A300 - Airbus

Transcription

A300 - Airbus

A300
AIRPLANE CHARACTERISTICS FOR AIRPORT PLANNING
HIGHLIGHTS
REVISION 22 – DEC 01/09
This revision concerns introduction of new pages and corrections of pages.
Description of change.
SECTION
PAGE(s)
REASON FOR CHANGE
1.1
p 1
Update Mail address.
1.2
p 1 and p 2
Update Presentation.
2.1
p 2
Update Presentation.
2.1.1
p 3 to p 4C
Update Presentation and added Weight Variants.
2.3
p 7
Added “Note”.
p 7A to p 9
Update Illustrations.
8.1
p 1
Change Text.
9.1.1
p 1 to p 4
Update Illustration.
9.2.1
p 1 to p 4
Update Illustration.
9.3.1
Deleted Section.
9.4.1
Deleted Section.
9.5.1
Deleted Section.
9.6.1
Deleted Section.
HIGHLIGHTS
Page 1 of 1
DEC 01/09
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Printed in France
A300
REVISION TRANSMITTAL SHEET
TO : ALL HOLDERS OF A300 AIRPLANE CHARACTERISTICS
R
The revision, dated DEC 01/09 is attached and covers all the Airplane
Characteristics, and the pavement data, which are identified in the
highlights.
FILING INSTRUCTIONS
NOTE : Before introducing this revision make certain that previous
revisions are incorporated.
− affected pages are listed on the “List of Effective Pages” and
designated as follows :
R = revised (to be replaced)
D = deleted (to be removed)
N = new
(to be introduced)
− make certain that the content of the manual is in compliance with
the List of Effective Pages.
− update the Record of Temporary Revisions page as required.
− update the Record of Revisions page accordingly.
− file the Revision Transmittal Sheet separately.
− remove and destroy the pages which are affected by this revision.
REASON FOR ISSUE
The attached Highlights detail the reasons for issue.
Page 1 of 1
DEC 01/09
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A300
RECORD OF REVISIONS
REV
No.
ISSUE
DATE
DATE
INSERTED
BY
REV
No.
ISSUE
DATE
DATE
INSERTED
BY
JUN. 1986
R
1
APR. 1970
2
APR. 1972
3
APR. 1973
4
MAR. 1974
5
JUN. 1974
6
DEC. 1974
7
SEP. 1975
8
DEC. 1976
9
MAR. 1977
10
MAR. 1978
11
MAR. 1979
12
FEB. 1980
13
OCT. 1980
14
JUL. 1982
15
MAR. 1986
16
OCT. 1987
17
FEB. 1988
18
OCT. 1989
19
JUN. 1992
20
APR. 1995
21
MAY. 1998
22
DEC. 2009
R.O.R.
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LIST OF EFFECTIVE PAGES
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3.0
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3.3
3.3
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5.3
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5.4
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5.4
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5.4
5.4
5.4
5.4
5.4
5.4
5.4
5.4
5.4
5.4
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5.4
5.4
5.4
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5.4
5.5
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6.1
6.1
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6.2
6.2
6.2
6.2
6.2
6.2
6.3
6.3
6.3
6.3
6.3
6.3
6.3
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OCT
OCT
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MAR
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APR
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7.2
7.2
7.3
7.3
7.4
7.4
7.5
7.5
7.5
7.5
7.5
7.5
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7.6
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7.6
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OCT 87
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DEC 01/09
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MAR 86
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MAR 86
8.0
8.1
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DEC 09
9.0
9.1.1
9.1.1
9.1.1
9.1.1
9.2.1
9.2.1
9.2.1
9.2.1
9.3.1
9.3.1
9.3.1
9.3.1
9.4.1
9.4.1
9.4.1
9.4.1
9.5.1
9.5.1
9.5.1
9.5.1
9.6.1
9.6.1
9.6.1
9.6.1
R
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10.1.0
10.2.0
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10.2.0
10.3.0
10.4.0
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L.E.P.
Page 5
DEC 01/09
R
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A300
TABLE OF CONTENTS
R
R
R
1.0
1.1
1.2
SCOPE
Purpose
Introduction
R
R
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2.0
2.1
2.1.1
2.2
2.3
2.4
2.4.1
2.4.2
2.4.3
2.4.4
2.5
2.5.1
2.5.2
2.5.3
2.6
2.6.1
2.6.2
2.6.3
2.7
2.8
2.8.1
2.8.2
2.8.3
2.8.4
2.8.5
2.8.6
2.8.7
2.8.8
2.8.9
AIRPLANE DESCRIPTION
General Airplane Characteristics
General Airplane Characteristics Data
General Dimensions
Ground Clearances
Interior Arrangement
Basic Version
Basic High Density Version
Basic Upper Deck Configuration
Optional Upper Deck Configuration
Passenger Cabin Cross Section
Seating Configuration — 6 Abreast — First Class
Seating Configuration — 8 Abreast — Tourist Class
Seating Configuration — 9 Abreast — Charter Operation
Lower Compartment
Weight and Volume Data
Containers
Pallets
Upper Deck Cargo
Door Clearances
Forward Passenger Door
Middle Passenger Door
AFT Passenger Door
Forward Cargo Compartment Door
Upper Deck Cargo Door
AFT Cargo Compartment Door
Bulk Cargo Compartment Door
Radome Travel
Main Landing Gear Door
R
T.O.C.
Page 1
DEC 01/09
R
Printed in France
A300
TABLE OF CONTENTS
3.0
3.1
3.2
3.2.1
3.2.2
3.3
3.3.1
3.3.2
3.3.3
3.3.4
3.4
3.4.1
3.4.2
3.4.3
3.5
3.5.1
3.5.2
AIRPLANE PERFORMANCE
General Information
Payload Range
Long Range and Recommended Cruise (U.S Units)
Long Range and Recommended Cruise (Metric Units)
FAR Takeoff Runway Lenght Requirements
ISA Conditions – Alternate (U.S Units)
ISA Conditions – Alternate (Metric Units)
ISA Conditions + 59°F (+ 15°C) — Alternate (U.S Units)
ISA Conditions + 59°F (+ 15°C) — Alternate (Metric Units)
FAR Landing Runway Requirements
Full Flaps (U.S Units)
Full Flaps (Metric Units)
Full Flaps
Landing Approach Speed
Landing Approach Speed (Metric Units)
Landing Approach Speed (U.S Units)
4.0
4.1
4.2
4.3
4.4
4.4.1
4.4.2
4.4.3
4.5
4.6
4.6.1
4.6.2
GROUND MANEUVERING
Turning Radii – No Slip Angle
Minimum Turning Radii
Visibility From Cockpit in Static Position
Runway and Taxiway Turnpaths
More than 90° Turn Runway to Taxiway
90° Turn Runway to Taxiway
90° Turn Taxiway to Taxiway
Runway Holding Apron
Minimum Parking Space Requirements
Minimum Parking Space Requirements (U.S Units)
Minimum Parking Space Requirements (Metric Units)
T.O.C.
Page 2
DEC 01/09
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A300
TABLE OF CONTENTS
5.0
5.1
5.1.1
5.1.2
5.1.3
5.1.4
5.1.5
5.1.6
5.1.7
5.1.8
5.2
5.2.1
5.2.2
5.2.3
5.2.4
5.3
5.3.1
5.4
5.4.1
5.4.2
5.4.3
5.4.4
5.4.5
5.4.6
5.4.7
5.4.8
5.4.9
5.4.10
5.5
5.5.1
5.5.2
5.5.3
5.6
5.6.1
5.6.2
5.6.3
5.6.4
5.7
5.7.1
5.7.2
5.8
5.8.1
5.8.2
TERMINAL SERVICING
Airplane Servicing Arrangement
Symbols Used On Servicing Diagrams
Open Apron Free Standing – APU Running
Open Apron Free Standing – APU Not Running
Two Passenger Gangways – Parallel – APU Running
Three passenger Gangways – Nose In – APU Not Running
Three passenger Gangways – Double Parallel – APU Running
Open Apron Free Standing – APU Running
Three Passenger Gangways – Nose In – APU Running
Terminal Operation
Turnround Station (30 Minutes – 1 Door Open)
Turnround Station (30 Minutes – 2 Doors Open)
Turnround Station (30 Minutes – 3 Doors Open)
Turnround Station (30 Minutes – Freight Mode)
Terminal Operation
Enroute Station (20 Minutes – 3 Doors Open)
Ground Service Connections
Ground Service Connections Data
Ground Service Connections Layout
Hydraulic System
Electrical System
Oxygen System
Fuel System
Pneumatic System
Oil System
Potable Water System
Toilet System
Engine Starting Pneumatic Requirements
Ambient Temperature —40°F (—40°C)
Ambient Temperature +60°F (+15°C)
Ambient Temperature +100°F (+38°C)
Ground Pneumatic Power Requirements
Heating (U.S Units)
Heating (Metric Units)
Cooling (U.S Units)
Cooling (Metric Units)
Preconditioned Airflow Requirements
(U.S Units)
(Metric Units)
Ground Towing Requirements
(U.S Units)
(Metric Units)
T.O.C.
Page 3
DEC 01/09
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A300
TABLE OF CONTENTS
6.0
6.1
6.1.1
6.1.2
6.1.3
6.1.4
6.1.5
6.1.6
6.1.7
6.1.8
6.1.9
6.1.10
6.1.11
6.1.12
6.2
6.2.1
6.2.2
6.2.3
6.3
6.3.1
6.3.2
6.3.3
6.3.4
OPERATING CONDITIONS
Jet Engine Exhaust Velocities and Temperatures
Exhaust Velocity Contours – Breakaway Power (U.S Units)
Exhaust Velocity Contours – Breakaway Power (Metric Units)
Exhaust Temperature Contours – Breakaway Power (U.S Units)
Exhaust Temperature Contours – Breakaway Power (Metric Units)
Exhaust Velocity Contours – Takeoff Power (U.S Units)
Exhaust Velocity Contours – Takeoff Power (Metric Units)
Exhaust Temperature Contours – Takeoff Power (U.S Units)
Exhaust Temperature Contours – Takeoff Power (Metric Units)
Exhaust Velocity Contours – Idle Power (U.S Units)
Exhaust Velocity Contours – Idle Power (Metric Units)
Exhaust Temperature Contours – Idle Power (U.S Units)
Exhaust Temperature Contours – Idle Power (Metric Units)
Airport and Community Noise
External Noise
Noise Data
APU Noise Levels
Danger Areas of the Engines
Danger Areas Forward of the Engines (Ground Idle)
Danger Areas Forward of the Engine (Takeoff)
Acoustic Protection Areas
APU — Exhaust GAS Temperature and Velocity
T.O.C.
Page 4
DEC 01/09
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A300
TABLE OF CONTENTS
7.0
PAVEMENT DATA (CONTENTS)
7.1
General Information
7.2
Landing Gear Frootprint
7.3
Maximum Pavement Loads
7.4
Landing Gear Loading on Pavement
7.4.1
Model B2/B2K
7.4.2
Model B4/C4
7.5
Flexible Pavement Requirements U.S Corps of Engineers Design Method
7.5.1
Model B2
7.5.1.1
137T Standard Tires (46x46—20”)
7.5.1.2
137T Optional Tires (49x17—20”)
7.5.1.3
7.5.1.4
7.5.2
Model B2K
7.5.2.1
7.5.2.2
7.5.3
Model B4
7.5.3.1
7.5.3.2
7.5.3.3
7.5.3.4
7.5.3.5
157.5T Standard Tires (46x16—20”)
7.5.3.6
157.5T Optional Tires (49x17—20”)
7.5.3.7
7.5.3
Model B4/C4
7.5.3.8
7.5.3.9
165T Optional Tires (49x17—20”) Landing Gear Geometry
7.5.3.10
T.O.C.
Page 5
DEC 01/09
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A300
TABLE OF CONTENTS
7.6
Flexible Pavement Requirements L.C.N Conversion
7.6.1
Model B2
7.6.1.1
7.6.1.2
7.6.1.3
7.6.1.4
7.6.2
Model B2K
7.6.2.1
7.6.2.2
7.6.3
Model B4
7.6.3.1
7.6.3.2
7.6.3.3
7.6.3.4
7.6.3.5
7.6.3.6
7.6.3.7
7.6.3
Model B4/C4
7.6.3.8
7.6.3.9
7.7
Rigid Pavement Requirements — Portland Cement Association
7.7.1
Model B2
7.7.1.1
7.7.1.2
7.7.1.3
7.7.1.4
7.7.2
Model B2K
7.7.2.1
7.7.2.2
7.7.3
Model B4
7.7.3.1
7.7.3.2
7.7.3.3
7.7.3.4
7.7.3.5
7.7.3.6
7.7.3.7
7.7.3
Model B4/C4
7.7.3.8
7.7.3.9
165T Optional Tires (49x17—20”) Landing Gear Geometry
7.7.3.10
T.O.C.
Page 6
DEC 01/09
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A300
TABLE OF CONTENTS
7.7.4.1
Radius of Relative Stiffness
7.7.4.2
Values of E and μ
7.7.4.3
Effect of E and μ on 1 Values
7.8
Rigid Pavement Requirements L.C.N Conversion
7.8.1
Model B2
7.8.1.1
7.8.1.2
7.8.1.3
7.8.1.4
7.8.2
Model B2K
7.8.2.1
7.8.2.2
7.8.3
Model B4
7.8.3.1
7.8.3.2
7.8.3.3
7.8.3.4
7.8.3.5
7.8.3.6
7.8.3.7
7.8.3
Model B4/C4
7.8.3.8
7.8.3.9
7.9
Aircraft Classification Number – ACN Flexible and Rigid Pavement
7.9.1
Flexible Pavement Model B2
7.9.1.1
7.9.1.3
7.9.1.4
7.9.2
Flexible Pavement Model B2K
7.9.2.1
7.9.2.2
7.9.3
Flexible Pavement Model B4
7.9.3.1
7.9.3.2
7.9.3.3
7.9.3.4
7.9.3.5
7.9.3.6
7.9.3.7
7.9.3
Flexible Pavement Model B4/C4
7.9.3.9
7.9.3.10
T.O.C.
Page 7
DEC 01/09
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A300
TABLE OF CONTENTS
7.9.4
7.9.4.1
7.9.4.3
7.9.4.4
7.9.5
7.9.5.1
7.9.5.2
7.9.6
7.9.6.1
7.9.6.2
7.9.6.3
7.9.6.4
7.9.6.5
7.9.6.6
7.9.6.7
7.9.6
7.9.6.9
7.9.6.10
7.9.7
Rigid Pavement — Model B2
Rigid Pavement — Model B2K
Rigid Pavement — Model B4
Flexible Pavement — Model B4/C4
Development of ACN Charts (for example)
R
R
8.0
8.1
DERIVATIVE AIRPLANE
Possible Future A300 Derivative Airplanes
R
R
R
9.0
9.1.1
9.2.1
SCALED DRAWINGS
A300 Scaled Drawing 1 in. = 500 ft.
A300 Scaled Drawing 1 cm. = 500 cm.
T.O.C.
Page 8
DEC 01/09
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A300
R 1.0
SCOPE
R
1.1
Purpose
R
1.2
Introduction
Chapter 1.0
Page 1
DEC 01/09
R
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A300
1.1 Purpose
The A300 AIRPLANE CHARACTERISTICS (AC) manual is issued for the
A300 basic versions to provide the necessary data needed by airport
operators and airlines for the planning of airport facilities.
This document conforms to NAS 3601.
CORRESPONDENCE
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
Chapter 1.1
Page 1
DEC 01/09
R
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A300
1.2 Introduction
This manual comprises 9 chapters with a List of Effective Pages (LEP) and a
Table Of Content (TOC) at the beginning of the manual.
Chapter 1 : SCOPE
Chapter 2 : AIRPLANE DESCRIPTION
This chapter contains general dimensional and other basic aircraft data.
It covers :
— aircraft dimensions and ground clearances,
— passengers and cargo compartments arrangement.
Chapter 3 : AIRPLANE PERFORMANCE
This chapter indicates the aircraft performance.
It covers
— payload
— takeoff
— landing
:
range,
and landing runway requirements,
approach speed.
Chapter 4 : GROUND MANEUVERING
This chapter provides the aircraft turning capability and maneuvering
characteristics on the ground.
It includes :
— turning radii and visibility from the cockpit,
— runway and taxiway turn path.
Chapter 5 : TERMINAL SERVICING
This chapter provides information for the arrangement of ground handling
and servicing equipments.
It covers :
— location and connections of ground servicing equipment,
— engines starting pneumatic and preconditioned airflow requirements.
Chapter 1.2
Page 1
DEC 01/09
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A300
Chapter 6 : OPERATING CONDITIONS
This chapter contains data and safety/environmental precautions related to
engine and APU operation on the ground.
It covers :
— contour size and shape of the jet engine exhaust velocities and
temperature,
— noise data.
Chapter 7 : PAVEMENT DATA
This chapter contains the pavement data helpful for airport planning.
It gives :
— landing gear foot print and static load,
— charts for flexible pavements with Load Classification Number (LCN),
— charts for rigid pavements with LCN,
— Aircraft Classification Number (ACN), Pavement Classification Number
(PCN), reporting system for flexible and rigid pavements.
Chapter 8 : DERIVATIVE AIRPLANES
This chapter gives relevant data of possible new version with the
associated size change.
Chapter 9 : SCALED DRAWING
This chapter contains different A300 scaled drawings.
Chapter 1.2
Page 2
DEC 01/09
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A300
R 2.0 AIRPLANE DESCRIPTION
2.1 General Airplane Characteristics
R
2.1.1 General Airplane Characteristics Data
R
2.2 General Dimensions
2.3 Ground Clearances
R
2.4 Interior Arrangement
2.4.1 Basic Version
2.4.2 Basic High Density Version
2.4.3 Basic Upper Deck Configuration
2.4.4 Optional Upper Deck Configuration
2.5 Passenger Cabin Cross Section
2.5.1 Seating Configuration – 6 Abreast – First Class
2.5.2 Seating Configuration – 8 Abreast – Tourist Class
2.5.3 Seating Configuration – 9 Abreast – Charter Operation
2.6 Lower Compartment
2.6.1 Weight and Volume Data
2.6.2 Containers
2.6.3 Pallets
2.7 Upper Deck Cargo
2.8 Door Clearances
2.8.1 Forward Passenger Door
2.8.2 Middle Passenger Door
2.8.3 AFT Passenger Door
2.8.4 Forward Cargo Compartment Door
2.8.5 Upper Deck Cargo Door
2.8.6 AFT Cargo Compartment Door
2.8.7 Bulk Cargo Compartment Door
2.8.8 Radome Travel
2.8.9 Main Landing Gear Door
Chapter 2.0
Page 1
DEC 01/09
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A300
2.1 General Airplane Characteristics
The weight terms used throughout this manual are given below together with
their respective definitions.
Maximum Taxi Weight (MTW) :
Maximum weight for ground maneuver as limited by aircraft strength and
airworthiness requirements. (It includes weight of run—up and taxi fuel).
It is also called Maximum Ramp Weight (MRW).
Maximum Landing Weight (MLW) :
Maximum weight for landing as limited by aircraft strength and
airworthiness requirements.
Maximum Takeoff Weight (MTOW) :
Maximum weight for takeoff as limited by aircraft strength and
airworthiness requirements. (This is the maximum weight at start of the
takeoff run).
Maximum Zero Fuel Weight (MZFW) :
Maximum operational weight of the aircraft without usable fuel.
Operational Empty Weight (OEW) :
Weight of structure, powerplant, furnishings, systems, and other items of
equipment that are an integral part of a particular aircraft configuration
plus the operator’s items.
The operator’s items are the flight and cabin crew and their baggage,
unusable fuel, engine oil, emergency equipment, toilet chemical and fluids,
galley structure, catering equipment, passenger seats and life vests,
documents, etc.
Maximum Payload :
Maximum Zero Fuel Weight (MZFW) minus Operational Empty Weight (OEW).
Maximum Seating Capacity :
Maximum number of passengers specifically certified or anticipated for
certification.
Maximum Cargo Volume :
Maximum usable volume available for cargo.
Usable Fuel :
Fuel available for aircraft propulsion.
Chapter 2.1
Page 2
DEC 01/09
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A300
Airplane version
A300B2—100
A300B2—200
WV001
WV002
WV003
WV002
WV001
WV003
(Basic)
137 900
142 900
134 900 142 900 137 900 134 900
304 017
Maximum Taxi
Weight (MTW)
kg
WV000
(Basic)
137 900
lb
304 017
Maximum Takeoff
Weight (MTOW)
kg
137 000
137 000
142 000
134 000
142 000
137 000
134 000
lb
302 032
302 032
313 056
295 419
313 056
302 032
295 419
315 040
297 403
315 040
304 017
297 403
Maximum Landing
Weight (MLW)
kg
127 500
130 000
130 000
130 000
130 000
130 000
130 000
lb
281 089
286 600
286 600
286 600
286 600
286 600
286 600
Maximum Zero Fuel
Weight (MZFW)
kg
116 500
120 500
120 500
120 500
120 500
120 500
120 500
lb
256 838
265 656
265 656
265 656
265 656
265 656
265 656
Estimated
Operational Empty
Weight (OEW)
Estimated
Maximum Payload
GE CF6—50
Standard Seating
Capacity
Usable
Fuel
Capacity
Pressurized
Fuselage Volume
(A/C non
equipped)
Passenger
Compartment
Volume
Cockpit
Volume
Usuable Cargo
Compartment
Volume (1)
GE CF6—50
85 910 kg (189 398 lb)
86 275 kg (190 203 lb)
kg
30 590
34 590
34 590
34 590
34 225
34 225
34 225
lb
67 439
76 257
76 257
76 257
75 453
75 453
75 453
Single—
class
l
269
269
44 000
44 000
11 623
11 623
35 540
35 540
78 352
78 352
542
542
19 140
19 140
m3
272
272
ft3
9 606
9 606
m3
17
17
ft3
600
600
m3
144
144
ft3
5 085
5 085
US Gallons
kg
(d=0.785)
lb
m3
ft3
(1) Volume of Cargo Compartments : Fwd Cargo Compartment
: 76 m3 (2 683 ft3)
Aft Cargo Hold Compartment : 49 m3 (1 730 ft3)
Bulk Cargo Compartment
: 19 m3 (670 ft3)
2.1 GENERAL AIRPLANE CHARACTERISTICS
2.1.1 GENERAL AIRPLANE CHARACTERISTICS DATA
Model B2
Chapter 2.1.1
Page 3
DEC 01/09
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A300
WV000
(Basic)
150 900
WV001
150 900
153 900
lb
332 677
339 291
349 211
349 211
332 677
339 291
Maximum Takeoff
Weight (MTOW)
kg
150 000
153 000
157 500
157 500
150 000
153 000
lb
330 693
337 306
347 227
347 227
330 693
337 306
Maximum Landing
Weight (MLW)
kg
133 000
133 000
133 000
134 000
133 000
134 000
lb
293 214
293 214
293 214
295 419
293 214
295 419
Maximum Zero Fuel
Weight (MZFW)
kg
122 000
122 000
122 000
124 000
122 000
124 000
lb
268 963
268 963
268 963
273 372
268 963
273 372
Estimated
Maximum Payload
GE CF6—50
Standard Seating
Capacity
Usable
Fuel
Capacity
Pressurized
Fuselage Volume
(A/C non equipped)
Passenger
Compartment
Volume
Cockpit
Volume
Usuable Cargo
Compartment
Volume (1)
88 180 kg (194 403 lb)
158 400
WV005
kg
GE CF6—50
158 400
WV004
Maximum Taxi
Weight (MTW)
Estimated
Operational Empty
Weight (OEW)
153 900
Airplane Version
A300B4—100
WV002
WV003
88 330 kg (194 734 lb)
88 180 kg (194 403 lb)
kg
33 820
33 820
33 670
35 670
33 820
35 820
lb
74 560
74 560
74 229
78 638
74 560
78 969
single—
class
l
269
58 100
US Gallons
kg
(d=0.785)
lb
15 348
45 608
100 548
m3
542
ft3
19 140
m3
272
ft3
9 606
m3
17
ft3
600
m3
144
ft3
5 085
: 76 m3 (2 683 ft3)
: 19 m3 (670 ft3)
Model B4
2.1.1
Page 4
DEC 01/09
R
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A300
WV013
Maximum Taxi
Weight (MTW)
kg
lb
332 677
349 211
332 677
339 291
365 740
365 740
349 211
Maximum Takeoff
Weight (MTOW)
kg
150 000
157 500
150 000
153 000
165 000
165 000
157 500
lb
330 693
347 227
330 693
337 306
363 760
363 760
347 227
Maximum Landing
Weight (MLW)
kg
134 000
134 000
134 000
134 000
134 000
136 000
134 000
lb
295 419
295 419
295 419
295 419
295 419
299 828
295 419
Maximum Zero Fuel
Weight (MZFW)
kg
126 000
126 000
126 000
126 000
124 000
126 000
124 000
lb
277 782
277 782
277 782
277 782
273 372
277 782
273 372
Estimated
Operational Empty
Weight (OEW)
Estimated
Maximum Payload
GE CF6—50
Standard Seating
Capacity
Usable
Fuel
Capacity
Pressurized
Fuselage Volume
(A/C non equipped)
Passenger
Compartment
Volume
Cockpit
Volume
Usuable Cargo
Compartment
Volume (1)
GE CF6—50
150 900
Airplane Version
A300B4—100
A300B4—200
WV014
WV015
WV016
WV006
WV007
WV008
(Basic)
158 400 150 900 153 900 165 900 165 900 158 400
88 180 kg
88 330 kg
88 180 kg (194 403 lb)
(194 403 lb) (194 734 lb)
88 505 kg (195 119 lb)
kg
37 820
37 670
37 820
37 820
35 495
37 495
35 495
lb
83 378
83 048
83 378
83 378
78 252
82 662
78 252
single—
class
l
US Gallons
kg
(d=0.785)
lb
269
269
58 100
62 000
15 348
16 380
45 608
48 470
100 548
107 299
m3
542
542
ft3
19 140
19 140
m3
272
272
9 606
9 606
17
17
ft3
600
600
m3
144
144
5 085
5 085
ft3
m3
ft3
: 76 m3 (2 683 ft3)
: 19 m3 (670 ft3)
Model B4
2.1.1
Page 4A
DEC 01/09
N
Printed in France
A300
WV014
158 400
Airplane Version
A300B4—200
WV016
WV017
153 900
148 400
Maximum Taxi
Weight (MTW)
kg
WV010
158 400
lb
349 211
349 211
339 291
327 165
365 740
349 211
Maximum Takeoff
Weight (MTOW)
kg
157 500
157 500
153 000
147 500
165 000
157 500
lb
347 227
347 227
337 304
325 181
363 760
347 227
Maximum Landing
Weight (MLW)
kg
136 000
134 000
140 000
136 000
134 000
134 000
lb
299 828
295 419
308 650
299 828
295 419
295 419
Maximum Zero Fuel
Weight (MZFW)
kg
126 000
126 000
130 000
126 000
126 000
126 000
lb
277 782
277 782
286 600
277 782
277 782
277 782
Estimated
Operational Empty
Weight (OEW)
Estimated
Maximum Payload
GE CF6—50
Standard Seating
Capacity
Usable
Fuel
Capacity
Pressurized
Fuselage Volume
(A/C non equipped)
Passenger
Compartment
Volume
Cockpit
Volume
Usuable Cargo
Compartment
Volume (1)
GE CF6—50
WV018
165 900
WV020
158 400
88 505 kg (195 119 lb)
kg
37 495
37 495
35 495
37 495
37 495
37 495
lb
82 662
82 662
78 252
82 662
82 662
82 662
single—
class
l
269
62 000
US Gallons
kg
(d=0.785)
lb
16 380
48 470
107 299
m3
542
ft3
19 140
m3
272
ft3
9 606
m3
17
ft3
600
m3
144
ft3
5 085
: 76 m3 (2 683 ft3)
: 19 m3 (670 ft3)
Model B4
2.1.1
Page 4B
DEC 01/09
N
Printed in France
A300
Maximum Taxi
Weight (MTW)
kg
Airplane Version
A300C4—200
WV006 (Basic)
WV007
165 900
165 900
A300F4—200
WV007 (Basic)
165 900
lb
365 740
365 740
365 740
kg
165 000
165 000
165 000
lb
363 760
363 760
363 760
Maximum Landing
Weight (MLW)
kg
134 000
136 000
136 000
lb
295 419
299 828
299 828
Maximum Zero Fuel
Weight (MZFW)
kg
124 000
126 000
126 000
lb
273 372
277 782
277 782
Maximum Takeoff
Weight (MTOW)
Estimated
Operational Empty
Weight (OEW)
Estimated
Maximum Payload
GE CF6—50
Standard Seating
Capacity
Usable
Fuel
Capacity
Pressurized
Fuselage Volume
(A/C non equipped)
Passenger
Compartment
Volume
Cockpit
Volume
Main Deck Cargo
Compartment Volume
Usuable Cargo
Compartment
Volume (1)
GE CF6—50
88 505 kg (195 119 lb)
84 000 kg (185 188 lb)
kg
35 495
37 495
42 000
lb
78 252
82 662
92 594
single—
class
l
269
4
62 000
62 000
16 380
16 380
48 670
48 670
107 299
107 299
m3
542
542
ft3
19 140
19 140
m3
272
ft3
9 606
US Gallons
kg
(d=0.785)
lb
m3
17
17
ft3
600
600
m3
540
10 069
ft3
m3
158
158
ft3
5 579
5 579
: 76 m3 (2 683 ft3)
: 21 m3 (741 ft3)
Model C4 — F4
2.1.1
Page 4C
DEC 01/09
N
Printed in France
AIRBUS
INDUSTR
IE
A 300
AIRPLANE CHARACTERISTICS
CHAPTER
2.3
2.2
Feb.
1980
GENERAL DIMENSIONS
MODEL B2 - B4
Chapter
Page
2
5
AIRBUS
INDUSTR
IE
CHAPTER
2.3
2.2
Chapter
Page 6
GENERAL DIMEXSIONS
NODEL C4
2
Feb.
1980
A300
NOTE : The distances given in the Ground Clearances charts are reference
distances calculated for A/C weight and CG conditions.
The conditions used in the calculations are maximum A/C weight
(minimum ground clearances) and a typical A/C maintenance weight
(typical ground clearances for maintenance).
Chapter 2.3
Page 7
DEC 01/09
R
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A300
Model B2
Chapter 2.3
Page 7A
DEC 01/09
N
Printed in France
A300
Model B2 – B4
Chapter 2.3
Page 8
DEC 01/09
R
Printed in France
A300
Model C4
Chapter 2.3
Page 9
DEC 01/09
R
Printed in France
AIRBUS
INDUSTR
IE
281 SEATS TOURIST CLASS
34 IN. PITCH, 8 ABREAST, 2-2/2-2
0
%
0
7 II
8
A
_ es
G
T
-r
0
$
ATTENDANT SEAT (FOL *DING)
CREW COAT STORAGE
GALLEY
TOILET
In
a
u
2.4
chapter
2
Page 10
INTERIOR
ARRANGEMENT
2.4.1
BASIC VERSION
MODEL B2 - B4 - C4
Feb.
1980
AIRBUS
INDUSTR
IE
A 300
309 SEATS TOURIST CLASS
31 IN. PITCH, 8 ABREAST, 2 -2m2
A
0
ccs
8
‘CT
0
G
-j-
2
ATTENDANT SEAT (FOLDING)
CREW COAT STORAGE
GALLEY
TOILET
In
u
a
2.4-2
Feb.
1980
2.4 INTERIOR
ARRANGEPENT
BASIC HIGH DENSITY VERSION
MODEL B2 - B4 - C4
Chapter
Page
2
11
INDUSTR
IE
281 seats
A variety
the seat
of seating
rails
The aircraft
or
configuration
floor
support
is certificated
is possible
without
modifications
to
structure.
for the carriage
of up to 345
passengers.
Mixed pallets
88”’ x 125’
96” x 125
The above
Either
01
88”
to 09.
figure
x 125”
Only
2.4
2.4.3
Chapter
2
Page 12
shows
the numbering
or 96”
88”
x 125”
x 125”
pallets
of the pallet
pallets
positions
can be loaded
can bc loaded
in tk
cabin.
in any positioli
in position
from
10 to 13.
INTERIOR
ARRANGEMENT
BASIC UPPER DECK CONFIGURATIONS
MODEL C4
Feb.
1980
AIRBUS
INDUSTR
IE
A
AlRPLANE CHARACTERISTICS
Confiiumtion
14palk
88-x
1
125’
Configuration 2
75seats
9paHets 88'" x 125’”
p‘
0
cr
0
n~gu~tion 3
145 seats
6patiets 88" x 125”
hr
0
In
a
a
2.4.4
Feb.
1980
2.4 INTERIOR
ARRANGEMENT
OPTIONAL UPPER DECK CONFIGURATIONS
MODEL c4
Chapter
Page
2
13
AIRBUS
INDUSTR
IE
A 300
3.84
t- 0.098
IN.
M.
In
a
a
2.5
2.5.1
Chapter
2
Page 14
SEATING
PASSENGER CABIN CROSS SECTION
CONFIGURATION
- 6 ABREAST - FIRST
MODEL B2 - B4 - C4
CLASS
Feb.
1980
INDUSTR
IE
0
I
,97.63 IN.
E
.-
-a
0
.-E
h
2.48
M.
1 IN.
i--%# I. “2
111,.
I
IN.
M.
2.46
M.
0
2
0
2
In
a
a
2.5.2
Feb.
1980
2.5
SEATING
PASSENGER CABIN CROSS SECTION
CONFIGURATION
- 8 ABREAST - TOURIST
HODEL B2 - B4 - C4
CLASS
Chapter
Page
2
15
AIRBUS
INDUSTR
A
IE
300
2.48
M. I
T
43.3
\
2.5.3
Chapter
2
Page 16
SEATING
2.5 PASSENGER CABIN CROSS SECTION
CONFIGURATION
- 9 ABREAST - CIIARTER
IlODEL B2 - B4 - C4
IN.
OPERATION
Feb.
1980
AIRBUS
INDUSTR
IE
FWD HOLD
Maximum Volume
Containers
AFT HOLD
TOTAL
BULK HOLD
Capacity
in Forward
and Aft
12 LD3
Containers
8 LD3
Containers
6 LDl
Containers
4 LDl
Containers
Holds
EACH
TOTAL
EACH
TOTAL
Pallets
in Forward
4
Pallets
Hold and Container
8 LD3
Containers
in Aft
Hold
EACH
l-==--l
35.76
TOTAL
10280
4
Pallets
22640
4 LDl
Containers
EACH
TOTAL
2.6 LOWER COMPARTMENTS
2.6.1 WEIGHT AND VOLUME DATA
MODEL B2 - B4 - C4
Feb.
198C
Chapter 2
Page 17
INOUSTR
IE
CARGO DOORS AND
BULK CARGO DOOR
R H SIDE
Compt
Ciimpt
64lN.
(1.63M.
I
2.6
LOWER COM?ARTMENTS
2.6.2
CONTAINERS
PllODEL B2 - B4 - C4
Chapter
2
Page 18
Feb.
1980
AIRBUS
INDUSTR
IE
AFTER MCD. 2295
A:2.70m(106in.)
4 PALLETS FRONT HOLD ONLYENTRY DOOR R H SIDE
64 IN.
1.63 M.
I
a a
2.6
LOWER COMPARTMENTS
2.6.3
PALLETS
MODEL B2 - 84 - C4
K
JuL
31/82
Chapter
Page
2
19
AIRBUS
Q
INOUSTR
IE
300
PERMISSIBLE
CARGO HEIGHT
LOCAL FLOOR LOADS
0 DOOR FORWARD LH SIDE
87.5in
= 2.222M.
86. Sin
= 2.197M.
0
79. Oin
a
a
64. Oin
= 2.006M.
= 1.625M.
0
0
0
The permissible
z
based
t-u
0
The reinforced
\n
a
floor
on a pallet
floor
will permit pallets
to be loaded.
a
2-7.
Chapter
2
Page 20
loading
width
of
structure
weighing
is,as
shown,
125in.
over the wing
13,3001b/6,
box
03OKg
UPPER DECK CARGO
MODEL C4
Feb.
1980
AIRBUS
INDUSTR
AIRPLANE
CRITICAL
CLEARANCE
LIMIT
-
IE
CHARACTERISTICS
\
.
33.4 IN
0.87M
SEE CHAPTER
2.3
2.8.1
Mar.
1986
I
I
II
/
2.8 DOOR CLEARANCES
FORWARD PASSENGER DOOR
MODEL B2 - B4 - C4
Chapter
Paqe
2
21
A
AIRPLANE
CHARACTERlSTICS
OF FUSELAGE
-_-_
~-_
CRITICAL
CLEARANCE
--I
-----v-1.
-----.s-____
---w------“---T.---------3
52 FT.
0.4
IN.
FROM NOSE OF FUSE
42FT. 19 8 IN.
13. 08fd.
FROM
NOSE OF
FUSELAGE
SEE
CHAPTER
2.
1
I
I
-
I
21.4 IN
I0.54M.
132 IN
3.36M.
2.8 DOOR CLEARANCES
2.8.2
MIDDLE PASSENGER DOOR
XODEL B2 - B4 - C4 G. E. ENGINES
Chapter
2
Page 22
I
Feb.
1980
AIRBUS
INDUSTR
IE
OF FUSELAGE
--e------
ol
I
-m---e-
’ 30.7 IN
0.78M
92.5
l-2.3%
IN
1lF-r. 7.5 IN
3.54 ht.
CRITICAL
CLEARANCE
LlMlT
---.mm_
-----...-L,,,,e--m
---.,,-et--------
52FT.
---.W--
-,..w’
4.3
15.96
M.
FROM NOSE OF FUSELAGE 1
i
ri
0
:
0
$
co
0
N
0
In
a
a
FROM
NOSE OF
FUSELAGE
c
nm
132 IN
3.36M.
,
2-8 DOOR CLEARANCES
2.8.2
MIDDLE PASSENGER DOOR
XODEL B2 - B4 - C4 P.& W, ENGINES
Feb.
1980
Chapter
Page
2
23
AIRBUS
INDUSTR
IE
A30
I
I
I
C ---------P---+.mP
I
I
5
I
II
I
CRITICAL
CLEARANCE
LIMIT
30.7 IN
0.78M
FROM NOSE
OF FUSELAGE
130 FT 6.1 IN
39.78M
1
1.8 IN
0.045M
oa
5s
CHAPTER
2.3
I
I
21.4 IN
0.64M
aa
2.8 DOOR CLEARANCES
2-8.3
AFT PASSENGER DOOR
MODEL B2 - B4 - C4
Chapter
2
Page 24
Mar,
1986
INDUSTR
AIRBUS
IE
t-
A
FROM NOSE
FORWARD
I
Q
.
; DOOR
FWD PASSENGER/CREW
I
I
A
= 94OOmm(370in.I
1830111m
(72in.)
A’ =
B = 2430mm
B’ = 610mm
(96in.I
(24in. 1
= 368Onnn Q45in)
D = 3600mm (142in 1
C
AFTER
A
MOD. 2295
= 9533mm
A’ =
(375in.l
1697mm (67in)
B = 2701mm
B’ = 345mm
(13.6in
c
(14Oin. )
= 3547mm
D = 3467mm
(106in.1
(135in.
1
2.8 DOOR CLEARANCES
2.8.4
Jut
31/82
FORWARD CARGO COMPARTXNT
MODEL B2 - 84 - C4
DOOR
Chapter
Page
2
25
AIRBUS
INDUSTR
IE
A30
-----
me--
--m----
OF FUSELAGE -a---_
I
I
32 FT. 7 IN.
9.93 M
FROM NOSE OF FUSELAGE
FROM NOSE OF FUS
/
I
:
I
I
\
--e-w---
In
1
a
a
2.8.5
Chapter
2
Page 26
2.8.
DOOR CLEARAXCES
UPPER DECK CARGO DOOR
MODEL C4 G, E. ZXGINES
Feb.
1930
AIRBUS
INDUSTR
IE
A
AIRPLANE
----e-w--
RISTIGS
--m----
OF FUSELAGE --w--_
52 R. 4.3
IS. 96 M.
FROM NOSE OF FUS
i
I
CHAPTER
2.8.
DOOR CLEARAXES
2.8.5
UPPER DECK CARGO DOOR
MODEL C4 P.& W. ENGIZES
Feb.
1980
Chapter
Page
2
27
INDUSTR
IE
---e-w-
Q
-I
OF FUSELAGE
- -
-
w
t
I
DIRECTION OF FLIGHT
‘O;y;;z
IN
0
t--
AFT ENTRY DOOR
I
I
AFT CONTAINER
I
0
3
0
8
1
03
0
16.34
IN.
0.415
M
z
u-l
a
a
2.8.6
Chapter
2
Page 28
2.8 DOOR CLEARANCES
AFT CARGO COMPARTMENT DOOR
MODEL B2 - B4 - C4
act
1980
AIRBUS
NDUSTR
A
0
AIRPLANE
-----
CTERISTICS
OF FUSELAGE
I----
IE
1;::‘;“”
-
- --
DIRECTION OF FLIGHT f$~
AFTENTRYDOOR
AFT CONTAINER CARGO DOOR
I
Ill
a
a
0.95
2.8.7
Feb.
1980
M
2.8 DOOR CLEARANCES
BULK CARGO COMPARTMENT DOOR
MODEL B2 - B4 - C4
Chapter
Page
2
29
@A300
AIRPLANE
CHARACTERISTICS
STA 7662.5
/-
-----
CE
‘t-
‘,
\
I
-be,-
\
v\
\
\ \
\ \
.
I’\
I
2.8 DOOR CLEARANCES
2.8.8
RADOME TRAVEL
Chapter
2
Page 30
Apr
Printed in France
1995
@A300
AIRPLANE
CHARACTERISTICS
000000000
23785 mm
936.4 in
AIRCRAFT
8
s
8
2.8.9
Apr
2.8 DOOR CLEARANCES
MAIN LANDING GEAR DOOR
Chapter
Page
1995
Printed in France
2
31
CDA300
THIS
Chapter
Page 32
PAGE LEFT
BLANK
INTENTIONALLY
2
Apr
Printed in France
1995
INDUSTR
AIRBUS
A
I E
300
3.0
3.1
3.2
3.2.1
3.2.2
3.3
3.3.1
3.3.2
3.3.3
3.3.4
3.4
3.4.1
3.4.2
3.4.3
3.5
3.5.1
3.5.2
Feb.
AIRPLANE PERFORMANCE
General information
Payload range
Long range and recommended cruise
(U.S. units)
Long range and recommended cruise
(Metric
units)
FAR takeoff
runway length
requirements
ISA conditions
- Alternate
(U.S. units)
(Metric
units)
ISA conditions
- Alternate
ISA conditions
+59OF (+15OC) - Alternate
(U.S. units)
ISA conditions
+59OF (+15'C) - Alternate
(Metric
units)
FAR landing
runway requirements
Full.flaps
(U.S. units)
Full flaps
(Metric
units)
Full flaps
Landing approach speed
Landing approach speed (Metric
units)
Landing
approach speed (U.S. units)
1980
Chapter
3
Page 1
AIRBUS
INDUSTR
IE
A 300
3.0
AIRPLANE
3.1
PERFORMANCE
General
Information
Section
3.2 indicates
payload
range information
altitudes
for recommended and long range cruise
ven fuel reserve
condition.
at specific
with a gi-
Section
3.3 represents
FAR Takeoff
runway lenqth
ments at ISA and ISA + 59°F (+ 15°C) conditions
certification.
requirefor FAA
Section
3.4 represents
FAR landing
ments for FAA certification.
Section
3.5
indicates
landing
Standard
day temperatures
lated below :
Chapter
Page 2
3
for
runway
approach
the
length
require-
speeds.
altitudes
shown are
Feb.
tabu-
1980
1
13
zz
0
W
or
CI
V
k.l
.
CI
W
BASIC kRSi0N’
I
I
I
5 % STAGE FUEL
3o t FUEL RESERVE
200 NAUTICAL MILES DiVERSI
40
50
60
70
80
90
AA5030201OAAO
’
I
I
I
I
RANGE (NAiJTICAL MILES)
I
NOTE :
I
I
in France
I
I
I
I
I
I
I
I
I
I
I
I
I
I 1
b
THESE CURVES ARE GIVEN FOR INFORMATION ONLY.
THE APPROVED VALUES ARE STATED IN THE “OPERATING
MANUALS” SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
Printed
b
-
I--
.
80)
5”/.STACEFUEL
BASIC VERSION
MAX SiRUCTUdAL
PAYiOAD
A A 5 03 02 01 0 AB 0
--i
I
I
RANGE (NAUTICAL
I
I
I
MILES)
NOTE :
I
Printed
I
in France
I
I
I
I
I
I
I
THE APPROVED VALUES ARE STATED IN TH’E “OPERATING
m
a
a:
ea
a
a
I
I
U!
I
I
pWl!ld
I
‘lzlW3tllV
3Hl 3NllVtJ3dO
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03hOtlddV
3Hl
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(S3liW
I
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I
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09
08
200 NAUTICAL MILES
A A 5 03 02
01 0
AD 0
RANGE (NAUTICAL
MILES)
NOTE :
Printed
in France
AIRBUS INDUSTR
IE
300
ii2
gN
6c!
z!z
-.
-c
f
.
;
t
-:
f
,
c
-;
‘
1
:.
In
a
a
3,2-l
Feb.
1980
”
/-
<
-
3.2 PAYLOAD RANGE
LONG RANGE AND RECOMMENDED CRUISE
MODEL B4-102
(U,S.
UNITS)
Chapter
Page
3
7
200 NAUTICAL MILES
A A 5 03 02 01 0 AF 0
RANGE (NAUTICAL
MILES)
NOTE :
Printed
500
in France
3000
3500
4000
D
m
v)
B
a
zi
co
E
C
m D
W
aJ
0
w
c,
L
e
W
80
5 % STAGE FUEL
200 NAUTICAL MILES
A A 5 03 02 01 0 AG 0
RANGE (NAUTICAL
MILES)
NOTE :
in France
Printed
m
(
11
2(
3(
4(
I3
61
7(
8(
9(
5”/.STACEFUEL
I
I
MAX STRUCTURAL
200 NAUTICAL MILES DIVERSION
FUEL RESERVE
BASIC VERSION
AA5030201OAHO
RANGE (NAUTICAL
I
PAYLOAD
MILES)
NOTE :
Printed
in France
I
I
1
I
.ITtb,., ,-Bee Ye?,-. . m.
m
h)
N
e
W
.
3a
15
s’ 25
c3
%
$ 2a
3
Q
35
5 5: STAGE FUEL
FUEL RESERVE
A A 5 03 02 02 0 AA 0
in France
RANGE (KILOMETERS)
NOTE :
Printed
5
10
15
20I
25
30
35
BASIC VERSION
FUEL RESERVE
.I MAX SiRUCTURiiL
40
45
PAYLbAD
A A 5 03 02 02 0 A0 0
1.1
Printed
in France
RANGE (KILOMETERS)
i
NOTE :
0
5
10
0
1000
5 % STAGE FUEL
2000
, -,r!rr,Jll,‘r.r!,r,.l,r,!rII~
PAYLOAD WITH ,MAX FUEL CAPAFITY
i
BASIC VERSION
15
20
25
30
35
4c
45i
A A 5 03 02 02 0 AC 0
3000
in France
5000
6600
I
I
7000
8000
RANGE (KILOMETERS)
4000
NOTE :
Printed
w
.
h)
.
N
8
0
r!
0
Y
I
5 % STAGE FUEL
FUEL RESERVE
AA5030202OADO
I
I
I
I
I
Printed
I
I
in France
I
MIUW,
(150,000
KGJ
I I
RANGE (KILOMETERS)
I
NOTE :
0
5
10
15
2c
2:
3t
3E
4c
4t
I
---..^-..-a.
-
1000
45 MINUTE HOLD AT
5 % STAGE FUEL
BASIC VERSION
FUEL RESERVE
,...
-...
-_-
A A 5 03 02 02 0 AE 0
2000
3000
I
in France
5000
6000
7000
8000
RANGE (KILOMETERS)
4000
NOTE :
Printed
3
:
'
2
s
2
a.
20
25
30
45 MINUTE HOLD AT 1,525
5 % STAGE FUEL
AYLOAO
M
WITH
A A 5 03 02 02 0 AF 0
MAX
FU
Printed
in France
THESE CURVES ARE GIVEN FOR INFORMATION ONLY,
THE APPROVE0 VALUES ARE STATE0 IN THE “OPERATING
RANGE (KILOMETERS)
NOTE :
N
N
*
W
.
03 02 02 OAG 0
5 % STAGE FUEL
BASIC VERSION
FUEL RESERVE
AA5
in France
5000
6000
7000
6000
RANGE (KILOMETERS)
000
NOTE :
Printed
5 % STAGE FUEL
FUELRESERVE
AA5030202OAHO
Printed
in France
RANGE (KILOMETERS)
NOTE :
m
b
INDUSTR
AIRBUS
IE
0
AIRPLANE
CHARACTERISTICS
NOTE : THESE CURVES ARE GIVEN FOR INFORMiTION
ONLY.
MANUALS”
SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
KVS MAXI
MY
340
Al RPORT
PRESSUfiL
ALTITUDE
\
330
s
2
IE
.9
320
-E
2
‘C
a
310
.’
(ft)
300
290
280
270
260
1
-’
250
/I
0
2
;
/
.’
/I
240
I/
/
I$
z
a
a
- - ---------
I
l/f
//
II
230
4
/
5
6
7
8
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
TYRE SPEED LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
9
10
RUNWAY
3.3
3.3.1
Feb.
1980
F.A.R.
I.S.A.
11
LENGTH
12
(lOOOft)
TAKEOFF RUNWAY LENGTH REQUIREMENTS
CONDITIONS
- ALTERNATE
(U.S.
UNITS)
PlODEL B2-101
Chapter
Page
3
19
AIRBUS
INDUSTR
IE
A 300
NOTE
: THESE CURVES ARE GIVEN FOR INFORMATION
ONLY.
MANUALS”
SPECIFIC TO THE AIRLINE OPERATING
THE AIRCRAFT.
36C
320
ALTITUDE
290
-
280
0
$
0
270
Ei
0”
0”
In
-
--
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
-- - RUNWAY/BRAKE
ENERGY LIMITATION
TYPE SPEED LIMITATION
-mm NO WIND
NO RUNWAY SLOPE
NO BLEED
2604
a
a
250,
3.3 F.A.R.
3.3.1
I.S.A,
Chapter
3
Page 20
CONDITIONS
- ATERNATE ( U.S.
UNITS )
MODEL B2-320
Feb.
1320
(ft)
AIRBUS
INDUSTR
AIRPLANE
NOTE
IE
CHARACTERISTICS
ONLY.
MANUALS”
ALTITUDE
--
a
a
5
6
7
8
--
9
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
10
RUNWAY
3.3
3.3-l
Feb.
1980
F.A.R.
I.S.A.
(ft)
11
12
LENGTH
13
(lOOOft)
CONDITIONS
- ALTERNATE (U.S,
UNITS)
MODEL B4-101
Chapter
Page
3
21
AIRBUS
INDUSTR
IE
A300
AIRPLANE CHARACTERlSTlCS
THESE CURVES ARE GIVEN FOR INFORMATION
ONLY.
MANUALS”
SPECIFIC
TO THE AIRLINE
OPERATING THE AIRCRAFT.
NOTE
360
ALTITUDE
(3 Oooft>
290
- - - -
280
0
9
0
0”
2
3
In
a
a
, ,
270
I
260
5
:
----
,’
I
-
RUNWAY LlMlTATlON
RUNWAY/2nd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
TYPE SPEED ~~I~~~ON
NO RUNWAY
NO BLEED
,I
1
6
7
8
9
10
RUNWAY
3.3 F.A.Rs
3.3.1
1-S-A.
Chapter
3
Page 22
II
LENGTH
12
SLOPE
13
(1 OOOft)
CONDITIONS
- ALTERNATE ( U.S. UNITS
MODEL B4-203 - C4
)
Feb.
1980
INDUSTR
AIRBUS
IE
NOTE
: THESE
CURVES
ARE GIVEN
FOR INFORMATION
ONLY.
THE APPROVED VALUES ARE STATED lN THE “OPERATING
A’
KVS MAXI
h
Es!
4L
3
AIRPORT
5
0
PRESSURE
-I
Y
II T,-rllhr ill11
,-\
AL I I I uut
--
/
‘?t=---/
/
----a
---m-s
-----a--.--
a
a
102
1.5
1.8
3.3 F.A.R.
3.3.2
I.S.A.
Feb.
1980
2.1
2.4
RUNWAY LIMITATION
RUNWAY/2nd SEGMENT LIMITATION
RUNWAY/BRAKE ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
2.7
3.0
3.3
3.6
RUNWAY LENGTH (1000m)
CONDITIONS
- ALTERNATE (METRIC UNITS)
MODEL B2-101
Chapter
Page
3
23
INDUSTR
IE
NOTE : THESE CURVES ARE GIVEN FOR 1NFORMATlON
ONLY.
MANUALS”
SPECIFIC TO THE AIRLINE
m
./
160
ALTITUDE
/-
1. 5
1. 8
3,3 F.A.R.
3.3.2
I.S.A,
Chapter
3
Page 24
-
-
--
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
-- - RUNWAY/BRAKE
ENERGY LIMITATION
-mm NO WIND
NO RUNWAY SLOPE
NO BLEED
3.0
3.3
RUNWAY
3.6
3.9
LENGTH (1000m)
CONDITIONS
MODEL B2 -320
Feb.
1980
(m>
AIRBUS
INDUSTR
IE
NOTE : THESE CURVES ARE GIVEN FOR INFORMATION ONLY,
FLAPS 15’
FLAPS 8’
c
..H----@
h
I”
.e-----=-
\
-------
Al RPbRT
PRESSURE
ALTITUDE (m)
- 0
B-----
2
3
2
In
a
a
1 5
1.8
2.1
2e4
2.7
RUNWAY LIMITATION
RUNWAY/2nd SEGMENT LIMITATION
RUNWAY/BRAKE ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
3.0
3.3
3.6
3.9
RUNWAY LENGTH (1000m)
3.3
3.3.2
Feb.
1980
F.A.R.
I.S.A.
TAKEOFF RUNWAY LENGTH REQUIREmNTS
CONDITIONS
MODEL 94-101
Chapter
Page
3
25
AIRBUS
INDUSTR
IE
A
NOTE : THESE CURVES ARE GIVEN FOR INFORMATION
ONLY.
MANUALS”
370
160
.
0
- - - -
130
-m
-..-
z
0
z
-
0”
$
In
a
120,
ALTITUDE
(m)
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATIO
NO WIND
NO RUNWAY SLOPE
NO BLEED
a
1.5
3.3
3.3.2.
Chapter
3
Page 26
1.8
F.A.R.
I.S.A.
2.
1
2.4
2.7
3.0
3.3
3.6
3.9
RUNWAY LENGTH (I OOOm)
CONDITIONS
MODEL B4-203
- C4
Feb.
1980
INDUSTR
AIRPLANE
NOTE
IE
0
CHARACTERISTICS
ONLY.
MANUALS”
KVS MAXI
\
340-1 a^
PRESSURE
ALTITUDE
(ft)
--v--m
i I!
/
---=a------II_
290
/‘!I
#z,
TYRE
IMITATION
nd SEGMENT LIMITATION
RAKE ENERGY LIMITATION
SPEED LIMITATION
NO WIND
NO RUNWAY
SLOPE
In
a
a
RUNWAY
3.3.3
Feb.
1980
3.3
I.S.A.
LENGTH
(lOOOft
F.A.R.
CONDITIONS
+59°F(+150C)
- ALTERNATE
(U.S.
MODEL B2-101
UNITS)
Chapter
Page
3
27
AIRBUS
INDUSTR
IE
ONLY.
MANUALS”
OPERATING THE AlRCRAFT.
\PRESSURE
ALTITUDE
-m__)
-se-
-
(ft)
RUNWAY LIMITATION
RUNWAYJ2nd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
In
a
a
5
3,3.3
6
8
3.3 F.A.R.
1,Sc.A.
CONDITIONS
+59°F(+150C)
- ALTERNATE (UeS.
MODEL B2-320
Chapter
3
Page 28
UNITS)
Feb.
1980
AIRBUS
INDUSTR
IE
A CHARACTERlSTlCS
300
AIRPLANE
NOTE
ONLY.
MANUALS”
PRESSURE
ALTITUDE
--m
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
------
5
6
7
8
9
10
RUNWAY
3a3.3
Feb.
1980
3.3
I.S.A.
(ft)
11
12
LENGTH
13
(1OOOft)
F.A.R.
CONDITIONS
+59°F(+150C)
- ALTERNATE
(U.S.
MODEL B4-101
UNITS)
Chapter
Page
3
29
AIRBUS
INOUSTR
IE
A 300
Al~PlANE CHARACTERM’ICS
NOTE
ONLY.
MANUALS”
OPERATING
THE AIRCRAFT-
370
‘LAPS
15
/
/I
/
/
1
’
/
1’
/
/I
r /
/
290
/
r
0
2
/I
,’
/
/I
1
’ ,’
1 I/
/I/
I//
“/
‘/
.//
270
0
g
2
0”
VI
a
a
I
/
280
260
1’
1
AIRPORT
PRESSURE
ALTITUDE
(ft)
/
J
/
----..-
/I
- -
,’
’
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
RUNWAY~RAKE
ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
//
250
3.3.3
Chapter
Page 30
5
6
3.3
I-S-A,
F.A.R,
CONDITIONS
+59°F(+150C)
- ALTER%ATE (U.S.
MODEL B4-203
- C4
3
7
8
9
10
11
RUNWAY
12
LENGTH
13
(lOOOft)
UNITS)
Feb.
1980
AIRBUS
INDUSTR
IE
300
A
ONLY.
MANUALS”
KVS MAXI
Al RPORT
PRESSURE
ALTITUDE
15(
/
(m>
--I__---
14( 1
-w-e-l
/
13c1
12c1
0
a
a
0
FLAPS
11c1
1'0‘2
1.5
1.8
2.1
8’1
2.4
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
ENERGYY LIMITATION
NO WIND
NO RUNWAY SLOPE
2.7
3.0
RUNWAY
3.3.4
Feb.
3.3
I.S.A.
1980
3.3
LENGTH
3.6
(1000m)
F,A.R.
CONDITIONS
+59"F(+lS"C)
- ALTERNATE (METRIC
MODEL B2-101
UNITS)
Chapter
Page
3
31
AIRBUS
INDUSTR
IE
A 300
AIRPLANE CHARACTERtSTtCS
ONLY.
MANUALS”
ALTITUDE
--P-m
3.3.4
-
I
(m)
RUNWAY LIMITATION
RUNWAYnnd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
1. 5
1. 8
3-3
I.S.A,
F.A.R.
CONDITIONS
+59'F(+1S°C)
- ALTERNATE (METRIC
MODEL B2-320
Chapter
3
Page 32
2. 1
2.4
2. 7
3. 0
3.3
3.6
3.9
UNITS)
Feb.
1980
AIRBUS
INDUSTR
IE
A 300
ONLY.
MANUALS”
160
Al RPORT
PRESSURE
ALTITUDE
--
-
0
2
- - ----
0
sm
a
a
.
5
1.8
2.1
2.4
2.7
RUNWAY LIMITATION
RUNWAY/2nd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
3.0
3.3
RUNWAY
3.3.4
Feb.
1980
3.3
I.S.A.
(m)
3.6
LENGTH
3.9
(1000m)
F-A-R.
CONDITIONS
+59"F(+1S°C)
- ALTERNATE (METRIC
tiODEL B4-101
UNITS)
Chapter
Page
3
33
AIRBUS
INDUSTR
A
AIRPLANE
IE
300
CHARACTERISTICS
ONLY.
MANUALS”
OPERATING
THE AIRCRAFT.
(ml
--
- -
0
m-..--
2
0
B
2
a
u-i
-
120-
RUNWAY LIMITATION
RUNWAYnnd
SEGMENT LIMITATION
RUNWAY/BRAKE
ENERGY LIMITATION
NO WIND
NO RUNWAY SLOPE
NO BLEED
a
a
1’ i
3.3.4
3.3
I.S.A.
Chapter
3
Page 34
1.8
2.1
2.4
2.7
3. 0
3.3
RUNWAY
3.6
LENGTH
3.9
(1 OOOm)
F.A.R.
CONDITIONS
+59*F(+is*c)
- ALTERNATE (METRIC
MODEL B4-203
- C4
UNITS)
Feb.
1980
AIRBUS
INDUSTR
A
AIRPLANE
IE
300
CRARACTERISTICS
ONLY.
MANUALS”
F-A. R. LANDING
FIELD
LENGTH
DRY RUNWAY
NO WIND
FLAPS 25’-SLATS
AIRPORT
= ACTUAL
DISTANCE
25’
PRESSURE
ALTITUDE
(ft)
GROSS WEIGHT
ALL
3.4
Feb.
1980
F.A.R.
AMBIENT
(lOOOlb>
TEMPERATURES
LANDING RUNWAY LENGTH REQUIREMENTS
3.4.1
FULL FLAPS (U.S.
UNITS)
MODEL B4/C4
Chapter
Page
3
35
AIRPLANE
CHARACTERISTICS
ONLY.
MANUALS”
SPEClFiC TO THE AIRLINE
F.A. R. LANDING
FIELD
LENGTH
= ACTUAL
DISTANCE
006
0
ml
cu/
gy
DRY RUNWAY
NO WIND
FLAPS 25O - SLATS 25”
2700
2400
$
4
c
AIRPORT
PRESSURE
ALTITUDE
2400
(RI)
ii
J
I
3
2100
;1
i
1800
1800
1500
-1200
0
3
0
GROSS WEIGHT
(1OOOKg)
s
‘d
0
ALL
-0”
AMBIENT
TEMPERATURES
In
a
a
3.4
Chapter
3
Page 36
F.A.R.
LANDING RUNWAY LENGTH REQUIREMENTS
3.4.2
FULL FLAPS (I'JETRIC UNITS)
MODEL B4/C4
Feb.
1980
INDUSTR
AIRBUS
AIRPLANE
25*
CHARACTERISTICS
THESE CURVES ARE GIVEN FOR
INFORMATION
ONLY. THE APPRhiitD
VALUES ARE STATED IN THE “OPERATING
MANUALS”
+ 15% ON FORESEEN
WET RUNWAY
SLATS
IE
FLAPS
25’
LANDING
DISTANCES
(kd
FINAL
M
a
a
. ..I
100
WEIGHT
3.4
I
Feb,
146’llo’
_.
1980
F.A.R.
(0
LANDING
3.4.3
.:.
. :
.i
TAIL
HEAD
WIND (kti
RUNWAY LENGTH REQUIREMENTS
FULL FLAPS
MODEL B 2
Chapter
Page
3
37
AIRBUS
INOUSTR
IE
A30
NOTE
:THESE
CURVES ARE GlVEN FOR INFORMATION
ONLY.
MANUALS”
SPECIFIC
TO THE AIRLINE OPERATING THE AIRCRAFT.
SLATS
2S”
VREF
FLAPS
= 1.3
MAXIMUM
LANDING
WEIGHT
25’
vs
2
127,500
!
B4
I
I
i
i
i
i
i F2 320
136,000
i!
ii
i!
I
-
e!
i
i
i
i
ii
i
iI
i!
i!
i!
ii ii' i I
ii
ii
m
130*
120%
0
3
10,
0
;:
g.
8In
100.
a
a
KG
133,
Chapter
3
Page 38
3.5 LANDING APPROACH SPEED
LANDING APPROACH SPEED (METRIC
MODEL B2 - B4
KG
-
-i
GROSS WEIGHT
3.5.1
OOOKG
(1000Kg)
UNITS)
Feb.
1980
INDUSTR
IE
0
NOTE :THESE CURVES ARE GIVEN FOR INFORMATION
ONLY.
MANUALS”
SLATS
25’
VREF
FLAPS
= 1.3
MAXIMUM
LANDiNG
WEIGHT
25’
Vs
c4
134,000
KG
I
i
i
i
i
w
0
5
.=
L
150
140
130
120’
110,
0
9
0
100.
;:
0”
2
in
a
a
GROSS WEIGHT (1OOOKg)
3.5.1
Feb.
1980
LANDING APPROACH SPEED (METRIC
MODEL C4
UNITS)
Chapter
Page
3
39
AIRBUS
INDUSTR
IE
NOTE
:THESE
CURVES ARE GIVEN FOR INFORMATION
ONLY.
MANUALS”
SPECIFIC TO THE AIRLINE OPERATING
THE AIRCRAFT.
B2
281,000
LB
I
SLATS
VREF
FLAPS
25O
= 1.3
25O
i
im
Vs
I
i
i
i
i
i-
150,
140
130
120
110
0
MAXIMUM
LANDING
WEIGHT
B4
29,3,200
LB
i
i 82 320
i
! 299,820
i
i
i'y i
f'
- -v
I
; 5
i
i
i
i
i
i
i i
i i
i i
LB
ii
ii
-ii
3
0
r:
z
0”
ul
a
a
100
200
300
250
GROSS WEIGHT
3-5-2
Chapter
Page 40
3
LANDING APPROACH SPEED (U.S.
MODEL B2 - B4
(1000lb~
UNITS)
Feb.
1980
INDUSTR
IE
NOTE
:THESE
CURVES ARE GIVEN FOR INFORMATION
ONLY.
MANUALS”
SLATS
VREF
25O
= l-3
FLAPS
25’
MAXIMUM
LANDING
WEIGHT
Vi
c4295,410
LB
i
i
0
8
i
im
100
0
r:
%
s
In
a
250
300
GROSS WEIGHT (1000lb)
a
3.5.2
Feb.
1980
LANDING APPROACH SPEED (U.S.
MODEL C4
UNITS)
Chapter
Page
3
41
AIRBUS
INDUSTR
IE
A.300
4.0
4.1
4.2
4.3
4.4
4.4.1
4.4.2
4.4.3
4.5
4.6
4.6.1
4.6.2
Feb.
GROUND MANEUVERING
Turning
radii
- No slip
angle
Minimum turning
radii
Visibility
from cockpit
in static
position
Runway and taxiway
turnpaths
More than 90' turn runway to taxiway
90' turn runway to taxiway
90' turn taxiway
to taxiway
Runway holding
apron
Minimum parking
space requirement
Minimum parking
space requirements(U.S.
Minimum parking
space requirements(Metric
1980
units)
units)
Chapter 4
Page 1
AIRBUS
INDUSTR
IE
A
AIRPLANE
CHARACTER ISTICS
I
+25”
FULL STEERING
ANGLE NORMALY
ALLOWS AIRCRAFT TO
PIVOT AROUND THIS POINT
NOTE :
ACTUAL OPERATING DATA
. . . .MAY
_... .
BE GREATER THAN VAL-me
.UES SHOWN
_..___._
SINCE TIRE SLIPPAGE IS NOT
CONSIDERED IN THESE CALCULATIONS
F4
/
/
STEERING
ANGL.E
0
m
I
-I 90.51i27.59
I
1122.01i37.19
4.1
Chapter
Page 2
4
i122.70i37.40
I
m.37i55.28
TURNING RADII NO SLIP
HODEL B2 - B4 - C4
il34.7&~.08
i163.&9.73
ANGLE
Feb.
1980
AIRBUS
AIRPLANE
INDUSTR
IE
CHARACTERISTICS
--c
I
KJ---!
4.2
Feb,
1980
.E*s;~~~;
NOSE GEAR RADII TRACK
MINIMUM TURNING RADII
MODEL B2 - B4 - C4
Chapter
Page
4
3
AIRBUS
INDUSTRIE
A
I
NOTTOBEUSED
FOR
LANDING
APPROACH
VISIBILITYI
ORIENTATION
ILOT
a
WITH
G
VI
EYE REF. POINT
MAXAFT VISION WITH HEAD
ROTATED
ABOUTSPINALCOLUMN
WITH HEADMOVED
4.3
Chapter
Page 4
VISIBILITY
FROM COCKPIT IN STATIC
MODEL B2 - B4 - C4
POSITION
4
Feb.
1980
I
AIRBUS
JNDUSTR
I
E
0
NOSE STEERING
ANGLE
-25O
NOSE GEAR TRACK
/
/
I
21.75FT.
(6.63M.I
(22.86M.j
/
0
d
0
;:
\
B
x
NOTE : COORDINATE WITH USING
OPERATING PROCEDURE
In
a
AIRLINE
FOR SPECIFIC
PLANNED
a
4.4-l
1
Feb.
1980
4.4 RUNWAY AND TAXIWAY TURN PATHS
MORE THAN 90° TURN RUNWAY TO TAXIWAY
MODEL B2 - B4 - C4
Chapter
Page
4
5
INOUSTR
AIRBUS
IE
A300
--
si
I1 -4
NOSE STEERING
ANGLE -25O
I
150FT.
(45.72M.)-
lOOFT.RAD.
U0.48M.)
I
---
F.
___-----------------I_______
-
NOTE :COORDiNATE WITH USING AIRLINE
OPERATING PROCEDURE
FOR SPECIFIC
PLANNED
4.4.2
90° TURN RUNWAY TO TAXIWAY
MODEL B2 - B4 - C4
Chapter
Page 6
4
Feb.
1980
1
INDUSTR
IE
NOSE STEERING
ANGLE -2S”
NOSE GEAR TRACK
I
-*r-PG
CL------------------------
0
In
a
NOTE : COORDINATE WITH USING AIRLINE
OPERATING PROCEDURE
.a
FOR SPECIFIC
PLANNED
4.4.3
90' TURN TAXIWAY TO TAXIWAY
MODEL B2 - B4 - C4
Feb.
1980
Chapter
Page
4
7
m
%Y
AIRBUS
INDUSTR
IE
NOSE STEERING
ANGLE
--
I
J I
-2S”
w-m--
I
r
me-
t
I
\
280FT.
(85.4M.I
I
-;\\
\’
20FT.
(6.1M.I
\
20FT.
(6.1M.I
\
’
c-
75FT.
(22.86M.I
150FT.
-(45.72M.I
m
: COORDINATE WITH USING AIRLINE
OPERATING PROCEDURE
FOR SPECIFIC
PLANNED
--
-
-I
4.5 RUNWAY HOLDING APRON
MODEL B2 - B4 - C4
Chapter
Page 8
4
Mar.
1986
AIRBUS
INDUSTR
IE
A 300
4.5 Minimum Parking
Space Requirements
The following
charts
show the rectangle
space required
for
parking
against
the terminal
building,
chart 4.5.1 is in feet
and chart 4.5.2 in meters.
The rectange
includes
allowance
for swinging
the airplane
on
arrival
and departure.
Four parking
and departure
techniques
are considered,
as follows
:
(a) Nose in
(Tow Out)
The A300 taxies
in at right
angles to the terminal
and
halts
with the radome 15 feet
(4.57 meters)
away from it.
On departure
it is towed out backwards
at right
angles to
the terminal.
An allowance
of 25 feet
(7.62 meters)
spanwise is added for clearance
from other airplane.
(b) Parallel
(Power Out)
The A300 taxies
in a right
angles to the terminal
then
swings with maximum nose wheel steering
(65O) to achieve
minimum turning
radius
as shown in chart 4-2, halting
when
the fuselage
centerline
lies parallel
to the terminal
after
a 10 feet
(3.05 meters)
taxiing
straight
forward.
On departure it taxies
10 feet
(3..05 meters)
straight
forward,
then
swings with maximum nose wheel steering
(65') until
facing
at right
angles away from the terminal.
Clearance
of at
least
25 feet
(7.62 meters)
is maintained
between the A300
and the terminal,
the critical
part being the wing tip during the arrival
swing.
An allowance
of 25 feet
(7.62 meters)
parallel
to the terminal is added for clearance
from other airplane,
the critical
parts
of the A300 being the tail
cone during
the
arrival
swing and the wing tip on departure.
(c)
45'
Angle
In
(Power Out)
The same procedure
is followed
as in the last case, excebt
that the A300 halts
with its fuselage
centerline
at 45' to
the terminal.
Clearance
and allowance
are the same.
(d)
45O Angle
In
(Tow Out)
The same procedure
is followed
as in
that on departure
the A300 is towed
wheel steering
with a 10 feet (3.05
run. Clearance
and allowance
are the
I
Feb.
1980
the last case, except
with maximum nose
meters)
initial
straight
same.
Chapter 4
Page 9
AIRBUS
INDUSTR
IE
3
‘AIRPLANE CHARACTERISTICS
NOTES :
65’NOSE WHEEL STEERING
(POWER OUT)
3 METER TRAVEL WITH
NOSE WHEEL STRAIGHT
AHEAD BEFORE AND
AFTER PARKED POSITION.
4,s METER BUILDING
CLEARANCE FOR NOSE-IN
PARKING
7,b METER BUILDING
CLEARANCE FOR OTHER
PARKING POSITIONS.
7,6 METER AIRPLANE TO
AIRPLANE CLEARANCE DURING
PARKING MANEUVERS.
COORDINATE WITH USING
AIRLINE FOR SPECIFIC
PLANNED OPERATING
PROCEDURE.
NGLE IN (POWER OUT)
.-am.*,-,
zuu
150
DISTANCE
OUT FROM
TERMINALFEET
100
In
a
a
DISTANCE ALONG TERMINAL-FEET
4.6.1
Chapter
4
Page 10
4.6 MINIMUM PARKING SPACE REQUIREMENTS
MINIMUM PARKING SPACE REQUIREMENTS
(U.S.
MODEL B2 - B4 - C4
UNITS)
Feb.
1980
J
AIRBUS
INDUSTR
IE
A
NOTES :
65O NOSE WHEEL STEERING
(POWER OUT)
7,6 METER BUILDING
CLEARANCEFOROTHER
PARKI NG POSITIONS
3 METER TRAVEL WITH
NOSE WHEEL STRAIGHT
AHEADBEFOREAND
AFTER PARKED POSITION
7,6 METER AIRPLANE TO..
AIRPLANE CLEARANCE DURING
PARKING MANEUVERS
4,5 METER BUILDING
CLEARANCE FOR NOSE-IN
PARKING
COORDINATE WITH USING
AIRLINE FOR SPECIFIC
PLANNED OPERATING
PROCEDURE
60
DISTANCE
OUT FROM
TERMINALMETERS
0
8
zIn
a
70
60
4.6 MINIMUM PARKING SPACE REQUIREMENTS
MINIMUM PARKING SPACE REQUIREMENTS
(METRIC
MODEL B2 - B4.C4
UNITS)
20
30
40
50
60
DISTANCE ALONG TERMINAL-METERS
a
4.6.2
I
Feb.
1980
Chapter
Page
4
11
5.0
5.1
5.1.1
5.1.2
5.1.3
5.1.4
5.1.5
5.1.6
R 5.1.7
R 5.1.8
5.2
5.2.1
5.2.2
5.2.3
5.2.4
5.3
5.3.1
5.4
'5.4.1
5.4,2
5.4.3
5.4.4
5.4.5
5.4.6
5.4.7
5.4.8
5.4.9
5.4.10
5.5
5.5.1
5.5.2
5.5.3
5.6
5.6.1
5.6.2
5.6.3
5.6.4
5.7
5.7.1
5.7.2
5.8
5.8.1
5.8.2
FOR AIRPORT PLANNING
TERMINAL SERVICING
Airplane
servicing
arrangement
Symbols used on servicing
diagrams
Open apron free standing
- APU running
- APU not running
Two passenger
gangways - Parallel
- APU running
Three passenger
gangways - Nose In - APU not running
Three passenger
gangways - Double parallel
- APU IWIning
- APU running
Three passengers
gangways - Nose In - APU running
Terminal
operation
Turnround
station
(30 minutes
- 1 door open)
Turnround
station
(30 minutes
- 2 doors open)
Turnround
station
(30 minutes
- 3 doors open)
Turnround
station
(30 minutes
- Freight
mode)
Terminal
operation
Enroute
station
(20 minutes
- 3 doors open)
Ground service
connections
Ground service
connections
data
Ground service
connections
layout
Hydraulic
system
Electrical.
system
Oxygen system
Fuel system
Pneumatic
system
Oil system
Potable
water system
Toilet
system
Engine starting
pneumatic
requirements
Ambient
temperature
-4O'F
(-40'~)
Ambient
temperature
+60°F (+lSOC)
Ambient
temperature
+lOO'F
(+38OC)
Ground pneumatic
power requirements
Heating
(U.S. units)
Heating
(Metric
units)
Cooling
(U.S. units)
Cooling
(Metric
units)
Preconditioned
airflow
requirements
U.S. units
Metric
units
Ground towing requirements
U.S. units
Metric
units
Chapter
5
Page 1
R Jun 1992
Printed in France
GA300
IIASAPU
- AUXILIARY
- AIR
I
CL
1 FC
POWER UNIT
STARTING
- CABIN
I
VEHICLE
CLEANING
- CONTAINER
- FREIGHT
TRUCK
LOADER
CONTAINER
G
- GALLEY
LOADING
GC
- PRECONDITIONED
TRAIN
VEHICLE
AIR
GROUND TRUCK
GPU - GROUND POWER UNIT
PS
- PASSENGER
- TOILET
ACCESS STEPS
SERVICING
VEHICLE
I
* NOTE : WHEN USING A FUEL TANKER THE SAFETY ZONE
CLEARANCES MUST BE IN ACCORDANCE WITH
LOCAL/AIRPORT
REGULATIONS.
5.1
5.1.1
R
Chapter
Page 2
AIRPLANE
SERVICING
ARRANGEMENT
SYMBOLS USED ON SERVICING
DIAGRAMS
MODEL B2 - B4 - C4
5
Jun
Printed in France
1992
5.1.2
R
Jun.
5.1 AIRPLANE SERVICING
ARRANGEMENT
OPEN APRON FREE STANDING - APU RUNNING
MODEL B2 - B4 - C4 PASS
Chapter'5
Page
1992
Rinted ifl fYatc@
3
AIRPLANE Cl-lARA~EfWi-ICS
5.1.1
R
Chapter
Page 4
ARRANGEMENT
MODEL C4 FREIGHT
5
Jun
printedin Ffarux
1992
%A300
5.1.2
R
Jun.
ARRANGEMENT
MODEL C4 FREIGHT/PASSENGER
Chapter'5
Page
1992
f%inted in Frame
5
$A300
_.
--.
_
,
~
ARRANGEMENT
OPEN APRON FREE STANDING - APU NOT RUNNING
5.1.3
R
Chapter
Page 6
I
5
Jun
Printed in France
1992
AiRPLANE CHARACTERISTICS
I!-I
II
5.1.3
R
Jun.
ARRANGEMENT
MODEL C4 FREIGHT
Chapter.5
Page
1992
Printad in France
7
GA300
AIRPLANE CHARACTERISTICS FOR AIRPORT PUNNING
I-I
H,, -I i
I
I iI 1i
I
I
I I I I
I
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8.
‘isy
SCALE - METERS
15.1.3
R
Chapter
Page
10
~20
30
4’0
ARRANGEMENT
5
8
Jun.
Printed in France
1992
I
$A300
I
I
I
I
I
nils
i
1s
ARRANGEMENT
PROPOSED’
FOR 70 MINYTES T~RNRO”,ND ONiY-+f&$+j
8
LL
(
ARRANGEMENT
TWO PASSENGER GANGWAYS - PARALLEL - APU RUNNING
Chapter
1992
Page
5.1.4
R
Jun.
Printed in France
5
9
t-t-l-2
t-
L-I
2
-I
II
-
FOR 30 MINUTES
1
TURNROUNO ONLY
ARRANGEMENT
THREE PASSENGER GANGWAYS - NOSE IN - APU NOT RUNNING
Chapter
5
Jun.
Page 10
5.1.5.
R
Printed in France
1992
GA300
______
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5.1.6
R
Jun.
IS PKUPUStD
30 MINUTES TURNROUNO ONLY
ARRANGEMENT
THREE PASSENGER GANGWAYS - DOUBLE PARALLEL
- APU RUNNING
Chapter
Page
1992
Printed in France
'5
11
GA300
5.1.7
R
ARRANGEMENT
Chapter
5
Page 12
Jun.
Printed in France
1992
i
I
:
I”,2 ~lwwwcIcN,c,
FOR 30 MINUTES TURNROUND ONLY
I
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ARRANGEMENT
THREE PASSENGER GANGWAYS - NOSE IN - APU RUNNING
Chapter.5
1992
Page 13
5.1.8
R
I
Printed in France
GA300
AIRPLANE CHARACTERISTICS FOR AIRPORT PIANNING
THIS
R
PAGE LEFT BLANK INTENTIONALLY
Chapter
5
Page 14
Jun.
Printed in France
1992
AIRBUS
INDUSTR
IE
A 300
ESTIMATED
TIME-MINUTES
POSITION JETWAYS
AND STAIRWAYS
PASSENGERS MOVEMEN‘
OPENING DOORS AND
POSITION LOADERS
BACGACEANDCARGD
MOVEMENT
CLEAN CABIN
SERVICE TOILET AND
WATER REPLENISHMENT
SERVICE GALLEY
REFUEL
WALKAROUNDCHECK
REMDVE LOADERS AND
CLOSECARGODOORS
REF.IOVE JETWAYS AED
STAIRWAYS
START ENGINES
DISCONNECTIONS
345 PASSENGERS - 1 DOOR OPEN - 100 ?. PASSENGER MOVEMENT
REFUELLING OF 80 7,
18 PAX/DOOR MINUTE - DEPLANING
PASSENGERFLOWRATE
<
16 PAX/DOOR MINUTE - BOARDING
APU RUNNING
FREIGHT AND BAGGAGE CONTAINERIZED
100% UNLOAD - LOAD
5.2.1
Feb.
1980
5.2 TERMINAL OPERATION
TURNROUND STATION - 30 MINUTES - 1 DOOR OPEN
Chapter
Page
5
15
AIRBUS
INDUSTR
IE
A
ESTIMATED
TIME-MINUTES
POSITION JETWAYS
AND STAIRWAYS
PASSENGERS MOVEMEN
OPENING DOORS AND
POSITION LOADERS
BAGCAGEANDCARGO
MOVEMENT
CLEAN CABIN
SERVICE TOILET AN0
WATER REPLENISHMEN
SERVICE GALLEY
REFUEL
WALK AROUND CHECK
REMOVE LOADERS AND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DISCONNECTiONS
.
A ’ ’ ’
75 PASSENGERS - 1 DOOR OPEN - 100 %PASSENGER MOVEMENT
REFUELLING OF 80 %
PASSENGERFLOWRATE
<
0
APU RUNNING
FREIGHT
AND BAGGAGE CONTAINERIZED
100% UNLOAD - LOAD
u-l
a
a
5.2-l
Chapter
5
Page 16
TURNROUND STATION - 30 MIWTES
- 1 DOOR OPEN
Feb.
1980
AIRBUS
AIRPLANE
INDUSTR
IE
0
CHARACTERISTICS
ESTIMATED
TIME-MINUTES
POSITION JETWAYS
AN0 STAIRWAYS
PASSENGERS MOVEMEN‘
6
2
r=
OPENING DOORS AND
POSITION. LOADERS
SAGGAGE AND CARGO
MOVEMENT
f
-u
0)
z
T
a
CLEAN CABIN
SERVICE TOILET AND
WATER REPLENISHMENT
SERVICE GALLEY
REFUEL
WALK AROUND CHECK
REMOVELOADERSAND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DISCONNECTIONS
281 PASSENGERS - 2 DOORS OPEN - 100 % PASSENGER
REFUELLING OF 80 ‘y*
MOVEMENT
PASSENGER FLOW RATE<
APU RUNNING
BAGGAGE CONTAINERIZED
I
5.2.2
TURNROUND STATION - 30 MINUTES
MODEL B2
- 2 DOORS OPEN
Chapter
Page
5
17
AIRBUS
AIRPLANE
INDUSTR
IE
CHARACTERISTICS
ESTIMATED
TIME-MINUTES
POSITION JETWAYS
AN0 STAIRWAYS
PASSENGERS MOVEMEN’
OPENING DOORS AND
POSITION LOADERS
BAGGAGEANDCARGO
MOVEMENT
CLEAN CABIN
SERVICE TOILET AND
WATER REPLENISHMEN
SERVICE GALLEY
REFUEL
WALK AROUND CHECK
REMOVE LOADERS AND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DISCONNECTIONS
281 PASSENGERS - 2 DOORS OPEN - 100 % PASSENGER MOVEMENT
REFUELLING OF 80 “/
PASSENGERFLOWRATE
<
APU RUNNING
5-2.2
Chapter
5
Page 18
MODEL 'B4 - C4 PASS
- 2 DOORS OPEN
I
Feb.
1980
I
AIRBUS
INDUSTR
AIRPLANE
CHARACTERISTlCS
ESTIMATED
0
POSITION JETWAYS
AND STAIRWAYS
PASSENGERS MOVEMEN’
OPENING DOORS AND
POSlTlON LOADERS
BAGGAGEANDCARGO
MOVEMENT
5
IE
10
~1
TIME-MINUTES
15
20
25
I t-
CLEAN CABIN
SERVICE TOILET AND
WATER REPLENISHMEN
SERVICE GALLEY
1I
“-1’
REFUEL
I
I
WALK AROUND CHECK
REMOVE LOADERS AND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DISCONNECTIONS
REFUE LLING OF 80 %
PASSENGER FLOW RATE < 16 PAX/DOOR MINUTE - BOARDING
APU RUNNING
5.2.3
I Feb.
1980
MODEL B2
- 3 DOORS OPEN
Chapter
Page
5
19
AIRBUS
INDUSTR
A
AIRPLANE
IE
characteristics
ESTtMATED
TIME-MINUTES
POSiTION JETWAYS
AND STAIRWAYS
PASSENGERS MOVEMENl
OPENING DOORS AND
POSITION LOADERS
BAGGAGEANDCARGO
MOVEMENT
CLEAN CABIN
SERVICE TOILET AND
WATER REPLENISHMENT
SERVICE GALLEY
REFUEL
WALK AROUND CHECK
REMOVE LOADERS AND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DISCONNECTIONS
REFUELLING OF 80 3
PASSENGER FLOW RATE <
APU RUNNING
5.2.3
Chapter
5
Page 20
MODEL B4 - C4 PASS
- 3 DOORS OPEN
I
Feb.
1950
I
AIRBUS
INDUSTR
A
IE
0
ESTIMATED
POSITION JETWAYS
AND STAIRWAYS
TIME-MINUTES
I)
OPENING DOORS AND
POSITION LOADERS
CARGO MOVEMENT
SERVICE TOILET AN0
WATER REPLENISHMEN
REFUEL
WALK AROUND CHECK
REMOVE LOADERS AND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DISCONNECTIONS
100% UNLOAD - LOAD
REFUELLINC
OF 80 %
APU RUNNING
FREIGHT
0
LL
v
0
CONTAINERIZED
0
0
g
i5
In
a
a
5.2.4
Feb.
1980
MODEL C4 FREIGHT
- FREIGHT
MODE
Chapter
Page
5
21
INOUSTR
1E
ESTIMATED
TIME-MINUTES
20
i
POSITION JETWAYS
AND STAIRWAYS
PASSENGERS MOVEMENT
OPENING DOORS AND
POSITION LOADERS
BAGGAGEANDCARGO
MOVEMENT
SERVICE TOILET AND
WATER REPLENISHMENT
SERVICE GALLEY
-
REFUEL
I
WALKAROUNDCHECK
I
REMOVELOADERSAND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DlSCtiNNECTlONS
I
281 PASSENGERS - 3 DOORS OPEN - 60 yo PASSENGER MOVEMENT
REFUELLING OF 30 ‘%
PASSENGERFLOWRATE
<
APU RUNNING
5.3.1
Chapter
5
Page 22
ENROUTE STATION - 20 MINUTES - 3 DOORS OPEN
MODEL B2
Feb.
1980
1
AIRBUS
INDUSTR
IE
30
ESTlMATED
TIME-MINUTES
POSITION JETWAYS
AND STAIRWAYS
PASSENGERS MOVEMENT
OPENING DOORS AND
POSITION LOADERS
BAGGAGEANDCARGO
MOVEMENT
SERVICE TOILET AND
WATER REPLENISHMENT
SERVICE GALLEY
REFUEL
WALKAROUNDCHECK
REMOVELOADERSAND
CLOSECARGODOORS
REMOVE JETWAYS AND
STAIRWAYS
START ENGINES
DISCONNECTIONS
REFUELLING OF 30 %
PASSENGER FLOW RATE <1 6 PAX/DOOR MINUTE - BDARDlNG
APU RUNNING
5.3-l
I
Feb,
1980
ENROUTE STATION - 20 MINUTES - 3 DOORS OPEN
MODEL B4 - C4 PASS
Chapter
Page
5
23
AIRBUS
INDUSTR
IE
A 300
POTABLE WATER FILLING
POTABLE
WATER FLUSHING
OXYGEN CHARGING
HYDRAULIC
POINT
POWER GROUND CONNECTION
ENGINE
AND CSD OIL
TOILET
SERVICING
ELECTRICAL
FILLING
CONNECTIONS
CONNECTION
GROUND CONNECTION
PRE-CONDITIONING
GRJkVITY
AND DRAINING
FUELING
ACCUMULATOR
AIR
CONNECTIONS
CONNECTIONS
CHARGING
HYDRAULIC
TANK FILLING
HYDRAULIC
TANK AIR
PRESSURE FUELING
- LP
CONNECTIONS
CHARGING
CONNECTIONS
5.4 GROUND SERVICE CONNECTIONS
5.4.1
GROUND SERVICE CONNECTIONS DATA
MODEL B2 - B4
Chapter
5
Page 24
Feb.
1980
I
AIRBUS
INDUSTR
A
AIRPLANE
IE
300
CHARACTERISTICS
Al
5.4
5.4.2
Feb.
1980
GROUND SERVICE CONNECTIONS
GROUND SERVICE CONNECTIONS LAYOUT
MODEL B2 - B4
Chapter
Page
5
25
AIRBUS
INDUSTR
IE
A300
A
POTABLE WATER FILLING
Al
POTABLE
B
OXYGEN,CHARGING
C
HYDRAULIC
D
ENGINE
AND CSD OIL
E
TOILET
SERVICING
F
ELECTRICAL
G
PRE-CONDITIONING
H
GRAVITY
I
ACCUMULATOR
J
HYDRAULIC
TANK FILLING
K
HYDRAULIC
TANK AIR
L
PRESSURE FUELING
CONNECTIONS
PRE-CONDITIONING
CONNECTION/ENGINE
M
111
WATER FLUSHING
AND DRAINING
POINT
POWER GROUND CONNECTION
FILLING
CONNECTIONS
CONNECTION
GROUND CONNECTION
FUELING
AIR
CONNECTIONS
- LP
CONNECTIONS
CHARGING
CONNECTIONS
CHARGING
STARTING
- HP
5.4 GROUND SERVICE CONNECTIONS
5.4.1
GROUND SERVICE CONNECTIONS DATA
MODEL C4
Chapter
5
Page 26
Feb.
1980
AIRBUS
INDUSTR
IE
0
in
a
a
5.4
5.4.2
Feb,
1980
GROUND SERVICE CONNECTIONS
GROUND SERVICE CONNECTIONS LAYOUT
MODEL C4
Chapter
Page
5
27
AIRBUS
INDUSTR
IE
A 300
AIRPLANE
CHARACTERISTICS
DISTANCE
CENTERLINE
A. Reservoir
charging
:
One l/4 in. self sealing
connection
common for
the 3 reservoirs
B. Accumulator
charging
:
Five MS 28889-l'.connections
(one per accumulator)
- Green
- Yellow
and Blue
- Braking
C. Reservoir
filling
:
connection
common for
the 3 reservoirs
D. Reservoir
overflow
Three l/4 in. sealf
sealing
connections
(one per reservoir)
- Green
- Yellow
:
and Blue
E. Ground test
Three 1 in. self sealing
connections
and three
1 l/4 in. self sealing
connections
(one pair
per system)
- Green
- Yellow
and Blue
5.4-3
Chapter
5
Page 28
Hydraulic
MODEL B2
System
Feb.
1980 J
AIRBUS
INDUSTRIE
A
AIRPLANE
CHARACTERISTICS
DISTANCE (FtMeters
AFT OF
NOSE
FROM AIRDT-a"=
CENTERLINE
CENTER
1 HEIGHT
I
RH SIDE
8
2
rt
.5
-0
al
2
a'C
I
LH SIDE
A. Reservoir
charging
:
connection
common for
the 3 reservoirs
B. Accumulator
charging
:
Five MS 28889-l
connections
(one per accumulater)
- Green
- Yellow
and Blue
- Braking
- Braking
C. Reservoir
filling
:
connection
common for
the 3 reservoirs
D. Reservoir
overflow
Three l/4 in, self
sealing
connections
(one per reservoir)
- Green
- Yellow
:
and Blue
E. Ground test
:
Three 1 in. self sealing
connections
and three
1 l/4 in. self
sealing
connections
(one pair
per system)
- Green
- Yellow
and Blue
System
5.4.3 Hydraulic
MODEL B2 320 - B4 - C4
1 Feb.
1980
Chapter 5
Page 29
AIRBUS
INDUSTR
IE
A3
AIRPLANE
CHiRACTERlSTlCS
ELECTRICAL SYSTEM
Meters
DISTANCE (Ft - In.)
RH SIDE
One standard
6 pin connection - IS0 R461 specification
LH SIDE
I
Supply :
115/200 Volt Phase 400 HZ
Power required
: 90 WA
5.4.4
Chapter
5
Page 30
Electrical
MODEL B2
System
Feb.
1980
1
@A300
ELECTRICAL
SYSTEM
Meters
DISTANCE
(ft
AFT OF
NOSE
-
in.)
FROM AIRPLANE
CENTERLINE
IRH SIDEILH
One standard
6 pin
IS0 R461 specification
Supply:
115/200
Volt
Power required:
R
Electrical
R
Note:
connection
3 Phase 400
90 KVA
Connectors
For
-
mating
for
connectors
4*40
(14-5)
1
SIDE1
3.30
/ (10-10)
Hz
Servicing
contact
5.4.4
Electrical
MODEL B2 320
May
/ (g;;
MEAN
HEIGHT
FROM
GROUND
HUBBEL
(FSCM 7H582)
System
- B4 - C4
Chapter
Page
*l/98
Printed in France
5
31
A300
K)R AIRPORT PLANNING
OXYGEN SYSTEM
Meters
DISTANCE
(ft
AFT OF
NOSE
- in.)
FROM AIRPLANE
CENTERLINE
MEAN
HEIGHT
FROM
GROUND
RH SIDE LH SIDE
One service
connection
(external
charging)
3/8
UNF x 24 TPI
12.05
(38-10)
in.
5.4.5
2.52
(8-3)
3.60
(11-9)
Oxygen System
MODEL B2
Chapter
5
Page 32
Feb.
Printed in France
1980
AIRBUS
INDUSTR
IE
A CHARACTERISTICS
300
AIRPLANE
OXYGEN SYSTEM
I
I
D1STANCE
AFT OF
NOSE
I
I
One service
connection
(external
charging)
3/8
UNF x 24 TPI
31/82
HEIGHT
FROM
GROUND
FROM AIR?'""
rum?E
CENTERLINE
RH SIDE1
I
LH SIDE
I
,-
I
II
in.
S-4.5
Oxygen
MODEL B2 320
Jul
I
Meters(Ft - In.)
System
- B4 - C4
Chapter
Page
5
33
AIRBUS
AIRPLANE
INDUSTR
IE
CHARACTERISTICS
FUEL SYSTEM
*ISTANCE
Meters
(Ft - In.)
I
FROM AIRPLANE
CENTERLINE
AFT OF
NOSE
RH SIDE I LH SIDE
Two standard
connections
Specification
MEAN
HEIGHT
FROM
GROUND
--
'4;27
(14-O)
2 l/2 in.
- IS0 R45
Two Standard
2 l/2 in.
connections
- IS0 R45
Specification
11.84
4.27
(14-O)
Two service
connections
(gravity
feed)
24.95
(81-10)
12-35
(40-6)
12.35
(40-6)
4.72
(15-6)
Two service
connections
(gravity
feed)
31.02
(101-9)
20.39
(66-11)
20.39
(66-11)
5.27
.(17-3)
(300 U.S.
gal/mn)
Flow Rate :
1135 l/mn (250 Imp.
Maximum Pressure
:
50 psig (3.45 bars)
gal/mn>
APPROX. CAPACITIES
Two outboard
Two inboard
Total
per
per
connection
PER AIRPLANE
tanks
tanks
airplane
5.4.6 Fuel System
MODEL B2-32X
Chapter
5
Page 34
Feb.
1980
I
AIRBUS
INDUSTRIE
A
300
FUEL SYSTEM
Meters
D1STANCE (Ft - In.)
I
MEAN
HEIGHT
FROM
GROUND
FROM AIRPLANE
CENTERLINE
AFT OF
NOSE
RH SIDE I LH SIDE
Two standard
connections
Specification
-
2 l/2 in.
- IS0 R45
TWO Standard
2 l/2 ino
connections
- IS0 R45
Specification
11.84
(38-10)
4.26
(13-11)
12.35
(40-6)
4.72
(15-5)
Two service
connections
(gravity
feed)
(81-10)
Two service
connections
(gravity
feed)
31.02
20.39
20.39
5.27
(101-9)
(66-11)
(66-11)
(17-3)
Flow Rate :
1135 l/mn (250 Imp.
Maximum Pressure
:
50 psig (3.45 bars)
24.95
gal/mn)
(300 U.S.
APPROX. CAPACITIES
Two outboard
Two inboard
Total
per
12.35
(40-6)
gal/mn)
per
connection
PER AIRPLANE
tanks
tanks
airplane
Fuel System
MODEL B2 320
5.4.6
Feb.
1980
Chapter 5
Page 35
FUEL SYSTEM
FOR AIRPOKF PLANNING
Meters
D1STANCE (Ft - In.)
FROM AIRPLANE
CENTERLINE
Two standard
connections
Specification
2 l/2 in.
- IS0 R45
Two Standard
2 l/2 in.
connections
- IS0 R45
Specification
Two service
connections
(gravity
feed)
Two service
connections
(gravity
feed)
Flow Rate :
1475 l/mn (325 Imp.
Maximum Pressure
:
50 psig (3.45 bars)
gal/mn)
(390 U.S.
APPROX. CAPACITIES
One center
R Chapter 5
Page 36
per
PER AIRPLANE
Two inboard
5.4.6
gal/mn)
Fuel System
MODEL B4
connection
GA300
AlRPLANECHARACTERlSTlCSFORAlRPdRTPLANNlNG
FUEL SYSTEM
Meters
D*STANCE (Ft - In.)
I
FROM AIRPLANE
CENTERLINE
AFT OF
NOSE
MEAN
HEIGHT
FROM
r;ROUNr:
RH SIDE I LH SIDE
Two standard
connections
Specification
2 l/2 in.
- IS0 R45
24.31
(79-9)
Two Standard
2 l/2 in.
- IS0 R45
24.31
(79-9)
connections
Specification
Two service
connections
(gravity
feed)
24.95
(81-10)
Two service
31.02
(101-9)
(gravity
connections
feed)
Flow Rate :
1475 l/mn (325 Imp.
Maximum Pressure
:
50 psig (3.45 bars)
gal/mn)
(13-11)
il.84
(38-10)
12.35
(40-6)
12.35
(40-6)
4.26
(13-11)
4.72
(15-S)
5.27
(17-3)
(390 U.S.
APPROX. CAPACITIES
4.26
11.84
(38-10)
gal/mn)
per
connection
PER AIRPLANE
LITERS LITERS IHP. GALLO?ISIMP. GALLONS U.S. GALLONS U.S. GALLONS
BASIC I OPTIONALI
BASIC
BASIC
OPTIONAL
I OPTIONAL I
Two outboard
tanks
2,450
Two inboard
tanks
9,280
,One center
tank
4,650
Total per
airplane
16,380
5.4.6
R Oct.
Fuel System
MODEL C4
1989
F%nted in France
Chapter 5
Page 37
AIRBUS
INDUSTR
AIRPLANE
PNEUMATIC SYSTEM
1E
CHARACTERISTICS
Meters
D1STANCE (Ft - In.)
AFT OF
NOSE
FROM AIRPLANE
CENTERLINE
1 RH SIDE1 LH SIDE
Two standard
3 in. IS0
TC20 connections
for engine
starting
and cabin conditioning.
Two standard
8 in. connections
(MS335621 for preconditioned
air (optional).
5.4.7
Chapter 5
Page 38
MEAN
HEIGHT
FROM
GROUND
I
1
21.60
(70-10)
0.88
(2-11)
2.15
(7-l)
17.31
(56-9)
0.82
(2-8)
0.82
(2-8)
2.27
(7-5)
2.27
(7-5)
16.82
(55-2)
I
Pneumatic
System
MODEL B2
Feb.
1980
J
AIRBUS
INDUSTR
AIRPLANE
PNEUMATIC SYSTEM
CHARACTERISTICS
Y*YIcaL.Ga
(FtMeters_ In,)
I
nTcrFan7rv
I AFT OF
Two standard
3 in. IS0
TC20 connections
for engine
starting
and cabin conditioning.
Two standard
8 in. connections
(MS335621 for preconditioned
air
(optional).
IE
I
NOSE
I
FROM AIRPLANE
CENTERLINE
RH SIDE
21.40
(70-10)
I
I
MEAN
HEIGHT
I
_::!-yClKUUNU
LH SIDE
I
0.88
(2-11)
2.16
(7-l)
17.31
(56-9)
0.82
16.82
(55-2)
0.82
(2-8)
2.27
(7-S)
2.27
(7-S)
(2-8)
5.4.7 Pneumatic System
i+4ODELB2 320 - B4 - C4
Feb.
1980
Chapter 5
Page 39
INDUSTR
AIRBUS
A
AIRPLANE
CHARACTERlSTlCS
OIL SYSTEM
Meters
D1STANCE (Ft - In.)
FROM AIRPLANE
CENTERLINE
AFT OF
NOSE
A. Engine oil replenishment
:
One gravity
fill
cap and
one pressure
fill
connection per engine fill
Delivery
pressure
Tank capacity
- Full level
- Usable
IE
required
:
: 6 U.S.
: 3 U.S.
Gal
Gal
_
18.00
(59-l)
: 25 psi
(22.710
(11.355
RH SIDE
LH SIDE
8.80
(28-11)
7.00
(22-11)
(1.72
MEAN
HEIGHT
FROM
GROUND
bars)
liters)
liters)
B. C.S.D. oil replenishment
:
One pressure
fill
connection per engine and one
gravity
fill
port
Delivery
pressure
Tank capacity
required
: 8-5
U.S.
5.4.8
R
Chapter 5
Page 40
: 25 psi
quarts
Engine
(8.04
(1.72
bars)
liters)
and CSD Oil
MODEL B2
System
Ott
1980
AIRBUS
INDUSTR
IE
A 300
OIL SYSTEM
Meters
D1STANCE (Ft - In.)
FROM AIRXANE
CENTERLINE
AFT OF
NOSE
:
One gravity
fill
cap and
one pressure
fill
Delivery
pressure
Tank capacity
- Full level
- Usable
required
:
: 10.6
: 8.6
U.S.
U.S.
.
LH SIDE
18.20
(59-8)
(29-l)
: 25 psi
(1.72
\T;al (40.12
Gal (32.55
liters)
liters)
7.02
(23-00)
MEAN
HEIGHT
FROM
GROUND
1.36
(d-6)
bar)
:
One pressure
fill
gravity
fill
port
Delivery
pressure
Tank capacity
required
: 8.5 U,S.
5.4.8
Ott
1980
: 25 psi
quarts
(1,72
( 8.04
bar)
liters)
Engine and CSD Oil
MODEL B2 320
System
Chapter 5
Page 41
AIRBUS
INDUSTR
IE
300
A
OIL SYSTEM
I
FROM AIRPLANE
CENTERLINE
AFT OF
NOSE
.RH SIDE
LH SIDE
8.80
(28711)
7.00
(22-11)
: -'
One gravity
fill
cap and
18.00
one pressure
fill
connec(59-l)
tion per engine fill
Delivery
pressure
Tank capacity
- Full level
- Usable
required
:
: 6 U.S.
: 3 U.S.
Gal
Gal
Meters
(Ft - In. )
“&“.I
nT~TiNcE
I
: 25 psi
(22.710
(11.355
(1.72
I
MEAN
HEIGHT
FROM
GROUND
1.40
(4-7)
bar)
liters)
liters)
B. C.S.D, oil replenishment
:
One pressure
fill
gravity
fill
port
Delivery
pressure
Tank capacity
required
: 8.5 U.S.
5.4-8
Chapter
5
Page 42
: 25 psi
quarts
(1.72
(8.04
Engine and CSD
MODEL B4
bar)
liters)
Oil
System
act
198@
AIRBUS
INDUSTR
IE
.A 300
OIL SYSTEM
Meters
D1STANCE (Ft - -J-n.)
FROM AIRPLANE
CENTERLINE
AFT OF:
NOSE I
RH SIDE
':
One gravity
fill
cap and
one pressure
fill
Delivery
pressure
Tank capacity
- Full level
- Usable
required
:
: 6 U.S.
: 3 U.S.
Gal
Gal
8.80
7.00
-( @-1.)
(28-11)
(22-11)
(22.710
(11.355
(1.72
FROM
GROUND
I
LH SIDE
.i8.00'
: 25 psi
MEAN
.I1 HEIC
;HT
1.40
(4-7)
bar)
liters)
liters)
:
One pressure
fill
gravity
fill
port
Delivery
pressure
Tank capacity
R
required
: 8.5
U.S.
5.4.8
act 1980
: 25 psi
quarts
Engine
(8.04
(1.72
bar)
liters)
and CSD Oil
MODEL C4
System
Chapter 5
Page 43
GA300
AIRPLANE CHARACJl-EiRISTlCS FOR AIRPORT PLANNING
POTABLE WATER SYSTEM
DISTANCE (Fpters
- In.)
FROM AIRPLANE
CENTERLINE
AFT OF
NOSE
One standard
3/4 in. self
quick
release
cousealing
pling
for filling.
Two drain and two flushing
connections
R
Fill
rate
- Flow
- Pressure
MEAN
HEIGHT
FROM
GROUND
I
18.41
(60-S)
5.13
(16-10)
42.10
(137-6)
0.70
(2-3)
I
2.48
(6-8)
4.32
(14-2)
:
: 91 l/mn (20 Imp. gal/mn)
: 25 psi (1.72 bar)
Usuable capacity
:
- 400 liters
(88 Imp.
gal.)
5.4.9
(106 U.S.
(24 U.S.
gal/mn)
gal.)
Potable Water
MODEL B2
R Chapter 5
Page 44
System
Oct.
F'rintedinFrance
1989
$A300
POTABLE
WATER SYSTEM
I
Meters
DISTANCE (Ft - In.)
FROM AU--'KPLANE
CENTE: RLINE
RH SIDE
R
Fill
rate
- Flow
- Pressure
:
gal.
(3-8)
2.48
(6-8)
1.63
(S-4)
(10-O)
(106 U.S.
(24 U.S.
4.33
(14-2)
gal/mn)
gal.)
5.4.9 Potable
Water System
MODEL B2 320 - B4 - C4
R Oct.
3.06
0.70
(2-3)
: 91 l/mn (20 Imp. gal/mn)
: 25 psi (1,72 bar)
Usuable capacity
:
- 400 liters
(88 Imp.
LH SIDE I
1.13
One standard
3/4 in. self
sealing
quick release
coupling
for filling.
Two drain and two flushing
connections
MEAN
HEIGHT
FROM
GROUND
1989
Printedinfiance
Chapter 5
Page 45
AIRBUS
INDUSTR
A
AIRPlANE
IE
0
CHARACTERISTICS
TOILET SYSTEM
Meters
plsTmCE
(Ft
-
In
l
)
I
AFT OF
NOSE
'RH SIDE
Per servicing
panelOne Standard
4 in. drain.
connection
and two 1 in.
flush
connection
4.40
(14-5)
42.16
(138-4)
Capacity
Single
- Waste
- Chemical
fluid
toilet
:
: 58,7 liters
: 9,5 liters
Capacity
Double
- Waste
- Chemical fluid
toilet
:
: 120,liters
: 19 liters
5.4.10
Chapter 5
Page 46
MESN
HEIGHT
FROM
GROUND
LH SIDE
1.71
(5.7)
0.64
(2-l)
(12;9 Imp. gal.)
(2.1 Imp. gal.)
(26.4 Imp. gal.)
(4.2 Imp. gal.)
3.28
(10-9)
4.26
(13-10)
(15.5 U.S. gal.)
(2.5 U.S. gal.)
(31.6 U.S. gal.)
(5.0 U.S. gal.)
Toilet
System
MODEL B2
Feb.
1980
I
AIRBUS
AIRPLANE
INDUSTR
IE
CHARACTERISTICS
TOILET SYSTEM
DISTANCE (F;Et;;=)
AFT OF
NOSE
FROM AIRPLANE
CENTERLINE
RH SIDE
Per servicing
panel
One Standard
4 in. drain
connection
and two 1 in.
flush
connection
m
aI
Capacity
- Waste
E
';:
a.2
-
Chemical
Single
fluid
Capacity
Double
- illaste
- Chemical
fluid
toilet
:
: 58,7 liters
: 9,5 liters
toilet
:
: 120 liters
: 19 liters
4.40
(14-5)
42.16
(138-4)
I
MEAN
HEIGHT
FROM
GROUND
I
LH SIDE
1.71
(5-7)
0.64
(2-l)
(12.9 Imp. gal.)
(2.1 Imp. gal.)
(26.4 Imp. gal.)
(4.2 Imp. gal.)
(15.5 U.S. gal.)
(2.5 U.S. gal.)
(31.6 U.S. gal.)
(5.0 U.S. gal.)
5.4-10 Toilet
System
MODEL B2 320 - B4 - C4
I
Feb.
1980
Chapter 5
Page 47
AIRBUS
INDUSTR
IE
AIR SUPPLY
AT
AIR
SUPPLY
PRESSURE
AT
GROUND
CONNECTION
TEMPERATURE
FUSELAGE
CONNECTION
I
I
PS
5
495
60
4
-
2
8,000
FT
395
TIMATED
ThlE
(2 = SEA
LlivllT
IDLE
:
65 sec.
LEVEL)
3
295i
30
AIRFLOW
2
!I0
KlLOGRAnllS
180
is0
260
POUNDS
0 TO 8,000
TEMP.
5.5
Chapter
5
Page 48
FT.
AMBIENT
100
PER
REWIRED
110
AT
GROUND
CONNECTiON
120
130
MINUTE
2iO
2io
PER MINUTE
ALT.
: - 2O“C
- 4’F
ENGINE STARTING PNEUMATIC REQUIREMENTS
5.5.1
AMBIENT TEMPERATURE -2O'C
(-4'F))
MODEL B2-320
Ott
1980
AIRBUS
INDUSTR
IE
AIR SUPPLY TEMPERATURE
AT FUSELAGE CONNECTION
AIR SUPPLY PRESSURE
AT GROUND CONNECTION
I
PS
sec.
70
60
50
3,s
3,
40
2,5,
30
‘O
100
125
120
“O
150
225
POUN:%R
250
130
275
MINlf!!”
0
a
a
0
0 TO 8,000 FT. ALT.
TEMP. AMBIENT : - 4OOC
;:
5.5
R
Ott
1980
-
40°F
5.5.1
AMBIENT TEMPERATURE -4O'C
(-40°F)
MODEL B2 - B4 - C4
Chapter
Page
5
49
AIRBUS
INDUSTR
IE
AIR SUPPLY
AT GROUNO
AIR
SUPPLY
AT
FUSELAGE
TEMPERATURE
CONNECTION
PRESSURE
CONNECTION
P!
L.
SOLUTE
-&gp
EARS
74
495
~vlAXldUtvl
6a
Z = SEA
4
-Z
50
DUCT
LEVEL
= 8,000
PRESSURE
- 45
psig
FT--,A
395
‘ESTIMATED
/
TlwlE LifullT TO IDLE
(Z - SEA LEVEL)
: 65
sec.
3
40
3a
0 TO 8,000
TEMP.
5.5
Chapter
5
Page 50
FT.
AMBIENT
ALT.
: + 15°C
+ 59JF
ENGINE STARTING PNEUMATIC REQUIRWIENTS
5.5.2
AMBIENT TEMPERATURE +lS°C
(+60°F)
MODEL B2-320
act
1980
INOUSTR
AIRBUS
IE
A 300
AIR SUPPLY PRESSURE
I
I
iB! SOLUTEBARS
PS IA
sec.
570
w
60I
4
I
395
3
KILOGRAMS PER MINUTE
125
100
150
175
200
225
250
275
POUNDS PER MINUTE
0 TO 8,000 FT. ALT.
TEMP. AMBIENT : + 15’3C + 60°F
R
5.5
AMBIENT TEMPERATURE +lS°C
(+60°F)
MODEL B2 - B4 - C4
565.2
Ott
1980
Chapter
Page
5
51
AIRBUS
INDUSTR
IE
AIR SUPPLY PRESSURE
PS
LSOLUTE BARS
5
495
60
4
-2
50
= 8,000
FT
395
STIMATED TIME LIMIT TO IO1.E ; 60 sec.
(2 = SEA LEVEL)
3
40
295
AIRFLOW REQUiREO AT GROUND CONNECTION
2
90
KILOGRAMS P%!INUTE
li0.
0
2eu,,,
,,$;2,,,
240
130
120
‘lo
2kI
2i6
9
0
0 TO 8,000
FT. ALT.
TEMP. AMBIENT : + 38%
+ IOO’F
m
a
a
N
5.5
5.5.3
AMBIENT TEMPERATURE +38'C
(+lOO°F)
MODEL B2-320
Chapter
5
Page 52
Ott
1980
AIRBUS
INDUSTR
IE
A30
ATFUSELAGECDNNECTION
AIR SUPPLY PRESSURE
PS
SOLUTE BARS
5
70
MAXIMUM DUCT PRESS”=
Z = SEA LEVEL - 53 psig
43
60
4
50
33
3
40
30
/
i
50
100
AIRFLOW
60
125
70
KILO!&J?S
loo
110
250
150
Pzk
0 TO 8,000 FT. ALT.
TEMP. AMBIENT : +37,8OC
PEf!INUTE
REQUIRED AT GROUND CONNECTION
PER f!f~~
120
130
275
225
+ lOOoF
VI
a
a
R
5.5 ENGINE STARTING PNEUMATIC REQUIREMENTS
5.5?3 AMBIENT TEMPERATURE +38OC (+lOO°F)
MODEL B2 - B4 - C4
Ott
1980
Chapter
Page
5
53
E
.M
V
e
E
;:
p.
5.6
Chapter
5
Page 54
GROUND PNEUMATIC POWER REQUIREMENTS
S-6.1
HEATING (U.S.
UNITS)
MODEL B2 - B4 - C4
I
Feb.
1980
1
AIRBUS
INOUSTR
A
IE
300
3
si
0
I
5.6
I
1 Feb.
1980
GROUND PNEUMATIC POWER REQUIREMENTS
5.6.2
HEATING
(METRIC UNITS)
MODEL 32 - B4 - C4
Chapter
Page
5
55
10
PDUNDSPER
A A 5 05 06 00 0 CM 0
SECON
20
TEMPERATURE
38” C
AT 38%
30
AT GROUND CONNECTION - 1,4’C
OUTSIDE AIR TEtiPERATURE
INITIAL CABIN TEMPERATURE
40
Printed
in France
50
COOLING
60 MINUTES
m
b
-
cl3
0
w
Lo
;Dr
tr
.
-
0 DM 0
20
TEMPERATURE
38” c
AT 38%
30
RELATIVE
HUMIDITY
AT GROUND CONNECTION - 1,4’C
OUTSIDE AIR TEMPERATURE
INITIAL CABIN TEMPERATURE
KG PER’SECOND
10
A A 5 05 06 00
40
Printed
50
in France
COOLING
60
MINUTES
a
CABIN
A
AT
NO GALLEY LOAD
LOAD 405OW
INLET TEMPERATURE
DEGREES CENTIGRADE
03 - 4 - 5- CABIN AT 24’C , NO CREW OR PASSENGERS NO OTHER HEAT LOAD
e 2 - CABIN AT 260,7 C. ALL OTHER CONDITIONS SAME AS IN 1
ELECTRICAL
24’ C PASSENGER AND CREW 279.
BRIGHT DAY SOLAR LOAD 4330W.
el-
01 00
06 00 EM 0
A 00 5 6 PO21
A A 5 05
I?
c
7J
CABIN AT 24’C PASSENGER AND CREW 279.
A
NO GALLEY LOAD
INLET TEMPERATURE
DEGREES CENTIGRADE
I
10
I
5
I
25
I
20
15
I
- 1
_
AT OUTSIDE
T$MP.
I
NOOTHERHEATLOAD
ALL OTHER CONDITIONS SAME AS IN 1
LOAD 405OW
3 - 4 - 5 - CABIN AT 24°C . NOCREWORPASSENGERS
2 - CABIN AT 26,7’C.
BRIGHT DAY SOLAR LOAD 4330W.ELECTRICAL
l-
01 00
06 00 FM 0
A 00 5 B PO22
A A 5 05
I
30
I
35
I
40
I
45
3l
co
C
ul
D
AIRBUS
INDUSTR
IE
A300
5.8 Ground Towing Requirements
The following
charts show the drawbar pull needed to tow the
A 300 under various conditions,
and also the total load needed
on the traction
wheels to enable them to exert this pull without slipping.
Chart S-8-1 is in U.S. Units and chart 5-8-2 is
in Metric Units.
EXAMPLEshown by broken line :
The airplane
at a weight of 290,000 lb (131,542 kg) is being
towed backwards on wet concrete up a 2% slope. Engines are not
running. The drawbar pull required is 19,500 lb (8,845kg).
The total weight on the traction
wheels should be at least
33,000 lb (13,745 kg). If the airplane were being towed with
engines running at idle thrust the pull required would be
24,050 lb (10,900 kg) and the traction
wheels weight 42,350 lb
(19,190 kg).
Chapter 5
Page 60
Feb. 1980 1
(0
B
AIRBUS
INDUSTR
IE
.UNUSUALBREAKAWAYCONDITlONSNOTREFLECTED
o ESTIMATED
FOR RUBBER TIRED TOW VEHICLES
o COEFFICIENTS
OF FRICTION $1 APPROXIMATE
300
A300
I
I4
8
s
a
60
TOTAL TRACTION LOAD x 1000
LBS
01234
PERCENTSLOPE
In
a
a
5.8
I
Feb.
1980
GROUND TOWING REQUIREM.ENTS
5.8.1
( U.S.
UNITS )
MODEL B2 - B4 - C4
Chapter
Page
5
61
INDUSTR
AIRBUS
IE
o UNUSUAL BREAKAWAY CONDITIONS NOT REFLECTED
o ESTIMATED
FOR RUBBER TIRED TOW VEHICLES
o COEFFICIENTS
OF FRICTION (~1 APPROXIMATE
150
A300
125
100
!
NO EiGINE
THRUST
TOTAL TRACTION LOAD x 1000
5.8
Chapter
5
Page 62
KG
I
BAiKING
AGAINST
IDLE
THRUST
i
i
PERCENTSLOPE
GROUND TOWING REQUIREMENTS
5.8.2
(METRIC UNITS)
MODEL B2 - B4 - C4
I
Feb.
1980
1
A300
6.0
OPERATING CONDITIONS
6.1
6.1.1
6.1.2
6.1.3
6.1.4
6.1.5
6.1.6
6.1.7
6.1.8
6.1.9
6.1.10
6.1.11
6.1.12
6.2
6.2.1
6.2.2
6.2.3
6.3
6.3.1
6.3.2
6.3.3
6.3.4
Jet
engine
Exhaust
Exhaust
Exhaust
Exhaust
(Metric
Exhaust
Exhaust
Exhaust
Exhaust
(Metric
Exhaust
Exhaust
Exhaust
Exhaust
Airport
exhaust
velocity
velocity
temperature
temperature
units)
velocity
velocity
temperature
temperature
units)
velocity
velocity
temperature
temperature
and communit
velocities
and temperatures
contours
- Breakaway power (U.S. units)
contours
- Breakaway power (Metric
units)
contours
- Breakaway
power (U.S. units)
contours
- Breakaway power
contours
- Take-off
power (U.S. units)
contours
- Take-off
power (Metric
units)
contours
- Take-off
power (U.S. units)
contours
- Take-off
power
contours
- Idle power (U-S units)
contours
- Idle power (Metric
units)
contours
- Idle power (U.S. units)
units)
contours
- Idle power (Metric
noise
External
noise
Noise data
APU noise levels
Danger
areas
of the
engines
Danger areas forward
of the engines
(Ground idle)
Danger areas forward
of the engines
(Take-off)
Accoustic
protection
areas
APU - Exhaust Gas Temperature
& Velocity
R - Definition
of Breakaway Power
R
Breakaway Power means the minimum
R
to be able to start
moving.
power
necessary
for
the
aircraft
Chapter
6
Page 1
May 01/98
Printed in France
Ft.
5’
-60
I
I -80
FEET lb0
9
3
0a
r;O
ELEVATION
A A 5 06 01 01 0 AA 0
b
S'O
Q AIRPLANE
lb0
ii0
2bo
1 MPH = 1.6 KM PER HOUR
CONVERSION FACTOR
260
8 700 POUNDS OF THRUST
ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR.
BREAKAWAY POWER - SEA LEVEL STATIC, ZERO WIND,
STANDARD DAY, ZERO RAMP GRADIENT ENGINE TYPE.
GROUNDPLANE
NOTE:
3bo
FEET&O
Ft.
-60
I
PLAN
5b
ELEVATION
A A 5 06 01 01 0 AB 0
I
sb
8700
E
150
AIKt’LANt
. ..-...
CONVERSION FACTOR
I MPH = I. 6 km/h
160
GROUND PLANE
POUNDS OF THRUST
2b0
NOTE : ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR.
BREAKAWAY POWER. SEA LEVEL STATIC, ZERO WIND,
STANDARD DAY, ZERO RAMP GRADIENT ENGINE TYPE
2io
3bo
f)
CD
C
u-l
D
METERS30
0
5-
IO-
15-
,A A 5 06 01.02
0 AA 0;
‘?
?
?5
30
1
NOTE:
in France
45
.
“I5
1MPH = 1.6 KM PER HOUR
CONVERSION FACTOR
6,0-
?O
ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR.
BREAKAWAY POWER - SEA LEVEL STATIC, ZERO WIND,
Printed
>
313
m
m
rn
-2
C
mD 03
3ii
-u
;5
z
c)
z
s
7
z
5
z
m
D
I
METERS30
0
5-
lo-
15-
M.
20-
ELEVATION
A A 5 06 01 02 0 AB 0
8700
CONVERSION FACTOR
I MPH = 1.6 km/l,
GROUND PLANE
POUNDS OF THRUST
BREAKAWAY POWER. SEA LEVEL STATIC ZERO WIND
Ft.
FEET lb0
-60
Ft.
A A 5 06 01 03 0 AA 0
5b
il
S'O
lb0
Printed
160
in France
CONVERSION FACTOR
TEMP. FO TO CO
Co = (F” - 32)
1.8
260
2ko
360
NOTE : ALL TEMPERATURES ARE IN DEGREES FAHSENHEIT.
BREAKAWAY POWER - SEAL LEVEL STATIC, ZERO WIND,
STANDARD DAY, ZERO RAMP GRADIENT ENGINE TYPE,
AIRBUS
INDUSTRIE
A
0
0
R
6.1.3
act
1980
6.1 JET ENGINE EXHAUST VELOCITIES
AND TEMPERATURES
EXHAUST TEMPERATURE CONTOURS - BREAKAWAY POWER (U,S*
MODELS B2-320
AND B4-120
UNITS)
Chapter
Page
6
7
METERS 30
15
ELEVATION
A 4 5 06 01 04 0 AA 0
0
15
Q AIRPLANE
30
GROUNDPLANt
. ..-
45
CONVERSION FACTOR
TEMP. FOTO Co
CO = fF”- 32)
-lx-
60
75
NOTE : ALL TEMPERATURES ARE IN DEGREES FAHRENHEIT.
BREAKAWAY POWER - SEAL LEVEL STATIC, ZERO WIND,
90
5
10
15
20
M.
25
METERS30
AA50601
04OABO’
8700
CONVERSION FACTOR
TEMP. F” TO Co
c=(m)
I.8
POUNDS OF THRUST.
NOTE : ALL TEMPERATURES ARE IN DEGREES FAHRENHEIT
BREAKWAY POWER, SEA LEVEL STATIC, ZERO WIND
m
AIRBUS
INDUSTR
A
AIRPLANE
IE
0
CHARACTERISTICS
d
F:
5
L
0
0”
0”
u-l
a
a
R
r:
L
6-1.5
.
iz
AND TEMPERATURES
EXHAUST VELOCITY CONTOURS - TAKEOFF POWER (U.S.
UNITS)
MODEL B2 - B4 - C4
Chapter
6
Page 10
Ott
19eo
-60
Ft.
-80
FEETlhO
Ft.
I -60
5b
ELEVATION
340
I
A A 5 06 01 05 0 AB 0
i
204
I
5b
136
I
lb0
140
CONVERSION FACTOR
I MPH = 1.6 km/h
GROUND PLANE
260
2io
NOTE : ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR
TAKEOFF POWER, SEA LEVEL STATIC, ZERO WIND
3bo
m
-i
a
n
m
C
cn
D
15-
20-
2s
M.
METERS 30
I
PLAN
1,5
A A 5 06 01 06 0 AA 0
?
I5
t
AIRPLANE
3O
4?
50 000
?5
CONVERSION FACTOR
60
I
POUNDS OF THRUST
g?
TAKE OFF POWER - SEA LEVEL STATIC, ZERO WIND,
AIRBUS
INDUSTR
IE
A
J
R
6.1.6
Ott
1980
AND TEMPERATURES
EXHAUST VELOCITY CONTOURS - TAKEOFF POWER (METRIC UNITS)
YODELS B2-320
AND B4-120
Chapter
Page
6
13
AIRBUS
AIRPLANE
R
6,1.7
6.1 JET
EXHAUST
Chapter
6
Page 14
INDUSTR
IE
CHARACTERISTICS
ENGINE EXHAUST VELOCITIES
AND TEMPERATURES
TEMPERATURE CONTOURS TAKEOFF POWER (U.S.
UNITS)
MODEL B2 - B4 - C4
Ott
1980
-20
-40
-60
Ft.
-80
FEET&O
-20
-40
Ft.
-60
300°
200’
50
ELEVATION
250’
A A 5 06 01 07 0 AB 0
ti
5b
160
140
CONVERTION FACTOR
TEMP. F” TO Co
C - (F”-32)
1.8
GROUND PLANE
51 720 POUNDS OF THRUST.
2bo
2bo
NOTE : ALL TEMPERATURES ARE IN DEGREES FAHRENHElT
TAKEOFF POWER,SEA LEVEL STATIC, ZERO WIND
STANDARD DAY, ZERO RAMP GRADIENT ENGINE TYPEa
3bo
b
AiRBUS
INDUSTR
IE
A 300
0
0”
8
u-t
a
a
6.1.8
AND TEMPERATURES
EXHAUST TEMPERATURE CONTOURS TAKEOFF POWER (METRIC UNITS)
MODEL B2 - B4 - C4
Chapter
6
Page 16
Ott
1980
AIRBUS
INDUSTR
IE
A
6.1.8
Ott
AND TEMPERATURES
EXHAUST TEMPERATURE CONTOURS - TAKEOFF POWER (METRIC
MODELS B2-320
AND B4-120
1980
UNITS)
Chapter
Page
6
17
FEET60
5b
A A 5 06 01 09 0 AA 0
I
5iO
I
100
Printed
40
2bo
in France
CONVERSION FACTOR
2bo
3bo
GROUND IDLE POWER - SEA LEVEL STATIC, ZERO WIND,
AIRBUS
INDUSTR
A
IE
0
0
m
a
0
%
Ei
8
In
a
a
R
6.1.9
Ott
1980
AND TEMPERATURES
EXHAUST VELOCITY CONTOURS - IDLE POWER (U.S.
UNITS)
MODELS B2-320
AND B4-120
Chapter
Page
6
19
METERS30
A A 5 06 01
30 0 AA 0
GROUND PLANE
CONVERSION FACTOR
1MPH = ‘1.6 KM PER HOUR
NOTE : ALL VELOCITY VALUES ARE STATUTE MILES PER HOUR,
0
5
10
15
20
M.
25
ELEVATION
A A 5 06 01 10 0 A8 0’
METERS30
-
30
GROUND PLANE
45
60
GROUND IDLE POWER, SEA LEVEL STATIC, ZERO WIND
-20
-40
-60
FEET160
0
II
0 AA 0
5'0
ELEVATION
A A 5 06 01
b
5b
Q. AIRPLANE
lb0
GROUNDPLANE
Printed
lb0
i50
in France
CONVERSION FACTOR
TEMP. FO TO Co
co = (F”- 32)
1.8
2bo
NOTE : ALL TEMPERATURES ARE IN DEGREES FAHRENHEIT.
STANDARD DAY, ZERO RAMP GRADIENT ENGfNE TYPE.
3bo
B
b
FEETdO
5b
A A 5 06 01 11 0 A6 0
i
5b
IdO
CONVERSION FACTOR
TEMP. F” TO Co
ii0
2bo
2io
NOTE : ALL TEMPERATURES ARE IN DEGREES FAHRENHEIT
3bo
5-
lo-
15-
20-
M.
25-
METERS 30
u
A A 5 06
12
0
AA 0
PLAN
ELEVATION
01
15
Q AIRPLANE
30
GROUND PLANE
45
CONVERSION FACTOR
TEMP. F’J TO Co
CO = (FO- 32)
-.-lx--
75
NOTE : ALL TEMPERATURES ARE IN OECREES FAHRENHEIT.
D
m
b
-
INDUSTR
IE
0
m
a
0
N
m
0”
t&t
ln
a
a
I
R
6.1.12
Ott
1980
AND TEMPERATURES
EXHAUST TEMPERATURE CONTOURS - IDLE POWER (METRIC
MODELS B2-320
AND B4-120
UNITS)
Chapter
Page
6
25
AIRBUS
INDUSTR
300
AIRPLANE
6.2 Airport
and Community
IE
CHARACTERlSTlCS
Noise
Noise level
footprint
contours
will
reflect
the noise level
impingement
upon a theoretical
ground level
plane at the same
elevation
as the runway.
Contours
are provided
for both takeoff and landing
operations.
These footprint
contours
will
permit
investigations
of the noise associated
with operation
of the airplane
at individual
airports
as it relates
to the airport
proper
and the adjoining
community.
This will
assist
in planning
investigations
related
to clear
zones, zoning for nonsensitive
land utilization
or
alternate
compatible
land development.
The foregoing
1. Action
noise
data
taken
2. Possible
3. Development
method
availability
on pending
restrictions
depends
legislation
imposed
and acceptance
by the
on :
related
to airplane
regulatory
of a common noise
agencies
measuring
As an interim
measure for airport
planning
it is recommended
that FAA DS-67-14 "Techniques
for Developing
Noise Exposure
Forecasts",
with the exception
of Section
4 "Land Use Planning"
be used as representative
of noise contours
for 2, 3 and 4 engine airplanes.
It must be kept in mind that the data presented is for effective
perceived
noise level
in units
of EPNdB,
and as such must be considered
to have a tolerance
of + 8
EPNdB.
In addition
to the preceding,
table
6.2.2 provides
cerning
engine maintenance
run-up noise to permit
possible
attenuation
requirements.
Chapter
6
Page 26
data conevaluation
Feb.
of
1980
z
2
L
.-c
w4J
.-z
(;:
AIRBUS
INDUSTRIE
A
CONDITIONS
FLight
APPROACH
EXTERNAL
Slats
NOISE
-
Flaps
path without
reduction
LEVEL
0”
0
2o
After
Mod.
1569
2 (21
=( (3)
Ln (4)
After
After
After
Mod.
Mod.
Mod.
1357
1614
1652
z
Take-off
(1)
*
with
Slats
a
a
6.2
Feb.
1980
16”/
Flaps 8”
FIELD HEIGHT
: sea level
ATMOSPHERE
: ISA + 10” without wind
relative humidity 70 %
AIRPORT AND COMMUNITY NOISE
6.2.1
EXTERNAL NOISE
3lODEL B2 - B4 - C4
Chapter
Page
6
27
AIRBUS
INDUSTR
1E
35 Hz (Extrapolated)
63
125
250
500
1000
Hz
Hz
Hz
Hz
Hz
96.7
2000 Hz
GROUND STATIC
TAKEOFF POWER
100 METERS RADIUS
45' LEVELS ARE AVERAGE OF 40’AND
SO’LEVELS
ui
a
a
6.2
Chapter
6
Page 28
AIRPORT AND COMMUNITY
6.2.2
NOISE DATA
MODEL B2 - B4 - C4
NOISE
Feb.
1980
AIRBUS
INDUSTR
IE
0
TO BE ISSUED
6.2
Feb.
1980
LATER
AIRPORT AND COMMUNITY
6.2.2
NOISE DATA
MODEL B2-320
NOISE
Chapter
Page
6
29
AIRBUS
INDUSTR
IE
6.2.3
APU NOISE LEVELS
The figures
presented
hereafter
have been obtained
after
analysis
of third
octave on the 45-11,
200Hz frequency
band in compliance
with Technical
Specifications.
Passenger
door sound levels
were recorded
1.50 metres from cabin
floor
and 0.30 m from outside
fuselage
wall.
SURROUNDING NOISE AT FORWARD/AFT
POINTS OF THE AIRCRAFT:
and in some other
points
(in dB)
-
neasuramt
ConfiQ.
AW ally
Points
operating
at 65%
1
Cmfig.
2
ml
at 84%
+ air
cond.
doors
closed
68.0
Config.
3
APU at 84%
+ air
cond.
some doors
QPm
Config.
4
Aw at 9n
- air
cmd.
FULL HEAT
70.0
n-2
69.8
72-l
m.s
72.3
76.1
80.7
7a.a
82.5
73.9
78.9
78.4
80.6
83.7
88.0
88.1
87.9
82.6
66.0
85.5
86.3
75.7
79.9
79.4
80.2
80.5
81.9
78.2
82.5
82.4
62.7
80.9
82.9
77.7
ai .o
79.9
60.9
75.9
80.2
79.8
80.7
al.3
80.9
80.8
ai .6
80.0
80.8
88.1
90.4
88.0
91.7
MEASUREMENT POINT LOCATION
SURROUN ING NC SE AT T.S.
REMENl
&AJ
Config.
1
APU only
operating
65%
Guarrntees
at
I
0
8323
ConfiQ.
2
Am at 84%
+ air
cond.
rioors
closed
Config.
3
APU at 84%
+ air
cond.
swc
doors
open
71.5
73.9
73.1
1x
83
23
77.1
81.1
81.3
III
Config.
4
APtI at 97x
) air
cond.
FULL HEAT
75.6
G
84.0
86.8
87
2 3
80.4
86.2
86.0
IV
a3
2 3
70.4
72.2.
74.9
V
83:3
75.2
78.5
77.5
a7 z 3
83.8
88.1
86.6
88.9
77.0
m.o*
79.08
a3.0*
82.1
85.2
84.6
86.9
74.4
c
80.8
2
VI
0
a
83
b
8323
c
87
3
85.9
87.7
87.5
90.0
f
a3 + 3
77.5
82.5*
m.o*
79.9
0”
s:
+ 3
*
8
In
a
a
Config.
3
middle
and aft
RH doors
were
open.
Values
marked
: Only
“G”
were
obtained
in the guarantee
conditions,
i-edoors
open.
Cases
pointed
out % correspond
to measureq mts
that
cannot
be proceeded
to.
The values
transcribed
are
estimations
from
measurements
recorded
for
very
ctose
wints,
namely
pt.
3 for
*‘a**, and a point
located
on the same vertical
axis
1.2 m above
the
ground
for
“1”.
6.2 AIRPORT AND COMMUNITY NOISE
6.2.3 APU NOISE LEVELS
MODEL B2 - B4 - C4
Chapter
6
Page 30
Feb.
1980
AIRBUS
INDUSTR
IE
A 300
LEVELS
RECORDED
( AIReseach
AROUND
TSCP 700-S
THE APU
APU 1
MEASUREMENTS ALONG A 30 METRE RADIUS
Config.
1 : APU alone
Config.
2 : APU + ai r cond.
packs
-
---m-a
Config.
3 : APU + air
cond.
packs
- Doors
. . . . . . .. . .
Config.
4 : APU + air
cond.
packs
- Rating
CIRCLE
65%
Doors
closed
- 84%
open
- 84%
on FULL HEAT
- 37%
In
a
a
6.2
Feb.
1980
AIRPORT AND COMMUNITY NOISE
6.2.3
APU NOISE LEVELS
:4ODEL B2 - B4 - C4
Chapter
Page
6
31
...............
................
...............
................
..............
INTAKE
SUCTION
ENTRY
CORRIDOR
SET WAKE
6.3.1
DANGER
AREA
GROUND
............
IDLE
AREA
6.3 DANGER AREAS OF THE ENGINES
DANGER AREAS OF THE ENGINES (GROUND IDLE)
MODEL B2 - B4 - C4
Chapter
6
Page 32
Mar.
1986
km
v
AIRBUS
AIRPLANE
INLET
SUNCTION
ENTRY
EXHAUST
DANGER
AREA
INDUSTR
IE
CHARACTERISTICS
GROUND
IDLE
CORRIDOR
WAKE
DANGER
t
6.3.1
Mar.
1986
6.3 DANGER A-SEAS OF THE ENGINES
DANGER AREAS OF THE ENGINES (GROUND IDLE)
MODEL B2-320
Chapter
Page
6
33
AIRBUS
m
w
INDUSTR
IE
0
Ezl
~NLETSUCTION
DANGER
EXHAUST
DANGER
6.3.2
WAKE
AREA
TAKE
OFF THRUST
DANGER AREAS OF THE ENGINES (TAKE OFF)
MODEL B2 - B4 - C4
Chapter
6
Page 34
Mar.
1986
AIRBUS
AIRPLANE C~ARAC7ERlSTlCS
::.
.*..
.::. ...-:......
.::.
‘. -:.-.-*
7‘ ‘6,P
INTAKE
lsl
SUCTION
JET WAKE
AREA
TAKEOFF
TURUST
AREA
6.3.2
1986
DANGER
DANGER AREAS OF THE ENGINES (TAKE OFF)
MODEL B2-320
Chapter
Page
6
35
AIRBUS
INOUSTR
IE
AIRPCANE CHARACTERISTICS
u-i
a
a
GENERAL ELECTRIC CF6-50C
6.3
6.3.3
Chapter
Page 36
6
ENGINES
DANGER AREAS OF THE ENGINES
ACOUSTIC PROTECTION AREAS
MODEL B2 - ?34 - C4
Feb,
1980
INDUSTR
IE
0
m
a
0
0”
a
0”
m
a
a
PRATT & WHITNEY JT9D59A
ENGINES
6.3.3
ACOUSTIC PROTECTION AREAS
MODEL B2-320
Feb.
1980
Chspter
Page
6
37
A300
AIRPLANE
CHARACTERISTICS
. V-4
IFeet)
-15
50
,40
-10
30
20
-5
10
.O
0
0
R
R
R
6.3
6.3.4
5
10
h-4
10
20
30
40
0
15
50
(Feet)
DANGER AREAS OF THE ENGINES
APU - Exhaust
Gas Temperature
MODEL B2 - B4 - C4
Chapter
6
Page 38
Apr
Printed in France
1995
A300
AIRPLANE
0
CHARACTERISTICS
lb
[m]
4b
R
R
R
1‘5
5'0
(Feet)
6.3 DANGER AREAS OF THE.ENGINES
6.3.4
APU - Exhaust
Gas Velocity
MODEL B2 - B4 - C4
Apr
Chapter
Page
1995
Printed in France
6
39
A300
THIS
Chapter
Page 40
PAGE LEFT
BLANK
INTENTIONALLY
6
Apr
Printed in France
1995
AIRBUS
INDUSTR
IE
A3
7.0
7.1
7.2
7.3
7.4
7.5
z
.,'
L
.s
7.6
7.7
7.8
7.9
I
I
Mar.
PAVEMENT DATA
General Information
Landing Gear Footprint
Maximum Pavement Loads
Landing Gear Loading on Pavement
Flexible
Pavement Requirements
US Corps of Engineers
Design Method
Flexible
Pavement Requirements
LCN Conversion
Rigid Pavement Requirements
- Portland
Cement Association
Rigid Pavement Requirements
LCN Conversion
Aircraft
Classification
Number
Flexible
and Rigid Pavement
1986
Chapter 7
Page 1
AIRPLANE C~ARACTE~rSTfCS
THIS
Chapter
Page 2
PAGE LEFT
BLANK
INTENTIONALLY
7
Feb.
1980
1
AIRBUS
INDUSTR
IE
7.1 GENERAL INFORMATION
A brief
helpful
description
of the appended pavement
in their
use for airport
planning.
charts
will
be
All pavement requirement
charts
give data for a constant
main
gear standardized
tire
pressure
(TRA* ) which will
produce a
tire
deflection
of 32 percent
with the airplane
loaded to the
maximum ramp weight and the C.G. at its maximum permissible
aft position.
.Sub-section
configuration
7.2 gives basic data
and tire
sizes.
Maximum ramp weights
indicated.
Sub-section
loads for
on the
and corresponding
7.3 gives maximum vertical
certain
critical
conditions.
landing
tire
gear
pressures
and horizontal
footprint
are also
pavement
Sub-section
7.4
provides
charts
which show the static
loads
supported
by the main landing
gear struts
for the operational
limits
of the airplane.
These main landing
gear loads are used
for the interpretation
of the attached
pavement design charts
from which load values are extrapolated
when necessary.
For the A300, the certified
C.G's are as follows
:
. 18 to 33 % of the MAC ** for take-off
. 15 to 35 % of the MAC** in flight
and for landing
Sub-section
7.5 presents
pavement requirement
charts
for flexible
pavements based upon format and procedures
set forth
in
SEFL report
No. 165A being "Evaluation
of C-5A (CX-BLS) Aircraft
Ground Flotation
Characteristics
for Operation
from
Flexible
Pavements"
dated Febrary
1965, prepared
by Systems
and Engineering
Group Research and Technology
Division,
Air
Force Systems Command, Wright-Patterson
Air Force Base, Ohio,
U.S.A.
Sub-section
7.6 consists
of LCN conversion
curves for flexible
pavements.
The LCN chart also gives load plots
for airplane
A300 showing equivalent
single
wheel load versus pavement
thickness
"h" for flexible
pavements.
Feb.
*TRA
:
Tire
** MAC
:
Mean Aerodynamic
1980
and Rim Association
Chord
Chapter 7
Page 3
AIRBUS
INDUSTR
IE
A 300
Sub-section
7.7 provides
rigid
pavement design curves prepared
with the use of the Westergaard
Equations
in general
accordance with the procedures
outlined
in the 1955 edition
of "Design
of Concrete
Airport
Pavement"
published
by the Portland
Cement
Association,
Illinois,
U.S.A, but modified
into the new computer program format described
in the 1968 Portland
Cement
Association
publication,
"Computer
Program for Airport
Pavement
Design".
(Programm PDILB) by Robert G. Packard.
The following
design curves
procedure
:
is used to develop
the rigid
pavement
9)
B
2
La.
2
1. Having established
the scale for pavement thickness
to the
left
and the scale for allowable
working
stress
to the
right,
an arbitrary
load line is drawn representing
the main
landing
gear maximum weight
to be shown.
2. All values of the subgrade modules
(k values)
plotted
using the maximum load lines.
are
vCJ
z
‘Z
al
then
3. Additional
load lines
for the incremental
value of weight
on the main landing
gear are then established
on the basis
of the curve for k = 300 psi,
already
established.
Sub-section
7.8 represents
LCN conversion
curves for rigid
pavements having been plotted
using procedures
and curves in
international
Civil
Aviation
Organization
(ICAO) document
7290-AN/865-2,
Aerodrome Manual, part 2, 2nd edition
1965, +
Addendum corrigendum
No. 1 dated 1.8.67.
The LCN charts
also illustrate
load plots
for airplane
A300
showing equivalent
single
wheel load versus radius
of relative
stiffness
factor
for rigid
pavements.
Note
: Pavement requirements
cover
sures presently
planned
for
on the A300.
All curves
pressure,
R
represent
data
loads,
tires
and tire
certified
commercial
at a constant
specified
presusage
tire
CAUTION :
TIRE INFLATING PRESSURES QUOTED BELOW ARE NOMINAL,
AIRPLANE ON JACKS. NOMINAL PRESSURES FOR TIRES
SUPPORTING THE AIRPLANR WHIGHT ARE 4% HIGHER.
OPERATORS SHALL CONFORM WITH THE TIRE‘ INFLATING
PRESSURES QUOTED IN THE RELEVANT MAINTENANCE
DOCUMENTS (MM CH 12 AND 32)
Chapter
Page 4
7
Ott
1980
I
INDUSTR
IE
Sub-section
7.9 represents
the ACN/PCN system as referenced
in
Amendment 35 to ICAO Annex 14, "Aerodromes",
7th Edition,
June
1976, provides
a standardized
international
airplane/pavement
rating
system replacing
the various
S, TT, LCN, AUW, ISWL, etc.,
rating
systems used throughout
the world,
ACN is the Aircraft
Classification
Number and PCN is the Pavement Classification
Number. An aircraft
having an ACN equal to or less than the PCN
can operate
on the pavement subject
to any limitation
on the tire
pressure.
Numerically,
the ACN is two times the derived
singlewheel load expressed
in thousands
of kilograms,
where the derived
single
wheel load is defined
as the load on a single
tire
inflated
to 1.25 MPa (181 psi) that would have the same pavement requirements as the aircraft.
Computationally,
the ACN/PCN system used
the PCA program PD ILB for rigid
pavements
and S-77-l
for flexible
pavements to calculate
ACN values.
The method of pavement evaluation is left
up to the airport
with the results
of their
evaluation presented
as follows
:
PCN
PAVEMENT SUBGRADE TIRE-PRESSURE
TYPE
CATEGORY
CATEGORY
R-Rigid
F-Flexible
Chapter
flexible
A-High
B-Medium
C-Low
D-Ultra
Low
Limit
X-To 1.5MPa
(217 psi)
Y-To l.OMPa
(145 psi)
Z-To 0,SMPa
(73 psi)
W-No
EVALUATION
METHOD
T-Technical
U-Using aircraft
7.9 pages 2 and 3 shows the aircraft
ACN values
pavements.
The four subgrade categories
are :
for
A-High Strength
- CBR 15
B-Medium Strength
- CBR 10
C-Low Strength
- CBR 6
D-Ultra
Low Strength
- CBR 3
Chapter
7.9 pages 4 and 5 shows the aircraft
pavements.
The four subgrade categories
are
ACN values
for
rigid
:
A-High Strength,
k = 150 MN/d
(550 pci)
B-Medium Strength,
k = 80 MN/m3 (300 pci)
C-Low Strength,
k = 40 MN/m3 (150 pci)
D-Ultra
L'ow Strength,
k = 20 MN/m3 (75 pci)
Mar.
1986
Chapter 7
Page 4A
AIRBUS
INDUSTR
IE
THIS
Chapter
7
Page 4B
PAGE LEFT
BLANK INTENTIONALLY
yar.
1986
AIRBUS
INDUSTR
IE
A 300
MDDEL
137,900
304,000
I-lain pear
size
I (standard
Kg
lb
82
02
142,900
315,000
Kg
lb
K
!4ODEL
142,900
315,000
Kg
lb
150,900
332,700
In.
x 16 in.
-20
Kg
lb
84
153,900
Kg
339,300
lb
46
in.
HODfL
158,400
349,200
Kg
lb
165,900
Kg
365,750
lb
165,900
365,750
Stage
I
tire
tiresJ
111
84
Type VII
I
49 in.
x 17
Type
in.
VII
-20
C4
Kg
lb
in.
18.6 m
61.05 ft
t
--
--____I_-
gi6'm
31,496
--
*
T
0.625 m
24.6 in
ft
---
0
a
a
0
z
*TRA standardized
tire
pressure
(TRA: Tire and Rim Association)
=r
z
ln
a
a
**Associated
(60in) for
to a landing
geometry
B2, B4, and C4.
of 0.978m
(38.5i.n)
x 1.524m
7.2 LANDING GEAR FOOTPRINT
MODEL B2 - B4 - C4
Mar.
1986
Chapter 7
Page 5
AIRBUS
INDUSTR
IE
300
THIS
Chapter
Page 6
PAGE LEFT
BLANK
INTENTIONALLY
7
Feb.
1980
in France
STATIC AT MOST
FORWARD CC
“NO
“NG = MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST FORWARD C.G.
"MG = MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST AFT C.G.
H = MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING
NOTE ALL LOADS CALCULATED USING AIRPLANE MAXIMUM GROSS WEIGHT.
A A 5 07 03 00 0 AA 0
Printed
m
INDUSTR
IE
THIS PAGE LEFT BLANC INTENTIONALLY
Chapter
Page 8
7
Feb.
1980
AIRBUS
INDUSTR
I E
300
A
P
8
4
r
.c
.
”
.
._..~ .
350
.
.
..
.
.
.
.
_
.
.
.-.- .
.
.
.
.
.
.
..*
..:
.
._.”
.
*
.i.
il.
.;.._
.:-
‘.
.
I.
._
i...
150
..i...
1429
137.9
300
12!
250
loo
- ..i. + . _
-..
-. ._.- /i.. .
..i:
.:
^...
7!
0
i..
:
.
.
._.
.._i.
*..
.......t
. ..
.
150
__2._
0
....
...
.
,
.. .
. ..-
.;
._._
...
_
............
..
.
_ ...
“..._
.
..”
.-.
:_
. .
. . . . r..
2
.
.
.L
<..”
1 .i . .
i . : .
.i
_:..
. .
:
.
i.
.._.
75
.
..- .
...
i
. .
.-i .
0”
B
b
0
. . . i...
,
lit
Al
In
a
a
i
90
Percentage
7.4-l
Feb.
1980
LANDING
95
of weight
on main landing geer
GEAR LOADING
MODEL B2/B2K
ON PAVEMENT
chapter
Page
7
9
AIRBUS
lNOUSTR
IE
A 300
0
d
:!5”
__.,
_. . .- . . .. . -.
. .
t 18’ ‘:m: : . . ..
. . . . -_.. . -.
. .-..-._. .._. -.. .--.
: ...i_._
. ...-...- ....
.:_
.
.
*.._.__- ._.
. .~
..
90
Percentage of weight
7.4.2
Chapter
7
Page 10
LANDING
95
on main landing
gear
GEAR LOADING ON PAVEMENT
MODEL B4 - C4
Feb.
1980
AIRBUS
INDUSTR
IE
A 300
I
ST ‘ANDARD
I
TIRES
46 x 16 - 20”
TIRE
PRESSURE
CONSTANT
AT
166 psi (11.6
FLEXIBLE
z PAVE MEN7
PC THlCl <NESS__
E
bed
g
2
!Y
25
Weight on main landing gear
1
125
kg
80 000
000
120 000
129 350 +
17270
%%o
220 460 98 060
264550 117680
285 160 126 850
60
(See page 7.4.1)
175
I I I ll1ll
1
3
I Ilil
4 5678910
20
h
0
SUBGRADE
In
STRENGTH
30 40
200
60 80100
(CBR)
a
a
7.5-1.1
FLEXIBLE
PAVEMENT REQUIREMENTS
U.S.
CORPS OF ENGINEERS DESIGN METHOD
MODEL B2 - 137t STANDARD TIRES
Feb.
1980
chapter
Page
7
11
ZIRBUS
INDUSTR
IE
300
A
AIRPLANE
CHARACTERISTICS
=-I EXIBLE
OPTIONAL
TIRES
49 x 17 - 20”
TIRE
PRESSURE
CONSTANT
AT
150 psi (10.35
bard
;j; 2 VEMENT
a TH ICKNESS
Weight on main landing gaar
80 boo
100 000
120000
129350 *
lb
173 370
220 460
264550
285 160
daN
76 450
98 060
117680
126850
3 125
I III
60
(See paga 7.4.1)
I
0
al
a
Maximum possible main gear load
at maximum ramp weight and aft C.G.
0
0”
%
yc
0
1
In
2
3
4
5678910
SUBGRADE
STRENGTH
(CBR)
a
a
7.5.1.2
FLEXIBLE
U.S. CORPS OF ENGINEERS DESIGN METHOD
MODEL B2 - 137t OPTIONAL TIRES
Chapter
7
Page 12
Feb.
1980
AIRBUS
INDUSTR
IE
A 300
STANDARD
TIRES 46 x 16 - 20” TIRE PRESSURE CONSTANT
AT 180 psi (12.4 bars)
z
K
FLEXlBL=
PAVEMEI
THICKNE
r
=
30
40
50
100000
220460
98060
1000 264550 117680
134 040 * 295 500 131450
60
70
1
2
ul
a
3
4
5678910
20
SUBGRADE STRENGTH
30 40
200
60 80100
(CBR)
a
7.5.1.3
FLEXIBLE
U.S.
Feb.
1980
Chapter
Page
7
13
AIRBUS
INDUSTR
IE
A 300
OPTIONAL
TIRES
49 x 17 - 20”
TIRE
PRESSURE
CONSTANT
AT
155 psi (lo.7
ban)
g
EXI6l.E
2 tVEMEN1
TH lICKNESt
r
:
20
5
30
40
80000
100000
120000
134040+
!LLL-LLL! I
173370
220460
264 550
295500
50
78450
iii
117680
131450
t
60
(See page 7.4.1)
70
0
0
a
0
at maximum
I
1
In
ra
Ill
2
3
200
4
5678910
SUBGRADE
a
a
20
STRENGTH
30 40
t
60 80100
(CBFI)
7.5.1.4
FLEXIBLE
Chapter
7
Page 14
Feb.
1980
AIRBUS
- INDUSTR
00
IE
THIS
Feb.
1980
PAGE LEFT
BLANK INTENTIONALLY
Chapter
Page
7
15
AIRBUS
INOUSTR
IE
A 300
STANDARD
TIRES
46 x 16 - 20”
TIRE
PRESSURE
FLEXIBLE
PAVEMENT
THICKNESS
CONSTANT
\I
\\-$-&t
.
-
kg
000
100 000
000
134 040 *
17E370
220 460
264550
295 500
7ds”&o
98 060
117680
131450
”
m 150
m
(See page 7.4.1)
I
I
I
I IIIlllIIlll
125
60
I I I-rrlrrm175
* Maximum possible main gear load
at maximum ram0 weiaht and aft C-G.
t
1
2
3
4
,
NUMBER oF CoVERAGES : 5.000 1
5678910
SUBGRADE
t! :i !iiii! ! ! !i Iiiif
I
20
STRENGTH
30 40
60 801
Y0
(CBR)
7.5.2.1
FLEXIBLE
PAVE-MENT REQUIREMENTS
U.S.
MODEL B2K - 142t STANDARD TIRES
Chapter
7
Page 16
Feb.
1980
AIRBUS
INDuSTR
IE
A 300
AIRPLANE CHARACTERJSTICS
OPTIONAL
TIRES
49 x 17 - 20”
TIRE
PRESSURE
CONSTANT
AT
155 dri (10.7
ban)
H
FLEXIBLE
PAVEMENT
THICKNESS
50
20
75
30
100
40
,
125
kg
80 000
100 000
120 000
134040”
17ib370 ;;!50
220 460 98 060
26 4550 117680
295500 131460
50
60
(See page 7.4.1)
70
0
z!
0
v
2
cu
1
2
z
3
4
20
5678910
SUBGRADE
STRENGTH
30 40
60 801
(CBR)
In
a
a
7.5.2.2
FLEXIBLE
U.S.
MODEL B2K - OPTIONAL TIRES
Feb.
1980
Chapter
Page
7
17
AIRBUS
INOUSTR
IE
THIS
Chapter
7
Page 18
PAGE LEFT
BLANK
INTENTIONALLY
Feb.
1980
AIRBUS
INDUSTR
IE
A 300
STANDARD
TIRES
46 x 16 - 20”
TIRE
PRESSURE
CONSTANT
AT
194 Psi (13.4
bars)
g
F:LEXIBLE
‘AVEMENT
F‘HICKNESS
30
40
90 bO0
110000
130000
141 550*
198 400
242500
286600
312060
50
107870
127500
138800
150
(See page 7.4.2)
I
at maxlmum
ramp weight and aft C-G.
4
NUMB
5678910
SUBGRADE
6
20
STRENGTH
30 40
200
60 80100
t
(CBR)
7.5.3.1
FLEXIBLE
U.S.
Feb.
1980
Chapter
Page
7
19
AIRBUS
INDUSTR
IE
A 300
OPTIONAL
TIRES 49 x 17 - 20”
TIRE PRESSURE CONSTANT
AT lB4 pri (11.3 ban1
gj PP
a ThaLmsucaa
147 550*
312060
138800
60
0
m
a
0
2
0"
2
t
1
v)
2
3
4
5678910
20
SUBGRAOE STRENGTH
a
30 40
60 80100
ICER)
a
7.5.3.2
FLEXIBLE
Chapter
7
Page 20
Feb.
1980
A
I R’S
U S
INDUSTR
IE
300
A
STANDARD
I
I
I I1111
I Illl
I
lllll
I
Illll
I I I IIII
G PAV
a THII
I III1I rii!
NT
2%
kg
90 000
110000
130000
144360
19&00
242500
286 600
* 318250
daN
88 260
107870
127 500
141 570
125
60
page
I I lltm
I
5
u
0
n
0
!s
t
I
I
I I IIIII
2
1
In
3
IIIII
SlkGRADE
u
u
10
4 5678-910
STRENGTH
(CBR)
7.5.3.3
FLEXIBLE
U.S.
Feb.
1980
Chapter
Page
7
21
AIRBUS
INDUSTR
IE
A 300;
OPTIONAL
I
I
TIRES 49 x 17 - 20”
I I I Ill1
TIRE PRESSURE CONSTANT
bars)
sti
j
2
I I1111 I III E
I I lllll
I
Illll
AT 164 psi Ill.3
FLEXIBLE
z PAVEMENT
@Z THICKNESS
I Ill1
daN
90 000
h~llOOO0
198 400
242 506
130000
286600
144360 + 318250
88260
107870
127500
141 570
-I
1
60
(See page 7.4.2)
Ii i i
175
0
0
a
0
at maximum ramp weight and aft C. G.
NUMBER OF COVERAGES
:5.000
0”
200
2
3
4
5678910
20
SUBGRADE STRENGTH
30 40
60 80100
(CBRI
7.5.3.4
FLEXIBLE
Chapter
7
Page 22
Feb.
1980
INDUSTR
IE
STANDARD
TIRES
46 x 16 - 20”
TIRE
PRESSURE
CONSTANT
AT
206 psi 114.2
bard
iij
a
-*
I-LtJ -YIBLE
PAVI EMENT
THIC. :KNESS
__
,120 000
264 550
140 000
308 650
148 850 * 327 560
117680
137 300
145 700
60
(See page 7.4.2)
ZOVERAGES
2
1
3
4
20
5678910
30 40
: 5.
71111
o"60 80 100
0
m
SUBGRADE
STRENGTH
(CBRI
a
a
7.5.3.5
FLEXIBLE
U.S.
MODEL B4 - 157.5t
STANDARD TIRES
Feb,
1980
Chapter
Page
7
23
INDUSTR
IE
AIRPLANE CRARA~TERISTICS
OPTIONAL
TIRES 49 x 17 - 20“ TIRE PRESSURE CONSTANT
AT 172 psi 111.85 bars)
FLEXIBLE
;ii PAVEMENT
fIJ THICKNESS
25
50
20
75
30
40
ka
100 300
120000
lb
22060
264550
308 650
148 850 * 327 660
daN
--- 98 060
125
50
117fMcl
- ---
ii7 300
145 700
60
(See page 7.4.2)
0
2
0
0”
0”
r-0
1
2
3
4
5678910
20
30 40
200
60 80100
v)
SUBGRADE STRENGTH
a
(CSR)
a
7.5.3.6
FLEXIBLE
MODEL B4 - 157.5t
OPTIONAL TIRES
Chapter
7
Page 24
Feb.
1980
AIRBUS
INDUSTR
IE
A 300
OPTIONAL
TIRES
49 x 17 - 20”
TIRE
PRESSURE
CONSTANT
AT
172 psi Ill.8
li; PA
IL: Tk
bad
00000
20000
~+#=++=++j-‘~ 30 000
850 *
t
at maximum
t
1
v)
ramp weight and- aft
- _C-G.
-_-_
1 1 I lllll
2
3
4
1Sfl
.“W
(See page 7.4.2)
I
1 I I IIII
IIlI
I
I I , ,
!
:
; : j I I
NUMBER OF COVERAGES
:,831
5.000.
‘II
60
i
I
I I I I I I I I I I I 12oo
1 I Ill
51 578'910
SUBGRADE
a
220460
98060
264550 117680
286 600 727 500
327 560 i415 700
20
STRENGTH
30 40
60 80100
K%Fl)
a
N
7.5.3.7
FLEXIBLE
U.S.
MODEL B4 - 157,St
OPTIONAL TIRES
LANDING GEAR GEOMETRY
38"5x60"
Ott
1980
Chapter
Page
7
25
AIRBUS
INDUSTR
A
AIRPLANE
STANDARD
115
0
CHARACTERISTICS
FLEXIELE
2 PAVEMENT
1: THICKNESS
ii
2
ii
iu
2
25
50
75
100
-1
125
m
100 500
120000
IO
155 600 *
220460
264550
308 650
343 040
117680
137 300
152 590
_
(See page 7.4.2)
_
at maximum
0”
0”
b
0
In
a
a
-60
175
0
8
a
0
150
-
1
1
N
1
ramp weight and aft C.G.
1 I lllll
2
3
! !!!I!
!!I
NUMBER OF Co\lEFA,GES :,UJ$
Illll
Ill11
4
5678910
'70
20
SUBGRADE STRENGTH
30 40
III
60 80 1 2ooo
(CBR)
7-5.3.8
FLEXIBLE
MODEL B4-C4 - 165t STANDARD TIRES
Chapter
7
Page 26
Ott
198G
AIRBUS
INDUSTR
IE
A 300
STANDARD
TIRES
49 x 17 - 20”
TIRE
PRESSURE
CONSTANT
AT
180 psi 112.4
bed
E
FLEXIBLE
PAVEMENT
THICKNESS
50
20
75
30
40
2&60
264 550
308 650
343 040
daN
96 060
117680
137 300
152 590
125
50
60
!e page 7.4
70
f
.
I
1
I I IIll
2 3 4
-
Illll
I I I Illll
5678910
20
SUBGRADE
N
STRENGTH
30 40
IIII
60 80'
ICBR)
7.5.3.9
FLEXIBLE
U.S.
MODEL B4-C4 - 165t
STANDARD TIRES
LANDING GEAR GEOMETRY
38”5x60”
Ott
1980
Chapter
Page
7
27
INDUSTR
AIRBUS
IE
A30
OPTIONAL
I
I
j
VW
lli
I I ! I IA A?izI
I
FLEXIBLE
- -AVEMENT
zr
1‘HICKNESS
I
I
I II
I
,.:. . . ..
{Ill
I IIll
,30
75
60
.
I
0
.
,,
II
,
,
1111
II
I
I
-
III1
a
0
a
1
22
G
I
I I 3Illll4
2
I
I IIll
IIlll
II
5678910
I Iii
IIll
NuMBEl
30 40
20
SUBGRADE STRENGTH
m
I
I
I
200
WV60 80100
(CBR)
a
a
7.5.3.10
FLEXIBLE
PAVEMENT REQUIRE;ENTS
U .S. CORPS OF ENGINEERS DESIGN iJETHOD
P:ODEL B4-C4 - 165t OPTIWAL
TIRES
Chapter
7
Page 28
Ott
1980
AIRBUS
INDUSTR
IE
A 300
7.6
FLEXIBLE PAVEMENT REQUIREMENTS - L.C.N.
CQNVERSION
In order to determine
the airplane
weight
that can be accommodated on a particular
flexible
airport
pavement,
both the LCN
of the pavement and the thickness
"h" of the pavement must be
known.
Example
No.
1
Determination
of the LCN of an A300 on a given
Data :
. Runway
e Aircraft
A300 B2
- Tires
: 46 x
- Average C.G.
runway.
: h = 25"
: Ramp weight
132 t
16-20 (standard)
position
a) Determination
of the weight
average C.G, position
Refer Page 7.4.1
- Load on main landing
on main
gear
landing
: 91 % of the
gear
total
for
load
the
:
132T-.x 91
100
= 120 T
b) Aircraft
LCN at "h" = 25"
Refer to page 7.6.1.1
Aircraft
LCN : 73
Example
No. 2
Determination
runway.
of
the max.' ramp weight
admissible
on a given
Data :
. Runway
: LCN 68
Thickness
: 48 cm
. Aircraft
A300 B4 basic
(150 T)
- Tires
: 49 x 17-20 (option)
- Max. aft C-G. position
a) Determination
of the max. admissible
gear
Refer to page 7.6.3.2
Admissible
Feb.
1980
weight
on main
landing
load
gear
on main
: 125,000
landing
kg.
Chapter 7
Page 29
INDUSTR
IE
b) Determination
of the max. permissible
Refer to page 7.4.2
aircraft
- % of weight on main landing
gear : 93.8
- Max. admissible
aircraft
ramp weight
:
ramp weight
%
125 000 kg x 100
93.8
= 133 260 kg
Chapter
7
Page 30
Feb.
1980
AIRBUS
f+$jhJDus+RlE
300
7.6.1-l
Mar.
1986
FLEXIBLE
PAVEMENT REQUIREMENTS L.C.N.
CONVERSION
Chapter
Page
7
31
AIRBUS
INDUSTR
IE
AIRPLANE
CHARACTERISTICS
8
P
rt
.P
-. -.- ___ .
---..
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E
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00
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7.6.1.2
Chapter
7
Page 32
FLEXIBLE
CONVERSION
Mar.
1986
AIRBUS
m
WINI
3USTR
IE
.f
7.6.1.3
Mar.
1986
FLEXIBLE
CONVERSION
Chapter
Page
7
33
AIRBUS
m
w
INDUSTR
IE
A 300
--.-_
.
-----.
-...
.
.__
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I
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7.6.1,4
Chapter
7
Page 34
FLEXIBLE
CONVERSION
Mar.
1986
INDUSTR
AIRBUS
IE
A30
AIRPLANE CHARACTERlSTiCS
THIS
Feb.
1980
PAGE LEFT
BLANK
INTENTIONALLY
Chapter
Page
7
35
50
60
70
80
100
90
s
dg
r
f
EOUIVALENT
SINGLE
WNEEL
LOAD
A.-..\
.
.
.
m
'i...:.
I
40
1
30
CONSTANT
60
FLEXIBLE
60
70 80
PAVEMENT
'
THtCKNESS
I.
100
bat
40!
THICKNESS
A,
WElOW
POSSIBLE
MAIN GEAR.LOAD
MIX,M”M
RAMP
AN0 APT CG _
MAXIMUM
301
180 p~i112.40
26
AT
46 I 1fJ. 20”
. 201:
PAVEMENT
SINGLE WHEEL
LOADS
BY METHODS
SHOWN
TIRES
PRESSURE
NOTE :
EQUIVALENT
ARE DERIVED
TIRE
STANOARO
-.
CLEXlSLl
-
IINCHES)
60
150
ICENTIME~ERSI
I”
!*1*I.'-!-I"'r
:
SO
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200
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:
100
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Printed
300
1.
!
.
..
.
ka I295940
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kg ,2204CiO
km llSS4Oll
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SO000
in France
LOAD
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CLASSIFICATION
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124240
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1
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NUMI.ER
IL.C.Nl
AIRBUS
INDUSTR
IE
A
--_____ __-_--.
.._. . ....-- -.-I--_ . . --._ .- - .--.
_-_
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..._._-
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._
8
7.6.2.2
Mar.
1986
Ogl-2
W
5:
s
I3
a
R
FLEXIBLE
MODEL B2K - 142t OPTIONAL
w
e
L.C.N.
TIRES
CONVERSION
Chapter
Page
7
37
AIRBUS
INDUSTR
A
IE
300
THIS
Chapter
7
Page 38
PAGE LEFT
BLANK INTENTIONALLY
Feb.
1980
:
:
2.‘
/”
p
f
10
it
EOUIVALENI
SINGLE
WHEEL
LOAO
’
I
20”
AT
25
194 pril13.37
I
30
PAVEMENT
.
bar
I
40
I
30
FLEXIBLE
50
60
I
4:
80
PAVEMENT
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aI
100
i
THICKNESS
j
:
IINCHES)
50
60
.
”
.
ICENT1METERSI
150
.
.
- -
200
1
70 80
I * 1-1”“~‘~““’
40
THICKNESS
‘1
NOTE :
EOUIVALENT
sra31.Ewnfm LOADS
ARE DERIVED
BY METHODS
SkIOWN
IN ICAO AERODRGME
MANUAL
9157. AN1901.1977.
PART 3. PARA 1.3
I
!
uAY1”II”llncP*PI
. . . _. . ..-. _. . ___, “_. c
MAIN OEAR.LOAO
AT
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ANCI AFT co
,
STANDARD
TIRES 46 I 16.
TIRE PRESSURE
CONSTANT
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I I.i.!lii!tI
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100
‘.
300
._ _,.. .___
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,
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100000
90000
LOAD
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110000
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130000
Ibl
kg 13125Oi
141750
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WEIGHT
ON MAlL
LANDtNO
GEAR
SEE PAGE 7.4.2
_
in France
:
i..
60
I
70
NUMSER
I
,L.C.N,
AIRBUS
m
w
INOUSTR
IE
. ,\i
j
I *
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I .i.
1;
*--7
.
7.6.3.2
Chapter
7
Page 40
.
I
..:I/
..
.
FLEXIBLE
I
II ,
i :
: .j- ;
1.;
CONVERSION
Mar.
1986
AIRBUS
INDUSTRIE
30
----
--..
-.
.
. ..+---
-._.
---
___
....-_
.- _.
7.6.3.3
Mar.
1986
FLEXIBLE
CONVERSION
Chapter
Page
7
41
60
60
70
80
100
90
160
.
m
10’0
16
26
30
40
60
60
70
80
26
40
60
6[
70
80
1'00
;
-
.
-
.
I
,
AT 167p&i/llbSbFr
I
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40
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FLEXIDLE
60
PAVEMENT
AT
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THICKNESS
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;
;
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.
.
-
ICENTIMETERSI
:
.-.
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.-
.-_
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i ’
60
160
(INCHESI
60
1 I * I ’
40
THICKNSSS
WC‘GH,
7U 8U
RAM?
CO
GEA‘bLOAO
MAXIMUM
AN0 AFT
MAIN
NOTE:
CGUIVALENT
SINGLE WHEEL
LOADS
ARE DERIVED
BY METHODS
SHOWN
IN ICAO AEROOAGME
MANUAL
9157. AN1901.1977.
PART 3. PAAA 1.3
1
!
MAXIMUM
POSSl9LE
OPTIONAL
TIAES49*
17.20”
T)RS PRSSSUR~CGNSTANT
I
T
t t3 .._I .ii .I i ,i 1..I..i I.
30
PAVEMLNf
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EQUIVALENT
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(
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CLASSIFICATION
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Ibi
lbl-
Ibl
IM
40
kg llSD4Op
kg 02045~
in France
““p
100OMl
1242SCfIbl
kg (26466f
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7.4.2
SEE PAGE
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OEAR
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14467b
14oooO
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70 80
’
;’
NUMBER
tL,C,NI
AIR
INDUSTR
IE
a
-p
f
$
g gf
v-w
7.9.6-10
RIGID
Chapter
7
Page 126
AIRCRAFT CLASSIFICATION
NUMBER
PAVEMENT - OPTIONAL TIRES
MODEL B4 - C4 - 165t
Mar.
1986
A300
R 8.0
DERIVATIVE AIRPLANES
R
8.1
Possible Future A300 Derivative Airplanes
Chapter 8.0
Page 1
DEC 01/09
R
Printed in France
A300
8.1 Possible Future A300 Derivative Airplanes
R
No derivative versions of the “A300” are currently planned.
Chapter 8.1
Page 1
DEC 01/09
R
Printed in France
A300
R 9.0
SCALED DRAWINGS
R
9.1
A300 Scaled Drawing 1 in. = 500 ft.
R
9.2
A300 Scaled Drawing 1 cm. = 500 cm.
Chapter 9.0
Page 1
DEC 01/09
R
Printed in France
A300
9.1.1 Scaled Drawing — 1 in. = 500 ft.
Model B2 – B4
Chapter 9.1.1
Page 1
DEC 01/09
R
Printed in France
A300
Model B2 – B4
Chapter 9.1.1
Page 2
DEC 01/09
R
Printed in France
A300
Model C4
Chapter 9.1.1
Page 3
DEC 01/09
R
Printed in France
A300
Model C4
Chapter 9.1.1
Page 4
DEC 01/09
R
Printed in France
A300
9.2.1 Scaled Drawing — 1 cm. = 500 cm.
Model B2 – B4
Chapter 9.2.1
Page 1
DEC 01/09
R
Printed in France
A300
Model B2 – B4
Chapter 9.2.1
Page 2
DEC 01/09
R
Printed in France
A300
Model C4
Chapter 9.2.1
Page 3
DEC 01/09
R
Printed in France
A300
Model C4
Chapter 9.2.1
Page 4
DEC 01/09
R
Printed in France

A300 - Airbus

Transcription

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