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE

R1 R2 R3 RMLG LMLG NLG 24.5 25 2 58.7 193 69.3 227 69.6 228 96.2 316 71.2 233 79.7 262 29.4 30 2 46.7 153 57.3 188 58.9 193 84.3 277 60.8 199 69.0 226 34.2 35 2 38.0 125 48.6 159 51.5 169 75.7 248 53.7 176 61.5 202 39.1 40 2 31.1 102 41.7 137 45.9 151 68.9 226 48.5 159 55.9 183 43.8 45 2 25.7 84 36.3 119 41.8 137 63.7 209 44.7 147 51.7 170 48.6 50 2 21.1 69 31.7 104 38.6 127 59.2 194 41.8 137 48.3 158 53.1 55 2 17.4 57 28.0 92 36.2 119 55.5 182 39.6 130 45.7 150 57.5 60 2 14.1 46 24.7 81 34.3 113 52.4 172 38.0 125 43.5 143 61.5 65 2 11.4 37 22.0 72 32.9 108 49.8 163 36.7 121 41.9 137 65.0 70 2 9.2 30 19.8 65 31.9 105 47.7 156 35.9 118 40.6 133 49.3 50 1 20.5 67 31.1 102 38.2 125 58.6 192 41.4 136 47.8 157 54.1 55 1 16.6 54 27.2 89 35.7 117 54.8 180 39.2 129 45.1 148 58.7 60 1 13.3 43 23.9 78 33.8 111 51.6 169 37.6 123 43.0 141 63.2 65 1 10.3 34 20.9 69 32.4 106 48.7 160 36.3 119 41.2 135 67.5 70 1 7.7 25 18.3 60 31.2 103 46.2 152 35.3 116 39.8 130 m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft

FROM TYPE 1 BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN. 66.1 72 (MAX) 2 8.5 28 19.1 63 31.6 104 47.0 154 35.6 117 40.2 132 m ft 69.2 72 (MAX) 1 6.7 22 17.3 57 30.9 101 45.3 149 35.0 115 39.2 129 m ft Turning Radii (Sheet 2 of 2) FIGURE-4-2-0-991-001-A01

4-2-0

4-3-0 Minimum Turning Radii **ON A/C A350-900

Minimum Turning Radii

**ON A/C A350-900 P_AC_040300_1_0010001_01_00 69.2 72 (MAX) TYPE OF TURN 1 EFFECTIVE STEERING ANGLE (deg) STEERING

ANGLE (deg)

28.7 94

A350−900 MINIMUM TURNING RADII

m ft 48.5 159 30.9 101 R4 45.3 149 R5 35.0 115 R6 39.2 129

WING NOSE TAIL

X A 66.1 72 (MAX) 2 28.7 94 51.1 168 31.6 104 47.0 154 35.6 117 40.2 132 m ft Y _NLGR3 10.9 36 12.7 42 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 1 BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN. TO INITIATE THE TURN ONLY

A

(MINIMUM TURNING WIDTH) X Y R5 R3 R6 R4

Minimum Turning Radii FIGURE-4-3-0-991-001-A01

4-4-0 Visibility from Cockpit in Static Position **ON A/C A350-900

Visibility from Cockpit in Static Position

**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 FOR LANDING 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 PILOT EYE POSITION.

3.04 m (9.97 ft)

MAX AFT VISION WITH HEAD TURNED AROUND SPINAL COLUMN.

WING TIP CAN BE SEEN WHEN HEAD IS MOVED TO THE SIDE.

VISUAL ANGLES IN HORIZONTAL PLANE THROUGH PILOT EYE POSITION.

FIRST OFFICER FIELD OF VIEW

VISUAL ANGLES IN PLANE PERPENDICULAR TO LONGITUDINAL AXIS. 120°

105.5°

Visibility from Cockpit in Static Position FIGURE-4-4-0-991-001-A01

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 Taxiway

The 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.

4-5-1 90˚ Turn - Runway to Taxiway **ON A/C A350-900

90˚ Turn - Runway to Taxiway

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

**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 APPROX 10.9 m (36 ft) TAXIWAY RUNWAY CENTERLINE NLG PATH MLG PATH FAA LEAD−IN FILLET

L=75 m (250 ft)

(150 ft) 45 m

CENTERLINE

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

**ON A/C A350-900 P_AC_040501_1_0010001_02_02 APPROX 5 m (16 ft) FILLET R = 25.5 m (85 ft) TURN R = 45 m (150 ft) (75 ft) 23 m TAXIWAY CENTERLINE RUNWAY CENTERLINE NLG PATH MLG PATH FAA LEAD−IN FILLET

L=75 m (250 ft)

(150 ft) 45 m

90˚ Turn - Runway to Taxiway

Cockpit over Centerline Method (Sheet 2 of 2) FIGURE-4-5-1-991-001-A01

4-5-2 135˚ Turn - Runway to Taxiway **ON A/C A350-900

135˚ Turn - Runway to Taxiway

**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) FILLET R = 25.5 m (85 ft) APPROX 5.8 m (19 ft) APPROX 7.6 m (25 ft) NLG PATH MLG PATH FAA LEAD−IN FILLET

L=75 m (250 ft)

CENTERLINE

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

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

**ON A/C A350-900 P_AC_040502_1_0010002_02_02 RUNWAY TAXIWAY 23 m (75 ft) FILLET R = 25.5 m (85 ft) 4.5 m (15 ft) EDGE CLEARANCE ADDITIONAL FILLET TO MEET TURN R = 45 m (150 ft) APPROX 1.6 m (5 ft) (150 ft) 45 m NLG PATH MLG PATH FAA LEAD−IN FILLET

L=75 m (250 ft) CENTERLINE

CENTERLINE

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

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.

**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 DIFFERENTIAL BRAKING DURING THE WHOLE TURN.

NOSE TIP PATH NLG PATH

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

4-5-4 90˚ Turn - Taxiway to Taxiway **ON A/C A350-900

90˚ Turn - Taxiway to Taxiway

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

**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 FILLET R = 25.5 m (85 ft) APPROX 10.5 m (34 ft) FAA LEAD−IN FILLET

L=75 m (250 ft) APPROX 12.9 m (42 ft) (75 ft) 23 m NLG PATH MLG PATH CENTERLINE

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

**ON A/C A350-900 TURN R = 45 m (150 ft) TAXIWAY CENTERLINE (75 ft) 23 m TAXIWAY FILLET R = 25.5 m (85 ft)

FAA LEAD−IN FILLET L=75 m (250 ft) APPROX 3.9 m (13 ft) (75 ft) 23 m 4.5 m (15 ft) EDGE CLEARANCE ADDITIONAL FILLET TO MEET

NLG PATH MLG PATH

P_AC_040504_1_0010001_02_02 CENTERLINE

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

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

4-5-5 135˚ Turn - Taxiway to Taxiway **ON A/C A350-900

135˚ Turn - Taxiway to Taxiway

**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) FILLET R = 25.5 m (85 ft) APPROX 8.8 m (29 ft) NLG PATH MLG PATH FAA LEAD−IN FILLET

L=75 m (250 ft)

P_AC_040505_1_0010002_01_02 CENTERLINE

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

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

**ON A/C A350-900 TAXIWAY CENTERLINE (75 ft) 23 m TAXIWAY 23 m (75 ft) FILLET R = 25.5 m (85 ft) 4.5 m (15 ft) EDGE CLEARANCE ADDITIONAL FILLET TO MEET TURN R = 45 m (150 ft) APPROX 2.5 m (8 ft) NLG PATH MLG PATH FAA LEAD−IN FILLET

L=75 m (250 ft)

P_AC_040505_1_0010002_02_02 CENTERLINE

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

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).

**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) TAXIWAY CENTERLINE RUNWAY CENTERLINE MAIN LANDING GEAR PATH HOLDING POINT NOTE:

COORDINATE WITH USING AIRCRAFT FOR SPECIFIC PLANNED OPERATING PROCEDURES.

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

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 to initiate the turn.

TODA: Take-Off Available Distance

ASDA: Acceleration-Stop Distance Available 2. 90˚ Turn on Runway Entry

This 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 at a distance of 4.5 m from taxiway edge, and finishing with the aircraft aligned on the centerline of the runway.

During the turn, all the clearances must meet the minimum value of 4.5 m for this category of aircraft as recommended in ICAO Annex 14.

3. 180˚ Turn on Runway Turn Pad

This 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 turn pad geometry.

It starts with the edge of the MLG at 4.5 m from pavement edge, and it finishes with the aircraft aligned on the centerline of the runway.

During the turn, all the clearances must meet the minimum value of 4.5 m for this category of aircraft as recommended in ICAO Annex 14.

4. 180˚ Turn on Runway Width

This 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 frozen parameter (45 m and 60 m).

As per the ”180˚ turn on runway” standard operating procedures described in the Flight Crew Operating Manual, the aircraft is initially angled with respect to runway centerline when starting the 180˚ turn.

The value of this angle depends on the aircraft type, and is mentioned in the FCOM.

During the turn, all the clearances must meet the minimum value of 4.5 m for this category of aircraft as recommended in ICAO Annex 14.

**ON A/C A350-900 P_AC_040700_1_0010001_01_00 TODA ASDA 4.5 m (15 ft) 4.5 m (15 ft)

90° TURN ON RUNWAY ENTRY

AIRCRAFT TYPE MAX STEERING ANGLE 45 m WIDE RUNWAY (STANDARD WIDTH) 60 m WIDE RUNWAY (STANDARD WIDTH) MINIMUM LINE−UP DISTANCE CORRECTION

ON TODA ON ASDA ON TODA ON ASDA

MINIMUM LINE−UP DISTANCE CORRECTION 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 AVAILABLE TODA: TAKE−OFF AVAILABLE DISTANCE

TAXIWAY CENTERLINE

RUNWAY CENTERLINE

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

**ON A/C A350-900

P_AC_040700_1_0020001_01_00 180° TURN ON RUNWAY TURNPAD

AIRCRAFT TYPE MAX STEERING ANGLE 45 m WIDE RUNWAY (STANDARD WIDTH) 60 m WIDE RUNWAY (STANDARD WIDTH) MINIMUM LINE−UP DISTANCE CORRECTION ON TODA ON ASDA MINIMUM LINE−UP DISTANCE CORRECTION 72° A350−900 122 ft 37.2 m NOTE:

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

216 ft 65.9 m 117 ft 35.7 m 211 ft 64.4 m ON TODA ON ASDA REQUIRED MINIMUM PAVEMENT 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) RUNWAY CENTERLINE

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

**ON A/C A350-900

P_AC_040700_1_0030001_01_00 180° TURN ON RUNWAY WIDTH

AIRCRAFT TYPE MAX STEERING ANGLE 45 m WIDE RUNWAY (STANDARD WIDTH) 60 m WIDE RUNWAY (STANDARD WIDTH) MINIMUM LINE−UP DISTANCE CORRECTION

ON TODA ON ASDA ON TODA ON ASDA

MINIMUM LINE−UP DISTANCE CORRECTION 72°

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

NOTE:

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

RUNWAY CENTERLINE > 4.5 m (15 ft) 4.5 m (15 ft) 4.5 m (15 ft) TODA ASDA 25°

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

4-8-0 Aircraft Mooring **ON A/C A350-900

Aircraft Mooring

1. This section provides information on aircraft mooring.

**ON A/C A350-900 TOWING FITTING A B

B

A

REMOVE BEFORE FLIGHT

P_AC_040800_1_0010001_01_00

Aircraft Mooring FIGURE-4-8-0-991-001-A01