A380 - Airbus

Transcription

A380 - Airbus

@AIRBUS
A380
AIRCRAFT CHARACTERISTICS
AIRPORT AND MAINTENANCE PLANNING
AC
The content of this document is the property of Airbus.
It is supplied in confidence and commercial security on its contents must be maintained.
It must not be used for any purpose other than that for which it is supplied, nor may
information contained in it be disclosed to unauthorized persons.
It must not be reproduced in whole or in part without permission in writing from the owners of
the copyright. Requests for reproduction of any data in this document and the media authorized
for it must be addressed to Airbus.
© AIRBUS S.A.S. 2005. All rights reserved.
AIRBUS S.A.S.
Customer Services
Technical Data Support and Services
31707 Blagnac Cedex
FRANCE
Issue: Mar 30/05
Rev: Dec 01/14
@A380
AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
HIGHLIGHTS
Revision No. 13 - Dec 01/14
LOCATIONS
CHAPTER 1
Section 1-1
Subject 1-1-0
Introduction
Section 1-2
Subject 1-2-1
Glossary
CHG
CODE
DESCRIPTIONS OF CHANGE
R
R
R
DESCRIPTION TITLE UPDATED
R
CHAPTER 2
Section 2-1
Subject 2-1-1
General Aircraft Characteristics Data
Section 2-3
Subject 2-3-0
R
Ground Clearances
FIGURE Ground Clearances
R
R
FIGURE Ground Clearances - Leading
Edge Slats - Extended
R
FIGURE Ground Clearances - Trailing
Edge Flaps - Extended
R
FIGURE Ground Clearances - Ailerons Down
R
FIGURE Ground Clearances - Ailerons Up
R
ADDED A/C CONFIGURATIONS ”HT1”
AND ”RD1”. IMPROVED LAYOUT AND
REVISED REFERENCE POINTS ON
FUSELAGE, WINGS AND TAILPLANE.
ILLUSTRATION REVISED
REVISED ILLUSTRATION TO ADD NOTE
ON DROOP NOSE AND IMPROVED
LAYOUT TO PUT THE REFERENCE
POINTS BELOW THE GROUND.
IMPROVED LAYOUT TO PUT THE
REFERENCE POINTS BELOW THE
GROUND.
GROUND.
GROUND.
HIGHLIGHTS
Page 1
Dec 01/14
@A380
LOCATIONS
FIGURE Ground Clearances - Flap Tracks
- Extended
FIGURE Ground Clearances - Trimmable
Horizontal Stabilizer and Elevators Down
Section 2-7
Subject 2-7-0
CHG
CODE
R
N
GROUND.
ADDED ILLUSTRATION TO SHOW THE
MINIMUM GROUND CLEARANCE WHEN
THS AND ELEVATORS ARE IN FULLY
DOWN POSITION.
ILLUSTRATION ADDED
R
Door Clearances
FIGURE Door Clearances - Forward
Passenger Doors
R
N
FIGURE Door Clearances - Main and
Upper Deck Passenger Doors
N
FIGURE Door Clearances - Aft Passenger
Doors
N
FIGURE Door Clearances - Forward Cargo
Compartment Door
N
FIGURE Door Clearances - Aft Cargo
Compartment Doors
N
FIGURE Door Clearances - Forward Nose
Landing Gear Doors
N
FIGURE Door Clearances - Wing Landing
Gears - Main Doors
N
FIGURE Door Clearances - Body Landing
Gears - Outer Doors
N
ILLUSTRATION MOVED FROM SECTION
2-7-1 AND ADDED COVER PLATE DATA.
ILLUSTRATION ADDED
ILLUSTRATION ADDED
ILLUSTRATION ADDED
2-7-5.
ILLUSTRATION ADDED
2-7-4.
ILLUSTRATION ADDED
2-7-6.
ILLUSTRATION ADDED
2-7-7.
ILLUSTRATION ADDED
2-7-8.
ILLUSTRATION ADDED
HIGHLIGHTS
Page 2
Dec 01/14
@A380
LOCATIONS
FIGURE Door Clearances - APU Doors
CHG
CODE
N
Subject 02-07-01
D
Subject 02-07-02
D
Subject 02-07-03
D
Subject 02-07-04
D
Subject 02-07-05
D
Subject 02-07-06
D
Subject 02-07-07
D
Subject 02-07-08
D
Subject 02-07-09
D
2-7-9.
ILLUSTRATION ADDED
Section 2-8
Subject 2-8-0
Escape Slides
R
FIGURE Escape Slides - Location
R
FIGURE Escape Slides - Dimensions
R
CHAPTER 3
Section 3-2
Subject 03-02-00
R
D
Subject 3-2-1
Payload/Range - ISA Conditions
R
Take-Off Weight Limitation - ISA
Conditions
FIGURE Take-Off Weight Limitation ISA Conditions - TRENT 900 Engines
R
R
FIGURE Take-Off Weight Limitation ISA Conditions - GP 7200 Engines
R
REVISED THE TITLE TO DELETE
”FAA/EASA”.
”FAA/EASA”.
Section 3-3
Subject 3-3-1
HIGHLIGHTS
Page 3
Dec 01/14
@A380
LOCATIONS
CHG
CODE
Subject 3-3-2
Take-Off Weight Limitation - ISA + 15
˚C (+59 ˚F) Conditions
R
FIGURE Take-Off Weight Limitation ISA + 15 ˚C (+59 ˚F) Conditions TRENT 900 Engines
R
FIGURE Take-Off Weight Limitation ISA + 15 ˚C (+59 ˚F) Conditions - GP
7200 Engines
R
”FAA/EASA” AND ADDED
”CONDITIONS”.
”FAA/EASA” AND ADDED
”CONDITIONS”.
Section 3-4
Subject 3-4-1
Landing Field Length
R
FIGURE Landing Field Length - Dry
Runway
R
”FAA/EASA”.
CHAPTER 4
Section 4-2
Subject 4-2-0
Turning Radii
R
FIGURE Turning Radii - (Sheet 1)
R
R
CORRECTED THE NOTE TO REPLACE
”PAGE 2” BY ”SHEET 2”.
DELETED THE FREIGHTER VERSION
(A380-800F) IN THE TABLE TITLE AND
IMPROVED LAYOUT.
Section 4-3
Subject 4-3-0
Minimum Turning Radii
R
FIGURE Minimum Turning Radii
R
CHAPTER 5
Section 05-00
DELETED THE FREIGHTER VERSION
(A380-800F) IN THE TABLE TITLE AND
IMPROVED LAYOUT.
R
D
HIGHLIGHTS
Page 4
Dec 01/14
@A380
LOCATIONS
CHG
CODE
Section 5-1
Subject 5-1-0
Aircraft Servicing Arrangements
R
Section 5-2
Subject 5-2-1
Typical Turn-Round Time - Standard
Servicing Via Main Deck and Upper Deck
R
FIGURE Typical Turn-Round Time Servicing Via Main and Upper Deck
R
REPLACED THE WORD ”DEBOARDING”
BY ”DEPLANING” AND ”TOILET” BY
”WASTE WATER”.
Subject 5-2-2
Typical Turn-Round Time - Servicing Via
Main Deck
FIGURE Typical Turn-Round Time Servicing Via Main Deck
Section 5-4
Subject 5-4-2
R
R
REPLACED THE WORD ”DEBOARDING”
BY ”DEPLANING” AND ”TOILET” BY
”WASTE WATER”.
R
R
Grounding (Earthing) Points
R
FIGURE Grounding (Earthing) Point NLG
R
FIGURE Grounding (Earthing) Points WLG
R
FIGURE Grounding (Earthing) Points BLG
R
REVISED THE TITLE AND ILLUSTRATION
TO ADD THE WORD ”EARTHING” TO
THE TERM ”GROUNDING”.
Subject 5-4-3
Hydraulic System
R
FIGURE Ground Service Connections Hydraulic Reservoir Servicing Panel
R
REVISED ILLUSTRATION TO SHOW THE
”DEPRESSURIZATION SWITCHES”.
HIGHLIGHTS
Page 5
Dec 01/14
@A380
LOCATIONS
CHG
CODE
Subject 5-4-4
Electrical System
FIGURE Ground Service Connections Ram Air Turbine Retracted
FIGURE Ground Service Connections Ram Air Turbine Extended
Subject 5-4-5
Oxygen System
R
NOTE AMENDED
R
R
R
Subject 5-4-6
Fuel System
R
FIGURE Ground Service Connections Overpressure Protector and NACA Flame
Arrestor - Wing
R
FIGURE Ground Service Connections Overpressure Protector and NACA Flame
Arrestor - Trim Tank
N
ADDED ILLUSTRATION TO SHOW
OVERPRESSURE PROTECTOR AND NACA
FLAME ARRESTOR ON TRIM TANK.
ILLUSTRATION ADDED
Subject 5-4-7
Pneumatic System
Subject 5-4-8
R
R
Engine Oil Servicing
R
FIGURE Ground Service Connections Engine Oil Servicing - TRENT 900
Engines
N
FIGURE Ground Service Connections Engine Oil Servicing - GP7200 Engines
N
VFG Oil Servicing
N
FIGURE Ground Service Connections VFG Oil Servicing - TRENT 900 Engines
N
NOTE AMENDED
MIGRATED THE SECTION ”ENGINE OIL
SERVICING” FROM ”05-04-09” TO
”05-04-08”.
ILLUSTRATION ADDED
MIGRATED THE SECTION ”ENGINE OIL
”05-04-08”.
ILLUSTRATION ADDED
MIGRATED THE SECTION ”VFG OIL
”05-04-08”.
ILLUSTRATION ADDED
HIGHLIGHTS
Page 6
Dec 01/14
@A380
LOCATIONS
FIGURE Ground Service Connections VFG Oil Servicing - GP7200 Engines
CHG
CODE
N
Starter Oil Servicing
N
FIGURE Ground Service Connections Starter Oil Servicing - TRENT 900
Engines
N
FIGURE Ground Service Connections Starter Oil Servicing - GP7200 Engines
N
APU Oil Servicing
N
FIGURE Ground Service Connections APU Oil Servicing
N
Subject 5-4-9
MIGRATED THE SECTION ”VFG OIL
”05-04-08”.
ILLUSTRATION ADDED
MIGRATED THE SECTION ”STARTER OIL
”05-04-08”.
ILLUSTRATION ADDED
MIGRATED THE SECTION ”STARTER OIL
”05-04-08”.
ILLUSTRATION ADDED
MIGRATED THE SECTION ”APU OIL
”05-04-08”.
ILLUSTRATION ADDED
R
Potable Water System
R
FIGURE Ground Service Connections Potable Water Ground Service Panel
N
FIGURE Ground Service Connections Potable Water Drain Panel
N
FIGURE Ground Service Connections Potable Water Tanks Location
N
NOTE AMENDED
MIGRATED THE SECTION ”POTABLE
WATER SYSTEM” FROM ”05-04-08” TO
”05-04-09”.
ILLUSTRATION ADDED
”05-04-09”.
ILLUSTRATION ADDED
”05-04-09”.
ILLUSTRATION ADDED
Subject 5-4-10
Waste Water System
R
FIGURE Ground Service Connections Waste Water Ground Service Panel
R
REVISED THE TITLE TO ”WASTE WATER
GROUND SERVICE PANEL”.
HIGHLIGHTS
Page 7
Dec 01/14
@A380
LOCATIONS
Subject 5-4-11
CHG
CODE
N
Cargo Control Panels
N
FIGURE Forward Cargo Control Panels
N
FIGURE Aft Cargo Control Panels
N
CHAPTER 6
Section 6-1
Subject 6-1-0
Engine Exhaust Velocities and
Temperatures
Section 06-02
Section 6-4
Subject 06-04-00
ADDED NEW ILLUSTRATION FOR
FORWARD CARGO CONTROL PANELS.
ILLUSTRATION ADDED
ADDED NEW ILLUSTRATION FOR AFT
CARGO CONTROL PANELS.
ILLUSTRATION ADDED
R
R
D
R
D
Subject 6-4-1
APU Exhaust Velocities and Temperatures
- ECS Conditions
R
CHAPTER 7
Section 7-2
Subject 7-2-0
Landing Gear Footprint
R
FIGURE Landing Gear Footprint
R
REVISED THE LANDING GEAR
FOOTPRINT DATA FOR WV009.
Section 7-3
Subject 7-3-0
Maximum Pavement Loads
FIGURE Maximum Pavement Loads
R
R
REVISED THE MAXIMUM PAVEMENT
LOADS FOR WV009.
Section 7-6
Subject 7-6-0
HIGHLIGHTS
Page 8
Dec 01/14
@A380
LOCATIONS
Flexible Pavement Requirements - LCN
Conversion
FIGURE Flexible Pavement Requirements
- LCN Table
- LCN - WV007, MRW 492 000 kg, CG
43 % - WLG
- LCN - WV008, MRW 577 000 kg, CG
41 % - WLG
Section 7-8
Subject 7-8-0
CHG
CODE
R
R
REVISED THE VALUES OF WV009 IN LCN
TABLE.
R
R
Rigid Pavement Requirements - LCN
Conversion
FIGURE Rigid Pavement Requirements LCN Table
Section 7-9
Subject 7-9-0
R
NOTE AMENDED
R
REVISED THE VALUES OF WV009 IN LCN
TABLE.
ACN/PCN Reporting System - Flexible
and Rigid Pavements
R
FIGURE Aircraft Classification Number ACN Table
FIGURE Aircraft Classification Number Flexible Pavement - WV007, MRW 492
000 kg, CG 43%
R
FIGURE Aircraft Classification Number Flexible Pavement - WV008, MRW 577
000 kg, CG 41%
R
R
R
REVISED THE VALUES OF WV009 IN ACN
TABLE.
R
CHAPTER 10
Section 10-0
Subject 10-0-0
FIGURE Emergency Evacuation Devices
R
ADDED NOTE TO MENTION THAT
ESCAPE SLIDES ARE SYMMETRICAL ON
BOTH SIDES.
HIGHLIGHTS
Page 9
Dec 01/14
@A380
LIST OF EFFECTIVE CONTENT
Revision No. 13 - Dec 01/14
CONTENT
CHG
CODE
LAST REVISION
DATE
R
Dec 01/14
R
Dec 01/14
R
Dec 01/14
CHAPTER 1
Subject 1-1-0
Introduction
Subject 1-2-1
Glossary
CHAPTER 2
Subject 2-1-1
Subject 2-2-0
General Aircraft Dimensions
Dec 01/13
FIGURE General Aircraft Dimensions
Dec 01/13
Subject 2-3-0
Ground Clearances
R
Dec 01/14
FIGURE Ground Clearances
R
Dec 01/14
FIGURE Ground Clearances - Leading Edge Slats - Extended
R
Dec 01/14
FIGURE Ground Clearances - Trailing Edge Flaps - Extended
R
Dec 01/14
FIGURE Ground Clearances - Spoilers - Extended
Dec 01/13
FIGURE Ground Clearances - Ailerons - Down
R
Dec 01/14
FIGURE Ground Clearances - Ailerons - Up
R
Dec 01/14
FIGURE Ground Clearances - Flap Tracks - Extended
R
Dec 01/14
N
Dec 01/14
FIGURE Ground Clearances - Trimmable Horizontal Stabilizer and
Elevators - Down
Subject 2-4-0
Interior Arrangement - Plan View
Dec 01/13
Subject 2-4-1
Standard Configuration - Pax
Dec 01/13
L.E.C.
Page 1
Dec 01/14
@A380
CONTENT
CHG
CODE
FIGURE Interior Arrangements - Plan View - Standard Configuration
- Upper Deck
FIGURE Interior Arrangements - Plan View - Standard Configuration
- Main Deck
Subject 2-5-0
LAST REVISION
DATE
Dec 01/13
Dec 01/13
Interior Arrangements - Cross Section
Dec 01/13
Subject 2-5-1
Typical Configuration - Pax
Dec 01/13
FIGURE Interior Arrangements - Cross-section - Typical Configuration
- Upper Deck
Dec 01/13
FIGURE Interior Arrangements - Cross-section - Typical Configuration
- Main Deck
Subject 2-6-0
Dec 01/13
Cargo Compartments
Dec 01/13
Subject 2-6-1
Location and Dimensions - Pax
Dec 01/13
FIGURE Cargo Compartments - Location and Dimensions
Dec 01/13
Subject 2-6-2
Loading Combinations - Pax
Dec 01/13
FIGURE Cargo Compartments - Loading Combinations
Dec 01/13
Subject 2-7-0
Door Clearances
R
Dec 01/14
FIGURE Door Clearances - Door Location (Sheet 1)
Dec 01/13
FIGURE Door Clearances - Door Location (Sheet 2)
Dec 01/13
FIGURE Door Clearances - Forward Passenger Doors
N
Dec 01/14
FIGURE Door Clearances - Main and Upper Deck Passenger Doors
N
Dec 01/14
FIGURE Door Clearances - Aft Passenger Doors
N
Dec 01/14
FIGURE Door Clearances - Forward Cargo Compartment Door
N
Dec 01/14
FIGURE Door Clearances - Aft Cargo Compartment Doors
N
Dec 01/14
FIGURE Door Clearances - Forward Nose Landing Gear Doors
N
Dec 01/14
L.E.C.
Page 2
Dec 01/14
@A380
CONTENT
FIGURE Door Clearances - Wing Landing Gears - Main Doors
CHG
CODE
N
LAST REVISION
DATE
Dec 01/14
FIGURE Door Clearances - Body Landing Gears - Outer Doors
N
Dec 01/14
FIGURE Door Clearances - APU Doors
N
Dec 01/14
Escape Slides
R
Dec 01/14
FIGURE Escape Slides - Location
R
Dec 01/14
FIGURE Escape Slides - Dimensions
R
Dec 01/14
Subject 2-8-0
Subject 2-9-0
Landing Gear
Dec 01/13
FIGURE Wing Landing Gear - General
Dec 01/13
FIGURE Body Landing Gear - General
Dec 01/13
FIGURE Nose Landing Gear - General
Dec 01/13
Landing Gear Maintenance Pits
Dec 01/13
FIGURE Landing Gear Maintenance Pits - Maintenance Pit Envelopes
Dec 01/13
FIGURE Landing Gear Maintenance Pits - Necessary Depths
Dec 01/13
- WLG Pit Dimensions
- BLG Pit Dimensions
Subject 2-10-0
Dec 01/13
Dec 01/13
Exterior Lighting
Dec 01/13
FIGURE Exterior Lighting
Dec 01/13
Dec 01/13
Dec 01/13
Dec 01/13
Dec 01/13
Subject 2-11-0
Antennas and Probes Location
Dec 01/13
FIGURE Antennas and Probes - Location
Dec 01/13
Subject 2-12-0
L.E.C.
Page 3
Dec 01/14
@A380
CONTENT
Auxiliary Power Unit
CHG
CODE
LAST REVISION
DATE
Dec 01/13
FIGURE Auxiliary Power Unit - Access Doors
Dec 01/13
FIGURE Auxiliary Power Unit - General Layout
Dec 01/13
Engine and Nacelle
Dec 01/13
FIGURE Power Plant Handling - Engine Dimensions - GP 7200
Engine
Dec 01/13
FIGURE Power Plant Handling - Nacelle Dimensions - GP 7200
Engine
Dec 01/13
FIGURE Power Plant Handling - Fan Cowls - GP 7200 Engine
Dec 01/13
FIGURE Power Plant Handling - Thrust Reverser Cowls - GP 7200
Engine
Dec 01/13
FIGURE Power Plant Handling - Fan Exhaust Cowls - GP 7200
Engine
Dec 01/13
FIGURE Power Plant Handling - Engine Dimensions - TRENT 900
Engine
Dec 01/13
FIGURE Power Plant Handling - Nacelle Dimensions - TRENT 900
Engine
Dec 01/13
FIGURE Power Plant Handling - Fan Cowls - TRENT 900 Engine
Dec 01/13
FIGURE Power Plant Handling - Thrust Reverser Cowls - TRENT
900 Engine
Dec 01/13
FIGURE Power Plant Handling - Fan Exhaust Cowls - TRENT 900
Engine
Dec 01/13
Subject 2-13-0
Leveling, Symmetry and Alignment
Dec 01/13
FIGURE Location of Leveling Points
Dec 01/13
Subject 2-14-0
Jacking for Maintenance
Dec 01/13
FIGURE Jacking for Maintenance - Jacking Points Location
Dec 01/13
FIGURE Jacking for Maintenance - Jacking Dimensions
Dec 01/13
FIGURE Jacking for Maintenance - Forward Jacking Point
Dec 01/13
FIGURE Jacking for Maintenance - Wing Jacking Point
Dec 01/13
L.E.C.
Page 4
Dec 01/14
@A380
CONTENT
CHG
CODE
FIGURE Jacking for Maintenance - Auxiliary Jacking Point - Safety
Stay
LAST REVISION
DATE
Dec 01/13
Jacking for Wheel Change
Dec 01/13
FIGURE Nose Landing Gear Jacking Point Heights
Dec 01/13
FIGURE Wing Landing Gear Jacking Point Heights
Dec 01/13
FIGURE Body Landing Gear Jacking Point Heights
Dec 01/13
FIGURE Nose Landing Gear Jacking Point Loads
Dec 01/13
FIGURE Wing Landing Gear Jacking Point Loads
Dec 01/13
FIGURE Body Landing Gear Jacking Point Loads
Dec 01/13
CHAPTER 3
Subject 3-1-0
General Information
Dec 01/13
Subject 3-2-1
R
Dec 01/14
FIGURE Payload/Range - ISA Conditions - TRENT 900 Engines
Dec 01/13
FIGURE Payload/Range - ISA Conditions - GP 7200 Engines
Dec 01/13
Subject 3-3-1
Take-Off Weight Limitation - ISA Conditions
R
Dec 01/14
FIGURE Take-Off Weight Limitation - ISA Conditions - TRENT 900
Engines
R
Dec 01/14
FIGURE Take-Off Weight Limitation - ISA Conditions - GP 7200
Engines
R
Dec 01/14
Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F) Conditions
R
Dec 01/14
FIGURE Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F)
Conditions - TRENT 900 Engines
R
Dec 01/14
FIGURE Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F)
Conditions - GP 7200 Engines
R
Dec 01/14
R
Dec 01/14
Subject 3-3-2
Subject 3-4-1
L.E.C.
Page 5
Dec 01/14
@A380
CONTENT
FIGURE Landing Field Length - Dry Runway
CHG
CODE
R
LAST REVISION
DATE
Dec 01/14
Subject 3-5-0
Final Approach Speed
Dec 01/13
CHAPTER 4
Subject 4-1-0
General
Dec 01/13
Subject 4-2-0
Turning Radii
R
Dec 01/14
R
Dec 01/14
R
Dec 01/14
R
Dec 01/14
FIGURE Minimum Turning Radii
R
Dec 01/14
Subject 4-3-0
Subject 4-4-0
Visibility from Cockpit in Static Position
Dec 01/13
FIGURE Visibility from Cockpit in Static Position
Dec 01/13
FIGURE Binocular Visibility Through Windows from Captain Eye
Position
Subject 4-5-0
Runway and Taxiway Turn Paths
Dec 01/13
Dec 01/13
Subject 4-5-1
135˚ Turn - Runway to Taxiway
FIGURE 135˚ Turn -- Runway to Taxiway - Judgemental Oversteer
Method
FIGURE 135˚ Turn -- Runway to Taxiway - Cockpit Tracks
Centreline Method
Subject 4-5-2
Dec 01/13
Dec 01/13
Dec 01/13
Dec 01/13
FIGURE 90˚ Turn -- Runway to Taxiway - Judgemental Oversteer
Method
Dec 01/13
L.E.C.
Page 6
Dec 01/14
@A380
CONTENT
FIGURE 90˚ Turn -- Runway to Taxiway - Cockpit Tracks Centreline
Method
Subject 4-5-3
CHG
CODE
LAST REVISION
DATE
Dec 01/13
180˚ Turn on a Runway
Dec 01/13
FIGURE 180˚ Turn on a Runway
Dec 01/13
Subject 4-5-4
90˚ Turn - Taxiway to Taxiway
FIGURE 90˚ Turn -- Taxiway to Taxiway - Judgemental Oversteer
Method
FIGURE 90˚ Turn -- Taxiway to Taxiway - Cockpit Tracks Centreline
Method
Subject 4-5-5
FIGURE 135˚ Turn -- Taxiway to Taxiway - Judgemental Oversteer
Method
FIGURE 135˚ Turn -- Taxiway to Taxiway - Cockpit Tracks
Centerline Method
Subject 4-6-0
Dec 01/13
Dec 01/13
Dec 01/13
Dec 01/13
Dec 01/13
Dec 01/13
Runway Holding Bay (Apron)
Dec 01/13
FIGURE Runway Holding Bay (Apron)
Dec 01/13
Subject 4-7-0
Minimum Line-Up Distance Corrections
Dec 01/13
FIGURE Minimum Line-Up Distance Corrections - 90˚ Turn on
Runway Entry
Dec 01/13
Runway Turn Pad
Dec 01/13
Runway Width
Dec 01/13
Subject 4-8-0
Aircraft Mooring
Dec 01/13
FIGURE Aircraft Mooring
Dec 01/13
CHAPTER 5
L.E.C.
Page 7
Dec 01/14
@A380
CONTENT
CHG
CODE
LAST REVISION
DATE
R
Dec 01/14
Subject 5-1-0
Subject 5-1-1
Typical Ramp Layout (Open Apron)
Dec 01/13
FIGURE Typical Ramp Layout - Open Apron
Dec 01/13
Subject 5-1-2
Typical Ramp Layout (Gate)
Dec 01/13
FIGURE Typical Ramp Layout - Gate
Dec 01/13
Subject 5-2-1
Typical Turn-Round Time - Standard Servicing Via Main Deck and
Upper Deck
R
Dec 01/14
FIGURE Typical Turn-Round Time - Servicing Via Main and Upper
Deck
Subject 5-2-2
R
Dec 01/14
Typical Turn-Round Time - Servicing Via Main Deck
R
Dec 01/14
FIGURE Typical Turn-Round Time - Servicing Via Main Deck
R
Dec 01/14
Subject 5-4-1
Ground Service Connections Layout
Dec 01/13
FIGURE Ground Service Connections Layout
Dec 01/13
Subject 5-4-2
R
Dec 01/14
FIGURE Grounding (Earthing) Point - NLG
R
Dec 01/14
FIGURE Grounding (Earthing) Points - WLG
R
Dec 01/14
FIGURE Grounding (Earthing) Points - BLG
R
Dec 01/14
Hydraulic System
R
Dec 01/14
FIGURE Ground Service Connections - Hydraulic Reservoir Servicing
Panel
FIGURE Ground Service Connections - Hydraulic Ground Connections
R
Dec 01/14
Subject 5-4-3
Dec 01/13
Subject 5-4-4
L.E.C.
Page 8
Dec 01/14
@A380
CONTENT
Electrical System
CHG
CODE
R
FIGURE Ground Service Connections - Electrical Service Panel
LAST REVISION
DATE
Dec 01/14
Dec 01/13
FIGURE Ground Service Connections - Ram Air Turbine Retracted
R
Dec 01/14
FIGURE Ground Service Connections - Ram Air Turbine Extended
R
Dec 01/14
R
Dec 01/14
Subject 5-4-5
Oxygen System
FIGURE Ground Service Connections - Oxygen System
Dec 01/13
Subject 5-4-6
Fuel System
R
Dec 01/14
FIGURE Ground Service Connections - Refuel/Defuel Control Panel
Dec 01/13
FIGURE Ground Service Connections - Pressure Refuel Connections
Dec 01/13
FIGURE Ground Service Connections - Overpressure Protector and
NACA Flame Arrestor - Wing
R
Dec 01/14
FIGURE Ground Service Connections - Overpressure Protector and
NACA Flame Arrestor - Trim Tank
Subject 5-4-7
N
Dec 01/14
R
Dec 01/14
Pneumatic System
FIGURE Ground Service Connections - Low Pressure Preconditioned
Air
FIGURE Ground Service Connections - High Pressure Preconditioned
Air
Subject 5-4-8
Dec 01/13
Dec 01/13
R
Dec 01/14
FIGURE Ground Service Connections - Engine Oil Servicing - TRENT
900 Engines
N
Dec 01/14
FIGURE Ground Service Connections - Engine Oil Servicing - GP7200
Engines
N
Dec 01/14
VFG Oil Servicing
N
Dec 01/14
FIGURE Ground Service Connections - VFG Oil Servicing - TRENT
900 Engines
N
Dec 01/14
FIGURE Ground Service Connections - VFG Oil Servicing - GP7200
Engines
N
Dec 01/14
L.E.C.
Page 9
Dec 01/14
@A380
CONTENT
CHG
CODE
N
LAST REVISION
DATE
Dec 01/14
FIGURE Ground Service Connections - Starter Oil Servicing - TRENT
900 Engines
N
Dec 01/14
FIGURE Ground Service Connections - Starter Oil Servicing - GP7200
Engines
N
Dec 01/14
APU Oil Servicing
N
Dec 01/14
FIGURE Ground Service Connections - APU Oil Servicing
N
Dec 01/14
R
Dec 01/14
FIGURE Ground Service Connections - Potable Water Ground Service
Panel
FIGURE Ground Service Connections - Potable Water Drain Panel
N
Dec 01/14
N
Dec 01/14
FIGURE Ground Service Connections - Potable Water Tanks Location
N
Dec 01/14
Waste Water System
R
Dec 01/14
FIGURE Ground Service Connections - Waste Water Ground Service
Panel
FIGURE Ground Service Connections - Waste Tanks Location
R
Dec 01/14
Subject 5-4-9
Subject 5-4-10
Dec 01/13
Subject 5-4-11
N
Dec 01/14
FIGURE Forward Cargo Control Panels
N
Dec 01/14
FIGURE Aft Cargo Control Panels
N
Dec 01/14
Subject 5-5-0
Engine Starting Pneumatic Requirements
Dec 01/13
FIGURE Example for Use of the Charts
Dec 01/13
FIGURE Engine Starting Pneumatic Requirements - Engine Alliance GP 7200
FIGURE Engine Starting Pneumatic Requirements - Rolls Royce Trent 900 Engine
Dec 01/13
Dec 01/13
Subject 5-6-0
Ground Pneumatic Power Requirements
Dec 01/13
L.E.C.
Page 10
Dec 01/14
@A380
CONTENT
CHG
CODE
FIGURE Ground Pneumatic Power Requirements - Heating
LAST REVISION
DATE
Dec 01/13
FIGURE Ground Pneumatic Power Requirements - Cooling
Dec 01/13
Subject 5-7-0
Preconditioned Airflow Requirements
Dec 01/13
FIGURE Preconditioned Airflow Requirements
Dec 01/13
Subject 5-8-0
Ground Towing Requirements
Dec 01/13
FIGURE Ground Towing Requirements
Dec 01/13
FIGURE Ground Towing Requirements - Nose Gear Towing Fittings
Dec 01/13
Subject 5-9-0
De-Icing and External Cleaning
Dec 01/13
CHAPTER 6
Subject 6-1-0
Engine Exhaust Velocities and Temperatures
R
Dec 01/14
Subject 6-1-1
Engine Exhaust Velocities - Ground Idle Power
Dec 01/13
FIGURE Engine Exhaust Velocities - Ground Idle Power - TRENT 900
Engines
Dec 01/13
FIGURE Engine Exhaust Velocities - Ground Idle Power - GP 7200
Engines
Dec 01/13
Subject 6-1-2
Engine Exhaust Temperatures - Ground Idle Power
Dec 01/13
FIGURE Engine Exhaust Temperatures - Ground Idle Power - TRENT
900 Engines
Dec 01/13
FIGURE Engine Exhaust Temperatures - Ground Idle Power - GP
7200 Engines
Dec 01/13
Subject 6-1-3
Engine Exhaust Velocities - Breakaway Power
Dec 01/13
FIGURE Engine Exhaust Velocities - Breakaway Power - TRENT 900
Engines
Dec 01/13
L.E.C.
Page 11
Dec 01/14
@A380
CONTENT
FIGURE Engine Exhaust Velocities - Breakaway Power - GP 7200
Engines
CHG
CODE
LAST REVISION
DATE
Dec 01/13
Subject 6-1-4
Engine Exhaust Temperatures - Breakaway Power
Dec 01/13
FIGURE Engine Exhaust Temperatures - Breakaway Power - TRENT
900 Engines
Dec 01/13
FIGURE Engine Exhaust Temperatures - Breakaway Power - GP 7200
Engines
Dec 01/13
Subject 6-1-5
Engine Exhaust Velocities - Max Take-off Power
Dec 01/13
FIGURE Engine Exhaust Velocities - Max. Take-Off Power - TRENT
900 Engines
Dec 01/13
FIGURE Engine Exhaust Velocities - Max. Take-Off Power - GP 7200
Engines
Dec 01/13
Subject 6-1-6
Engine Exhaust Temperatures - Max Take-off Power
Dec 01/13
FIGURE Engine Exhaust Temperatures - Max Take-Off Power TRENT 900 Engines
Dec 01/13
FIGURE Engine Exhaust Temperatures - Max Take-Off Power - GP
7200 Engines
Dec 01/13
Subject 6-3-0
Danger Areas of the Engines
Dec 01/13
Subject 6-3-1
Danger Areas of the Engines - Ground Idle Power
Dec 01/13
FIGURE Danger Areas of the Engines - Ground Idle Power - TRENT
900 Engines
Dec 01/13
FIGURE Danger Areas of the Engines - Ground Idle Power - GP 7200
Engines
Dec 01/13
Subject 6-3-2
Danger Areas of the Engines - Max. Take-Off Power
Dec 01/13
FIGURE Danger Areas of the Engines - Max Take-Off Power TRENT 900 Engines
Dec 01/13
L.E.C.
Page 12
Dec 01/14
@A380
CONTENT
CHG
CODE
FIGURE Danger Areas of the Engines - Max Take-Off Power - GP
7200 Engines
LAST REVISION
DATE
Dec 01/13
Subject 6-3-3
Danger Areas of the Engines - Breakaway Power
Dec 01/13
FIGURE Danger Areas of the Engines - Breakaway Power - TRENT
900 Engines
Dec 01/13
FIGURE Danger Areas of the Engines - Breakaway Power - GP 7200
Engines
Dec 01/13
Subject 6-4-1
APU Exhaust Velocities and Temperatures - ECS Conditions
R
Dec 01/14
FIGURE APU Exhaust Velocities and Temperatures - Max. ECS
Conditions
Subject 6-4-2
Dec 01/13
APU Exhaust Velocities and Temperatures - MES Conditions
Dec 01/13
FIGURE APU Exhaust Velocities and Temperatures - MES Conditions
Dec 01/13
CHAPTER 7
Subject 7-1-0
General Information
Dec 01/13
Subject 7-2-0
R
Dec 01/14
FIGURE Landing Gear Footprint
R
Dec 01/14
R
Dec 01/14
FIGURE Maximum Pavement Loads
R
Dec 01/14
Subject 7-3-0
Subject 7-4-0
Landing Gear Loading on Pavement
Dec 01/13
FIGURE Landing Gear Loading on Pavement - WV007, MRW 492
000 kg, CG 43% (Sheet 1 of 2)
Dec 01/13
FIGURE Landing Gear Loading on Pavement - WV008, MRW 577
000 kg CG 41% (Sheet 1 of 2)
Dec 01/13
Subject 7-5-0
L.E.C.
Page 13
Dec 01/14
@A380
CONTENT
CHG
CODE
Flexible Pavement Requirements - US Army Corps of Engineers
Design Method
LAST REVISION
DATE
Dec 01/13
FIGURE Flexible Pavement Requirements - WV007, MRW 492 000
kg, CG 43 % - Wing Landing Gear (Sheet 1 of 2)
Dec 01/13
FIGURE Flexible Pavement Requirements - WV008, MRW 577 000
kg, CG 41 % - Wing Landing Gear (Sheet 1 of 2)
Dec 01/13
Subject 7-6-0
Flexible Pavement Requirements - LCN Conversion
R
Dec 01/14
FIGURE Flexible Pavement Requirements - LCN Table
R
Dec 01/14
FIGURE Flexible Pavement Requirements - LCN - WV007, MRW 492
000 kg, CG 43 % - WLG
R
Dec 01/14
FIGURE Flexible Pavement Requirements - LCN - WV008, MRW 577
000 kg, CG 41 % - WLG
R
Dec 01/14
Subject 7-7-0
Rigid Pavement Requirements - Portland Cement Association Design
Method
FIGURE Rigid Pavement Requirements - WV007, MRW 492 000 kg,
CG 43 % - WLG
FIGURE Rigid Pavement Requirements - WV008, MRW 577 000 kg,
CG 41 % - WLG
Subject 7-8-0
Dec 01/13
Dec 01/13
Dec 01/13
Rigid Pavement Requirements - LCN Conversion
R
Dec 01/14
FIGURE Rigid Pavement Requirements - LCN Table
R
Dec 01/14
FIGURE Radius of Relative Stiffness (L)
Dec 01/13
FIGURE Rigid Pavement Requirements - LCN - WV007, MRW 492
000 kg, CG 43% - WLG
Dec 01/13
FIGURE Rigid Pavement Requirements - LCN - WV008, MRW 577
000 kg, CG 41% - WLG
Dec 01/13
FIGURE Radius of Relative Stiffness (Effect E and µ on ”L” values)
Dec 01/13
Subject 7-9-0
ACN/PCN Reporting System - Flexible and Rigid Pavements
R
Dec 01/14
FIGURE Aircraft Classification Number - ACN Table
R
Dec 01/14
L.E.C.
Page 14
Dec 01/14
@A380
CONTENT
FIGURE Aircraft Classification Number - Flexible Pavement - WV007,
MRW 492 000 kg, CG 43%
FIGURE Aircraft Classification Number - Flexible Pavement - WV008,
MRW 577 000 kg, CG 41%
CHG
CODE
R
LAST REVISION
DATE
Dec 01/14
R
Dec 01/14
CHAPTER 8
Subject 8-0-0
Scaled Drawings
Dec 01/13
FIGURE Scaled Drawing
Dec 01/13
CHAPTER 10
Subject 10-0-0
Aircraft Rescue and Fire Fighting
Dec 01/13
FIGURE Front Page
Dec 01/13
FIGURE Highly Flammable and Hazardous Materials and Components
Dec 01/13
FIGURE Batteries Location and Access
Dec 01/13
FIGURE Crew Rest Compartments Location
Dec 01/13
FIGURE Wheel/Brake Overheat - Wheel Safety Area
Dec 01/13
FIGURE Composite Materials Location
Dec 01/13
FIGURE Landing Gear - Ground Lock Safety Devices
Dec 01/13
FIGURE Emergency Evacuation Devices
R
Dec 01/14
FIGURE Pax/Crew Doors and Emergency Exits
Dec 01/13
FIGURE Cargo Doors - FWD and AFT Lower Deck Cargo Doors
Dec 01/13
FIGURE Control Panels
Dec 01/13
FIGURE APU Compartment Access
Dec 01/13
FIGURE Aircraft Ground Clearances
Dec 01/13
FIGURE Structural Break-in Points
Dec 01/13
L.E.C.
Page 15
Dec 01/14
@A380
TABLE OF CONTENTS
1
1-1-0
1-2-1
SCOPE
Introduction
Glossary
2
AIRCRAFT DESCRIPTION
2-1-1
2-2-0
2-3-0
Ground Clearances
2-4-0
2-4-1
Standard Configuration
2-5-0
2-5-1
Typical Configuration
2-6-0
Cargo Compartments
2-6-1
Location and Dimensions
2-6-2
Loading Combinations
2-7-0
Door Clearances
2-8-0
Escape Slides
2-9-0
Landing Gear
2-10-0
Exterior Lighting
2-11-0
2-12-0
Power Plant
2-13-0
2-14-0
Jacking
3
3-1-0
3-2-1
3-3-1
3-3-2
3-4-1
3-5-0
AIRCRAFT PERFORMANCE
General Information
ISA Conditions
Take Off Weight Limitation - ISA Conditions
Take Off Weight Limitation - ISA + 15 ˚C (59 ˚F)
4
4-1-0
4-2-0
GROUND MANEUVERING
General Information
Turning Radii
T.O.C.
Page 1
Dec 01/14
@A380
4-3-0
4-4-0
4-5-0
4-5-1
4-5-2
4-5-3
4-5-4
4-5-5
4-6-0
4-7-0
4-8-0
Aircraft Mooring
5
TERMINAL SERVICING
5-1-0
5-1-1
5-1-2
5-2-1
Typical Turn-Round Time - Standard Servicing Via Main Deck and Upper Deck
5-2-2
5-4-1
5-4-2
5-4-3
Hydraulic System
5-4-4
Electrical System
5-4-5
Oxygen System
5-4-6
Fuel System
5-4-7
Pneumatic System
5-4-8
Oil System
5-4-9
5-4-10
Vacuum Toilet System
5-4-11
5-5-0
5-6-0
5-7-0
5-8-0
5-9-0
6
6-1-0
6-1-1
OPERATING CONDITIONS
T.O.C.
Page 2
Dec 01/14
@A380
6-1-2
6-1-3
6-1-4
6-1-5
6-1-6
6-3-0
6-3-1
6-3-2
6-3-3
6-4-1
6-4-2
7
7-1-0
7-2-0
7-3-0
7-4-0
7-5-0
7-6-0
7-7-0
7-8-0
7-9-0
PAVEMENT DATA
General Information
Flexible Pavement Requirements - US Army Corps of Engineers Design Method
Rigid Pavement Requirements - Portland Cement Association Design Method
8
8-0-0
SCALED DRAWINGS
SCALED DRAWINGS
10
AIRCRAFT RESCUE AND FIRE FIGHTING
10-0-0
T.O.C.
Page 3
Dec 01/14
@A380
SCOPE
1-1-0
Introduction
**ON A/C A380-800
Introduction
1.
General
The A380 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING (AC)
manual is issued for the A380 series aircraft to provide necessary data to airport operators, airlines
and Maintenance/Repair Organizations (MRO) for airport and maintenance facilities planning.
This document is not customized and must not be used for training purposes. No information within
may constitute a contractual commitment.
The A380-800 is a subsonic, very long range and very high capacity civil transport aircraft. The
A380-800 offers several payload capabilities ranging from 400 passengers in a very comfortable multiclass configuration, up to 853 passengers in an all economy class configuration.
Designed in close collaboration with major airlines, airports and airworthiness authorities, the A380 is
the most advanced, spacious and productive aircraft in service setting a new standard in air travel
and environmental efficiency.
The A380 Family starts from a baseline passenger aircraft - the A380-800. A higher capacity version,
the A380-900 could be developed when required by the market.
Two engine types are currently offered, the Engine Alliance GP7200 series and the Rolls-Royce Trent
900 series. Both engines use state of the art technology for better performance, maintainability, lower
fuel consumption and environmental impact.
The A380-800 was designed to be compatible with current airport infrastructure and equipment, as
proven in service. Bigger, quieter and capable of achieving quick turn around times, the A380-800
provides an efficient solution for airports and airlines to grow in a sustainable manner.
Correspondence concerning this publication should be directed to:
AIRBUS S.A.S.
Customer Services
Technical Data Support and Services
1, Rond Point Maurice BELLONTE
31707 BLAGNAC CEDEX
FRANCE
1-1-0
Page 1
Dec 01/14
@A380
1-2-1
Glossary
**ON A/C A380-800
Glossary
1. List of Abbreviations
A/C
ACN
AMM
APU
B/C
BLG
CBR
CC
CG
C/L
E
ECS
ELEC
ESWL
FAA
F/C
FDL
FR
FSTE
FWD
GPU
GSE
ICAO
ISA
L
L
LCN
LD
LD
LH
LPS
MAC
MAX
Aircraft
Aircraft Classification Number
Aircraft Maintenance Manual
Business Class
Body Landing Gear
California Bearing Ratio
Cargo Compartment
Center of Gravity
Center Line
Young’s Modulus
Environmental Control System
Electric, Electrical, Electricity
Equivalent Single Wheel Load
Federal Aviation Administration
First Class
Fuselage Datum Line
Frame
Full Size Trolley Equivalent
Forward
Ground Power Unit
Ground Support Equipment
International Civil Aviation Organisation
International Standard Atmosphere
Left
Radius of relative stiffness
Load Classification Number
Load Device
Lower Deck
Left Hand
Last Pax Seating
Mean Aerodynamic Chord
Maximum
1-2-1
Page 1
Dec 01/14
@A380
MD
MIN
NLG
OAT
PAX
PBB
PB/D
PCA
PCN
PRM
R
RH
UD
ULD
US
VFG
WLG
WV
Y/C
2.
Main Deck
Minimum
Nose Landing Gear
Outside Air Temperature
Passenger
Passenger Boarding Bridge
Passenger Boarding/Deplaning
Portland Cement Association
Pavement Classification Number
Passenger with Reduced Mobility
Right
Right Hand
Upper Deck
Unit Load Device
United States
Variable Frequency Generator
Wing Landing Gear
Weight Variant
Tourist Class
Design Weight Terminology
- Maximum Design Ramp Weight (MRW):
Maximum weight for ground maneuver (including weight of taxi and run-up fuel) as limited by
aircraft strength and airworthiness requirements. It is also called Maximum Design Taxi Weight
(MTW).
- Maximum Design Landing Weight (MLW):
Maximum weight for landing as limited by aircraft strength and airworthiness requirements.
- Maximum Design Take-Off Weight (MTOW):
Maximum weight for take-off as limited by aircraft strength and airworthiness requirements. (This
is the maximum weight at start of the take-off run).
- Maximum Design Zero Fuel Weight (MZFW):
Maximum permissible weight of the aircraft without usable fuel.
- Maximum Seating Capacity:
Maximum number of passengers specifically certified or anticipated for certification.
- Usable Volume:
Usable volume available for cargo, pressurized fuselage, passenger compartment and cockpit.
- Water Volume:
Maximum volume of cargo compartment.
- Usable Fuel:
Fuel available for aircraft propulsion.
1-2-1
Page 2
Dec 01/14
@A380
AIRCRAFT DESCRIPTION
2-1-1
**ON A/C A380-800
1.
The following table provides characteristics of A380-800 Models, these data are specific to each
Weight Variant:
WV000
Aircraft Characteristics
WV001
WV002
Maximum Ramp Weight
(MRW)
562 000 kg
512 000 kg 571 000 kg
Maximum Taxi Weight (1 238 998 lb) (1 128 766 lb) (1 258 839 lb)
(MTW)
Maximum Take-Off
Weight (MTOW)
560 000 kg
510 000 kg 569 000 kg
(1 234 588 lb) (1 124 357 lb) (1 254 430 lb)
Maximum Landing
Weight (MLW)
Maximum Zero Fuel
Weight (MZFW)
386 000 kg
(850 984 lb)
361 000 kg
(795 869 lb)
394 000 kg
(868 621 lb)
372 000 kg
(820 119 lb)
391 000 kg
(862 007 lb)
366 000 kg
(806 892 lb)
WV006
WV007
WV005
Maximum Ramp Weight
(MRW)
562 000 kg
575 000 kg 492 000 kg
Maximum Taxi Weight (1 238 998 lb) (1 267 658 lb) (1 084 674 lb)
(MTW)
Maximum Take-Off
Weight (MTOW)
560 000 kg
573 000 kg 490 000 kg
(1 234 588 lb) (1 263 248 lb) (1 080 265 lb)
Maximum Landing
Weight (MLW)
Maximum Zero Fuel
Weight (MZFW)
386 000 kg
(850 984 lb)
366 000 kg
(806 892 lb)
393 000 kg
(866 416 lb)
368 000 kg
(811 301 lb)
395 000 kg
(870 826 lb)
373 000 kg
(822 324 lb)
2-1-1
WV003
WV004
512 000 kg
(1 128 766
lb)
562 000 kg
(1 238 998 lb)
510 000 kg
560 000 kg
(1 124 357
(1 234 588 lb)
lb)
395 000 kg
391 000 kg
(870 826 lb) (862 007 lb)
373 000 kg
366 000 kg
(822 324 lb) (806 892 lb)
WV008
WV009
577 000 kg
(1 272 067
lb)
512 000 kg
(1 128 766 lb)
575 000 kg
510 000 kg
(1 267 658
(1 124 357 lb)
lb)
394 000 kg
386 000 kg
(868 621 lb) (850 984 lb)
369 000 kg
361 000 kg
(813 506 lb) (795 869 lb)
Page 1
Dec 01/14
@A380
2.
The following table provides characteristics of A380-800 Models, these data are common to each
Weight Variant:
Standard Seating
Capacity
555
Usable Fuel Capacity
(density = 0.785
kg/l)
323 546 l
(85 472 US gal)
253 983 kg
(559 937 lb)
Pressurized Fuselage
Volume (A/C non
equipped, main and
upper deck)
Passenger
Compartment Volume
(main deck)
Passenger
Compartment Volume
(upper deck)
Cockpit Volume
Usable Volume, FWD
CC
(Based on LD3)
Usable Volume, AFT
CC
(Based on LD3)
Usable Volume, Bulk
CC
Water Volume, FWD
CC
Water Volume, AFT
CC
Water Volume, Bulk
CC
2 100 m3
(74 161 ft3)
775 m3
(27 369 ft3)
530 m3
(18 717 ft3)
12 m3
(424 ft3)
89.4 m3
(3 157 ft3)
71.5 m3
(2 525 ft3)
14.3 m3
(505 ft3)
131 m3
(4 626 ft3)
107.8 m3
(3 807 ft3)
17.3 m3
(611 ft3)
2-1-1
Page 2
Dec 01/14
@A380
2-2-0
**ON A/C A380-800
1.
This section provides General Aircraft Dimensions.
2-2-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
72.73 m
(238.62 ft)
70.4 m
(230.97 ft)
53.94 m
(176.97 ft)
14.08 m
(46.19 ft)
4.7 m
(15.42 ft)
8.41 m
(27.59 ft)
14.59 m
(47.87 ft)
12.06 m
(39.57 ft)
8.56 m
(28.08 ft)
4.97 m
(16.31 ft)
33.58 m − WLG
(110.17 ft)
36.85 m − BLG
(120.9 ft)
30.37 m
(99.64 ft)
79.75 m
(261.65 ft)
12.46 m
(40.88 ft)
7.14 m
(23.43 ft)
5.26 m
(17.26 ft)
14.34 m
(47.05 ft)
29.6 m
(97.11 ft)
51.4 m
(168.64 ft)
NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.
L_AC_020200_1_0010101_01_02
(Sheet 1 of 2)
FIGURE-2-2-0-991-001-A01
2-2-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
72.57 m
(238.09 ft)
68.85 m
(225.89 ft)
46.97 m
(154.1 ft)
3.98 m
(13.06 ft)
52.07 m
(170.83 ft)
29.94 m
(98.23 ft)
11.57 m
(37.96 ft)
3.72 m
(12.2 ft)
22.23 m
(72.93 ft)
17.67 m
(57.97 ft)
NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.
25.97 m
(85.2 ft)
17.65 m
(57.91 ft)
21.87 m
(71.75 ft)
13.49 m
(44.26 ft)
9.36 m
(30.71 ft)
L_AC_020200_1_0010103_01_00
(Sheet 2 of 2)
FIGURE-2-2-0-991-001-A01
2-2-0
Page 3
Dec 01/14
@A380
2-3-0
Ground Clearances
**ON A/C A380-800
Ground Clearances
1.
This section provides the heights of various points of the aircraft, above the ground, for different
aircraft configurations.
Dimensions in the tables are approximate and will vary with tire type, weight and balance and other
special conditions.
The dimensions are given for:
- A light weight, for an aircraft in maintenance configuration with a FWD CG and an AFT CG,
- An aircraft at Maximum Ramp Weight with a FWD CG and an AFT CG,
- Aircraft on jacks, FDL at 7.20 m (23.62 ft).
NOTE : Passenger and cargo door ground clearances are measured from the center of the door sill
and from floor level.
2-3-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
M1
M2
F2
U1
M3
W1 W2 C3 C2
VT
A/C
CONFIGURATION
FUSELAGE
WINGS
TAILPLANE
M1
M2
M3
M4
M5
U1
U2
U3
C1
C2
C3
F1
F2
F3
BF1
BF2
CP1
RD1
W1
W2
HT
HT1
VT
N1
N2
HT1 HT
RD1 CP1
C1
BF2
DOORS
U2 M4 U3 M5
F3
N2 BF1 N1
MRW
FWD CG
AFT CG
(37.8%)
(41%)
m
m
ft
ft
5.10
16.8
5.13
16.7
5.12
16.9
5.14
16.8
5.15
16.9
5.15
16.9
5.18
16.9
5.15
17.0
5.20
16.9
5.16
17.1
7.87
25.9
7.89
25.8
7.91
25.9
7.90
26.0
7.94
26.0
7.91
26.0
3.05
10.1
3.08
10.0
3.11
10.2
3.10
10.2
3.24
10.6
3.23
10.6
2.34
7.7
2.38
7.8
35.3
35.4
10.75
10.79
35.5
35.4
10.83
10.78
5.4
5.4
1.66
1.66
7.4
7.3
2.27
2.22
7.13
23.4
23.5
7.17
4.74
15.6
4.82
15.8
7.55
7.49
24.8
24.6
5.27
5.21
17.3
17.1
9.20
9.15
30.2
30.0
7.65
7.60
25.1
24.9
79.3
79.1
24.17
24.12
1.05
1.08
3.4
3.5
1.90
6.2
1.90
6.2
F1
300 t
FWD CG
AFT CG
(29%)
(44%)
m
m
ft
ft
17.6
16.9
5.14
5.36
17.5
5.20
5.34
17.1
5.30
5.31
17.4
17.4
17.3
17.6
5.37
5.28
17.3
17.8
5.42
5.27
26.2
26.5
7.98
8.08
26.6
26.4
8.10
8.04
26.7
26.3
8.15
8.02
10.6
10.8
3.24
3.30
10.7
10.6
3.27
3.23
11.0
3.41
3.36
11.2
2.45
8.0
2.59
8.5
35.6
36.1
10.84
11.00
36.0
35.9
10.97
10.93
6.0
6.0
1.82
1.82
7.9
7.8
2.38
2.41
7.16
23.5
24.3
7.42
4.76
15.6
5.02
16.5
8.27
8.22
27.0
27.1
5.97
5.94
19.6
19.5
9.30
9.20
30.5
30.2
7.75
7.65
25.4
25.1
79.6
79.3
24.27
24.17
1.30
1.30
4.3
4.3
7.4
7.4
2.27
2.27
ENGINE/
NACELLE
NOTE:
− PASSENGER AND CARGO DOOR GROUND CLEARANCES ARE MEASURED
FROM THE CENTER OF THE DOOR SILL AND FROM FLOOR LEVEL.
− MAXIMUM JACKING WEIGHT = 333 700 kg (735 682 lb).
A/C JACKED
FDL = 7.20 m
(23.6 ft)
m
7.15
7.15
7.15
7.15
7.15
9.90
9.90
9.90
5.12
5.12
5.24
4.41
12.82
12.82
3.68
4.27
9.22
6.84
10.12
7.84
11.14
9.59
26.11
3.14
4.13
ft
23.5
23.5
23.5
23.5
23.5
32.5
32.5
32.5
16.8
16.8
17.2
14.5
42.1
42.1
12.1
14.0
30.2
22.4
33.2
25.7
36.5
31.5
85.7
10.3
13.5
L_AC_020300_1_0010101_01_04
Ground Clearances
(Sheet 1 of 2)
FIGURE-2-3-0-991-001-A01
2-3-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
A
B
C D
E
F
J
G H
K
L
LEADING EDGE SLATS EXTENDED
MRW
FWD CG
DESCRIPTION
DN1* INBD END
MRW
AFT CG
300 t
MID CG
m
ft
m
ft
m
ft
A
3.95
13.0
3.98
13.1
4.10
13.5
DN1/DN2*
B
4.60
15.1
4.62
15.2
4.78
15.7
DN2* OUTBD END
C
5.12
16.8
5.13
16.8
5.32
17.5
SLAT 2 INBD END
D
5.12
16.8
5.13
16.8
5.35
17.6
SLAT 2/3
E
5.34
17.5
5.35
17.6
5.61
18.4
SLAT 3/4
F
5.53
18.1
5.53
18.1
5.85
19.2
SLAT 4 OUTBD END
G
5.65
18.5
5.65
18.5
6.04
19.8
SLAT 5 INBD END
H
5.78
19.0
5.77
18.9
6.21
20.4
SLAT 5/6
J
5.89
19.3
5.87
19.3
6.40
21.0
SLAT 6/7
K
5.98
19.6
5.96
19.6
6.58
21.6
SLAT 7 OUTBD END
L
6.05
19.8
6.02
19.8
6.75
22.1
NOTE:
* DN − DROOP NOSE
L_AC_020300_1_0040101_01_01
Ground Clearances
Leading Edge Slats - Extended
FIGURE-2-3-0-991-004-A01
2-3-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
D
B
C
A
FLAPS EXTENDED
MRW
FWD CG
DESCRIPTION
m
ft
MRW
AFT CG
m
ft
300 t
MID CG
m
ft
INNER END
A
1.54
5.1
1.53
5.0
1.71
5.6
INNER/MID
B
3.43
11.3
3.42
11.2
3.66
12.0
MID OUTER
C
4.56
15.0
4.54
14.9
4.92
16.1
OUTER END
D
5.11
16.8
5.08
16.7
5.61
18.4
L_AC_020300_1_0050101_01_01
Ground Clearances
Trailing Edge Flaps - Extended
FIGURE-2-3-0-991-005-A01
2-3-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
K
J
H
F
G
E
DC
B
A
SPOILERS EXTENDED
MRW
FWD CG
DESCRIPTION
m
SPOILER 1 INBD
SPOILER 1/2
SPOILER 2 OUTBD END
SPOILER 3
SPOILER 3/4
SPOILER 4/5
SPOILER 5/6
SPOILER 6/7
SPOILER 7/8
SPOILER 8 OUTBD END
A
B
C
D
E
F
G
H
J
K
4.98
5.62
6.09
6.32
6.56
6.79
6.94
7.02
7.02
7.00
ft
16.3
18.4
20.0
20.7
21.5
22.3
22.8
23.0
23.0
23.0
MRW
AFT CG
m
4.97
5.61
6.08
6.31
6.55
6.78
6.93
7.00
7.00
6.98
ft
16.3
18.4
19.9
20.7
21.5
22.2
22.7
23.0
23.0
22.9
300 t
MID CG
m
5.17
5.81
6.31
6.55
6.80
7.07
7.25
7.36
7.42
7.45
ft
17.0
19.1
20.7
21.5
22.3
23.2
23.8
24.1
24.3
24.4
L_AC_020300_1_0060101_01_00
Ground Clearances
Spoilers - Extended
FIGURE-2-3-0-991-006-A01
2-3-0
Page 5
Dec 01/14
@A380
**ON A/C A380-800
D
C
B
A
AILERONS DOWN
MRW
FWD CG
DESCRIPTION
m
INNER END
INNER/MID
MID OUTER
OUTER END
A
B
C
D
5.83
5.90
5.99
6.12
ft
19.1
19.4
19.7
20.1
MRW
AFT CG
m
5.80
5.87
5.96
6.08
ft
19.0
19.3
19.6
19.9
300 t
MID CG
m
6.32
6.43
6.58
6.78
ft
20.7
21.1
21.6
22.2
L_AC_020300_1_0070101_01_01
Ground Clearances
Ailerons - Down
FIGURE-2-3-0-991-007-A01
2-3-0
Page 6
Dec 01/14
@A380
**ON A/C A380-800
D
C
B
A
AILERONS UP
MRW
FWD CG
DESCRIPTION
m
INNER END
INNER/MID
MID OUTER
OUTER END
A
B
C
D
6.38
6.41
6.45
6.50
ft
20.9
21.0
21.2
21.3
MRW
AFT CG
m
6.35
6.38
6.41
6.46
ft
20.8
20.9
21.0
21.2
300 t
MID CG
m
6.87
6.94
7.04
7.17
ft
22.5
22.8
23.1
23.5
L_AC_020300_1_0080101_01_01
Ground Clearances
Ailerons - Up
FIGURE-2-3-0-991-008-A01
2-3-0
Page 7
Dec 01/14
@A380
**ON A/C A380-800
D
E
C
B
A
FLAP TRACKS EXTENDED
MRW
FWD CG
DESCRIPTION
m
TRACK 2
TRACK 3
TRACK 4
TRACK 5
TRACK 6
A
B
C
D
E
2.17
2.87
3.08
3.48
3.86
ft
7.1
9.4
10.1
11.4
12.7
MRW
AFT CG
m
2.15
2.85
3.06
3.45
3.82
ft
7.1
9.4
10.0
11.3
12.5
300 t
MID CG
m
2.37
3.12
3.42
3.89
4.35
ft
7.8
10.2
11.2
12.8
14.3
L_AC_020300_1_0090101_01_01
Ground Clearances
Flap Tracks - Extended
FIGURE-2-3-0-991-009-A01
2-3-0
Page 8
Dec 01/14
@A380
**ON A/C A380-800
6.55 m
(21.49 ft)
NOTE:
TRIMMABLE HORIZONTAL STABILIZER AND ELEVATORS
ARE IN FULLY DOWN POSITION.
L_AC_020300_1_0100101_01_00
Ground Clearances
Trimmable Horizontal Stabilizer and Elevators - Down
FIGURE-2-3-0-991-010-A01
2-3-0
Page 9
Dec 01/14
@A380
2-4-0
**ON A/C A380-800
1.
2-4-0
Page 1
Dec 01/14
@A380
2-4-1
Standard Configuration
**ON A/C A380-800
Standard Configuration - Pax
1.
This section gives the standard configuration of A380-800 models
2-4-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
UPPER DECK
PASSENGER SEATS UPPER DECK (199 TOTAL)
BUSINESS CLASS 96 SEATS
TOURIST CLASS 103 SEATS
ATTENDANT SEATS 8
COAT STOWAGE 6
GALLEYS 8
LAVATORIES 7
STOWAGES 1
LIFT 2
STAIRS 2
CREW REST BUNKS 5
L_AC_020401_1_0010101_01_00
Interior Arrangements - Plan View
Standard Configuration - Upper Deck
FIGURE-2-4-1-991-001-A01
2-4-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
MAIN DECK
PASSENGER SEATS MAIN DECK (356 TOTAL)
FIRST CLASS 22 SEATS
TOURIST CLASS 334 SEATS
ATTENDANT SEATS 12
COAT STOWAGE 1
GALLEYS 9
LAVATORIES 10
STOWAGES 1
LIFT 2
STAIRS 2
L_AC_020401_1_0020101_01_00
Interior Arrangements - Plan View
Standard Configuration - Main Deck
FIGURE-2-4-1-991-002-A01
2-4-1
Page 3
Dec 01/14
@A380
2-5-0
**ON A/C A380-800
1.
2-5-0
Page 1
Dec 01/14
@A380
2-5-1
Typical Configuration
**ON A/C A380-800
Typical Configuration - Pax
1.
This section gives the typical configuration of A380-800 models.
2-5-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
UPPER DECK
TOURIST CLASS 8 ABREAST
1.07 m
1.07 m
1.07 m
1.07 m
(42 in)
(42 in)
(42 in)
(42 in)
0.51 m
(20 in)
UPPER DECK
BUSINESS CLASS 6 ABREAST
1.37 m
(54 in)
1.37 m
(54 in)
1.37 m
(54 in)
0.58 m
(23 in)
L_AC_020501_1_0010101_01_00
Interior Arrangements - Cross-section
Typical Configuration - Upper Deck
FIGURE-2-5-1-991-001-A01
2-5-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
MAIN DECK
TOURIST CLASS 10 ABREAST
1.57 m
(62 in)
1.07 m
1.07 m
(42 in)
(42 in)
1.57 m
(62 in)
0.51 m
(20 in)
MAIN DECK
FIRST CLASS 6 ABREAST
1.45 m
(57 in)
1.45 m
(57 in)
1.45 m
(57 in)
0.97 m
(38 in)
L_AC_020501_1_0020101_01_00
Interior Arrangements - Cross-section
Typical Configuration - Main Deck
FIGURE-2-5-1-991-002-A01
2-5-1
Page 3
Dec 01/14
@A380
2-6-0
Cargo Compartments
**ON A/C A380-800
Cargo Compartments
1.
Cargo Compartments
2-6-0
Page 1
Dec 01/14
@A380
2-6-1
**ON A/C A380-800
Location and Dimensions - Pax
1.
This section gives the cargo compartments location and dimensions of A380-800 models.
2-6-1
Page 1
Dec 01/14
@A380
LOWER DECK
BULK CARGO
COMPARTMENT
LOWER DECK
FORWARD AFT CARGO LOWER DECK
COMPARTMENT
REAR AFT CARGO
(T−SHAPED
COMPARTMENT
COMPARTMENT)
1.1 m
(43.3 in)
2.8 m
(110.2 in)
2.8 m
(110.2 in)
8.2 m
(322.8 in)
9.7 m
(381.9 in)
FR44
FR57
FR86 FR90
**ON A/C A380-800
17.4 m
(685.04 in)
LOWER DECK
FORWARD CARGO
COMPARTMENT
FR17
3.1 m
(122.8 in)
L_AC_020601_1_0010101_01_00
Cargo Compartments
FIGURE-2-6-1-991-001-A01
2-6-1
Page 2
Dec 01/14
@A380
2-6-2
**ON A/C A380-800
Loading Combinations - Pax
1.
This section gives cargo compartments loading combinations.
2-6-2
Page 1
Dec 01/14
STANDARD: 20 LD−3 OR 7 PALLETS 88 in / 96 in X 125 in
OPTION: 22 LD−3 OR 7 PALLETS 88 in / 96 in X 125 in
STANDARD: 16 LD−3 OR 6 LD−3 3 PALLETS 88 in / 96 in X 125 in
OPTION: 6 PALLETS 88 in / 96 in X 125 in
@A380
**ON A/C A380-800
L_AC_020602_1_0010101_01_00
Cargo Compartments
FIGURE-2-6-2-991-001-A01
2-6-2
Page 2
Dec 01/14
@A380
2-7-0
Door Clearances
**ON A/C A380-800
Door Clearances
1.
This section provides door clearances and location.
2-7-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
EMERGENCY
EXIT DOOR
M3L
DOOR
U1L
DOOR
M1L
DOOR
U2L
DOOR
M2L
DOOR
U3L
DOOR
M4L
DOOR
U3R
DOOR
M5R
BULK
CARGO DOOR
DOOR
U2R
EMERGENCY
EXIT DOOR
M3R
DOOR
M5L
DOOR
U1R
DOOR
M2R
DOOR
M4R
AFT
CARGO DOOR
DOOR
M1R
FWD
CARGO DOOR
L_AC_020700_1_0010101_01_01
Door Clearances
Door Location (Sheet 1)
FIGURE-2-7-0-991-001-A01
2-7-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
53.63 m
(175.95 ft)
49.19 m
(161.38 ft)
44.74 m
(146.78 ft)
40.3 m
(132.22 ft)
32.68 m
(107.22 ft)
20.94 m
(68.7 ft)
16.5 m
(54.13 ft)
6.32 m
(20.73 ft)
11.73 m
(38.48 ft)
48.07 m
(157.71 ft)
51.09 m
(167.62 ft)
L_AC_020700_1_0020101_01_01
Door Clearances
Door Location (Sheet 2)
FIGURE-2-7-0-991-002-A01
2-7-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
MAIN DECK DOOR
M1L, M1R
2.13 m
(6.99 ft)
1.90 m
(6.23 ft)
0.05 m
(0.16 ft)
SEE
CHAPTER
2−3
FWD
1.26 m
(4.13 ft)
0.04 m
(0.13 ft)
0.04 m
(0.13 ft)
1.07 m
(3.51 ft)
0.86 m
01
(2.82 ft)
2.51 m
(8.23 ft)
FWD
0.72 m
01
(2.36 ft)
NOTE:
01 MEASURED FROM THE EXTERNAL POINT OF
THE SCUFF PLATE AND THE MOST
EXTERNAL POINT OF THE DOOR SKIN.
L_AC_020700_1_0050101_01_00
Door Clearances
Forward Passenger Doors
FIGURE-2-7-0-991-005-A01
2-7-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
UPPER DECK DOOR
U1L, U2L, U3L, U1R, U2R, U3R
MAIN DECK DOOR
M2L, M3L, M4L, M2R, M3R, M4R
2.11 m
(6.92 ft)
1.92 m
(6.30 ft)
1.90 m
(6.23 ft)
0.08 m
(0.26 ft)
FWD
2.13 m
(6.99 ft)
SEE
CHAPTER
2−3
0.05 m
(0.16 ft)
SEE
CHAPTER
2−3
0.04 m
(0.13 ft)
0.52 m
(1.71 ft) 01
0.72 m
01
(2.36 ft)
0.04 m
(0.13 ft)
FWD
1.07 m
(3.51 ft)
1.07 m
(3.51 ft)
2.51 m
(8.23 ft)
0.04 m
(0.13 ft)
1.26 m
(4.13 ft)
0.89 m
(2.92 ft) 01
ON M3L/M3R
0.70 m
(2.30 ft) 02
1.02 m
(3.35 ft) 01
ON M3L/M3R
0.84 m
(2.76 ft) 02
0.04 m
(0.13 ft)
2.51 m
(8.23 ft)
NOTE:
01 MEASURED FROM THE EXTERNAL POINT OF THE SCUFF PLATE
AND THE MOST EXTERNAL POINT OF THE DOOR SKIN.
02
ON DOOR M3L/M3R MEASURED FROM THE EXTERNAL POINT
OF THE CUTOUT IN THE BELLY FAIRING AND THE MOST
EXTERNAL POINT OF THE BELLY FAIRING FROM THE DOOR.
L_AC_020700_1_0060101_01_00
Door Clearances
Main and Upper Deck Passenger Doors
FIGURE-2-7-0-991-006-A01
2-7-0
Page 5
Dec 01/14
@A380
**ON A/C A380-800
MAIN DECK DOOR
M5L, M5R
1.90 m
(6.23 ft)
0.05 m
(0.16 ft)
2.13 m
(6.99 ft)
SEE
CHAPTER
2−3
FWD
0.04 m
(0.13 ft)
1.26 m
(4.13 ft)
0.04 m
(0.13 ft)
0.96 m
(3.15 ft) 01
1.07 m
(3.51 ft)
1.09 m
(3.58 ft) 01
2.51 m
(8.23 ft)
FWD
NOTE:
01 MEASURED FROM THE EXTERNAL POINT OF THE SCUFF PLATE
AND THE MOST EXTERNAL POINT OF THE DOOR SKIN.
L_AC_020700_1_0070101_01_00
Door Clearances
Aft Passenger Doors
FIGURE-2-7-0-991-007-A01
2-7-0
Page 6
Dec 01/14
@A380
**ON A/C A380-800
A
A
FWD
3.11 m
(10.20 ft)
1.75 m
(5.74 ft)
SEE
CHAPTER
2−3
2.12 m
(6.96 ft)
R 2.99 m
(9.81 ft)
2.09 m
(6.86 ft)
GROUND LINE
6.34 m
(20.80 ft)
A A
L_AC_020700_1_0080101_01_00
Door Clearances
Forward Cargo Compartment Door
FIGURE-2-7-0-991-008-A01
2-7-0
Page 7
Dec 01/14
@A380
**ON A/C A380-800
A
B
SEE
CHAPTER
2−3
B
1.13 m
(3.71 ft)
A
2.79 m
(9.15 ft)
SEE
CHAPTER
2−3
FWD
6.42 m
(21.06 ft)
2.09 m
(6.86 ft)
1.75 m
(5.74 ft)
R 3.07 m (10.07 ft) AT FR81A
2.01 m R 2.95 m (9..68ft) AT FR85
(6.59 ft)
R 1.40 m
(4.59 ft)
GROUND LINE
0.99 m
(3.25 ft)
B B
A A
L_AC_020700_1_0090101_01_00
Door Clearances
Aft Cargo Compartment Doors
FIGURE-2-7-0-991-009-A01
2-7-0
Page 8
Dec 01/14
@A380
**ON A/C A380-800
B
AIRCRAFT C/L
A
1.36 m
(4.46 ft)
R 1.89 m
(6.20 ft)
FORWARD NOSE
LANDING GEAR
DOOR
62°
2.50 m
(8.20 ft)
0.94 m
(3.08 ft)
GROUND LINE
A
LH SHOWN
RH SYMMETRICAL
L_AC_020700_1_0100101_01_00
Door Clearances
Forward Nose Landing Gear Doors (Sheet 1 of 2)
FIGURE-2-7-0-991-010-A01
2-7-0
Page 9
Dec 01/14
@A380
**ON A/C A380-800
0.75 m
(2.46 ft)
AIRCRAFT C/L
R 1.89 m
(6.20 ft)
0.50 m
(1.64 ft)
69.2°
AFT NOSE LANDING
GEAR DOOR
B
LH SHOWN
RH SYMMETRICAL
L_AC_020700_1_0100102_01_00
Door Clearances
Aft Nose Landing Gear Doors (Sheet 2 of 2)
FIGURE-2-7-0-991-010-A01
2-7-0
Page 10
Dec 01/14
@A380
**ON A/C A380-800
A
3.95 m
(12.96 ft)
30.91 m
(101.41 ft)
4.28 m
(14.04 ft)
AIRCRAFT
1.71 m
(5.61 ft)
R 2.30 m
(7.55 ft)
MAX 79°
WING−LANDING−GEAR
MAIN DOOR
MAX. 0.25 m (0.82 ft)
01
MIN. 0.10 m (0.33 ft)
GROUND LINE
3.23 m
(10.60 ft)
A
LH SHOWN
RH SYMMETRICAL
NOTE:
01 DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.
L_AC_020700_1_0110101_01_00
Door Clearances
Wing Landing Gears - Main Doors
FIGURE-2-7-0-991-011-A01
2-7-0
Page 11
Dec 01/14
@A380
**ON A/C A380-800
A B
5.17 m
(16.96 ft)
35.67 m
(117.03 ft)
5.02 m
(16.47 ft)
AIRCRAFT
2.25 m
(7.38 ft)
R 2.90 m
(9.51 ft)
MAX 99°
BODY−LANDING−GEAR
OUTER DOOR
4.72 m
(15.49 ft)
MAX. 0.35 m (1.15 ft)
01
MIN. 0.25 m (0.82 ft)
GROUND LINE
A
LH SHOWN
RH SYMMETRICAL
NOTE:
L_AC_020700_1_0120101_01_00
Door Clearances
Body Landing Gears - Outer Doors (Sheet 1 of 2)
FIGURE-2-7-0-991-012-A01
2-7-0
Page 12
Dec 01/14
@A380
**ON A/C A380-800
2.25 m
(7.38 ft)
BODY−LANDING−GEAR
INNER DOOR
AIRCRAFT
R 1.32 m
(4.33 ft)
MAX 94°
1.18 m
(3.87 ft)
MAX. 0.95 m (3.12 ft)
MIN. 0.70 m (2.30 ft) 01
1.23 m
(4.04 ft)
GROUND LINE
B
LH SHOWN
RH SYMMETRICAL
NOTE:
L_AC_020700_1_0120102_01_00
Door Clearances
Body Landing Gears - Inner Doors (Sheet 2 of 2)
FIGURE-2-7-0-991-012-A01
2-7-0
Page 13
Dec 01/14
@A380
**ON A/C A380-800
FR112
FR117
APU DOOR
FUSELAGE DATUM LINE
01 MAX. 5.52 m (18.11 ft)
MIN. 5.49 m (18.01 ft)
MAX. 6.66 m (21.85 ft)
01
MIN. 6.63 m (21.75 ft)
GROUND LINE
NOTE:
L_AC_020700_1_0130101_01_00
Door Clearances
APU Doors
FIGURE-2-7-0-991-013-A01
2-7-0
Page 14
Dec 01/14
@A380
2-8-0
Escape Slides
**ON A/C A380-800
Escape Slides
1.
General
This section provides the location of cabin escape facilities and related clearances.
2.
Location
A.
Escape facilities are provided at the following locations:
(1) Upper deck evacuation:
- One slide-raft at each passenger/crew door (total six).
(2) Main deck evacuation:
- One slide-raft at each passenger/crew door (total eight)
- One slide for each emergency exit door (total two). The slides are housed in the belly
fairing for off-the-wing evacuation.
2-8-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
MAIN DECK DUAL−LANE
SLIDE/RAFT
UPPER DECK DUAL−LANE
SLIDE/RAFT
SLIDE/RAFT
SLIDE/RAFT
OFFWING DUAL−LANE
SLIDE/RAFT
COCKPIT ESCAPE
ROPE
SLIDE/RAFT
SLIDE/RAFT
NOTE:
LH SHOWN, RH SYMMETRICAL
L_AC_020800_1_0010101_01_01
Escape Slides
Location
FIGURE-2-8-0-991-001-A01
2-8-0
Page 2
Dec 01/14
@A380
NOTE:
− 42
− 39
− 36
− 33
− 30
− 27
− 24
− 21
− 18
− 15
− 12
−9
−6
−3
0
EMERGENCY DESCENT DEVICE
THROUGH WINDOW OPENING
GRID EQUALS 1 m (3.28 ft) IN REALITY
**ON A/C A380-800
L_AC_020800_1_0020101_01_01
Escape Slides
Dimensions
FIGURE-2-8-0-991-002-A01
2-8-0
Page 3
Dec 01/14
@A380
2-9-0
Landing Gear
**ON A/C A380-800
Landing Gear
1.
General
The aircraft has:
- Two Wing Landing Gears (WLG) with four wheel bogie assembly and related doors
- Two Body Landing Gears (BLG) with six wheel bogie assembly and related doors
- A Nose Landing Gear (NLG) with twin wheel assembly and related doors.
The Wing Landing Gears are located under the wing and retract sideways towards the fuselage
centerline.
The Body Landing Gears are located on the belly and retract rearward into a bay in the fuselage.
The Nose Landing Gear retracts forward into a fuselage compartment below the cockpit.
The landing gear and landing gear doors operation are controlled electrically and are hydraulically and
mechanically operated.
In abnormal operation, the landing gear can be extended by gravity.
For landing gear footprint and tire size, refer to 07-02-00.
2.
Wing Landing Gear
Each wing landing gear has a leg assembly and a four-wheel bogie beam. The WLG leg includes a
Bogie Trim Actuator (BTA) and an oleo-pneumatic shock absorber.
A two-piece side-stay assembly holds the WLG in the extended position. A lock-stay keeps the sidestay assembly stable in the locked down position.
3.
Body Landing Gear
The two body landing gears have a six-wheel bogie beam and a leg assembly that includes an oleopneumatic shock absorber. A two-piece drag-stay assembly mechanically locks the leg in the extended
position.
4.
Nose Landing Gear
The nose landing gear includes a single-stage direct acting oleo-pneumatic shock absorber. A twopiece drag-stay assembly with a lock-stay, mechanically locks the leg in the extended position.
5.
Steering
The wheel steering control system has two parts:
- Nose wheel Steering (NWS)
- Body Wheel Steering (BWS)
Steering is controlled by two hand wheels in the cockpit. For steering angle controlled by the hand
wheels, refer to AMM 32-51-00 (NWS) and refer to AMM 32-54-00 (BWS).
For steering angle limitation, refer to AMM 09-10-00.
2-9-0
Page 1
Dec 01/14
@A380
A steering disconnection box installed on the nose landing gear to allow steering deactivation for
towing purpose.
6.
7.
Landing Gear Servicing Points
A.
General
Filling of the landing gear shock absorbers is through MS28889 standard valves.
Charging of the landing gear shock absorbers is accomplished with nitrogen through MS28889
standard valves.
B.
Charging Pressure
For charging of the landing gear shock absorbers, refer to AMM 32-00-00.
Braking
A.
General
Carbon brakes are installed on each wheel of the WLG and on the wheels of the front and
center axles of the BLG.
The braking system is electrically controlled and hydraulically operated.
The braking system has four braking modes plus autobrake and anti-skid systems:
- Normal braking with anti-skid capability
- Alternative braking with anti-skid capability
- Emergency Braking (with Ultimate Braking)
- Emergency braking without anti-skid protection is also available as an alternative function of
the alternate braking system.
- A park brake system that is manually set is available for the BLG only. This system can also
be used to supply emergency braking.
B.
In-Flight Wheel Braking
Braking occurs automatically during the retraction of the landing gear. This stops the rotation
of the BLG and WLG wheels (except the wheels on the aft axle of each BLG) before the landing
gears go into their related bays.
8.
Tire Pressure Indicating System (TPIS)
The TPIS automatically monitors the tire pressures and shows these values on Test Equipment
(BITE) and also supplies other data and warnings on the WHEEL page of the System Display (SD).
The TPIS includes Built In Test Equipment.
9.
Built In Test Equipment (BITE)
The BITE has these functions, it:
- Continuously monitors its systems for failures
- Sends failure data (maintenance and warnings) to other systems in the aircraft
- Keeps a record of the failures
- Automatically does specified tests of the system, or part of the system, at specified times
- Lets specified tests to be done during the maintenance procedures.
The BITE for the following systems is described in these chapters:
- The Brakes and Steering
2-9-0
Page 2
Dec 01/14
@A380
-
The TPIS
The Landing Gear.
2-9-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
HINGED DOOR
FAIRING DOOR
B
A
AUXILIARY
DOOR
F
MAIN DOOR
(HYDRAULICALLY OPERATED)
E
WLG LEG
ASSEMBLY
D
G
SHOCK
ABSORBER
TORQUE
LINKS
AFT
AXLE
SLAVE
LINKS
BOGIE TRIM
ACTUATOR
BRAKE ROD
ASSEMBLY
BOGIE BEAM
ASSEMBLY
FWD
AXLE
TIRE INFLATION ADAPTER
(EXAMPLE)
A
L_AC_020900_1_0050101_01_00
Wing Landing Gear
General (Sheet 1 of 3)
FIGURE-2-9-0-991-005-A01
2-9-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
WLG DOOR
ACTUATOR
QUICK RELEASE PIN
C
WARNING FLAG
B
SAFETY COLLAR
C
LOCK LINK
DOWNLOCK
SPRINGS
UNLOCK
ACTUATOR
GROUND LOCK PIN
SIDE STAY
ASSEMBLY
D
L_AC_020900_1_0050102_01_00
Wing Landing Gear
Safety Devices (Sheet 2 of 3)
FIGURE-2-9-0-991-005-A01
2-9-0
Page 5
Dec 01/14
@A380
**ON A/C A380-800
GROUND POINT
CHARGE VALVE
(NITROGEN)
E
CHECK/FILL
VALVE (OIL)
F
SEAL CHANGEOVER
VALVE (COV)
G
L_AC_020900_1_0050103_01_00
Wing Landing Gear
Servicing (Sheet 3 of 3)
FIGURE-2-9-0-991-005-A01
2-9-0
Page 6
Dec 01/14
@A380
**ON A/C A380-800
CENTER DOOR
ACTUATOR
DRAG BRACE ASSEMBLY
D
OUTER DOOR ACTUATOR
BLG LEG
ASSEMBLY
B
CENTER DOOR
OUTER DOOR
A
J
INNER DOOR
F
PINTLE
FRAME
BOGIE TRIM
ACTUATOR
STEERING
ACTUATOR
G
OUTER
CYLINDER
H
SLAVE
LINKS
G
SHOCK
ABSORBER
TORQUE
LINKS
BOGIE/AXLE
ASSEMBLY
BRAKE ROD
TIRE INFLATION
ADAPTOR
(EXAMPLE)
A
L_AC_020900_1_0060101_01_00
Body Landing Gear
FIGURE-2-9-0-991-006-A01
2-9-0
Page 7
Dec 01/14
@A380
**ON A/C A380-800
INNER DOOR
ACTUATOR
SAFETY COLLAR
C
B
QUICK
RELEASE
PIN
WARNING
FLAG
C
L_AC_020900_1_0060102_01_00
Body Landing Gear
Door Safety Devices (Sheet 2 of 4)
FIGURE-2-9-0-991-006-A01
2-9-0
Page 8
Dec 01/14
@A380
**ON A/C A380-800
BLG OUTER
DOOR ACTUATOR
SAFETY COLLAR
E
QUICK
RELEASE
PIN
QUICK
RELEASE
PIN
WARNING
FLAG
CENTER DOOR
FITTING
D
QUICK
RELEASE
PIN
LOCKING
PIN
ATTACHMENT PIN
LOCKING
PIN
SAFETY STRUT
SOLID
PIN
ATTACHMENT PIN
E
L_AC_020900_1_0060103_01_00
Body Landing Gear
Door Safety Devices (Sheet 3 of 4)
FIGURE-2-9-0-991-006-A01
2-9-0
Page 9
Dec 01/14
@A380
**ON A/C A380-800
DRAIN
VALVE
CHARGING VALVE
(NITROGEN)
F
G
GROUNDING
POINTS
TYPICAL
LOCK LINKS
SEAL CHANGEOVER
VALVE (COV)
LOCK SPRINGS
GROUND LOCK PIN
H
J
L_AC_020900_1_0060104_01_00
Body Landing Gear
Servicing and Safety Device (Sheet 4 of 4)
FIGURE-2-9-0-991-006-A01
2-9-0
Page 10
Dec 01/14
@A380
**ON A/C A380-800
FORWARD
DOOR
B
DRAG STAY ASSEMBLY
DOOR
ACTUATOR
RETRACTION
ACTUATOR
REAR
DOOR
STEERING
MECHANISM
NWS
ACTUATOR
A
C
STEERING
DISCONNECT
PANEL
L
TOWING
ADAPTER
E
MAIN FITTING
MAINTENANCE
SERVICE PANEL
H
J
TORQUE
LINKS
SHOCK
ABSORBER
AXLE
TIRE INFLATION
ADAPTER
JACKING
POINT
A
L_AC_020900_1_0070101_01_00
Nose Landing Gear
FIGURE-2-9-0-991-007-A01
2-9-0
Page 11
Dec 01/14
@A380
**ON A/C A380-800
D
NLG DOOR
ACTUATOR
LOCK STAY
UNLOCK
ACTUATOR
GROUND LOCK PIN
C
WARNING FLAG
B
SAFETY COLLAR
QUICK
RELEASE PIN
D
L_AC_020900_1_0070102_01_00
Nose Landing Gear
Safety Devices (Sheet 2 of 4)
FIGURE-2-9-0-991-007-A01
2-9-0
Page 12
Dec 01/14
@A380
**ON A/C A380-800
F
G
E
GROUND TOWING SWITCH
SAFETY PIN
G
F
24GC
STEERING DISCONNECT PANEL
L_AC_020900_1_0070103_01_00
Nose Landing Gear
Steering Disconnect Panel (Sheet 3 of 4)
FIGURE-2-9-0-991-007-A01
2-9-0
Page 13
Dec 01/14
@A380
**ON A/C A380-800
K
GROUND
POINT
SEAL CHANGEOVER
VALVE (COV)
J
H
DRAIN VALVE
CHARGE VALVE
(NITROGEN)
L
K
L_AC_020900_1_0070104_01_00
Nose Landing Gear
Servicing (Sheet 4 of 4)
FIGURE-2-9-0-991-007-A01
2-9-0
Page 14
Dec 01/14
@A380
**ON A/C A380-800
1.
General
The maintenance pit envelopes for the landing gear shock absorber maintenance are shown in Figures
1 - 4.
The three envelopes show the minimum dimensions for these maintenance operations:
- Extension and retraction
- Gear removal
- Piston removal.
All dimensions shown are minimum dimensions with zero clearances. The dimensions for the pits have
been determined as follows:
- The length and width of the pits allow the gear to rotate as the weight is taken off the landing
gear
- The landing gear is in the maximum grown condition
- The WLG and BLG bogie beams are removed before the piston is removed
- The NLG wheels are removed before the piston is removed
- All pistons are removed vertically.
Dimensions for elevators and associated mechanisms must be added to those in Figures 1 - 3.
A.
Elevators
These can be either mechanical or hydraulic. They are used to:
(1) Permit easy movement of persons and equipment around the landing gears.
(2) To lift and remove landing gear assemblies out of the pits.
B.
Jacking
The aircraft must be in position over the pits to put the gear on the elevators. Jacks must be
installed and engaged with all the jacking points, Ref. Section 2-14 for aircraft maintenance
jacking. Jacks must support the total aircraft weight, i.e. when the landing gears do not touch
the elevators on retraction/extension tests.
When tripod support jacks are used the tripod-base circle radius must be limited because the
locations required for positioning the columns are close to the sides of the pits.
2-9-0
Page 15
Dec 01/14
1 663
(65.5)
2-9-0
LH SHOWN
RH SYMMETRICAL
WING JACKING POINT
4 506
(177.4)
AIRCRAFT CENTER LINE
33 659
(1 325.2)
FWD JACKING POINT
NLG EXTENSION/RETRACTION PIT OUTLINE
DIMENSIONS IN mm
(INCHES IN BRACKETS)
MINIMUM DIMENSIONS, ZERO CLEARANCES SHOWN
5 625.5
(221.5)
2 598
(102.3)
763
(30)
1 526
(60.1)
WLG PISTON REMOVAL PIT OUTLINE
WLG EXTENSION/RETRACTION
PIT OUTLINE
WLG REMOVAL PIT OUTLINE
BLG EXTENSION/RETRACTION
PIT OUTLINE
BLG PISTON REMOVAL PIT OUTLINE
BLG REMOVAL PIT OUTLINE
@A380
**ON A/C A380-800
FRONT OF NOSE RADOME
L_AC_020900_1_0010101_01_00
Maintenance Pit Envelopes
FIGURE-2-9-0-991-001-A01
Page 16
Dec 01/14
@A380
**ON A/C A380-800
DIMENSIONS IN mm
576
(22.7)
NLG EXTENSION/RETRACTION
709
(27.9)
NLG REMOVAL/INSTALLATION
1 725
(67.9)
NLG PISTON REMOVAL/INSTALLATION
802
(31.6)
1 243
(48.9) 1 989
(78.3)
WLG PISTON REMOVAL/INSTALLATION
WLG REMOVAL/INSTALLATION
BLG PISTON REMOVAL/INSTALLATION
804
(31.7) 1 127
(44.4)
1 977
(77.8)
BLG REMOVAL/INSTALLATION
L_AC_020900_1_0020101_01_00
Necessary Depths
FIGURE-2-9-0-991-002-A01
2-9-0
Page 17
Dec 01/14
3 560
(140.2)
2-9-0
1 067
(42)
513
(20.2)
2 585
(101.8)
7 134
(280.9)
3 158
(124.3)
3 711
(146.1)
WLG PISTON REMOVAL
PIT OUTLINE
2 791
(109.9)
DIMENSIONS IN mm
WLG REMOVAL
PIT OUTLINE
6 228
(245.2)
PIT OUTLINE
972
(38.3)
952
(37.5)
1 929
(75.9)
2 368
(93.2)
4 126
(162.4)
1 490
(58.7)
BLG REMOVAL PIT OUTLINE
@A380
**ON A/C A380-800
L_AC_020900_1_0030101_01_00
Maintenance Pit Envelopes - WLG Pit Dimensions
FIGURE-2-9-0-991-003-A01
Page 18
Dec 01/14
2-9-0
1 168
(46)
3 188
(125.5)
BLG REMOVAL
PIT OUTLINE
DIMENSIONS IN mm
PIT OUTLINE
2 632
(103.6)
7 134
(280.9)
4 856
(191.2)
133
(5.2)
2 105
(82.9)
1 490
(58.7)
WLG EXTENSION/RETRACTION PIT OUTLINE
WLG REMOVAL PIT OUTLINE
BLG PISTON REMOVAL
PIT OUTLINE
1 680
(66.1)
1 052
(41.4)
@A380
**ON A/C A380-800
L_AC_020900_1_0040101_01_00
Maintenance Pit Envelopes - BLG Pit Dimensions
FIGURE-2-9-0-991-004-A01
Page 19
Dec 01/14
@A380
2-10-0
Exterior Lighting
**ON A/C A380-800
Exterior Lighting
1.
General
This section gives the location of the aircraft exterior lighting.
EXTERIOR LIGHTING
ITEM
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
DESCRIPTION
RIGHT NAVIGATION LIGHT (GREEN)
LEFT NAVIGATION LIGHT (RED)
TAIL NAVIGATION LIGHT (WHITE)
OBSTRUCTION LIGHT
UPPER ANTI-COLLISION LIGHTS/BEACONS
(RED)
LOWER ANTI-COLLISION LIGHT/BEACON
(RED)
LOGO LIGHTS
ENGINE SCAN LIGHTS
WING SCAN LIGHTS
WING STROBE LIGHT (HIGH INTENSITY,
WHITE)
TAIL STROBE LIGHT (HIGH INTENSITY,
WHITE)
TAXI CAMERA LIGHTS (NLG)
TAXI CAMERA LIGHTS (MLG)
LANDING LIGHTS
RUNWAY TURN-OFF LIGHTS
TAXI LIGHTS
TAKE-OFF LIGHTS
CARGO COMPARTMENT FLOOD LIGHTS
LANDING GEAR BAY/WELL LIGHTS (DOME)
2-10-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
7
5
10
4
1 RH
8
2 LH
9
11
3
13
6
12
L_AC_021000_1_0070101_01_00
Exterior Lighting
FIGURE-2-10-0-991-007-A01
2-10-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
16
14
17
15
L_AC_021000_1_0080101_01_00
Exterior Lighting
FIGURE-2-10-0-991-008-A01
2-10-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
3
1
2
8
8
15
15
17
L_AC_021000_1_0090101_01_00
Exterior Lighting
FIGURE-2-10-0-991-009-A01
2-10-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
11
5
5
6
10
10
9
9
16
16
14
14
L_AC_021000_1_0100101_01_00
Exterior Lighting
FIGURE-2-10-0-991-010-A01
2-10-0
Page 5
Dec 01/14
@A380
**ON A/C A380-800
7
7
18
19
18
19
EXAMPLE FOR LIGHT N° 18
CEILING LIGHT
SPOT LIGHT
GROUND
L_AC_021000_1_0110101_01_00
Exterior Lighting
FIGURE-2-10-0-991-011-A01
2-10-0
Page 6
Dec 01/14
@A380
2-11-0
**ON A/C A380-800
1.
This section gives the location of antennas and probes.
2-11-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
WEATHER RADAR
SSA(1)
GPS(2)
GPS(1)
TCAS TOP(1)
TCAS TOP(2)
VHF(1)
SATCOM(1)
ISP(1−1)
HF
VHF(3)
ELT
MFP(1)
ISP(2−1)
ISP(3−1)
RADIO ALTIMETRE(1)
MARKER
VHF(2)
RADIO ALTIMETRE(2)
RADIO ALTIMETRE(3)
ICE DETECTOR PROBE LH
GLIDE TRACK
STBY PITOT
STBY STATIC PROBE(1)
GLIDE CAPTURE
LOC
VOR
SSA(2/3)
ADF(2)
STBY STATIC PROBE(2)
ADF(1)
ISP(1−2)
ISP(2−2)
MFP(2)
DME(2) BOTTOM
MFP(3)
TCAS BOTTOM(1)
DME(1) BOTTOM
ISP(3−2)
TCAS BOTTOM(2)
ICE DETECTOR PROBE RH
L_AC_021100_1_0010101_01_00
Antennas and Probes
Location
FIGURE-2-11-0-991-001-A01
2-11-0
Page 2
Dec 01/14
@A380
2-12-0
Power Plant
**ON A/C A380-800
1.
General
- The APU is installed in the tail cone, at the rear part of the fuselage (Section 19.1), inside a
fireproof compartment (between frames 112 and 117).
- The Air Intake System is located on top of the APU and crosses the space between the APU
plenum chamber and the aircraft outside (upper right side position). The Air Intake Housing is
located between frames 111 and 113 and the Air Intake Duct is located in the space between
frames 113 and 115.
- The Exhaust Muffler is located at the end of the tail cone, aligned with the APU and crosses
three different zones, from frame 116 to the rear fairing.
- The Electronic Control Box (ECB) is installed in an electronic cooled rack, closed to frame 95,
within the pressurized fuselage.
2.
Controls and Indication
Primary APU controls and indications are installed in the cockpit, mainly in the overhead panel,
center pedestal panel and forward center panel. Additionally, two external emergency shutoff controls
are installed on the Nose Landing Gear panel and on the Refuel/Defuel panel.
2-12-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
Z310
A B
STA75622 / FR117
313AZ
STA72922 / FR112
STA72320 / FR110
317AB
315BL
315AR
315AL
313AB
A
NOTE: THE DISTANCE FROM FR94, FR98, FR100 BOTTOM
CENTERLINE TO FUSELAGE DATUM (FD) AS FOLLOWS:
FR112 TO FD = 974.9 mm (38.38 in)
FR117 TO FD = 1 772.4 mm (69.78 in)
FR120 TO FD = 2 239.8 mm (88.18 in).
L_AC_021200_1_0010101_01_00
Access Doors
FIGURE-2-12-0-991-001-A01
2-12-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
COOLING AIR DUCT
AIR INTAKE
DUCT ASSEMBLY
EXHAUST
MUFFLER
FIREWALL
STA75622 / FR117
BLEED
LINE
FIRE EXTINGUISHER
BOTTLE
STA72922 / FR112
FIREWALL
STA72320 / FR110
B
L_AC_021200_1_0020101_01_00
General Layout
FIGURE-2-12-0-991-002-A01
2-12-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
Engine and Nacelle
1.
Engine and Nacelle - GP 7200 Engine
A.
Engine
The engine is a high by-pass ratio, two-rotor, axial flow turbofan engine with a high
compression ratio. The Engine has Four Major Sections as Follows:
- compressor section
- combustion section
- turbine section
- accessory drive section.
The compressor section supplies High Pressure (HP) compressed air to the diffuser/burner for
core engine thrust, aircraft service bleed systems, and by-pass air for thrust. A five-stage Low
Pressure (LP) compressor rotor assembly is located to the rear of the fan rotor. An acoustic
splitter fairing directs the primary airstream into the nine-stage HP compressor rotor assembly.
The HP compressor has three stages of variable Inlet Guide Vanes (IGVs) and external bleeds
from stages four, seven, and nine, with an internal bleed from stage six.
The combustion section receives compressed heated air from the HP compressor and fuel from
the fuel nozzles. The mixture of hot air and fuel is ignited and burned in the single-annular
combustion chamber to generate a HP stream of hot gas to turn the HP turbine and LP
turbine.
The turbine section consists of HP turbine and LP turbine. The two-stage HP turbine rotor
assembly receives the hot gas from the diffuser/burner. The HP turbine supplies the power to
turn the HP compressor. The six-stage LP turbine has an active clearance control system for
more efficient engine operation. The LP turbine provides the power to turn the LP compressor
and fan rotor. The Turbine Exhaust Case (TEC) assembly supplies the structural support for the
rear of the engine. The TEC straightens the exhaust gas flow as it exits the engine.
The accessory drive section consists of Main Gearbox (MGB) and Angle Gearbox (AGB). The
MGB supplies the power to turn the attached engine and aircraft accessories. The AGB
transmits the power from the engine rotor to the MGB. During engine start, the AGB transmits
the power from the MGB to turn the engine rotor.
The LP rotor system is independent of the HP rotor system. The LP rotor system consists of
the LP compressor and the LP turbine. The HP rotor system consists of the HP compressor and
the HP turbine.
B.
Nacelle
The Nacelle gives an aerodynamic shape to the engine and supports the thrust reverser system.
Each engine is housed in a nacelle suspended from a pylon attached below the wing.
The nacelle consists of the following major components:
(1) Air Intake Cowl Assembly
The air intake cowl is an interchangeable aerodynamic cowl installed on the forward face
of the engine fan case with bolts. It is designed to provide contour for airflow entering the
engine and attenuates the fan noise.
2-12-0
Page 4
Dec 01/14
@A380
(2) Fan Cowl Assembly
The fan-cowl doors are an assembly of aerodynamic cowls attached to the aircraft pylon
structure through its hinges. It is installed between the air intake cowl and the fan exhaust
cowl/thrust reverser, around the engine fan case. It is composed of two semicircular
panels, the left and the right fan cowl door.
(3) Thrust Reverser
The thrust reverser assembly is installed at the aft part of the nacelle. The thrust reverser
cowls are installed on the aircraft inboard engines. It is attached to the wing pylon by
hinges. The thrust reverser assembly is a standard fixed cascade, translating cowl and
blocker door type thrust reverser. It is only installed on the aircraft inboard position
nacelles. It is made of two halves that make a duct around the engine. Each half consists
of a fixed structure, which gives support for the cascades and actuation system and a
translating cowl.
The thrust reverser assembly encloses the engine core with an aerodynamic flow path and
uses the outer translating cowl to give a fan exhaust duct and nozzle exit.
In stow mode, the thrust reverser is an aerodynamic structure that adds to the engine
thrust generation.
In reverse mode, it is used to turn and direct the fan exhaust air in the forward direction
using blocker door through the cascades. The thrust reverser increases the aircraft braking
function in order to reduce the landing or aborted take-off distance, especially on a
contaminated runway.
(4) Fan Exhaust Cowl Assembly
The fan exhaust cowls is a component of the aircraft propulsion system nacelle. It is
installed at the aft part of the nacelle. The fan exhaust cowls are installed on the aircraft
outboard engines.
The fan exhaust cowls are attached to the wing pylon by hinges. The two halves of the fan
exhaust cowl close the engine core with an aerodynamic flow path.
The fan exhaust structure has two half-cowls hinged at the top to the wing pylon and
latched together at the bottom centerline. Its forward end is secured on the aft of the fan
case and aft of the intermediate engine case.
(5) Exhaust System
The primary air flow is the part of the air absorbed by the engine that enters into the
engine combustor and that is exhausted to atmosphere through the turbine exhaust
system.
The turbine exhaust flow path is formed by the inner wall of the exhaust nozzle and the
outer wall of the exhaust plug.
The secondary air flow is the part of the air absorbed by the fan that bypasses the core
engine and flows through the thrust reverser and fan exhaust cowl directly to the
atmosphere.
2-12-0
Page 5
Dec 01/14
@A380
2.
Engine and Nacelle -TRENT 900 Engine
A.
Engine
The RB211-TRENT 900 engine is a high by-pass ratio, triple spool turbo-fan.
The principal modules of the engine are:
- Low Pressure Compressor (LPC) rotor
- Intermediate Pressure (IP) compressor
- Intermediate case
- HP system (this includes the High Pressure Compressor (HPC), the combustion system and
the High Pressure Turbine (HPT))
- IP turbine
- external gearbox
- LPC case
- Low Pressure Turbine (LPT)
The Intermediate Pressure (IP) and Low Pressure Compressor (LPC)/Low Pressure Turbine
(LPT) assemblies turn in a counter clockwise direction and the High Pressure Compressor
(HPC)/ High Pressure Turbine (HPT) assembly turns in a clockwise direction (when seen from
the rear of the engine) during engine operation.
The compressors increase the pressure of the air, which flows through the engine. The necessary
power to turn the compressors is supplied by turbines.
The LP system has a one-stage compressor installed at the front of the engine. A shaft connects
the single-stage LPC to a five-stage axial flow turbine at the rear of the gas generator. The gas
generator also includes an eight-stage IP compressor, a six-stage HPC and a combustion system.
Each of the compressors in the gas generator is connected to, and turned by, a different turbine.
Between the HPC and the HPT is the annular combustion system which burns a mixture of fuel
and air to supply energy as heat. Behind the LPT there is a collector nozzle assembly through
which the hot gas exhaust flows.
B.
Nacelle
A nacelle gives the engine an aerodynamic shape and supports the thrust reverser system. Each
engine is housed in a nacelle suspended from a pylon attached below the wing.
The nacelle consists of the following major components:
(1) Air Intake Cowl Assembly
The air intake cowl is an interchangeable aerodynamic cowl installed at the front of the
engine. It ducts the airflow to the fan and the engine core. The cowl has panels for easy
access to the components. Acoustic materials are used in the manufacture of the cowl to
help decrease the engine noise.
(2) Fan Cowl Assembly
The fan cowl assembly has two semicircular panels, the left fan cowl door and the right
fan cowl door. The installation of the fan cowl doors is around the engine fan case
between the air intake cowl and the thrust reverser cowl.
2-12-0
Page 6
Dec 01/14
@A380
The fan Cowl Opening System (COS) have two electrical actuators which open or close
the fan cowls. Personnel operate the actuators from the ground only during engine
maintenance operations. The personnel use a switch box located on the air intake cowl.
(3) Thrust Reverser
The thrust reverser assembly is installed at the aft part of the nacelle. The thrust reversers
are installed on the aircraft inboard engines. It is attached to the wing pylon by hinges.
The thrust reverser assembly is a standard fixed cascade, translating cowl and blocker door
type thrust-reverser. It is only installed on the aircraft inboard engine nacelles. It is made
of two halves that make a duct around the engine. Each half has a fixed structure that
holds the cascades, the actuation system and a translating cowl.
The thrust reverser assembly closes the engine core with an aerodynamic flow path and
uses the outer translating cowl to make a fan exhaust duct and nozzle exit.
In stow mode, the thrust reverser is an aerodynamic structure that makes the engine
thrust.
In reverse mode, it changes the direction of the fan exhaust air in the forward direction by
use of the blocker doors through the cascades. The thrust reverser increases the aircraft
braking and speed braking function in order to decrease the landing or aborted take-off
distance, especially on a dirty runway.
(4) Fan Exhaust Cowl Assembly
The fan exhaust cowl is a component of the aircraft engine nacelle. It is installed at the aft
part of the nacelle. The fan exhaust structures are installed on the aircraft outboard
engines. They are attached to the wing pylon by hinges. The left and right fan exhaust
structures closed the engine core with an aerodynamic flow path. The structure gives a fire
protection and a support for the aerodynamic, inertial and engine loads.
The fan exhaust structure has left and right cowls hinged at the top to the wing pylon and
latched together at the bottom centerline. Its forward end is attached at the aft of the fan
case.
(5) Exhaust System
Primary air is the part of the air absorbed by the fan that enters the engine near the fan
blade platform, continues through the Low Pressure (LP) and High Pressure (HP)
compressors, the combustor, and the HP and LP turbines, and is accelerated and
exhausted to the atmosphere through the turbine exhaust system.
The turbine exhaust flow path is formed by the inner surface of the exhaust nozzle and the
outer surface of the exhaust plug.
Secondary air is the part of the air absorbed by the fan that is directly discharged from the
outer portion of the fan, by-passes the core engine and flows through the fan exhaust to
the atmosphere.
2-12-0
Page 7
Dec 01/14
@A380
**ON A/C A380-800
A
4.93 m
(16.17 ft)
4.72 m
(15.49 ft)
2.77 m
(9.09 ft)
HP COMPRESSOR
LP COMPRESSOR
COMBUSTOR
SECTION
LP
TURBINE
TURBINE
EXHAUST
CASE
3.15 m
(10.33 ft)
TURBINE
CENTER FRAME
HP
TURBINE
1.93 m
(6.33 ft)
MAIN
GEARBOX
ANGLE
GEARBOX
A
ACCESSORY
DRIVE SECTION
L_AC_021200_1_0030101_01_00
Power Plant Handling
Engine Dimensions - GP 7200 Engine
FIGURE-2-12-0-991-003-A01
2-12-0
Page 8
Dec 01/14
@A380
**ON A/C A380-800
1.5 m
(4.92 ft)
NOSE
COWL
FAN COWL
THRUST REVERSER
PRIMARY NOZZLE
PLUG
A
1.17 m
(3.84 ft)
2.18 m
(7.15 ft)
2.52 m
(8.27 ft)
2.11 m
(6.92 ft)
3.8 m
(12.47 ft)
3.9 m
(12.8 ft)
1.31 m
(4.3 ft)
2.33 m
(7.64 ft)
INBOARD POSITION
A
OUTBOARD POSITION
L_AC_021200_1_0040101_01_00
Nacelle Dimensions - GP 7200 Engine
FIGURE-2-12-0-991-004-A01
2-12-0
Page 9
Dec 01/14
@A380
**ON A/C A380-800
A
A
A
A
A
1
1
B
45°
C
1: FAN COWL
OPEN
POSITION
45°
A
B
A
ALL ENGINES
6.8 m
(22.31 ft)
ENGINE 1−4
MIN.
2.64 m
(8.66 ft)
MAX.
3.14 m
(10.3 ft)
C
ENGINE 2−3
MIN.
1.86 m
(6.1 ft)
MAX.
2.16 m
(7.09 ft)
NOTE: B AND C DEPENDING ON AIRCRAFT CONFIGURATION.
SEE AC SECTION
2−3−0
L_AC_021200_1_0050101_01_00
Fan Cowls - GP 7200 Engine
FIGURE-2-12-0-991-005-A01
2-12-0
Page 10
Dec 01/14
@A380
**ON A/C A380-800
A
A
A
A
1
1
35°
B
B
C
1
1
C
45°
1 : THRUST REVERSER
A
OPEN
POSITION
A
35°
45°
B
5.8 m
(19.03 ft)
MIN.
1.52 m
(4.99 ft)
MAX.
1.82 m
(5.97 ft)
6.32 m
(20.73 ft)
1.86 m
(6.1 ft)
2.16 m
(7.09 ft)
C
SEE AC SECTION
2−3−0
L_AC_021200_1_0060101_01_00
Thrust Reverser Cowls - GP 7200 Engine
FIGURE-2-12-0-991-006-A01
2-12-0
Page 11
Dec 01/14
@A380
**ON A/C A380-800
A
A
A
A
35°
B
B
C
1
1
1
1
C
45°
1: FAN EXHAUST COWL
A
OPEN
POSITION
A
35°
45°
B
5.8 m
(19.03 ft)
MIN.
2.3 m
(7.55 ft)
MAX.
2.8 m
(9.19 ft)
6.32 m
(20.73 ft)
2.64 m
(8.66 ft)
3.14 m
(10.3 ft)
C
SEE AC SECTION
2−3−0
L_AC_021200_1_0070101_01_00
Fan Exhaust Cowls - GP 7200 Engine
FIGURE-2-12-0-991-007-A01
2-12-0
Page 12
Dec 01/14
@A380
**ON A/C A380-800
A
0.79 m
(2.59 ft)
5.14 m
(16.86 ft)
1.88 m
(6.17 ft)
1.5 m
(4.92 ft)
IP COMPRESSOR
LP COMPRESSOR
COMBUSTOR
SECTION
LP TURBINE
TURBINE EXHAUST
NOZZLE
3.11 m
(10.2 ft)
PLUG
1.84 m
(6.04 ft)
IP TURBINE
8.07 m
(26.48 ft)
HP TURBINE
1.66 m
(5.45 ft)
HP COMPRESSOR
ACCESSORY DRIVE SECTION
A
L_AC_021200_1_0080101_01_00
Engine Dimensions - TRENT 900 Engine
FIGURE-2-12-0-991-008-A01
2-12-0
Page 13
Dec 01/14
@A380
**ON A/C A380-800
NOSE COWL
THRUST REVERSER
FAN COWL
PRIMARY NOZZLE
PLUG
A
1.3 m
(4.27 ft)
1.63 m
(5.35 ft)
2.18 m
(7.15 ft)
2.39 m
(7.84 ft)
2.19 m
(7.19 ft)
FWD
3.88 m
(12.73 ft)
3.9 m
(12.8 ft)
1.18 m
(3.87 ft)
2.38 m
(7.81 ft)
INBOARD
INSTALLATION
A
OUTBOARD
INSTALLATION
L_AC_021200_1_0090101_01_00
Nacelle Dimensions - TRENT 900 Engine
FIGURE-2-12-0-991-009-A01
2-12-0
Page 14
Dec 01/14
@A380
**ON A/C A380-800
A
A
A
A
A
1
1
50°
OPEN POSITIONS:
INITIAL: 40°
FULL: 50°
40°
B
C
1: FAN COWL
OPEN
POSITION
40°
50°
A
A
ALL ENG.
6.95 m
(22.8 ft)
7.3 m
(23.95 ft)
B
INBOARD ENG.
2m
(6.56 ft)
2.4 m
(7.87 ft)
C
OUTBOARD ENG.
3m
(9.84 ft)
3.4 m
(11.15 ft)
INBOARD ENG.
1.3 m
(4.27 ft)
1.3 m
(4.27 ft)
OUTBOARD ENG.
2.27 m
(7.45 ft)
2.27 m
(7.45 ft)
L_AC_021200_1_0100101_01_00
Fan Cowls - TRENT 900 Engine
FIGURE-2-12-0-991-010-A01
2-12-0
Page 15
Dec 01/14
@A380
**ON A/C A380-800
A
A
A
A
1
1
35°
B
B
C
1
1
C
45°
1 : THRUST REVERSER
A
OPEN
POSITION
A
35°
45°
B
5.8 m
(19.03 ft)
MIN.
1.52 m
(4.99 ft)
MAX.
1.82 m
(5.97 ft)
6.32 m
(20.73 ft)
1.86 m
(6.1 ft)
2.16 m
(7.09 ft)
C
SEE AC SECTION
2−3−0
L_AC_021200_1_0110101_01_00
Thrust Reverser Cowls - TRENT 900 Engine
FIGURE-2-12-0-991-011-A01
2-12-0
Page 16
Dec 01/14
@A380
**ON A/C A380-800
A
A
A
A
1
1
35°
B
B
C
1: FAN EXHAUST COWL
1
1
C
45°
A
OPEN
POSITION
A
35°
45°
B
5.8 m
(19.03 ft)
MIN.
2.3 m
(7.55 ft)
MAX.
2.8 m
(9.19 ft)
6.32 m
(20.73 ft)
2.64 m
(8.66 ft)
3.14 m
(10.3 ft)
C
SEE AC SECTION
2−3−0
L_AC_021200_1_0120101_01_00
Fan Exhaust Cowls - TRENT 900 Engine
FIGURE-2-12-0-991-012-A01
2-12-0
Page 17
Dec 01/14
@A380
2-13-0
**ON A/C A380-800
1.
Quick Leveling
There are three alternative procedures to level the aircraft:
- Quick leveling procedure with Air Data/Inertial Reference System (ADIRS).
- Quick leveling procedure with a spirit level in the upper or main deck passenger compartment.
- Quick leveling procedure with a spirit level in the FWD cargo compartment.
2.
Precise Leveling
For precise leveling, it is necessary to install sighting rods in the receptacles located under the
fuselage (points 11 and 16 for longitudinal leveling) and under the wings (points 1L and 1R for lateral
leveling) and use a sighting tube. With the aircraft on jacks, adjust the jacks until the reference
marks on the sighting rods are aligned in the sighting plane (aircraft level).
3.
Symmetry and Alignment Check
Possible deformation of the aircraft is measured by photogrammetry.
2-13-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
FR36 FR35
1R
RIB6
11
RIB6
1L
FR88
FR89
16
L_AC_021300_1_0010101_01_00
Location of Leveling Points
FIGURE-2-13-0-991-001-A01
2-13-0
Page 2
Dec 01/14
@A380
2-14-0
Jacking
**ON A/C A380-800
1.
Aircraft Jacking Points for Maintenance
A.
General
(1) The A380-800 can be jacked:
- At not more than 333 700 kg (735 682 lb)
- Within the limits of the permissible wind speed when the aircraft is jacked outside a
closed environment.
B.
Primary Jacking Points
(1) The aircraft is provided with three primary jacking points:
- One located under the forward fuselage
- Two located under the wings (one under each wing).
(2) Three jack adapters (ground equipment) are used as intermediary parts between the
aircraft jacking points and the jacks:
- One male spherical jack adapter at the forward fuselage
- Two female spherical jack pad adapters at the wings (one at each wing).
C.
Auxiliary Jacking Point (Safety Stay)
(1) When the aircraft is on jacks, a safety stay is installed under the AFT fuselage (Ref. Fig.
Jacking Point Location) to prevent tail tipping caused by accidental displacement of the
aircraft center of gravity.
(2) The safety point must not be used for lifting the aircraft.
(3) One male spherical stay adapter (ground equipment) is used as an intermediary part
between the aircraft safety point and the stay.
2.
Jacks and Safety Stay
A.
Jack Design
(1) The maximum eligible loads given in the table (Ref. Fig. Jacking Point Location) are the
maximum loads applicable on jack fittings.
(2) In fully retracted position (jack stroke at minimum), the height of the jacks is such that
the jack may be placed beneath the aircraft under the most adverse conditions, namely,
tires deflated and shock absorbers depressurized, with sufficient clearance between the
aircraft jacking point and the jack upper end.
(3) The jacks stroke enables the aircraft to be jacked up so that the Fuselage Datum Line
(FDL) may be positioned up to 7 200 mm (283.46 in) from the ground to allow all
required maintenance procedures and in particular, the removal/installation of the landinggear shock absorbers.
2-14-0
Page 1
Dec 01/14
@A380
B.
Safety Stay
(1) The stay stroke enables the aircraft tail to be supported up to the Fuselage Datum Line
(FDL) positioned 7 200 mm (283.46 in) from the ground.
2-14-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
B’
X
WING JACKING
POINT
A
C
Y
FWD JACKING
POINT
SAFETY
STAY
B
WING JACKING
POINT
X
MAXIMUM
LOAD ELIGIBLE
Y
m
ft
m
ft
daN
FORWARD FUSELAGE
JACKING POINT
A
7.29
23.92
0
0
34 011
WING JACKING
POINT
B
35.23
115.58
12.22
40.09
157 480
B’
35.23
115.58
−12.22
−40.09
157 480
SAFETY STAY
C
59.34
194.68
0
0
7 874
NOTE: SAFETY STAY IS NOT USED FOR JACKING.
L_AC_021400_1_0010101_01_00
Jacking Points Location
FIGURE-2-14-0-991-001-A01
2-14-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
FUSELAGE DATUM LINE
N
L
M
L
M
N
AIRCRAFT ON WHEELS WITH STANDARD TIRES, MAX. JACK
WEIGHT 333 700 kg (735 682 lb)
AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED AND
TIRES FLAT
2 472 mm
(97.32 in)
5 112 mm
(201.26 in)
4 707 mm
(185.31 in)
2 259 mm
(88.94 in)
4 788 mm
(188.5 in)
4 462 mm
(175.67 in)
AIRCRAFT ON WHEELS, NOSE LANDING GEAR SHOCK
ABSORBERS DEFLATED AND TIRES FLAT
2 296 mm
(90.39 in)
5 117 mm
(201.46 in)
5 044 mm
(198.58 in)
AIRCRAFT ON WHEELS, LEFT WING AND BODY LANDING
GEARS SHOCK ABORBERS DEFLATED AND TIRES FLAT (SAME
DATA FOR RIGHT SIDE CONDITIONS)
AIRCRAFT ON WHEELS, WING AND BODY LANDING GEARS
SHOCK ABSORBERS DEFLATED AND TIRES FLAT
2 474 mm
(97.4 in)
4 523 mm
(178.07 in)
4 257 mm
(167.6 in)
2 391mm
(94.13 in)
4 803 mm
(189.09 in)
4 291 mm
(168.94 in)
3 673 mm
(144.61 in)
6 158 mm
(242.44 in)
5 830 mm
(229.53 in)
4 523 mm
(178.07 in)
7 008 mm
(275.91 in)
6 680 mm
(262.99 in)
4 523 mm
(178.07 in)
N/A
2 910 mm
(114.57 in)
AIRCRAFT ON JACKS, FUSELAGE DATUM LINE
PARALLEL TO GROUND AT 6 350 mm (250 in) FOR LANDING
GEARS EXTENSION/RETRACTION
AIRCRAFT ON JACKS, FUSELAGE DATUM LINE
PARALLEL TO GROUND AT 7 200 mm (283.46 in) FOR LANDING
GEARS REMOVAL/INSTALLATION
AIRCRAFT JACKED AT FORWARD JACKING POINT,
WING AND BODY LANDING GEARS WHEELS ON THE GROUND,
FOR NOSE LANDING GEAR EXTENSION/RETRACTION TEST
L_AC_021400_1_0020101_01_01
Jacking Dimensions
FIGURE-2-14-0-991-002-A01
2-14-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
FR20
A
Z−2676.63
B
A
ADAPTOR−JACK NOSE
B
L_AC_021400_1_0030101_01_00
Forward Jacking Point
FIGURE-2-14-0-991-003-A01
2-14-0
Page 5
Dec 01/14
@A380
**ON A/C A380-800
A
RIB16
LOWER SURFACE
RIB16
A
B
RIB16
A
EXAMPLE
Z−147
OUTER SKIN
JACKING PAD SET− WING
B
L_AC_021400_1_0100101_01_00
Wing Jacking Point
FIGURE-2-14-0-991-010-A01
2-14-0
Page 6
Dec 01/14
@A380
**ON A/C A380-800
FR101
A
FR101
Z−519.589
ADAPT−SUPP, AFT JACK
A
FWD
L_AC_021400_1_0110101_01_00
Auxiliary Jacking Point - Safety Stay
FIGURE-2-14-0-991-011-A01
2-14-0
Page 7
Dec 01/14
@A380
**ON A/C A380-800
Jacking for Wheel Change
1.
To replace a wheel or wheel brake assembly on any of the landing gears it is necessary to lift the
landing gear with a jack. The landing gear can be lifted by a pillar jack or with a cantilever jack.
NOTE : You can lift the aircraft at Maximum Ramp Weight (MRW).
A.
Nose Landing Gear (NLG)
The nose gear can be lifted with a pillar jack or a cantilever jack. The NLG has a dome shaped
jacking adaptor at the base of the shock absorber strut. The adapter is 31.75 mm (1.25 in) in
diameter.
Important dimensions of the NLG when lifted are shown in Fig. 001.
The reaction loads at the jacking position are shown in Fig. 004.
NOTE : The load at each jacking position is the load required to give a 25.5 mm (1 in)
clearance between the ground and the tire.
B.
Wing Landing Gear (WLG)
An adapter at the front and rear of each bogie is fitted to make sure that the jack is located
correctly. The adapter is 31.75 mm (1.25 in) in diameter. The wheels and brake units can be
replaced on the end of the bogie beam that is lifted.
The FWD and AFT ends of the bogie can be lifted at the same time. When lifting both ends at
the same time the bogie beam must always be kept level to prevent damage.
If a WLG has all four tires deflated or shredded, replace the wheel assemblies in this sequence:
- Replace the wheel assemblies on the AFT axle
- Replace the wheel assemblies on the FWD axle.
Important dimensions of the WLG when lifted are shown in Fig. 002.
C.
Body Landing Gear (BLG)
An adapter at the front and at the rear of each bogie is fitted to make sure that the jack is
located correctly. The adapter is 31.75 mm (1.25 in) in diameter. Both wheels and brake units
can be replaced on the end of the bogie beam that is lifted.
For a center wheel change only, the FWD and AFT ends of the bogie can be lifted at the same
time. When lifting both ends at the same time the bogie beam must always be kept level to
prevent damage.
If a BLG has all six tires deflated or shredded, replace the wheel assemblies in this sequence:
- Replace the wheel assemblies on the AFT axle
- Replace the wheel assemblies on the center axle
- Replace the wheel assemblies on the FWD axle.
2-14-0
Page 8
Dec 01/14
@A380
Important dimensions of the BLG when lifted are shown in Fig. 003.
2-14-0
Page 9
Dec 01/14
@A380
**ON A/C A380-800
VIEW LOOKING INBOARD LHS
(LH WHEEL NOT SHOWN)
B
A
DATA FOR 1 270 x 455 R22 TIRES
CONFIGURATION
WEIGHT CG%
DIM. A
DIM. B
2 INFLATED TIRES
MRW
43
400 (15.75)
541 (21.3)
1 INFLATED TIRE
MRW
43
353 (13.9)
530 (20.87)
2 DEFLATED TIRES +50%
RIM DAMAGE
MLW
−PAX
29
134 (5.28)
519 (20.43)
RIM DAMAGE
MLW
−PAX
44
136 (5.35)
519 (20.43)
2 DEFLATED TIRES
NO RIM DAMAGE
MLW
−PAX
29
164 (6.46)
519 (20.43)
2 DEFLATED TIRES
NO RIM DAMAGE
MLW
−PAX
44
166 (6.54)
519 (20.43)
RIM DAMAGE
N/A
N/A
137 (5.39)
519 (20.43)
20 DEFLATED TIRES
NO RIM DAMAGE
N/A
N/A
168 (6.61)
519 (20.43)
MAXIMUM JACKING
HEIGHT TO CHANGE
WHEELS
N/A
N/A
506 (19.92)
N/A
NOTE: DIMENSIONS IN MILLIMETERS (INCHES IN BRACKETS)
MRW = 562 000 kg (1 238 998 lb)
MLW = 386 000 kg (850 984 lb)
L_AC_021400_1_0040101_01_00
Nose Landing Gear Jacking Point Heights
FIGURE-2-14-0-991-004-A01
2-14-0
Page 10
Dec 01/14
@A380
**ON A/C A380-800
A
A
C
B
WEIGHT
CG%
DIM. A
FWD
DIM. A
AFT
DIM. B
DIM. C
ALL 4 TIRES
SERVICEABLE
MRW
43
347 (13.66)
347 (13.66)
750 (29.53)
364 (14.33)
1 FWD TIRE
DEFLATED
MRW
43
264 (10.39)
353 (13.9)
718 (28.27)
364 (14.33)
1 AFT TIRE
DEFLATED
MRW
43
353 (13.9)
264 (10.39)
718 (28.27)
364 (14.33)
2 DEFLATED FWD
TIRES +50% RIM
DAMAGE
MLW
−PAX
44
93 (3.66)
406 (15.98)
686 (27.01)
364 (14.33)
2 DEFLATED AFT
TIRES +50% RIM
DAMAGE
MLW
−PAX
44
406 (15.98)
93 (3.66)
686 (27.01)
364 (14.33)
4 TIRES DEFLATED
+50% RIM DAMAGE
MLW
−PAX
44
93 (3.66)
93 (3.66)
686 (27.01)
364 (14.33)
FWD TIRE CHANGE
MAX. GROWN TIRE
MRW
43
513 (20.2)
331 (13.03)
795 (31.3)
364 (14.33)
AFT TIRE CHANGE
MAX. GROWN TIRE
MRW
43
331 (13.03)
513 (20.2)
795 (31.3)
364 (14.33)
20 FLAT TIRES
+50% RIM DAMAGE
N/A
N/A
83 (3.27)
83 (3.27)
686 (27.01)
364 (14.33)
CONFIGURATION
MRW = 562 000 kg (1 238 998 lb)
MLW = 386 000 kg (850 984 lb)
L_AC_021400_1_0050101_01_00
Wing Landing Gear Jacking Point Heights
FIGURE-2-14-0-991-005-A01
2-14-0
Page 11
Dec 01/14
@A380
**ON A/C A380-800
A
A
C
B
CONFIGURATION
WEIGHT CG%
DIM. A
FWD
DIM. A
AFT
DIM. B
DIM. C
FWD
DIM. C
AFT
ALL 6 TIRES
SERVICEABLE
MRW
43
347 (13.66) 312 (12.28) 930 (36.61)
460 (18.11)
432 (17.01)
1 FWD TIRE
UNSERVICEABLE
MRW
43
295 (11.61) 328 (12.91) 898 (35.35)
460 (18.11)
432 (17.01)
1 CENTER TIRE
UNSERVICEABLE
MRW
43
334 (13.15) 299 (11.77) 898 (35.35)
460 (18.11)
432 (17.01)
1 AFT TIRE
UNSERVICEABLE
MRW
43
363 (14.29) 260 (10.24) 898 (35.35)
460 (18.11)
432 (17.01)
2 FWD TIRES
DEFLATED +50%
RIM DAMAGE
MLW
−PAX
44
505 (19.88) 866 (34.09)
460 (18.11)
432 (17.01)
2 CENTER TIRES
DEFLATED
MLW
−PAX
44
358 (14.09) 323 (12.72) 866 (34.09)
460 (18.11)
432 (17.01)
2 AFT TIRES
DEFLATED +50%
RIM DAMAGE
MLW
−PAX
44
540 (21.26)
40 (1.57)
866 (34.09)
460 (18.11)
432 (17.01)
6 TIRES DEFLATED
+50% RIM
DAMAGE
MLW
−PAX
44
74 (2.91)
39 (1.54)
866 (34.09)
460 (18.11)
432 (17.01)
FWD TIRE CHANGE
MAX. GROWN TIRE
MRW
43
496 (19.53) 264 (10.39) 975 (38.39)
460 (18.11)
432 (17.01)
CTR TIRE CHANGE
POSITION
MAX. GROWN TIRE
MRW
43
496 (19.53) 461 (18.15) 975 (38.39)
460 (18.11)
432 (17.01)
AFT TIRE CHANGE
MAX. GROWN TIRE
MRW
43
299 (11.77) 461 (18.15) 975 (38.39)
460 (18.11)
432 (17.01)
N/A
N/A
102 (4.02)
460 (18.11)
432 (17.01)
20 DEFLATED
TIRES +50% RIM
DAMAGE
74 (2.91)
67 (2.64)
866 (34.09)
MRW = 562 000 kg (1 238 998 lb)
MLW = 386 000 kg (850 984 lb)
L_AC_021400_1_0060101_01_00
Body Landing Gear Jacking Point Heights
FIGURE-2-14-0-991-006-A01
2-14-0
Page 12
Dec 01/14
@A380
**ON A/C A380-800
60
132
55
122
45
102
92
40
82
35
72
30
62
25
LOAD AT JACKING POINT (x 1 000 lb)
LOAD AT JACKING POINT (x 1 000 kg)
112
CG POSITION
29% MAC
33% MAC
37.5% MAC
41% MAC
43% MAC
50
52
20
42
15
32
10
260
600
300
700
340
380
800
420
460
(x 1 000 kg)
900
1 000
500
540
1 100
1 200
22
580
(x 1 000 lb)
AIRCRAFT GROSS WEIGHT
L_AC_021400_1_0070101_01_00
Nose Landing Gear Jacking Point Loads
FIGURE-2-14-0-991-007-A01
2-14-0
Page 13
Dec 01/14
@A380
**ON A/C A380-800
55
121
116
CG POSITION
29% MAC
33% MAC
37.5% MAC
41% MAC
43% MAC
51
111
106
47
96
43
91
39
86
81
35
76
101
71
31
66
61
27
56
23
260
300
340
380
420
460
500
540
51
580
(x 1 000 kg)
600
700
800
900
1 000
1 100
1 200
(x 1 000 lb)
L_AC_021400_1_0080101_01_00
Wing Landing Gear Jacking Point Loads
FIGURE-2-14-0-991-008-A01
2-14-0
Page 14
Dec 01/14
@A380
**ON A/C A380-800
82
175
CG POSITION
29% MAC
33% MAC
37.5% MAC
41% MAC
43% MAC
74
165
70
155
66
145
62
135
58
125
54
115
50
78
105
46
95
42
85
38
34
260
600
300
340
700
380
800
420
460
(x 1 000 kg)
900
1 000
500
1 100
540
75
580
1 200
(x 1 000 lb)
L_AC_021400_1_0090101_01_00
Body Landing Gear Jacking Point Loads
FIGURE-2-14-0-991-009-A01
2-14-0
Page 15
Dec 01/14
@A380
AIRCRAFT PERFORMANCE
3-1-0
General Information
**ON A/C A380-800
General Information
1.
Standard day temperatures for the altitudes shown are tabulated below :
FEET
0
2000
4000
6000
8000
Standard day temperatures for the altitudes
Altitude
Standard Day Temperature
˚F
METERS
˚C
0
59.0
15.0
610
51.9
11.6
44.7
1220
7.1
1830
37.6
3.1
2440
30.5
-0.8
3-1-0
Page 1
Dec 01/14
@A380
3-2-1
ISA Conditions
**ON A/C A380-800
1.
This section provides the payload/range at ISA conditions.
3-2-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
NOTE:
THESE CURVES ARE GIVEN FOR INFORMATION ONLY.
THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"
SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
RANGE (km)
7400
8400
9400
10400 11400
90
MAXIMUM STRUCTURAL PAYLOAD
12400
13400
14400
15400
16400
17400
180
70
160
PAYLOAD (x 1000 lb)
80
140
60
PAYLOAD (t)
18400
200
MAXIMUM PASSENGER PAYLOAD
120
50
100
40
80
30
20
10
60
40
TYPICAL INTERNATIONAL FLIGHT PROFILE
ISA / NO WIND
5% TRIP FUEL ALLOWANCE, 30 min HOLDING
200 nm DIVERSION
0
4000
4500
5000
5500
6000
6500
20
7000
7500
RANGE (nm)
8000
8500
9000
9500
0
10000
L_AC_030201_1_0010101_01_00
Payload/Range
ISA Conditions - TRENT 900 Engines
FIGURE-3-2-1-991-001-A01
3-2-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
NOTE:
RANGE (km)
7400
8400
9400
10400 11400
90
MAXIMUM STRUCTURAL PAYLOAD
12400
13400
14400
15400
16400
17400
180
70
160
PAYLOAD (x 1000 lb)
80
140
60
PAYLOAD (t)
18400
200
MAXIMUM PASSENGER PAYLOAD
120
50
100
40
80
30
20
10
60
40
TYPICAL INTERNATIONAL FLIGHT PROFILE
ISA / NO WIND
5% TRIP FUEL ALLOWANCE, 30 min HOLDING
200 nm DIVERSION
0
4000
4500
5000
5500
6000
6500
20
7000
7500
RANGE (nm)
8000
8500
9000
9500
0
10000
L_AC_030201_1_0080101_01_00
Payload/Range
ISA Conditions - GP 7200 Engines
FIGURE-3-2-1-991-008-A01
3-2-1
Page 3
Dec 01/14
@A380
3-3-1
Take Off Weight Limitation - ISA Conditions
**ON A/C A380-800
Take-Off Weight Limitation - ISA Conditions
1.
This section provides the take-off weight limitation at ISA conditions.
3-3-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
NOTE:
RUNWAY LENGTH (ft)
6000
7000
8000
9000 10000 11000 12000 13000 14000 15000 16000 17000 18000
0
AIRFIELD PRESSURE ALTITUDE (ft)
2000
TAKE−OFF WEIGHT (t)
600
4000
6000
550
8000
500
1360
1260
1160
1060
450
960
400
860
350
760
300
1500
2000
2500
3000
3500
4000
4500
5000
TAKE−OFF WEIGHT (x 1000 lb)
5000
650
660
5500
RUNWAY LENGTH (m)
L_AC_030301_1_0010101_01_00
Take-Off Weight Limitation
ISA Conditions - TRENT 900 Engines
FIGURE-3-3-1-991-001-A01
3-3-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
NOTE:
RUNWAY LENGTH (ft)
6000
7000
8000
9000 10000 11000 12000 13000 14000 15000 16000 17000 18000
0
2000
600
4000
6000
550
8000
500
1360
1260
1160
1060
450
960
400
860
350
760
300
1500
2000
2500
3000
3500
4000
4500
5000
5000
650
660
5500
RUNWAY LENGTH (m)
L_AC_030301_1_0080101_01_00
ISA Conditions - GP 7200 Engines
FIGURE-3-3-1-991-008-A01
3-3-1
Page 3
Dec 01/14
@A380
3-3-2
Take Off Weight Limitation - ISA + 15 ˚C (59 ˚F)
**ON A/C A380-800
Take-Off Weight Limitation - ISA + 15 ˚C (+59 ˚F) Conditions
1.
This section provides the take-off weight limitation at ISA + 15˚C (+59˚F) conditions.
3-3-2
Page 1
Dec 01/14
@A380
**ON A/C A380-800
NOTE:
RUNWAY LENGTH (ft)
6000
7000
8000
9000 10000 11000 12000 13000 14000 15000 16000 17000 18000
0
2000
600
4000
6000
550
8000
500
1360
1260
1160
1060
450
960
400
860
350
760
300
1500
2000
2500
3000
3500
4000
4500
5000
5000
650
660
5500
RUNWAY LENGTH (m)
L_AC_030302_1_0010101_01_00
ISA + 15 ˚C (+59 ˚F) Conditions - TRENT 900 Engines
FIGURE-3-3-2-991-001-A01
3-3-2
Page 2
Dec 01/14
@A380
**ON A/C A380-800
NOTE:
RUNWAY LENGTH (ft)
6000
7000
8000
9000 10000 11000 12000 13000 14000 15000 16000 17000 18000
0
2000
600
4000
6000
550
8000
500
1360
1260
1160
1060
450
960
400
860
350
760
300
1500
2000
2500
3000
3500
4000
4500
5000
5000
650
660
5500
RUNWAY LENGTH (m)
L_AC_030302_1_0080101_01_00
ISA + 15 ˚C (+59 ˚F) Conditions - GP 7200 Engines
FIGURE-3-3-2-991-008-A01
3-3-2
Page 3
Dec 01/14
@A380
3-4-1
**ON A/C A380-800
1.
This section provides the landing field length on a dry runway.
3-4-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
NOTE:
GROSS WEIGHT (x 1000 lb)
670
720
770
820
870
LANDING FIELD LENGTH (m)
2600
2500
2300
970
AIRFIELD ELEVATION (ft) 9000
8000
8600
6000
8200
4000
7800
2700
2400
920
VALID FOR ALL TEMPERATURES
2000 7400
2200
0
2100
7000
2000
6600
1900
6200
1800
5800
1700
5400
1600
5000
1500
1400
280
LANDING FIELD LENGTH (ft)
620
2800
300
320
340
360
380
GROSS WEIGHT (t)
400
420
440
4600
460
L_AC_030401_1_0010101_01_01
Dry Runway
FIGURE-3-4-1-991-001-A01
3-4-1
Page 2
Dec 01/14
@A380
3-5-0
**ON A/C A380-800
1.
This section gives the final approach speed which is the indicated airspeed at threshold in the landing
configuration at the certificated maximum flap setting and maximum landing weight at standard
atmospheric conditions. The approach speed is used to classify the aircraft into Aircraft Approach
Category, a grouping of aircraft based on the indicated airspeed at threshold.
2.
The final approach speed is 138 kt at a Maximum Landing Weight (MLW) of 395 000 kg (870 826
lb) and classifies the aircraft into the Aircraft Approach Category C.
NOTE : This value is given for information only.
3-5-0
Page 1
Dec 01/14
@A380
GROUND MANEUVERING
4-1-0
General Information
**ON A/C A380-800
General
1.
This section provides aircraft turning capability and maneuvering characteristics.
For ease of presentation, this data has been determined from the theoretical limits imposed by the
geometry of the aircraft, and where noted, provides for a normal allowance for tire slippage. As such,
it reflects the turning capability of the aircraft in favorable operating circumstances. This data should
only be used as a guidelines for the method of determination of such parameters and for the
maneuvering characteristics of this aircraft type.
In ground operating mode, varying airline practices may demand that more conservative turning
procedures be adopted to avoid excessive tire wear and reduce possible maintenance problems. Airline
operating techniques will vary in the level of performance, over a wide range of operating
circumstances throughout the world. Variations from standard aircraft operating patterns may be
necessary to satisfy physical constraints within the maneuvering area, such as adverse grades, limited
area or a high risk of jet blast damage. For these reasons, ground maneuvering requirements should
be coordinated with the airlines in question prior to layout planning.
4-1-0
Page 1
Dec 01/14
@A380
4-2-0
Turning Radii
**ON A/C A380-800
Turning Radii
1.
This section provides the turning radii.
4-2-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
55°
60°
29.83 m
(97.9 ft)
65°
70°
R3
R5
R6
R4
NOTE:
FOR TURNING RADII VALUES, REFER TO SHEET 2.
L_AC_040200_1_0010101_01_01
Turning Radii
(Sheet 1)
FIGURE-4-2-0-991-001-A01
4-2-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
A380−800 TURNING RADII
TYPE
OF
TURN
STEERING
ANGLE
EFFECTIVE
STEERING
ANGLE
2
20°
17.9°
2
25°
22.7°
2
30°
27.5°
2
35°
32.1°
2
40°
36.6°
2
45°
41.0°
2
50°
45.1°
1
55°
51.2°
1
60°
57.3°
1
65°
63.4°
1
70°
69.5°
m
ft
m
ft
m
ft
m
ft
m
ft
m
ft
m
ft
m
ft
m
ft
m
ft
m
ft
R3
NLG
R4
WING
R5
NOSE
R6
THS
100.16
328.6
78.86
258.7
65.69
215.5
56.84
186.5
50.59
166.0
46.02
151.0
42.61
139.8
40.13
131.6
37.64
123.5
35.15
115.3
32.66
107.2
135.45
444.4
113.14
371.2
98.90
324.5
88.97
291.9
81.61
267.8
75.94
249.1
71.43
234.4
67.02
219.9
62.60
205.4
58.18
190.9
53.76
176.4
101.01
331.4
80.12
262.9
67.33
220.9
58.83
193.0
52.89
173.5
48.61
159.5
45.45
149.1
43.22
141.8
40.98
134.5
38.75
127.1
36.52
119.8
115.87
380.1
94.90
311.4
81.91
268.7
73.13
239.9
66.84
219.3
62.16
203.9
58.57
192.2
55.43
181.9
52.29
171.5
49.15
161.2
46.01
150.9
NOTE:
TYPE 1 TURNS USE :
ASYMMETRIC THRUST − BOTH ENGINES ON THE INSIDE OF THE TURN TO BE AT IDLE THRUST.
DIFFERENTIAL BRAKING − BRAKING APPLIED TO THE WING GEAR WHEELS ON THE INSIDE OF
THE TURN.
TYPE 2 TURNS USE :
SYMMETRIC THRUST AND NO BRAKING.
L_AC_040200_1_0020101_01_01
Turning Radii
(Sheet 2)
FIGURE-4-2-0-991-002-A01
4-2-0
Page 3
Dec 01/14
@A380
4-3-0
**ON A/C A380-800
1.
This section provides the minimum turning radii.
4-3-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
29.83 m
(97.9 ft)
55°
60°
65°
R3
A
(MINIMUM
TURNING WIDTH)
70°
Y
R5
OUTSIDE FACE
OF TIRE
R6
R4
A380−800 MINIMUM TURNING RADIUS
TYPE
OF
TURN
STEERING
ANGLE
EFFECTIVE
STEERING
ANGLE
1
70°
69.5°
Y
A
R3
NLG
R4
WING
R5
NOSE
R6
THS
m
11.08
50.91
32.66
53.76
36.52
46.01
ft
36.3
167.0
107.2
176.4
119.8
150.9
NOTE:
TURN PERFORMED WITH ASYMMETRIC THRUST AND DIFFERENTIAL BRAKING.
L_AC_040300_1_0010101_01_02
FIGURE-4-3-0-991-001-A01
4-3-0
Page 2
Dec 01/14
@A380
4-4-0
**ON A/C A380-800
1.
This section gives the visibility from cockpit in static position.
4-4-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
NOT TO BE USED FOR
LANDING APPROACH VISIBILITY
DIMENSIONS ARE APPROXIMATE
31°
VISUAL ANGLES IN VERTICAL
PLANE THROUGH PILOT
EYE POSITION.
19.5°
2.92 m
(9.58 ft)
17.36 m
(56.96 ft)
7.17 m
(23.52 ft)
107°
121°
FIRST OFFICER
FIELD OF VIEW
4.97 m
(16.31 ft)
MAX AFT VISION WITH HEAD TURNED
AROUND SPINAL COLUMN.
WING TIP CAN BE SEEN WHEN HEAD IS MOVED
TO THE SIDE.
VISUAL ANGLES IN HORIZONTAL
PLANE THROUGH PILOT
EYE POSITION.
CAPTAIN FIELD OF VIEW
107°
121°
VISUAL ANGLES IN PLANE
PERPENDICULAR TO
LONGITUDINAL AXIS.
30°
30°
24°
24°
NOTE:
PILOT EYE POSITION WHEN PILOT’S EYES ARE IN LINE WITH THE RED AND WHITE BALLS.
ZONE THAT CANNOT BE SEEN
L_AC_040400_1_0010101_01_01
FIGURE-4-4-0-991-001-A01
4-4-0
Page 2
Dec 01/14
CAPTAIN
WINDSHIELD
FIRST OFFICER
SLIDING WINDOW
20°
24°
30°
10°
0°
10°
20°
30°
40°
50°
4-4-0
PILOT EYE POSITION
(CAPTAIN POSITION)
FIRST OFFICER
WINDSHIELD
FIRST OFFICER
FIXED WINDOW
EXAMPLE: WHEN CAPTAIN TURNS HIS HEAD BY 90° LEFT, VISIBILITY
WILL BE 30° UP AND 24° DOWN THROUGH THE SLIDING WINDOW FRAME.
CAPTAIN FIELD OF VIEW SHOWN.
FIRST OFFICER FIELD OF VIEW SYMMETRICAL.
A380
ARP 4101−2
CAPTAIN
FIXED WINDOW
130°120°110°100° 90° 80° 70° 60° 50° 40° 30° 20° 10° 0° 10° 20° 30° 40° 50° 60° 70° 80° 90°100°110°120°130°140°150°
CAPTAIN SLIDING
WINDOW
@A380
**ON A/C A380-800
L_AC_040400_1_0020101_01_00
Binocular Visibility Through Windows from Captain Eye Position
FIGURE-4-4-0-991-002-A01
Page 3
Dec 01/14
@A380
4-5-0
**ON A/C A380-800
1.
4-5-0
Page 1
Dec 01/14
@A380
4-5-1
**ON A/C A380-800
1.
This section gives the 135˚ turn -- runway to taxiway.
4-5-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
TURN R = 45 m
(150 ft)
FA
NOMINAL
OFFSET 7 m
(23 ft)
L
APPROX 4.9 m
(16 ft)
A
=
LE
A
75 D−
m IN
(2 FIL
50 L
ft) ET
APPROX 6.6 m
(22 ft)
FILLET R = 25.5 m
(85 ft)
RUNWAY
CENTERLINE
TAXIWAY CENTERLINE
23 m
(75 ft)
45 m
(150 ft)
NLG PATH
WLG PATH
COCKPIT PATH
NOTE: FAA GROUP V FACILITIES.
L_AC_040501_1_0010101_01_01
135˚ Turn -- Runway to Taxiway
Judgemental Oversteer Method
FIGURE-4-5-1-991-001-A01
4-5-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
TURN R = 51 m
(167 ft)
FA
L
A
=
LE
A
75 D−
m IN
(2 FIL
50 L
ft) ET
APPROX 5.8 m
(19 ft)
FILLET R = 25.5 m
(85 ft)
TAXIWAY CENTERLINE
30 m
(100 ft)
RUNWAY CENTERLINE
60 m
(200 ft)
NLG PATH
WLG PATH
NOTE: FAA GROUP VI FACILITIES.
L_AC_040501_1_0020101_01_01
Cockpit Tracks Centreline Method
FIGURE-4-5-1-991-002-A01
4-5-1
Page 3
Dec 01/14
@A380
4-5-2
**ON A/C A380-800
1.
This section gives the 90˚ turn -- runway to taxiway.
4-5-2
Page 1
Dec 01/14
@A380
**ON A/C A380-800
APPROX 7 m
(23 ft)
APPROX 10 m
(33 ft)
FAA LEAD−I
N FILLET
L = 75 m (2
50 ft)
APPROX 9.2 m
(30 ft)
TAXIWAY
CENTERLINE
23 m
(75 ft)
FILLET R = 25.5 m
(85 ft)
TURN R = 45 m
(150 ft)
RUNWAY CENTERLINE
45 m
(150 ft)
NLG PATH
WLG PATH
COCKPIT PATH
L_AC_040502_1_0010101_01_01
FIGURE-4-5-2-991-001-A01
4-5-2
Page 2
Dec 01/14
@A380
**ON A/C A380-800
TURN R = 51 m
(167 ft)
FAA LEAD−I
30 m
(100 ft)
N FILLET
L = 75 m (250
ft)
TAXIWAY
CENTERLINE
APPROX 10.2 m
(33 ft)
FILLET R = 25.5 m
(85 ft)
RUNWAY CENTERLINE
60 m
(200 ft)
NLG PATH
WLG PATH
L_AC_040502_1_0020101_01_01
FIGURE-4-5-2-991-002-A01
4-5-2
Page 3
Dec 01/14
@A380
4-5-3
**ON A/C A380-800
1.
This section gives the 180˚ turn on a runway.
4-5-3
Page 1
Dec 01/14
@A380
**ON A/C A380-800
60 m
(200 ft)
R4 = 54 m
(177 ft)
RUNWAY
CENTERLINE
R5 = 36.6 m
(120 ft)
R3 = 32.7 m
(107 ft)
R6 = 46 m
(151 ft)
0.7 m
(2 ft)
23.2 m
(76 ft)
16.8 m
(55 ft)
31.2 m
(102 ft)
4.5 m
(15 ft)
4.5 m
(15 ft)
NLG PATH
WLG PATH
NOSE TIP PATH
51 m
(167 ft)
WING TIP PATH
TAIL TIP PATH
NOTE: 70° NOSE GEAR STEERING − ASYMMETRIC THRUST AND BRAKING
ON A 60 m (200 ft) WIDE RUNWAY.
NLG WHEEL
OUTER−FACE PATH
L_AC_040503_1_0010101_01_01
FIGURE-4-5-3-991-001-A01
4-5-3
Page 2
Dec 01/14
@A380
4-5-4
**ON A/C A380-800
1.
This section gives the 90˚ turn - taxiway to taxiway.
4-5-4
Page 1
Dec 01/14
@A380
**ON A/C A380-800
NOMINAL OFFSET 7 m
(23 ft)
FAA LEAD
−IN FILLET
L = 75 m (2
50 ft)
APPROX 10 m
(33 ft)
23 m
(75 ft)
APPROX 8.9 m
(29 ft)
TAXIWAY
CENTERLINE
FILLET R = 25.5 m
(85 ft)
TURN R = 45 m
(150 ft)
TAXIWAY CENTERLINE
23 m
(75 ft)
NLG PATH
WLG PATH
COCKPIT PATH
L_AC_040504_1_0010101_01_01
90˚ Turn -- Taxiway to Taxiway
FIGURE-4-5-4-991-001-A01
4-5-4
Page 2
Dec 01/14
@A380
**ON A/C A380-800
TURN R = 51 m
(167 ft)
FAA LEA
30 m
(100 ft)
D−IN FIL
LET
L = 75 m
(250 ft)
TAXIWAY
CENTERLINE
APPROX 8.7 m
(29 ft)
FILLET R = 25.5 m
(85 ft)
TAXIWAY CENTERLINE
30 m
(100 ft)
NLG PATH
WLG PATH
L_AC_040504_1_0020101_01_01
FIGURE-4-5-4-991-002-A01
4-5-4
Page 3
Dec 01/14
@A380
4-5-5
**ON A/C A380-800
1.
This section gives the 135˚ turn - taxiway to taxiway.
4-5-5
Page 1
Dec 01/14
@A380
**ON A/C A380-800
TURN R = 45 m
(150 ft)
APPROX 7 m
(23 ft)
FA
A
LE
A
75 D−
APPROX 4.9 m m IN
(2 FIL
(16 ft)
50 L
ft) ET
L
=
APPROX 8.5 m
(28 ft)
FILLET R = 25.5 m
(85 ft)
TAXIWAY CENTERLINE
TAXIWAY CENTERLINE
23 m
(75 ft)
23 m
(75 ft)
NLG PATH
WLG PATH
COCKPIT PATH
L_AC_040505_1_0010101_01_01
FIGURE-4-5-5-991-001-A01
4-5-5
Page 2
Dec 01/14
@A380
**ON A/C A380-800
TURN R = 51 m
(167 ft)
FA
L
A
L
= EA
75 D−
m IN
(2 FI
50 LL
ft) ET
APPROX 7.4 m
(24 ft)
FILLET R = 25.5 m
(85 ft)
TAXIWAY CENTERLINE
TAXIWAY CENTERLINE
30 m
(100 ft)
30 m
(100 ft)
NLG PATH
WLG PATH
L_AC_040505_1_0020101_01_01
Cockpit Tracks Centerline Method
FIGURE-4-5-5-991-002-A01
4-5-5
Page 3
Dec 01/14
@A380
4-6-0
**ON A/C A380-800
1.
This section gives the runway holding bay (Apron).
4-6-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
6.1 m
(20 ft)
90 m
(300 ft)
110 m
(360 ft)
12.2 m
(40 ft)
HOLDING POINT
6.1 m
(20 ft)
190 m
(625 ft)
TAXIWAY
CENTERLINE
RUNWAY CENTERLINE
60 m
(200 ft)
30 m
(100 ft)
NOTE: COORDINATE WITH USING AIRLINE FOR SPECIFIC PLANNED OPERATING PROCEDURE.
L_AC_040600_1_0010101_01_01
FIGURE-4-6-0-991-001-A01
4-6-0
Page 2
Dec 01/14
@A380
4-7-0
**ON A/C A380-800
1.
The ground manoeuvres were performed using asymmetric thrust and differential only braking to
initiate the turn.
TODA: Take-Off Available Distance
ASDA: Acceleration-Stop Distance Available
2.
90˚ Turn on Runway Entry
This section gives the minimum line-up distance correction for a 90˚ turn on runway entry.
This manoeuvre consists in a 90˚ turn at minimum turn radius starting with the edge of the WLG at
a distance of 4.5 m (15 ft) from taxiway edge, and finishing with the aircraft aligned on the
centerline of the runway, see FIGURE 4-7-0-991-003-A.
During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft) for this category of
aircraft as recommended in ICAO Annex 14.
3.
180˚ Turn on Runway Turn Pad
This section gives the minimum line-up distance correction for a 180˚ turn on runway turn pad.
This manoeuvre consists in a 180˚ turn at minimum turn radius on a standard ICAO runway turn
pad geometry, .
It starts with the edge of the WLG at 4.5 m (15 ft) from pavement edge, and it finishes with the
aircraft aligned on the centerline of the runway, see FIGURE 4-7-0-991-004-A.
4.
180˚ Turn on Runway Width
This section gives the minimum line-up distance correction for a 180˚ turn on runway width.
For this manoeuvre, the pavement width is considered to be the runway width, which is a frozen
parameter (45 m (150 ft) and 60 m (200 ft)).
As per the ”180˚ turn on runway” standard operating procedures described in the Flight Crew
Operating Manual, the aircraft is initially angled with respect to runway centerline when starting the
180˚ turn, see FIGURE 4-7-0-991-005-A.
4-7-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
4.5 m
(15 ft)
TODA
TAXIWAY
CENTERLINE
ASDA
> 4.5 m
(15 ft)
RUNWAY CENTERLINE
90° TURN ON RUNWAY ENTRY
AIRCRAFT
TYPE
MAX
STEERING
ANGLE
A380−800
70°
45 m (150 ft) WIDE RUNWAY
(STANDARD WIDTH)
MINIMUM LINE−UP
DISTANCE CORRECTION
ON TODA
ON ASDA
28.6 m
94 ft
58.5 m
192 ft
MINIMUM LINE−UP
DISTANCE CORRECTION
ON TODA
ON ASDA
22.8 m
75 ft
52.7 m
173 ft
NOTE:
ASDA: ACCELERATION−STOP DISTANCE AVAILABLE
TODA: TAKE−OFF DISTANCE AVAILABLE
L_AC_040700_1_0030101_01_00
90˚ Turn on Runway Entry
FIGURE-4-7-0-991-003-A01
4-7-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
MINIMUM PAVEMENT WIDTH
4.5 m
(15 ft)
TODA
4.5 m
(15 ft)
> 4.5 m
(15 ft)
ASDA
RUNWAY CENTERLINE
180° TURN ON RUNWAY TURNPAD
(STANDARD WIDTH)
MAX
REQUIRED
REQUIRED
MINIMUM LINE−UP
MINIMUM LINE−UP
AIRCRAFT STEERING
MINIMUM
MINIMUM
DISTANCE
DISTANCE
TYPE
PAVEMENT
PAVEMENT
ANGLE
CORRECTION
CORRECTION
WIDTH
WIDTH
ON TODA
ON ASDA
ON TODA
ON ASDA
68.1 m 224 ft
64 m 209.9 ft
A380−800
70°
39.5 m 130 ft 69.3 m 227 ft
37.1 m 122 ft 66.9 m 219 ft
NOTE:
L_AC_040700_1_0040101_01_00
180˚ Turn on Runway Turn Pad
FIGURE-4-7-0-991-004-A01
4-7-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
4.5 m
(15 ft)
4.5 m
(15 ft)
TODA
ASDA
>4.5 m
(15 ft)
15°
RUNWAY CENTERLINE
180° TURN ON RUNWAY WIDTH
AIRCRAFT
TYPE
MAX
STEERING
ANGLE
A380−800
70°
(STANDARD WIDTH)
MINIMUM LINE−UP
DISTANCE CORRECTION
ON TODA
ON ASDA
NOT POSSIBLE
MINIMUM LINE−UP
DISTANCE CORRECTION
ON TODA
ON ASDA
NOT POSSIBLE
NOTE:
IN THE A380 FCOM, THERE IS AN OPERATIONAL PROCEDURE THAT DESCRIBES HOW TO PERFORM A 180°
TURN ON A 60 m (200 ft) RUNWAY WIDTH, BUT THE RECOMMENDED 4.5 m (15 ft) MARGINS CANNOT BE MET.
L_AC_040700_1_0050101_01_00
180˚ Turn on Runway Width
FIGURE-4-7-0-991-005-A01
4-7-0
Page 4
Dec 01/14
@A380
4-8-0
Aircraft Mooring
**ON A/C A380-800
Aircraft Mooring
1.
This section provides information on aircraft mooring.
4-8-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
A
SLING
TOWING FITTING
LOCKING SCREW
MOVABLE PIN
HOOK
MOORING POINT
HOOK PIN
FWD
A
L_AC_040800_1_0010101_01_00
Aircraft Mooring
FIGURE-4-8-0-991-001-A01
4-8-0
Page 2
Dec 01/14
@A380
5-1-0
**ON A/C A380-800
1.
This section provides typical ramp layouts, showing the various GSE items in position during typical
turn-round scenarios.
These ramp layouts show typical arrangements only. Each operator will have its own specific
requirements/regulations for positioning and operation on the ramp.
This table gives the symbols used on servicing diagrams.
AC
AS
BULK
CAT
CB
CLEAN
FUEL
GPU
LDCL
LV
PBB
PS
TOW
UDCAT
ULD
WV
GROUND SUPPORT EQUIPMENT
AIR CONDITIONING UNIT
AIR START UNIT
BULK TRAIN
CATERING TRUCK
CONVEYOR BELT
CLEANING TRUCK
FUEL HYDRANT DISPENSER or TANKER
GROUND POWER UNIT
LOWER DECK CARGO LOADER
LAVATORY VEHICLE
PASSENGER BOARDING BRIDGE
PASSENGER STAIRS
TOW TRACTOR
UPPER DECK CATERING TRUCK
ULD TRAIN
POTABLE WATER VEHICLE
5-1-0
Page 1
Dec 01/14
@A380
5-1-1
**ON A/C A380-800
1.
This section gives the typical ramp layout (Open Apron).
The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) from
the aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheel
chocks in position on landing gears).
5-1-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
TOW
48
AS
5
10 15
METERS
GPU
GPU
PS
CLEAN
LD CL
ULD
PS
CAT
UDCAT
AC
EL
0
FEET
16 32
FU
0
CAT
WV
PS
LD CL
ULD
CAT
CB
LV
BULK
STAND SAFETY LINE
L_AC_050101_1_0010101_01_02
Typical Ramp Layout
Open Apron
FIGURE-5-1-1-991-001-A01
5-1-1
Page 2
Dec 01/14
@A380
5-1-2
**ON A/C A380-800
1.
This section gives the baseline ramp layout (Gate).
The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) from
the aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheel
chocks in position on landing gears).
5-1-2
Page 1
Dec 01/14
@A380
**ON A/C A380-800
0
0
FEET
16 32
TOW
48
AS
5
10 15
METERS
GPU
GPU
CLEAN
PB
B
LD CL
PB
ULD
B
CAT
UDCAT
AC
FUEL
FUEL
CAT
WV
CAT
LD CL
ULD
LV
CB
BULK
STAND SAFETY LINE
L_AC_050102_1_0010101_01_02
Typical Ramp Layout
Gate
FIGURE-5-1-2-991-001-A01
5-1-2
Page 2
Dec 01/14
@A380
5-2-1
**ON A/C A380-800
1.
This section provides a typical turn-round time chart showing the typical time for ramp activities
during aircraft turn-round.
Actual times may vary due to each operator’s specific practices, resources, equipment and operating
conditions.
2.
Assumptions used for standard servicing via main and upper deck during typical turn-round time
A.
PASSENGER HANDLING
555 pax (22 F/C + 96 B/C + 437 Y/C).
All passengers deplane and board the aircraft.
2 Passenger Boarding Bridges (PBB) used at doors M2L and U1L.
Equipment positioning main deck + opening door = +3 min.
Closing door + equipment removal main deck = +3 min.
Equipment positioning upper deck + opening door = +4 min.
Closing door + equipment removal upper deck = +4 min.
No Passenger with Reduced Mobility (PRM) on board.
Deplaning:
- 356 pax at door M2L (22 F/C + 334 Y/C)
- 199 pax at door U1L (96 B/C + 103 Y/C)
- Deplaning rate = 25 pax/min per door
- Priority deplaning for premium passengers.
Boarding:
- 356 pax at door M2L (22 F/C + 334 Y/C)
- 199 pax at door U1L (96 B/C + 103 Y/C)
- Boarding rate = 15 pax/min per door
- Last Pax Seating allowance (LPS) + headcounting = +4 min.
B.
CARGO
2 cargo loaders + 1 belt loader.
Opening door + equipment positioning = +2.5 min.
Equipment removal + closing door = +2.5 min.
100% cargo exchange:
- FWD cargo compartment: 20 containers
- AFT cargo compartment: 16 containers
- Bulk cargo compartment: 1 000 kg (2 205 lb).
Container unloading/loading times:
5-2-1
Page 1
Dec 01/14
@A380
-
Unloading = 1.2 min/container
Loading = 1.4 min/container.
Bulk unloading/loading times:
- Unloading = 110 kg/min (243 lb/min)
- Loading = 95 kg/min (209 lb/min).
C.
REFUELING
242 700 l (64 115 US gal) at 40 psig.
Dispenser positioning + connection = +8 min.
Disconnection + dispenser removal = +8 min.
D.
CLEANING
Cleaning is performed in available time.
E.
CATERING
3 main deck catering trucks + 1 upper deck catering truck.
Main deck equipment positioning + door opening = +5 min.
Main deck closing door + equipment removal = 3 min.
Upper deck equipment positioning + door opening = +9 min.
Upper deck closing door + equipment removal = 4 min.
Full Size Trolley Equivalent (FSTE) to unload and load: 78 FSTE
- 28 FSTE at door M2R
- 23 FSTE at door U1R
- 11 FSTE at door M5L.
Time for trolley exchange = 1.5 min per FSTE.
Time for trolley exchange via lift = 2 min per FSTE.
F.
GROUND HANDLING/SERVICING
Start of operations:
- Bridges/stairs: t0 = 0
- Other equipment: t = t0 + 1 min.
Ground Power Unit (GPU): up to 4 x 90 kVA.
Air conditioning: up to 4 hoses.
Potable water servicing: 100% uplift, 1 700 l (449 US gal).
Waste water servicing: draining + rinsing.
5-2-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
TRT: 90 min
DEPLANING/BOARDING
AT M2L
DEPLANING/BOARDING
AT U1L
HEADCOUNTING & LPS
0
10
20
30
40
50
60
70
80
90
CATERING AT M2R
CATERING AT M4R
CATERING AT U1R
CATERING AT M5L
CLEANING AT M1R
AVAILABLE TIME
CARGO FWD CC
CARGO AFT CC
BULK
REFUELING
POTABLE WATER SERVICING
WASTE WATER SERVICING
GSE POSITIONING/REMOVAL
ACTIVITY
CRITICAL PATH
L_AC_050201_1_0020101_01_03
Typical Turn-Round Time
Servicing Via Main and Upper Deck
FIGURE-5-2-1-991-002-A01
5-2-1
Page 3
Dec 01/14
@A380
5-2-2
**ON A/C A380-800
1.
This section provides a typical turn-round time chart showing the typical time for ramp activities
during aircraft turn-round.
Actual times may vary due to each operator’s specific practices, resources, equipment and operating
conditions.
2.
Assumptions used for standard servicing via main deck only during typical turn-round time
A.
PASSENGER HANDLING
555 pax (22 F/C + 96 B/C + 437 Y/C).
All passengers deplane and board the aircraft.
2 Passenger Boarding Bridges (PBB) used at doors M1L and M2L.
Equipment positioning main deck + opening door = +3 min.
Closing door + equipment removal main deck = +3 min.
No Passenger with Reduced Mobility (PRM) on board.
Deplaning:
- 221 pax at door M1L (22 F/C + 96 B/C + 103 Y/C)
- 334 pax at door M2L (334 Y/C)
- Deplaning rate = 25 pax/min per door
- Priority deplaning for premium passengers.
Boarding:
- 221 pax at door M1L (22 F/C + 96 B/C + 103 Y/C)
- 334 pax at door M2L (334 Y/C)
- Boarding rate = 15 pax/min per door
- Last Pax Seating allowance (LPS) + headcounting = +4 min.
B.
CARGO
2 cargo loaders + 1 belt loader.
Opening door + equipment positioning = +2.5 min.
Equipment removal + closing door = +2.5 min.
100% cargo exchange:
- FWD cargo compartment: 20 containers
- AFT cargo compartment: 16 containers
- Bulk compartment: 1 000 kg (2 205 lb).
Container unloading/loading times:
- Unloading = 1.2 min/container
- Loading = 1.4 min/container.
5-2-2
Page 1
Dec 01/14
@A380
Bulk unloading/loading times:
- Unloading = 110 kg/min (243 lb/min)
- Loading = 95 kg/min (209 lb/min).
C.
REFUELING
242 700 l (64 115 US gal) at 40 psig.
Dispenser positioning + connection = +8 min.
Disconnection + dispenser removal = +8 min.
D.
CLEANING
Cleaning is performed in available time.
E.
CATERING
3 main deck catering trucks.
Main deck equipment positioning + door opening = +5 min.
Main deck closing door + equipment removal = +3 min.
Full Size Trolley Equivalent (FSTE) to unload and load: 78 FSTE.
- 23 FSTE at door U1R
- 11 FSTE at door M5L.
Time for trolley exchange = 1.5 min per FSTE.
Time for trolley exchange via lift = 2 min per FSTE.
F.
GROUND HANDLING/SERVICING
Start of operations:
- Bridges/stairs: t0 = 0
- Other equipment: t = t0 + 1 min.
Ground Power Unit (GPU): up to 4 x 90 kVA.
Air conditioning: up to 4 hoses.
Potable water servicing: 100% uplift, 1 700 l (449 US gal).
Waste water servicing: draining + rinsing.
5-2-2
Page 2
Dec 01/14
@A380
**ON A/C A380-800
TRT: 140 min
DEPLANING/BOARDING
AT M1L
DEPLANING/BOARDING
AT M2L
HEADCOUNTING & LPS
0
20
40
60
80
100
120
140
CATERING AT M2R
CATERING AT M4R
CATERING AT M5L
CLEANING AT M1R
AVAILABLE TIME
CARGO FWD CC
CARGO AFT CC
BULK
REFUELING
POTABLE WATER SERVICING
WASTE WATER SERVICING
GSE POSITIONING/REMOVAL
ACTIVITY
CRITICAL PATH
L_AC_050202_1_0010101_01_03
Typical Turn-Round Time
Servicing Via Main Deck
FIGURE-5-2-2-991-001-A01
5-2-2
Page 3
Dec 01/14
@A380
5-4-1
**ON A/C A380-800
1.
This section gives the ground service connections layout.
5-4-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
8 7
12
10
5
8 7
13
1
16 15
3 2
4
6 8
9
16
18
15
17
12
14
19
11
20
8
7
7
15
16
1 − GROUNDING POINT NLG
2 − GROUND ELECTRICAL POWER CONNECTORS
3 − POTABLE WATER DRAIN PANEL
4 − OXYGEN SYSTEM
5 − LOW PRESSURE PRECONDITIONED AIR
6 − HIGH PRESSURE AIR ENGINE START
7 − VFG AND STARTER OIL FILLING
8 − ENGINE OIL FILLING*
9 − HYDRAULIC RESERVOIR SERVICING PANEL
10 − YELLOW HYDRAULIC GROUND CONNECTOR
11 − GREEN HYDRAULIC GROUND CONNECTOR
12 − PRESSURE REFUEL CONNECTORS
13 − GROUNDING POINT WLG
14 − GROUNDING POINT BLG
15 − NACA FLAME ARRESTOR
16 − OVERPRESSURE PROTECTOR
17 − REFUEL/DEFUEL CONTROL PANEL
18 − POTABLE WATER SERVICE PANEL
19 − TOILET AND WASTE SERVICE PANEL
20 − APU OIL FILLING
NOTE:
* THE ENGINE OIL SERVICING POINTS (8) ARE SHOWN FOR THE RR TRENT 900 ENGINE.
FOR THE GP 7200 ENGINE, THE ENGINE OIL SERVICING POINTS (8) ARE LOCATED SYMMETRICALLY
ON THE LH SIDE OF EACH ENGINE.
L_AC_050401_1_0010101_01_03
FIGURE-5-4-1-991-001-A01
5-4-1
Page 2
Dec 01/14
@A380
5-4-2
**ON A/C A380-800
1.
ACCESS
On Nose Landing
Gear leg
On Wing Gear leg
(Inboard)
On Body Gear leg
(Outboard)
On Body Gear leg
(Inboard)
AFT OF NOSE
5.71 m
(18.73 ft)
34.21 m
(112.24 ft)
37.16 m
(121.92 ft)
37.16 m
(121.92 ft)
DISTANCE
FROM AIRCRAFT CENTERLINE
LH SIDE
RH SIDE
0.18 m
(0.59 ft)
5.95 m
5.95 m
(19.52 ft)
(19.52 ft)
2.85 m
2.85 m
(9.35 ft)
(9.35 ft)
2.41 m
2.41 m
(7.91 ft)
(7.91 ft)
MEAN HEIGHT
FROM GROUND
1.39 m
(4.56 ft)
1.24 m
(4.07 ft)
1.38 m
(4.53 ft)
1.38 m
(4.53 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 (earthing) studs are used to connect the aircraft to approved ground (earth)
connection on the ramp or in the hangar for:
- Refuel/defuel operations
- Maintenance operations
- Bad weather conditions.
5-4-2
Page 1
Dec 01/14
@A380
**ON A/C A380-800
A
GROUNDING (EARTHING)
POINT
A
L_AC_050402_1_0010101_01_01
Grounding (Earthing) Point - NLG
FIGURE-5-4-2-991-001-A01
5-4-2
Page 2
Dec 01/14
@A380
**ON A/C A380-800
A
GROUNDING (EARTHING) POINT
A
L_AC_050402_1_0020101_01_01
Grounding (Earthing) Points - WLG
FIGURE-5-4-2-991-002-A01
5-4-2
Page 3
Dec 01/14
@A380
**ON A/C A380-800
A
GROUNDING (EARTHING) POINT
(RIGHT ONE SHOWN LEFT ONE SIMILAR)
A
L_AC_050402_1_0030101_01_01
Grounding (Earthing) Points - BLG
FIGURE-5-4-2-991-003-A01
5-4-2
Page 4
Dec 01/14
@A380
5-4-3
Hydraulic System
**ON A/C A380-800
Hydraulic System
1.
Ground Service Panel
ACCESS
Hydraulic Reservoir Servicing Panel:
Access Door 197CB
A.
AFT OF
NOSE
31.89 m
(104.63 ft)
DISTANCE
FROM AIRCRAFT
CENTERLINE
LH SIDE
RH SIDE
2.34 m
(7.68 ft)
MEAN HEIGHT
FROM GROUND
1.71 m
(5.61 ft)
Connectors
(1) Reservoir Filling:
- One 3022079-312
(2) Reservoir Pressurization/Depressurization:
- One 3022079-324 (pressurization)
- One pressure-switch (green hydraulic reservoir depressurization)
- One pressure-switch (yellow hydraulic reservoir depressurization).
2.
Ground Test
ACCESS
Green Hydraulic Ground Connectors:
Behind Engine 2
Access Door 469FL
Yellow Hydraulic Ground Connectors:
Behind Engine 3
Access Door 479FL
A.
AFT OF
NOSE
34.67 m
(113.75 ft)
34.67 m
(113.75 ft)
DISTANCE
FROM AIRCRAFT
CENTERLINE
LH SIDE
RH SIDE
14.90 m
(48.88 ft)
MEAN HEIGHT
FROM GROUND
5.08 m
(16.67 ft)
14.90 m
(48.88 ft)
5.08 m
(16.67 ft)
Connectors
- One D24331000 (Suction)
- One D24330000 (Delivery).
5-4-3
Page 1
Dec 01/14
@A380
**ON A/C A380-800
A
Z190
B
A
GREEN HYD RESERVOIR
DEPRESSURIZATION
SWITCH
RESERVOIR
PRESSURIZATION
CONNECTOR
RESERVOIR FILLING
CONNECTOR
YELLOW HYD RESERVOIR
DEPRESSURIZATION
SWITCH
FWD
B
L_AC_050403_1_0010101_01_01
Ground Service Connections
Hydraulic Reservoir Servicing Panel
FIGURE-5-4-3-991-001-A01
5-4-3
Page 2
Dec 01/14
@A380
**ON A/C A380-800
B C
Z470
A
Z460
A
A
GREEN HP
SELF SEALING
GND CONNECTOR
YELLOW HP
SELF SEALING
GND CONNECTOR
GREEN SUCTION
SELF SEALING
GND CONNECTOR
YELLOW SUCTION
SELF SEALING
GND CONNECTOR
B
C
FOR LH PYLON
FOR RH PYLON
L_AC_050403_1_0020101_01_00
Hydraulic Ground Connections
FIGURE-5-4-3-991-002-A01
5-4-3
Page 3
Dec 01/14
@A380
5-4-4
Electrical System
**ON A/C A380-800
Electrical System
1.
AC External Power
ACCESS
DISTANCE
AFT OF NOSE
5.99 m
(19.65 ft)
5.99 m
(19.65 ft)
Right Side Access Door:
134AR
Left Side Access Door:
133AL
2.
LH SIDE
RH SIDE
0.45 m
(1.48 ft)
0.45 m
(1.48 ft)
MEAN HEIGHT
FROM
GROUND
2.59 m
(8.50 ft)
2.59 m
(8.50 ft)
Technical Specifications
A.
External Power Receptacles:
- Four receptacles according to MS 90362-3 (without shield MS 17845-1) - 90 kVA.
NOTE : Make sure that for connectors featuring micro switches, the connectors are chamfered
to properly engage in the receptacles.
3.
B.
Power Supply:
- Three-phase, 115V, 400 Hz.
C.
Electrical Connectors:
- AC outlets: HUBBELL 5258
- DC outlets: HUBBELL 7472.
AC Emergency Generation
ACCESS
RAT Safety-Pin
Installation
Access Panel: 531DL
DISTANCE
AFT OF NOSE
31.00 m
(101.71 ft)
LH SIDE
RH SIDE
9.50 m
(31.17 ft)
MEAN HEIGHT
FROM
GROUND
3.20 m
(10.5 ft)
5-4-4
Page 1
Dec 01/14
@A380
**ON A/C A380-800
A
FR17
FR18
134AR
EXTERNAL POWER
RECEPTACLES
FR17
FR18
133AL
B
A
FWD
FR17
EXTERNAL POWER
RECEPTACLES
FR18
B
FWD
L_AC_050404_1_0010101_01_01
Electrical Service Panel
FIGURE-5-4-4-991-001-A01
5-4-4
Page 2
Dec 01/14
@A380
**ON A/C A380-800
531DL
Z531
A
B
A
C
B
RAT UPLOCK SAFETY−PIN
RAM AIR TURBINE (RAT)
C
NOTE:
ALWAYS KEEP THE WARNING FLAG
OUT OF THE RAT FAIRING HAND HOLE.
L_AC_050404_1_0050101_01_00
Ram Air Turbine Retracted
FIGURE-5-4-4-991-005-A01
5-4-4
Page 3
Dec 01/14
@A380
**ON A/C A380-800
531KL
Z531
B
A
531KR
A
RAM AIR TURBINE (RAT)
1.65 m
(5.41 ft)
GROUND
B
FWD
L_AC_050404_1_0060101_01_00
Ram Air Turbine Extended
FIGURE-5-4-4-991-006-A01
5-4-4
Page 4
Dec 01/14
@A380
5-4-5
Oxygen System
**ON A/C A380-800
Oxygen System
1.
Oxygen System
ACCESS
Access Panels: 132AJW
132EJW
DISTANCE
FROM AIRCRAFT CENTERLINE MEAN HEIGHT
FROM
AFT OF NOSE
LH SIDE
RH SIDE
GROUND
13.32 m
2.23 m
3.25 m
(43.70 ft)
(7.32 ft)
(10.66 ft)
A.
Access:
Get access to the forward lower-deck cargo-compartment.
The access panel to the crew oxygen servicing point is located on the rear triangular area of the
FWD cargo door.
B.
Technical Specifications:
- MIL-DTL-7891 standard service connection
- Zero, one or two service connections (external charging in the FWD cargo compartment).
5-4-5
Page 1
Dec 01/14
@A380
**ON A/C A380-800
Z130
A
FR34
FR29
FR17
B
PASSENGER
OXYGEN
FILLING POINT
A
CREW OXYGEN
FILLING POINT
FR29
B
L_AC_050405_1_0020101_01_00
Oxygen System
FIGURE-5-4-5-991-002-A01
5-4-5
Page 2
Dec 01/14
@A380
5-4-6
Fuel System
**ON A/C A380-800
Fuel System
1.
Refuel/Defuel Control Panel
ACCESS
Refuel/Defuel Control
Panel
Access Door 199KB
2.
AFT OF NOSE
48 m
(157.48 ft)
0.68 m
(2.23 ft)
MEAN HEIGHT
FROM GROUND
1.98 m
(6.50 ft)
Refuel/Defuel Connectors
ACCESS
AFT OF NOSE
Refuel/Defuel Coupling
Access
522GB
31.89 m
Door:
(LH)
(104.63 ft)
622GB
(RH)
3.
DISTANCE
LH SIDE
RH SIDE
DISTANCE
LH SIDE
RH SIDE
17.97 m
(58.96 ft)
A.
Refuel/Defuel couplings:
- Four standard 2.5 in. ISO 45 connections.
B.
Refuel pressure:
- Maximum pressure: 50 psi (3.45 bar).
17.97 m
(58.96 ft)
MEAN HEIGHT
FROM GROUND
5.94 m
(19.49 ft)
Overpressure Protector and NACA Flame Arrestor
ACCESS
Overpressure Protector
(Wing)
Access
550CB (LH)
Panel:
650CB (RH)
NACA Flame Arrestor
(Wing)
Access
550BB (LH)
Panel:
650BB (RH)
AFT OF NOSE
DISTANCE
LH SIDE
RH SIDE
MEAN HEIGHT
FROM GROUND
46.65 m
(153.05 ft)
36.75 m
(120.57 ft)
36.75 m
(120.57 ft)
7.51 m
(24.64 ft)
46.33 m
(152.00 ft)
35.98 m
(118.04 ft)
35.98 m
(118.04 ft)
7.44 m
(24.41 ft)
5-4-6
Page 1
Dec 01/14
@A380
ACCESS
Overpressure Protector
(Trim Tank)
Access Panel 344AB
NACA Flame Arrestor
(Trim Tank)
Access Panel 344AB
AFT OF NOSE
DISTANCE
LH SIDE
RH SIDE
MEAN HEIGHT
FROM GROUND
62.75 m
(205.87 ft)
5.19 m
(17.03 ft)
7.68 m
(25.20 ft)
63.97 m
(209.88 ft)
4.64 m
(15.22 ft)
7.55 m
(24.77 ft)
5-4-6
Page 2
Dec 01/14
@A380
**ON A/C A380-800
Z190
A
B
A
SHUTOFF
TEST
POWER SUPPLY
BATTERY
L OUTR
FEED 1
FEED 2
FEED 3
FEED 4
R OUTR
OPEN
NORMAL
SHUT
FAULT
OVERFLOW
HI LVL
L OUTR
FEED 1
FEED 2
FEED 3
FEED 4
ACTUAL (FOB)
R OUTR
kg
L MID
L INR
TRIM
R INR
PRESELECT (PFQ)
R MID
STATUS
HI LVL
OPEN
L MID
L INR
TRIM
R INR
R MID
SHUT
REFUEL/DEFUEL VALVES
MAN
REFUEL
OFF
INCREASE
AUTO
REFUEL
APU EMERGENCY
SHUTDOWN
DEFUEL
DECREASE
XFR
MODE SELECT
PRESELECT
42QU
B
L_AC_050406_1_0010101_01_00
Refuel/Defuel Control Panel
FIGURE-5-4-6-991-001-A01
5-4-6
Page 3
Dec 01/14
@A380
**ON A/C A380-800
Z500
B
A
A
A
Z600
LH SIDE SHOWN
RH SIDE SYMETRICAL
REFUEL / DEFUEL COUPLINGS
REFUEL PRESSURE
B
L_AC_050406_1_0020101_01_00
Pressure Refuel Connections
FIGURE-5-4-6-991-002-A01
5-4-6
Page 4
Dec 01/14
@A380
**ON A/C A380-800
550CB
(650CB)
A
550BB
(650BB)
C
B
A
FWD
A
LH SIDE SHOWN
RH SIDE SYMMETRICAL
NACA FLAME ARRESTOR
B
C
OVERPRESSURE PROTECTOR
L_AC_050406_1_0030101_01_01
Overpressure Protector and NACA Flame Arrestor - Wing
FIGURE-5-4-6-991-003-A01
5-4-6
Page 5
Dec 01/14
@A380
**ON A/C A380-800
RIB8
RIB9
A
344AB
Z344
B
F
W
D
A
OVERPRESSURE
PROTECTOR
BOTTOM SKIN
NACA INTAKE
B
L_AC_050406_1_0040101_01_00
Overpressure Protector and NACA Flame Arrestor - Trim Tank
FIGURE-5-4-6-991-004-A01
5-4-6
Page 6
Dec 01/14
@A380
5-4-7
Pneumatic System
**ON A/C A380-800
Pneumatic System
1.
Low Pressure Connectors
ACCESS
AFT OF NOSE
21.85 m
Access Door 191GB (71.69 ft)
22.36 m
Access Door 191JB (73.36 ft)
21.85 m
Access Door 191HB (71.69 ft)
22.36 m
Access Door 191KB (73.36 ft)
A.
DISTANCE
LH SIDE
RH SIDE
1.24 m
(4.07 ft)
1.76 m
(5.77 ft)
1.24 m
(4.07 ft)
1.76 m
(5.77 ft)
MEAN HEIGHT
FROM GROUND
2.08 m
(6.82 ft)
2.08 m
(6.82 ft)
2.08 m
(6.82 ft)
2.08 m
(6.82 ft)
Connectors:
(1) Four standard 8 in. SAE AS4262 type B connections.
2.
High Pressure Connectors
ACCESS
AFT OF NOSE
25.37 m
Access Door 193BB (83.23 ft)
A.
DISTANCE
LH SIDE
RH SIDE
0.2 m
(0.66 ft)
MEAN HEIGHT
FROM GROUND
1.78 m
(5.84 ft)
Connectors:
(1) Three standard 3 in. ISO 2026 connections.
5-4-7
Page 1
Dec 01/14
@A380
**ON A/C A380-800
B
Z190
B
B
A
B
A
LOW PRESSURE AIR CONNECTOR
B
L_AC_050407_1_0010101_01_00
Low Pressure Preconditioned Air
FIGURE-5-4-7-991-001-A01
5-4-7
Page 2
Dec 01/14
@A380
**ON A/C A380-800
Z190
A
B
A
HIGH PRESSURE AIR CONNECTORS
B
L_AC_050407_1_0020101_01_00
High Pressure Preconditioned Air
FIGURE-5-4-7-991-002-A01
5-4-7
Page 3
Dec 01/14
@A380
5-4-8
Oil System
**ON A/C A380-800
1.
Engine Oil Servicing (TRENT 900 Engines)
ACCESS
AFT OF NOSE
DISTANCE
FROM AIRCRAFT
CENTERLINE
LH SIDE
32.65 m
(107.12 ft)
24.98 m
(81.96 ft)
24.98 m
(81.96 ft)
32.65 m
(107.12 ft)
Engine 1:
Access Door 416BR
Engine 2:
Access Door 426BR
Engine 3:
Access Door 436BR
Engine 4:
Access Door 446BR
2.
RH SIDE
23.58 m
(77.36 ft)
12.74 m
(41.80 ft)
16.61 m
(54.49 ft)
27.45 m
(90.06 ft)
MEAN
HEIGHT
FROM
GROUND
4.24 m
(13.91 ft)
3.08 m
(10.10 ft)
3.08 m
(10.10 ft)
4.24 m
(13.91 ft)
Engine Oil Servicing (GP7200 Engines)
ACCESS
AFT OF NOSE
DISTANCE
FROM AIRCRAFT
CENTERLINE
LH SIDE
Engine 1:
Access Door
Engine 2:
Access Door
Engine 3:
Access Door
Engine 4:
Access Door
415CL
425CL
435CL
445CL
33.03 m
(108.37 ft)
25.35 m
(83.17 ft)
25.35 m
(83.17 ft)
33.03 m
(108.37 ft)
RH SIDE
27.42 m
(89.96 ft)
16.62 m
(54.53 ft)
12.78 m
(41.93 ft)
23.62 m
(77.49 ft)
5-4-8
MEAN
HEIGHT
FROM
GROUND
4.40 m
(14.44 ft)
3.13 m
(10.27 ft)
3.13 m
(10.27 ft)
4.40 m
(14.44 ft)
Page 1
Dec 01/14
@A380
**ON A/C A380-800
A
A
L_AC_050408_1_0060101_01_00
Engine Oil Servicing - TRENT 900 Engines
FIGURE-5-4-8-991-006-A01
5-4-8
Page 2
Dec 01/14
@A380
**ON A/C A380-800
A
FWD
B
"T" HANDLE
B
OIL TANK
FILLER CAP
E−00236 (1007)
PW V
PIN
ENGAGEMENT
OIL TANK
SIGHT GAGE
A
L_AC_050408_1_0070101_01_00
Engine Oil Servicing - GP7200 Engines
FIGURE-5-4-8-991-007-A01
5-4-8
Page 3
Dec 01/14
@A380
**ON A/C A380-800
VFG Oil Servicing
1.
VFG Oil Servicing (TRENT 900 Engines)
ACCESS
Engine 1
Access Door:
415AL
Engine 2
Access Door:
425AL
Engine 3
Access Door:
435AL
Engine 4
Access Door:
445AL
AFT OF NOSE
33.17 m
(108.83 ft)
25.57 m
(83.89 ft)
DISTANCE
LH SIDE
RH SIDE
26.14 m
(85.76 ft)
15.31 m
(50.23 ft)
MEAN HEIGHT
FROM GROUND
2.56 m
(8.40 ft)
1.33 m
(4.36 ft)
25.57 m
(83.89 ft)
13.93 m
(45.70 ft)
1.33 m
(4.36 ft)
33.17 m
(108.83 ft)
24.90 m
(81.69 ft)
2.56 m
(8.40 ft)
For VFG oil servicing (TRENT 900 Engines), open:
- Left Fan Exhaust Cowl.
2.
VFG Oil Servicing (GP7200 Engines)
ACCESS
Engine 1
Access Doors:
415AL and 417AL
Engine 2
Access Doors:
425AL and 427AL
Engine 3
Access Doors:
435AL and 437AL
Engine 4
Access Doors:
445AL and 447AL
AFT OF NOSE
DISTANCE
LH SIDE
RH SIDE
MEAN HEIGHT
FROM GROUND
34.49 m
(113.16 ft)
25.43 m
(83.43 ft)
2.63 m
(8.63 ft)
26.81 m
(87.96 ft)
14.63 m
(48.00 ft)
1.36 m
(4.46 ft)
26.81 m
(87.96 ft)
14.63 m
(48.00 ft)
1.36 m
(4.46 ft)
34.49 m
(113.16 ft)
25.43 m
(83.43 ft)
2.63 m
(8.63 ft)
For VFG oil servicing (GP7200 Engines), open:
- Left Fan Exhaust Cowl
- Left Thrust Reverser Cowl.
5-4-8
Page 4
Dec 01/14
@A380
**ON A/C A380-800
A
B
PRESSURE FILL
VALVE
CASE DRAIN
PLUG
VFG
OIL LEVEL
OVERFLOW
DRAIN VALVE
B
A
L_AC_050408_1_0080101_01_00
VFG Oil Servicing - TRENT 900 Engines
FIGURE-5-4-8-991-008-A01
5-4-8
Page 5
Dec 01/14
@A380
**ON A/C A380-800
VFG
B
CASE DRAIN
PLUG
A
C
OIL LEVEL
OVERFLOW
DRAIN VALVE
A
PRESSURE
FILL VALVE
B
C
L_AC_050408_1_0090101_01_00
VFG Oil Servicing - GP7200 Engines
FIGURE-5-4-8-991-009-A01
5-4-8
Page 6
Dec 01/14
@A380
**ON A/C A380-800
1.
Starter Oil Servicing (TRENT 900 Engines)
ACCESS
Engine 1
Engine 2
Engine 3
Engine 4
2.
DISTANCE
LH SIDE
RH SIDE
25.78 m
(84.57 ft)
14.94 m
(49.01 ft)
14.42 m
(47.30 ft)
25.25 m
(82.84 ft)
MEAN HEIGHT
FROM GROUND
2.59 m
(8.49 ft)
1.39 m
(4.56 ft)
1.39 m
(4.56 ft)
2.59 m
(8.49 ft)
DISTANCE
LH SIDE
RH SIDE
27.34 m
(89.70 ft)
16.55 m
(54.30 ft)
12.71 m
(41.70 ft)
23.53 m
(77.20 ft)
MEAN HEIGHT
FROM GROUND
3.35 m
(10.99 ft)
2.47 m
(8.10 ft)
2.47 m
(8.10 ft)
3.35 m
(10.99 ft)
AFT OF NOSE
39.78 m
(130.51 ft)
32.15 m
(105.49 ft)
32.15 m
(105.49 ft)
39.78 m
(130.51 ft)
Starter Oil Servicing (GP7200 Engines)
ACCESS
Engine 1
Engine 2
Engine 3
Engine 4
AFT OF NOSE
40.42 m
(132.61 ft)
32.74 m
(107.41 ft)
32.74 m
(107.41 ft)
40.42 m
(132.61 ft)
For access to Starter Oil Servicing, open Fan Cowl.
5-4-8
Page 7
Dec 01/14
@A380
**ON A/C A380-800
A
OIL FILL PLUG
OILSIGHT
GLASS
A
L_AC_050408_1_0100101_01_00
Starter Oil Servicing - TRENT 900 Engines
FIGURE-5-4-8-991-010-A01
5-4-8
Page 8
Dec 01/14
@A380
**ON A/C A380-800
A
PNEUMATIC STARTER
5000ES
STARTER CONTROL VALVE
4005KS
V−BAND
CLAMP
AND QAD
ADAPTER
FILL
PORT
E−00549 (0308)
PW V
MAGNETIC
CHIP
DETECTOR
A
L_AC_050408_1_0110101_01_00
Starter Oil Servicing - GP7200 Engines
FIGURE-5-4-8-991-011-A01
5-4-8
Page 9
Dec 01/14
@A380
**ON A/C A380-800
APU Oil Servicing
1.
APU Oil Servicing
ACCESS
Access Doors:
315AL, 315AR
A.
AFT OF NOSE
67.55 m
(221.62 ft)
DISTANCE
LH SIDE
RH SIDE
0.44 m
(1.44 ft)
MEAN HEIGHT
FROM GROUND
6.83 m
(22.41 ft)
Capacity:
- 18.13 l (4.79 US gal).
5-4-8
Page 10
Dec 01/14
@A380
**ON A/C A380-800
B
Z310
FWD
A
A
FILL CAP
FR117
C
FR112
FULL MARK
B
VISUAL SIGHT−GLASS
C
L_AC_050408_1_0120101_01_00
APU Oil Servicing
FIGURE-5-4-8-991-012-A01
5-4-8
Page 11
Dec 01/14
@A380
5-4-9
**ON A/C A380-800
1.
This section provides data related to the location of the ground service connections.
ACCESS
AFT OF NOSE
DISTANCE
FROM AIRCRAFT
CENTERLINE
LH SIDE
Potable Water Ground Service Panel:
Access Door 199NB
Potable Water Drain Panel:
Access Door 133BL
43.67 m
(143.27 ft)
9.83 m
(32.25 ft)
RH SIDE
0.37 m
(1.21 ft)
0.30 m
(0.98 ft)
MEAN
HEIGHT
FROM
GROUND
2.13 m
(6.99 ft)
2.74 m
(8.99 ft)
NOTE : Distances are approximate.
A.
Connections
Fill and drain port - ISO 17775, 3/4 in.
B.
Capacity:
(1) Total Capacity
- Standard configuration (six tanks): 1700 l (449 US gal)
- Optional configuration (seven tanks): 1998 l (528 US gal)
- Optional configuration (eight tanks): 2267 l (599 US gal).
C.
Filling Pressure:
(1) Max Filling Pressure: 8.6 bar (125 psi).
5-4-9
Page 1
Dec 01/14
@A380
**ON A/C A380-800
FR76
A
Z190
199NB
A
B
LWL PRE
80
100
/0
0
50
0
PRESS UP OR DOWN TO PRESET
DOWN
PRESET WATER
UP
MENU
SELECT
DRAIN
FILL
FILL/DRAIN PORT
NORMAL
B
FWD
L_AC_050409_1_0160101_01_00
Potable Water Ground Service Panel
FIGURE-5-4-9-991-016-A01
5-4-9
Page 2
Dec 01/14
@A380
**ON A/C A380-800
FR23
Z130
A
FR24
A
B
DRAIN VALVE
CONTROL HANDLE
DRAIN PORT
B
ACCESS DOOR
133BL
L_AC_050409_1_0170101_01_00
Potable Water Drain Panel
FIGURE-5-4-9-991-017-A01
5-4-9
Page 3
Dec 01/14
@A380
**ON A/C A380-800
A
Z140
OPTIONAL
FR55
FR57
FR59
OPTIONAL
POTABLE WATER TANKS
(STANDARD: 6 TANKS,
OPTION: 7 OR 8 TANKS)
A
L_AC_050409_1_0180101_01_00
Potable Water Tanks Location
FIGURE-5-4-9-991-018-A01
5-4-9
Page 4
Dec 01/14
@A380
5-4-10
Vacuum Toilet System
**ON A/C A380-800
Waste Water System
1.
Waste Water System
This section provides data related to the location of the ground service connections.
ACCESS
Waste Water Ground
Service Panel:
Access door 171AL
AFT OF NOSE
53.31 m
(174.90 ft)
DISTANCES
LH SIDE
RH SIDE
0.26 m
(0.85 ft)
MEAN HEIGHT
FROM GROUND
3.40 m
(11.15 ft)
NOTE : Distances are approximate.
2.
Technical Specifications
A.
Connectors
(1) Waste water drain-connection - ISO 17775, 4 in.
(2) Waste water rinse/fill port - ISO 17775, 1 in.
B.
Capacity
There are four waste tanks, two upper deck tanks and two main deck tanks, see FIGURE
5-4-10-991-003-A.
(1) Upper Deck Waste Tanks
- Two tanks (373 l (99 US gal) each).
Each tank is precharged with 35 l (9 US gal) of chemical fluid.
(2) Main Deck Waste Tanks
- Two tanks (675 l (178 US gal) each).
Each tank is precharged with 35 l (9 US gal) of chemical fluid.
(3) Total Waste Tank Capacity
- 2096 l (554 US gal).
C.
Pressure
Maximum pressure for rinsing and precharge to the rinse/fill port is 3.45 bar (50 psi).
5-4-10
Page 1
Dec 01/14
@A380
**ON A/C A380-800
Z160
FR86
A
FR91
B
A
WASTE DRAIN
CONNECTION
FILL AND RINSE
CONNECTION
CONTROL
LEVER
WASTE TANK DRAIN VALVE
OPEN
UPPER
DECK
RH
LH
MAIN
DECK
RH
LH
CLOSE
B
FWD
L_AC_050410_1_0010101_01_00
Waste Water Ground Service Panel
FIGURE-5-4-10-991-001-A01
5-4-10
Page 2
Dec 01/14
@A380
**ON A/C A380-800
A
Z170
WASTE TANK
(STANDARD: 4 TANKS)
FR95
FR94
FR93
FR92
FR91
A
L_AC_050410_1_0030101_01_01
Waste Tanks Location
FIGURE-5-4-10-991-003-A01
5-4-10
Page 3
Dec 01/14
@A380
5-4-11
**ON A/C A380-800
1.
ACCESS
FWD CLS* Panel:
Access Door 132AR
FWD Cargo Door
Panel:
Access Door 132BR
AFT CLS* Panel:
Access Door 152AR
AFT Cargo Door
Panel:
Access Door 199DR
AFT OF NOSE
9.83 m
(32.25 ft)
DISTANCE
LH SIDE
RH SIDE
3.08 m
(10.10 ft)
MEAN HEIGHT
FROM GROUND
4.40 m
(14.44 ft)
9.85 m
(32.32 ft)
2.42 m
(7.94 ft)
3.40 m
(11.15 ft)
46.32 m
(151.97 ft)
3.11 m
(10.20 ft)
4.38 m
(14.37 ft)
45.67 m
(149.84 ft)
2.45 m
(8.04 ft)
3.08 m
(10.10 ft)
NOTE : * CLS - CARGO LOADING SYSTEMS
5-4-11
Page 1
Dec 01/14
@A380
**ON A/C A380-800
FWD CARGO DOOR
A
B
Z130
C
SYST ON LAMP
FR23
FR24
A
INDICATOR LIGHT
"CARGO DOOR FULLY
OPEN AND ARRESTED"
JOYSTICK
132BR
132AR
PWR ON/OFF SWITCH
B
TOGGLE SWITCH
OPEN OR CLOSE
CARGO DOOR
PROTECTION
COVER
OUTSIDE CARGO LOADING
SYSTEM CONTROL PANEL
MANUAL
OPERATING DEVICE
C
CARGO DOOR CONTROL PANEL
L_AC_050411_1_0010101_01_00
Forward Cargo Control Panels
FIGURE-5-4-11-991-001-A01
5-4-11
Page 2
Dec 01/14
@A380
**ON A/C A380-800
FR79
Z190
FR80
FR81
B
Z150
A
C
AFT CARGO DOOR
A
SYST ON LAMP
JOYSTICK
INDICATOR LIGHT
"CARGO DOOR FULLY
OPEN AND ARRESTED"
MANUAL OPERATING
DEVICE
199DR
152AR
PWR ON/OFF SWITCH
TOGGLE SWITCH
OPEN OR CLOSE
CARGO DOOR
B
OUTSIDE CARGO LOADING
SYSTEM CONTROL PANEL
PROTECTION
COVER
C
CARGO DOOR CONTROL PANEL
L_AC_050411_1_0020101_01_00
Aft Cargo Control Panels
FIGURE-5-4-11-991-002-A01
5-4-11
Page 3
Dec 01/14
@A380
5-5-0
**ON A/C A380-800
1.
The purpose of this section is to provide the air data at the aircraft connection, needed to start the
engine within no more than 90 seconds, at sea level (0 ft), for a set of Outside Air Temperatures
(OAT).
ABBREVIATION
A/C
ASU
HPGC
OAT
DEFINITION
Aircraft
Air Start Unit
High Pressure Ground Connection
A.
Air data (discharge temperature, absolute discharge pressure) are given at the HPGC.
B.
For the requirements below, the configuration with two HPGC is used. Using more than two
connectors (for a given mass flow rate and discharge pressure from the ASU) will lower the
pressure loss in the ducts of the bleed system and therefore increase the performances at the
engine starter.
C.
For a given OAT the following charts are used to determine an acceptable combination for air
data: discharge temperature, absolute discharge pressure and mass flow rate at the HPGC.
D.
This section addresses requirements for the ASU only, and is not representative of the start
performance of the aircraft using the APU or engine cross bleed procedure.
E.
To protect the A/C, the charts feature, if necessary:
- The maximum discharge pressure at the HPGC
- The maximum discharge temperature at the HPGC.
5-5-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
ENGINE ALLIANCE GP 7200/SEA LEVEL
STARTING TIME: LESS THAN 90 s
AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)
140
AIRFLOW (kg/min)
250
120
230
110
210
100
190
90
170
80
70
150
40
45
50
ABSOLUTE PRESSURE (psia)
60
AIRFLOW (lb/min)
270
130
55
58
56
54
52
50
48
46
44
42
40
−45
−35
−40
−25
−20
−15
−5
5
15
25
35
OUTSIDE AIR TEMPERATURE OAT (° C)
20
40
60
80
0
OUTSIDE AIR TEMPERATURE OAT (° F)
100
45
55
120
ASU DISCHARGE TEMPERATURE:
60° C (140° F)
135° C (275° F)
265° C (509° F) MAX.
EXAMPLE:
FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 135° C (275° F)
AT HPGC:
− THE REQUIRED PRESSURE AT HPGC IS 42.8 psia
− THE REQUIRED AIRFLOW AT A/C CONNECTION IS 96 kg/min.
NOTE:
IN CASE THE ACTUAL DISCHARGE TEMPERATURE OF THE ASU DIFFERS SUBSTANTIALLY FROM THE
ONES GIVEN IN THE CHARTS, A SIMPLE INTERPOLATION (LINEAR) IS SUFFICIENT TO DETERMINE THE
REQUIRED AIR DATA.
EXAMPLE:
FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 195° C (383° F)
AT HPGC, INTERPOLATING BETWEEN THE LINES 135° C (275° F) AND 265° C (509° F) RESULTS IN:
− A REQUIRED PRESSURE AT HPGC OF 41.8 psia
− A REQUIRED AIRFLOW AT A/C CONNECTION OF 88 kg/min.
L_AC_050500_1_0030101_01_02
Example for Use of the Charts
FIGURE-5-5-0-991-003-A01
5-5-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
ENGINE ALLIANCE GP 7200/SEA LEVEL
140
270
250
120
230
110
210
100
190
90
170
80
70
AIRFLOW (lb/min)
AIRFLOW (kg/min)
130
150
45
50
40
55
60
58
56
54
52
50
48
46
44
42
40
5
15
25
0
20
40
60
80
60° C (140° F)
135° C (275° F)
265° C (509° F) MAX.
35
100
45
55
120
L_AC_050500_1_0040101_01_01
Engine Alliance - GP 7200
FIGURE-5-5-0-991-004-A01
5-5-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
ROLLS ROYCE TRENT 900/SEA LEVEL
160
290
280
140
270
130
250
120
230
110
210
100
190
90
80
AIRFLOW (lb/min)
AIRFLOW (kg/min)
150
170
40
45
50
55
60
5
15
25
35
65
65
60
55
50
45
40
0
20
40
60
80
55° C (131° F)
130° C (266° F)
255° C (491° F) MAX.
100
45
55
120
L_AC_050500_1_0050101_01_01
Rolls Royce - Trent 900 Engine
FIGURE-5-5-0-991-005-A01
5-5-0
Page 4
Dec 01/14
@A380
5-6-0
**ON A/C A380-800
1.
General
This section describes the required performance for the ground equipment to maintain the cabin
temperature at 27 ˚C (80.6 ˚F) after boarding (Section 5.7 - steady state), and provides the time
needed to cool down or heat up the aircraft cabin to the required temperature (Section 5.6 - dynamic
cases with aircraft empty).
ABBREVIATION
A/C
AHM
AMM
GC
GSE
IFE
LPGC
OAT
PCA
A.
DEFINITION
Aircraft
Aircraft Handling Manual
Aircraft Maintenance Manual
Ground Connection
Ground Service Equipment
In-Flight Entertainment
Low Pressure Ground Connection
Pre-Conditioned Air
The air flow rates and temperature requirements for the GSE, provided in Sections 5.6 and 5.7,
are given at A/C ground connection.
NOTE : The cooling capacity of the equipment (kW) is only indicative and is not sufficient by
itself to ensure the performance (outlet temperature and flow rate combinations are
the requirements needed for ground power).
An example of cooling capacity calculation is given in Section 5.7.
B.
The air flow rates and temperature requirements for the GSE are given for the A/C in the
configuration ”4 LP ducts connected”.
NOTE : The maximum air flow is driven by pressure limitation at LPGC.
C.
2.
For temperatures at ground connection below +2 ˚C (+35.6 ˚F) (Subfreezing), the ground
equipment shall be compliant with the Airbus document ”Subfreezing PCA Carts - Compliance
Document for Suppliers” (contact Airbus to obtain this document) defining all the requirements
with which Subfreezing Pre-Conditioning Air equipment must comply to allow its use on Airbus
aircraft. These requirements are in addition to the functional specifications included in the IATA
AHM997.
This section provides the ground pneumatic power requirements for:
5-6-0
Page 1
Dec 01/14
@A380
-
Heating (pull up) the cabin, initially at OAT, up to 21 ˚C (69.8 ˚F) (see FIGURE
5-6-0-991-001-A)
Cooling (pull down) the cabin, initially at OAT, down to 27 ˚C (80.6 ˚F) (see FIGURE
5-6-0-991-002-A).
5-6-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
PULL UP PERFORMANCE
7
15
MAXIMUM AIR FLOW
14
AIR FLOW AT GC (kg/s)
6
13
5.5
12
5
11
4.5
10
9
4
AIR FLOW AT GC (lb/s)
6.5
8
3.5
7
3
0
20
40
60
80
100
120
TIME TO HEAT CABIN TO +21° C (+69.8° F) ON GROUND (min)
OAT ISA −38° C (−36.4° F); GC OUTLET +70° C (+158° F); EMPTY CABIN; IFE OFF;
NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON
L_AC_050600_1_0010101_01_00
Heating
FIGURE-5-6-0-991-001-A01
5-6-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
PULL DOWN PERFORMANCE
7
MAXIMUM AIR FLOW
14
6
5
10
4
8
3
6
2
AIR FLOW AT GC (lb/s)
AIR FLOW AT GC (kg/s)
12
4
1
2
0
0
20
40
60
80
100
0
120
TIME TO COOL CABIN TO +27° C (+80.6° F) ON GROUND (min)
OAT ISA +23° C (+73.4° F); GC OUTLET +2° C (+35.6° F); EMPTY CABIN; IFE OFF;
SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON
OAT ISA +23° C (+73.4° F); GC OUTLET −10° C (+14° F); EMPTY CABIN; IFE OFF;
SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON
L_AC_050600_1_0020101_01_00
Cooling
FIGURE-5-6-0-991-002-A01
5-6-0
Page 4
Dec 01/14
@A380
5-7-0
**ON A/C A380-800
1.
This section provides the preconditioned airflow rate and temperature needed to maintain the cabin
temperature at 27˚C (80.6˚F).
These settings are not intended to be used for operation (they are not a substitute for the settings
given in the AMM). They are based on theoretical simulations and give the picture of a real steady
state.
For the air conditioning operation, the AMM details the procedure and the preconditioned airflow
settings to maintain the cabin temperature below 27˚C (80.6˚F) during boarding (therefore it is not
a steady state).
5-7-0
Page 1
Dec 01/14
6.5
0
−15
C1
10
−10
C2
20
−5
5
10
40
50
INLET TEMPERATURE AT GC (° F)
30
INLET TEMPERATURE AT GC (° C)
0
SETTINGS NOT INTENDED
TO BE USED FOR OPERATION
C3
MAXIMUM AIRFLOW
60
15
20
70
H
25
80
30
8.0
9.0
10.0
11.0
12.0
13.0
14.0
AIRFLOW AT GC (lb/s)
5-7-0
EXAMPLE:
COOLING CAPACITY CALCULATION:
FOR THE CONDITIONS C3, THE COOLING CAPACITY OF 4 kg/s x 1 kJ/(kg. ° C) x [27 − (−13)] = 152 kW
(OR 45 TONS COOLING CAPACITY) IS NEEDED TO MAINTAIN THE CABIN TEMPERATURE AT 27 ° C (80.6 ° F)
[4 kg/s AT −13 ° C (8.6 ° F) FOR AIR AT GC INLET].
AIRFLOW AT GC (kg/s)
OAT ISA +30 ° C (86 ° F); 723 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON
OAT ISA +23 ° C (73.4 ° F); 723 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON
OAT ISA; 723 PASSENGERS AND CREW; IFE ON; LIGHTS ON; SOLAR LOAD; RECIRCULATION FANS ON
OAT ISA −38 ° C (−36.4 ° F); EMPTY CABIN; IFE OFF; LIGHTS ON; NO SOLAR LOAD; RECIRCULATION FANS ON
3.5
−20
4.0
4.5
5.0
5.5
6.0
6.3
COOLING/HEATING PERFORMANCE
@A380
**ON A/C A380-800
L_AC_050700_1_0010101_01_05
FIGURE-5-7-0-991-001-A01
Page 2
Dec 01/14
@A380
5-8-0
**ON A/C A380-800
1.
This section provides information on aircraft Towing.
The A380-800 is designed with means for conventional towing or towbarless towing. Information on
towbarless towing can be found in SIL 09-002 and chapter 9 of the Aircraft Maintenance Manual.
It is possible to tow or push the aircraft, at maximum ramp weight with engines at zero or up to idle
thrust, using a towbar attached to the nose gear leg. The towbar fitting is installed at the front of
the leg (optional towing fitting for towing from the rear of the NLG available).
The body gears have attachment points for towing or debogging (for details refer to chapter 7 of the
Aircraft Recovery Manual).
NOTE : Information on aircraft towing procedures and corresponding aircraft limitations are given in
chapter 9 of the Aircraft Maintenance Manual.
Ground Towing Requirements A380-800 Models shows the chart to determine the towbar pull and
tow tractor mass requirements as function of the following physical characteristics, see FIGURE
5-8-0-991-001-A:
- Aircraft weight,
- Slope,
- Number of engines at idle.
The chart is based on the A380-800 engine type with the highest idle thrust. The chart is therefore
valid for all A380-800 models.
2.
Towbar design guidelines
The aircraft towbar shall respect the following norms:
- SAE AS 1614, ”Main Line Aircraft TowBar Attach Fitting Interface”,
- SAE ARP1915, ”Aircraft TowBar”,
- 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 standard type towbar should be equipped with a damping system to protect the nose gear against
jerks and with towing shear pins:
- A traction shear pin calibrated at 62000 daN (139381.53 lbf),
- A torsion pin calibrated at 4800 m.daN (424778.76 lbf.in).
The towing head is designed according to SAE/AS 1614 cat. V.
5-8-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
DRAWBAR PULL [ t ]
50
BREAKAWAY RESISTANCE 4%
# OF ENGINES ON FOR PB:2
45 ENGINE THRUST 1779.3 daN
A/C WEIGHT [ t ]
40
600
560
550
500
1.5% SLOPE
2 ENGINES ON
34.4
=
CO
NC
RE
25
DR
Y
20
15
5
0.
400
350
E
TE
30
450
7
=0
.8
35
ET
C
300
R
C
N
O
ET
W
2
10
D
HAR
5
0
W
SNO
ICE
0
10
20
30
40
= 0.
= 0.05
60.4
50
TRACTOR WEIGHT [ t ]
60
70
80 0
1
2
3
4 0
NO OF ENGINES AT IDLE
0.5
1.0
2.0
1.5
SLOPE [ % ]
EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A380 AT 560 t, AT 1.5% SLOPE,
2 ENGINES AT IDLE AND FOR WET TARMAC CONDITIONS:
−ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (560 t),
−FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (1.5%),
−FROM THE POINT OBTAINED DRAW A STRAIGHT HORIZONTAL LINE UNTIL No. OF ENGINES AT IDLE = 4,
−FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUESTED NUMBER OF ENGINES (2),
−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 (34.4 t),
−SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE.
THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (60.4 t).
L_AC_050800_1_0010101_01_02
FIGURE-5-8-0-991-001-A01
5-8-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
A
0.200 m
(7.9 in)
0.555 m
(21.85 in)
A
L_AC_050800_1_0040101_01_00
Nose Gear Towing Fittings
FIGURE-5-8-0-991-004-A01
5-8-0
Page 3
Dec 01/14
@A380
5-9-0
**ON A/C A380-800
1.
De-Icing and External Cleaning on Ground
The mobile equipment for aircraft de-icing and external cleaning must be capable of reaching heights
up to approximately 24 m (79 ft).
2.
De-Icing
Wing Top Surface
(Both Sides)
AIRCRAFT
TYPE
A380 - 800
ft2
7782
m2
723
AIRCRAFT TYPE
Fuselage Top Surface
(Top Third - 120˚ Arc)
ft2
m2
A380 - 800
Wingtip Devices
(Both Inside and
Outside Surfaces)
(Both Sides)
ft2
m2
10
108
497
5350
VTP
(Both Sides)
HTP Top Surface
(Both Sides)
m2
186
ft2
2002
Nacelle and Pylon
(Top Third - 120˚ Arc)
(All Engines)
ft2
m2
1206
112
ft2
2476
m2
230
Total De-Iced Area
ft2
18912
m2
1757
NOTE : Dimensions are approximate.
3.
External Cleaning
AIRCRAFT
TYPE
A380 - 800
Wing Top
Surface
(Both Sides)
m2
723
ft2
7782
Wing Lower
Wingtip Devices
Surface
(Both Inside and
HTP Top
Surface
(Including Flap
Outside
Track Fairing)
Surfaces)
(Both Sides)
(Both Sides)
(Both Sides)
2
2
ft
ft2
ft2
m
m2
m2
794
8547
10
108
186
2002
VTP
(Both Sides)
AIRCRAFT TYPE
ft2
m2
A380 - 800
230
2476
Fuselage and
Belly Fairing
ft2
m2
1531
16480
Nacelle and Pylon
(All Engines)
ft2
m2
373
4015
HTP Lower
Surface
(Both Sides)
m2
186
ft2
2002
Total Cleaned Area
m2
4034
ft2
43422
NOTE : Dimensions are approximate.
5-9-0
Page 1
Dec 01/14
@A380
OPERATING CONDITIONS
6-1-0
**ON A/C A380-800
1.
General
This section provides the estimated engine exhaust efflux velocity and temperature contours for
Maximum Take-off, Breakaway and Idle conditions for the A380 engine.
Contours are available for both Rolls-Royce’s Trent 900 engine and the Engine Alliance’s GP7200
engine.
The Maximum Take-off data are presented at the maximum thrust rating for all the A380 engine.
The Breakaway data are presented at a rating corresponding to the minimum thrust level required to
initiate movement of an A380-800 at its maximum ramp weight from static position and on uphill
ground.
The Idle data are directly provided by the engine manufacturers.
In the charts, longitudinal distances are measured from the inboard engine core nozzle exit station,
while lateral distances are measured from the aircraft fuselage centerline.
A.
Data from Rolls-Royce’s Trent 900:
The estimated efflux data are presented at ISA +15˚C (+59˚F), Sea Level Static and
negligible wind conditions.
The analysis assumes that the core and bypass streams are fully mixed and calculates the jet
behaviour in free, still air and therefore does not take into account effects such as on-wing
installation, ground entrainment and ambient wind conditions.
Velocity contours are presented at 50 ft/s (15 m/s), 100 ft/s (30 m/s) and 150 ft/s (46 m/s),
while temperature contours are presented at 104 ˚F (40˚C), 122˚F (50˚C) and 140˚F
(60˚C).
B.
Data from Engine Alliance’s GP7200:
6-1-0
Page 1
Dec 01/14
@A380
The estimated efflux data are presented at ISA +15˚C (+59˚F), Sea Level Static with 20 kt
headwind. It also assumed ground plane and proximity effects. Velocity contours are presented
at 35 mph (16 m/s), 65 mph (29 m/s) and 105 mph (47 m/s), while temperature contours are
presented at 122˚F (50˚C), 212˚F (100˚C) and 392˚F (200˚C). Engine Alliance strongly
recommends that jet blast studies using their contours include the effect of a 20 kt headwind.
6-1-0
Page 2
Dec 01/14
@A380
6-1-1
**ON A/C A380-800
1.
This section gives engine exhaust velocities at ground idle power.
6-1-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
m
ft
60
150 ft/sec
(46 m/sec)
15
100 ft/sec
(30 m/sec)
50 ft/sec
(15 m/sec)
40
10
5
20
0
ELEVATION
10
METERS 0
FEET 0
m
15
15
15
20
30
20
40
60
80
100
40
120
140
60
50
160
180
200
220
ft
60
150 ft/sec
(46 m/sec)
100 ft/sec
(30 m/sec)
50 ft/sec
(15 m/sec)
60
60
15
60
15
40
10
5
20
deh0002317
0
PLAN
L_AC_060101_1_0010101_01_00
Engine Exhaust Velocities
Ground Idle Power - TRENT 900 Engines
FIGURE-6-1-1-991-001-A01
6-1-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
FEET
(METERS)
140
(43)
105 MPH
(169 km/h)
70
(21)
0
65 MPH
(105 km/h)
ELEVATION
35 MPH
(56 km/h)
GROUND PLANE
FEET
FEET
(METERS)
140
0
150
300
0
(METERS)
(46)
(91)
105 MPH
(169 km/h)
65 MPH
(105 km/h)
35 MPH
(56 km/h)
70
(21)
0
CL AIRPLANE
E−00224 (0207)
PW V
PLAN
NOTE:
ALL VELOCITY VALUES ARE IN STATUE MILES PER HOUR.
CONVERSION FACTOR
1 MPH = 1.6 km/h
DANGER (KEEP OUT) ZONES
35 MPH
L_AC_060101_1_0020101_01_01
Ground Idle Power - GP 7200 Engines
FIGURE-6-1-1-991-002-A01
6-1-1
Page 3
Dec 01/14
@A380
6-1-2
**ON A/C A380-800
1.
This section gives engine exhaust temperatures at ground idle power.
6-1-2
Page 1
Dec 01/14
@A380
**ON A/C A380-800
m
GROUND IDLE POWER
ft
60
140°F
(60°C)
15
122°F
(50°C)
104°F
(40°C)
40
10
5
20
0
ELEVATION
METERS 0
FEET 0
m
35
30
25
20
10
20
40
40
30
80
60
100
120
122°F
(50°C)
104°F
(40°C)
140
50
160
ft
120
100
140°F
(60°C)
80
20
60
15
40
10
5
20
deh0002316
0
PLAN
L_AC_060102_1_0010101_01_01
Engine Exhaust Temperatures
FIGURE-6-1-2-991-001-A01
6-1-2
Page 2
Dec 01/14
@A380
**ON A/C A380-800
FEET
(METERS)
105
(32)
70
(21)
392°F (200°C)
212°F (100°C)
35
(11)
0
122°F (50°C)
ELEVATION
GROUND PLANE
FEET
0
75
150
225
0
(METERS)
(23)
(46)
(69)
392°F (200°C)
105
(32)
212°F (100°C)
122°F (50°C)
70
(21)
35
(11)
0
E−00226 (0207)
PW V
PLAN
CL AIRPLANE
NOTE: ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).
L_AC_060102_1_0020101_01_01
FIGURE-6-1-2-991-002-A01
6-1-2
Page 3
Dec 01/14
@A380
6-1-3
**ON A/C A380-800
1.
This section gives engine exhaust velocities at breakaway power.
6-1-3
Page 1
Dec 01/14
@A380
**ON A/C A380-800
m
ft
60
100 ft/sec
(30 m/sec)
150 ft/sec
(46 m/sec)
50 ft/sec
(15 m/sec)
15
10
5
40
20
0
ELEVATION
METERS 0
FEET 0
m ft
35 120
20
40
40
80
120
150 ft/sec
(46 m/sec)
160
100 ft/sec
(30 m/sec)
200
100
80
60
240
280
320
360
50 ft/sec
(15 m/sec)
30 100
25 80
20
60
15
10
40
5 20
0
deh0002319
PLAN
L_AC_060103_1_0010101_01_00
Breakaway Power - TRENT 900 Engines
FIGURE-6-1-3-991-001-A01
6-1-3
Page 2
Dec 01/14
@A380
**ON A/C A380-800
FEET
(METERS)
140
(43)
105 MPH
(169 km/h)
65 MPH
(105 km/h)
70
(21)
0
ELEVATION
35 MPH
(56 km/h)
GROUND PLANE
FEET
0
150
300
450
0
(46)
(91)
(137)
(METERS)
FEET
105 MPH
(169 km/h)
140
(43)
65 MPH
(105 km/h)
35 MPH
(56 km/h)
70
(21)
E−02200 (0207)
PW V
0
CL AIRPLANE
PLAN
NOTE: ALL VELOCITY VALUES ARE IN STATUE MILES PER HOUR.
CONVERSION FACTOR
1 MPH = 1.6 km/h
35 MPH
L_AC_060103_1_0020101_01_01
Breakaway Power - GP 7200 Engines
FIGURE-6-1-3-991-002-A01
6-1-3
Page 3
Dec 01/14
@A380
6-1-4
**ON A/C A380-800
1.
This section gives engine exhaust temperatures at breakaway power.
6-1-4
Page 1
Dec 01/14
@A380
**ON A/C A380-800
m
BREAKAWAY POWER
(11% MAX TAKE−OFF THRUST)
ft
60
140°F 122°F 104°F
(60°C) (50°C) (40°C)
15
40
10
5
20
0
ELEVATION
m
35
METERS
0
FEET
0
20
10
20
40
60
80
100
40
50
140
120
160
180
ft
120
140°F 122°F
(60°C) (50°C)
30 100
25
30
104°F
(40°C)
80
20
60
15
40
10
5
20
deh0002318
0
PLAN
L_AC_060104_1_0010101_01_01
FIGURE-6-1-4-991-001-A01
6-1-4
Page 2
Dec 01/14
@A380
**ON A/C A380-800
E−02201 (0805)
PW V
FEET
(METERS)
392°F (200°C)
105
(32)
212°F (100°C)
122°F (50°C)
70
(21)
35
(11)
0
ELEVATION
GROUND PLANE
FEET
0
75
150
225
0
(METERS)
(23)
(46)
(69)
392°F (200°C)
105
(32)
212°F (100°C)
70
(21)
122°F (50°C)
35
(11)
0
PLAN
CL AIRPLANE
NOTE : ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).
L_AC_060104_1_0020101_01_00
FIGURE-6-1-4-991-002-A01
6-1-4
Page 3
Dec 01/14
@A380
6-1-5
**ON A/C A380-800
1.
This section gives engine exhaust velocities at max take-off power.
6-1-5
Page 1
Dec 01/14
@A380
**ON A/C A380-800
m
20
10
150 ft/sec
(46 m/sec)
ft
80
100 ft/sec
(30 m/sec)
TO
1800 ft
(540 m)
50 ft/sec
(15 m/sec)
40
0
ELEVATION
METERS 0
FEET
m
ft
60 160
40
120
30
80
20
10 40
20
40
100
60
200
80
100
300
150 ft/sec
(46 m/sec)
120
140
400
160
600
500
100 ft/sec
(30 m/sec)
200
180
220
700
50 ft/sec
(15 m/sec)
240
800
TO
1800 ft
(540 m)
0
deh0002315
PLAN
L_AC_060105_1_0010101_01_00
Max. Take-Off Power - TRENT 900 Engines
FIGURE-6-1-5-991-001-A01
6-1-5
Page 2
Dec 01/14
@A380
**ON A/C A380-800
105 MPH
OUT TO
724 ft
(221 m)
FEET
(METERS)
140
(43)
65 MPH
OUT TO
1090 ft
(332 m)
35 MPH
OUT TO
1553 ft
(473 m)
70
(21)
0
ELEVATION
FEET
GROUND PLANE
0
150
300
450
600
0
(METERS)
(46)
(91)
(137)
(183)
105 MPH
OUT TO
724 ft
(221 m)
FEET
(METERS)
65 MPH
OUT TO
1090 ft
(332 m)
35 MPH
OUT TO
1553 ft
(473 m)
140
(43)
70
(21)
E−00225 (0207)
PW V
0
CL AIRPLANE
PLAN
NOTE: ALL VELOCITY VALUES ARE IN STATUE MILES PER HOUR.
CONVERSION FACTOR
1 MPH = 1.6 km/h
35 MPH
L_AC_060105_1_0020101_01_01
Max. Take-Off Power - GP 7200 Engines
FIGURE-6-1-5-991-002-A01
6-1-5
Page 3
Dec 01/14
@A380
6-1-6
**ON A/C A380-800
1.
This section gives engine exhaust temperatures at max take-off power.
6-1-6
Page 1
Dec 01/14
@A380
**ON A/C A380-800
MAX TAKE−OFF POWER
ft
60
m
15
140°F
(60 C)
104°F
(40 C)
122°F
(50 C)
TO
540 ft
(162 m)
40
10
20
5
0
ELEVATION
METERS 0
FEET 0
ft
35 120
m
40
20
40
80
120
60
200
160
140°F
(60 C)
240
122°F
(50 C)
104°F
(40 C)
120
100
80
280
320
360
400
TO
540 ft
(162 m)
30 100
25
20
15
10
5
80
60
40
20
0
deh0002314
PLAN
L_AC_060106_1_0010101_01_01
Max Take-Off Power - TRENT 900 Engines
FIGURE-6-1-6-991-001-A01
6-1-6
Page 2
Dec 01/14
@A380
**ON A/C A380-800
E−00227 (0704)
PW V
FEET
(METERS)
105
(32)
392°F (200°C)
212°F (100°C)
70
(21)
122°F (50°C)
35
(11)
0
ELEVATION
FEET
0
0
(METERS)
GROUND PLANE
75
150
225
(23)
(46)
(69)
392°F (200°C)
212°F (100°C)
105
(32)
122°F (50°C)
70
(21)
35
(11)
0
PLAN
CL AIRPLANE
NOTE : ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).
L_AC_060106_1_0020101_01_00
Max Take-Off Power - GP 7200 Engines
FIGURE-6-1-6-991-002-A01
6-1-6
Page 3
Dec 01/14
@A380
6-3-0
**ON A/C A380-800
1.
The intake suction danger areas, which are plotted in this chapter, correspond to very low suction
velocities in order to prevent very low density objects (hat, handkerchief) from ingestion by engines.
The primary aim of those danger areas is to protect the people working around the engines.
The A380 outer engines are high enough above ground to prevent the ingestion of typical loose
objects, which can be found on ground at the edge of runways/taxiways paved areas (loose gravels
for example), in the following conditions:
- at usual taxiway thrust (i.e. up to the breakaway power setting), even if the loose objects are
below the A380 outer engines.
- at usual take-off thrust (i.e. up to the maximum take-off power setting), if the loose objects are
beyond 3 meters from the A380 outer engines centreline.
6-3-0
Page 1
Dec 01/14
@A380
6-3-1
**ON A/C A380-800
1.
This section gives danger areas of the engines at ground idle power conditions.
6-3-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
4.5 m
(15 ft)
1.3 m
(4 ft 3 in)
30
TO 70 m (230 ft) AFT OF EXHAUST NOZZLES
deh0001513
INTAKE SUCTION DANGER AREA MINIMUM IDLE POWER
EXHAUST DANGER AREA
ENTRY CORRIDOR
L_AC_060301_1_0010101_01_00
FIGURE-6-3-1-991-001-A01
6-3-1
Page 2
Dec 01/14
@A380
**ON A/C A380-800
15 ft
(4.6 m)
A
A
A
5 ft
(1.5 m)
A
B
B
C
C
C
C
33°
E−02197 (0207)
PW V
AREA A − INTAKE SUCTION DANGER AREA
AREA B − ENTRY CORRIDOR
AREA C − EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE)
277 ft (84 m) − GROUND IDLE (20 kt HEADWIND)
L_AC_060301_1_0020101_01_01
FIGURE-6-3-1-991-002-A01
6-3-1
Page 3
Dec 01/14
@A380
6-3-2
**ON A/C A380-800
1.
This section gives danger areas of the engines at max take-off power conditions.
6-3-2
Page 1
Dec 01/14
@A380
**ON A/C A380-800
8.9 m
(29 ft)
30
TO 548.6 m (1800 ft) AFT OF EXHAUST NOZZLES
deh0001515
INTAKE SUCTION DANGER AREA MAX TAKE−OFF POWER
EXHAUST DANGER AREA
L_AC_060302_1_0010101_01_00
Max Take-Off Power - TRENT 900 Engines
FIGURE-6-3-2-991-001-A01
6-3-2
Page 2
Dec 01/14
@A380
**ON A/C A380-800
32 ft
(9.8 m)
A
11 ft
(3.4 m)
A
B
B
C
C
41°
E−02199 (0207)
PW V
1553 ft (473 m) − MAXIMUM TAKEOFF (20 kt HEADWIND)
L_AC_060302_1_0020101_01_01
Max Take-Off Power - GP 7200 Engines
FIGURE-6-3-2-991-002-A01
6-3-2
Page 3
Dec 01/14
@A380
6-3-3
**ON A/C A380-800
1.
This section gives danger areas of the engines at breakaway power.
6-3-3
Page 1
Dec 01/14
@A380
**ON A/C A380-800
6.0 m
4 ENGINE BREAKAWAY (20 ft)
30
TO 123.4 m (405 ft) AFT OF EXHAUST NOZZLES
deh0001514
INTAKE SUCTION DANGER AREA BREAKAWAY POWER
EXHAUST DANGER AREA
L_AC_060303_1_0010101_01_00
FIGURE-6-3-3-991-001-A01
6-3-3
Page 2
Dec 01/14
@A380
**ON A/C A380-800
20 ft
(6.10 m)
A
A
6.5 ft
(1.98 m)
A
A
B
B
C
C
38°
E−02198 (0207)
PW V
415 ft (126 m) − BREAKAWAY (20 kt HEADWIND)
L_AC_060303_1_0020101_01_01
FIGURE-6-3-3-991-002-A01
6-3-3
Page 3
Dec 01/14
@A380
6-4-1
**ON A/C A380-800
APU Exhaust Velocities and Temperatures - ECS Conditions
1.
This section provides APU exhaust velocities and temperatures in max. ECS conditions.
6-4-1
Page 1
Dec 01/14
@A380
**ON A/C A380-800
DISTANCE FROM AIRCRAFT CENTERLINE
6
0
10
20
40
50
60
70
80
90
100
FEET
20
574 °C (1065 °F)
260 °C (500 °F)
3
10
149 °C (300 °F)
0
0
204 °C (400 °F)
−3
93 °C (200 °F)
−10
316 °C (600 °F)
−6
0
3
6
METERS
6
30
0
9
12
15
18
21
24
27
30
80
90
100
−20
DISTANCE DOWNSTREAM FROM NOZZLE
10
20
30
40
50
60
70
FEET
20
68 m/s (223 ft/s)
37 m/s (120 ft/s)
3
10
18 m/s (60 ft/s)
0
0
9 m/s (30 ft/s)
−3
−10
27 m/s (90 ft/s)
46 m/s (150 ft/s)
−6
0
3
6
9
12
15
18
21
24
METERS
NOTE: THE DATA GIVEN IS BASED ON THE FOLLOWING ASSUMPTIONS:
−SEA LEVEL STATIC CONDITIONS
−ISA + 23 °C (73 °F)
−NO WIND
27
30
−20
L_AC_060401_1_0010101_01_00
Max. ECS Conditions
FIGURE-6-4-1-991-001-A01
6-4-1
Page 2
Dec 01/14
@A380
6-4-2
**ON A/C A380-800
1.
This section gives the APU exhaust velocities and temperatures in MES conditions.
6-4-2
Page 1
Dec 01/14
@A380
**ON A/C A380-800
0
10
20
30
40
50
60
70
80
90
6
100 FEET
20
458 °C (857 °F)
260 °C (500 °F)
3
10
149 °C (300 °F)
0
0
−3
93 °C (200 °F)
204 °C (400 °F)
−10
316 °C (600 °F)
−6
0
3
6
9
METERS
6
0
12
15
18
21
−20
24
27
30
80
90
100 FEET
20
10
20
30
40
50
60
70
80 m/s (263 ft/s)
37 m/s (120 ft/s)
3
10
18 m/s (60 ft/s)
0
0
9 m/s (30 ft/s)
−3
−10
27 m/s (90 ft/s)
46 m/s (150 ft/s)
−6
0
METERS
3
6
9
12
15
18
21
24
27
30
−20
NOTE: THE DATA GIVEN IS BASED ON THE FOLLOWING ASSUMPTIONS:
−SEA LEVEL STATIC CONDITIONS
−ISA + 23 °C (73 °F)
−NO WIND
L_AC_060402_1_0010101_01_00
L_AC_060402_0_AAM0_01_00
MES Conditions
FIGURE-6-4-2-991-001-A01
6-4-2
Page 2
Dec 01/14
@A380
PAVEMENT DATA
7-1-0
General Information
**ON A/C A380-800
General Information
1.
General
A brief description of the pavement charts that follow will help in airport planning.
To aid in the interpolation between the discrete values shown, each aircraft configuration is shown
with a minimum range of five loads on the Main Landing Gear (MLG).
All curves on the charts represent data at a constant specified tire pressure with:
- The aircraft loaded to the Maximum Ramp Weight (MRW),
- The CG at its maximum permissible aft position.
Pavement requirements for commercial aircraft are derived from the static analysis of loads imposed
on the MLG struts.
Landing Gear Footprint:
Section 07-02-00 presents basic data on the landing gear footprint configuration, MRW and tire sizes
and pressures.
Maximum Pavement Loads:
Section 07-03-00 shows maximum vertical and horizontal pavement loads for certain critical
conditions at the tire-ground interfaces.
Landing Gear Loading on Pavement:
Section 07-04-00 contains charts to find these loads throughout the stability limits of the aircraft at
rest on the pavement.
These MLG loads are used as the point of entry to the pavement design charts which follow,
interpolating load values where necessary.
Flexible Pavement Requirements - US Army Corps of Engineers Design Method:
Section 07-05-00 uses procedures in Instruction Report No. S-77-1 ”Procedures for Development of
CBR Design Curves”, dated June 1977 and as modified according to the methods described in ICAO
Aerodrome Design Manual, Part 3. Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCN
Method), and utilizing the alpha factors approved by ICAO in October 2007.
The report was prepared by the ”U.S. Army Corps Engineers Waterways Experiment Station, Soils
and Pavement Laboratory, Vicksburg, Mississippi”.
The line showing 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).
7-1-0
Page 1
Dec 01/14
@A380
Flexible Pavement Requirements - LCN Conversion Method:
The flexible pavement charts in Section 07-06-00 show Load Classification Number (LCN) against
Equivalent Single Wheel Load (ESWL), and ESWL against pavement thickness.
All the LCN curves shown in the ’Flexible Pavement Requirements’ were developed from a computer
program based on data in International Civil Aviation Organization (ICAO) document 7920AN/865/2, Aerodrome Manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.
Rigid Pavement Requirements - PCA (Portland Cement Association) Design Method:
Section 07-07-00 gives the rigid pavement design curves that have been prepared with the use of the
Westergaard Equation.
This is in general accordance with the procedures outlined in the Portland Cement Association
publications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for Airport
Pavement Design” (Program PDILB), 1967 both by Robert G. Packard.
Rigid Pavement Requirements - LCN Conversion:
Section 07-08-00 gives data about the rigid pavement requirements for the LCN conversion:
- For the radius of relative stiffness,
- For the radius of relative stiffness (other values of E and µ).
All the LCN curves shown in Rigid Pavement Requirements - LCN conversion were developed from a
computer program based on data in International Civil Aviation Organization (ICAO) document 7920AN/865/2, Aerodrome Manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.
Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness:
The rigid pavement charts show LCN against ESWL, and ESWL against radius of relative stiffness.
Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness (other values of E and
µ):
The rigid pavement charts show LCN against ESWL, and ESWL against radius of relative stiffness
affected by the other values of E and µ.
ACN/PCN Reporting System:
Section 07-09-00 provides ACN data prepared according to the ACN/PCN system as referenced in
ICAO Annex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations” Fourth Edition, July
2004, incorporating Amendments 1 to 6.
The ACN/PCN system provides a standardized international aircraft/pavement rating system
replacing the various S, T, TT, LCN, AUW, ISWL, etc., rating systems used throughout the world.
ACN is the Aircraft Classification Number and PCN is the corresponding Pavement Classification
Number.
An aircraft having an ACN less than or equal to the PCN can operate without restriction on the
pavement.
Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.
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.
7-1-0
Page 2
Dec 01/14
@A380
Computationally the ACN/PCN system uses PCA program PDILB for rigid pavements and S-77-1 for
flexible pavements to calculate ACN values.
The Airport Authority must decide on the method of pavement analysis and the results of their
evaluation shown as follows:
PCN
PAVEMENT TYPE
SUBGRADE
TIRE PRESSURE
EVALUATION
CATEGORY
CATEGORY
METHOD
R - Rigid
A - High
W - No pressure limit
T - Technical
F - Flexible
B - Medium
X - High pressure limited U - Using Aircraft
to 1.75 MPa (254 psi)
Y - Medium pressure
C - Low
limited to 1.25 MPa (181
psi)
D - Ultra Low
Z - Low pressure limited
to 0.5 MPa (73 psi)
For flexible pavements, the four subgrade categories are:
-
A. High Strength
B. Medium Strength
C. Low Strength
D. Ultra Low Strength
CBR
CBR
CBR
CBR
15
10
6
3
For rigid pavements, the four subgrade categories are:
- A. High Strength Subgrade k
=
- B. Medium Strength Subgrade k =
- C. Low Strength Subgrade k
=
- D. Ultra Low Strength Subgrade =
k
150 MN/m3 (550 pci)
80 MN/m3 (300 pci)
40 MN/m3 (150 pci)
20 MN/m3 (75 pci)
7-1-0
Page 3
Dec 01/14
@A380
7-2-0
**ON A/C A380-800
1.
This section provides data about the landing gear footprint in relation with the aircraft Maximum
Ramp Weight (MRW) and tire sizes and pressures.
The landing gear footprint information is given for all the aircraft operational weight variants.
7-2-0
Page 1
Dec 01/14
1.050 m
(3.445 ft)
NOSE LANDING
GEAR
7-2-0
31.881 m
(104.596 ft)
28.605 m
(93.848 ft)
1.700 m
(5.577 ft)
12.456 m
(40.866 ft)
1.350 m
(4.429 ft)
1.530 m
(5.020 ft)
1.700 m
(5.577 ft)
WING LANDING
GEAR
1.550 m
(5.085 ft)
5.264 m
(17.270 ft)
1.530 m
(5.020 ft)
1.700 m
(5.577 ft)
BODY LANDING
GEAR
@A380
**ON A/C A380-800
L_AC_070200_1_0030101_01_01
(Sheet 1 of 2)
FIGURE-7-2-0-991-003-A01
Page 2
Dec 01/14
7-2-0
WV009
512 000 kg
(1 128 775 lb)
492 000 kg
(1 084 675 lb)
577 000 kg
WV008
(1 272 075 lb)
95.1%
1 270x455 R22 32PR
OR 50x20 R22 34PR
14.1 bar
(205 psi)
1 400x530 R23 40PR
1 400x530 R23 40PR
14.1 bar
(205 psi)
1 270x455 R22 32PR
OR 50x20 R22 34PR
1 400x530 R23 40PR
14.1 bar
(205 psi)
94.3%
1270x455 R22 32PR
OR 50x20 R22 34PR
1 400x530 R23 40PR
14.1 bar
(205 psi)
1 400x530 R23 40PR
94.3%
575 000 kg
(1 267 650 lb)
WV006
1 270x455 R22 32PR
OR 50x20 R22 34PR
1 400x530 R23 40PR
14.1 bar
(205 psi)
1 400x530 R23 40PR
14.1 bar
(205 psi)
14.1 bar
(205 psi)
95.1%
562 000 kg
(1 239 000 lb)
WV005
1 270x455 R22 32PR
OR 50x20 R22 34PR
1 400x530 R23 40PR
14.1 bar
(205 psi)
1 270x455 R22 32PR
OR 50x20 R22 34PR
95.1%
562 000 kg
(1 239 000 lb)
WV004
1 270x455 R22 32PR
OR 50x20 R22 34PR
1 270x455 R22 32PR
OR 50x20 R22 34PR
95.1%
95.1%
512 000 kg
(1 128 775 lb)
WV003
WV007
94.3%
571 000 kg
(1 258 850 lb)
WV002
14 bar
(203 psi)
15 bar
(218 psi)
14 bar
(203 psi)
15 bar
(218 psi)
15 bar
(218 psi)
15 bar
(218 psi)
14 bar
(203 psi)
15 bar
(218 psi)
1 400x530 R23 40PR
1 400x530 R23 40PR
1 400x530 R23 40PR
1 400x530 R23 40PR
1 400x530 R23 40PR
1 400x530 R23 40PR
1 400x530 R23 40PR
1 400x530 R23 40PR
14 bar
(203 psi)
15 bar
(218 psi)
14 bar
(203 psi)
15 bar
(218 psi)
15 bar
(218 psi)
15 bar
(218 psi)
14 bar
(203 psi)
15 bar
(218 psi)
PERCENTAGE
NOSE
WING
BODY
OF WEIGHT
NOSE GEAR
WING GEAR
BODY GEAR
WEIGHT MAXIMUM
RAMP
GEAR TIRE
GEAR TIRE
GEAR TIRE
ON MAIN
TIRE SIZE
TIRE SIZE
TIRE SIZE
VARIANT WEIGHT
PRESSURE
PRESSURE
PRESSURE
GEAR GROUP
562 000 kg
15 bar
15 bar
1 270x455 R22 32PR 14.1 bar
95.1%
1 400x530 R23 40PR
1 400x530 R23 40PR
WV000
(1 239 000 lb)
(218 psi)
(218 psi)
OR 50x20 R22 34PR (205 psi)
14 bar
14 bar
512 000 kg
1 270x455 R22 32PR 14.1 bar
95.1%
1 400x530 R23 40PR
1 400x530 R23 40PR
WV001
(203 psi)
(203 psi)
(1 128 775 lb)
OR 50x20 R22 34PR (205 psi)
@A380
**ON A/C A380-800
L_AC_070200_1_0030102_01_01
(Sheet 2 of 2)
FIGURE-7-2-0-991-003-A01
Page 3
Dec 01/14
@A380
7-3-0
**ON A/C A380-800
1.
This section provides maximum vertical and horizontal pavement loads for some critical conditions at
the tire-ground interfaces.
The maximum pavement loads are given for all the operational weight variants of the aircraft.
7-3-0
Page 1
Dec 01/14
7-3-0
66 730 kg
(147 125 lb)
512 000 kg 39 760 kg 35.81 %
MAC
(1 128 775 lb) (87 675 lb) (a)
WV003
NOTE:
(a) LOADS CALCULATED USING AIRCRAFT AT MRW
(b) BRAKED WING GEAR
(c) BRAKED BODY GEAR
69 850 kg
(154 000 lb)
571 000 kg 39 780 kg 37.8 %
MAC
(1 258 850 lb) (87 700 lb) (a)
WV002
66 730 kg
(147 125 lb)
512 000 kg 39 760 kg 35.81 %
MAC
(1 128 775 lb) (87 675 lb) (a)
WV001
STATIC
BRAKING
AT 10 ft/s²
DECELERATION
69 430 kg
(153 075 lb)
STATIC LOAD
AT
MOST FWD CG
562 000 kg 39 830 kg 37.5 %
MAC
(1 239 000 lb) (87 800 lb) (a)
MAXIMUM
RAMP
WEIGHT
WEIGHT
VARIANT
WV000
2
1
H
STATIC LOAD
AT
MAX AFT CG
97 410 kg 43 % 146 110 kg 43 %
MAC
MAC
(214 750 lb) (a) (322 125 lb) (a)
107 720 kg 41 % 161 570 kg 41 %
MAC
MAC
(237 475 lb) (a) (356 200 lb) (a)
97 410 kg 43 % 146 110 kg 43 %
MAC
MAC
(214 750 lb) (a) (322 125 lb) (a)
106 920 kg 43 % 160 380 kg 43 %
MAC
MAC
(235 725 lb) (a) (353 575 lb) (a)
STATIC LOAD
AT
MAX AFT CG
STEADY
BRAKING
AT 10 ft/s²
DECELERATION
34 930 kg (b)
(77 025 lb)
52 400 kg (c)
(115 525 lb)
31 830 kg (b)
(70 175 lb)
47 740 kg (c)
(105 250 lb)
35 490 kg (b)
(78 250 lb)
53 240 kg (c)
(117 375 lb)
31 830 kg (b)
(70 175 lb)
47 740 kg (c)
(105 250 lb)
AT
INSTANTANEOUS
BRAKING
COEFFICIENT = 0.8
85 540 kg
(b)
(188 575 lb)
128 310 kg
(c)
(282 875 lb)
77 930 kg
(b)
(171 800 lb)
116 890 kg
(c)
(257 700 lb)
86 170 kg
(b)
(189 975 lb)
129 260 kg
(c)
(284 975 lb)
77 930 kg
(b)
(171 800 lb)
116 890 kg
(c)
(257 700 lb)
V(WG) V (BG)
V(NG) MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST FWD CG
V(WG) MAXIMUM VERTICAL WING GEAR GROUND LOAD AT MAX AFT CG
V(BG) MAXIMUM VERTICAL BODY GEAR GROUND LOAD AT MAX AFT CG
H
MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING
3
4
5
6
7
V(BG)
V(WG)
V (NG)
H (PER STRUT)
(PER STRUT)
(PER STRUT)
V(NG)
@A380
**ON A/C A380-800
L_AC_070300_1_0060101_01_00
(Sheet 1 of 2)
FIGURE-7-3-0-991-006-A01
Page 2
Dec 01/14
7-3-0
69 430 kg
(153 075 lb)
70 340 kg
(155 075 lb)
65 610 kg
(144 650 lb)
70 590 kg
(155 625 lb)
66 690 kg
(147 025 lb)
562 000 kg 39 830 kg 37.5 %
MAC
(1 239 000 lb) (87 800 lb) (a)
575 000 kg 40 050 kg 37.8 %
MAC
(1 267 650 lb) (88 300 lb) (a)
492 000 kg 39 700 kg 35.06 %
MAC
(1 084 675 lb) (87 525 lb) (a)
577 000 kg 40 190 kg 37.8 %
MAC
(1 272 075 lb) (88 600 lb) (a)
512 000 kg 39 720 kg 35.83 %
MAC
(1 128 775 lb) (87 575 lb) (a)
WV005
WV006
WV007
WV008
NOTE:
(a) LOADS CALCULATED USING AIRCRAFT AT MRW
(b) BRAKED WING GEAR
(c) BRAKED BODY GEAR
WV009
69 430 kg
(153 075 lb)
562 000 kg 39 830 kg 37.5 %
MAC
(1 239 000 lb) (87 800 lb) (a)
STATIC
BRAKING
AT 10 ft/s²
DECELERATION
4
WV004
STATIC LOAD
AT
MOST FWD CG
MAXIMUM
RAMP
WEIGHT
WEIGHT
VARIANT
V (NG)
3
2
1
STATIC LOAD
AT
MAX AFT CG
6
V(BG)
(PER STRUT)
97 410 kg 43 % 146 110 kg 43 %
MAC
MAC
(214 750 lb) (a) (322 125 lb) (a)
108 850 kg 41 % 163 270 kg 41 %
MAC
MAC
(239 975 lb) (a) (359 950 lb) (a)
93 600 kg 43 % 140 410 kg 43 %
MAC
MAC
(206 350 lb) (a) (309 550 lb) (a)
108 470 kg 41 % 162 700 kg 41 %
MAC
MAC
(239 125 lb) (a) (358 700 lb) (a)
106 920 kg 43 % 160 380 kg 43 %
MAC
MAC
(235 725 lb) (a) (353 575 lb) (a)
106 920 kg 43 % 160 380 kg 43 %
MAC
MAC
(235 725 lb) (a) (353 575 lb) (a)
STATIC LOAD
AT
MAX AFT CG
5
V(WG)
(PER STRUT)
STEADY
BRAKING
AT 10 ft/s²
DECELERATION
34 930 kg (b)
(77 025 lb)
52 400 kg (c)
(115 525 lb)
34 930 kg (b)
(77 025 lb)
52 400 kg (c)
(115 525 lb)
35 740 kg (b)
(78 800 lb)
53 610 kg (c)
(118 200 lb)
30 580 kg (b)
(67 425 lb)
45 880kg (c)
(101 150 lb)
35 870 kg (b)
(79 075 lb)
53 800 kg (c)
(118 600 lb)
31 830 kg (b)
(70 175 lb)
47 740 kg (c)
(105 250 lb)
AT
INSTANTANEOUS
BRAKING
COEFFICIENT = 0.8
85 540 kg
(b)
(188 575 lb)
128 310 kg
(c)
(282 875 lb)
85 540 kg
(b)
(188 575 lb)
128 310 kg
(c)
(282 875 lb)
86 780 kg
(b)
(191 300 lb)
130 160 kg
(c)
(286 950 lb)
74 880 kg
(b)
(165 100 lb)
112 320 kg
(c)
(247 625 lb)
87 080 kg
(b)
(191 975 lb)
130 620 kg
(c)
(287 950 lb)
77 930 kg
(b)
(171 800 lb)
116 890 kg
(c)
(257 700 lb)
H (PER STRUT)
7
@A380
**ON A/C A380-800
L_AC_070300_1_0060102_01_01
(Sheet 2 of 2)
FIGURE-7-3-0-991-006-A01
Page 3
Dec 01/14
@A380
7-4-0
**ON A/C A380-800
1.
This section gives data about landing gear loading on pavement.
The MLG loading on pavement graphs are given for the weight variants that produce (at the MRW
and max aft CG) the lowest MLG load and the highest MLG load for each type of aircraft.
2.
MLG Loading on Pavement
Example, see FIGURE 7-4-0-991-001-A (sheet 1), calculation of the total weight on the MLG for:
- An aircraft with a MRW of 492 000 kg (1 084 675 lb),
- The aircraft gross weight is 420 000 kg (925 950 lb).
- A percentage of weight on the MLG of 95.1% (percentage of weight on the MLG at MRW and
max aft CG).
The total weight on the MLG group is 399 530 kg (880 800 lb).
3.
Wing Gear and Body Gear Loading on Pavement
The MLG group consists of two wing gears (4-wheel bogies) plus two body gears (6-wheel bogies).
Example, see FIGURE 7-4-0-991-001-A (sheet 2), calculation of the total weight on the MLG for:
- The aircraft gross weight is 420 000 kg (925 950 lb).
The load on the two wing gears is 159 810 kg (352 325 lb) and the load on the two body gears is
239 720 kg (528 475 lb).
The total weight on the MLG group is 399 530 kg (880 800 lb).
NOTE : The CG in the figure title is the CG used for ACN/LCN calculation.
7-4-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
PERCENTAGE MAC
40
45
50
55
CG FOR ACN/LCN
CALCULATION
43% MAC
MTOW − 490 000 kg
35.06% MAC
MLW
MZFW
TAKE OFF
LANDING
88
90
92
94
96
98
100
600
590
580
570
560
550
540
530
520
510
500
490
480
470
460
450
440
430
420
410
400
390
380
370
360
350
340
330
320
310
300
290
280
270
260
1 300
1 250
1 200
1 150
1 100
1 050
1 000
950
900
850
(x 1 000 lb)
35
(x 1 000 kg)
WEIGHT ON MAIN LANDING GEAR (x 1 000 kg)
30
600
590
580
570
560
550
540
530
520
510
500
490
480
470
460
450
440
430
420
410
400
390
380
370
360
350
340
330
320
310
300
290
280
270
260
800
750
700
650
600
PERCENTAGE OF WEIGHT ON MAIN GEAR
L_AC_070400_1_0010101_01_00
WV007, MRW 492 000 kg, CG 43% (Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-7-4-0-991-001-A01
7-4-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
400
500
600
540
400
380
100
120
140
160
180
200
220
240
260
280
300
320
340
260
600
280
300
320
340
BODY GEARS
360
800
700
AIRCRAFT GROSS WEIGHT (x 1 000 kg)
520
460
420
440
1 000
900
(x 1 000 lb)
480
500
1 100
1 200
WING GEARS
560
580
1 300
600
700
300
(x 1 000 lb)
LOAD ON CENTER GEARS OR LOAD ON WING GEARS (x 1 000 kg)
L_AC_070400_1_0010102_01_00
WV007, MRW 492 000 kg, CG 43 % (Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-7-4-0-991-001-A01
7-4-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
PERCENTAGE MAC
40
45
50
55
CG FOR ACN/LCN
CALCULATION
MTOW − 575 000 kg
41% MAC
37.8% MAC
MLW
MZFW
TAKE OFF
LANDING
88
90
92
94
96
98
100
600
590
580
570
560
550
540
530
520
510
500
490
480
470
460
450
440
430
420
410
400
390
380
370
360
350
340
330
320
310
300
290
280
270
260
1 300
1 250
1 200
1 150
1 100
1 050
1 000
950
900
850
(x 1 000 lb)
35
(x 1 000 kg)
WEIGHT ON MAIN LANDING GEAR (x 1 000 kg)
30
600
590
580
570
560
550
540
530
520
510
500
490
480
470
460
450
440
430
420
410
400
390
380
370
360
350
340
330
320
310
300
290
280
270
260
800
750
700
650
600
PERCENTAGE OF WEIGHT ON MAIN GEAR
L_AC_070400_1_0020101_01_00
WV008, MRW 577 000 kg CG 41% (Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-7-4-0-991-002-A01
7-4-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
400
500
600
580
560
AIRCRAFT GROSS WEIGHT (x 1 000 kg)
460
100
120
140
160
180
200
220
240
260
280
300
320
340
260
600
280
300
700
320
340
360
380
BODY GEARS
400
420
440
1 000
900
800
(x 1 000 lb)
480
500
1 100
520
540
1 200
WING GEARS
1 300
600
700
300
(x 1 000 lb)
LOAD ON CENTER GEARS OR LOAD ON WING GEARS (x 1 000 kg)
L_AC_070400_1_0020102_01_00
WV008, MRW 577 000 kg, CG 41% (Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-7-4-0-991-002-A01
7-4-0
Page 5
Dec 01/14
@A380
7-5-0
**ON A/C A380-800
1.
This section gives data about the flexible pavement requirements.
The flexible pavement requirements graphs are given at standard tire pressure for the weight variants
that produce (at the MRW and max aft CG) the lowest MLG and the highest MLG load of each type
of aircraft.
They are calculated with the US Army Corps of Engineers Design Method.
To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annual
departure level and the weight on one MLG.
The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).
The procedure that follows is used to develop flexible pavement design curves:
- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random
line is made to show 10 000 coverages,
- A plot is then made of the incremental values of the weight on the MLG,
- Annual departure lines are made based on the load lines of the weight on the MLG that is shown
on the graph.
Example, see FIGURE 7-5-0-991-001-A (Sheet 1), calculation of the thickness of the flexible
pavement for Wing Landing Gear:
- A ”CBR” value of 10,
- An annual departure level of 3 000,
- The load on one WLG of 75 000 kg (165 350 lb).
The required flexible pavement thickness is 58.5 cm (23 in).
Example, see FIGURE 7-5-0-991-001-A (Sheet 2), calculation of the thickness of the flexible
pavement for Body Landing Gear:
- An aircraft with a Maximum Ramp Weight (MRW) of 492 000 kg (1 084 675 lb),
- A ”CBR” value of 10,
- An annual departure level of 3 000,
- The load on one BLG of 125 000 kg (275 575 lb).
The required flexible pavement thickness is 61.1 cm (24 in).
NOTE : The CG in the figure title is the CG used for ACN calculation.
7-5-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
SUBGRADE STRENGTH − CBR
3
6
10
15
20
30
40
60
80
WEIGHT ON ONE WING LANDING GEAR
93 600 kg (206 350 lb)
75 000 kg (165 350 lb)
60 000 kg (132 275 lb)
45 000 kg (99 200 lb)
30 000 kg (66 150 lb)
MAXIMUM POSSIBLE WING
LANDING GEAR LOAD AT
MAXIMUM RAMP WEIGHT
AND AFT CG
10 000 COVERAGES USED
FOR ACN CALCULATIONS
ALPHA FACTOR = 0.8
ANNUAL DEPARTURES*
1 200
3 000
6 000
15 000
25 000
*20 YEAR PAVEMENT LIFE
3
10
6
10
15
20
15
(in)
30
40
(cm)
20
30
60
80
40
60
80
100 120 150 180
FLEXIBLE PAVEMENT THICKNESS
1 400 x 530 R23 40PR TIRES
TIRE PRESSURE CONSTANT AT 14 bar (203 psi)
L_AC_070500_1_0010101_01_00
Flexible Pavement Requirements
WV007, MRW 492 000 kg, CG 43 % - Wing Landing Gear (Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-7-5-0-991-001-A01
7-5-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
3
6
10
15
20
30
40
60
80
WEIGHT ON ONE BODY LANDING GEAR
140 410 kg (309 550 lb)
125 000 kg (275 575 lb)
110 000 kg (242 500 lb)
95 000 kg (209 450 lb)
80 000 kg (176 375 lb)
MAXIMUM POSSIBLE BODY
MAXIMUM RAMP WEIGHT
AND AFT CG
ALPHA FACTOR = 0.72
ANNUAL DEPARTURES*
1 200
3 000
6 000
15 000
25 000
3
10
6
10
15
20
15
(in)
30
40
(cm)
20
30
60
80
40
60
80
100 120 150 180
1 400 x 530 R23 40PR TIRES
L_AC_070500_1_0010102_01_00
WV007, MRW 492 000 kg, CG 43 % - Body Landing Gear (Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-7-5-0-991-001-A01
7-5-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
3
6
10
15
20
30
40
60
80
108 850 kg (239 975 lb)
85 000 kg (187 400 lb)
70 000 kg (154 325 lb)
55 000 kg (121 250 lb)
40 000 kg (88 175 lb)
MAXIMUM RAMP WEIGHT
AND AFT CG
ALPHA FACTOR = 0.8
ANNUAL DEPARTURES*
1 200
3 000
6 000
15 000
25 000
3
10
6
10
15
20
15
(in)
30
40
(cm)
20
30
60
80
40
60
80
100 120 150 180
1 400 x 530 R23 40PR TIRES
L_AC_070500_1_0020101_01_00
WV008, MRW 577 000 kg, CG 41 % - Wing Landing Gear (Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-7-5-0-991-002-A01
7-5-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
3
6
10
15
20
30
40
60
80
163 270 kg (359 950 lb)
145 000 kg (319 675 lb)
130 000 kg (286 600 lb)
115 000 kg (253 525 lb)
100 000 kg (220 450 lb)
MAXIMUM RAMP WEIGHT
AND AFT CG
ALPHA FACTOR = 0.72
ANNUAL DEPARTURES*
1 200
3 000
6 000
15 000
25 000
3
10
6
10
15
20
15
(in)
30
40
(cm)
20
30
60
80
40
60
80
100 120 150 180
1 400 x 530 R23 40PR TIRES
L_AC_070500_1_0020102_01_00
WV008, MRW 577 000 kg, CG 41 % - Body Landing Gear (Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-7-5-0-991-002-A01
7-5-0
Page 5
Dec 01/14
@A380
7-6-0
**ON A/C A380-800
1.
This section provides data about the flexible pavement requirements for Load Classification Number
(LCN) conversion.
The flexible pavement requirements graphs are given at standard tire pressure for the weight variants
producing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load for
each type of aircraft.
They are calculated with the LCN conversion method.
To find the aircraft weight that a flexible pavement can support, you must know the LCN of the
pavement and the thickness.
Example, see FIGURE 7-6-0-991-002-A (sheet 1), calculation of the weight on one WLG for flexible
pavement:
- The flexible pavement thickness is 1 270 mm (50 in) with a related LCN of 112.
The weight on one WLG is 75 000 kg (165 350 lb).
Example, see FIGURE 7-6-0-991-002-A (sheet 2), calculation of the weight on one BLG for flexible
pavement:
- The flexible pavement thickness is 1 270 mm (50 in) with a related LCN of 104.
The weight on one BLG is 125 000 kg (275 575 lb).
2.
Flexible Pavement Requirements - LCN Table
The table in FIGURE 7-6-0-991-001-A provides LCN data in a tabular format similar to the one used
by ICAO in the ”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use the
system accurately you should know the total pavement thickness for flexible pavement.
However, the pavement thickness for particular runways is not frequently published in the standard
airport information sources (Jeppesen, AERAD, DOD, etc.).
Therefore it is common practice to use a standard thickness (20 in) when determining the LCN and
the ESWL of the aircraft.
If the LCN for an intermediate weight between the MRW and the empty weight of the aircraft is
required or if the real thickness is known, refer to the figures that follow.
NOTE : The CG in the figure title is the CG used for LCN calculation.
7-6-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
WEIGHT
VARIANT
ALL UP
MASS (kg)
562 000
WV000
300 000
512 000
WV001
300 000
571 000
WV002
300 000
512 000
WV003
300 000
562 000
WV004
300 000
562 000
WV005
300 000
575 000
WV006
300 000
492 000
WV007
300 000
577 000
WV008
300 000
512 000
WV009
300 000
FLEXIBLE PAVEMENT
LOAD ON
TIRE
ESWL
ONE MAIN
PRESSURE
LCN
GEAR LEG
x 1 000 kg
x 1 000 lb
(MPa)
(%)
h = 510 mm (20 in)
19 (WLG)
28
62
99
28.5 (BLG)
59
96
27
1.50
19 (WLG)
56
31
14
28.5 (BLG)
31
56
14
19 (WLG)
55
88
25
28.5 (BLG)
53
85
24
1.40
19 (WLG)
54
31
14
28.5 (BLG)
54
31
14
18.9 (WLG)
62
28
100
28.3 (BLG)
59
97
27
1.50
18.9 (WLG)
55
31
14
28.3 (BLG)
55
31
14
19 (WLG)
55
25
88
28.5 (BLG)
53
85
24
1.40
19 (WLG)
54
31
14
28.5 (BLG)
54
31
14
19 (WLG)
62
99
28
28.5 (BLG)
59
96
27
1.50
19 (WLG)
31
56
14
28.5 (BLG)
31
56
14
19 (WLG)
62
99
28
28.5 (BLG)
59
96
27
1.50
19 (WLG)
31
56
14
28.5 (BLG)
31
56
14
18.9 (WLG)
62
28
101
28.3 (BLG)
59
97
27
1.50
18.9 (WLG)
55
31
14
28.3 (BLG)
55
31
14
19 (WLG)
53
85
24
28.5 (BLG)
51
83
23
1.40
19 (WLG)
54
31
14
28.5 (BLG)
54
31
14
18.9 (WLG)
62
28
101
28.3 (BLG)
59
98
27
1.50
18.9 (WLG)
55
31
14
28.3 (BLG)
55
31
14
19 (WLG)
55
88
25
28.5 (BLG)
53
24
85
1.40
19 (WLG)
31
54
14
28.5 (BLG)
31
54
14
L_AC_070600_1_0010101_01_01
LCN Table
FIGURE-7-6-0-991-001-A01
7-6-0
Page 2
Dec 01/14
7-6-0
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
10
20
40 50 60
150
230
80 100
120
190
70
LOAD CLASSIFICATION NUMBER (LCN)
30
10
20
30
40
50
60
70
1 400 x 530 R23 40PR TIRES
NOTE:
EQUIVALENT SINGLE WHEEL LOADS ARE DERIVED BY METHODS SHOWN IN
ICAO AERODROME MANUAL PART 2 PAR 4.1.3 SECOND EDITION 1965.
30
1 500 2 000 2 500
50 60 70 80 100
90
FLEXIBLE PAVEMENT THICKNESS (in)
20
GEAR LOAD AT MAXIMUM
RAMP WEIGHT AND
AFT CG
40
750 1 000
WEIGHT ON ONE WING
LANDING GEAR
93 600 kg (206 350 lb)
75 000 kg (165 350 lb)
60 000 kg (132 275 lb)
45 000 kg
(99 200 lb)
30 000 kg
(66 150 lb)
500
FLEXIBLE PAVEMENT THICKNESS (mm)
@A380
**ON A/C A380-800
EQUIVALENT SINGLE WHEEL LOAD (x 1 000 kg)
EQUIVALENT SINGLE WHEEL LOAD (x 1 000 lb)
L_AC_070600_1_0020101_01_00
WV007, MRW 492 000 kg, CG 43 % - WLG (Sheet 1 of 2)
FIGURE-7-6-0-991-002-A01
Page 3
Dec 01/14
7-6-0
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
10
20
40 50 60
150
230
80 100
120
190
70
30
10
20
30
40
50
60
70
1 400 x 530 R23 40PR TIRES
NOTE:
30
1 500 2 000 2 500
50 60 70 80 100
90
20
RAMP WEIGHT AND
AFT CG
40
750 1 000
WEIGHT ON ONE BODY
LANDING GEAR
140 410 kg (309 550 lb)
125 000 kg (275 575 lb)
110 000 kg (242 500 lb)
95 000 kg (209 450 lb)
80 000 kg (176 375 lb)
500
@A380
**ON A/C A380-800
L_AC_070600_1_0020102_01_00
WV007, MRW 492 000 kg, CG 43 % - BLG (Sheet 2 of 2)
FIGURE-7-6-0-991-002-A01
Page 4
Dec 01/14
7-6-0
10
20
30
40
50
60
70
80
90
10
40
20
40 50 60
150
230
80 100
120
190
70
30
10
20
30
40
50
60
70
1 400 x 530 R23 40PR TIRES
NOTE:
30
1 500 2 000 2 500
50 60 70 80 100
90
20
RAMP WEIGHT AND
AFT CG
110
120
130
140
100
750 1 000
WEIGHT ON ONE WING
LANDING GEAR
108 850 kg (239 975 lb)
85 000 kg (187 400 lb)
70 000 kg (154 325 lb)
55 000 kg (121 250 lb)
40 000 kg
(88 175 lb)
500
150
160
@A380
**ON A/C A380-800
L_AC_070600_1_0030101_01_00
FIGURE-7-6-0-991-003-A01
Page 5
Dec 01/14
7-6-0
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
10
20
40 50 60
150
230
80 100
120
190
70
30
10
20
30
40
50
60
70
1 400 x 530 R23 40PR TIRES
NOTE:
30
1 500 2 000 2 500
50 60 70 80 100
90
20
RAMP WEIGHT AND
AFT CG
40
750 1 000
WEIGHT ON ONE BODY
LANDING GEAR
163 270 kg (359 950 lb)
145 000 kg (319 675 lb)
130 000 kg (286 600 lb)
115 000 kg (253 525 lb)
100 000 kg (220 450 lb)
500
@A380
**ON A/C A380-800
L_AC_070600_1_0030102_01_00
FIGURE-7-6-0-991-003-A01
Page 6
Dec 01/14
@A380
7-7-0
**ON A/C A380-800
1.
This section gives data about the rigid pavement requirements for the PCA (Portland Cement
Association) design method.
The rigid pavement requirement graphs are given at standard tire pressure for the weight variants
producing (at the MRW and max aft CG) the lowest MLG load and the highest MLG load for each
A/C type.
To find a rigid pavement thickness, you must know the Subgrade Modulus (k), the permitted working
stress and the weight on one MLG.
The procedure that follows is used to develop rigid pavement design curves:
- With the scale for pavement thickness on the left and the scale for permitted working stress on
the right, a random load line is made. This represents the MLG maximum weight to be shown,
- A plot is then made of all values of the subgrade modulus (k values),
- More load lines for the incremental values of the weight on the MLG are made based on the
curve for k = 80 MN/m3, which is already shown on the graph.
Example, see FIGURE 7-7-0-991-001-A (sheet 1), calculation of the thickness of the rigid pavement
for the WLG:
- A k value of 80 MN/m3 (300 lbf/in3),
- A permitted working stress of 38.67 kg/cm2 (550 lb/in2),
- The load on one MLG is 75 000 kg (165 350 lb).
The required rigid pavement thickness is 224 mm (9 in).
Example, see FIGURE 7-7-0-991-001-A (sheet 2), calculation of the thickness of the rigid pavement
for the BLG:
- A k value of 80 MN/m3 (300 lbf/in3),
- A permitted working stress of 38.67 kg/cm2 (550 lb/in2),
- The load on one MLG is 125 000 kg (275 575 lb).
The required rigid pavement thickness is 239 mm (9 in).
7-7-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
1 400 x 530 R23 40PR TIRES
36
900
k = 20 MN/m³
k = 40 MN/m³
k = 80 MN/m³
k = 150 MN/m³
14
60
800
RAMP WEIGHT AND AFT CG
34
13
700
12
600
50
30
11
500
10
400
9
300
(lb/in²)
28
40
(in)
RIGID PAVEMENT THICKNESS
(cm)
32
30
26
24
22
20
18
8
7
WEIGHT ON ONE WING
LANDING GEAR
93 600 kg (206 350 lb)
75 000 kg (165 350 lb)
60 000 kg (132 275 lb)
45 000 kg (99 200 lb)
30 000 kg (66 150 lb)
NOTE:
THE VALUES OBTAINED BY USING
THE MAXIMUM LOAD REFERENCE
LINE AND ANY VALUES FOR k ARE
EXACT.
FOR LOADS LESS THAN MAXIMUM,
THE CURVES ARE EXACT FOR k =
80 MN/m³ BUT DEVIATE SLIGHTLY
FOR ANY OTHER VALUES OF k.
(kg/cm²)
ALLOWABLE WORKING STRESS
15
38
20
200
10
100
REFERENCE:
"DESIGN OF CONCRETE AIRPORT
PAVEMENTS" AND "COMPUTER
PROGRAM FOR AIRPORT
PAVEMENT DESIGN − PROGRAM
PDILB" PORTLAND CEMENT
ASSOCIATION.
L_AC_070700_1_0010101_01_00
Rigid Pavement Requirements
FIGURE-7-7-0-991-001-A01
7-7-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
1 400 x 530 R23 40PR TIRES
36
900
k = 20 MN/m³
k = 40 MN/m³
k = 80 MN/m³
k = 150 MN/m³
14
60
800
34
13
700
12
600
50
30
11
500
10
400
9
300
(lb/in²)
28
40
(in)
(cm)
32
30
26
24
22
20
18
8
7
WEIGHT ON ONE BODY
LANDING GEAR
140 410 kg (309 550 lb)
125 000 kg (275 575 lb)
110 000 kg (242 500 lb)
95 000 kg (209 450 lb)
80 000 kg (176 375 lb)
NOTE:
EXACT.
(kg/cm²)
15
38
20
200
10
100
REFERENCE:
PROGRAM FOR AIRPORT
ASSOCIATION.
L_AC_070700_1_0010102_01_00
FIGURE-7-7-0-991-001-A01
7-7-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
1 400 x 530 R23 40PR TIRES
36
900
k = 20 MN/m³
k = 40 MN/m³
k = 80 MN/m³
k = 150 MN/m³
14
60
800
34
13
700
12
600
50
30
11
500
10
400
9
300
(lb/in²)
28
40
(in)
(cm)
32
30
26
24
22
20
18
8
7
WEIGHT ON ONE WING
LANDING GEAR
108 850 kg (239 975 lb)
85 000 kg (187 400 lb)
70 000 kg (154 325 lb)
55 000 kg (121 250 lb)
40 000 kg (88 175 lb)
NOTE:
EXACT.
(kg/cm²)
15
38
20
200
10
100
REFERENCE:
PROGRAM FOR AIRPORT
ASSOCIATION.
L_AC_070700_1_0020101_01_00
FIGURE-7-7-0-991-002-A01
7-7-0
Page 4
Dec 01/14
@A380
**ON A/C A380-800
1 400 x 530 R23 40PR TIRES
36
900
k = 20 MN/m³
k = 40 MN/m³
k = 80 MN/m³
k = 150 MN/m³
14
60
800
34
13
700
12
600
50
30
11
500
10
400
9
300
(lb/in²)
28
40
(in)
(cm)
32
30
26
24
22
20
18
8
7
WEIGHT ON ONE BODY
LANDING GEAR
163 270 kg (359 950 lb)
145 000 kg (319 675 lb)
130 000 kg (286 600 lb)
115 000 kg (253 525 lb)
100 000 kg (220 450 lb)
NOTE:
EXACT.
(kg/cm²)
15
38
20
200
10
100
REFERENCE:
PROGRAM FOR AIRPORT
ASSOCIATION.
L_AC_070700_1_0020102_01_00
FIGURE-7-7-0-991-002-A01
7-7-0
Page 5
Dec 01/14
@A380
7-8-0
**ON A/C A380-800
1.
This section provides data about the rigid pavement requirements for the Load Classification Number
(LCN) conversion (radius of relative stiffness).
The rigid pavement requirement graphs are given at standard tire pressure for the weight variants
producing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load for
each type of aircraft.
To find the aircraft weight that a rigid pavement can support, you must know the LCN of the
pavement and the radius of relative stiffness (L).
The calculation of the radius of relative stiffness (L) is done with the formula and the table given in
”Radius of Relative Stiffness” (L values based on Young’s Modulus (E) of 4 000 000 psi and
Poisson’s Ratio (µ) of 0.15), see FIGURE 7-8-0-991-002-A.
Example, see FIGURE 7-8-0-991-003-A (Sheet 1), calculation of the aircraft weight through the
radius of relative stiffness (L) of the rigid pavement for the Wing Landing Gear (WLG):
- The radius of relative stiffness is shown at 1 270 mm (50 in) with a related LCN of 86.
The weight on one WLG is 75 000 kg (165 350 lb).
Example, see FIGURE 7-8-0-991-003-A (Sheet 2), calculation of the aircraft weight through the
radius of relative stiffness (L) of the rigid pavement for the Body Landing Gear (BLG):
- The radius of relative stiffness is shown at 1 270 mm (50 in) with a related LCN of 81.
The weight on one BLG is 125 000 kg (275 575 lb).
The following table provides LCN data in a tabular format similar to the one used by ICAO in the
”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use the system accurately
you should know the total pavement radius of relative stiffness (L-value) for rigid pavement.
However, the pavement radius of relative stiffness for a particular runway are not frequently published
in the standard airport information sources (Jeppesen, AERAD, DOD, etc.). Therefore it is common
practice to use a standard radius of relative stiffness (30 inches) when determining the LCN and the
ESWL of the aircraft.
If the LCN for an intermediate weight between the maximum ramp weight and the empty weight of
the aircraft is required or if the real thickness is known, refer to the figures that follow.
2.
Radius of Relative Stiffness (Other values of E and µ)
This section provides data about the rigid pavement requirements for the Load Classification Number
(LCN) conversion (radius of relative stiffness) with other values of E (Young’s modulus) and µ
(Poisson’s ratio).
The other values of E and µ have an effect on the radius of relative stiffness (L-value).
7-8-0
Page 1
Dec 01/14
@A380
The effect of E and µ on the radius of relative stiffness (L-value) is shown in the graphs in FIGURE
7-8-0-991-005-A.
The table in FIGURE 7-8-0-991-002-A shows L-values based on a Young’s modulus (E) of 4 000 000
psi and a Poisson’s ratio (µ) of 0.15.
To find the L-value, you must know the values of E and µ.
Example, see FIGURE 7-8-0-991-005-A, calculation of the L-values of the rigid pavement for an E of
3 000 000 psi.
The ”E” factor is 0.931.
The radius of relative stiffness (L-value) is the value found in the table (see FIGURE 7-8-0-991-002A) multiplied by 0.931.
NOTE : The CG in the figure title is the CG used for LCN calculation.
7-8-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
WEIGHT
VARIANT
ALL UP
MASS (kg)
562 000
WV000
300 000
512 000
WV001
300 000
571 000
WV002
300 000
512 000
WV003
300 000
562 000
WV004
300 000
562 000
WV005
300 000
575 000
WV006
300 000
492 000
WV007
300 000
577 000
WV008
300 000
512 000
WV009
300 000
RIGID PAVEMENT
LOAD ON
TIRE
ESWL
ONE MAIN
PRESSURE
LCN
GEAR LEG
x 1 000 kg
x 1 000 lb
(MPa)
(%)
L = 760 mm (30 in)
19 (WLG)
26
58
95
28.5 (BLG)
20
74
9
1.50
19 (WLG)
31
53
14
28.5 (BLG)
11
41
5
19 (WLG)
53
84
24
28.5 (BLG)
18
66
8
1.40
19 (WLG)
51
31
14
28.5 (BLG)
40
11
5
18.9 (WLG)
96
59
27
28.3 (BLG)
20
74
9
1.50
18.9 (WLG)
53
31
14
28.3 (BLG)
40
11
5
19 (WLG)
53
84
24
28.5 (BLG)
18
66
8
1.40
19 (WLG)
51
31
14
28.5 (BLG)
40
11
5
19 (WLG)
95
58
26
28.5 (BLG)
20
74
9
1.50
19 (WLG)
53
31
14
28.5 (BLG)
11
41
5
19 (WLG)
95
58
26
28.5 (BLG)
20
74
9
1.50
19 (WLG)
53
31
14
28.5 (BLG)
11
41
5
18.9 (WLG)
96
59
27
28.3 (BLG)
20
75
9
1.50
18.9 (WLG)
53
31
14
28.3 (BLG)
40
11
5
19 (WLG)
82
51
23
28.5 (BLG)
18
64
8
1.40
19 (WLG)
51
31
14
28.5 (BLG)
40
11
5
18.9 (WLG)
97
59
27
28.3 (BLG)
20
75
9
1.50
18.9 (WLG)
53
31
14
28.3 (BLG)
40
11
5
19 (WLG)
53
84
24
28.5 (BLG)
18
8
66
1.40
19 (WLG)
51
31
14
28.5 (BLG)
11
40
5
L_AC_070800_1_0010101_01_01
LCN Table
FIGURE-7-8-0-991-001-A01
7-8-0
Page 3
Dec 01/14
@A380
**ON A/C A380-800
RADIUS OF RELATIVE STIFFNESS (L)
VALUES IN INCHES
L= 4
WHERE
Ed
12 (1 −
= 24.1652 4
)k
d
k
E = YOUNG’S MODULUS = 4 x 10 psi
k = SUBGRADE MODULUS, lb/in
d = RIGID PAVEMENT THICKNESS, (in)
= POISSON’S RATIO = 0.15
d
k = 75
k = 100
k = 150
k = 200
k = 250
k = 300
k = 350
k = 400
k = 550
6.0
6.5
7.0
7.5
31.48
33.43
35.34
37.22
29.30
31.11
32.89
34.63
26.47
28.11
29.72
31.29
24.63
26.16
27.65
29.12
23.30
24.74
26.15
27.54
22.26
23.64
24.99
26.32
21.42
22.74
24.04
25.32
20.72
22.00
23.25
24.49
19.13
20.31
21.47
22.61
8.0
8.5
9.0
9.5
39.06
40.88
42.67
44.43
36.35
38.04
39.71
41.35
32.85
34.37
35.88
37.36
30.57
31.99
33.39
34.77
28.91
30.25
31.58
32.89
27.62
28.91
30.17
31.42
26.58
27.81
29.03
30.23
25.70
26.90
28.08
29.24
23.74
24.84
25.93
27.00
10.0
10.5
11.0
11.5
46.18
47.90
49.60
51.28
42.97
44.57
46.16
47.72
38.83
40.28
41.71
43.12
36.14
37.48
38.81
40.13
34.17
35.45
36.71
37.95
32.65
33.87
35.07
36.26
31.42
32.59
33.75
34.89
30.39
31.52
32.64
33.74
28.06
29.11
30.14
31.16
12.0
12.5
13.0
13.5
52.94
54.59
56.22
57.83
49.27
50.80
52.32
53.82
44.52
45.90
47.27
48.63
41.43
42.72
43.99
45.26
39.18
40.40
41.61
42.80
37.44
38.60
39.75
40.89
36.02
37.14
38.25
39.35
34.84
35.92
36.99
38.06
32.17
33.17
34.16
35.14
14.0
14.5
15.0
15.5
59.43
61.02
62.59
64.15
55.31
56.78
58.25
59.70
49.98
51.31
52.63
53.94
46.51
47.75
48.98
50.20
43.98
45.16
46.32
47.47
42.02
43.15
44.26
45.36
40.44
41.51
42.58
43.64
39.11
40.15
41.19
42.21
36.12
37.08
38.03
38.98
16.0
16.5
17.0
17.5
65.69
67.23
68.75
70.26
61.13
62.56
63.98
65.38
55.24
56.53
57.81
59.08
51.41
52.61
53.80
54.98
48.62
49.75
50.88
52.00
46.45
47.54
48.61
49.68
44.70
45.74
46.77
47.80
43.23
44.24
45.24
46.23
39.92
40.85
41.78
42.70
18.0
19.0
20.0
21.0
71.76
74.73
77.66
80.55
66.78
69.54
72.27
74.96
60.34
62.84
65.30
67.74
56.15
58.48
60.77
63.04
53.11
55.31
57.47
59.62
50.74
52.84
54.91
56.96
48.82
50.84
52.84
54.81
47.22
49.17
51.10
53.01
43.61
45.41
47.19
48.95
22.0
23.0
24.0
25.0
83.41
86.24
89.04
91.81
77.63
80.26
82.86
85.44
70.14
72.52
74.87
77.20
65.28
67.49
69.68
71.84
61.73
63.83
65.90
67.95
58.98
60.98
62.96
64.92
56.75
58.68
60.58
62.46
54.89
56.75
58.59
60.41
50.69
52.41
54.11
55.79
REFERENCE:
PORTLAND CEMENT ASSOCIATION.
L_AC_070800_1_0020101_01_00
Radius of Relative Stiffness (L)
FIGURE-7-8-0-991-002-A01
7-8-0
Page 4
Dec 01/14
1 000 1 250 1 500
2 000 2 500
40
50
60
70 80 90 100
20
40
50 60 70
100 150 190
80
120
30
7-8-0
NOTE:
RADIUS OF RELATIVE STIFFNESS (in)
5
30
10
15
20
25
30
35
40
45
50
10
20
RAMP WEIGHT AND
AFT CG
93 600 kg (206 350 lb)
75 000 kg (165 350 lb)
60 000 kg (132 275 lb)
45 000 kg
(99 200 lb)
30 000 kg
(66 150 lb)
750
1 400 x 530 R23 40PR TIRES
20
30
40
50
60
70
80
90
100
110
120
RADIUS OF RELATIVE STIFFNESS (mm)
@A380
**ON A/C A380-800
L_AC_070800_1_0030101_01_00
WV007, MRW 492 000 kg, CG 43% - WLG (Sheet 1 of 2)
FIGURE-7-8-0-991-003-A01
Page 5
Dec 01/14
1 000 1 250 1 500
2 000 2 500
40
50
60
70 80 90 100
20
40
50 60 70
100 150 190
80
120
30
7-8-0
NOTE:
5
30
10
15
20
25
30
35
40
45
50
10
20
RAMP WEIGHT AND
AFT CG
140 410 kg (309 550 lb)
125 000 kg (275 575 lb)
110 000 kg (242 500 lb)
95 000 kg (209 450 lb)
80 000 kg (176 375 lb)
750
1 400 x 530 R23 40PR TIRES
20
30
40
50
60
70
80
90
100
110
120
@A380
**ON A/C A380-800
L_AC_070800_1_0030102_01_00
WV007, MRW 492 000 kg, CG 43% - BLG (Sheet 2 of 2)
FIGURE-7-8-0-991-003-A01
Page 6
Dec 01/14
1 000 1 250 1 500
2 000 2 500
40
50
60
70 80 90 100
20
40
50 60 70
100 150 190
80
120
30
7-8-0
NOTE:
5
30
10
15
20
25
30
35
40
45
50
10
20
RAMP WEIGHT AND
AFT CG
108 850 kg (239 975 lb)
85 000 kg (187 400 lb)
70 000 kg (154 325 lb)
55 000 kg (121 250 lb)
40 000 kg
(88 175 lb)
750
1 400 x 530 R23 40PR TIRES
20
30
40
50
60
70
80
90
100
110
120
@A380
**ON A/C A380-800
L_AC_070800_1_0040101_01_00
WV008, MRW 577 000 kg, CG 41% - WLG (Sheet 1 of 2)
FIGURE-7-8-0-991-004-A01
Page 7
Dec 01/14
1 000 1 250 1 500
2 000 2 500
40
50
60
70 80 90 100
20
40
50 60 70
100 150 190
80
120
30
7-8-0
NOTE:
5
30
10
15
20
25
30
35
40
45
50
10
20
RAMP WEIGHT AND
AFT CG
163 270 kg (359 950 lb)
145 000 kg (319 675 lb)
130 000 kg (286 600 lb)
115 000 kg (253 525 lb)
100 000 kg (220 450 lb)
750
1 400 x 530 R23 40PR TIRES
20
30
40
50
60
70
80
90
100
110
120
@A380
**ON A/C A380-800
L_AC_070800_1_0040102_01_00
WV008, MRW 577 000 kg, CG 41% - BLG (Sheet 2 of 2)
FIGURE-7-8-0-991-004-A01
Page 8
Dec 01/14
@A380
**ON A/C A380-800
EFFECT OF E ON L VALUES
1.10
1.05
E FACTOR
1.00
0.95
0.90
0.85
0.80
0
1
2
3
4
5
E, YOUNG’S MODULUS (10 psi)
1.015
EFFECT OF
ON L VALUES
FACTOR
1.010
1.005
1.000
0.995
0.00
0.05
0.10
0.15
0.20
0.25
, POISSON’S RATIO
NOTE:
BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THE L VALUES
OF RADIUS OF RELATIVE STIFFNESS (L) TABLE.
L_AC_070800_1_0050101_01_00
Radius of Relative Stiffness (Effect E and µ on ”L” values)
FIGURE-7-8-0-991-005-A01
7-8-0
Page 9
Dec 01/14
@A380
7-9-0
**ON A/C A380-800
1.
This section provides data about the Aircraft Classification Number (ACN) for an aircraft gross
weight in relation with a subgrade strength value for flexible and rigid pavement.
The flexible and rigid pavement requirement graphs are given at standard tire pressure for the weight
variants producing (at the MRW and max aft CG) the lowest MLG load and the highest MLG load
for each type of aircraft.
To find the ACN of an aircraft on flexible and rigid pavement, you must know the aircraft gross
weight and the subgrade strength.
NOTE : An aircraft with an ACN equal to or less than the reported PCN can operate on that
pavement, subject to any limitation on the tire pressure.
(Ref: ICAO Aerodrome Design Manual, Part 3, Chapter 1, Second Edition 1983).
Example, see FIGURE 7-9-0-991-002-A (sheet 1), calculation of the ACN for flexible pavement for:
- An aircraft gross weight of 420 000 kg (925 950 lb),
- A medium subgrade strength (code B).
The ACN for flexible pavement is 43.
Example, see FIGURE 7-9-0-991-002-A (sheet 2), calculation of the ACN for rigid pavement for:
- An aircraft gross weight of 420 000 kg (925 950 lb),
- A medium subgrade strength (code B).
The ACN for rigid pavement is 44.
2.
Aircraft Classification Number - ACN table
The table in FIGURE 7-9-0-991-001-A provides ACN data in tabular format similar to the one used
by ICAO in the ”Aerodrome Design Manual Part 3, Pavements - Edition 1983”. If the ACN for an
intermediate weight between MRW and the minimum weight of the aircraft is required, refer to the
figures that follow.
7-9-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
WEIGHT
VARIANT
ALL UP
MASS
(kg)
562 000
WV000
300 000
512 000
WV001
300 000
571 000
WV002
300 000
512 000
WV003
300 000
562 000
WV004
300 000
562 000
WV005
300 000
575 000
WV006
300 000
492 000
WV007
300 000
577 000
WV008
300 000
512 000
WV009
300 000
LOAD ON
ONE MAIN
GEAR LEG
(%)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
18.9 (WLG)
28.3 (BLG)
18.9 (WLG)
28.3 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
18.9 (WLG)
28.3 (BLG)
18.9 (WLG)
28.3 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
18.9 (WLG)
28.3 (BLG)
18.9 (WLG)
28.3 (BLG)
19 (WLG)
28.5 (BLG)
19 (WLG)
28.5 (BLG)
ACN FOR
ACN FOR
RIGID PAVEMENT
FLEXIBLE PAVEMENT
TIRE
SUBGRADES−MN/m³
SUBGRADES−CBR
PRESSURE
(MPa)
HIGH MEDIUM LOW ULTRA−LOW HIGH MEDIUM LOW ULTRA−LOW
10
80
6
3
150
40
20
15
1.50
1.40
1.50
1.40
1.50
1.50
1.50
1.40
1.50
1.40
56
55
27
29
49
48
26
28
57
56
27
28
49
48
26
28
56
55
27
29
56
55
27
29
58
56
27
28
46
46
26
28
58
56
27
28
49
48
26
28
66
68
29
29
57
57
29
28
67
69
29
29
57
57
29
28
66
68
29
29
66
68
29
29
67
69
29
29
54
54
29
28
68
70
29
29
57
57
29
28
78
88
34
34
68
75
33
33
79
89
33
34
68
75
33
33
78
88
34
34
78
88
34
34
80
90
33
34
64
70
33
33
80
91
33
34
68
75
33
33
91
110
39
42
79
94
38
42
91
111
38
42
79
94
38
42
91
110
39
42
91
110
39
42
92
113
38
42
75
89
38
42
93
113
38
42
79
94
38
42
59
56
27
25
51
49
27
25
59
57
27
25
51
49
27
25
59
56
27
25
59
56
27
25
60
57
27
25
49
47
27
25
60
58
27
25
51
49
27
25
64
62
29
27
56
54
28
27
64
63
28
26
56
54
28
27
64
62
29
27
64
62
29
27
65
63
28
26
53
51
28
27
65
64
28
26
56
54
28
27
75
75
31
30
66
65
31
30
76
76
31
30
66
65
31
30
75
75
31
30
75
75
31
30
77
77
31
30
62
61
31
30
77
77
31
30
66
65
31
30
102
106
40
40
90
92
40
40
104
107
40
39
90
92
40
40
102
106
40
40
102
106
40
40
105
108
40
39
85
87
40
40
105
108
40
39
90
92
40
40
L_AC_070900_1_0010101_01_01
ACN Table
FIGURE-7-9-0-991-001-A01
7-9-0
Page 2
Dec 01/14
7-9-0
20
30
40
50
60
70
80
90
100
110
120
250
600
800
300
350
SUBGRADE STRENGTH
D − CBR 3 (ULTRA LOW)
C − CBR 6 (LOW)
B − CBR 10 (MEDIUM)
A − CBR 15 (HIGH)
400
1 000
450
(x 1 000 kg)
900
ALPHA FACTOR = 0.8 FOR WLG
ALPHA FACTOR = 0.72 FOR BLG
700
(x 1 000 lb)
1 400 x 530 R23 40PR TIRES
500
1 100
550
1 200
600
1 300
ACN WAS DETERMINED AS REFERENCED IN
ICAO AERODROME DESIGN MANUAL PART 3
CHAPTER 1. SECOND EDITION 1983.
SEE SECTION 7−4−0.
@A380
**ON A/C A380-800
AIRCRAFT CLASSIFICATION NUMBER (ACN)
L_AC_070900_1_0020101_01_00
Flexible Pavement - WV007, MRW 492 000 kg, CG 43% (Sheet 1 of 2)
FIGURE-7-9-0-991-002-A01
Page 3
Dec 01/14
7-9-0
20
30
40
50
60
70
80
90
100
110
120
250
700
800
300
350
SUBGRADE STRENGTH
D − k = 20 MN/m³ (ULTRA LOW)
C − k = 40 MN/m³ (LOW)
B − k = 80 MN/m³ (MEDIUM)
A − k = 150 MN/m³ (HIGH)
600
(x 1 000 kg)
450
1 000
400
900
(x 1 000 lb)
1 400 x 530 R23 40PR TIRES
500
1 100
550
1 200
600
1 300
@A380
**ON A/C A380-800
L_AC_070900_1_0020102_01_00
Rigid Pavement - WV007, MRW 492 000 kg, CG 43% (Sheet 2 of 2)
FIGURE-7-9-0-991-002-A01
Page 4
Dec 01/14
7-9-0
20
30
40
50
60
70
80
90
100
110
120
250
600
800
300
350
SUBGRADE STRENGTH
D − CBR 3 (ULTRA LOW)
C − CBR 6 (LOW)
B − CBR 10 (MEDIUM)
A − CBR 15 (HIGH)
400
1 000
450
(x 1 000 kg)
900
ALPHA FACTOR = 0.8 FOR WLG
ALPHA FACTOR = 0.72 FOR BLG
700
(x 1 000 lb)
1 400 x 530 R23 40PR TIRES
500
1 100
550
1 200
600
1 300
@A380
**ON A/C A380-800
L_AC_070900_1_0030101_01_00
Flexible Pavement - WV008, MRW 577 000 kg, CG 41% (Sheet 1 of 2)
FIGURE-7-9-0-991-003-A01
Page 5
Dec 01/14
7-9-0
20
30
40
50
60
70
80
90
100
110
120
250
700
800
300
350
SUBGRADE STRENGTH
D − k = 20 MN/m³ (ULTRA LOW)
C − k = 40 MN/m³ (LOW)
B − k = 80 MN/m³ (MEDIUM)
A − k = 150 MN/m³ (HIGH)
600
(x 1 000 kg)
450
1 000
400
900
(x 1 000 lb)
1 400 x 530 R23 40PR TIRES
500
1 100
550
1 200
600
1 300
@A380
**ON A/C A380-800
L_AC_070900_1_0030102_01_00
Rigid Pavement - WV008, MRW 577 000 kg, CG 41% (Sheet 2 of 2)
FIGURE-7-9-0-991-003-A01
Page 6
Dec 01/14
@A380
SCALED DRAWINGS
8-0-0
SCALED DRAWINGS
**ON A/C A380-800
Scaled Drawings
1.
This section provides the scaled drawings.
NOTE : When printing this drawing, make sure to adjust for proper scaling.
8-0-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
FEET
0 10 20 30 40 50 60
0
4
8
12 16
METERS
20
FEET
0 10 20 30 40 50 60
0
4
8
12 16
METERS
20
NOTE: WHEN PRINTING THIS DRAWING, MAKE SURE TO ADJUST FOR PROPER SCALING.
DB1A
L_AC_080000_1_0010101_01_01
Scaled Drawing
FIGURE-8-0-0-991-001-A01
8-0-0
Page 2
Dec 01/14
@A380
10-0-0
**ON A/C A380-800
Aircraft Rescue and Fire Fighting
1.
Aircraft Rescue and Fire Fighting Charts
This section gives data related to aircraft rescue and fire fighting.
The figures contained in this section are the figures that are in the Aircraft Rescue and Fire Fighting
Charts poster available on AIRBUSWorld and the Airbus website.
10-0-0
Page 1
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0010101_01_01
Front Page
FIGURE-10-0-0-991-001-A01
10-0-0
Page 2
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0020101_01_02
Highly Flammable and Hazardous Materials and Components
FIGURE-10-0-0-991-002-A01
10-0-0
Page 3
Dec 01/14
BAT−1
BAT−ESS
FR86
B
ACCESS DOOR 272AFZ
VIA UPPER DECK
A
FR91
10-0-0
C
BAT−2
A
DIVIDER NET ACCESS
VIA AFT CARGO DOOR
ACCESS VIA BULK
CARGO DOOR 823
ACCESS DOOR 132CFZ
VIA FWD CARGO DOOR
ACCESS VIA
ACCESS DOOR 811
C
FR5
FR17
ACCESS DOOR 131CFZ
VIA FWD CARGO DOOR
B
FR21
BAT−APU
@A380
**ON A/C A380-800
L_AC_100000_1_0170101_01_00
Batteries Location and Access
FIGURE-10-0-0-991-017-A01
Page 4
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0160101_01_00
Crew Rest Compartments Location
FIGURE-10-0-0-991-016-A01
10-0-0
Page 5
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0140101_01_00
Wheel/Brake Overheat
Wheel Safety Area (Sheet 1 of 2)
FIGURE-10-0-0-991-014-A01
10-0-0
Page 6
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0140102_01_00
Wheel/Brake Overheat
Recommendations (Sheet 2 of 2)
FIGURE-10-0-0-991-014-A01
10-0-0
Page 7
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0030101_01_01
Composite Materials Location
FIGURE-10-0-0-991-003-A01
10-0-0
Page 8
Dec 01/14
@A380
A
A
B
B
C
C
**ON A/C A380-800
L_AC_100000_1_0040101_01_01
Landing Gear
Ground Lock Safety Devices
FIGURE-10-0-0-991-004-A01
10-0-0
Page 9
Dec 01/14
OFFWING DUAL−LANE
SLIDE/RAFT
10-0-0
− 18
− 15
− 12
−9
−6
−3
NOTE:
OPENING WITH THE ESCAPE ROPE
SLIDE/RAFT
EMERGENCY DESCENT THROUGH THE WINDOW
COCKPIT ESCAPE
ROPE
SLIDE/RAFT
GRID EQUALS 1 m (3.28 ft) IN REALITY
SLIDE/RAFT
SLIDE/RAFT
SLIDE/RAFT
SLIDE/RAFT
@A380
**ON A/C A380-800
L_AC_100000_1_0050101_01_03
Emergency Evacuation Devices
FIGURE-10-0-0-991-005-A01
Page 10
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0060101_01_02
Pax/Crew Doors and Emergency Exits
FIGURE-10-0-0-991-006-A01
10-0-0
Page 11
Dec 01/14
@A380
197CB
6336MJ
132BR /199DR
5070JE1
**ON A/C A380-800
L_AC_100000_1_0070101_01_02
Cargo Doors
FWD and AFT Lower Deck Cargo Doors
FIGURE-10-0-0-991-007-A01
10-0-0
Page 12
Dec 01/14
E
L
E
C
10-0-0
OFF
OFF
ON
ON
WING
OFF
ON
OFF
OFF
RWY TURN OFF
& CAMERA
ON
AUTO
OFF
LAND
NAV
EXT LT
ON
3
FAULT
ENG
ON
2
FAULT
BEACON
ON
1
FAULT
WING
FAULT
OFF
FAULT
4
OFF
FAULT
OFF
ON
OFF
ON
ON
NOSE
LOGO
FAULT
DISC
FAULT
ANTI ICE
OFF
DISC
AUTO MODE
FAULT
FAULT
OFF
OFF
AUTO
OFF
TAXI
T.O
OFF
B
ON
AVAIL
START
ON
FAULT
MASTER SW
APU
NORM
OFF
DISC
FAULT
DRIVE
ON
AVAIL
OFF
AUTO
A
U
T
O
DISC
FAULT
OFF
AUTO
MAN
MODE
BRT
OFF
1215VM
E
L
E
C
1225VM
F
I
R
E
1245VM
OFF
ARM
ON
ON
EMER EXIT LT
DIM
TRGT
DN
DITCHING
UP
ON
AVAIL
CABIN V/S
OFF
OFF
EXT 4
FAULT
4 GEN
ANN LT
TEST
A
U
T
O
SIGNS
OFF
STORM
ON
INT LT
MAN
SEAT BELTS NO SMOKING
ON
ON
OFF
ICE
IND
STBY
COMPASS
OFF
AC BUS 4
DRIVE
A
U
T
O
DISCH
SQUIB
AGENT 2
COMMERCIAL
1
2
CABIN PRESS
OFF
OFF
EXT 3
FAULT
3 GEN
AC BUS 3
CABIN ALT
TRGT
IGN
MODE
INC
START DEC
ENG START
FAULT
APU GEN B
A
U
T
O
ALTN
FAULT
AC ESS FEED
DISCH
DISCH
DISCH
GALLEY
SQUIB
SQUIB
PAX SYS
AGENT 1
AGENT 2
PUSH
FIRE
ENG 4
SQUIB
PUSH
FIRE
ENG3
C
AGENT 1
FAULT
CRANK
ON
OFF
BUS TIE
OFF
FAULT
ELMU
A
TEST
APU GEN A
AC ESS
BUS
DISCH
SQUIB
AGENT 2
2 GEN
AC BUS 2
OFF
FAULT
APU BAT
DISCH
SQUIB
AGENT 1
DRIVE
ON
1 GEN
AVAIL
ON
DRIVE
EXT 2
AVAIL
OFF
FAULT
EXT 1
AC BUS 1
FAULT
FAULT
BAT 2
DISCH
DISCH
ESS BAT
SQUIB
BAT 1
AGENT 2
PUSH
PUSH
SQUIB
FIRE
FIRE
AGENT 1
STROBE
ON
F
I
R
E
ENG 2
ENG 1
E
B
D
A
FLT INT
SVCE INT
APU
FIRE
FAULT
OFF
FAULT
OFF
FAULT
OFF
FAULT
OFF
FAULT
CAB FANS
OFF
OFF
C
FAST
SLOW
ON
4
ENG
A
U
T
O
WIPER
ON
3
OVRD
VENT
BTL 2
AVNCS
EXTRACT
MAN
START
ON
2
RAIN RPLNT
ON
1
SMOKE
AVNCS
DISCH
SMOKE
BTL 1
CARGO SMOKE
AGENT TO FWD
25
OFF
FAULT
COOLG
TEST
DISCH
SMOKE
A
U
T
O
AGENT TO AFT
OFF
FAULT
HEATER
5
25
5
OFF
TEMP REGUL
15
TEMP REGUL
15
OFF
FAULT
ISOL VALVES
ISOL VALVES
ISOL VALVES
1212VM
AFT
BULK
APU
SHUT
OFF
FWD
CARGO AIR COND
SEC 2
PRIM 2
F/CTL
HORN RESET
AVNCS VENT
LIGHT TEST
ELT
COCKPIT
CALL
OFF
IR1
NAV
OFF
FAULT
OFF
FAULT
ADR1
L MID
L MID
L OUTR
L OUTR
OFF
ATT
L INR
L INR
FEED 1
FEED 1
HI LVL
HI LVL
FEED 3
FEED 3
R INR
R INR
FEED 4
FEED 4
D
OFF
FAULT
ADR3
NAV
OFF
FAULT
IR3
ADIRS
PUSH
FIRE
APU
OFF
FAULT
ADR2
ATT
ON
A
U
T
O
PROBE/WINDOW
HEAT
ATT
OFF
NAV
OFF
FAULT
IR2
DISCH
SQUIB
AGENT
1221VM
REFUEL/DEFUEL VALVES
TRIM
TRIM
FEED 2
FEED 2
R MID
R MID
R OUTR
R OUTR
SHUT
OPEN
SHUT
OPEN
OFF
ON
FAULT
1
FIRE
TO
GA
0
T
H
R
A
CL
FLX
M
C
T
OFF
ON
AUTO
REFUEL
2
FIRE
FAULT
1
3
E
ENG
MASTER
2
PRESELECT
DECREASE
INCREASE
PRESELECT (PFQ)
OFF
MODE SELECT
XFR
DEFUEL
MAN
REFUEL
kg
ACTUAL (FOB)
NORMAL
BATTERY
POWER SUPPLY
4
FAULT
OFF
ON
0
T
H
R
A
CL
FLX
M
C
T
TO
GA
4
OFF
ON
1125 VU
FAULT
FIRE
APU EMERGENCY
SHUTDOWN
FIRE
3
OVERFLOW
STATUS
FAULT
SHUTOFF
TEST
@A380
**ON A/C A380-800
L_AC_100000_1_0100101_01_01
Control Panels
FIGURE-10-0-0-991-010-A01
Page 13
Dec 01/14
@A380
FR112
315AR
A
FR117
315AL
A
**ON A/C A380-800
L_AC_100000_1_0110101_01_01
APU Compartment Access
FIGURE-10-0-0-991-011-A01
10-0-0
Page 14
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0120101_01_01
Aircraft Ground Clearances
FIGURE-10-0-0-991-012-A01
10-0-0
Page 15
Dec 01/14
@A380
**ON A/C A380-800
L_AC_100000_1_0130101_01_02
Structural Break-in Points
FIGURE-10-0-0-991-013-A01
10-0-0
Page 16
Dec 01/14

A380 - Airbus

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