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@AIRBUSA350-900
AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING
AC
The content of this document is the property of Airbus.It is supplied in confidence and commercial security on its contents must be maintained.It must not be used for any purpose other than that for which it is supplied, nor mayinformation contained in it be disclosed to unauthorized persons.It must not be reproduced in whole or in part without permission in writing from the owners ofthe copyright. Requests for reproduction of any data in this document and the media authorizedfor it must be addressed to Airbus.
7-8-2 Radius of Relative Stiffness (Other values of E and µ)
7-9-0 Aircraft Classification Number - Flexible Pavement
7-9-1 Aircraft Classification Number - Rigid Pavement
8 SCALED DRAWINGS
8-0-0 Scaled Drawings
10 AIRCRAFT RESCUE AND FIRE FIGHTING
10-0-0 Aircraft Rescue and Fire Fighting
T.O.C.Page 3
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
SCOPE
1-1-0 INTRODUCTION
**ON A/C A350-900
Introduction
1. General
The A350 AIRCRAFT CHARACTERISTICS AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A350-900 series aircraft to provide necessary data to airport operators andairlines for airport facilities planning.
The data given in this issue of the A350 AIRCRAFT CHARACTERISTICS AIRPORT ANDMAINTENANCE PLANNING (AC) can be subject to change pending completion of the design andflight test phase. It is given for guidance only and does not constitute a contractual commitment.
This document is not customized and must not be used for training purposes.
The A350 XWB is a new family of mid-size medium to long range new technology aircraft that willdeliver superior fuel efficiency, passenger comfort, environmental characteristics and economics, witha global market coverage.The aircraft is designed to offer multiple payload capabilities with a consistant range ability acrossthe family.The A350 XWB is equipped with two Rolls-Royce Trent XWB engines.This engine will incorporate the most advanced technologies to provide the best aircraft performance,maintainability, lowest fuel consumption and environmental impact.Reflecting market needs, the A350 XWB offers a high level of cargo hold capability and flexibility.Two wide cargo doors and a Cargo Loading System (CLS) compatible with most lower deck cargocontainers and pallet standards, allowing interlining operations, ease the loading.The A350 XWB provides easy and cost effective ground handling minimizing aircraft turn round time.The innovative A350 XWB design increases planning flexibility to perform maintenance during theaircraft scheduled downtime.
Correspondence concerning this publication should be directed to:
AIRBUS S.A.S.Customer ServicesTechnical Data Support and Services1 Rond Point Maurice BELLONTE31707 BLAGNAC CEDEXFRANCE
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
1-2-0 Glossary
**ON A/C A350-900
Glossary
1. List of Abbreviations
A/C Aircraft
ACN Aircraft Classification NumberAPU Auxiliary Power Unit
B/C Business Class
CBR California Bearing Ratio
CC Cargo Compartment
CG Center of Gravity
E Young’s Modulus
ESWL Equivalent Single Wheel Load
FAA Federal Aviation AdministrationFDL Fuselage Datum Line
FR FrameFSTE Full Size Trolley Equivalent
FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment
ICAO International Civil Aviation Organisation
ISA International Standard Atmosphere
L Radius of relative stiffnessLCN Load Classification NumberLD Load DeviceLD Lower DeckLH Left HandLP Low PressureLPS Last Pax Seating
MAC Mean Aerodynamic Chord
MAX MaximumMIN MinimumMLG Main Landing Gear
NLG Nose Landing Gear
OAT Outside Air Temperature
PAX Passenger
PBB Passenger Boarding Bridge
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ULD Unit Load DeviceUS United StatesVFG Variable Frequency Generator
WV Weight Variant
Y/C Economic Class
2. Design Weight TerminologyMaximum Design Ramp Weight (MRW):Maximum weight for ground maneuver (including weight of taxi and run-up fuel) as limited byaircraft strength and airworthiness requirements. It is also called Maximum Design Taxi Weight(MTW).
Maximum Design Landing Weight (MLW):Maximum weight for landing as limited by aircraft strength and airworthiness requirements.
Maximum Design Takeoff Weight (MTOW):Maximum weight for takeoff as limited by aircraft strength and airworthiness requirements. (This isthe maximum weight at start of the take-off run).
Maximum Design Zero Fuel Weight (MZFW):Maximum permissible weight of the aircraft without usable fuel.
Maximum Seating Capacity:Maximum number of passengers specifically certified or anticipated for certification.
Usable Volume:Usable volume available for cargo, pressurized fuselage, passenger compartment and cockpit.
Water Volume:Maximum volume of cargo compartment.
Usable Fuel:Fuel available for aircraft propulsion.
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
AIRCRAFT DESCRIPTION
2-1-0 General Aircraft Characteristics
**ON A/C A350-900
General Aircraft Characteristics
1. The following table provides characteristics of the A350--900.
Aircraft CharacteristicsBasic Weights
Maximum Taxi Weight (MTW)Maximum Ramp Weight (MRW)
268900 kg(592824.0 lb)
Maximum Take Off Weight (MTOW) 268000 kg(590839.0 lb)
Maximum Landing Weight (MLW) 205000 kg(451948.0 lb)
Maximum Zero Fuel Weight (MZFW) 192000 kg(423288.0 lb)
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Aircraft CharacteristicsWater Volume, AFT CC 95.8 m3
(3383.16 ft.3)
Water Volume, Bulk CC 11.4 m3(402.59 ft.3)
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-2-0 General Aircraft Dimensions
**ON A/C A350-900
General Aircraft Dimensions
1. This section provides general aircraft dimensions.
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
66.61 m(218.54 ft)
3.04 m(9.97 ft)
65.26 m(214.11 ft)
4.63 m(15.19 ft)
9.42 m(30.90 ft)
18.79 m(61.65 ft)
1.74 m(5.71 ft)
12.87 m(42.22 ft)
10.60 m(34.77 ft)
0.75 m(2.46 ft)
64.75 m(212.43 ft)
28.66 m(94.03 ft)
RELATED TO AIRCRAFT ATTITUDE AND WEIGHT
6.09 m(19.98 ft)
P_AC_020200_1_0010001_01_01
General Aircraft Dimensions(Sheet 1 of 2)
FIGURE-2-2-0-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
10.50 m(34.45 ft)
RELATED TO AIRCRAFT ATTITUDE AND WEIGHT
21.97 m(72.08 ft)
46.68 m(153.15 ft)
66.80 m(219.16 ft)
2.46 m(8.07 ft)
9.62 m(31.56 ft)
7.86 m(25.79 ft) 12.75 m
(41.83 ft)
17.02 m(55.84 ft)
5.96 m(19.55 ft)
5.18 m(16.99 ft)
P_AC_020200_1_0010001_02_01
General Aircraft Dimensions(Sheet 2 of 2)
FIGURE-2-2-0-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-3-0 Ground Clearances
**ON A/C A350-900
Ground Clearances
1. This section gives the height of various points of the aircraft, above the ground, for different aircraftconfigurations.Dimensions in the tables are approximate and will vary with tire type, weight and balance and otherspecial conditions.The dimensions are given for:- A light weight, for an A/C in maintenance configuration with FWD CG and a AFT CG,- An aircraft at MRW with a FWD CG and a AFT CG,- Aircraft on jacks, FDL at 6.50 m (21.33 ft.).
NOTE : Passenger and cargo door ground clearances are measured from the center of the door silland from floor level.
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
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.
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**ON A/C A350-900
A
A
1.06 m(3.48 ft)
2 m(6.56 ft)
61.8 °
R 0.78 m(2.56 ft)
2.93 m(9.61 ft)
R 1.06 m(3.48 ft)
0.77 m(2.53 ft)
P_AC_020707_1_0010001_01_00
Nose Landing Gear DoorsForward Nose Landing Gear Doors (Sheet 1 of 2)
FIGURE-2-7-7-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
0.76 m(2.49 ft)
2.03 m(6.66 ft)
69.8 °
2.15 m(7.05 ft)
0.59 m(1.94 ft)
A
A
R 0.72 m(2.36 ft)
R 0.71 m(2.33 ft)
P_AC_020707_1_0010001_02_00
Nose Landing Gear DoorsAft Nose Landing Gear Doors (Sheet 2 of 2)
FIGURE-2-7-7-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
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.
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
2.75 m(9.02 ft)
R 2.43 m(7.97 ft)
0.19 m(0.62 ft)
81.3 °
1.63 m(5.35 ft)
0.13 m(0.43 ft)
A
A
P_AC_020708_1_0010001_01_00
Main Landing Gear DoorsFIGURE-2-7-8-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-8-0 Escape Slides
**ON A/C A350-900
Escape Slides
1. GeneralThis section gives location of escape facilities and related clearances.
2. LocationEscape facilities are provided at the following locations:- One cockpit escape rope is kept in a dedicated stowage compartment adjacent to the escape
hatch,- One slide-raft at each passenger/crew door (total eight).
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**ON A/C A350-900
P_AC_020800_1_0010001_01_01
COCKPITESCAPE ROPE
CABIN DUAL−LANESLIDE/RAFT
CABIN SINGLE−LANESLIDE/RAFT
CABIN DUAL−LANESLIDE/RAFT
CABIN DUAL−LANESLIDE/RAFT
Escape SlidesLocation (Sheet 1 of 2)
FIGURE-2-8-0-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_020800_1_0010001_02_00
GR
ID E
QU
ALS
1 m
(3.
28 ft
) IN
RE
ALI
TY
03691215182124273033
EM
ER
GE
NC
Y D
ES
CE
NT
TH
RO
UG
H T
HE
ES
CA
PE
HA
TC
H W
ITH
TH
E E
SC
AP
E R
OP
E
Escape SlidesDimensions (Sheet 2 of 2)FIGURE-2-8-0-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-9-0 Landing Gear
**ON A/C A350-900
Landing Gear
1. MLG System DescriptionThe two MLGs are mounted in the LH and RH wing just outboard of the wing root within thetrailing edge.The MLGs retract sideways into bays in the fuselage. Each MLG has a four wheel twin-tandem bogie.Each MLG has one associated main door operated by a single door actuator.Each MLG has a gear uplock and a door uplock.The MLG has a double side stay arrangement to improve load distribution on the composite wing.Each side stay has a separate lock stay assembly to provide a positive means to lock landing gear inthe extended position for landing and ground manoeuvres.Each MLG leg contains a single stage oleo shock strut consisting of a sliding piston and a main fittingthat is supported by the two folding side stays and pivots on the top of the main fitting forextension/retraction.In flight, the MLGs are retracted and locked up.The MLG doors are closed and locked to enclose the MLG bay in flight and on the ground, onlyopening when the landing gear is extending or retracting.Hydraulic power for the MLG extension/retraction is from the green hydraulic system.
2. NLG System DescriptionThe NLG is located in the forward lower fuselage on the aircraft centerline below the cockpit.It is forward retracting and consists of a twin wheel axle mounted on a main fitting that incorporatesa single stage oleo shock strut supported by a forward drag brace.The NLG main fitting accommodates the steering assembly for the NWS system.In flight, the NLG is retracted and locked up while the four sideways opening NLG Doors are closedand locked to enclose the NLG bay.The two forward doors are each operated by two independent door actuators.When retracted, the NLG is held by an uplock and the two main NLG doors are held by a single dooruplock assembly, containing an uplock hook for each door.The hydraulically powered Forward NLG Doors are also closed after the NLG is extended.The aft doors are mechanically driven and remain open when the NLG is extended.Hydraulic power for the NLG extension/retraction comes from the Yellow hydraulic system.
3. Landing Gear Extension and Retraction SystemThe Landing Gear Extension and Retraction System is made up of three sub-systems:- Normal extension and retraction system, for normal extension and retraction,- Alternate extension system, for extension in flight if normal system is unavailable,- Ground door opening system, to allow on ground access to the landing gear bays for maintenance
purposes.
2-9-0Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_020900_1_0010001_01_00
AA
HINGE DOOR
FIXEDFAIRINGDOOR
MAIN DOOR B
C
D
A
HINGE
GUIDE
GUIDE ROLLER RAMP
B
MECHANICAL LINKAGE
C
F
LH SHOWNRH SYMMETRICAL
Main Landing GearDoors overview (Sheet 1 of 3)FIGURE-2-9-0-991-001-A01
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**ON A/C A350-900
P_AC_020900_1_0010001_02_00
RETRACTIONACTUATOR
MAIN FITTING
FORWARD LOCKSTAY ACTUATOR
FORWARDLOCK STAY
FORWARDSIDE STAY
FORWARDDOWNLOCK
SPRINGSSLIDINGPISTON
BOGIE
AFT LOCKSTAY ACTUATOR
AFTLOCK STAY
AFTSIDE STAY
AFTDOWNLOCKSPRINGS
UPPERTORQUE LINK
LOWERTORQUE LINK
BOGIE PITCHTRIMMER ACTUATOR
E
D
E
H
H
Main Landing GearOverview (Sheet 2 of 3)
FIGURE-2-9-0-991-001-A01
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**ON A/C A350-900
P_AC_020900_1_0010001_03_00
SAFETY
SAFETYPIN
F
TYPICAL INSTALLATION
SAFETYPIN
COLLAR
SAFETYPIN
ACTUATOR
LOCK STAY
HINGE
G
G
H
Main Landing GearSafety Devices (Sheet 3 of 3)FIGURE-2-9-0-991-001-A01
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**ON A/C A350-900
P_AC_020900_1_0020001_01_00
A
B
C
A
B
HINGE
HINGEFREE FALL
NLG Z−STOP
DRIVEN
RAMP
LINKAGE ROD
FORWARDDOOR
AFTDOOR
RH SHOWNLH SYMMETRICAL
E
Nose Landing GearDoors overview (Sheet 1 of 4)FIGURE-2-9-0-991-002-A01
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**ON A/C A350-900
P_AC_020900_1_0020001_02_00
RETRACTION ACTUATOR
LOCK STAY ACTUATOR
MAIN FITTING
UPPER DRAGBRACE
LOWER DRAGBRACE
FORWARD/ AFT LOCK STAYS
DOWNLOCKSPRINGS
STEERINGASSEMBLY
JACKINGDOME
UPPERTORQUE LINK
LOWERTORQUE LINK
SLIDINGPISTON
C
D
D
G
H
Nose Landing GearOverview (Sheet 2 of 4)
FIGURE-2-9-0-991-002-A01
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**ON A/C A350-900
P_AC_020900_1_0020001_03_00
E
SAFETY
SAFETYPIN
SAFETYPIN
SAFETYPIN
COLLAR
ACTUATOR
LOCK STAY
F
G
F
Nose Landing GearSafety Devices (Sheet 3 of 4)FIGURE-2-9-0-991-002-A01
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**ON A/C A350-900
P_AC_020900_1_0020001_04_00
1GN2GN
H
J
JK
K
FWD
FWD
Nose Landing GearService Panels (Sheet 4 of 4)FIGURE-2-9-0-991-002-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-10-0 Exterior Lighting
**ON A/C A350-900
Exterior Lighting
1. This section gives the location of the aircraft exterior lighting.
EXTERIOR LIGHTINGITEM DESCRIPTION
1 RIGHT NAVIGATION LIGHT (GREEN)
2 LEFT NAVIGATION LIGHT (RED)
3 TAIL NAVIGATION LIGHT (WHITE)
4UPPER ANTI-COLLISION LIGHT/BEACON(RED)
5LOWER ANTI-COLLISION LIGHT/BEACON(RED)
6 LOGO LIGHTS7 ENGINE SCAN LIGHTS8 WING SCAN LIGHTS
21 − DME 122 − TCAS 1 (BOTTOM)23 − PITOT24 − MFP 125 − AOA26− ICE PROBE DETECTOR27 − GLIDE28 − WEATHER RADAR29 − VOR30 − ISP RH31 − TCAS 1 (TOP)32 − SSA 2, 333 − ICE PROBE PROTECTOR34 − MFP 2, 335 − RADIO ALT E136 − RADIO ALT R137 − RADIO ALT R338 − RADIO ALT E339 − TCAS 2 (BOTTOM)
33
40 − VHF 220 − RADIO ALT E2NOTE:LOCATION DEPENDING OF AIRCRAFT CONFIGURATION
Antennas and Probes LocationFIGURE-2-11-0-991-001-A01
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2-12-0 Engine and Nacelle
**ON A/C A350-900
Engine and Nacelle
1. Power PlantThe A350--900 has two main power plants, one installed under each wing on a pylon.Each power plant can be lowered for removal from its pylon.The power plant comprises the:- Nacelle,- Engine.
2. NacelleThe nacelle comprises the following assemblies:- Air intake,- Fan cowls,- Thrust reverser,- Exhaust system.
A. Fan CowlA power door opening system is installed to assist in opening the cowls.The cowls have access doors for fan case-mounted components.
B. Thrust ReverserThe engine thrust reverser consists primarily of a inner fixed structure and an outer translatingsleeve.The fan exhaust stream is reversed by the cascades and blocker doors, which form part of thetranslating sleeve actuated by an electrical Thrust Reverser Actuation System (TRAS).A power door opening system is used to assist thrust reverser cowl opening.The thrust reverser latching system is designed so that the remote latches close only when thehooks are engaged.Means are provided to latch and secure a thrust reverser in the stowed position.Means are provided to permit actuation of the thrust reversers without engine operation, formaintenance purposes, either using the TRAS powered by the aircraft or by manual drive withexternal Ground Support Equipment (GSE).
C. Exhaust SystemThe exhaust system consists of a primary nozzle and a center body plug.The exhaust system is designed to optimize aerodynamics and acoustic performance.
3. Engine
A. IgnitionEach engine is equipped with a dual ignition system controlled by the FADEC.Each engine is equipped with an automatic flame-out protection.
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B. Cooling SystemA nacelle cooling and ventilating system automatically provides the airflow required for coolingengine and nacelle accessories and associated structure.
C. Power ControlForward thrust of each engine is controlled by a throttle control lever mounted on the centerpedestal in the cockpit.Thrust reverser control is by means of a separate lever for each engine.
D. Engine Master ControlEngine fuel shutoff is controlled by switches installed on the center pedestal.
E. Emergency ShutdownActuation of the fire controls closes the associated LP valves.
F. IndicatingIndications for each engine are displayed on the Control and Display System (CDS).
G. OilThe propulsion system has an independent integral oil system that is able to provide theappropriate quantity of oil, at the temperature necessary for continuous propulsion systemoperation, for all achievable conditions within the propulsion system operating envelope.Means are provided for gravity filling.It is possible to visually check and replenish the engine oil level without opening the fan cowldoor.Magnetic chip detectors are installed in the lubrication system.
H. StartingThe engine is equipped with a pneumatic air turbine starter.The starter can be supplied with air either from the APU, or the other engine, or an Air StartUnit (AS).Standard types of GSE can be used.
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**ON A/C A350-900
P_AC_021200_1_0010001_01_00
1.53 m(5.02 ft)
5.09 m(16.70 ft)
2.03 m(6.66 ft)
0.72 m(2.39 ft)
1.65 m(5.41 ft)
1.94 m(6.36 ft)
3.17 m(10.40 ft)3.52 m
(11.55 ft)
1.48 m(4.86 ft) 0.89 m
(2.92 ft)REFER
APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATIONNOTE:
3.94 m(12.93 ft)
11.10 m(36.42 ft)
2.09 m(6.86 ft)
1.68 m(5.51 ft)
6.40 m(21 ft)
1.40 m(4.59 ft)
TO SECTION2−3−0
Engine and Nacelle(Sheet 1 of 3)
FIGURE-2-12-0-991-001-A01
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**ON A/C A350-900
P_AC_021200_1_0010001_02_00
APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION.NOTE:
B
C
5.50 m(18.04 ft)
1.01 m(3.31 ft)
A B
6.39 m(20.96 ft)
1.28 m(4.20 ft)
C D
D
A
TRFC
FC: FAN COWL AND TR: THRUST REVERSER
Engine and Nacelle(Sheet 2 of 3)
FIGURE-2-12-0-991-001-A01
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**ON A/C A350-900
P_AC_021200_1_0010001_03_00
B
C
6.42 m(21.06 ft)
1.51 m(4.95 ft)
A B
7.13 m(23.40 ft)
1.81 m(5.94 ft)
C D
D
A
TRFC
TR=45° FC=50°
APPROXIMATE DIMENSIONS DEPENDING ON AIRCRAFT CONFIGURATION.NOTE:
FC: FAN COWL AND TR: THRUST REVERSER
Engine and Nacelle(Sheet 3 of 3)
FIGURE-2-12-0-991-001-A01
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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.
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**ON A/C A350-900
, Z315 Z316
A
FR104
FR112
ENGINE
ENGINE FUELAND
CONTROLSYSTEM
EXHAUSTSYSTEM
AIR SYSTEM
IGNITIONAND
STARTINGSYSTEM
AIR SYSTEM
OILSYSTEM
FR109
FR104
A
B
B
P_AC_021201_1_0010001_01_00
APUFIGURE-2-12-1-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-13-0 Levelling, Symmetry and Alignement
**ON A/C A350-900
Levelling, Symmetry and Alignement
1. Quick LevelingThere are three alternative procedures to level the aircraft:- Quick leveling procedure with Air Data/Inertial Reference System (ADIRS),- Quick leveling procedure with a spirit level in the passenger compartment,- Quick leveling procedure with a spirit level in the FWD cargo compartment.
2. Precise LevelingFor precise leveling, it is necessary to install sighting rods in the receptacles located under thefuselage (points 10 and 17 for longitudinal leveling) and under the wings (points 1 LH and 1 RH forlateral leveling) and use a sighting tube.With the aircraft on jacks, adjust the jacks until the reference marks on the sighting rods are alignedin the sighting plane (aircraft level).
3. Symmetry and Alignment CheckPossible deformation of the aircraft is measured by photogrammetry.
2-13-0Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_021300_1_0010001_01_00
FR22FR23
FR92
10
17
1RH
1LH
RIB4
RIB5
RIB5
RIB4
Location of Leveling PointsFIGURE-2-13-0-991-001-A01
2-13-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-14-1 Jacking for Maintenance
**ON A/C A350-900
Jacking for Maintenance
1. Aircraft Jacking Points for Maintenance
A. The A350-900 can be jacked:- At not more than 163000 kg (359354 lb),- within the limits of the permissible wind speed when the aircraft is jacked outside a closed
environment.:
B. Primary Jacking PointsThe aircraft is provided with three primary jacking points:- One located on the forward lower left fuselage (FR12),- Two located under the wings (one under each wing, RIB9).
C. Auxiliary Jacking Point (Safety Stay)When the aircraft is on jacks, a safety stay is placed under the fuselage at FR98 to prevent tailtipping caused by accidental displacement of the aircraft center of gravity.The safety point must not be used for lifting the aircraft.
2. Jacks and Safety Stay
A. Jack DesignThe Maximum Eligible Static Load given in table FIGURE 2-14-1-991-001-A are the maximumloads applicable on jack fittings.
(1) In fully retracted position (jack stroke at minimum), the height of the jacks is such thatthey may be placed beneath the aircraft under the most adverse conditions, namely, tiresdeflated and shock absorbers depressurized and, in addition, with a sufficient clearancebetween the aircraft jacking point and the jack upper end.
(2) The jacks stroke enables the aircraft to be jacked up so that the Fuselage Datum Line(FDL) may be positioned up to 7.30 m (23.95 ft.) from the ground to allow all requiredmaintenance procedure and in particular, the landing gear shock absorbersremoval/installation.
B. Safety StayThe stay stroke enables the aircraft tail to be supported up to the Fuselage Datum Line (FDL)positioned at 7.30 m (23.95 ft.) from the ground.
2-14-1Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
FUSELAGE DATUM LINE
X
FR12
FWD JACKING POINT
RIB9
RIB9
WING JACKING POINT
WING JACKING POINT
SAFETY POINTFR98
Y
A
B
B’
C
SAFETY STAY
WING JACKINGPOINT
C
B’
B
FORWARD FUSELAGEJACKING POINT A
4.77
33.22
33.22
58.75
15.65
108.99
108.99
192.75
−1.72
8.71
−8.71
0
−5.64
28.58
−28.58
0
MAXIMUMLOAD ELIGIBLE
m ft
18630
daN
YX
76600
76600
7650
m ft
NOTE:SAFETY STAY IS NOT USED FOR JACKING.
P_AC_021401_1_0010001_01_00
Jacking for MaintenanceJacking Points Location (Sheet 1 of 5)
FIGURE-2-14-1-991-001-A01
2-14-1Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
POSITIONCG
(% MAC)
AIRCRAFT ON WHEELS, SHOCK−ABSORBERDEFLATED, TIRES DEFLATED (RH)
A/C ON JACKS, FDL AT 6.50 m (21.33 ft),
SHOCK−ABSORBER RELAXED, CLEARANCEOF MAIN GEAR WHEELS = 1.17 m (3.84 ft)(STANDARD TIRES *), CLEARANCE OFNOSE GEAR WHEELS = 1.38 m (4.53 ft)(STANDARD TIRES *)
AIRCRAFT ON WHEELS (STANDARD TIRES *)MAXIMUM JACKING WEIGHT= 163 000 kg (359 353 lb)
AIRCRAFT ON WHEELS (STANDARD TIRES *)A/C WEIGHT = 142 000 kg (313 056 lb)
3.122015.42 LH
4.00 RH4.71
41 3.364.68 LH
4.00 RH4.48
20 4.32 6.125.66
41
20 3.06 16.904.58
41 3.29 4.914.57
20 3.09 17.034.62
41 3.34 4.934.60
HEIGHT
L M N
4.32 5.66
CONFIGURATION
NOTE:* STANDARD TIRES: NOSE LANDING GEAR = 1 050 x 395 R16
MAIN LANDING GEAR = 1 400 x 530 R23
10.24
11.02
14.17
14.17
10.04
10.79
10.14
10.96
4.70 LH
13.12 RH
15.35 LH
13.12 RH
18.57
18.57
15.03
14.99
15.16
15.09
15.45
14.70
20.08
6.12 20.08
5.15
16.11
5.19
16.18
m ft m mft ft
NML
FUSELAGE DATUM LINE
A/C FUSELAGE PARALLEL TO THE GROUND,
P_AC_021401_1_0010001_02_00
Jacking for MaintenanceJacking Dimensions (Sheet 2 of 5)
FIGURE-2-14-1-991-001-A01
2-14-1Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
FR12
FR13
FR14
FR11
NOSE JACKADAPTOR
A
FR12FR13
Z120
A
P_AC_021401_1_0010001_03_00
Jacking for MaintenanceForward Jacking Point (Sheet 3 of 5)
FIGURE-2-14-1-991-001-A01
2-14-1Page 4
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
A
A
1
2
3
4
A
A
A A
REAR SPAR
RIB9
Z571 (Z671)
WING JACKADAPTOR
PLATE COVERPROTECTOR
571FB (671FB)
P_AC_021401_1_0010001_04_00
Jacking for MaintenanceWing Jacking Point (Sheet 4 of 5)
FIGURE-2-14-1-991-001-A01
2-14-1Page 5
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
FR98
FR98
BEAM5
FR98
5
A
B
A
FWD
B
Z310
AFT JACKADAPTOR
P_AC_021401_1_0010001_05_00
Jacking for MaintenanceAuxiliary Jacking Point - Safety (Sheet 5 of 5)
FIGURE-2-14-1-991-001-A01
2-14-1Page 6
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2-14-2 Jacking for wheel change
**ON A/C A350-900
Jacking for wheel change
1. GeneralTo replace either the wheel or brake unit assemblies on any of the landing gears, it is necessary to liftthe landing gear with a jack.The landing gear can be lifted by a pillar jack or with a cantilever jack.
NOTE : You can lift the aircraft at Maximum Ramp Weight (MRW).
2. Nose Landing Gear (NLG)To lift the NLG axle with a jack, a dome shaped pad is installed between the wheels.The reaction loads at the jacking position are shown in FIGURE 2-14-2-991-002-A.
NOTE : The maximum load at NLG jacking point is 33758 daN.
3. Main Landing Gear (MLG)To lift the MLG bogie with jacks, a dome shaped pad is installed below the FWD and AFT ends ofeach bogie beam.Each pair of wheels and brake units can be replaced on the end of the bogie that is lifted.Both FWD and AFT ends of the bogie beam can be lifted together, but the bogie beam must be keptlevel during the lift to prevent damage.The reaction loads at the jacking position are shown in FIGURE 2-14-2-991-003-A.
NOTE : The maximum load at each MLG jacking point is 83892.5 daN.
2-14-2Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
FWD
CONFIGURATION (ASSUMEALL OTHER TYRES ONTHE A/C ARE INTACT)
WEIGHT (T)CG
(% MAC)DIM A DIM B
2 TYRES (NORMAL)
1 FLAT TYRE
2 FLAT TYRES & 50% RIMFLANGE DAMAGE
2 FLAT TYRES & NO RIMFLANGE DAMAGE
MRW
MRW
MLW
MLW
26.2
26.2
20
20
291
227
75
97
10.27
8.42
7.51
7.51
11.45
8.93
2.95
3.81
261
214
191
191
mm in mm in
DOME HEIGHT− A : DISTANCE BETWEEN TYRES− B :
A350−900 NLG (1 050 x 395 R16)
B
A
A
A
P_AC_021402_1_0020001_01_00
Nose Landing Gear Jacking Point HeightsFIGURE-2-14-2-991-002-A01
2-14-2Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
8 FLAT TYRES &50% RIM DAMAGE8 FLAT TYRES &NO RIM DAMAGE
(ASSUME ALL OTHERTYRES ON THE A/C
CONFIGURATION
ARE INTACT)
TYRE CHANGE
WEIGHT(T)
CG(% MAC)
14.88
11.96
11.22
15.00
14.72
14.88 40.51
38.62
38.34
40.78
40.98
40.66
10.51
7.63
6.88
10.66
10.39
10.51
mm in mm in mm in mm in mm in mm in
DOME HEIGHT− A : DISTANCE BETWEEN TYRES− B : DISTANCE BETWEEN BRAKE RODS AND GROUND − C :
DIM AFWD
DIM BFWD
DIM CFWD
A350−900 MLG (1 400 x 530 R23)
A
FWD
A
A
C
B
P_AC_021402_1_0030001_01_00
Main Landing Gear Jacking Point HeightsFIGURE-2-14-2-991-003-A01
2-14-2Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
GROUND MANEUVERING
4-2-0 Turning Radii
**ON A/C A350-900
Turning Radii
1. This section gives the turning radii.
4-2-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040200_1_0010001_01_00
R5
R3
R4
R6
R2
60°65°70°
R1
NOTE:FOR TURNING RADII VALUES, REFER TO SHEET 2
Turning Radii(Sheet 1 of 2)
FIGURE-4-2-0-991-001-A01
4-2-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040200_1_0010001_02_00
19.620
TYPE OFTURN
2
EFFECTIVESTEERING ANGLE (deg)
STEERINGANGLE (deg)
76.3250
A350−900 TURNING RADII
mft
86.9285
86.0282
R4
113.6373
R5
87.1286
R6
96.0315
WING NOSE TAIL
NOTE:ABOVE 50°, AIRLINES MAY USE TYPE 1 OR TYPE 2 TURNS DEPENDING ON THE SITUATIONTYPE 1 TURNS USE: ASYMMETRIC THRUST DURING THE WHOLE TURN;AND DIFFERENTIAL BRAKING TO INITIATE THE TURN ONLYTYPE 2 TURNS USE: SYMMETRIC THRUST DURING THE WHOLE TURN;AND NO DIFFERENTIAL BRAKING AT ALL IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE
R1 R2 R3RMLG LMLG NLG
24.525258.7193
69.3227
69.6228
96.2316
71.2233
79.7262
29.430246.7153
57.3188
58.9193
84.3277
60.8199
69.0226
34.235238.0125
48.6159
51.5169
75.7248
53.7176
61.5202
39.140231.1102
41.7137
45.9151
68.9226
48.5159
55.9183
43.845225.784
36.3119
41.8137
63.7209
44.7147
51.7170
48.650221.169
31.7104
38.6127
59.2194
41.8137
48.3158
53.155217.457
28.092
36.2119
55.5182
39.6130
45.7150
57.560214.146
24.781
34.3113
52.4172
38.0125
43.5143
61.565211.437
22.072
32.9108
49.8163
36.7121
41.9137
65.07029.230
19.865
31.9105
47.7156
35.9118
40.6133
49.350120.567
31.1102
38.2125
58.6192
41.4136
47.8157
54.155116.654
27.289
35.7117
54.8180
39.2129
45.1148
58.760113.343
23.978
33.8111
51.6169
37.6123
43.0141
63.265110.334
20.969
32.4106
48.7160
36.3119
41.2135
67.57017.725
18.360
31.2103
46.2152
35.3116
39.8130
mftmftmftmftmftmftmftmftmftmft
mftmftmftmftmft
FROM TYPE 1 BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN.
66.172 (MAX)28.528
19.163
31.6104
47.0154
35.6117
40.2132
mft
69.272 (MAX)16.722
17.357
30.9101
45.3149
35.0115
39.2129
mft
Turning Radii(Sheet 2 of 2)
FIGURE-4-2-0-991-001-A01
4-2-0Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-3-0 Minimum Turning Radii
**ON A/C A350-900
Minimum Turning Radii
1. This section gives the minimum turning radii.
4-3-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040300_1_0010001_01_00
69.272 (MAX)
TYPE OFTURN
1
EFFECTIVESTEERING ANGLE (deg)
STEERINGANGLE (deg)
28.794
A350−900 MINIMUM TURNING RADII
mft
48.5159
30.9101
R4
45.3149
R5
35.0115
R6
39.2129
WING NOSE TAILX A
66.172 (MAX)228.794
51.1168
31.6104
47.0154
35.6117
40.2132
mft
YR3
NLG
10.936
12.742
NOTE:TYPE 1 TURNS USE: ASYMMETRIC THRUST DURING THE WHOLE TURN; AND DIFFERENTIAL BRAKING
TYPE 2 TURNS USE: SYMMETRIC THRUST DURING THE WHOLE TURN; AND NO DIFFERENTIAL BRAKING AT ALL
NOTE:IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1BY APPLYING DIFFERENTIAL BRAKING DURING THE WHOLE TURN.
TO INITIATE THE TURN ONLY
A(MINIMUM TURNING WIDTH)
X
Y
R5
R3
R6
R4
Minimum Turning RadiiFIGURE-4-3-0-991-001-A01
4-3-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-4-0 Visibility from Cockpit in Static Position
**ON A/C A350-900
Visibility from Cockpit in Static Position
1. This section gives the visibility from cockpit in static position.
4-4-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040400_1_0010001_01_00
27°
20°
14.20 m(46.59 ft)
4.63 m(15.19 ft)
VISUAL ANGLES IN VERTICAL
DIMENSIONS ARE APPROXIMATE
105.5°
CAPTAIN FIELD OF VIEW
0.53 m(1 ft 8.88 in)
32°
15° 15°
32°
120°
NOT TO BE USED FORLANDING APPROACH VISIBILITY
NOTE:PILOT EYE POSITION WHEN PILOT’S EYES ARE IN LINE WITH THE RED AND WHITE BALLS.
ZONE THAT CANNOT BE SEEN
PLANE THROUGH PILOTEYE POSITION.
3.04 m(9.97 ft)
MAX AFT VISION WITH HEAD TURNEDAROUND SPINAL COLUMN.WING TIP CAN BE SEEN WHEN HEAD IS MOVEDTO THE SIDE.
VISUAL ANGLES IN HORIZONTALPLANE THROUGH PILOTEYE POSITION.
FIRST OFFICERFIELD OF VIEW
VISUAL ANGLES IN PLANEPERPENDICULAR TOLONGITUDINAL AXIS.
120°105.5°
Visibility from Cockpit in Static PositionFIGURE-4-4-0-991-001-A01
4-4-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-5-0 Runway and Taxiway Turn Paths
**ON A/C A350-900
Introduction
1. This section gives the runway and taxiway turnpaths for the following configurations:- 90˚ Turn --- Runway to Taxiway- 135˚ Turn --- Runway to Taxiway- 180˚ U-Turn on Runway- 90˚ Turn --- Taxiway to Taxiway- 135˚ Turn --- Taxiway to TaxiwayThe turnpaths Runway to Taxiway and Taxiway to Taxiway are defined using 2 methods:- Oversteering method,- Cockpit over centerline method.The 180 U-Turn on runway is defined using the following method:- U-Turn using edge of runway method.
4-5-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-5-1 90˚ Turn - Runway to Taxiway
**ON A/C A350-900
90˚ Turn - Runway to Taxiway
1. This section gives the 90˚ turn - runway to taxiway.
4-5-1Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040501_1_0010001_01_02
APPROX 13.3 m(44 ft)
FILLET R = 25.5 m(85 ft)
TURN R = 45 m(150 ft)
(75 ft)23 m
APPROX 10.9 m(36 ft)
TAXIWAY
RUNWAY CENTERLINE
NLG PATH
MLG PATH
FAA LEAD−IN FILLETL=75 m (250 ft)
(150 ft)45 m
CENTERLINE
90˚ Turn - Runway to TaxiwayOversteering Method (Sheet 1 of 2)
FIGURE-4-5-1-991-001-A01
4-5-1Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040501_1_0010001_02_02
APPROX 5 m(16 ft)
FILLET R = 25.5 m(85 ft)
TURN R = 45 m(150 ft)
(75 ft)23 m
TAXIWAY CENTERLINE
RUNWAY CENTERLINE
NLG PATH
MLG PATH
FAA LEAD−IN FILLETL=75 m (250 ft)
(150 ft)45 m
90˚ Turn - Runway to TaxiwayCockpit over Centerline Method (Sheet 2 of 2)
FIGURE-4-5-1-991-001-A01
4-5-1Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-5-2 135˚ Turn - Runway to Taxiway
**ON A/C A350-900
135˚ Turn - Runway to Taxiway
1. This section gives the 135˚ turn - runway to taxiway.
4-5-2Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040502_1_0010002_01_02
23 m(75 ft)
TAXIWAY
RUNWAY CENTERLINE
(150 ft)45 m
TURN R = 45 m(150 ft)
FILLET R = 25.5 m(85 ft)
APPROX 5.8 m(19 ft)
APPROX 7.6 m(25 ft)
NLG PATH
MLG PATH
FAA LEAD−IN FILLETL=75 m (250 ft)
CENTERLINE
135˚ Turn - Runway to TaxiwayOversteering Method (Sheet 1 of 2)
FIGURE-4-5-2-991-001-B01
4-5-2Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040502_1_0010002_02_02
RUNWAY
TAXIWAY23 m(75 ft)
FILLET R = 25.5 m(85 ft)
4.5 m (15 ft) EDGE CLEARANCEADDITIONAL FILLET TO MEET
TURN R = 45 m(150 ft)
APPROX1.6 m (5 ft)
(150 ft)45 m
NLG PATH
MLG PATH
FAA LEAD−IN FILLETL=75 m (250 ft)
CENTERLINE
CENTERLINE
135˚ Turn - Runway to TaxiwayCockpit over Centerline Method (Sheet 2 of 2)
FIGURE-4-5-2-991-001-B01
4-5-2Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-5-3 180˚ Turn on a Runway
**ON A/C A350-900
180˚ Turn on a Runway
1. This section gives the 180˚ turn on a runway.
4-5-3Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040503_1_0010001_01_01
APPROX 48.5 m(159.12 ft)
R4 = 45.3 m(149 ft)
R3 = 30.9 m(101 ft)
R5 = 35 m(115 ft)
4.5 m(15 ft)
4.5 m(15 ft)
RUNWAY CENTERLINE
MLG PATH
WING TIP PATH
NOTE:TYPE 1 VALUES.IT IS POSSIBLE TO GET LOWER VALUES THAN THOSE FROM TYPE 1 BY APPLYING DIFFERENTIALBRAKING DURING THE WHOLE TURN.
NOSE TIP PATH
NLG PATH
180˚ Turn on a RunwayFIGURE-4-5-3-991-001-A01
4-5-3Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-5-4 90˚ Turn - Taxiway to Taxiway
**ON A/C A350-900
90˚ Turn - Taxiway to Taxiway
1. This section gives the 90˚ turn - taxiway to taxiway.
4-5-4Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040504_1_0010001_01_02
TURN R = 45 m(150 ft)
TAXIWAY CENTERLINE
(75 ft)23 m
TAXIWAY
FILLET R = 25.5 m(85 ft)
APPROX 10.5 m(34 ft)
FAA LEAD−IN FILLETL=75 m (250 ft)
APPROX 12.9 m(42 ft)
(75 ft)23 m
NLG PATH
MLG PATH
CENTERLINE
90˚ Turn - Taxiway to TaxiwayOversteering Method (Sheet 1 of 2)
FIGURE-4-5-4-991-001-A01
4-5-4Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
TURN R = 45 m(150 ft)
TAXIWAY CENTERLINE
(75 ft)23 m
TAXIWAY
FILLET R = 25.5 m(85 ft)
FAA LEAD−IN FILLETL=75 m (250 ft)
APPROX 3.9 m(13 ft)
(75 ft)23 m
4.5 m (15 ft) EDGE CLEARANCEADDITIONAL FILLET TO MEET
NLG PATH
MLG PATH
P_AC_040504_1_0010001_02_02
CENTERLINE
90˚ Turn - Taxiway to TaxiwayCockpit over Centerline Method (Sheet 2 of 2)
FIGURE-4-5-4-991-001-A01
4-5-4Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-5-5 135˚ Turn - Taxiway to Taxiway
**ON A/C A350-900
135˚ Turn - Taxiway to Taxiway
1. This section gives the 135˚ turn - taxiway to taxiway.
4-5-5Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
TURN R = 45 m(150 ft)
TAXIWAY CENTERLINE
(75 ft)23 m
TAXIWAY
23 m(75 ft)
APPROX 6.9 m(23 ft)
FILLET R = 25.5 m(85 ft)
APPROX 8.8 m(29 ft)
NLG PATH
MLG PATH
FAA LEAD−IN FILLETL=75 m (250 ft)
P_AC_040505_1_0010002_01_02
CENTERLINE
135˚ Turn - Taxiway to TaxiwayOversteering Method (Sheet 1 of 2)
FIGURE-4-5-5-991-001-B01
4-5-5Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
TAXIWAY CENTERLINE
(75 ft)23 m
TAXIWAY
23 m(75 ft)
FILLET R = 25.5 m(85 ft)
4.5 m (15 ft) EDGE CLEARANCEADDITIONAL FILLET TO MEET
TURN R = 45 m(150 ft)
APPROX2.5 m (8 ft)
NLG PATH
MLG PATH
FAA LEAD−IN FILLETL=75 m (250 ft)
P_AC_040505_1_0010002_02_02
CENTERLINE
135˚ Turn - Taxiway to TaxiwayCockpit over Centerline Method (Sheet 2 of 2)
FIGURE-4-5-5-991-001-B01
4-5-5Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-6-0 Runway Holding Bay (Apron)
**ON A/C A350-900
Runway Holding Bay (Apron)
1. This section gives the runway holding bay (Apron).
4-6-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040600_1_0010001_01_00
45 m(150 ft)
23 m(75 ft)
190 m(625 ft)
6.1 m(20 ft)
90 m(300 ft)102 m
(335 ft)
6.1 m(20 ft)
12.2 m(40 ft)
TAXIWAYCENTERLINE
RUNWAYCENTERLINE
MAIN LANDINGGEAR PATH
HOLDINGPOINT
NOTE:COORDINATE WITH USING AIRCRAFT FOR SPECIFIC PLANNED OPERATING PROCEDURES.
Runway Holding Bay (Apron)FIGURE-4-6-0-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-7-0 Minimum Line-Up Distance Corrections
**ON A/C A350-900
Minimum Line-Up Distance Corrections
1. The ground manoeuvres were performed using asymmetric thrust and differential only braking toinitiate the turn.TODA: Take-Off Available DistanceASDA: Acceleration-Stop Distance Available
2. 90˚ Turn on Runway EntryThis section gives the minimum line-up distance correction for a 90˚ turn on runway entry.
This manoeuvre consists in a 90˚ turn at minimum turn radius starting with the edge of the MLG ata distance of 4.5 m from taxiway edge, and finishing with the aircraft aligned on the centerline of therunway.During the turn, all the clearances must meet the minimum value of 4.5 m for this category ofaircraft as recommended in ICAO Annex 14.
3. 180˚ Turn on Runway Turn PadThis section gives the minimum line-up distance correction for a 180˚ turn on runway turn pad.
This manoeuvre consists in a 180˚ turn at minimum turn radius on a standard ICAO runway turnpad geometry.It starts with the edge of the MLG at 4.5 m from pavement edge, and it finishes with the aircraftaligned on the centerline of the runway.During the turn, all the clearances must meet the minimum value of 4.5 m for this category ofaircraft as recommended in ICAO Annex 14.
4. 180˚ Turn on Runway WidthThis section gives the minimum line-up distance correction for a 180˚ turn on runway width.
For this manoeuvre, the pavement width is considered to be the runway width, which is a frozenparameter (45 m and 60 m).As per the ”180˚ turn on runway” standard operating procedures described in the Flight CrewOperating Manual, the aircraft is initially angled with respect to runway centerline when starting the180˚ turn.The value of this angle depends on the aircraft type, and is mentioned in the FCOM.During the turn, all the clearances must meet the minimum value of 4.5 m for this category ofaircraft as recommended in ICAO Annex 14.
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040700_1_0010001_01_00
TODA
ASDA4.5 m(15 ft)
4.5 m(15 ft)
90° TURN ON RUNWAY ENTRY
AIRCRAFTTYPE
MAXSTEERING
ANGLE
45 m WIDE RUNWAY
(STANDARD WIDTH)
60 m WIDE RUNWAY
(STANDARD WIDTH)
MINIMUM LINE−UPDISTANCE CORRECTION
ON TODA ON ASDA ON TODA ON ASDA
MINIMUM LINE−UPDISTANCE CORRECTION
72°A350−900 84 ft 25.7 m 178 ft 54.3 m 72 ft 21.8 m 166 ft 50.5 m
NOTE:ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF AVAILABLE DISTANCE
TAXIWAYCENTERLINE
RUNWAYCENTERLINE
90˚ Turn on Runway EntryFIGURE-4-7-0-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040700_1_0020001_01_00
180° TURN ON RUNWAY TURNPAD
AIRCRAFTTYPE
MAXSTEERING
ANGLE
45 m WIDE RUNWAY
(STANDARD WIDTH)
60 m WIDE RUNWAY
(STANDARD WIDTH)
MINIMUM LINE−UPDISTANCE CORRECTIONON TODA ON ASDA
MINIMUM LINE−UPDISTANCE CORRECTION
72°A350−900 122 ft 37.2 m
NOTE:ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF AVAILABLE DISTANCE
216 ft 65.9 m 117 ft 35.7 m 211 ft 64.4 mON TODA ON ASDA
REQUIRED MINIMUMPAVEMENT WIDTH
206 ft 62.9 m
4.5 m(15 ft)
4.5 m(15 ft)
MINIMUM PAVEMENT WIDTH
TODA
ASDA
4.5 m(15 ft)
RUNWAYCENTERLINE
180˚ Turn on Runway Turn PadFIGURE-4-7-0-991-002-A01
4-7-0Page 3
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_040700_1_0030001_01_00
180° TURN ON RUNWAY WIDTH
AIRCRAFTTYPE
MAXSTEERING
ANGLE
45 m WIDE RUNWAY
(STANDARD WIDTH)
60 m WIDE RUNWAY
(STANDARD WIDTH)
MINIMUM LINE−UPDISTANCE CORRECTION
ON TODA ON ASDA ON TODA ON ASDA
MINIMUM LINE−UPDISTANCE CORRECTION
72°A350−900 NOT POSSIBLE 156 ft 47.5 m 250 ft 76.2 m
NOTE:ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF AVAILABLE DISTANCE
RUNWAYCENTERLINE
> 4.5 m(15 ft)
4.5 m(15 ft)
4.5 m(15 ft)
TODA
ASDA
25°
180˚ Turn on Runway WidthFIGURE-4-7-0-991-003-A01
4-7-0Page 4
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4-8-0 Aircraft Mooring
**ON A/C A350-900
Aircraft Mooring
1. This section provides information on aircraft mooring.
4-8-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
TOWING FITTING
A
B
B
FLAG
MOORING
A
POINT
TOWINGFITTING
SLING
HOOK
HOOK PIN
MOVABLEPIN
REMOVE BEFORE FLIGHT
P_AC_040800_1_0010001_01_00
Aircraft MooringFIGURE-4-8-0-991-001-A01
4-8-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
TERMINAL SERVICING
5-1-0 Aircraft Servicing Arrangements
**ON A/C A350-900
Aircraft Servicing Arrangements
1. This section provides typical ramp layouts, showing the various GSE items in position during typicalturn round scenarios.These ramp layouts show typical arrangements only. Each operator will have its own specificrequirements/regulations for the positioning and operation on the ramp.
This table gives the symbols used on servicing diagrams.
Ground Support Equipment
AC AIR CONDITIONING UNITAS AIR START UNIT
BULK BULK TRAINCAT CATERING TRUCK
CB CONVEYOR BELTCLEAN CLEANING TRUCK
FUEL FUEL HYDRANT DISPENSER or TANKERGPU GROUND POWER UNIT
LDCL LOWER DECK CARGO LOADERLV LAVATORY VEHICLE
PBB PASSENGER BOARDING BRIDGEPS PASSENGER STAIRS
TOW TOW TRACTORULD ULD TRAINWV POTABLE WATER VEHICLE
5-1-0Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-1-1 Typical Ramp Layout (Open Apron)
**ON A/C A350-900
Typical Ramp Layout (Open Apron)
1. This section gives the typical ramp layout (open apron).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.50 m (24.61 ft.)from the aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).
5-1-1Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-1-2 Typical Ramp Layout (Gate)
**ON A/C A350-900
Typical Ramp Layout (Gate)
1. This section gives the baseline ramp layout (gate).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.50 m (24.61 ft.)from the aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).
5-1-2Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-2-0 Terminal Operations - Full Servicing Turn Round Time
**ON A/C A350-900
Terminal Operations - Full Servicing Turn Round Time
1. This section provides a typical turn round time chart showing the typical time for ramp activitiesduring aircraft turn round.Actual times may vary due to each operator’s specific practice, resources, equipment and operatingconditions.
2. Assumptions used for full servicing turn round time chart
A. PASSENGER HANDLING315 pax: 48 B/C + 267 Y/C.All passengers deplane and board the aircraft.2 Passenger Boarding Bridges (PBB) used at doors L1 and L2.Equipment positioning/removal + opening/closing door = + 3 min.No Passenger with Reduced Mobility (PRM) on boardDeplaning:- 158 pax at door L1,- 157 pax at door L2,- Deplaning rate = 25 pax/min per door,- Priority deplaning for premium passengers.Boarding:- 158 pax at door L1,- 157 pax at door L2,- Boarding rate = 15 pax/min per door,- Last Pax Seated Allowance (LPS) + headcounting = + 4 min.
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
- Loading = 2.8 min/pallet.
C. REFUELLING81000 l (21398 US gal) at 50 psig (3.45 bars-rel).Dispenser positioning/removal = + 3 min.
D. CLEANINGCleaning is performed in available time.
E. CATERING3 catering trucks for servicing galleys simultaneously at doors R1, R2 and R4.Equipment positioning + door opening = + 5 min.Closing door + equipment removal = + 3 min.Full Size Trolley Equivalent (FSTE) to unload and load: 42 FSTE:- 10 FSTE at door R1,- 7 FSTE at door R2,- 23 FSTE at door R4.Time for trolley exchange = 1.5 min per FSTE.
F. GROUND HANDLING / SERVICING. GENERAL.Start of operations:- Bridges/Stairs: t0=0,- Other equipment: t = t0 + 1 min.Ground Power Unit (GPU): up to 2 × 90 kVA.Air Conditioning: up to 2 hoses.Potable water servicing: 100% uplift, 1060 l (280 US gal).Toilet servicing: draining + rinsing.
5-2-0Page 2
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
0 10 20 30 40 50 60 70
DEPLANING/BOARDING AT L1
HEADCOUNTING
CATERING AT R1
CLEANING
CARGO FWD CC
BULK
REFUELLING
POTABLE WATER SERVICING
TOILET SERVICING
DEPLANING/BOARDING AT L2
CATERING AT R2
CATERING AT R4
CARGO AFT CC
TRT : 61 min
POSITIONING/REMOVAL
ACTIVITY
AVAILABLE TIME
CRITICAL PATH
P_AC_050200_1_0010001_01_01
Full Servicing Turn Round Time ChartFIGURE-5-2-0-991-001-A01
5-2-0Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-3-0 Terminal Operations - Transit Turn Round Time
**ON A/C A350-900
Terminal Operations - Transit Turn Round Time
1. This section provides a typical turn round time chart showing the typical time for ramp activitiesduring aircraft turn round.Actual times may vary due to each operator’s specific practice, resources, equipment and operatingconditions.
2. Assumptions used for transit turn round time chart
A. PASSENGER HANDLING315 pax: 48 B/C + 267 Y/C.50% passengers deplane and board the aircraft.1 Passenger Boarding Bridge (PBB) used at Door L2.Equipment positioning/removal + opening/closing door = + 3 min.No Passenger with Reduced Mobility (PRM) on board.Deplaning:- 158 pax at door L2,- Deplaning rate = 25 pax/min per door.Boarding:- 158 pax at door L2,- Boarding rate = 15 pax/min per door,- Last Pax Seated Allowance (LPS) + headcounting = + 4 min.
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
D. CLEANINGCleaning is performed in available time.
E. CATERINGOne catering truck for servicing the galleys as required.
F. GROUND HANDLING / SERVICING. GENERALStart of operations:- Bridges: t0 = 0,- Other equipment: t = t0 + 1 min.Ground Power Unit (GPU): up to 2 × 90 kVA.Air conditioning: up to 2 hoses .No potable water servicing.No toilet servicing.
5-3-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
0 5 15 20 25 30 35
DEPLANING/BOARDING AT L2
TRT : 30 min
POSITIONING/REMOVAL
ACTIVITY
10
P_AC_050300_1_0010002_01_01
HEADCOUNTING
CATERING
CLEANING
CARGO AFT CC
BULK
AVAILABLE TIME
AVAILABLE TIME
Transit Turn Round TimeFIGURE-5-3-0-991-001-B01
5-3-0Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-0 Ground Service Connections layout
**ON A/C A350-900
Ground Service Connections layout
1. This section gives the ground service connections layout.
5-4-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
1 − GROUNDING POINT NLG2 − GROUND ELECTRICAL POWER CONNECTORS
4 − VFG OIL SERVICING5 − STARTER OIL SERVICING6 − ENGINE OIL SERVICING7 − AIR START UNIT CONNECTORS
10 − PRESSURE REFUEL CONNECTORS (LH WING) − OPTION11 − GROUNDING POINT MLG12 − REFUEL/DEFUEL CONTROL PANEL13 − HYDRAULIC SERVICING PANEL14 − GREEN HYDRAULIC GROUND CONNECTOR
16 − POTABLE WATER SERVICING PANEL17 − WASTE WATER SERVICING PANEL18 − APU OIL SERVICING
1 2 4−5 8 11 12−14 16 17 18
1510
P_AC_050400_1_0010001_01_01
Ground Service Connections layoutFIGURE-5-4-0-991-001-A01
5-4-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-1 Grounding Points
**ON A/C A350-900
Grounding Points
1. Grounding (Earthing) Point Locations
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
On Nose LandingGear
4.42 m(14.5 ft.)
0.07 m(0.23 ft.)
1.06 m(3.48 ft.)
On Left MainLanding Gear Leg
32.95 m(108.1 ft.)
5.59 m(18.34 ft.)
1.55 m(5.09 ft.)
On Right MainLanding Gear Leg
32.95 m(108.1 ft.)
5.59 m(18.34 ft.)
1.55 m(5.09 ft.)
A. The grounding (earthing) stud on each landing gear is designed for use with a clip-on connector,such as an Appleton TGR.
B. The grounding studs are used to connect the aircraft to approved ground connection on theramp or in the hangar for:
(1) Refuel/defuel operations
(2) Maintenance operations
(3) Bad weather conditions.
NOTE : In all other conditions, the electrostatic discharge through the tire is sufficient.
5-4-1Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
A
A
B
C
B
GROUNDING (EARTHING) POINT
C
P_AC_050401_1_0010001_01_00
Ground Point NLGFIGURE-5-4-1-991-001-A01
5-4-1Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
A
A
A
B
C
LH SHOWN
GROUNDING (EARTHING) POINT
B
C
RH SYMMETRICAL
P_AC_050401_1_0020001_01_00
Ground Point MLGFIGURE-5-4-1-991-002-A01
5-4-1Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-2 Hydraulic System
**ON A/C A350-900
Hydraulic System
1. Ground Service Panel
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
Green HydraulicGroundAccess Door:197 LB
36.37 m(119.32 ft.)
0.61 m(2.0 ft.)
2.39 m(7.84 ft.)
Yellow HydraulicGroundAccess Door:194 KB
30.35 m(99.57 ft.)
1.51 m(4.95 ft.)
2.24 m(7.35 ft.)
Hydraulic ReservoirServicingAccess Door:197 LB
36.42 m(119.49 ft.)
0.87 m(2.85 ft.)
2.51 m(8.23 ft.)
A. Reservoir pressurization
(1) One connector ISO 4570, 1/4 in.
B. Reservoir filling
(1) One connector AE96993E, 1/4 in.
5-4-2Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
RESERVOIR FILLINGCONNECTOR
LOW PRESSURE CONNECTOR
HIGH PRESSURE CONNECTOR
P_AC_050402_1_0010001_01_00
Green Ground Service PanelFIGURE-5-4-2-991-001-A01
5-4-2Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
HIGH PRESSURE CONNECTORLOW PRESSURE CONNECTOR
P_AC_050402_1_0020001_01_00
Yellow Ground Service PanelFIGURE-5-4-2-991-002-A01
5-4-2Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-3 Electrical System
**ON A/C A350-900
Electrical System
1. Electrical System
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
A/C ExternalPowerAccess Door:122 AR
6.63 m(21.75 ft.)
0.91 m(2.99 ft.)
2.58 m(8.46 ft.)
A. External power receptacle :
(1) Two standard ISO 461 Style3 --- 90 kVA each.
B. Power supply :
(1) Three-phase, 115 V, 400 Hz.
C. Electrical connectors for servicing :
(1) AC outlets : HUBBELL 5258
(2) DC outlets : HUBBELL 7472
5-4-3Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
122AR
A
925VU
FWD
A
ELECTRICAL POWERRECEPTACLES
P_AC_050403_1_0010001_01_01
Electrical Service PanelFIGURE-5-4-3-991-001-A01
5-4-3Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
A
B
C
Z190
B
C
A 198QR
198PR
198VR
SAFETY PIN
P_AC_050403_1_0030001_01_00
RATFIGURE-5-4-3-991-003-A01
5-4-3Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-4 Oxygen System
**ON A/C A350-900
Oxygen System
1. Oxygen systemGet access to the forward lower-deck cargo-compartment.The access panel to the crew oxygen servicing point is located on the rear triangular area of the FWDcargo door.
5-4-4Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
Z130
FR20
FR30
B
A
A
B
CREW OXYGEN
CREW OXYGENFILLING PORT
FILLING GAGE
FR28
FR29
P_AC_050404_1_0010001_01_00
Oxygen SystemFIGURE-5-4-4-991-001-A01
5-4-4Page 2
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_050406_1_0020001_01_00
HIGH PRESSURE AIR CONNECTORS
High Pressure Preconditioned AirFIGURE-5-4-6-991-002-A01
5-4-6Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-7 Potable Water System
**ON A/C A350-900
Potable Water System
1. Potable Water System
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
Potable WaterGround ServiceAccess Door:164 AR
50.2 m(164.7 ft.)
1.6 m(5.25 ft.)
3.3 m(10.83 ft.)
A. Technical SpecificationsConnectors :
(1) Fill/drain nipple, ISO 17775, 3/4 in.
(2) Overflow, SAE AS5132-16
B. Capacity :
(1) Standard configuration --- 2 tanks: 1060 l (280 USgal)
(2) Optional --- 2 tanks: 1500 l (396 USgal)
C. Filling pressure :
(1) Max filling pressure: 8.60 bar (125 psi)
5-4-7Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
FR86FR85
FR84
FR71
164AR
A
Z160
A
FWD
FILL/DRAIN PORT
PANELINDICATION
WATERPOTABLE
NIPPLEOVERFLOW
FILL STOP DRAIN
P_AC_050407_1_0010001_01_00
Potable Water Ground Service PanelFIGURE-5-4-7-991-001-A01
5-4-7Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
FR12FR13
Z120
DRAIN PORT
A
A
P_AC_050407_1_0020001_01_00
Forward Drain panelFIGURE-5-4-7-991-002-A01
5-4-7Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
Z170
A
A
POTABLEWATER TANK
FR86
FR89
FR93
P_AC_050407_1_0030001_01_00
Potable Water Tanks LocationFIGURE-5-4-7-991-003-A01
5-4-7Page 4
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-8 Oil System
**ON A/C A350-900
Oil System
1. Engine Oil Servicing
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
Oil Engine 1Access Door:415 BR
24.75 m(81.2 ft.)
8.6 m(28.22 ft.)
3.23 m(10.6 ft.)
Oil Engine 2Access Door:425 BR
24.68 m(80.97 ft.)
12.29 m(40.32 ft.)
3.23 m(10.6 ft.)
2. VFG Oil Servicing
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
2 VFG on Engine 1Fan Cowl:415 AL
24.32 m(79.79 ft.)
11.02 m(36.15 ft.)
1.22 m(4.0 ft.)
2 VFG on Engine 2Fan Cowl:425 AL
24.34 m(79.86 ft.)
9.86 m(32.35 ft.)
1.22 m(4.0 ft.)
3. Starter Oil Servicing
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
Starter Engine 1Fan Cowl:415 AL
24.6 m(80.71 ft.)
10.57 m(34.68 ft.)
1.08 m(3.54 ft.)
Starter Engine 2Fan Cowl:425 AL
24.6 m(80.71 ft.)
10.31 m(33.83 ft.)
1.08 m(3.54 ft.)
5-4-8Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
4. APU Oil Servicing
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
APUAccess Door316 BR
62.52 m(205.12 ft.)
0.48 m(1.57 ft.)
6.45 m(21.16 ft.)
5-4-8Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_050408_1_0010001_01_00
OIL FILLER CAP
OIL LEVELSIGHT GLASS
OIL TANK
Engine Oil ServicingFIGURE-5-4-8-991-001-A01
5-4-8Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_050408_1_0020001_01_00
PRESSURE FILL
FILTER BOWL
OVERFLOW/STANDPIPE
DISCONNECT RESET HANDLE
SIGHT GLASS
DRAIN
TYPICAL
VFG Oil ServicingFIGURE-5-4-8-991-002-A01
5-4-8Page 4
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
OIL DRAIN PLUG
MAGNETIC CHIP DETECTOR
PRESSURE FILL PORT
PRESSURE SPILL PORT
A
A
P_AC_050408_1_0030001_01_01
Starter Oil ServicingFIGURE-5-4-8-991-003-A01
5-4-8Page 5
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_050408_1_0040001_01_00
FILL CAP
SIGHT GLASS
APU Oil ServicingFIGURE-5-4-8-991-004-A01
5-4-8Page 6
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-4-9 Vacuum Toilet System
**ON A/C A350-900
Vacuum Toilet System
1. Waste Water System
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSER SIDE L SIDE
MEAN HEIGHTFROM GROUND
Waste WaterGround ServiceAccess Door:171 AL
52.21 m(171.29 ft.) on centerline
3.69 m(12.11 ft.)
A. Connectors :
(1) Draining, ISO 17775, 4 in
(2) Flushing and Filling, ISO 17775, 1 in
B. Capacity per tank (two tanks), 595 l (157.19 USgal)
C. Waste tank --- rinsing :
(1) Operating pressure, 3.45 bar (50.04 psi)
D. Waste precharge per tank (two tanks), 23 l (6.08 USgal)
5-4-9Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_050409_1_0010001_01_00
WASTE DRAINCONNECTION
FILL AND RINSECONNECTION
CONTROLLEVER
Ground Service PanelFIGURE-5-4-9-991-001-A01
5-4-9Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
Z170
A
A
WASTE TANK
FR86
FR89
FR93
P_AC_050409_1_0020001_01_00
Waste Tanks LocationFIGURE-5-4-9-991-002-A01
5-4-9Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-6-0 Ground Pneumatic Power Requirements
**ON A/C A350-900
Ground Pneumatic Power Requirements
1. This document describes the required performance for the ground equipment to maintain the cabintemperature at 27 deg.C (80.6 deg.F) after boarding (Section 5.7 - steady state), and provides thetime needed to cool down or heat up the aircraft cabin to the required temperature (Section 5.6 -dynamic cases with aircraft empty).
ABBREVIATION DEFINITION
A/C Aircraft
AHM Aircraft Handling Manual
GC Ground ConnectionGSE Ground Service Equipment
IFE In-Flight Entertainment
LP Low PressureOAT Outside Air Temperature
PCA Preconditioned Air
A. The air flow rates and temperature requirements for the GSE, provided in Sections 5.6 and 5.7,are given at A/C ground connection.
NOTE : The cooling capacity of the equipment (kW) is only indicative and is not sufficient byitself to ensure the performance (outlet temperature and flow rate combinations arethe requirements needed for ground power). An example of cooling capacitycalculation is given in Section 5.7.
B. The air flow rates and temperature requirements for the GSE are given for the A/C in theconfiguration ”2 LP ducts connected”.
NOTE : The maximum air flow is driven by the limitation on pressure at ground connection.
C. For temperature below 2 deg.C (35.6 deg.F), the ground equipment shall be compliant with theAirbus document ”Subfreezing PCA Carts -- Compliance Document for Suppliers” (contactAirbus to obtain this document) defining all the requirements to which Subfreezing Pre-Conditioning Air equipment needs to comply to allow its use on Airbus aircraft.These requirements come in addition to the functional specifications included in the IATAAHM997.
2. Ground Pneumatic Power Requirements - HeatingThis section provides the ground pneumatic power requirements for heating (pull up) the cabin,initially at OAT, up to 21 deg.C (69.8 deg.F) FIGURE 5-6-0-991-001-A Sheet 1.
3. Ground Pneumatic Power Requirements - CoolingThis section provides the ground pneumatic power requirements for cooling (pull down) the cabin,initially at OAT, down to 27 deg.C (80.6 deg.F) FIGURE 5-6-0-991-001-A Sheet 2.
5-6-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
PU
LL U
P P
ER
FO
RM
AN
CE
(+
70°
C (
+15
8°F
) G
C O
UT
LET
)
AIR FLOW AT GC (kg/s)
TIM
E T
O H
EA
T C
AB
IN T
O +
21°
C (
+69
.8°
F)
ON
GR
OU
ND
(m
in)
PU
1: O
AT
ISA
−38
°C
(−
36.4
°F
); G
C O
UT
LET
+70
°C
(+
158°
F);
A/C
EM
PT
Y; I
FE
OF
F; N
O S
OLA
R L
OA
D; L
IGH
TS
ON
;R
EC
IRC
ULA
TIO
N F
AN
S O
N
MA
X A
IR F
LOW
PU
1 "I
SA
−38
°C
(−
36.4
°F
)"
PU
2 "I
SA
−45
°C
(−
49°
F )
"
3035
4045
5055
6065
2.5
2.7
2.9
3.1
3.3
3.5
3.7
3.9
4.1
4.3
4.5
PU
LL U
P C
AS
ES
:
PU
2: O
AT
ISA
−45
°C
(−
49°
F);
GC
OU
TLE
T +
70°
C (
+15
8°F
); A
/C E
MP
TY
; IF
E O
FF
; NO
SO
LAR
LO
AD
; LIG
HT
S O
N;
RE
CIR
CU
LAT
ION
FA
NS
ON
P_AC_050600_1_0010001_01_02
Ground Pneumatic Power RequirementsHeating (Sheet 1 of 2)
FIGURE-5-6-0-991-001-A01
5-6-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
PU
LL D
OW
N P
ER
FO
RM
AN
CE
TIM
E T
O C
OO
L C
AB
IN T
O +
27°
C (
+80
.6°
F)
ON
GR
OU
ND
(m
in)
AIR FLOW AT GC (kg/s)M
AX
AIR
FLO
W
PD
1 "I
SA
+23
°C
(+
73.4
°F
) / G
C O
UT
LET
+2°
C (
+35
.6°
F)"
PD
2 "I
SA
+23
°C
(+
73.4
°F
) / G
C O
UT
LET
−10
°C
(+
14°
F)"
PD
3 "I
SA
+23
°C
(+
73.4
°F
) / G
C O
UT
LET
−20
°C
(−
4°F
)"
1020
3040
5060
7080
902.
5
2.7
2.9
3.1
3.3
3.5
3.7
3.9
4.1
4.3
4.5
PD
1: O
AT
ISA
+23
°C
(+
73.4
°F
); G
C O
UT
LET
+ 2
°C
(+
35.6
°F
); A
/C E
MP
TY
; IF
E O
FF
; SO
LAR
LO
AD
; LIG
HT
S O
N;
RE
CIR
CU
LAT
ION
FA
NS
ON
PU
LL D
OW
N C
AS
ES
:
PD
2: O
AT
ISA
+23
°C
(+
73.4
°F
); G
C O
UT
LET
−10
°C
(+
14°
F);
A/C
EM
PT
Y; I
FE
OF
F; S
OLA
R L
OA
D; L
IGH
TS
ON
;R
EC
IRC
ULA
TIO
N F
AN
S O
NP
D3:
OA
T IS
A +
23°
C (
+73
.4°
F);
GC
OU
TLE
T −
20°
C (
−4°
F);
A/C
EM
PT
Y; I
FE
OF
F; S
OLA
R L
OA
D; L
IGH
TS
ON
;R
EC
IRC
ULA
TIO
N F
AN
S O
N
P_AC_050600_1_0010001_02_01
Ground Pneumatic Power RequirementsCooling (Sheet 2 of 2)
FIGURE-5-6-0-991-001-A01
5-6-0Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-7-0 Preconditioned Airflow Requirements
**ON A/C A350-900
Preconditioned Airflow Requirements
1. This section provides the necessary information for the design of a ground unit; it gives the air flowrate and temperature combinations needed to maintain the cabin temperature at 27 deg.C (80.6deg.F).These settings are not intended to be used for operation (they don’t substitute to the settings givenin the AMM):They are issued from theoretical simulations and give the picture of a real steady state.For the air conditioning operation, Airlines will refer to the AMM that details the procedure and thePCA settings to maintain the cabin temperature below 27 deg.C (80.6 deg.F) during boarding(therefore it is not a steady state).
5-7-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-8-0 Towing Requirements
**ON A/C A350-900
Towing Requirements
1. This section provides information on aircraft towing.
The A350 is designed with means for conventional or towbarless towing.
It is possible to tow or push the aircraft, at maximum ramp weight with engines at zero or up to idlethrust, using a towbar attached to the NLG.One towbar fitting is installed at the front of the leg (optional towing fitting for towing from the rearof the NLG available).
The first part of this section shows the chart to determine the draw bar pull and tow tractor massrequirements as function of the following physical characteristics:- Aircraft weight,- Slope,- Number of engines at idle.
2. Towbar design guidelines
The A350 towbar requirements are identical to the towbar requirements for the long range aircraft.- ISO 8267-1, ”Aircraft - Towbar Attachment Fitting - Interface Requirements - Part 1: Main Line
Aircraft”,- ISO 9667, ”Aircraft Ground Support Equipment - Towbars”,- IATA Airport Handling Manual AHM 958, ”Functional Specification for an Aircraft Towbar”.
A conventional type towbar is required which should be equipped with a damping system to protectthe NLG against jerks and with towing shear pins :- A traction shear pin calibrated at 28 620 daN (64 340 lbf),- A torsion pin calibrated at 3 130 m.daN (27 7028 lbf.in).The towing head is designed according to ISO 8267--1 (Aircraft Weight Category III)..
5-8-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
TOTAL TRACTION WHEEL LOAD ( x 1000 kg ) No. OF ENGINES SLOPE ( % )
DRAWBAR PULL ( x 1000 kg )
ICE = 0.05
A/C WEIGHT ( x 1000 kg )
EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A350 AT 250 000 kg, AT 2% SLOPE,1 ENGINE AT IDLE AND FOR WET TARMAC CONDITIONS:
− ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (250 000 kg),− FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (2%),− FROM THIS POINT OBTAINED DRAW A STRAIGHT HORIZONTAL LINE UNTIL No. OF ENGINES AT IDLE = 2,− FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUESTED NUMBER OF ENGINES (1),− FROM THIS POINT DRAW A STRAIGHT HORIZONTAL LINE TO THE DRAWBAR PULL AXIS,− THE Y−COORDINATE OBTAINED IS THE NECESSARY DRAWBAR PULL FOR THE TRACTOR (17 000 kg),− SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE. THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (29 800 kg).
AT IDLE
P_AC_050800_1_0010001_01_00
29.8
17.0
280
255
230
205
180
155
130
2% SLOPE
HARD SNOW = 0.2
BREAKWAY RESISTANCE 4%# OF ENGINES ON FOR PB: 1ENGINE THRUST 811 daN
1 ENGINE ON
WET
CO
NC
RET
E
= 0
.57
DR
Y C
ON
CR
ETE
= 0.
8250
Towing RequirementsFIGURE-5-8-0-991-001-A01
5-8-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
5-9-0 De-icing and External cleaning
**ON A/C A350-900
De-icing and External cleaning
1. De-Icing and External Cleaning on Ground.The mobile equipment for aircraft de-icing and external cleaning must be capable of reaching heightsup to approximately 17 m (56 ft.).
2. De-Icing
AIRCRAFT TYPE Wing Top Surface(Both Sides)
Wingtip Devices(Both Inside and
(Outside Surfaces)(Both Sides)
HTP Top Surface(Both Sides)
VTP(Both Sides)
A350--900 354 m2(3810 ft.2)
25 m2(269 ft.2)
69 m2(743 ft.2)
102 m2(1098 ft.2)
AIRCRAFT TYPE Fuselage Top Surface(Top Third - 120? Arc)
Nacelle and Pylon(Top Third - 120? Arc)
(All Engines)
Total De-Iced Area
A350--900 357 m2(3843 ft.2)
56 m2(603 ft.2)
962 m2(10355 ft.2)
NOTE : Dimensions are approximate
3. External Cleaning
AIRCRAFTTYPE
Wing TopSurface
(Both Sides)
Wing LowerSurface
(Including FlapTrack Fairing)(Both Sides)
Wingtip Devices(Both Inside
and(OutsideSurfaces)
(Both Sides)
HTP TopSurface
(Both Sides)
HTP LowerSurface
(Both Sides)
A350--900 354 m2(3810 ft.2)
384 m2(4133 ft.2)
25 m2(269 ft.2)
69 m2(743 ft.2)
69 m2(743 ft.2)
AIRCRAFT TYPE VTP(Both Sides)
Fuselage andBelly Fairing
Nacelle and Pylon(All Engines)
Total Cleaned Area
A350--900 102 m2(1098 ft.2)
1073 m2(11550 ft.2)
166 m2(1787 ft.2)
2242 m2(24133 ft.2)
NOTE : Dimensions are approximate
5-9-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
OPERATING CONDITIONS
6-4-0 APU Exhaust Velocities and Temperatures
**ON A/C A350-900
APU Exhaust Velocities and Temperatures
1. This section gives APU exhaust velocities and temperatures.
6-4-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_060400_1_0010001_01_00
0 5 10 15 200
5
10
0
0 10
0 5 10 15 200
5
10
0
FD
FD
[m]
[ft]
[m] [ft]
[m]
[ft]
0
[m] [ft]
15 m/s30.5 m/s46 m/s61 m/s
93°C
149°C204°C
315.5°C427°C
260°C
20 30 40 50 60
10
20
30
40
10
20
30
40
10 20 30 40 50 60
APU Exhaust Velocities and TemperaturesFIGURE-6-4-0-991-001-A01
6-4-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
PAVEMENT DATA
7-1-0 General Information
**ON A/C A350-900
General Information
1. A brief description of the pavement charts that follow will help in airport planning.
To aid in the interpolation between the discrete values shown, each aircraft configuration is shownwith a minimum range of five loads on the MLG.
All curves on the charts represent data at a constant specified tire pressure with:- The aircraft loaded to the maximum ramp weight,- The CG at its maximum permissible aft position.Pavement requirements for commercial aircraft are derived from the static analysis of loads imposedon the MLG struts.
Landing Gear Footprint.Section 7-2-0 , presents basic data on the landing gear footprint configuration, maximum rampweights and tire sizes and pressures.
Maximum Pavement Loads.Section 7-3-0, shows maximum vertical and horizontal pavement loads for certain critical conditionsat the tire-ground interfaces.
Landing Gear Loading on Pavement.Section 7-4-0 contains charts to find these loads throughout the stability limits of the aircraft at reston the pavement.These MLG loads are used as the point of entry to the pavement design charts which follow,interpolating load values where necessary.
Flexible Pavement Requirements - US Army Corps of Engineers Design Method.Section 7-5-0 uses procedures in Instruction Report No S-77-1 ”Procedures for Development of CBRDesign Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3.Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007. The report wasprepared by the U.S. Army Corps Engineers Waterways Experiment Station, Soils and PavementLaboratory, Vicksburg, Mississippi”.The line showing 10 000 coverages is used to calculate Aircraft Classification Number (ACN).
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
The flexible pavement charts in Section 7-6-0 show LCN against Equivalent Single Wheel Load(ESWL), and ESWL against pavement thickness.All LCN curves shown in ’Flexible Pavement Requirements’ were developed from a computer programbased on data in International Civil Aviation Organisation (ICAO) document 7920-AN/865/2,Aerodrome manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.
Rigid Pavement Requirements - PCA (Portland Cement Association) Design Method.Section 7-7-0 gives the rigid pavement design curves that have been prepared with the use of theWestergaard Equation.This is in general accordance with the procedures outlined in the Portland Cement Associationpublications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for AirportPavement Design”, (Program PDILB), 1967 both by Robert G. Packard.
Rigid Pavement Requirements - LCN Conversion.Section 7-8-0 gives the rigid pavement requirements.All LCN curves shown in ’Rigid Pavement Requirements - Radius of Relative Stiffness (other valuesof E and µ) - were developed from a computer program based on data in International Civil AviationOrganisation (ICAO) document 7920-AN/865/2, Aerodrome manual, Part 2, ”Aerodrome PhysicalCharacteristics”, Second Edition, 1965.The rigid pavement charts in Section 7-8-0 show LCN against ESWL, and ESWL against radius ofrelative stiffness.
Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness.Section 7-8-1 allow to find the radius of relative stiffness based on other values of E and µ.
Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness (other values of E andµ).The rigid pavement charts show LCN in Section 7-8-2 against ESWL and ESWL against radius ofrelative stiffness affected by the other values of E and µ.
ACN/PCN Reporting System.Section 7-9 provides ACN data prepared according to the ACN/PCN system as referenced in ICAOAnnex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations.” Fourth Edition July 2004,incorporating Amendments 1 to 6.Fourth Edition July 2004, incorporating Amendments 1 to 6. The ACN/PCN system provides astandardized international aircraft / pavement rating system replacing the various S, T, TT, LCN,AUW, ISWL, etc., rating systems used throughout the world.ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.An aircraft having an ACN equal to or less than the PCN can operate without restriction on thepavement.Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.
7-1-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
The derived single wheel load is defined as the load on a single tire inflated to 1.25 Mpa (181 psi)that would have the same pavement requirements as the aircraft.Computationally the ACN/PCN system uses PCA program PDILB for rigid pavements and S-77-1 forflexible pavements to calculate ACN values.The Airport Authority must decide on the method of pavement analysis and the results of theirevaluation shown as follows:
PCN
PAVEMENT TYPESUBGRADECATEGORY
TIRE PRESSURECATEGORY
EVALUATIONMETHOD
R - Rigid A - High W - No Limit T - Technical
F - Flexible B - Medium X - To 1.5 Mpa (217psi)
U - Using Aircraft
C - Low Y - To 1 Mpa (145 psi)
D - Ultra Low Z - To 0.5 Mpa (73 psi)
Section 7-9-0 shows the aircraft ACN values for flexible pavements.The four subgrade categories are:- A . High Strength CBR 15- B . Medium Strength CBR 10- C . Low Strength CBR 6- D . Ultra Low Strength CBR 3
Section 7-9-1 shows the aircraft ACN values for rigid pavements.The four subgrade categories are:- A . High Strength Subgrade k = 150 MN/m3 (550 pci )- B . Medium Strength Subgrade k = 80 MN/m3 (300 pci )- C . Low Strength Subgrade k = 40 MN/m3 (150 pci )- D . Ultra Low Strength Subgrade k = 20 MN/m3 (75 pci )
7-1-0Page 3
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-2-0 Landing Gear Footprint
**ON A/C A350-900
Landing Gear Footprint
1. This section gives data about the landing gear footprint in relation with the aircraft MRW and tiresizes and pressures.
7-2-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
MAXIMUM RAMP WEIGHT
PERCENTAGE OF WEIGHTON MAIN GEAR GROUP
NOSE GEAR TIRE SIZE
NOSE GEAR TIRE PRESSURE
MAIN GEAR TIRE SIZE
MAIN GEAR TIRE PRESSURE
268 900 kg(592 825 lb)
SEE SECTION 7−4−0
1050x395R16 28PR
12.2 bar (177 psi)
1400x530R23 42PR
16.6 bar (241 psi)
10.600 m(34.777 ft)
28.665 m(94.050 ft)
1.735 m(5.692 ft) 2.040 m
(6.693 ft)
0.748 m(2.454 ft)
P_AC_070200_1_0010001_01_01
Landing Gear FootprintFIGURE-7-2-0-991-001-A01
7-2-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-3-0 Maximum Pavement Loads
**ON A/C A350-900
Maximum Pavement Loads
1. This section shows maximum vertical and horizontal pavement loads for some critical conditions atthe tire-ground interfaces.
7-3-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
H
V(M
G)
(1)
(2)
NO
TE
:
MR
W =
2
68 9
00 k
g
F
WD
CG
= 2
5.5
% M
AC
AT
A/C
WE
IGH
T=
268
900
kg
ALL
LO
AD
S C
ALC
ULA
TE
D U
SIN
G A
IRC
RA
FT
MA
XIM
UM
RA
MP
WE
IGH
T
V(N
G)
V(M
G)
H
MA
XIM
UM
VE
RT
ICA
L M
AIN
GE
AR
GR
OU
ND
LO
AD
AT
MO
ST
AF
T C
G
MA
XIM
UM
HO
RIZ
ON
TA
L G
RO
UN
D L
OA
D F
RO
M B
RA
KIN
G
12
34
56
MO
DE
L
lbkg
lbkg
VN
G
kglb
lbkg
lbkg
lbkg
AT
INS
TA
NT
AN
EO
US
BR
AK
ING
CO
EF
FIC
IEN
T =
0.8
VM
G (
PE
R S
TR
UT
)H
(P
ER
ST
RU
T)
ST
AT
IC L
OA
DA
T M
AX
AF
TC
.G. (
2)
MA
XIM
UM
RA
MP
WE
IGH
T
ST
AT
IC L
OA
DA
T M
OS
T F
WD
C.G
. (1)
MA
XIM
UM
VE
RT
ICA
L N
OS
E G
EA
R G
RO
UN
D L
OA
D A
T M
OS
T F
OR
WA
RD
CG
592
825
268
900
51 5
7523
400
85 5
0038
780
277
700
125
960
ST
AT
IC B
RA
KIN
G
DE
CE
LER
AT
ION
ST
EA
DY
BR
AK
ING
@ 1
0 ft/
DE
CE
LER
AT
ION
s²@
10
ft/s²
V(N
G)
92 1
2541
790
222
150
100
770
MR
W =
2
68 9
00 k
g
A
FT
CG
= 3
3 %
MA
C A
T A
/C W
EIG
HT
=26
8 90
0 kg
−90
0
P_AC_070300_1_0010001_01_01
Maximum Pavement LoadsFIGURE-7-3-0-991-001-A01
7-3-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-4-0 Landing Gear Loading on Pavement
**ON A/C A350-900
Landing Gear Loading on Pavement
1. This section gives data about the landing gear loading on pavement.
Example, see FIGURE 7-4-0-991-001-A, calculation of the total weight on the MLG for:- An aircraft with a MTOW of 268000 kg (590839 lb)- The aircraft gross weight is 190000 kg (418879 lb)- A percentage of weight on the MLG of 93.68 %.The total weight on the MLG group is 178000 kg (392423 lb).
7-4-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070400_1_0010001_01_00
5 10 15 20 25 30 35 40 45 50
120 120
125
130
135
140
145
150
155
160
165
170
175
180
185
190
195
200
205
210
215
220
225
230
235
240
245
250
255
260
265
270
84
125
130
135
140
145
150
155
160
165
170
175
180
185
190
195
200
205
210
215
220
225
230
235
240
245
250
255
260
265
270
86 88 90 92 94 96 98 100
AIR
CR
AF
T G
RO
SS
WE
IGH
T (
x 10
00 k
g)
PERCENTAGE OF WEIGHT ON MAIN GEAR
PERCENTAGE MAC
WE
IGH
T O
N M
AIN
LA
ND
ING
GE
AR
(x
1000
kg)
MTOW − 268 000 kg CG FOR ACNCALCULATION
MLW − 205 000 kg
MZFW − 192 000 kg
LANDING
TAKE OFF
Landing Gear Loading on PavementMTOW 268 000 kg
FIGURE-7-4-0-991-001-A01
7-4-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-5-0 Flexible Pavement Requirements - US Army Corps of Engineers Design Method S-77-1
**ON A/C A350-900
Flexible Pavement Requirements - US Army Corps of Engineers Design Method S-77-1
1. This section gives data about the flexible pavement requirements.They are calculated with the US Army Corps of Engineers Design Method.To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annualdeparture level and the weight on one MLG.The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).The procedure that follows is used to develop flexible pavement design curves:- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random
line is made to show 10 000 coverages,- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shown
on the graph.Example, see FIGURE 7-5-0-991-001-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- A CBR value of 10,- An annual departure level of 3 000,- The load on one MLG of 110000 kg (242509 lb).The required flexible pavement thickness is 593 mm (23 in.).
7-5-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
SUBGRADE STRENGTH − CBR
3 6 10 15 20 30 40 60 80
[in]
[cm]
FLEXIBLE PAVEMENT THICKNESS
1400x530R23 42PR TIRESTIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)
10 15 20 30 40 60 80 100 120 150 180
3 6 10 15 20 30 40 60 80
WEIGHT ON ONE MAIN LANDING GEAR 125 960 kg (277 700 lb) 110 000 kg (242 500 lb)
90 000 kg (198 425 lb) 80 000 kg (176 375 lb)
10 000 COVERAGESUSED FOR ACNCALCULATIONS
ANNUALDEPARTURES*1 2003 0006 00015 00025 000*20 YEARPAVEMENT LIFE
ALPHA FACTOR = 0.8
P_AC_070500_1_0010001_01_01
100 000 kg (220 450 lb)
MAXIMUM POSSIBLE MAIN GEAR LOAD AT
MAXIMUM RAMPWEIGHT AND AFT CG
Flexible Pavement RequirementsMTOW 268 000 kg
FIGURE-7-5-0-991-001-A01
7-5-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
1. This section gives data about the flexible pavement requirements for Load Classification Number(LCN) conversion.They are calculated with the LCN conversion method.To find the aircraft weight that a flexible pavement can support, you must know the LCN of thepavement and the thickness.Example, see FIGURE 7-6-0-991-001-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb)- The flexible pavement thickness is 1397 mm (55 in.) with a related LCN of 154.The weight on one MLG is 110000 kg (242509 lb).
The following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”.In order to use the system accurately you should know the total pavement thickness for flexiblepavement.However, the pavement thickness for a particular runway are not frequently published in the standardairport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard thickness (20 inches) when determining the LCNand the ESWL of the aircraft.
If the LCN for an intermediate weight between MRW and the empty weight of the aircraft is requiredor if the real thickness is known, refer to charts in FIGURE 7-6-0-991-001-A.
FLEXIBLE PAVEMENTESWLAIRCRAFT
TYPEWEIGHT
LOAD ONONE MLGLEG (%)
TIREPRESSURE
(Mpa) x 1000 kg x 1000 lbLCN
h =510 mm(20 in.)
A350--900268900 kg(592824 lb) 46.8 31 69.4 116
A350--900142000 kg(313057 lb) 46.8
1.66
17 36.7 68
7-6-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070600_1_0010001_01_00
40708090100
110
120
130
EQUIVALENT SINGLE WHEEL LOAD (1000 lb)
230
70
LOA
D C
LAS
SIF
ICA
TIO
N N
UM
BE
R (
LCN
)
EQUIVALENT SINGLE WHEEL LOAD (1000 kg)
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L LO
AD
S A
RE
DE
RIV
ED
BY
ME
TH
OD
S S
HO
WN
INIC
AO
AE
RO
DR
OM
E M
AN
UA
L P
AR
T 2
PA
R 4
.1.3
S
EC
ON
D E
DIT
ION
196
5
1400
x 5
30R
23 4
2PR
TIR
ES
TIR
E P
RE
SS
UR
E C
ON
ST
AN
T A
T 1
6.6
bar
(241
psi
)F
LEX
IBLE
PA
VE
ME
NT
TH
ICK
NE
SS
(m
m)
500
750
1000
1500
2500
70
1020
3040
100
8060
50
FLE
XIB
LE P
AV
EM
EN
T T
HIC
KN
ES
S (
in)
60 50150
140
160
2000
200
150
120
100
80
60 50 40 30 20
L
AN
DIN
G G
EA
R 1
25 9
60 k
g (2
77 7
00 lb
) 1
10
00
0 k
g
(2
42
50
0 lb
) 100 0
00 k
g (2
20 4
50 lb
)
90
00
0 k
g
(1
98
42
5 lb
)
80
00
0 k
g
(1
76
37
5 lb
)
WE
IGH
T O
N O
NE
MA
IN
MA
XIM
UM
PO
SS
IBLE
MA
IN G
EA
RLO
AD
AT
MA
XIM
UM
RA
MP
WE
IGH
T A
ND
AF
T C
G
NO
TE
:
Flexible Pavement Requirements - LCNMTOW 268 000 kg
FIGURE-7-6-0-991-001-A01
7-6-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-7-0 Rigid Pavement Requirements - Portland Cement Association Design Method
**ON A/C A350-900
Rigid Pavement Requirements - Portland Cement Association Design Method
1. This section gives data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.They are calculated with the PCA design method.To find a rigid pavement thickness, you must know the Subgrade Modulus (K), the permittedworking stress and the weight on MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on
the right, a random load line is made. This represents the MLG maximum weight to be shown,- A plot is then made of all values of the subgrade modulus (k values),- More load lines for the incremental values of weight on the MLG are made based on the curve for
k= 80MN/m3 already shown on the graph.Example, see FIGURE 7-7-0-991-001-A, calculation of the thickness of the flexible pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 35.15 kg/cm2 (500 lb/in2),- The load on one MLG of 110000 kg (242509 lb).The required rigid pavement thickness is 290 mm (11 in.).
7-7-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070700_1_0010001_01_00
THE VALUES OBTAINED BY USING
FOR LOADS LESS THAN MAXIMUM,
15
14
13
12
11
10
9
8
7
1000
900
800
700
600
500
400
300
200
38
36
34
32
30
28
26
24
22
20
70
65
60
55
50
45
40
35
30
25
20
1518
LANDING GEAR 125 960 kg (277 700 lb) 110 000 kg (242 500 lb)
100 000 kg (220 450 lb) 90 000 kg (198 425 lb) 80 000 kg (176 375 lb)
WEIGHT ON ONE MAIN
NOTES:
THE MAXIMUM LOAD REFERENCELINE AND ANY VALUES FOR K ARE EXACT.
THE CURVES ARE EXACT FOR K = 80 MN/m³BUT DEVIATE SLIGHTLY FOR ANY OTHER VALUES OF K
"DESIGN OF CONCRETE AIRPORT
PAVEMENT DESIGN − PROGRAM
REFERENCE:
PAVEMENTS" AND "COMPUTERPROGRAM FOR AIRPORT
PDILB" PORTLAND CEMENTASSOCIATION
TIRE PRESSURE CONSTANT AT 16.6 bar (241 psi)1400x530R23 42PR TIRES
(cm
)R
IGID
PA
VE
ME
NT
TH
ICK
NE
SS
(in)
(lb/in
²)
ALL
OW
AB
LE W
OR
KIN
G S
TR
ES
S(k
g/cm
²)
MAXIMUM POSSIBLE MAINGEAR LOAD AT MAXIMUMRAMP WEIGHT AND AFT CG
K = 20 MN/m³
K = 40 MN/m³
K = 80 MN/m³
K = 150 MN/m³
Rigid Pavement RequirementsMTOW 268 000 kg
FIGURE-7-7-0-991-001-A01
7-7-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
1. This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness).- For the radius of relative stiffness, see Section 7--8--1,- For the radius of relative stiffness (other values of E and µ), see Section 7--8--2.Example, see FIGURE 7-8-0-991-001-A, calculation of the aircraft weight with the thickness of therigid pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- The radius of relative stiffness is shown at1143 mm (45 in.) with a related LCN of 119.The weight on one MLG is 110000 kg (242509 lb).
The following table provides LCN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”.In order to use the system accurately you should know the total pavement radius of relative stiffness(L-value) for rigid pavement.However, the pavement radius of relative stiffness for a particular runway are not frequently publishedin the standard airport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard radius of relative stiffness (30 inches) whendetermining the LCN and the ESWL of the aircraft.If the LCN for an intermediate weight between maximum ramp weight and the empty weight of theaircraft is required or if the real thickness is known, refer to charts FIGURE 7-8-0-991-001-A.
RIGID PAVEMENTESWL LCN
AIRCRAFTTYPE
WEIGHT
LOAD ONONE MLGLEG (%)
TIREPRESSURE
(Mpa) x 1000 kg x 1000 lb
L =760 mm(30 in.)
A350--900268900 kg(592824 lb) 46.8 28 62 107
A350--900142000 kg(313057 lb) 46.8
1.66
15 33 59
7-8-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070800_1_0010001_01_00
2030405060708090100
110
120
EQUIVALENT SINGLE WHEEL LOAD (1000 lb)
190
5060
7080
40
LOA
D C
LAS
SIF
ICA
TIO
N N
UM
BE
R (
LCN
)
EQUIVALENT SINGLE WHEEL LOAD (1000 kg)
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L LO
AD
S A
RE
DE
RIV
ED
BY
ME
TH
OD
S S
HO
WN
INIC
AO
AE
RO
DR
OM
E M
AN
UA
L P
AR
T 2
PA
R 4
.1.3
S
EC
ON
D E
DIT
ION
196
5
1400
x 5
30R
23 4
2PR
TIR
ES
TIR
E P
RE
SS
UR
E C
ON
ST
AN
T A
T 1
6.6
bar
(241
psi
)R
AD
IUS
OF
RE
LAT
IVE
ST
IFF
NE
SS
(m
m)
750
1000
1250
1500
2000
2500
150
120
100
905141924293439444954
2030
4050
100
9080
7060
RA
DIU
S O
F R
ELA
TIV
E S
TIF
FN
ES
S (
inch
es)
WE
IGH
T O
N O
NE
MA
IN L
AN
DIN
G G
EA
R 1
25 9
60 k
g (2
77 7
00 lb
) 1
10
00
0 k
g
(2
42
50
0 lb
) 100 0
00 k
g (2
20 4
50 lb
) 90 0
00 k
g (1
98 4
25 lb
)
80
00
0 k
g
(1
76
37
5 lb
)
MA
XIM
UM
PO
SS
IBLE
MA
IN G
EA
RLO
AD
AT
MA
XIM
UM
RA
MP
WE
IGH
T A
ND
AF
T C
G
NO
TE
:
Rigid Pavement Requirements - LCNMTOW 268 000 kg
FIGURE-7-8-0-991-001-A01
7-8-0Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-8-1 Radius of Relative Stiffness (L)
**ON A/C A350-900
Radius of Relative Stiffness (L)
1. This section gives the radius of relative stiffness.
7-8-1Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070801_1_0010001_01_00
WHERE
=
E
k
d
Ed4
=
=
=
dk
= 24.1652 4
RIGID PAVEMENT THICKNESS, (in)
YOUNG’S MODULUS = 4 x 10 psi
RADIUS OF RELATIVE STIFFNESS VALUES IN INCHES
L
SUBGRADE MODULUS, lb/in
= POISSON’S RATIO = 0.15
6.06.57.07.5
31.4833.4335.3437.22
29.3031.1132.8934.63
26.4728.1129.7231.29
24.6326.1627.6529.12
23.3024.7426.1527.54
22.2623.6424.9926.32
21.4222.7424.0425.32
20.7222.0023.2524.49
19.1320.3121.4722.61
8.08.59.09.5
39.0640.8842.6744.43
36.3538.0439.7141.35
32.8534.3735.8837.36
30.5731.9933.3934.77
28.9130.2531.5832.89
27.6228.9130.1731.42
26.5827.8129.0330.23
25.7026.9028.0829.24
23.7424.8425.9327.00
10.010.511.011.5
46.1847.9049.6051.28
38.8340.2841.7143.12
36.1437.4838.8140.13
34.1735.4536.7137.95
32.6533.8735.0736.26
31.4232.5933.7534.89
30.3931.5232.6433.74
28.0629.1130.1431.16
12.012.513.013.5
52.9454.5956.2257.83
49.2750.8052.3253.82
44.5245.9047.2748.63
41.4342.7243.9945.26
39.1840.4041.6142.80
37.4438.6039.7540.89
36.0237.1438.2539.35
34.8435.9236.9938.06
32.1733.1734.1635.14
14.014.515.015.5
16.016.517.017.5
55.3156.7858.2559.70
65.6967.2368.7570.26
61.1362.5663.9865.38
49.9851.3152.6353.94
46.5147.7548.9850.20
43.9845.1646.3247.47
55.2456.5357.8159.08
51.4152.6153.8054.98
48.6249.7550.8852.00
42.0243.1544.2645.36
40.4441.5142.5843.64
39.1140.1541.1942.21
36.1237.0838.0338.98
46.4547.5448.6149.68
44.7045.7446.7747.80
43.2344.2445.2446.23
39.9240.8541.7842.70
18.019.020.021.0
22.023.024.025.0
71.7674.7377.6680.55
83.4186.2489.0491.81
66.7869.5472.2774.96
77.6380.2682.8685.44
60.3462.8465.3067.74
70.1472.5274.8777.20
56.1558.4860.7763.04
65.2867.4969.6871.84
53.1155.3157.4759.62
61.7363.8365.9067.95
50.7452.8454.9156.96
58.9860.9862.9664.92
48.8250.8452.8454.81
56.7558.6860.5862.46
54.8956.7558.5960.41
47.2249.1751.1053.01
43.6145.4147.1948.95
50.6952.4154.1155.79
d k=75 k=100 k=150 k=200 k=250 k=300 k=350 k=400 k=550
59.4361.0262.5964.15
42.9744.5746.1647.72
( )L
12 (1 − ) k
REFERENCE: PORTLAND CEMENT ASSOCIATION
Radius of Relative Stiffness (L)FIGURE-7-8-1-991-001-A01
7-8-1Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-8-2 Radius of Relative Stiffness (Other values of E and µ)
**ON A/C A350-900
Radius of Relative Stiffness (Other values of E and µ)
1. The table of Section 7--8--1 radius of relative stiffness, presents L values based on young’s modulus(E) of 4 000 000 psi and poisson’s ratio (µ) of 0.15.
To find L values based on other values of E and µ, see FIGURE 7-8-2-991-001-B.
For example, to find an L value based on an E of 3 000 000 psi, the ”E” factor of 0.931 is multipliedby the L value found in the table of Section 7-8-1 radius of relative stiffness.
The effect of variations of µ on the L value is treated in a similar manner.
7-8-2Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070802_1_0010002_01_00
0 1 2 3 4 50.80
0.85
0.90
0.95
1.00
1.05
1.10EFFECT OF E ON VALUESL
E F
AC
TO
R
0.00 0.05 0.10 0.15 0.20 0.250.995
1.000
1.005
1.010
1.015EFFECT OF L
FA
CT
OR
, POISSON’S RATIO
NOTE: BOTH CURVES ON THIS PAGE ARE USED TO ADJUSTTHE VALUES OF TABLE 7−8−1L
E, YOUNG’S MODULUS (10 psi)
ON VALUES
Radius of Relative Stiffness (Effect E and µ ON ”L” values)FIGURE-7-8-2-991-001-B01
7-8-2Page 2
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-9-0 Aircraft Classification Number - Flexible Pavement
**ON A/C A350-900
Aircraft Classification Number - Flexible Pavement
1. This section gives data about the Aircraft Classification Number (ACN) for flexible pavement for anaircraft gross weight in relation with a subgrade strength value.To find the ACN of an aircraft on flexible pavement, you must know the aircraft gross weight andthe subgrade strength.
NOTE : An aircraft with an ACN equal to or less than the reported PCN can operate on thatpavement, subject to any limitation on the tire pressure (Ref: ICAO Aerodrome DesignManual Part 3 Chapter 1 Second Edition 1983).
Example, see FIGURE 7-9-0-991-001-A, calculation of the ACN for flexible pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- An aircraft gross weight of 210000 kg (462971 lb),- A medium subgrade strength (code B).The ACN for flexible pavement is 51.
2. Aircraft Classification Number - ACN TableThe following table provides ACN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1983”. If the ACN for an intermediateweight between maximum ramp weight and the empty weight of the aircraft is required, refer tochart FIGURE 7-9-0-991-001-A.
ACN FOR FLEXIBLE PAVEMENT SUBGRADES -CBRAIRCRAFT
TYPEWEIGHT
LOAD ONONE MLGLEG (%)
TIREPRESSURE
(Mpa) High15
Medium10
Low6
Ultral-low3
A350--900
268900 kg(592824
lb)46.8 66 70 80 110
A350--900
142000 kg(313057
lb)46.8
1.66
31 32 34 41
7-9-0Page 1
Jun 01/13
@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070900_1_0010001_01_00
ALP
HA
FA
CT
OR
= 0
.8
SU
BG
RA
DE
ST
RE
NG
TH
B −
CB
R 1
0 (M
ED
IUM
)A
− C
BR
15
(HIG
H)
280
310
340
370
400
430
460
490
520
550
580
610
( x1
000
lb)
120
110
100 90 80 70 60 50 40 30 2012
014
016
018
020
022
024
026
028
0
AIRCRAFT CLASSIFICATION NUMBER (ACN)
( x1
000
kg)
AIR
CR
AF
T G
RO
SS
WE
IGH
T
AC
N W
AS
DE
TE
RM
INE
D A
S R
EF
ER
EN
CE
D IN
ICA
O A
ER
OD
RO
ME
DE
SIG
N M
AN
UA
L P
AR
T 3
CH
AP
TE
R 1
. SE
CO
ND
ED
ITIO
N 1
983.
CG
US
ED
FO
R A
CN
CA
LCU
LAT
ION
S: 3
3% M
AC
1400
x530
R23
42P
R T
IRE
ST
IRE
PR
ES
SU
RE
CO
NS
TA
NT
AT
16.
6 ba
r (2
41 p
si)
SE
E S
EC
TIO
N 7
−4−
0
C −
CB
R63
(LO
W)
(ULT
RA
LO
W)
D −
CB
R
Aircraft Classification Number - Flexible PavementMTOW 268 000 kg
FIGURE-7-9-0-991-001-A01
7-9-0Page 2
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
7-9-1 Aircraft Classification Number - Rigid Pavement
**ON A/C A350-900
Aircraft Classification Number - Rigid Pavement
1. This section gives data about the Aircraft Classification Number (ACN) for rigid pavement for anaircraft gross weight in relation with a subgrade strength value.To find the ACN of an aircraft on rigid pavement, you must know the aircraft gross weight and thesubgrade strength.
NOTE : An aircraft with an ACN equal to or less than the reported PCN can operate on thatpavement, subject to any limitation on the tire pressure. (Ref: ICAO Aerodrome DesignManual Part 3 Chapter 1 Second Edition 1983).
Example, see FIGURE 7-9-1-991-001-A, calculation of the ACN for rigid pavement for:- An aircraft with a MTOW of 268000 kg (590839 lb),- An aircraft gross weight of 210000 kg (462971 lb),- A medium subgrade strength (code B).The ACN for rigid pavement is 52.
2. Aircraft Classification Number - ACN TableThe following table provides ACN data in tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1983”. If the ACN for an intermediateweight between maximum ramp weight and the empty weight of the aircraft is required, refer tochart FIGURE 7-9-1-991-001-A.
ACN FOR RIGID PAVEMENT SUBGRADES -MN/m3AIRCRAFT
TYPEWEIGHT
LOAD ONONE MLGLEG (%)
TIREPRESSURE
(Mpa) High150
Medium80
Low40
Ultral-low20
A350--900
268900 kg(592824
lb)46.8 64 71 83 96
A350--900
142000 kg(313057
lb)46.8
1.66
32 33 36 41
7-9-1Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_070901_1_0010001_01_00
280
310
340
370
400
430
460
490
520
550
580
610
( x1
000
lb)
120
110
100 90 80 70 60 50 40 30 2012
014
016
018
020
022
024
026
028
0
AIRCRAFT CLASSIFICATION NUMBER (ACN)
( x1
000
kg)
AIR
CR
AF
T G
RO
SS
WE
IGH
T
AC
N W
AS
DE
TE
RM
INE
D A
S R
EF
ER
EN
CE
D IN
ICA
O A
ER
OD
RO
ME
DE
SIG
N M
AN
UA
L P
AR
T 3
CH
AP
TE
R 1
. SE
CO
ND
ED
ITIO
N 1
983.
CG
US
ED
FO
R A
CN
CA
LCU
LAT
ION
S: 3
3% M
AC
1400
x530
R23
42P
R T
IRE
ST
IRE
PR
ES
SU
RE
CO
NS
TA
NT
AT
16.
6 ba
r (2
41 p
si)
SE
E S
EC
TIO
N 7
−4−
0
SU
BG
RA
DE
ST
RE
NG
TH
D −
K =
20
MN
/m³(
ULT
RA
LO
W)
C −
K =
40
MN
/m³
B −
K =
80
MN
/m³
A −
K =
150
MN
/m³(L
OW
)
(ME
DIU
M)
(HIG
H)
Aircraft Classification Number - Rigid PavementMTOW 268 000 kg
FIGURE-7-9-1-991-001-A01
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
SCALED DRAWINGS
8-0-0 Scaled Drawings
**ON A/C A350-900
Scaled Drawings
1. This section provides the scaled drawings.
NOTE : When printing this drawing, make sure to adjust for proper scaling.
8-0-0Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
0 10 20 30 40 50 60FEET
0 4 8 12 16 20METERS
WHEN PRINTING THIS DRAWING, MAKE SURE TO ADJUST FOR PROPER SCALING
010
2030
4050
60F
EE
T
04
812
1620
ME
TE
RS
NOTE:
P_AC_080000_1_0010001_01_00
Scaled DrawingsFIGURE-8-0-0-991-001-A01
8-0-0Page 2
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
AIRCRAFT RESCUE AND FIRE FIGHTING
10-0-0 Aircraft Rescue and Fire Fighting
**ON A/C A350-900
Aircraft Rescue and Fire Fighting
1. This sections gives data related to aircraft rescue and fire fighting.The figures contained in this section are the figures that are in the Aircraft Rescue and Fire FightingCharts poster available for download on AIRBUSWorld and the Airbus website.
10-0-0Page 1
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
TH
IS C
HA
RT
GIV
ES
TH
E G
EN
ER
AL
LA
YO
UT
OF
TH
E A
350−
900
ST
AN
DA
RD
VE
RS
ION
.
RE
FE
RE
NC
E
:
JUN
E 2
013
P_AC_100000_1_0010001_01_01
Front PageFIGURE-10-0-0-991-001-A01
10-0-0Page 2
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A350-900
P_AC_100000_1_0030001_01_01
Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-0-0-991-003-A01
10-0-0Page 3
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@A350-900AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING