Airbus A350-900 Booklet

@AIRBUS A350-900

AIRCRAFT CHARACTERISTICS AIRPORT 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 may information 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 of the copyright. Requests for reproduction of any data in this document and the media authorized for it must be addressed to Airbus. © AIRBUS S.A.S. 2005. All rights reserved.

AIRBUS S.A.S. Customer Services Technical Data Support and Services 31707 Blagnac Cedex FRANCE

Issue: Jun 01/13

Rev: Jun 01/13

@A350-900 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

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

CHG CODE

LAST REVISION DATE

N

Jun 01/13

N

Jun 01/13

N

Jun 01/13

General Aircraft Dimensions

N

Jun 01/13

FIGURE General Aircraft Dimensions

N

Jun 01/13

Ground Clearances

N

Jun 01/13

FIGURE Ground Clearances

N

Jun 01/13

Interior Arrangements - Plan View

N

Jun 01/13

FIGURE Standard Configuration

N

Jun 01/13

Interior Arrangements - Cross Section

N

Jun 01/13

FIGURE Typical Configuration

N

Jun 01/13

Cargo Compartments

N

Jun 01/13

FIGURE Cargo Compartments

N

Jun 01/13

Door Clearances and Location

N

Jun 01/13

FIGURE Door Location

N

Jun 01/13

CHAPTER 1 Subject 1-1-0 Introduction Subject 1-2-0 Glossary CHAPTER 2 Subject 2-1-0 General Aircraft Characteristics Subject 2-2-0

Subject 2-3-0

Subject 2-4-0

Subject 2-5-0

Subject 2-6-0

Subject 2-7-0

L.E.C. Page 1 Jun 01/13


CONTENT

CHG CODE

LAST REVISION DATE

Forward Doors

N

Jun 01/13

FIGURE Forward Doors

N

Jun 01/13

FIGURE Forward Doors

N

Jun 01/13

Aft Doors

N

Jun 01/13

FIGURE Aft Doors

N

Jun 01/13

FIGURE Aft Doors

N

Jun 01/13

Forward Cargo Compartment Door

N

Jun 01/13

FIGURE Forward Cargo Compartment Door

N

Jun 01/13

Aft Cargo Compartment Door

N

Jun 01/13

FIGURE Aft Cargo Compartment Door

N

Jun 01/13

Bulk Cargo Compartment Door

N

Jun 01/13

FIGURE Bulk Cargo Compartment Door

N

Jun 01/13

Nose Landing Gear Doors

N

Jun 01/13

FIGURE Nose Landing Gear Doors

N

Jun 01/13

Main Landing Gear Doors

N

Jun 01/13

FIGURE Main Landing Gear Doors

N

Jun 01/13

Escape Slides

N

Jun 01/13

FIGURE Escape Slides

N

Jun 01/13

Landing Gear

N

Jun 01/13

FIGURE Main Landing Gear

N

Jun 01/13

Subject 2-7-1

Subject 2-7-3

Subject 2-7-4

Subject 2-7-5

Subject 2-7-6

Subject 2-7-7

Subject 2-7-8

Subject 2-8-0

Subject 2-9-0



CONTENT

CHG CODE N

LAST REVISION DATE Jun 01/13

Exterior Lighting

N

Jun 01/13

FIGURE Exterior Lighting

N

Jun 01/13


N

Jun 01/13


N

Jun 01/13


N

Jun 01/13


N

Jun 01/13

Antennas and Probes Location

N

Jun 01/13

FIGURE Antennas and Probes Location

N

Jun 01/13

Engine and Nacelle

N

Jun 01/13

FIGURE Engine and Nacelle

N

Jun 01/13

APU

N

Jun 01/13

FIGURE APU

N

Jun 01/13

Levelling, Symmetry and Alignement

N

Jun 01/13

FIGURE Location of Leveling Points

N

Jun 01/13

Jacking for Maintenance

N

Jun 01/13

FIGURE Jacking for Maintenance

N

Jun 01/13

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

FIGURE Nose Landing Gear Subject 2-10-0

Subject 2-11-0

Subject 2-12-0

Subject 2-12-1

Subject 2-13-0

Subject 2-14-1

Subject 2-14-2

CHAPTER 4 Subject 4-2-0 L.E.C. Page 3 Jun 01/13


CONTENT

CHG CODE N


N

Jun 01/13

Minimum Turning Radii

N

Jun 01/13

FIGURE Minimum Turning Radii

N

Jun 01/13

Visibility from Cockpit in Static Position

N

Jun 01/13

FIGURE Visibility from Cockpit in Static Position

N

Jun 01/13

N

Jun 01/13

90˚ Turn - Runway to Taxiway

N

Jun 01/13

FIGURE 90˚ Turn - Runway to Taxiway

N

Jun 01/13


N

Jun 01/13

FIGURE 135˚ Turn - Runway to Taxiway

N

Jun 01/13

180˚ Turn on a Runway

N

Jun 01/13

FIGURE 180˚ Turn on a Runway

N

Jun 01/13

90˚ Turn - Taxiway to Taxiway

N

Jun 01/13

FIGURE 90˚ Turn - Taxiway to Taxiway

N

Jun 01/13


N

Jun 01/13

FIGURE 135˚ Turn - Taxiway to Taxiway

N

Jun 01/13

Runway Holding Bay (Apron)

N

Jun 01/13

FIGURE Runway Holding Bay (Apron)

N

Jun 01/13

Turning Radii FIGURE Turning Radii Subject 4-3-0

Subject 4-4-0

Subject 4-5-0 Introduction Subject 4-5-1

Subject 4-5-2

Subject 4-5-3

Subject 4-5-4

Subject 4-5-5

Subject 4-6-0

Subject 4-7-0



CONTENT

CHG CODE N


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

Aircraft Mooring

N

Jun 01/13

FIGURE Aircraft Mooring

N

Jun 01/13

N

Jun 01/13

Typical Ramp Layout (Open Apron)

N

Jun 01/13

FIGURE Typical Ramp Layout (Open Apron)

N

Jun 01/13

Typical Ramp Layout (Gate)

N

Jun 01/13

FIGURE Typical Ramp Layout (Gate)

N

Jun 01/13

Terminal Operations - Full Servicing Turn Round Time

N

Jun 01/13

FIGURE Full Servicing Turn Round Time Chart

N

Jun 01/13

Terminal Operations - Transit Turn Round Time

N

Jun 01/13

FIGURE Transit Turn Round Time

N

Jun 01/13

Ground Service Connections layout

N

Jun 01/13

FIGURE Ground Service Connections layout

N

Jun 01/13

Grounding Points

N

Jun 01/13

FIGURE Ground Point NLG

N

Jun 01/13

FIGURE Ground Point MLG

N

Jun 01/13

Minimum Line-Up Distance Corrections

Subject 4-8-0

CHAPTER 5 Subject 5-1-0 Aircraft Servicing Arrangements Subject 5-1-1

Subject 5-1-2

Subject 5-2-0

Subject 5-3-0

Subject 5-4-0

Subject 5-4-1



CONTENT

CHG CODE

LAST REVISION DATE

Hydraulic System

N

Jun 01/13

FIGURE Green Ground Service Panel

N

Jun 01/13

FIGURE Yellow Ground Service Panel

N

Jun 01/13

Electrical System

N

Jun 01/13

FIGURE Electrical Service Panel

N

Jun 01/13

FIGURE RAT

N

Jun 01/13

Oxygen System

N

Jun 01/13

FIGURE Oxygen System

N

Jun 01/13

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

Pneumatic System

N

Jun 01/13

FIGURE Low Pressure Preconditioned Air

N

Jun 01/13

FIGURE High Pressure Preconditioned Air

N

Jun 01/13

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

Oil System

N

Jun 01/13

FIGURE Engine Oil Servicing

N

Jun 01/13

FIGURE VFG Oil Servicing

N

Jun 01/13

Subject 5-4-2

Subject 5-4-3

Subject 5-4-4

Subject 5-4-5

Subject 5-4-6

Subject 5-4-7

Subject 5-4-8



CONTENT

CHG CODE N


N

Jun 01/13

Vacuum Toilet System

N

Jun 01/13

FIGURE Ground Service Panel

N

Jun 01/13

FIGURE Waste Tanks Location

N

Jun 01/13

Ground Pneumatic Power Requirements

N

Jun 01/13

FIGURE Ground Pneumatic Power Requirements

N

Jun 01/13

Preconditioned Airflow Requirements

N

Jun 01/13

FIGURE Preconditioned Airflow Requirements

N

Jun 01/13

Towing Requirements

N

Jun 01/13

FIGURE Towing Requirements

N

Jun 01/13

N

Jun 01/13

APU Exhaust Velocities and Temperatures

N

Jun 01/13

FIGURE APU Exhaust Velocities and Temperatures

N

Jun 01/13

N

Jun 01/13

Landing Gear Footprint

N

Jun 01/13

FIGURE Landing Gear Footprint

N

Jun 01/13

N

Jun 01/13

FIGURE Starter Oil Servicing FIGURE APU Oil Servicing Subject 5-4-9

Subject 5-6-0

Subject 5-7-0

Subject 5-8-0

Subject 5-9-0 De-icing and External cleaning CHAPTER 6 Subject 6-4-0

CHAPTER 7 Subject 7-1-0 General Information Subject 7-2-0

Subject 7-3-0 Maximum Pavement Loads



CONTENT

CHG CODE N


Landing Gear Loading on Pavement

N

Jun 01/13

FIGURE Landing Gear Loading on Pavement

N

Jun 01/13

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

Flexible Pavement Requirements - LCN Conversion

N

Jun 01/13

FIGURE Flexible Pavement Requirements - LCN

N

Jun 01/13

N

Jun 01/13

N

Jun 01/13

Rigid Pavement Requirements - LCN Conversion

N

Jun 01/13

FIGURE Rigid Pavement Requirements - LCN

N

Jun 01/13

Radius of Relative Stiffness (L)

N

Jun 01/13

FIGURE Radius of Relative Stiffness (L)

N

Jun 01/13

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

Aircraft Classification Number - Flexible Pavement

N

Jun 01/13

FIGURE Aircraft Classification Number - Flexible Pavement

N

Jun 01/13

Aircraft Classification Number - Rigid Pavement

N

Jun 01/13

FIGURE Aircraft Classification Number - Rigid Pavement

N

Jun 01/13

FIGURE Maximum Pavement Loads Subject 7-4-0

Subject 7-5-0

Subject 7-6-0

Subject 7-7-0 Rigid Pavement Requirements - Portland Cement Association Design Method FIGURE Rigid Pavement Requirements Subject 7-8-0

Subject 7-8-1

Subject 7-8-2

Subject 7-9-0

Subject 7-9-1



CONTENT

CHG CODE

LAST REVISION DATE

Scaled Drawings

N

Jun 01/13

FIGURE Scaled Drawings

N

Jun 01/13

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

CHAPTER 8 Subject 8-0-0

CHAPTER 10 Subject 10-0-0



TABLE OF CONTENTS

1 1-1-0 1-2-0

SCOPE INTRODUCTION 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 4-2-0 4-3-0 4-4-0 4-5-0 4-5-1

GROUND MANEUVERING Turning Radii Minimum Turning Radii Visibility from Cockpit in Static Position Runway and Taxiway Turn Paths 90˚ Turn - Runway to Taxiway T.O.C. Page 1 Jun 01/13


4-5-2 4-5-3 4-5-4 4-5-5 4-6-0 4-7-0 4-8-0

135˚ Turn - Runway to Taxiway 180˚ Turn on a Runway 90˚ Turn - Taxiway to Taxiway 135˚ Turn - Taxiway to Taxiway Runway Holding Bay (Apron) Minimum Line-Up Distance Corrections Aircraft Mooring

5 5-1-0 5-1-1 5-1-2 5-2-0 5-3-0 5-4-0 5-4-1 5-4-2 5-4-3 5-4-4 5-4-5 5-4-6 5-4-7 5-4-8 5-4-9 5-6-0 5-7-0 5-8-0 5-9-0

TERMINAL SERVICING Aircraft Servicing Arrangements Typical Ramp Layout (Open Apron) Typical Ramp Layout (Gate) Terminal Operations - Full Servicing Turn Round Time Terminal Operations - Transit Turn Round Time Ground Service Connections layout Grounding Points Hydraulic System Electrical System Oxygen System Fuel System Pneumatic System Potable Water System Oil System Vacuum Toilet System Ground Pneumatic Power Requirements Preconditioned Airflow Requirements Towing Requirements De-icing and External cleaning

6 6-4-0

OPERATING CONDITIONS APU Exhaust Velocities and Temperatures

7 7-1-0 7-2-0 7-3-0 7-4-0 7-5-0

PAVEMENT DATA General Information Landing Gear Footprint Maximum Pavement Loads Landing Gear Loading on Pavement Flexible Pavement Requirements - US Army Corps of Engineers Design Method S-77-1 T.O.C. Page 2 Jun 01/13


7-6-0 7-7-0 7-8-0 7-8-1 7-8-2 7-9-0 7-9-1 8 8-0-0

Flexible Pavement Requirements - LCN Conversion Rigid Pavement Requirements - Portland Cement Association Design Method Rigid Pavement Requirements - LCN Conversion Radius of Relative Stiffness (L) Radius of Relative Stiffness (Other values of E and µ) Aircraft Classification Number - Flexible Pavement Aircraft Classification Number - Rigid Pavement SCALED DRAWINGS 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 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

1-1-0

Page 1 Jun 01/13


1-2-0

Glossary

**ON A/C A350-900 Glossary 1. List of Abbreviations Aircraft A/C ACN Aircraft Classification Number APU Auxiliary Power Unit Business Class B/C California Bearing Ratio CBR 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 Ground Support Equipment GSE ICAO International Civil Aviation Organisation International Standard Atmosphere ISA 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 Outside Air Temperature OAT PAX Passenger PBB Passenger Boarding Bridge

1-2-0

Page 1 Jun 01/13


PCA PCN PRM RH ULD US VFG WV Y/C 2.

Portland Cement Association Pavement Classification Number Passenger with Reduced Mobility Right Hand Unit Load Device United States Variable Frequency Generator Weight Variant Economic Class

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.

1-2-0

Page 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 Characteristics Basic Weights 268900 kg (592824.0 lb) 268000 kg (590839.0 lb) 205000 kg (451948.0 lb) 192000 kg (423288.0 lb)

Maximum Taxi Weight (MTW) Maximum Ramp Weight (MRW) Maximum Take Off Weight (MTOW) Maximum Landing Weight (MLW) Maximum Zero Fuel Weight (MZFW)

Aircraft Characteristics Standard Seating Capacity Usable Fuel Capacity (density = 0.785 kg/l)

Pressurized Fuselage Volume Cockpit Volume Passenger Compartment Volume Usable Volume, FWD CC (Based on LD3) Usable Volume, AFT CC (Based on LD3) Usable Volume, Bulk CC Water Volume, FWD CC

315 (2 class) 138000 l (36456.4 USgal) 108330 kg (238827.0 lb) 971 m3 (34291.0 ft.3) 8.23 m3 (291.0 ft.3) 473.7 m3 (16729.0 ft.3) 89.4 m3 (3157.0 ft.3) 71.5 m3 (2525.0 ft.3) 9.12 m3 (322.07 ft.3) 113.4 m3 (4004.7 ft.3)

2-1-0

Page 1 Jun 01/13


Aircraft Characteristics Water Volume, AFT CC Water Volume, Bulk CC

95.8 m3 (3383.16 ft.3) 11.4 m3 (402.59 ft.3)

2-1-0

Page 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.

2-2-0

Page 1 Jun 01/13


**ON A/C A350-900 66.61 m (218.54 ft) 3.04 m (9.97 ft) 6.09 m (19.98 ft)

9.42 m (30.90 ft)

4.63 m (15.19 ft) 28.66 m (94.03 ft) 65.26 m (214.11 ft) 64.75 m (212.43 ft) 18.79 m (61.65 ft)

1.74 m (5.71 ft) 0.75 m (2.46 ft)

10.60 m (34.77 ft) 12.87 m (42.22 ft) RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

P_AC_020200_1_0010001_01_01

General Aircraft Dimensions (Sheet 1 of 2) FIGURE-2-2-0-991-001-A01

2-2-0

Page 2 Jun 01/13


**ON A/C A350-900 66.80 m (219.16 ft)

2.46 m (8.07 ft) 5.96 m (19.55 ft)

10.50 m (34.45 ft)

7.86 m (25.79 ft) 12.75 m (41.83 ft) 17.02 m (55.84 ft)

9.62 m (31.56 ft)

21.97 m (72.08 ft)

5.18 m (16.99 ft) 46.68 m (153.15 ft)

RELATED TO AIRCRAFT ATTITUDE AND WEIGHT

P_AC_020200_1_0010001_02_01

General Aircraft Dimensions (Sheet 2 of 2) FIGURE-2-2-0-991-001-A01

2-2-0

Page 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 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.

2-3-0

Page 1 Jun 01/13


**ON A/C A350-900

VT

AP

D4 C3 C2 F2 F4

D3 BF3

D2 BF1

BF2

F3 C1

D1 D5

RD1 CP1

F1

N1 WL1

FT3

FT2

FT1

HT

WL2

A/C (142 000 kg) (142 000 kg) A/C JACKED MRW MRW CONFIGURATION FWD CG (26%) AFT CG (33.1%) FWD CG (20%) AFT CG (40%) FDL = 6.5 m (21.33 ft) AP BF1 BF2 BF3 C1 C2 C3 CP1 D1 D2 D3 D4 D5 F1 F2 F3 F4 FT1 FT2 FT3 HT N1 RD1 VT WL1 WL2

m ft 6.61 21.69 2.44 8.01 1.93 6.33 2.52 8.27 3.09 10.14 3.25 10.66 3.25 10.66 5.84 19.16 5.05 16.57 5.10 16.73 5.17 16.92 5.22 17.13 7.25 23.79 2.41 7.91 8.30 2.53 8.50 27.89 8.41 27.59 3.72 12.21 4.53 14.86 5.17 16.96 7.67 25.16 0.74 2.43 3.98 13.06 17.17 56.33 9.40 30.84 6.98 22.90

m 6.55 2.46 1.93 2.50 3.13 3.22 3.21 5.90 5.10 5.12 5.15 5.18 7.31 2.45 2.50 8.54 8.38 3.71 4.52 5.16 7.60 0.75 4.04 17.10 9.37 6.96

ft 21.49 8.07 6.33 8.20 10.27 10.56 10.53 19.36 16.73 16.80 16.90 17.00 23.98 8.04 8.20 28.02 27.49 12.17 14.83 16.93 24.93 2.46 13.26 56.10 30.74 22.84

m 6.83 2.56 2.07 2.68 3.19 3.43 3.43 5.93 5.15 5.22 5.32 5.41 7.33 2.51 2.70 8.61 8.59 3.87 4.68 5.32 7.88 0.87 4.06 17.39 9.57 7.14

ft m 6.52 22.41 2.66 8.40 6.79 2.08 8.79 2.59 10.47 3.37 11.25 3.29 11.25 3.26 6.20 19.46 5.37 16.90 5.33 17.13 5.27 17.45 5.21 17.75 24.05 7.61 8.23 2.70 8.86 2.58 8.78 28.25 8.45 28.18 3.84 12.70 15.35 4.64 17.45 5.27 25.85 7.56 0.93 2.85 13.32 4.34 57.05 17.07 31.40 9.44 23.43 7.04

ft 21.39 8.73 6.82 8.50 11.06 10.79 10.70 20.34 17.62 17.49 17.29 17.09 24.97 8.86 8.46 28.81 27.72 12.60 15.22 17.29 24.80 3.05 14.24 56.00 30.97 23.10

m 7.72 3.71 3.16 3.71 4.39 4.43 4.41 7.18 6.37 6.37 6.37 6.37 8.59 3.71 3.71 9.80 9.58 4.94 5.74 6.38 8.77 1.99 5.32 18.27 10.57 8.17

ft 25.33 12.17 10.37 12.17 14.40 14.53 14.47 23.56 20.90 20.90 20.90 20.90 28.18 12.17 12.17 32.15 31.43 16.21 18.83 20.93 28.77 6.53 17.45 59.94 34.68 26.80

NOTE: PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED FROM THE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.

P_AC_020300_1_0010001_01_02

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

2-3-0

Page 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.

2-4-0

Page 1 Jun 01/13

A

G

L

S

A L

PASSENGER DOOR 1 LH

L

G

PASSENGER DOOR 1 RH

ITEM G L A S

G

DESIGNATION (12) GALLEY (9) LAVATORY ATTENDANT SEAT (8) (1) STOWAGE

PASSENGER DOOR 2 LH

A

A

PASSENGER DOOR 2 RH

2-4-0

SEAT PITCHES: ECONOMY 32 in. BUSINESS 60 in.

G A

A

G G

G G G G

PASSENGER DOOR 4 LH

L

L

PASSENGER DOOR 4 RH

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

PASSENGER SEATS (315 TOTAL)

PASSENGER DOOR 3 LH

L A

L

L

L A

PASSENGER DOOR 3 RH

@A350-900

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A350-900

P_AC_020400_1_0010001_01_01

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

Page 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.

2-5-0

Page 1 Jun 01/13


**ON A/C A350-900 BUSINESS CLASS / FIRST CLASS 6 ABREAST

1.50 m (59 in)

0.57 m (22.5 in)

0.55 m (21.5 in)

0.18 m (7 in)

0.09 m (3.5 in)

BASELINE ECONOMY CLASS 9 ABREAST

1.53 m (60.11 in)

0.04 m (1.5 in)

0.46 m (18 in)

0.46 m (18.1in) 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

2-5-0

Page 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.

2-6-0

Page 1 Jun 01/13

2.90 m (114.55 in)

FR19

16.221 m (638.62 in)

LOWER DECK FORWARD CARGO COMPARTMENT

FR44

2-6-0

13.578 m (535.57 in)

2.85 m (112.34 in)

LOWER DECK AFT CARGO COMPARTMENT

FR61 FR85

0.95 m (37.4 in)

1.91 m (75.20 in)

LOWER DECK BULK CARGO COMPARTMENT

FR82

@A350-900


**ON A/C A350-900

P_AC_020600_1_0020001_01_00

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

Page 2 Jun 01/13


STANDARD: 20 LD3 CONTAINERS

STANDARD: 6 PALLETS 88 in / 96 in X 125 in

STANDARD: 16 LD3 CONTAINERS

STANDARD: 5 PALLETS 88 in / 96 in X 125 in

**ON A/C A350-900

P_AC_020600_1_0020001_02_00

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

2-6-0

Page 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.

2-7-0

Page 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

COCKPIT ESCAPE HATCH

PAX DOOR 4 RH

PAX DOOR 3 RH

PAX DOOR 2 RH

AFT CARGO DOOR

PAX DOOR 1 RH

FORWARD CARGO DOOR

P_AC_020700_1_0010001_01_01

Door Location (Sheet 1 of 2) FIGURE-2-7-0-991-001-A01

2-7-0

Page 2 Jun 01/13


**ON A/C A350-900 52.55 m (172.41 ft)

37.93 m (124.44 ft)

18.85 m (61.84 ft)

6.85 m (22.47 ft)

49.99 m (164.01 ft)

4.12 m (13.52 ft)

11.69 m (38.35 ft) 47.30 m (155.18 ft)

P_AC_020700_1_0010001_02_01

Door Location (Sheet 2 of 2) FIGURE-2-7-0-991-001-A01

2-7-0

Page 3 Jun 01/13


2-7-1

Forward Doors

**ON A/C A350-900 Forward Doors 1.

This section gives forward door clearances.

2-7-1

Page 1 Jun 01/13


**ON A/C A350-900

2.16 m (7.09 ft)

0.06 m (0.20 ft)

FWD

0.82 m (2.69 ft)

0.73 m (2.40 ft)

2.46 m (8.07 ft) FWD P_AC_020701_1_0010001_01_00

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

2-7-1

Page 2 Jun 01/13


**ON A/C A350-900

2.16 m (7.09 ft)

0.06 m (0.20 ft)

FWD

0.84 m (2.76 ft)

2.46 m (8.07 ft)

0.70 m (2.30 ft)

FWD

P_AC_020701_1_0020001_01_00

Forward Doors FIGURE-2-7-1-991-002-A01

2-7-1

Page 3 Jun 01/13


2-7-3

Aft Doors

**ON A/C A350-900 Aft Doors 1.

This section gives aft door clearances.

2-7-3

Page 1 Jun 01/13


**ON A/C A350-900

2.11 m (6.92 ft)

0.06 m (0.20 ft)

FWD

0.84 m (2.76 ft)

0.70 m (2.30 ft)

2.46 m (8.07 ft) FWD P_AC_020703_1_0010002_01_00

Aft Doors FIGURE-2-7-3-991-001-B01

2-7-3

Page 2 Jun 01/13


**ON A/C A350-900

2.16 m (7.09 ft)

0.06 m (0.20 ft)

FWD

0.75 m (2.46 in)

0.80 m (2.62 ft)

2.45 m (8.04 ft) FWD

P_AC_020703_1_0020001_01_00

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

2-7-3

Page 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.

2-7-4

Page 1 Jun 01/13


**ON A/C A350-900

A

FWD

A

2.51 m (8.23 ft)

1.90 m (6.23 ft)

SEE CHAPTER 2−3

2.59 m (8.50 ft)

0.08 m (0.26 ft)

A A P_AC_020704_1_0010001_01_00

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

2-7-4

Page 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.

2-7-5

Page 1 Jun 01/13


**ON A/C A350-900

A

FWD

A

2.53 m (8.30 ft)

1.91 m (6.27 ft)

SEE CHAPTER 2−3

2.57 m (8.43 ft)

0.10 m (0.33 ft)

A A P_AC_020705_1_0010001_01_00

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

2-7-5

Page 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.

2-7-6

Page 1 Jun 01/13


**ON A/C A350-900

A

FWD

A

0.77 m (2.53 ft)

1.75 m (5.74 ft)

SEE CHAPTER 2−3

A A P_AC_020706_1_0010001_01_00

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

2-7-6

Page 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.

2-7-7

Page 1 Jun 01/13


**ON A/C A350-900

A

1.06 m (3.48 ft)

61.8 °

R 0.78 m (2.56 ft)

R 1.06 m (3.48 ft) 2.93 m (9.61 ft)

0.77 m (2.53 ft)

2m (6.56 ft)

A

P_AC_020707_1_0010001_01_00

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

2-7-7

Page 2 Jun 01/13


**ON A/C A350-900

A

0.76 m (2.49 ft)

R 0.71 m (2.33 ft) R 0.72 m (2.36 ft)

69.8 °

0.59 m (1.94 ft)

2.03 m (6.66 ft)

2.15 m (7.05 ft)

A P_AC_020707_1_0010001_02_00

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

2-7-7

Page 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.

2-7-8

Page 1 Jun 01/13


**ON A/C A350-900

A

2.75 m (9.02 ft)

1.63 m (5.35 ft)

81.3 °

R 2.43 m (7.97 ft)

0.13 m 0.19 m (0.43 ft) (0.62 ft)

A

P_AC_020708_1_0010001_01_00

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

2-7-8

Page 2 Jun 01/13


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

2-8-0

Page 1 Jun 01/13


**ON A/C A350-900

CABIN DUAL−LANE SLIDE/RAFT



COCKPIT ESCAPE ROPE

CABIN SINGLE−LANE SLIDE/RAFT

P_AC_020800_1_0010001_01_01

Escape Slides Location (Sheet 1 of 2) FIGURE-2-8-0-991-001-A01

2-8-0

Page 2 Jun 01/13


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

**ON A/C A350-900

P_AC_020800_1_0010001_02_00

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

2-8-0

Page 3 Jun 01/13


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.

2-9-0

Page 1 Jun 01/13


**ON A/C A350-900 HINGE DOOR FIXED FAIRING DOOR

C A

D

A

HINGE

F MAIN DOOR

B

A LH SHOWN RH SYMMETRICAL GUIDE

MECHANICAL LINKAGE

GUIDE

RAMP

ROLLER

B

C

P_AC_020900_1_0010001_01_00

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

2-9-0

Page 2 Jun 01/13


**ON A/C A350-900 FORWARD LOCK STAY ACTUATOR FORWARD LOCK STAY

RETRACTION ACTUATOR

H MAIN FITTING

FORWARD DOWNLOCK SPRINGS

E

FORWARD SIDE STAY

SLIDING PISTON

AFT LOCK STAY ACTUATOR AFT LOCK STAY

BOGIE

H

AFT DOWNLOCK SPRINGS

D AFT SIDE STAY

UPPER TORQUE LINK LOWER TORQUE LINK

BOGIE PITCH TRIMMER ACTUATOR

E P_AC_020900_1_0010001_02_00

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

2-9-0

Page 3 Jun 01/13


**ON A/C A350-900

SAFETY COLLAR ACTUATOR

G SAFETY PIN

SAFETY PIN

F

G

HINGE

LOCK STAY

SAFETY PIN

H TYPICAL INSTALLATION P_AC_020900_1_0010001_03_00

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

2-9-0

Page 4 Jun 01/13


**ON A/C A350-900

A FORWARD DOOR

B AFT DOOR

C

E

A

HINGE

HINGE FREE FALL RAMP

NLG Z−STOP

DRIVEN LINKAGE ROD

B RH SHOWN LH SYMMETRICAL

P_AC_020900_1_0020001_01_00

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

2-9-0

Page 5 Jun 01/13


**ON A/C A350-900 RETRACTION ACTUATOR

G LOCK STAY ACTUATOR FORWARD/ AFT LOCK STAYS UPPER DRAG BRACE LOWER DRAG BRACE MAIN FITTING

DOWNLOCK SPRINGS

D

H STEERING ASSEMBLY

JACKING DOME

C UPPER TORQUE LINK SLIDING PISTON

LOWER TORQUE LINK

D P_AC_020900_1_0020001_02_00

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

2-9-0

Page 6 Jun 01/13


**ON A/C A350-900

ACTUATOR

SAFETY COLLAR

F

SAFETY PIN SAFETY PIN

F

E

LOCK STAY

SAFETY PIN

G P_AC_020900_1_0020001_03_00

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

2-9-0

Page 7 Jun 01/13


**ON A/C A350-900

J

K

2GN

1GN

H

J FWD

K FWD P_AC_020900_1_0020001_04_00

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

2-9-0

Page 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 LIGHTING ITEM

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18

DESCRIPTION RIGHT NAVIGATION LIGHT (GREEN) LEFT NAVIGATION LIGHT (RED) TAIL NAVIGATION LIGHT (WHITE) UPPER ANTI-COLLISION LIGHT/BEACON (RED) LOWER ANTI-COLLISION LIGHT/BEACON (RED) LOGO LIGHTS ENGINE SCAN LIGHTS WING SCAN LIGHTS WING STROBE LIGHT (HIGH INTENSITY, WHITE) TAIL STROBE LIGHT (HIGH INTENSITY, WHITE) TAXI CAMERA LIGHTS (NLG) TAXI CAMERA LIGHTS (MLG) LANDING LIGHTS RUNWAY TURN-OFF LIGHTS TAXI LIGHTS TAKE-OFF LIGHTS CARGO COMPARTMENT FLOOD LIGHTS LANDING GEAR BAY/WELL LIGHTS (DOME)

2-10-0

Page 1 Jun 01/13


**ON A/C A350-900

9

3 6

1

6 4

9

2

7 8

7 8

11 12

5

12

10

P_AC_021000_1_0010002_01_00

Exterior Lighting FIGURE-2-10-0-991-001-B01

2-10-0

Page 2 Jun 01/13


**ON A/C A350-900

13

13

16 15

16 14

6

6

P_AC_021000_1_0020001_01_00

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

2-10-0

Page 3 Jun 01/13


**ON A/C A350-900 3

5

1

2

4

8

7 11

11

14

14

15

P_AC_021000_1_0030002_01_00

Exterior Lighting FIGURE-2-10-0-991-003-B01

2-10-0

Page 4 Jun 01/13


**ON A/C A350-900 10

12

12 9

9

16

13

13

P_AC_021000_1_0040001_01_00


2-10-0

Page 5 Jun 01/13


**ON A/C A350-900

18

17

17

18

EXAMPLE FOR LIGHT N° 17 CEILING LIGHT

SPOT LIGHT

P_AC_021000_1_0050001_01_00


2-10-0

Page 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.

2-11-0

Page 1 Jun 01/13


**ON A/C A350-900

15

1

2

3 4

5 6 7

23 28 24 27 26 25

8

9

10

11 12

13

14

17 22 21 20 19 18

16

29

30

31 32

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 20 − RADIO ALT E2

39 38 37 36 35 34 33

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) 40 − VHF 2

NOTE: LOCATION DEPENDING OF AIRCRAFT CONFIGURATION

P_AC_021100_1_0010001_01_00

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

2-11-0

Page 2 Jun 01/13


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.

3.

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.

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.

2-12-0

Page 1 Jun 01/13


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). Standard types of GSE can be used.

2-12-0

Page 2 Jun 01/13


**ON A/C A350-900 5.09 m (16.70 ft)

0.72 m (2.39 ft)

11.10 m (36.42 ft)

2.03 m (6.66 ft)

1.53 m (5.02 ft)

1.68 m (5.51 ft) 1.94 m (6.36 ft) 2.09 m (6.86 ft)

1.40 m (4.59 ft) 6.40 m (21 ft)

1.65 m (5.41 ft) 3.94 m (12.93 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 TO SECTION 2−3−0

NOTE: APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION

P_AC_021200_1_0010001_01_00

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

2-12-0

Page 3 Jun 01/13


**ON A/C A350-900

C A

FC

A

D

TR

B

B

5.50 m (18.04 ft)

1.01 m (3.31 ft)

C

D

6.39 m (20.96 ft)

1.28 m (4.20 ft)

NOTE: APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION. FC: FAN COWL AND TR: THRUST REVERSER P_AC_021200_1_0010001_02_00


2-12-0

Page 4 Jun 01/13


**ON A/C A350-900

C A

FC

A TR=45°

D

TR

B

B

6.42 m (21.06 ft)

1.51 m (4.95 ft)

FC=50°

C

D

7.13 m (23.40 ft)

1.81 m (5.94 ft)

NOTE: APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION. FC: FAN COWL AND TR: THRUST REVERSER P_AC_021200_1_0010001_03_00


2-12-0

Page 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.

2-12-1

Page 1 Jun 01/13


**ON A/C A350-900

Z315, Z316 ENGINE

A

FR112

EXHAUST SYSTEM

AIR SYSTEM

B

IGNITION AND STARTING SYSTEM

FR104

A

ENGINE FUEL AND CONTROL SYSTEM

AIR SYSTEM

FR104

FR109

B

OIL SYSTEM

P_AC_021201_1_0010001_01_00

APU FIGURE-2-12-1-991-001-A01

2-12-1

Page 2 Jun 01/13


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 Possible deformation of the aircraft is measured by photogrammetry.

2-13-0

Page 1 Jun 01/13


**ON A/C A350-900

RIB5 RIB4 1RH

FR92 17 RIB5

RIB4 10 1LH FR22 FR23

P_AC_021300_1_0010001_01_00

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

2-13-0

Page 2 Jun 01/13


2-14-1

Jacking for Maintenance

**ON A/C A350-900 Jacking for Maintenance 1.

2.

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.

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.

2-14-1

Page 1 Jun 01/13


**ON A/C A350-900

RIB9

WING JACKING POINT B FUSELAGE DATUM LINE SAFETY POINT

FR98

FR12

A

C Y

X FWD JACKING POINT B’

WING JACKING POINT RIB9

X

MAXIMUM LOAD ELIGIBLE

Y

m

ft

m

ft

daN

FORWARD FUSELAGE JACKING POINT A

4.77

15.65

−1.72

−5.64

18630

WING JACKING POINT

B

33.22

108.99

8.71

28.58

76600

B’

33.22

108.99

−8.71

−28.58

76600

SAFETY STAY

C

58.75

192.75

0

0

7650

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

2-14-1

Page 2 Jun 01/13


**ON A/C A350-900

FUSELAGE DATUM LINE

N

M

L

CONFIGURATION

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

A/C ON JACKS, FDL AT 6.50 m (21.33 ft), A/C FUSELAGE PARALLEL TO THE GROUND, 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)

CG POSITION (% MAC)

HEIGHT L

M

m

ft

m

N ft

4.70 LH 15.42 LH 4.00 RH 13.12 RH 4.68 LH 15.35 LH 4.00 RH 13.12 RH

m

ft

4.71

15.45

4.48

14.70

20

3.12 10.24

41

3.36

20

4.32 14.17

5.66

18.57

6.12

20.08

41

4.32 14.17

5.66

18.57

6.12

20.08

20

3.06

10.04

4.58

15.03

5.15

16.90

41

3.29

10.79

4.57

14.99

4.91

16.11

20

3.09

10.14

4.62

15.16

5.19

17.03

41

3.34

10.96

4.60

15.09

4.93

16.18

11.02

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

NOTE: * STANDARD TIRES: NOSE LANDING GEAR = 1 050 x 395 R16 MAIN LANDING GEAR = 1 400 x 530 R23

P_AC_021401_1_0010001_02_00

Jacking for Maintenance Jacking Dimensions (Sheet 2 of 5) FIGURE-2-14-1-991-001-A01

2-14-1

Page 3 Jun 01/13


**ON A/C A350-900

A Z120

FR11 FR12

FR12 FR13

FR13 FR14

NOSE JACK ADAPTOR

A P_AC_021401_1_0010001_03_00

Jacking for Maintenance Forward Jacking Point (Sheet 3 of 5) FIGURE-2-14-1-991-001-A01

2-14-1

Page 4 Jun 01/13


**ON A/C A350-900 RIB9 REAR SPAR

A 571FB (671FB)

A Z571 (Z671)

PLATE COVER PROTECTOR

A WING JACK ADAPTOR

A

4

1 2 3

A A P_AC_021401_1_0010001_04_00

Jacking for Maintenance Wing Jacking Point (Sheet 4 of 5) FIGURE-2-14-1-991-001-A01

2-14-1

Page 5 Jun 01/13


**ON A/C A350-900

FR98

BEAM5

Z310

FR98

A B

A

AFT JACK ADAPTOR

FR98

5

B FWD P_AC_021401_1_0010001_05_00

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

2-14-1

Page 6 Jun 01/13


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.

2-14-2

Page 1 Jun 01/13


**ON A/C A350-900

A

A

B FWD

A

− A : DOME HEIGHT − B : DISTANCE BETWEEN TYRES A350−900 NLG (1 050 x 395 R16) CONFIGURATION (ASSUME ALL OTHER TYRES ON THE A/C ARE INTACT)

WEIGHT (T)

2 TYRES (NORMAL)

MRW

1 FLAT TYRE

DIM A

CG (% MAC)

DIM B

mm

in

mm

in

26.2

291

11.45

261

10.27

MRW

26.2

227

8.93

214

8.42

2 FLAT TYRES & 50% RIM FLANGE DAMAGE

MLW

20

75

2.95

191

7.51

2 FLAT TYRES & NO RIM FLANGE DAMAGE

MLW

20

97

3.81

191

7.51

P_AC_021402_1_0020001_01_00

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

2-14-2

Page 2 Jun 01/13


**ON A/C A350-900

A

A

C

B

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

A

A350−900 MLG (1 400 x 530 R23) CONFIGURATION DIM A DIM A DIM B DIM B (ASSUME ALL OTHER WEIGHT CG AFT FWD AFT FWD TYRES ON THE A/C (T) (% MAC) mm in mm in mm in mm in ARE INTACT) 4 TYRES (NORMAL) 33.2 378 14.88 378 14.88 1 029 40.51 1 036 40.78 MRW FWD INNER TYRE 33.2 304 11.96 381 15.00 981 38.62 1 041 40.98 MRW UNSERVICEABLE FWD OUTER TYRE 33.2 285 11.22 374 14.72 974 38.34 1 033 40.66 MRW UNSERVICEABLE AFT INNER TYRE 33.2 381 15.00 304 11.96 1 032 40.62 983 38.70 MRW UNSERVICEABLE AFT OUTER TYRE 33.2 374 14.72 285 11.22 1 025 40.35 975 38.38 MRW UNSERVICEABLE 2 FLAT FWD TYRES 42 129 5.07 404 15.90 967 38.07 1 071 42.16 MLW & 50% RIM DAMAGE 2 FLAT AFT TYRES 42 404 15.90 129 5.07 1 060 41.73 967 38.07 MLW & 50% RIM DAMAGE 4 FLAT TYRES & 42 136 5.35 136 5.35 967 38.07 967 38.07 MLW 50% RIM DAMAGE 2 FLAT FWD TYRES 42 159 6.25 403 15.86 967 38.07 1 071 42.16 MLW & NO RIM DAMAGE 2 FLAT AFT TYRES 42 403 15.86 159 6.25 1 059 41.69 967 38.07 MLW & NO RIM DAMAGE 4 FLAT TYRES & 42 166 6.53 166 6.53 967 38.07 967 38.07 MLW NO RIM DAMAGE TYRE CHANGE FWD MAX GROWN TYRE 25 mm 33.2 541 21.29 378 14.88 1 113 43.81 1 029 40.51 MRW FROM GROUND AFT MAX GROWN 33.2 378 14.88 541 21.29 1 029 40.51 1 113 43.81 MRW TYRE 25 mm FROM GROUND 8 FLAT TYRES & 26.2 118 4.64 118 4.64 967 38.07 967 38.07 MRW 50% RIM DAMAGE 8 FLAT TYRES & 26.2 149 5.86 149 5.86 967 38.07 967 38.07 MRW NO RIM DAMAGE

DIM C FWD mm

in

DIM C AFT mm

in

267 10.51 267 10.51 194 7.63

271 10.66

175 6.88 264 10.39 271 10.66 193 7.59 264 10.39 175 6.88 18

0.70 293 11.53

293 11.53 18

0.70

26

1.02

1.02

48

1.88 293 11.53

26

293 11.53 48

1.88

55

2.16

2.16

55

431 16.96 268 10.55 268 10.55 430 16.92 7

0.27

7

0.27

39

1.53

39

1.53

P_AC_021402_1_0030001_01_00

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

2-14-2

Page 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.

4-2-0

Page 1 Jun 01/13


**ON A/C A350-900

R5

R3

R1

70° 65°

60°

R2

R4

R6

NOTE: FOR TURNING RADII VALUES, REFER TO SHEET 2

P_AC_040200_1_0010001_01_00

Turning Radii (Sheet 1 of 2) FIGURE-4-2-0-991-001-A01

4-2-0

Page 2 Jun 01/13


**ON A/C A350-900 A350−900 TURNING RADII TYPE OF STEERING EFFECTIVE TURN ANGLE (deg) STEERING ANGLE (deg) 2

20

19.6

2

25

24.5

2

30

29.4

2

35

34.2

2

40

39.1

2

45

43.8

2

50

48.6

2

55

53.1

2

60

57.5

2

65

61.5

2

70

65.0

2

72 (MAX)

66.1

1

50

49.3

1

55

54.1

1

60

58.7

1

65

63.2

1

70

67.5

1

72 (MAX)

69.2

R1 R2 RMLG LMLG

R3 NLG

R4 WING

R5 NOSE

R6 TAIL

m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft m ft

76.3 250 58.7 193 46.7 153 38.0 125 31.1 102 25.7 84 21.1 69 17.4 57 14.1 46 11.4 37 9.2 30 8.5 28

86.9 285 69.3 227 57.3 188 48.6 159 41.7 137 36.3 119 31.7 104 28.0 92 24.7 81 22.0 72 19.8 65 19.1 63

86.0 282 69.6 228 58.9 193 51.5 169 45.9 151 41.8 137 38.6 127 36.2 119 34.3 113 32.9 108 31.9 105 31.6 104

113.6 373 96.2 316 84.3 277 75.7 248 68.9 226 63.7 209 59.2 194 55.5 182 52.4 172 49.8 163 47.7 156 47.0 154

87.1 286 71.2 233 60.8 199 53.7 176 48.5 159 44.7 147 41.8 137 39.6 130 38.0 125 36.7 121 35.9 118 35.6 117

96.0 315 79.7 262 69.0 226 61.5 202 55.9 183 51.7 170 48.3 158 45.7 150 43.5 143 41.9 137 40.6 133 40.2 132

m ft m ft m ft m ft m ft m ft

20.5 67 16.6 54 13.3 43 10.3 34 7.7 25 6.7 22

31.1 102 27.2 89 23.9 78 20.9 69 18.3 60 17.3 57

38.2 125 35.7 117 33.8 111 32.4 106 31.2 103 30.9 101

58.6 192 54.8 180 51.6 169 48.7 160 46.2 152 45.3 149

41.4 136 39.2 129 37.6 123 36.3 119 35.3 116 35.0 115

47.8 157 45.1 148 43.0 141 41.2 135 39.8 130 39.2 129

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 FROM TYPE 1 BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN. P_AC_040200_1_0010001_02_00

Turning Radii (Sheet 2 of 2) FIGURE-4-2-0-991-001-A01

4-2-0

Page 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.

4-3-0

Page 1 Jun 01/13


**ON A/C A350-900

R5

R3

X

Y

R4 A (MINIMUM TURNING WIDTH) R6

NOTE: 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 A350−900 MINIMUM TURNING RADII TYPE OF STEERING EFFECTIVE TURN ANGLE (deg) STEERING ANGLE (deg) 1

72 (MAX)

69.2

2

72 (MAX)

66.1

m ft m ft

X

Y

A

R3 NLG

R4 WING

R5 NOSE

R6 TAIL

28.7 94 28.7 94

10.9 36 12.7 42

48.5 159 51.1 168

30.9 101 31.6 104

45.3 149 47.0 154

35.0 115 35.6 117

39.2 129 40.2 132

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

P_AC_040300_1_0010001_01_00

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

4-3-0

Page 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.

4-4-0

Page 1 Jun 01/13


**ON A/C A350-900 NOT TO BE USED FOR LANDING APPROACH VISIBILITY DIMENSIONS ARE APPROXIMATE

27°

VISUAL ANGLES IN VERTICAL PLANE THROUGH PILOT EYE POSITION.

20°

3.04 m (9.97 ft) 14.20 m (46.59 ft)

105.5° 120° FIRST OFFICER FIELD OF VIEW

4.63 m (15.19 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.

CAPTAIN FIELD OF VIEW 105.5° 120° 0.53 m (1 ft 8.88 in)

VISUAL ANGLES IN PLANE PERPENDICULAR TO LONGITUDINAL AXIS. 32°

32°

15°

15°

NOTE: PILOT EYE POSITION WHEN PILOT’S EYES ARE IN LINE WITH THE RED AND WHITE BALLS. ZONE THAT CANNOT BE SEEN P_AC_040400_1_0010001_01_00

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

4-4-0

Page 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 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.

4-5-0

Page 1 Jun 01/13


4-5-1


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

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

4-5-1

Page 1 Jun 01/13


**ON A/C A350-900

FAA LEAD−IN FILLET L=75 m (250 ft) APPROX 10.9 m (36 ft)

23 m (75 ft) APPROX 13.3 m (44 ft)

TAXIWAY CENTERLINE

FILLET R = 25.5 m (85 ft)

TURN R = 45 m (150 ft)

NLG PATH MLG PATH RUNWAY CENTERLINE

45 m (150 ft) P_AC_040501_1_0010001_01_02

90˚ Turn - Runway to Taxiway Oversteering Method (Sheet 1 of 2) FIGURE-4-5-1-991-001-A01

4-5-1

Page 2 Jun 01/13


**ON A/C A350-900

FAA LEAD−IN FILLET L=75 m (250 ft)

APPROX 5 m (16 ft)

23 m (75 ft)

TAXIWAY CENTERLINE FILLET R = 25.5 m (85 ft)

TURN R = 45 m (150 ft)

NLG PATH MLG PATH RUNWAY CENTERLINE

45 m (150 ft) P_AC_040501_1_0010001_02_02

90˚ Turn - Runway to Taxiway Cockpit over Centerline Method (Sheet 2 of 2) FIGURE-4-5-1-991-001-A01

4-5-1

Page 3 Jun 01/13


4-5-2


**ON A/C A350-900 135˚ Turn - Runway to Taxiway 1.

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

4-5-2

Page 1 Jun 01/13


**ON A/C A350-900

APPROX 5.8 m (19 ft)




TURN R = 45 m (150 ft)

TAXIWAY CENTERLINE

23 m (75 ft)

NLG PATH RUNWAY CENTERLINE

MLG PATH

45 m (150 ft)

P_AC_040502_1_0010002_01_02

135˚ Turn - Runway to Taxiway Oversteering Method (Sheet 1 of 2) FIGURE-4-5-2-991-001-B01

4-5-2

Page 2 Jun 01/13


**ON A/C A350-900

RUNWAY CENTERLINE

TURN R = 45 m (150 ft)

FAA LEAD−IN FILLET L=75 m (250 ft) APPROX 1.6 m (5 ft)


ADDITIONAL FILLET TO MEET 4.5 m (15 ft) EDGE CLEARANCE

TAXIWAY CENTERLINE

23 m (75 ft)

NLG PATH MLG PATH

45 m (150 ft)

P_AC_040502_1_0010002_02_02

135˚ Turn - Runway to Taxiway Cockpit over Centerline Method (Sheet 2 of 2) FIGURE-4-5-2-991-001-B01

4-5-2

Page 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.

4-5-3

Page 1 Jun 01/13


**ON A/C A350-900

RUNWAY CENTERLINE

R4 = 45.3 m (149 ft)

R3 = 30.9 m (101 ft)

4.5 m (15 ft)

R5 = 35 m (115 ft) 4.5 m (15 ft)

APPROX 48.5 m (159.12 ft) NLG PATH NOSE TIP PATH 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.

P_AC_040503_1_0010001_01_01

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

4-5-3

Page 2 Jun 01/13


4-5-4


**ON A/C A350-900 90˚ Turn - Taxiway to Taxiway 1.

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

4-5-4

Page 1 Jun 01/13


**ON A/C A350-900



23 m (75 ft) APPROX 12.9 m (42 ft)

TAXIWAY CENTERLINE


TURN R = 45 m (150 ft)

NLG PATH

TAXIWAY CENTERLINE

MLG PATH 23 m (75 ft)

P_AC_040504_1_0010001_01_02

90˚ Turn - Taxiway to Taxiway Oversteering Method (Sheet 1 of 2) FIGURE-4-5-4-991-001-A01

4-5-4

Page 2 Jun 01/13


**ON A/C A350-900



23 m (75 ft)


TAXIWAY CENTERLINE


TURN R = 45 m (150 ft)

TAXIWAY CENTERLINE

NLG PATH MLG PATH

23 m (75 ft)

P_AC_040504_1_0010001_02_02

90˚ Turn - Taxiway to Taxiway Cockpit over Centerline Method (Sheet 2 of 2) FIGURE-4-5-4-991-001-A01

4-5-4

Page 3 Jun 01/13


4-5-5


**ON A/C A350-900 135˚ Turn - Taxiway to Taxiway 1.

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

4-5-5

Page 1 Jun 01/13


**ON A/C A350-900



APPROX 8.8 m (29 ft) FILLET R = 25.5 m (85 ft)

TURN R = 45 m (150 ft) TAXIWAY CENTERLINE

TAXIWAY CENTERLINE

23 m (75 ft)

NLG PATH MLG PATH

23 m (75 ft)

P_AC_040505_1_0010002_01_02

135˚ Turn - Taxiway to Taxiway Oversteering Method (Sheet 1 of 2) FIGURE-4-5-5-991-001-B01

4-5-5

Page 2 Jun 01/13


**ON A/C A350-900

TURN R = 45 m (150 ft)


APPROX 2.5 m (8 ft)



TAXIWAY CENTERLINE 23 m (75 ft)

TAXIWAY CENTERLINE

NLG PATH MLG PATH

23 m (75 ft)

P_AC_040505_1_0010002_02_02

135˚ Turn - Taxiway to Taxiway Cockpit over Centerline Method (Sheet 2 of 2) FIGURE-4-5-5-991-001-B01

4-5-5

Page 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).

4-6-0

Page 1 Jun 01/13


**ON A/C A350-900

6.1 m (20 ft)

MAIN LANDING GEAR PATH 90 m (300 ft)

102 m (335 ft)

12.2 m (40 ft)

6.1 m (20 ft)

HOLDING POINT

190 m (625 ft)

TAXIWAY CENTERLINE

RUNWAY CENTERLINE 23 m (75 ft)

45 m (150 ft)

NOTE: COORDINATE WITH USING AIRCRAFT FOR SPECIFIC PLANNED OPERATING PROCEDURES. P_AC_040600_1_0010001_01_00

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

4-6-0

Page 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 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.

4-7-0

Page 1 Jun 01/13


**ON A/C A350-900

4.5 m (15 ft)

TODA

TAXIWAY CENTERLINE

4.5 m (15 ft)

ASDA

RUNWAY CENTERLINE

90° TURN ON RUNWAY ENTRY 45 m WIDE RUNWAY AIRCRAFT TYPE

MAX STEERING ANGLE

A350−900

72°

60 m WIDE RUNWAY

(STANDARD WIDTH)

(STANDARD WIDTH)

MINIMUM LINE−UP DISTANCE CORRECTION ON TODA ON ASDA 84 ft 25.7 m 178 ft 54.3 m


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

P_AC_040700_1_0010001_01_00

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

4-7-0

Page 2 Jun 01/13


**ON A/C A350-900

MINIMUM PAVEMENT WIDTH 4.5 m (15 ft)

TODA

4.5 m (15 ft)

4.5 m (15 ft)

ASDA

RUNWAY CENTERLINE

180° TURN ON RUNWAY TURNPAD

MAX AIRCRAFT STEERING TYPE ANGLE A350−900

72°

45 m WIDE RUNWAY

60 m WIDE RUNWAY

(STANDARD WIDTH)

(STANDARD WIDTH)

MINIMUM LINE−UP MINIMUM LINE−UP DISTANCE CORRECTION DISTANCE CORRECTION ON TODA ON ASDA ON TODA ON ASDA 122 ft 37.2 m 216 ft 65.9 m 117 ft 35.7 m 211 ft 64.4 m


REQUIRED MINIMUM PAVEMENT WIDTH

206 ft

62.9 m

P_AC_040700_1_0020001_01_00

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

4-7-0

Page 3 Jun 01/13


**ON A/C A350-900

4.5 m (15 ft)

> 4.5 m (15 ft)

TODA

ASDA

4.5 m (15 ft)

25°

RUNWAY CENTERLINE

180° TURN ON RUNWAY WIDTH 45 m WIDE RUNWAY AIRCRAFT TYPE

MAX STEERING ANGLE

A350−900

72°

60 m WIDE RUNWAY

(STANDARD WIDTH)

(STANDARD WIDTH)

MINIMUM LINE−UP DISTANCE CORRECTION ON TODA ON ASDA NOT POSSIBLE



P_AC_040700_1_0030001_01_00

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

4-7-0

Page 4 Jun 01/13


4-8-0

Aircraft Mooring

**ON A/C A350-900 Aircraft Mooring 1.

This section provides information on aircraft mooring.

4-8-0

Page 1 Jun 01/13


**ON A/C A350-900

SLING TOWING FITTING

A B

HOOK PIN

TOWING FITTING MOORING POINT

HOOK

A

MOVABLE HT PIN LIG F E OR EF B VE MO

RE

FLAG

B P_AC_040800_1_0010001_01_00

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

4-8-0

Page 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 typical turn round scenarios. These ramp layouts show typical arrangements only. Each operator will have its own specific requirements/regulations for the positioning and operation on the ramp. This table gives the symbols used on servicing diagrams. Ground Support Equipment AC AIR CONDITIONING UNIT AS AIR START UNIT BULK BULK TRAIN CAT CATERING TRUCK CB CONVEYOR BELT CLEAN CLEANING TRUCK FUEL FUEL HYDRANT DISPENSER or TANKER GPU GROUND POWER UNIT LDCL LOWER DECK CARGO LOADER LV LAVATORY VEHICLE PBB PASSENGER BOARDING BRIDGE PS PASSENGER STAIRS TOW TOW TRACTOR ULD ULD TRAIN WV POTABLE WATER VEHICLE

5-1-0

Page 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 (wheel chocks in position on landing gears).

5-1-1

Page 1 Jun 01/13


**ON A/C A350-900

TOW AS GPU

PS

CAT ULD AC LDCL

CAT

PS

FUEL

LDCL BULK

CLEAN

STAND SAFETY LINE

ULD

CB

WV

CAT

LV

FEET 0 10 20 30 40 50 60 0

4

8 12 16 METERS

20

P_AC_050101_1_0010001_01_01

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

5-1-1

Page 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 (wheel chocks in position on landing gears).

5-1-2

Page 1 Jun 01/13


**ON A/C A350-900

TOW AS GPU

PS

CAT ULD AC LDCL

CAT

PS

FUEL

LDCL BULK

CLEAN

STAND SAFETY LINE

ULD

CB

WV

CAT

LV

FEET 0 10 20 30 40 50 60 0

4

8 12 16 METERS

20

P_AC_050102_1_0010001_01_01

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

5-1-2

Page 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 activities during aircraft turn round. Actual times may vary due to each operator’s specific practice, resources, equipment and operating conditions.

2.

Assumptions used for full servicing turn round time chart A.

PASSENGER HANDLING 315 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 board Deplaning: - 158 pax at door L1, - 157 pax at door L2, - Deplaning rate = 25 pax/min per door, - Priority deplaning for premium passengers. Boarding: - 158 pax at door L1, - 157 pax at door L2, - Boarding rate = 15 pax/min per door, - Last Pax Seated Allowance (LPS) + headcounting = + 4 min.

B.

CARGO 2 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,

5-2-0

Page 1 Jun 01/13


-

Loading = 2.8 min/pallet.

C.

REFUELLING 81000 l (21398 US gal) at 50 psig (3.45 bars-rel). Dispenser positioning/removal = + 3 min.

D.

CLEANING Cleaning is performed in available time.

E.

CATERING 3 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.

5-2-0

Page 2 Jun 01/13


**ON A/C A350-900

TRT : 0

10

61

min

20

30

40

50

60

70

DEPLANING/BOARDING AT L1 DEPLANING/BOARDING AT L2 HEADCOUNTING CATERING AT R1 CATERING AT R2 CATERING AT R4 CLEANING

AVAILABLE TIME

CARGO FWD CC CARGO AFT CC BULK REFUELLING POTABLE WATER SERVICING TOILET SERVICING

ACTIVITY CRITICAL PATH POSITIONING/REMOVAL

P_AC_050200_1_0010001_01_01

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

5-2-0

Page 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 activities during aircraft turn round. Actual times may vary due to each operator’s specific practice, resources, equipment and operating conditions.

2.

Assumptions used for transit turn round time chart A.

PASSENGER HANDLING 315 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.

CARGO 1 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.

REFUELLING No refuelling.

5-3-0

Page 1 Jun 01/13


D.

CLEANING Cleaning is performed in available time.

E.

CATERING One catering truck for servicing the galleys as required.

F.

GROUND HANDLING / SERVICING. GENERAL Start 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.

5-3-0

Page 2 Jun 01/13


**ON A/C A350-900

TRT : 0

5

10

30 15

20

min 25

30

35

DEPLANING/BOARDING AT L2 HEADCOUNTING CATERING

AVAILABLE TIME

CLEANING

AVAILABLE TIME

CARGO AFT CC BULK

ACTIVITY POSITIONING/REMOVAL

P_AC_050300_1_0010002_01_01

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

5-3-0

Page 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.

5-4-0

Page 1 Jun 01/13


**ON A/C A350-900

10

1

4−5

2

8

15

16 17

11 12−14

18

15 10 4 5 1

11 13 14

6

2

3

7

17

12

8

16

18

11

6 9 15

1 − GROUNDING POINT NLG 2 − GROUND ELECTRICAL POWER CONNECTORS 3 − PRE CONDITIONNED AIR CONNECTORS 4 − VFG OIL SERVICING 5 − STARTER OIL SERVICING 6 − ENGINE OIL SERVICING 7 − AIR START UNIT CONNECTORS 8 − YELLOW HYDRAULIC GROUND CONNECTOR 9 − PRESSURE REFUEL CONNECTORS (RH WING)

10 − PRESSURE REFUEL CONNECTORS (LH WING) − OPTION 11 − GROUNDING POINT MLG 12 − REFUEL/DEFUEL CONTROL PANEL 13 − HYDRAULIC SERVICING PANEL 14 − GREEN HYDRAULIC GROUND CONNECTOR 15 − NACA AND OVERPRESSURE PANEL 16 − POTABLE WATER SERVICING PANEL 17 − WASTE WATER SERVICING PANEL 18 − APU OIL SERVICING P_AC_050400_1_0010001_01_01

Ground Service Connections layout FIGURE-5-4-0-991-001-A01

5-4-0

Page 2 Jun 01/13


5-4-1

Grounding Points

**ON A/C A350-900 Grounding Points 1.

Grounding (Earthing) Point Locations

AFT OF NOSE On Nose Landing Gear On Left Main Landing Gear Leg On Right Main Landing Gear Leg

4.42 m (14.5 ft.) 32.95 m (108.1 ft.) 32.95 m (108.1 ft.)

DISTANCE FROM AIRCRAFT CENTERLINE R SIDE L SIDE 0.07 m (0.23 ft.) 5.59 m (18.34 ft.) 5.59 m (18.34 ft.)

MEAN HEIGHT FROM GROUND 1.06 m (3.48 ft.) 1.55 m (5.09 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 the ramp 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.

5-4-1

Page 1 Jun 01/13


**ON A/C A350-900

A B

A

C

GROUNDING (EARTHING) POINT

B

C P_AC_050401_1_0010001_01_00

Ground Point NLG FIGURE-5-4-1-991-001-A01

5-4-1

Page 2 Jun 01/13


**ON A/C A350-900

B A A

A

C

LH SHOWN RH SYMMETRICAL

GROUNDING (EARTHING) POINT

B

C P_AC_050401_1_0020001_01_00

Ground Point MLG FIGURE-5-4-1-991-002-A01

5-4-1

Page 3 Jun 01/13


5-4-2

Hydraulic System

**ON A/C A350-900 Hydraulic System 1.

Ground Service Panel AFT OF NOSE

Green Hydraulic 36.37 m Ground (119.32 ft.) Access Door: 197 LB Yellow Hydraulic 30.35 m Ground (99.57 ft.) Access Door: 194 KB Hydraulic Reservoir 36.42 m Servicing (119.49 ft.) Access Door: 197 LB A.

DISTANCE FROM AIRCRAFT CENTERLINE R SIDE L SIDE 0.61 m (2.0 ft.)

1.51 m (4.95 ft.)

MEAN HEIGHT FROM GROUND 2.39 m (7.84 ft.)

2.24 m (7.35 ft.)

0.87 m (2.85 ft.)

2.51 m (8.23 ft.)

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

B.

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

5-4-2

Page 1 Jun 01/13


**ON A/C A350-900

HIGH PRESSURE CONNECTOR

LOW PRESSURE CONNECTOR

RESERVOIR FILLING CONNECTOR

P_AC_050402_1_0010001_01_00

Green Ground Service Panel FIGURE-5-4-2-991-001-A01

5-4-2

Page 2 Jun 01/13


**ON A/C A350-900

HIGH PRESSURE CONNECTOR

LOW PRESSURE CONNECTOR

P_AC_050402_1_0020001_01_00

Yellow Ground Service Panel FIGURE-5-4-2-991-002-A01

5-4-2

Page 3 Jun 01/13


5-4-3

Electrical System

**ON A/C A350-900 Electrical System 1.

Electrical System DISTANCE FROM AIRCRAFT CENTERLINE R SIDE L SIDE

AFT OF NOSE A/C External Power Access Door: 122 AR A.

6.63 m (21.75 ft.)

0.91 m (2.99 ft.)


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

5-4-3

Page 1 Jun 01/13


**ON A/C A350-900

122AR

A ELECTRICAL POWER RECEPTACLES

925VU

A FWD P_AC_050403_1_0010001_01_01

Electrical Service Panel FIGURE-5-4-3-991-001-A01

5-4-3

Page 2 Jun 01/13


**ON A/C A350-900 198VR

B 198QR

A Z190

C 198PR

SAFETY PIN

A

B

C

P_AC_050403_1_0030001_01_00

RAT FIGURE-5-4-3-991-003-A01

5-4-3

Page 3 Jun 01/13


5-4-4

Oxygen System

**ON A/C A350-900 Oxygen System 1.

Oxygen system Get 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 FWD cargo door.

5-4-4

Page 1 Jun 01/13


**ON A/C A350-900

FR20

A

FR30

B Z130

FR29

A FR28

CREW OXYGEN FILLING PORT CREW OXYGEN FILLING GAGE

B

P_AC_050404_1_0010001_01_00

Oxygen System FIGURE-5-4-4-991-001-A01

5-4-4

Page 2 Jun 01/13


5-4-5

Fuel System

**ON A/C A350-900 Fuel System 1.

Refuel/Defuel Control Panel and Connectors

AFT OF NOSE Refuel/Defuel Control Panel Access Door: 197 KB Refuel/Defuel Connectors, Left (Optional) Access Door: 523 EB Refuel/Defuel Connectors, Right Access Door: 623 EB A.

36.30 m (119.09 ft.)

DISTANCE FROM AIRCRAFT CENTERLINE R SIDE L SIDE

32.57 m (106.86 ft.)

2.18 m (7.15 ft.)

on centerline

32.57 m (106.86 ft.)

MEAN HEIGHT FROM GROUND

15.83 m (51.94 ft.)

15.83 m (51.94 ft.)

5.50 m (18.04 ft.)

5.50 m (18.04 ft.)

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 ACCESS

Overpressure Protector NACA Intake for Vent Tank

AFT OF NOSE 38.24 m (125.46 ft.) 38.69 m (126.94 ft.)

POSITION FROM AIRCRAFT CENTERLINE RH SIDE LH SIDE 22.33 m 22.33 m (73.26 ft.) (73.26 ft.) 23.07 m 23.07 m (75.69 ft.) (75.69 ft.)

5-4-5

MEAN HEIGHT FROM GROUND 6.13 m (20.11 ft.) 6.19 m (20.31 ft.)

Page 1 Jun 01/13


**ON A/C A350-900

P_AC_050405_1_0010001_01_00

Refuel/Defuel Control Panel FIGURE-5-4-5-991-001-A01

5-4-5

Page 2 Jun 01/13


**ON A/C A350-900

LH SIDE SHOWN RH SIDE SYMMETRICAL

REFUEL/DEFUEL COUPLINGS

P_AC_050405_1_0020002_01_00

Ground Service Connections FIGURE-5-4-5-991-002-B01

5-4-5

Page 3 Jun 01/13


**ON A/C A350-900

LH SIDE SHOWN RH SIDE SYMMETRICAL

NACA INTAKE NACA DUCT PANEL TANK OVER PRESSURE DISC OVER PRESSURE PANEL

P_AC_050405_1_0030001_01_00

NACA and Overpressure Locations FIGURE-5-4-5-991-003-A01

5-4-5

Page 4 Jun 01/13


5-4-6

Pneumatic System

**ON A/C A350-900 Pneumatic System 1.

Low Pressure Connectors AFT OF NOSE

Low Pressure Connector Access Door: 193 CB Low Pressure Connector Access Door: 194 CR A. 2.


MEAN HEIGHT FROM GROUND

23.58 m (77.36 ft.)

1.05 m (3.44 ft.)

2.59 m (8.5 ft.)

23.58 m (77.36 ft.)

1.87 m (6.14 ft.)

2.87 m (9.42 ft.)

Connectors : Two standard ISO 1034, 8 in.

High Pressure Connectors

AFT OF NOSE High Pressure Connectors Access door: 193 KB A.

26.81 m (87.96 ft.)



on centerline

Connectors: Two standard ISO 2026, 3 in.

5-4-6

Page 1 Jun 01/13


**ON A/C A350-900

LOW PRESSURE AIR CONNECTORS

P_AC_050406_1_0010001_01_00

Low Pressure Preconditioned Air FIGURE-5-4-6-991-001-A01

5-4-6

Page 2 Jun 01/13


**ON A/C A350-900

HIGH PRESSURE AIR CONNECTORS

P_AC_050406_1_0020001_01_00

High Pressure Preconditioned Air FIGURE-5-4-6-991-002-A01

5-4-6

Page 3 Jun 01/13


5-4-7


**ON A/C A350-900 Potable Water System 1.


AFT OF NOSE Potable Water Ground Service Access Door: 164 AR A.

50.2 m (164.7 ft.)



Technical Specifications Connectors : (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)

5-4-7

Page 1 Jun 01/13


**ON A/C A350-900

Z160

FR71

164AR

A

FR84 FR85 FR86

OVERFLOW NIPPLE

POTABLE WATER INDICATION PANEL

FILL

STOP

DRAIN

FILL/DRAIN PORT

A FWD P_AC_050407_1_0010001_01_00

Potable Water Ground Service Panel FIGURE-5-4-7-991-001-A01

5-4-7

Page 2 Jun 01/13


**ON A/C A350-900

A Z120 FR12 FR13

DRAIN PORT

A

P_AC_050407_1_0020001_01_00

Forward Drain panel FIGURE-5-4-7-991-002-A01

5-4-7

Page 3 Jun 01/13


**ON A/C A350-900

A Z170

FR93

POTABLE WATER TANK

FR89

FR86

A

P_AC_050407_1_0030001_01_00

Potable Water Tanks Location FIGURE-5-4-7-991-003-A01

5-4-7

Page 4 Jun 01/13


5-4-8

Oil System

**ON A/C A350-900 Oil System 1.

Engine Oil Servicing

AFT OF NOSE Oil Engine 1 Access Door: 415 BR Oil Engine 2 Access Door: 425 BR 2.

24.75 m (81.2 ft.) 24.68 m (80.97 ft.)

8.6 m (28.22 ft.) 12.29 m (40.32 ft.)


VFG Oil Servicing

AFT OF NOSE 2 VFG on Engine 1 24.32 m Fan Cowl: (79.79 ft.) 415 AL 2 VFG on Engine 2 24.34 m Fan Cowl: (79.86 ft.) 425 AL 3.


DISTANCE FROM AIRCRAFT CENTERLINE R SIDE L SIDE 11.02 m (36.15 ft.) 9.86 m (32.35 ft.)


Starter Oil Servicing

AFT OF NOSE Starter Engine 1 Fan Cowl: 415 AL Starter Engine 2 Fan Cowl: 425 AL


24.6 m (80.71 ft.) 24.6 m (80.71 ft.)

10.57 m (34.68 ft.) 10.31 m (33.83 ft.)


5-4-8

Page 1 Jun 01/13


4.

APU Oil Servicing

AFT OF NOSE APU Access Door 316 BR

62.52 m (205.12 ft.)



5-4-8

Page 2 Jun 01/13


**ON A/C A350-900

OIL TANK OIL LEVEL SIGHT GLASS OIL FILLER CAP

P_AC_050408_1_0010001_01_00

Engine Oil Servicing FIGURE-5-4-8-991-001-A01

5-4-8

Page 3 Jun 01/13


**ON A/C A350-900

FILTER BOWL

DISCONNECT RESET HANDLE

PRESSURE FILL DRAIN

SIGHT GLASS

OVERFLOW/STANDPIPE

TYPICAL

P_AC_050408_1_0020001_01_00

VFG Oil Servicing FIGURE-5-4-8-991-002-A01

5-4-8

Page 4 Jun 01/13


**ON A/C A350-900

A

PRESSURE FILL PORT

OIL DRAIN PLUG PRESSURE SPILL PORT

A

MAGNETIC CHIP DETECTOR

P_AC_050408_1_0030001_01_01

Starter Oil Servicing FIGURE-5-4-8-991-003-A01

5-4-8

Page 5 Jun 01/13


**ON A/C A350-900

FILL CAP

SIGHT GLASS

P_AC_050408_1_0040001_01_00

APU Oil Servicing FIGURE-5-4-8-991-004-A01

5-4-8

Page 6 Jun 01/13


5-4-9

Vacuum Toilet System

**ON A/C A350-900 Vacuum Toilet System 1.

Waste Water System

AFT OF NOSE Waste Water Ground Service Access Door: 171 AL A.

52.21 m (171.29 ft.)



on centerline

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)

5-4-9

Page 1 Jun 01/13


**ON A/C A350-900

WASTE DRAIN CONNECTION

FILL AND RINSE CONNECTION

CONTROL LEVER

P_AC_050409_1_0010001_01_00

Ground Service Panel FIGURE-5-4-9-991-001-A01

5-4-9

Page 2 Jun 01/13


**ON A/C A350-900

A Z170

FR93

FR89

FR86

WASTE TANK

A

P_AC_050409_1_0020001_01_00

Waste Tanks Location FIGURE-5-4-9-991-002-A01

5-4-9

Page 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 cabin temperature at 27 deg.C (80.6 deg.F) after boarding (Section 5.7 - steady state), and provides the time needed to cool down or heat up the aircraft cabin to the required temperature (Section 5.6 dynamic cases with aircraft empty). ABBREVIATION

A/C AHM GC GSE IFE LP OAT PCA A.

DEFINITION Aircraft Aircraft Handling Manual Ground Connection Ground Service Equipment In-Flight Entertainment Low Pressure Outside Air Temperature Preconditioned Air 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 by itself to ensure the performance (outlet temperature and flow rate combinations are the requirements needed for ground power). An example of cooling capacity calculation is given in Section 5.7.

B.

The air flow rates and temperature requirements for the GSE are given for the A/C in the configuration ”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 the Airbus document ”Subfreezing PCA Carts -- Compliance Document for Suppliers” (contact Airbus to obtain this document) defining all the requirements to which Subfreezing PreConditioning Air equipment needs to comply to allow its use on Airbus aircraft. These requirements come in addition to the functional specifications included in the IATA AHM997.

2.

Ground Pneumatic Power Requirements - Heating This 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 - Cooling This 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.

5-6-0

Page 1 Jun 01/13

AIR FLOW AT GC (kg/s) 2.5

2.7

2.9

3.1

3.3

3.5

3.7

3.9

4.1

4.3

4.5

5-6-0 35

40

45

50

55

TIME TO HEAT CABIN TO +21°C (+69.8°F) ON GROUND (min)

60

65

PU1 "ISA −38°C (−36.4°F )" PU2 "ISA −45°C (−49°F )"

PU1: OAT ISA −38°C (−36.4°F); GC OUTLET +70°C (+158°F); A/C EMPTY; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON PU2: OAT ISA −45°C (−49°F); GC OUTLET +70°C (+158°F); A/C EMPTY; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON

PULL UP CASES:

30

MAX AIR FLOW

PULL UP PERFORMANCE (+70°C (+158°F) GC OUTLET)

@A350-900


**ON A/C A350-900

P_AC_050600_1_0010001_01_02

Ground Pneumatic Power Requirements Heating (Sheet 1 of 2) FIGURE-5-6-0-991-001-A01

Page 2 Jun 01/13

AIR FLOW AT GC (kg/s)

2.5

2.7

2.9

3.1

3.3

3.5

3.7

3.9

4.1

4.3

4.5

20

5-6-0

30 40

50

60

70

TIME TO COOL CABIN TO +27°C (+80.6°F) ON GROUND (min)

PD1 "ISA +23°C (+73.4°F) / GC OUTLET +2°C (+35.6°F)" PD2 "ISA +23°C (+73.4°F) / GC OUTLET −10°C (+14°F)" PD3 "ISA +23°C (+73.4°F) / GC OUTLET −20°C (−4°F)"

PD1: OAT ISA +23°C (+73.4°F); GC OUTLET + 2°C (+35.6°F); A/C EMPTY; IFE OFF; SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON PD2: OAT ISA +23°C (+73.4°F); GC OUTLET −10°C (+14°F); A/C EMPTY; IFE OFF; SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON PD3: OAT ISA +23°C (+73.4°F); GC OUTLET −20°C (−4°F); A/C EMPTY; IFE OFF; SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON

PULL DOWN CASES:

10

MAX AIR FLOW

PULL DOWN PERFORMANCE

80

90

@A350-900


**ON A/C A350-900

P_AC_050600_1_0010001_02_01

Ground Pneumatic Power Requirements Cooling (Sheet 2 of 2) FIGURE-5-6-0-991-001-A01

Page 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 flow rate and temperature combinations needed to maintain the cabin temperature at 27 deg.C (80.6 deg.F). These settings are not intended to be used for operation (they don’t substitute to the settings given in 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 the PCA settings to maintain the cabin temperature below 27 deg.C (80.6 deg.F) during boarding (therefore it is not a steady state).

5-7-0

Page 1 Jun 01/13

5-7-0 −10

C2

C1

−5

C3

0

5 10

MAX AIR FLOW

15 20 25 30 GC OUTLET TEMPERATURE (°C)

35

40

H1

45

H2 50

OAT ISA−38°C (−36.4°F); A/C EMPTY; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON OAT ISA−45°C (−49°F); A/C EMPTY; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON OAT ISA−55°C (−67°F); A/C EMPTY; IFE OFF; NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON

OAT ISA+30°C (86°F); 446 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON OAT ISA+23°C (73.4°F); 446 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON OAT ISA; 446 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON

1,8

2,3

2,8

3,3

3,8

4,3

COOLING/HEATING PERFORMANCE

EXAMPLE: COOLING CAPACITY CALCULATION: FOR THE CONDITIONS C3, THE COOLING CAPACITY OF 4.25 kg/s x 1kJ/(kg.°C) X (27−2) = 106 kW IS NEEDED TO MAINTAIN THE CABIN TEMPERATURE BELOW 27°C (86°F) (4.25 kg/s AT GC OUTLET OF 2°C (35.6°F)).

AIRFLOW FROM GC (kg/s)

4,8

H3 55

@A350-900


**ON A/C A350-900

P_AC_050700_1_0010001_01_01

Preconditioned Airflow Requirements FIGURE-5-7-0-991-001-A01

Page 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 idle thrust, 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 rear of the NLG available). The first part of this section shows the chart to determine the draw bar pull and tow tractor mass requirements 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 protect the 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)..

5-8-0

Page 1 Jun 01/13


**ON A/C A350-900

DRAWBAR PULL ( x 1000 kg ) 25

17.0

15

10

=0 .57

=0

.8

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

DR YC ON CR WE ETE TC ON CR ET E

20

A/C WEIGHT ( x 1000 kg )

280

2% SLOPE

1 ENGINE ON

250

205

.2

=0

180 155

W

D AR

255 230

O SN

130

H

5

ICE

= 0.05

29.8

0 0

10

20

30

40

50

60

70

80

TOTAL TRACTION WHEEL LOAD ( x 1000 kg )

0

1

2

No. OF ENGINES AT IDLE

0

0.5

1.0

1.5

2.0

SLOPE ( % )

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).

P_AC_050800_1_0010001_01_00

Towing Requirements FIGURE-5-8-0-991-001-A01

5-8-0

Page 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 heights up to approximately 17 m (56 ft.).

2.

De-Icing Wing Top Surface (Both Sides)

AIRCRAFT TYPE

354 m2 (3810 ft.2)

A350--900

AIRCRAFT TYPE

A350--900

Wingtip Devices HTP Top Surface (Both Inside and (Both Sides) (Outside Surfaces) (Both Sides) 25 m2 69 m2 (269 ft.2) (743 ft.2)

Fuselage Top Surface (Top Third - 120? Arc) 357 m2 (3843 ft.2)

VTP (Both Sides)

102 m2 (1098 ft.2)

Nacelle and Pylon Total De-Iced Area (Top Third - 120? Arc) (All Engines) 56 m2 962 m2 (603 ft.2) (10355 ft.2)

NOTE : Dimensions are approximate 3.

External Cleaning Wing Top Surface (Both Sides)

AIRCRAFT TYPE

A350--900

354 m2 (3810 ft.2)

AIRCRAFT TYPE A350--900

Wing Lower Wingtip Devices HTP Top Surface (Both Inside Surface (Including Flap and (Both Sides) Track Fairing) (Outside (Both Sides) Surfaces) (Both Sides) 384 m2 25 m2 69 m2 (4133 ft.2) (269 ft.2) (743 ft.2)

VTP (Both Sides) 102 m2 (1098 ft.2)

Fuselage and Belly Fairing 1073 m2 (11550 ft.2)

HTP Lower Surface (Both Sides)

69 m2 (743 ft.2)

Nacelle and Pylon Total Cleaned Area (All Engines) 166 m2 2242 m2 (1787 ft.2) (24133 ft.2)

NOTE : Dimensions are approximate

5-9-0

Page 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.

6-4-0

Page 1 Jun 01/13


**ON A/C A350-900

[m]

[ft] 40

15 m/s 10

46 m/s 30.5 m/s

61 m/s

30

20

FD

5 10

0

[m] 0

5

10

15

0

20

[ft] 0

10

20

30

40

50

60

[m]

[ft] 40

93°C

10

427°C

30

315.5°C

FD

204°C

20

149°C

5

260°C

10

0

[m] 0

5

10

15

0

20

[ft] 0

10

20

30

40

50

60

P_AC_060400_1_0010001_01_00

APU Exhaust Velocities and Temperatures FIGURE-6-4-0-991-001-A01

6-4-0

Page 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 shown with 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 imposed on the MLG struts. Landing Gear Footprint. Section 7-2-0 , presents basic data on the landing gear footprint configuration, maximum ramp weights and tire sizes and pressures. Maximum Pavement Loads. Section 7-3-0, shows maximum vertical and horizontal pavement loads for certain critical conditions at 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 rest on 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 CBR Design Curves”, dated June 1977 and as modified according to the methods described in ICAO Aerodrome Design Manual, Part 3.Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCN Method), and utilizing the alpha factors approved by ICAO in October 2007. The report was prepared by the U.S. Army Corps Engineers Waterways Experiment Station, Soils and Pavement Laboratory, Vicksburg, Mississippi”. The line showing 10 000 coverages is used to calculate Aircraft Classification Number (ACN). Flexible Pavement Requirements - LCN Conversion Method.

7-1-0

Page 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 program based 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 the Westergaard Equation. This is in general accordance with the procedures outlined in the Portland Cement Association publications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for Airport Pavement 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 values of E and µ) - were developed from a computer program based on data in International Civil Aviation Organisation (ICAO) document 7920-AN/865/2, Aerodrome manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965. The rigid pavement charts in Section 7-8-0 show LCN against ESWL, and ESWL against radius of relative 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 and µ). The rigid pavement charts show LCN in Section 7-8-2 against ESWL and ESWL against radius of relative 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 ICAO Annex 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 a standardized 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 Classification Number. An aircraft having an ACN equal to or less than the PCN can operate without restriction on the pavement. Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.

7-1-0

Page 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 for flexible pavements to calculate ACN values. The Airport Authority must decide on the method of pavement analysis and the results of their evaluation shown as follows: PCN SUBGRADE TIRE PRESSURE EVALUATION PAVEMENT TYPE CATEGORY CATEGORY METHOD R - Rigid A - High W - No Limit T - Technical F - Flexible B - Medium U - Using Aircraft X - To 1.5 Mpa (217 psi) 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 )

7-1-0

Page 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 tire sizes and pressures.

7-2-0

Page 1 Jun 01/13


**ON A/C A350-900

MAXIMUM RAMP WEIGHT

268 900 kg (592 825 lb)

PERCENTAGE OF WEIGHT ON MAIN GEAR GROUP

SEE SECTION 7−4−0

NOSE GEAR TIRE SIZE NOSE GEAR TIRE PRESSURE MAIN GEAR TIRE SIZE MAIN GEAR TIRE PRESSURE

1050x395R16 28PR 12.2 bar (177 psi) 1400x530R23 42PR 16.6 bar (241 psi)

28.665 m (94.050 ft) 10.600 m (34.777 ft)

0.748 m (2.454 ft)

1.735 m (5.692 ft)

2.040 m (6.693 ft)

P_AC_070200_1_0010001_01_01

Landing Gear Footprint FIGURE-7-2-0-991-001-A01

7-2-0

Page 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 at the tire-ground interfaces.

7-3-0

Page 1 Jun 01/13

−900

MODEL

1

2 VNG

4

V

lb

kg

lb

7-3-0 (NG)

92 125

41 790

DECELERATION kg lb

222 150

268 900 kg 268 900 kg

MRW = MRW =

(1) (2)

NOTE: ALL LOADS CALCULATED USING AIRCRAFT MAXIMUM RAMP WEIGHT

AFT CG = 33 % MAC AT A/C WEIGHT=268 900 kg

FWD CG = 25.5 % MAC AT A/C WEIGHT=268 900 kg

MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING

H

100 770

COEFFICIENT = 0.8 kg lb

MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST FORWARD CG

125 960

kg

STEADY BRAKING AT INSTANTANEOUS BRAKING @ 10 ft/s²

6 H (PER STRUT)

V MAXIMUM VERTICAL MAIN GEAR GROUND LOAD AT MOST AFT CG (MG)

V

lb

38 780 277 700

kg

STATIC LOAD AT MAX AFT C.G. (2)

5 VMG (PER STRUT)

(MG)

STATIC LOAD STATIC BRAKING AT MOST FWD @ 10 ft/s² C.G. (1) DECELERATION

3

592 825 268 900 51 575 23 400 85 500

WEIGHT lb kg

MAXIMUM RAMP

V (NG)

H

@A350-900


**ON A/C A350-900

P_AC_070300_1_0010001_01_01

Maximum Pavement Loads FIGURE-7-3-0-991-001-A01

Page 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).

7-4-0

Page 1 Jun 01/13


**ON A/C A350-900

PERCENTAGE MAC 5

10

15

20

30

25

35

40

45

50

270

270

265

265

260

260 255

WEIGHT ON MAIN LANDING GEAR (x 1000 kg)

250

CG FOR ACN CALCULATION

MTOW − 268 000 kg

250

245

245

240

240

235

235

230

230

225

225

220

220

215

215

210

210

205

205

200

200

MLW − 205 000 kg

195

195

190

190

185

185

180

180

175

175 170

170 MZFW − 192 000 kg

165

165

160

160

155

155

150

150

145

145

TAKE OFF

140

140

LANDING

135

135

130

130

125

125

120 84

86

88

90

92

AIRCRAFT GROSS WEIGHT (x 1000 kg)

255

94

96

98

120 100

PERCENTAGE OF WEIGHT ON MAIN GEAR P_AC_070400_1_0010001_01_00

Landing Gear Loading on Pavement MTOW 268 000 kg FIGURE-7-4-0-991-001-A01

7-4-0

Page 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 annual departure 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.).

7-5-0

Page 1 Jun 01/13


**ON A/C A350-900

SUBGRADE STRENGTH − CBR 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) 100 000 kg (220 450 lb) 90 000 kg (198 425 lb) 80 000 kg (176 375 lb)

MAXIMUM POSSIBLE MAIN GEAR LOAD AT MAXIMUM RAMP WEIGHT AND AFT CG 10 000 COVERAGES USED FOR ACN CALCULATIONS ALPHA FACTOR = 0.8 ANNUAL DEPARTURES* 1 200 3 000 6 000 15 000 25 000 *20 YEAR PAVEMENT LIFE

3

10

6

15

20

30

40

60

80

[in] 10

15

20

30

40 [cm]

60

80 100 120 150 180

FLEXIBLE PAVEMENT THICKNESS 1400x530R23 42PR TIRES TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)

P_AC_070500_1_0010001_01_01

Flexible Pavement Requirements MTOW 268 000 kg FIGURE-7-5-0-991-001-A01

7-5-0

Page 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 the pavement 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 flexible pavement. However, the pavement thickness for a particular runway are not frequently published in the standard airport information sources (Jeppesen, AERAD, DOD, etc.). Therefore it is common practice to use a standard thickness (20 inches) when determining the LCN and the ESWL of the aircraft. If the LCN for an intermediate weight between MRW and the empty weight of the aircraft is required or if the real thickness is known, refer to charts in FIGURE 7-6-0-991-001-A. FLEXIBLE PAVEMENT TIRE LOAD ON AIRCRAFT PRESSURE ESWL ONE MLG WEIGHT LCN TYPE (Mpa) LEG (%) x 1000 kg x 1000 lb h= 510 mm (20 in.) 268900 kg A350--900 46.8 31 69.4 116 (592824 lb) 1.66 142000 kg A350--900 46.8 17 36.7 68 (313057 lb)

7-6-0

Page 1 Jun 01/13

EQUIVALENT SINGLE WHEEL LOAD (1000 lb)

7-6-0 40

50

60

70

80

90

100

110

120

130

140

150

160

10

750

1000

30

40

50 60

1500

80

100

2000 2500

70

100

120

150

200 230 LOAD CLASSIFICATION NUMBER (LCN)

80

20

30

40

50

60

70

1400 x 530R23 42PR TIRES TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)

NOTE: EQUIVALENT SINGLE WHEEL LOADS ARE DERIVED BY METHODS SHOWN IN ICAO AERODROME MANUAL PART 2 PAR 4.1.3 SECOND EDITION 1965

FLEXIBLE PAVEMENT THICKNESS (in)

20

MAXIMUM POSSIBLE MAIN GEAR LOAD AT MAXIMUM RAMP WEIGHT AND AFT CG


500

FLEXIBLE PAVEMENT THICKNESS (mm)

@A350-900


**ON A/C A350-900

P_AC_070600_1_0010001_01_00

Flexible Pavement Requirements - LCN MTOW 268 000 kg FIGURE-7-6-0-991-001-A01

Page 2 Jun 01/13

EQUIVALENT SINGLE WHEEL LOAD (1000 kg)


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 Cement Association) design method. They are calculated with the PCA design method. To find a rigid pavement thickness, you must know the Subgrade Modulus (K), the permitted working 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.).

7-7-0

Page 1 Jun 01/13


**ON A/C A350-900 1400x530R23 42PR TIRES TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi) 1000

15

38

70

MAXIMUM POSSIBLE MAIN GEAR LOAD AT MAXIMUM RAMP WEIGHT AND AFT CG 36

14

65 900

K = 20 MN/m³ 60

K = 40 MN/m³

34

K = 80 MN/m³ 13

K = 150 MN/m³

800 55

50

700

30 45 11

600 (lb/in²)

28

26 10

500

9

400

40

35

(kg/cm²) ALLOWABLE WORKING STRESS

12

(in)

RIGID PAVEMENT THICKNESS (cm)

32

24 30

22

20

18

8


7

25 300 20

200

NOTES: THE VALUES OBTAINED BY USING THE MAXIMUM LOAD REFERENCE LINE AND ANY VALUES FOR K ARE EXACT. FOR LOADS LESS THAN MAXIMUM, THE CURVES ARE EXACT FOR K = 80 MN/m³ BUT DEVIATE SLIGHTLY FOR ANY OTHER VALUES OF K

15

REFERENCE: "DESIGN OF CONCRETE AIRPORT PAVEMENTS" AND "COMPUTER PROGRAM FOR AIRPORT PAVEMENT DESIGN − PROGRAM PDILB" PORTLAND CEMENT ASSOCIATION

P_AC_070700_1_0010001_01_00

Rigid Pavement Requirements MTOW 268 000 kg FIGURE-7-7-0-991-001-A01

7-7-0

Page 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 the rigid 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 published in the standard airport information sources (Jeppesen, AERAD, DOD, etc.). Therefore it is common practice to use a standard radius of relative stiffness (30 inches) when determining the LCN and the ESWL of the aircraft. If the LCN for an intermediate weight between maximum ramp weight and the empty weight of the aircraft is required or if the real thickness is known, refer to charts FIGURE 7-8-0-991-001-A. AIRCRAFT TYPE

A350--900 A350--900

WEIGHT

268900 kg (592824 lb) 142000 kg (313057 lb)

LOAD ON ONE MLG LEG (%)

TIRE PRESSURE (Mpa)

46.8

RIGID PAVEMENT ESWL x 1000 kg x 1000 lb L= 760 mm (30 in.)

LCN

28

62

107

15

33

59

1.66 46.8

7-8-0

Page 1 Jun 01/13

1250 1500

2500

50

60

70

19

24

29

34

39

44

49

54

7-8-0

NOTE: EQUIVALENT SINGLE WHEEL LOADS ARE DERIVED BY METHODS SHOWN IN ICAO AERODROME MANUAL PART 2 PAR 4.1.3 SECOND EDITION 1965

5 80 90 100 120 150 190 LOAD CLASSIFICATION NUMBER (LCN) 40


20

30 40 50 60 70 80 90 100 RADIUS OF RELATIVE STIFFNESS (inches)

2000

14 20

1000

MAXIMUM POSSIBLE MAIN GEAR LOAD AT MAXIMUM RAMP WEIGHT AND AFT CG

750

1400 x 530R23 42PR TIRES TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)

30

40

50

60

70

80

90

100

110

120

RADIUS OF RELATIVE STIFFNESS (mm)

@A350-900


**ON A/C A350-900

P_AC_070800_1_0010001_01_00

Rigid Pavement Requirements - LCN MTOW 268 000 kg FIGURE-7-8-0-991-001-A01

Page 2 Jun 01/13

EQUIVALENT SINGLE WHEEL LOAD (1000 kg)

EQUIVALENT SINGLE WHEEL LOAD (1000 lb)


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.

7-8-1

Page 1 Jun 01/13


**ON A/C A350-900 RADIUS OF RELATIVE STIFFNESS (L) VALUES IN INCHES

L= 4

WHERE

Ed 12 (1 −

= 24.1652 4

)k

d k

E = YOUNG’S MODULUS = 4 x 10 psi k = SUBGRADE MODULUS, lb/in d = RIGID PAVEMENT THICKNESS, (in) = POISSON’S RATIO = 0.15

d

k=75

k=100

k=150

k=200

k=250

k=300

k=350

k=400

k=550

6.0 6.5 7.0 7.5

31.48 33.43 35.34 37.22

29.30 31.11 32.89 34.63

26.47 28.11 29.72 31.29

24.63 26.16 27.65 29.12

23.30 24.74 26.15 27.54

22.26 23.64 24.99 26.32

21.42 22.74 24.04 25.32

20.72 22.00 23.25 24.49

19.13 20.31 21.47 22.61

8.0 8.5 9.0 9.5

39.06 40.88 42.67 44.43

36.35 38.04 39.71 41.35

32.85 34.37 35.88 37.36

30.57 31.99 33.39 34.77

28.91 30.25 31.58 32.89

27.62 28.91 30.17 31.42

26.58 27.81 29.03 30.23

25.70 26.90 28.08 29.24

23.74 24.84 25.93 27.00

10.0 10.5 11.0 11.5

46.18 47.90 49.60 51.28

42.97 44.57 46.16 47.72

38.83 40.28 41.71 43.12

36.14 37.48 38.81 40.13

34.17 35.45 36.71 37.95

32.65 33.87 35.07 36.26

31.42 32.59 33.75 34.89

30.39 31.52 32.64 33.74

28.06 29.11 30.14 31.16

12.0 12.5 13.0 13.5

52.94 54.59 56.22 57.83

49.27 50.80 52.32 53.82

44.52 45.90 47.27 48.63

41.43 42.72 43.99 45.26

39.18 40.40 41.61 42.80

37.44 38.60 39.75 40.89

36.02 37.14 38.25 39.35

34.84 35.92 36.99 38.06

32.17 33.17 34.16 35.14

14.0 14.5 15.0 15.5

59.43 61.02 62.59 64.15

55.31 56.78 58.25 59.70

49.98 51.31 52.63 53.94

46.51 47.75 48.98 50.20

43.98 45.16 46.32 47.47

42.02 43.15 44.26 45.36

40.44 41.51 42.58 43.64

39.11 40.15 41.19 42.21

36.12 37.08 38.03 38.98

16.0 16.5 17.0 17.5

65.69 67.23 68.75 70.26

61.13 62.56 63.98 65.38

55.24 56.53 57.81 59.08

51.41 52.61 53.80 54.98

48.62 49.75 50.88 52.00

46.45 47.54 48.61 49.68

44.70 45.74 46.77 47.80

43.23 44.24 45.24 46.23

39.92 40.85 41.78 42.70

18.0 19.0 20.0 21.0

71.76 74.73 77.66 80.55

66.78 69.54 72.27 74.96

60.34 62.84 65.30 67.74

56.15 58.48 60.77 63.04

53.11 55.31 57.47 59.62

50.74 52.84 54.91 56.96

48.82 50.84 52.84 54.81

47.22 49.17 51.10 53.01

43.61 45.41 47.19 48.95

22.0 23.0 24.0 25.0

83.41 86.24 89.04 91.81

77.63 80.26 82.86 85.44

70.14 72.52 74.87 77.20

65.28 67.49 69.68 71.84

61.73 63.83 65.90 67.95

58.98 60.98 62.96 64.92

56.75 58.68 60.58 62.46

54.89 56.75 58.59 60.41

50.69 52.41 54.11 55.79

REFERENCE: PORTLAND CEMENT ASSOCIATION P_AC_070801_1_0010001_01_00

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

7-8-1

Page 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 multiplied by 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.

7-8-2

Page 1 Jun 01/13


**ON A/C A350-900

EFFECT OF E ON L VALUES 1.10 1.05

E FACTOR

1.00 0.95 0.90 0.85 0.80

0

1

2

3

4

5

E, YOUNG’S MODULUS (10 psi)

EFFECT OF

ON L VALUES

1.015

FACTOR

1.010

1.005

1.000

0.995 0.00

0.05

0.10

0.15

0.20

0.25

, POISSON’S RATIO

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

P_AC_070802_1_0010002_01_00

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

7-8-2

Page 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 an aircraft 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 and the subgrade strength. NOTE : An aircraft with an ACN equal to or less than the reported PCN can operate on that pavement, subject to any limitation on the tire pressure (Ref: ICAO Aerodrome Design Manual 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 Table The 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 intermediate weight between maximum ramp weight and the empty weight of the aircraft is required, refer to chart FIGURE 7-9-0-991-001-A. ACN FOR FLEXIBLE PAVEMENT SUBGRADES TIRE LOAD ON CBR AIRCRAFT WEIGHT ONE MLG PRESSURE High Medium Low Ultral-low TYPE (Mpa) LEG (%) 15 10 6 3 268900 kg (592824 A350--900 46.8 66 70 80 110 lb) 1.66 142000 kg (313057 A350--900 46.8 31 32 34 41 lb)

7-9-0

Page 1 Jun 01/13

7-9-0 20 120

30

40

50

60

70

80

90

100

110

120

280

340

370

140

160

SUBGRADE STRENGTH D − CBR 3 (ULTRA LOW) C − CBR 6 (LOW) B − CBR 10 (MEDIUM) A − CBR 15 (HIGH)

ALPHA FACTOR = 0.8

310

200 ( x1000 kg)

430

460

AIRCRAFT GROSS WEIGHT

180

400

( x1000 lb)

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

220

490

240

520

550

260

580

ACN WAS DETERMINED AS REFERENCED IN ICAO AERODROME DESIGN MANUAL PART 3 CHAPTER 1. SECOND EDITION 1983. CG USED FOR ACN CALCULATIONS: 33% MAC SEE SECTION 7−4−0

280

610

@A350-900


**ON A/C A350-900

P_AC_070900_1_0010001_01_00

Aircraft Classification Number - Flexible Pavement MTOW 268 000 kg FIGURE-7-9-0-991-001-A01

Page 2 Jun 01/13

AIRCRAFT CLASSIFICATION NUMBER (ACN)


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 an aircraft 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 the subgrade strength. NOTE :

An aircraft with an ACN equal to or less than the reported PCN can operate on that pavement, subject to any limitation on the tire pressure. (Ref: ICAO Aerodrome Design Manual 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 Table The 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 intermediate weight between maximum ramp weight and the empty weight of the aircraft is required, refer to chart FIGURE 7-9-1-991-001-A. ACN FOR RIGID PAVEMENT SUBGRADES TIRE LOAD ON MN/m3 AIRCRAFT WEIGHT ONE MLG PRESSURE TYPE High Medium Low Ultral-low (Mpa) LEG (%) 150 80 40 20 268900 kg (592824 A350--900 46.8 64 83 96 71 lb) 1.66 142000 kg (313057 A350--900 46.8 32 33 36 41 lb)

7-9-1

Page 1 Jun 01/13

7-9-1 20 120

30

40

50

60

70

80

90

100

110

120

280

340

370

140

160

A − K = 150 MN/m³ (HIGH)

B − K = 80 MN/m³ (MEDIUM)

C − K = 40 MN/m³ (LOW)

D − K = 20 MN/m³(ULTRA LOW)

SUBGRADE STRENGTH

310

200 ( x1000 kg)

430

460

AIRCRAFT GROSS WEIGHT

180

400

( x1000 lb)

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

220

490

240

520

550

260

580

ACN WAS DETERMINED AS REFERENCED IN ICAO AERODROME DESIGN MANUAL PART 3 CHAPTER 1. SECOND EDITION 1983. CG USED FOR ACN CALCULATIONS: 33% MAC SEE SECTION 7−4−0

280

610

@A350-900


**ON A/C A350-900

P_AC_070901_1_0010001_01_00

Aircraft Classification Number - Rigid Pavement MTOW 268 000 kg FIGURE-7-9-1-991-001-A01

Page 2 Jun 01/13

AIRCRAFT CLASSIFICATION NUMBER (ACN)


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.

8-0-0

Page 1 Jun 01/13


**ON A/C A350-900 0

0

10

4

20 FEET 30 40

8 12 METERS

50

16

60 20 0 0

10 4

20

FEET 30 40 8 12 METERS

50 16

60 20

NOTE: WHEN PRINTING THIS DRAWING, MAKE SURE TO ADJUST FOR PROPER SCALING P_AC_080000_1_0010001_01_00

Scaled Drawings FIGURE-8-0-0-991-001-A01

8-0-0

Page 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 Fighting Charts poster available for download on AIRBUSWorld and the Airbus website.

10-0-0

Page 1 Jun 01/13


JUNE 2013 : REFERENCE

THIS CHART GIVES THE GENERAL LAYOUT OF THE A350−900 STANDARD VERSION.

**ON A/C A350-900

P_AC_100000_1_0010001_01_01

Front Page FIGURE-10-0-0-991-001-A01

10-0-0

Page 2 Jun 01/13


**ON A/C A350-900

P_AC_100000_1_0030001_01_01

Highly Flammable and Hazardous Materials and Components FIGURE-10-0-0-991-003-A01

10-0-0

Page 3 Jun 01/13

10-0-0

EMERGENCY EXIT

ACCESS DOOR

NOTE: THE CREW REST COMPARTMENT INSTALLATION IS OPTIONAL AND RELATED TO AIRCRAFT CONFIGURATION.

ACCESS DOOR

EMERGENCY EXIT

FLIGHT CREW REST COMPARTMENT

CABIN CREW REST COMPARTMENT

@A350-900


**ON A/C A350-900

P_AC_100000_1_0040001_01_01

Crew Rest Compartments Location FIGURE-10-0-0-991-004-A01

Page 4 Jun 01/13


**ON A/C A350-900

P_AC_100000_1_0050001_01_00

Wheel/Brake Overheat Wheel Safety Area (Sheet 1 of 2) FIGURE-10-0-0-991-005-A01

10-0-0

Page 5 Jun 01/13


**ON A/C A350-900

P_AC_100000_1_0050001_02_00

Wheel/Brake Overheat Recommendations (Sheet 2 of 2) FIGURE-10-0-0-991-005-A01

10-0-0

Page 6 Jun 01/13


TITANIUM

QUARTZ, GLASS

CFRP SANDWICH

CFRP MONOLITHIC

COMPOSITE MATERIALS

ALU ALLOY

**ON A/C A350-900

P_AC_100000_1_0060001_01_00

Composite Materials Location FIGURE-10-0-0-991-006-A01

10-0-0

Page 7 Jun 01/13


NOSE LANDING GEAR

MAIN LANDING GEAR

TYPICAL INSTALLATION

**ON A/C A350-900

P_AC_100000_1_0070001_01_00

Ground Lock Safety Devices FIGURE-10-0-0-991-007-A01

10-0-0

Page 8 Jun 01/13

10-0-0

CABIN DUAL−LANE SLIDE/RAFT 9.38 m (30.77 ft)

CABIN SINGLE−LANE SLIDE/RAFT 10.25 m (33.63 ft)

EMERGENCY DESCENT THROUGH THE ESCAPE HATCH WITH THE ESCAPE ROPE NOTE: DIMENSIONS ARE APPROXIMATE

0

3

6

9

12

15



COCKPIT ESCAPE ROPE

@A350-900


**ON A/C A350-900

P_AC_100000_1_0080001_01_01

Emergency Evacuation Devices FIGURE-10-0-0-991-008-A01

Page 9 Jun 01/13

10-0-0

MECHANICAL DOOR−LOCKING INDICATORS

TO OPEN: 1 − MAKE SURE THAT RESIDUAL CABIN−PRESSURE WARNING LIGHTS DOES NOT FLASH. 2 − PUSH FLAP TO GRASP HANDLE. 3 − LIFT HANDLE FULLY UP TO HORIZONTAL POSITION (GREEN LINE). 4 − PULL THE DOOR OUT AND MOVE IT FORWARD.

OUTER HANDLE

SLIDE ARMED WARNING−LIGHT AND BUZZER (SLIDE WILL BE DISARMED AUTOMATICALLY IF DOOR IS OPEN FROM OUTSIDE)

RESIDUAL CABIN−PRESSURE WARNING−LIGHT

PASSENGER/CREW DOORS AND EMERGENCY EXITS EXTERIOR CONTROL HANDLES

@A350-900


**ON A/C A350-900

P_AC_100000_1_0090001_01_00

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

Page 10 Jun 01/13

10-0-0

TO OPEN: 1 − PUSH ON THE HANDLE. THE HANDLE IS EJECTED FROM ITS HOUSING. 2 − TURN THE HANDLE COUNTERCLOCKWISE TO DESENGAGE THE LATCHES. 3 − PUSH ON THE ESCAPE HATCH. IT OPENS INSIDE THE COCKPIT.

NOTE: THE ESCAPE HATCH IS THE COCKPIT EMERGENCY EXIT. MAKE SURE THAT NO PERSON IN THE COCKPIT IS BELOW THE ESCAPE HATCH.

ESCAPE ROPE

@A350-900


**ON A/C A350-900

P_AC_100000_1_0100001_01_00

Cockpit Emergency Exit FIGURE-10-0-0-991-010-A01

Page 11 Jun 01/13

TOGGLE SWITCH

MANUAL OPERATING DEVICE

10-0-0

HANDLE

HYDRAULIC AUXILIARY− PUMP

194KB

4 − CONNECT A POWER HAND TOOL OR THE HANDLE TO OPERATE THE HYDRAULIC AUXILIARY−PUMP UNTIL THE GREEN INDICATOR LIGHT COMES ON (CARGO DOOR FULLY OPEN AND LOCKED). 5 − RELEASE THE MANUAL OPERATING DEVICE.

4 − RELEASE THE TOGGLE SWITCH.

2 − TURN THE MANUAL OPERATING DEVICE CLOCKWISE TO THE "OPEN" POSITION AND HOLD IT. 3 − ON THE YELLOW GROUND−SERVICE PANEL; PUT THE HYDRAULIC AUXILIARY−PUMP GEARBOX IN THE POSITION ON THE HYDRAULIC AUXILIARY−PUMP AND TIGHTEN THE BOLTS.

1− DO THE OPERATIONS 1 AND 2 AS FOR "NORMAL OPERATION".

NOTE: TWO OPERATORS ARE REQUIRED FOR THIS OPERATION. A POWER HAND TOOL (MINIMUM 600 RPM, ELECTRIC OR PNEUMATIC) OR THE HANDLE (ON THE YELLOW GROUND−SERVICE PANEL) IS REQUIRED FOR THIS OPERATION.

MANUAL OPERATION

GREEN INDICATOR LIGHT

3 − PUSH THE TOGGLE SWITCH ON THE DOOR OPERATION PANEL TO THE "OPEN" POSITION AND HOLD IT UNTIL THE GREEN INDICATOR LIGHT COMES ON (CARGO DOOR FULLY OPEN AND LOCKED).

2 − QUICKLY AND FULLY PULL THE LATCHING HANDLE DOWN WITH A CONTINUOUS MOVEMENT (OUT AND DOWN).

1− PUSH THE LOCKING HANDLE FLAP IN AND PULL THE LOCKING HANDLE TO THE "UNLOCKED" POSITION (OUTWARD AND UPWARD). MAKE SURE THAT YOU SEE ALL THE INDICATOR FLAGS (EIGHT FLAGS).

NORMAL OPERATION

WARNING: MAKE SURE THAT THE RESIDUAL PRESSURE WARNING−LIGHT DOES NOT FLASH.

WARNING: ENSURE THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR OF CARGO DOOR AREA.

LATCHING HANDLE

LOCKING HANDLE

FWD AND AFT CARGO COMPARTMENT DOOR CONTROLS

PRESSURE WARNING LIGHT

YELLOW GROUND−SERVICE PANEL

HYDRAULIC AUXILIARY− PUMP GEARBOX

@A350-900


**ON A/C A350-900

P_AC_100000_1_0110001_01_00

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

Page 12 Jun 01/13


INSTALLED ON NLG

**ON A/C A350-900

P_AC_100000_1_0120001_01_00

Control Panels FIGURE-10-0-0-991-012-A01

10-0-0

Page 13 Jun 01/13

10-0-0 HOOK LATCHES

316AR

316AL

PIN LATCHES

1 − OPEN THE OVERPRESSURE DOOR 316BR TO RELEASE UNWANTED AIR PRESSURE. 2 − TURN THE MECHANISM LEVER AND BLOCK IT. 3 − RELEASE THE HOOK LATCHES ON RIGHT ACCESS DOOR 316AR. 4 − OPERATE PIN LATCHES (FORWARD AND AFT). 5 − OPEN RIGHT ACCESS DOOR 316AR AND LOCK MANUALLY THE FIXED ROD WHEN DOOR IS FULLY OPEN. 6 − OPERATE PIN LATCHES (FORWARD AND AFT) ON LEFT ACCESS DOOR 315AL. 7 − OPEN LEFT ACCESS DOOR 315AL AND LOCK MANUALLY THE FIXED ROD WHEN DOOR IS FULLY OPEN.

OPERATION:

316BR

PIN LATCHES

APU ACCESS DOORS

@A350-900


**ON A/C A350-900

P_AC_100000_1_0150001_01_00

APU Compartment Access FIGURE-10-0-0-991-015-A01

Page 14 Jun 01/13

10-0-0

FT3

WL1 FT1

D3 BF3

RAT

BF2

BF1

N1

D2

HT

F3 C1

D1 D5 F1

AP BF1 BF2 BF3 C1 C2 C3 CP1 D1 D2 D3 D4 D5

m 6.52 2.66 2.08 2.59 3.37 3.29 3.26 6.20 5.37 5.33 5.27 5.21 7.61

ft 21.39 8.73 6.82 8.50 11.06 10.79 10.70 20.34 17.62 17.49 17.29 17.09 24.97

A/C (142 000 kg) CONFIGURATION AFT CG (40%)

F1 F2 F3 F4 FT1 FT2 FT3 HT N1 RAT RD1 VT WL1 WL2

m 2.70 2.58 8.78 8.45 3.84 4.64 5.27 7.56 0.93 1.25 4.34 17.07 9.44 7.04

ft 8.86 8.46 28.81 27.72 12.60 15.22 17.29 24.80 3.05 4.10 14.24 56.00 30.97 23.10

A/C (142 000 kg) CONFIGURATION AFT CG (40%)

DIMENSIONS ARE RELATED TO AIRCRAFT WEIGHT AND CG CONFIGURATION

FT2

D4 C3 C2 F2 F4

AP

NOTE: PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED FROM THE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.

VT

WL2

RD1 CP1

@A350-900


**ON A/C A350-900

P_AC_100000_1_0160001_01_01

Aircraft Ground Clearances FIGURE-10-0-0-991-016-A01

Page 15 Jun 01/13


=

=

=

=

CUT HERE IN EMERGENCY

NOT MARKED ON ALL AIRCRAFT

COLORED

**ON A/C A350-900

P_AC_100000_1_0170001_01_01

Structural Break-in Points FIGURE-10-0-0-991-017-A01

10-0-0

Page 16 Jun 01/13


BAT 1

BAT EMER 1

BAT 2

BAT EMER 2

ACCESS VIA FWD CARGO COMPARTMENT DOOR

811

ACCESS VIA ACCESS DOOR 811

**ON A/C A350-900

P_AC_100000_1_0180001_01_00

Batteries Location and Access FIGURE-10-0-0-991-018-A01

10-0-0

Page 17 Jun 01/13

Airbus A350-900 Booklet

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