airport planning manual
TRANSCRIPT
AIRPORT PLANNINGMANUAL
APM-225928 JUNE 2005
REVISION 5 - 07 OCTOBER 2008
EMBRAER S.A - P.O. BOX 8050
12227-901 SAO JOSE DOS CAMPOS - S.P.
BRAZIL
PHONE: + + 55 12 3927-7517
FAX: + + 55 12 3927-7546
http://www.embraer.com
e-mail: [email protected]
Copyright 2008 by EMBRAER - Empresa Brasileira de Aeronautica S.A. All rights reserved.This document shall not becopied or reproduced, whether in whole or in part, in any form or by any means without the express written authorizationof Embraer. The information, technical data, designs and drawings disclosed in this document are proprietary information
of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer.
REVNo.
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DATEINSERTED
BYREVNo.
ISSUEDATE
DATEINSERTED
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RECORD OF REVISIONS
The user must update the Record of Revisions when a revision is put into the manual.
RETAIN THIS RECORD IN THE FRONT OF MANUAL OR CHAPTER.ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER REVISION NUMBER, DATEINSERTED AND INITIALS.
TitleTRList
1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/072 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/07
SBList1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/062 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/06
List of Effective Pages
* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08Table of Contents
* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
List of Tables1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/062 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/05
List of Figures
* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/083 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/074 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/06
Section 11-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/061-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/061-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/061-4 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/05
Section 2
* 2-1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 2-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/062-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/062-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/052-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/062-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/062-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/062-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
* 2-10 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/052-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/052-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/052-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/06
Section 3(Not Available)Section 4
* 4-1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 4-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 4-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/05
* 4-5 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 4-6 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 4-7 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 4-8 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 4-9 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
* 4-10 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08Section 5
5-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/055-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/055-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/055-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/055-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/055-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
* 5-14 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08Section 6
6-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/056-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/056-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/056-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/056-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/056-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
Section 77-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/06
AIRPORTPLANNING MANUAL
Pages revised or added by the current revision are indicated by an asterisk (*). Pages deleted by the currentrevision are indicated by * (del). Pages deleted by the previous revision are indicated by (del).
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7-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/067-18 Blank . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/06
Section 88-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/058-2 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/05
Section 99-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/059-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/059-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/059-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/059-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/059-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 28/05
AIRPORTPLANNING MANUAL
Pages revised or added by the current revision are indicated by an asterisk (*). Pages deleted by the currentrevision are indicated by * (del). Pages deleted by the previous revision are indicated by (del).
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TABLE OF CONTENTS
SECTION 1 - SCOPE
1. Scope .............................................................................................................................. 1-11.1. Purpose ........................................................................................................................... 1-11.2. Introduction ..................................................................................................................... 1-11.3. Abbreviations .................................................................................................................. 1-2
SECTION 2 - AIRCRAFT DESCRIPTION
2. Aircraft Description .......................................................................................................... 2-12.1. Aircraft Characteristics .................................................................................................... 2-12.2. General Aircraft Dimensions ............................................................................................ 2-22.3. Ground Clearances ......................................................................................................... 2-52.4. Interior Arrangement ........................................................................................................ 2-82.5. Passenger Cabin Cross Section ..................................................................................... 2-112.6. Lower Compartment Containers ...................................................................................... 2-132.7. Door Clearances ............................................................................................................. 2-14
SECTION 3 - AIRCRAFT PERFORMANCE (NOT AVAILABLE)
SECTION 4 - GROUND MANEUVERING
4. Ground Maneuvering ....................................................................................................... 4-14.1. General Information ......................................................................................................... 4-14.2. Turning Radii ................................................................................................................... 4-14.3. Minimum Turning Radii ................................................................................................... 4-34.4. Visibility From Cockpit ..................................................................................................... 4-44.5. Runway and Taxiway Dimensions ................................................................................... 4-54.6. Runway Holding Bay ....................................................................................................... 4-10
SECTION 5 - TERMINAL SERVICING
5. Terminal Servicing ........................................................................................................... 5-15.1. Aircraft Servicing Arrangement ........................................................................................ 5-25.2. Terminal Operations - Turnaround Station ....................................................................... 5-45.3. Terminal Operations - En Route Station .......................................................................... 5-65.4. Ground Servicing Connections ........................................................................................ 5-75.5. Engine Starting Pneumatic Requirements ....................................................................... 5-95.6. Ground Pneumatic Power Requirements ........................................................................ 5-115.7. Preconditioned Airflow Requirements .............................................................................. 5-125.8. Ground Towing Requirements ......................................................................................... 5-14
SECTION 6 - OPERATING CONDITIONS
6. Operating Conditions ....................................................................................................... 6-16.1. Engine Exhaust Velocities and Temperatures .................................................................. 6-26.2. Airport and Community Noise ......................................................................................... 6-86.3. Hazard Areas .................................................................................................................. 6-9
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SECTION 7 - PAVEMENT DATA
7. Pavement Data ............................................................................................................... 7-17.1. General Information ......................................................................................................... 7-17.2. Footprint .......................................................................................................................... 7-27.3. Maximum Pavement Loads ............................................................................................. 7-37.4. Landing Gear Loading on Pavement ............................................................................... 7-47.5. Flexible Pavement Requirements, U.S. Corps of Engineers Design Method .................. 7-57.6. Flexible Pavement Requirements, LCN Method .............................................................. 7-77.7. Rigid Pavement Requirements, Portland Cement Association Design Method ............... 7-97.8. Rigid Pavement Requirements, LCN Method .................................................................. 7-117.9. ACN - PCN System - Flexible and Rigid Pavements ...................................................... 7-15
SECTION 8 - POSSIBLE EMBRAER 175 DERIVATIVE AIRCRAFT
8. Possible EMBRAER 175 Derivative Aircraft .................................................................... 8-18.1. Not Applicable ................................................................................................................. 8-1
SECTION 9 - SCALED DRAWINGS
9. Scaled Drawings ............................................................................................................. 9-19.1. General ........................................................................................................................... 9-1
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LIST OF TABLES
TABLE TITLE SECTION PAGE
1.1 APM Arrangement .................................................................................. 01 1
2.1 Aircraft General Characteristics ............................................................. 02 2
2.2 Ground Clearance - STD Aircraft Model ................................................ 02 6
2.3 Ground Clearance - LR Aircraft Model................................................... 02 7
2.4 Capacity of the Cargo Compartment ..................................................... 02 10
4.1 Reference Codes.................................................................................... 04 5
7.1 Pavement Evaluation.............................................................................. 07 15
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LIST OF FIGURES
FIGURE TITLE SHEET SECTION PAGE
2.1 General Aircraft Dimensions ................................................. 02 4
2.2 Ground Clearances ............................................................... 02 5
2.3 Typical Interior Arrangements ............................................... 02 9
2.4 Economy Class Passenger Cabin Cross-Section................. 02 11
2.5 First Class Passenger Cabin Cross-Section......................... 02 12
2.6 Door Dimensions................................................................... 02 14
4.1 Turning Radii - No Slip Angle ............................................... 04 2
4.2 Minimum Turning Radius ...................................................... 04 3
4.3 Visibility from Cockpit in Static Position................................ 04 4
4.4 More than 90° Turn - Runway to Taxiway ............................ 04 7
4.5 90° Turn - Runway to Taxiway .............................................. 04 8
4.6 90° Turn - Taxiway to Taxiway .............................................. 04 9
4.7 Runway Holding Bay............................................................. 04 10
5.1 Aircraft Servicing Arrangement With Passenger Stairs ........ 05 2
5.2 Aircraft Servicing Arrangement With Passenger Bridge ....... 05 3
5.3 Air Terminal Operation - Turnaround Station ........................ 05 5
5.4 Ground Servicing Connections ............................................. 05 7
5.5 Ground Servicing Connections ............................................. 05 8
5.6 Engine Starting Pneumatic Requirements - Airflow x Tem-perature ................................................................................. 05 9
5.7 Engine Starting Pneumatic Requirements - Pressure xTemperature .......................................................................... 05 10
5.8 Ground Pneumatic Power Requirements ............................. 05 11
5.9 Preconditioned Airflow Requirements ................................... 05 13
5.10 Ground Towing Requirements............................................... 05 14
6.1 Jet Wake Velocity Profile - Takeoff Power ............................ 06 2
6.2 Jet Wake Temperature Profile - Takeoff Power .................... 06 3
6.3 Jet Wake Velocity Profile - Ground Idle................................ 06 4
6.4 Jet Wake Temperature Profile - Ground Idle ........................ 06 5
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FIGURE TITLE SHEET SECTION PAGE
6.5 Jet Wake Velocity Profile - Breakaway Power...................... 06 6
6.6 Jet Wake Temperature Profile - Breakaway Power .............. 06 7
6.7 Hazard Areas - Takeoff Power .............................................. 06 9
6.8 Hazard Areas - Ground Idle .................................................. 06 10
7.1 Footprint ................................................................................ 07 2
7.2 Maximum Pavement Loads................................................... 07 3
7.3 Landing Gear Loading on Pavement .................................... 07 4
7.4 Flexible Pavement Requirements - US Army Corps of En-gineers Design Method ......................................................... 07 6
7.5 Flexible Pavement Requirements - LCN Method ................. 07 8
7.6 Rigid Pavement Requirements - Portland Cement Associa-tion Design Method ............................................................... 07 10
7.7 Radius of Relative Stiffness .................................................. 07 12
7.8 Radius of Relative Stiffness (other values)........................... 07 13
7.9 Rigid Pavement Requirements - LCN Method ..................... 07 14
7.10 ACN For Flexible Pavement ................................................. 07 16
7.11 ACN For Rigid Pavement...................................................... 07 17
9.1 Scale: 1 Inch Equals 32 Feet................................................ 09 2
9.2 Scale: 1 Inch Equals 50 Feet................................................ 09 3
9.3 Scale: 1 Inch Equals 100 Feet.............................................. 09 4
9.4 Scale: 1 to 500...................................................................... 09 5
9.5 Scale: 1 to 1000.................................................................... 09 6
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1. SCOPE1.1. PURPOSE
This document provides airplane characteristics for general airport planning. Since the operationalpractices vary among the airlines, specific data should be coordinated with the using airlines before thefacility design is made.EMBRAER should be contacted for any additional information required.
1.2. INTRODUCTION
The APM has been prepared in accordance with NAS 3601.It provides aircraft characteristics for general airport planning, airport operators, airlines, and engineer-ing consultant organizations.The APM is arranged as shown in the table below:
Table 1.1 - APM ArrangementARRANGEMENTS CONTENTS
Manual Front Matter
Title PageCostumer Comment FormHighlightsRecord of Revision SheetTemporary Revision SheetList of Service BulletinsList of Effective PagesTable of ContentsList of TablesList of Figures
Section
ScopeAircraft DescriptionAircraft PerformanceGround ManeuveringTerminal ServicingOperating ConditionsPavement DataPossible Derivative AircraftScaled Drawings
The front matter for the whole manual contains:
• Title Page: Shows the manufacturer’s masthead, identification of the manual, the initial issue date,and revision number and date.
• Highlights: Advises the operator on the revised pages.
• Record of Revisions Sheet: Lists the successive revision numbers, issue date, insertion date andincorporators initials, which must be kept current by the operator.
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• List of Service Bulletins: Lists the Service Bulletins, including all issued revisions, which affect themanual as well as the affected section(s) (APM Section Number), the aircraft affected by the ServiceBulletin, and the date of incorporation of the SB in the manual.
• Temporary Revision Sheet: Lists the temporary revision numbers, page number, issue date, personresponsible for the insertion and insertion date.
• List of Effective Pages: Lists all sections and their list of effective pages with the latest issue dates.
For additional information, please contact:
• For assistance regarding purchasing and distribution of manuals (in hard copies or CD-ROM), pleasecontact us through the e-mail: [email protected]
• For assistance regarding technical contents related to Maintenance Technical Publications, GSE,and Service Bulletins, please contact us through the e-mail: [email protected]
• For Digital Technical Publications support, please contact us through the e-mail:[email protected]
1.2.1. Revisions
Embraer may revise this manual periodically as required to update information or provide informationnot available at the time of printing.Revised data may result from Embraer approved aircraft modifications and new available options.Changes to the text are indicated by a black bar in the page left-side margin, beside the revised, added,or deleted material.Relocated or rearranged text or illustrations will be indicated by a black bar beside the page number.
1.3. ABBREVIATIONS
This list gives all the abbreviations, acronyms and measurement units used in this manual with theirdefinitions.
Table 1.2 - List of Acronyms and Abbreviations used in the APMACRONYMS AND ABBREVIATIONS DESCRIPTION°C Degree Celsius°F Degree Fahrenheit! LiterACN Aircraft Classification NumberAFM Airplane Flight ManualAOM Airplane Operations ManualAPM Airport Planning ManualAPU Auxiliary Power UnitATTCS Automatic Takeoff-Thrust Control-SystemBOW Basic Operating WeightCBR California Bearing RatioECS Environmental Control SystemFAA Federal Aviation AdministrationFAR Federal Aviation RegulationsFWD Forward
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Table 1.2 - List of Acronyms and Abbreviations used in the APM
ACRONYMS AND ABBREVIATIONS DESCRIPTIONGEAE General Electric Aircraft EnginesICAO International Civil Aviation OrganizationISA International Standard AtmosphereJAR Joint Aviation RequirementsLCN Load Classification NumberLH Left-HandLR Long RangeMLW Maximum Landing WeightMRW Maximum Ramp WeightMTOW Maximum Takeoff WeightMZFW Maximum Zero Fuel WeightN NewtonRBHA Requisitos Brasileiros de Homologação AeronáuticaRH Right-HandSTD StandarddBA A-Weighted Decibelft Footft2 Square Footft3 Cubic Footgal. Gallonin Inchin2 Square InchinHg Inch of MercurykPa Kilopascalkg Kilogramlb Poundlb/in3 Pound per Cubic Inchlbf Pound Forcem Meterm2 Square Meterm3 Cubic Metermin Minutepsi Pounds per Square Inch
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2. AIRCRAFT DESCRIPTION2.1. AIRCRAFT CHARACTERISTICS
The aircraft is:
• Predominantly metallic;
• Low winged;
• Conventional tailed;
• Monoplane;
• Retractable tricycle-type with twin-wheeled landing-gear.
There are two high bypass ratio turbofan GEAE CF34–8E with 63.2 kN (14200 lbf) maximum takeoffthrust (sea level, static and ISA + 15 °C) installed under the wings.The aircraft has two versions, with different ranges () as a function of the difference between theMTOWs:
• The STD aircraft model - MTOW 37500 kg (82673 lb)
• The LR aircraft model - MTOW 38790 kg (85517 lb)
2.1.1. Definitions
MRW
It is the maximum allowed aircraft weight for taxiing or maneuvering on the ground.
MLW
It is the maximum allowed weight with which the aircraft can normally be landed.
MTOW
It is the maximum allowed total loaded aircraft weight at the start of the takeoff run.
BOW
It is the weight of the structure, powerplant, instruments, flight controls, hydraulic, electronic, electrical,air conditioning, oxygen, anti-icing and pressurization systems, interior furnishings, portable and emer-gency equipment and other items of equipment that are an integral part of the aircraft configuration. Italso includes unusable fuel, total engine and APU oil, total hydraulic fluid, toilet fluid and water, potablewater, crew and crew baggage, navigation kit (manuals, charts), catering (beverages and food) andremovable service equipment for the galley.
MZFW
It is the maximum allowed weight without usable fuel in the tanks.
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Maximum Payload
It is the difference between the MZFW and the BOW.
Maximum Seating Capacity
It is the maximum number of passengers specifically certified or anticipated for certification.
Maximum Cargo Volume
It is the maximum space available for cargo.
Usable Fuel
Fuel available for the aircraft propulsion.
Table 2.1 - Aircraft General Characteristics
DESIGN WEIGHTS[1] AIRCRAFT MODELSSTD LR
MRW 37660 kg (83026 lb) 38950 kg (85870 lb)MTOW 37500 kg (82673 lb) 38790 kg (85517 lb)MLW 34000 kg (74957 lb)
BOW [2] 21500 kg (47399 lb)MZFW 31700 kg (69886 lb)
Maximum Payload [2] 10200 kg (22487 lb)Maximum Seating Capacity 86 passengersMaximum Cargo Volume [3] 17.12 m3 (604.59 ft3)
UsableFuel [4]
9428 kg (20785 lb)11625 ! (3071 gal.)
1. Applicable for standard models. For further information, refer to AFM and AOM.2. Standard configuration (weights may vary according to optional equipment installed or interior layouts).3. Standard configuration (volume may vary according to optional equipment installed).4. Adopted fuel density of 0.811 kg/! (6.77 lb/gal.)
2.2. GENERAL AIRCRAFT DIMENSIONS
2.2.1. External Dimensions
• Span over winglets - 26.00 m (85 ft 4 in.)
• Height (maximum) - 9.82 m (32 ft 3 in.)
• Overall length - 31.68 m (103 ft 11 in.)
2.2.2. Wing
• Reference area - 72.72 m2 (783 ft2)
• Reference aspect ratio - 8.6
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2.2.3. Fuselage
• Total Length - 31.68 m (103 ft 11 in.)
• Length of pressurized section - 24.52 m (80 ft 5 in.)
2.2.4. Horizontal Tail
• Span - 10.00 m (32 ft 9 in.)
• Area - 23.25 m2 (250 ft2 37 in2)
2.2.5. Vertical Tail
• Reference area - 16.20 m2 (174 ft2 55 in2)
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5.20 m(17 ft)
20.00 m(65 ft 7.4 in.)
7.66 m(22 ft 11.6 in.)
11.40 m(37 ft 5 in.)
9.82 m(32 ft 3 in.)
4.71 m(15 ft 5.4 in.)
23.04 m(75 ft 7 in.)
10.00 m(32 ft 9 in.)
26.00 m(85 ft 4 in.)
4.27 m(14 ft )
23.04 m(75 ft 7 in.)
EM17
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31.68 m(103 ft 11 in.)
4.13 m(13 ft 6 in.)
17.46 m(57 ft 3 in.)
General Aircraft DimensionsFigure 2.1
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2.3. GROUND CLEARANCES
F
G
EM17
0APM
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17A.
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N
A
(REF.)FUSLG ANGLE
B
CD
E
L
M
KJH
Ground ClearancesFigure 2.2
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EFFECTIVITY: ALL Section 2Page 2-5Jun 28/05
Table2.2-G
roundClearance-S
TDAircraftModel
WEIGHT
CG(%MAC)
FUS
ANGLE
(DEG
)(A)
NOSE
(B)
FOR-
WARD
SERVICE
DOOR
(C)
FOR-
WARD
PASSEN-
GER
DOOR
(D)
FOR-
WARD
CARG
ODO
OR
(E)
NACELLE
(F)
WINGLET
(G)
AFT
CARG
ODO
OR
(H)
AFT
SERVICE
DOOR
(J)
AFT
PASSEN-
GER
DOOR
(K)
VERTI-
CAL
TAIL
(L)
TAILSKID
ANGU-
LAR
CLEAR-
ANCE
(DEG
)(M)
37660kg
83026lb
10.1
0.4
2.14
m7ft
2.54
m8ft4in.
2.54
m8ft4in.
1.46
m4ft9in.
0.47
m1ft7in.
4.48
m14
ft8in.
1.45
m4ft9
in.
2.42
m7ft11
in.
2.42
m7ft11
in.
9.61
m31
ft6in.
11.7
37660kg
83026lb
25.6
0.6
2.20
m7ft3in.
2.58
m8ft6in.
2.58
m8ft6in.
1.48
m4ft10
in.
0.47
m1ft7in.
4.45
m14
ft7in.
1.42
m4ft8in.
2.38
m7ft10
in.
2.38
m7ft10
in.
9.54
m31
ft4in.
11.4
37500kg
82673lb
10.1
0.4
2.14
m7ft
2.54
m8ft4in.
2.54
m8ft4in.
1.46
m4ft9
in.
0.47
m1ft7in.
4.48
m14
ft8in.
1.45
m4ft9
in.
2.42
m7ft11
in.
2.42
m7ft11
in.
9.61
m31
ft6in.
11.7
37500kg
82673lb
25.6
0.6
2.20
m7ft3in.
2.58
m8ft6in.
2.58
m8ft6in.
1.48
m4ft10
in.
0.47
m1ft7in.
4.46
m14
ft8in.
1.42
m4ft8in.
2.38
m7ft10
in.
2.38
m7ft10
in.
9.54
m31
ft4in.
11.4
34000kg
74957lb
7.0
0.3
2.14
m7ft
2.55
m8ft4in.
2.55
m8ft4in.
1.47
m4ft10
in.
0.48
m1ft7in.
4.50
m14
ft9in.
1.47
m4ft10
in.
2.45
m8ft
2.45
m8ft
9.65
m31
ft8in.
11.9
34000kg
74957lb
27.0
0.6
2.21
m7ft3in.
2.60
m8ft6in.
2.59
m8ft6in.
1.50
m4ft11
in.
0.49
m1ft7in.
4.47
m14
ft8in.
1.44
m4ft9
in.
2.39
m7ft10in.
2.39
m7ft10in.
9.56
m31
ft4in.
11.5
31700kg
69886lb
7.1
0.3
2.14
m7ft
2.55
m8ft4in.
2.55
m8ft4in.
1.48
m4ft10
in.
0.49
m1ft7in.
4.52
m14
ft10
in.
1.49
m4ft11in.
2.46
m8ft1in.
2.46
m8ft1in.
9.67
m31
ft9in.
11.9
31700kg
69886lb
27.0
0.6
2.22
m7ft3in.
2.60
m8ft6in.
2.60
m8ft6in.
1.51
m4ft11
in.
0.50
m1ft8in.
4.49
m14
ft9in.
1.45
m4ft9
in.
2.41
m7ft11
in.
2.41
m7ft11
in.
9.57
m31
ft5in.
11.6
27500kg
60627lb
27.0
0.5
2.23
m7ft4in.
2.62
m8ft7in.
2.61
m8ft7in.
1.53
m5ft
0.52
m1ft8
in.
4.52
m14
ft10
in.
1.48
m4ft10
in.
2.44
m8ft
2.44
m8ft
9.61
m31
ft6in.
11.7
22500kg
49604lb
7.0
0.1
2.16
m7ft1in.
2.59
m8ft6in.
2.59
m8ft6in.
1.52
m5ft
0.55
m1ft10
in.
4.60
m15
ft1in.
1.58
m5ft2in.
2.56
m8ft5
in.
2.56
m8ft5
in.
9.79
m32
ft1in.
12.4
22500kg
49604lb
21.0
0.32
2.21
m7ft3in.
2.62
m8ft7in.
2.62
m8ft7in.
1.54
m5ft11
in.
0.55
m1ft10
in.
4.58
m15
ft1.54
m5ft1in.
2.52
m8ft3
in.
2.52
m8ft3
in.
9.72
m31
ft11
in.
12.1
22500kg
49604lb
27.0
0.5
2.25
m7ft5in.
2.64
m8ft8in.
2.64
m8ft8in.
1.55
m5ft1in.
0.56
m1ft10
in.
4.56
m14
ft11in.
1.53
m5ft
2.59
m8ft6in.
2.59
m8ft6in.
9.68
m31
ft9in.
12.0
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Table2.3-G
roundClearance-LRAircraftModel
WEIGHT
CG(%MAC)
FUS
ANGLE
(DEG
)(A)
NOSE
(B)
FOR-
WARD
SERVICE
DOOR
(C)
FOR-
WARD
PASSEN-
GER
DOOR
(D)
FOR-
WARD
CARG
ODO
OR
(E)
NACELLE
(F)
WINGLET
(G)
AFT
CARG
ODO
OR
(H)
AFT
SERVICE
DOOR
(J)
AFT
PASSEN-
GER
DOOR
(K)
VERTI-
CAL
TAIL
(L)
TAILSKID
ANGU-
LAR
CLEAR-
ANCE
(DEG
)(M)
38950kg
85870lb
11.2
0.4
2.15
m7ft1
in.
2.54
m8ft4in.
2.54
m8ft4in.
1.46
m4ft9in.
0.46
m1ft6in.
4.47
m14
ft8in.
1.44
m4ft9
in.
2.41
m7ft11
in.
2.41
m7ft11
in.
9.59
m31
ft6in.
11.6
38950kg
85870lb
25.1
0.6
2.19
m7ft2in.
2.58
m8ft6in.
2.57
m8ft5in.
1.48
m4ft10
in.
0.47
m1ft7in.
4.45
m14
ft7in.
1.41
m4ft8in.
2.37
m7ft9in.
2.37
m7ft9in.
9.53
m31
ft3in.
11.4
38790kg
85517lb
11.2
0.4
2.15
m7ft1
in.
2.55
m8ft4in.
2.54
m8ft4in.
1.46
m4ft9
in.
0.46
m1ft6in.
4.47
m14
ft8in.
1.44
m4ft9
in.
2.41
m7ft11
in.
2.41
m7ft11
in.
9.59
m31
ft6in.
11.7
38790kg
85517lb
25.1
0.6
2.19
m7ft2in.
2.58
m8ft6in.
2.57
m8ft5in.
1.48
m4ft10
in.
0.47
m1ft7in.
4.45
m14
ft7in.
1.41
m4ft8in.
2.37
m7ft9
in.
2.37
m7ft9in.
9.53
m31
ft3in.
11.4
34000kg
74957lb
7.0
0.3
2.14
m7ft
2.55
m8ft4in.
2.55
m8ft4in.
1.47
m4ft10
in.
0.48
m1ft7in.
4.50
m14
ft9in.
1.47
m4ft10
in.
2.45
m8ft
2.45
m8ft
9.65
m31
ft8in.
11.9
34000kg
74957lb
27.0
0.6
2.21
m7ft3in.
2.60
m8ft6in.
2.59
m8ft6in.
1.50
m4ft11
in.
0.49
m1ft7in.
4.47
m14
ft8in.
1.44
m4ft9
in.
2.39
m7ft10in.
2.39
m7ft10in.
9.56
m31
ft4in.
11.5
31700kg
69886lb
7.1
0.3
2.14
m7ft
2.55
m8ft4in.
2.55
m8ft4in.
1.48
m4ft10
in.
0.49
m1ft7in.
4.52
m14
ft10
in.
1.49
m4ft11in.
2.46
m8ft1in.
2.46
m8ft1in.
9.67
m31
ft9in.
11.9
31700kg
69886lb
27.0
0.6
2.22
m7ft3in.
2.60
m8ft6in.
2.60
m8ft6in.
1.51
m4ft11
in.
0.50
m1ft8in.
4.49
m14
ft9in.
1.45
m4ft9
in.
2.41
m7ft11
in.
2.41
m7ft11
in.
9.57
m31
ft5in.
11.6
27500kg
60627lb
27.0
0.5
2.23
m7ft4in.
2.62
m8ft7in.
2.61
m8ft7in.
1.53
m5ft
0.52
m1ft8
in.
4.52
m14
ft10
in.
1.48
m4ft10
in.
2.44
m8ft
2.44
m8ft
9.61
m31
ft6in.
11.7
22500kg
49604lb
7.0
0.1
2.16
m7ft1in.
2.59
m8ft6in.
2.59
m8ft6in.
1.52
m5ft
0.55
m1ft10
in.
4.60
m15
ft1in.
1.58
m5ft2in.
2.56
m8ft5
in.
2.56
m8ft5
in.
9.79
m32
ft1in.
12.4
22500kg
49604lb
21.0
0.32
2.21
m7ft3in.
2.62
m8ft7in.
2.62
m8ft7in.
1.54
m5ft11
in.
0.55
m1ft10
in.
4.58
m15
ft1.54
m5ft1in.
2.52
m8ft3
in.
2.52
m8ft3
in.
9.72
m31
ft11
in.
12.1
22500kg
49604lb
27.0
0.5
2.25
m7ft5in.
2.64
m8ft8in.
2.64
m8ft8in.
1.55
m5ft1in.
0.56
m1ft10
in.
4.56
m14
ft11in.
1.53
m5ft
2.59
m8ft6in.
2.59
m8ft6in.
9.68
m31
ft9in.
12.0
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2.4. INTERIOR ARRANGEMENT
The interior arrangement provides accommodation for two pilots, one observer, two flight attendants,and 78 passengers in 32 in pitch standard configuration. One additional flight attendant seat is availableas an option.
2.4.1. Passenger Cabin
The passenger cabin accommodates 78 passengers in 19 double seats on the LH side, and 20 doubleseats on the RH side.As an option, the passenger cabin can be provided with double first-class seats on the RH side andsingle first-class seats on the LH side.The main dimensions of the passenger cabin are presented below:
• Height - 2.00 m (6 ft 7 in.)
• Width - 2.74 m (9 ft)
• Aisle width - 0.49 m (1 ft 7 in.)
• Pitch - 0.82 m (32 in.)
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2 − WARDROBE 7 − AFT LAVATORY
9 − OVERHEAD BIN
OVERHEAD BIN
UNDERSEAT VOLUME
0.06 m / pax (2.0 ft / pax)
0.04 m / pax (1.4 ft / pax)
3
3
3
3
8 − CARGO COMPARTMENT
CARGO COMPARTMENT
10 − PASSENGER SEAT
3 − FWD RH G1 GALLEY
4 − FWD RH G2 GALLEY
5 − AFT RH GALLEY
CARGO/BAGGAGE VOLUME
1 − FLIGHT ATTENDANT SEAT
1.68 m 4.58 m 1.35 m 1.85 m(5 ft 6.14 in.)
0.81 m32.0 in.
34
6 1 2
3 4 10 5
71
88
59
0.87 m(2 ft 10 in.)
0.78 m(2 ft 6.7 in.)
0.90 m(2 ft 11.4 in.)
6 − FWD LAVATORY
(15 ft) (4 ft 5.15 in.) (6 ft)
21.34 m(70 ft)
7.36 m(24 ft 1.76in.)
5.86 m(19 ft 2.7in.)
17.12 m (604.59 ft )3 3
EM17
0APM
0200
18B.
DG
N
Typical Interior ArrangementsFigure 2.3
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2.4.2. Cargo Compartments
Two cargo compartments located underfloor are available, one forward of the wing, and the other aft ofthe wing.The cargo compartments comply with the FAR-25/JAR-25/RBHA-25 “class C” compartment classifica-tion.The table below contains the capacity of the cargo compartment:
Table 2.4 - Capacity of the Cargo CompartmentCARGO COMPARTMENT LOADING VOLUME
FWD [1] 1500 kg (3307 lb) 9.92 m3 (350.32 ft3)AFT 1150 kg (2535 lb) 7.2 m3 (254.27 ft3)Total 2650 kg (5842 lb) 17.12 m3 (604.59 ft3)
1. Standard configuration (loading and volume may vary according to optional equipment installed).
The cargo compartments are provided with the following features:
• Optional vertical nets;
• Door net at each cargo door.
2.4.3. Cockpit
The cockpit is acoustically and thermally insulated for appearance and durability. It follows the worldwidetrend of rounded edges to avoid harm to the flight crew.The cockpit is separated from the passenger cabin by a bulkhead provided with a lockable door. Thecockpit door has a locking system, which can only be opened from the cockpit side, a peep hole and anescape mechanism on the cockpit side.
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2.5. PASSENGER CABIN CROSS SECTION
2.00 m(6 ft 7 in.)
1.44 m(4 ft 9 in.)
0.94 m(3 ft 1 in.)
0.78 m(2 ft 7 in.)
0.46 m(1 ft 6 in.)
0.49 m
(1 ft 7 in.)
2.74 m(9 ft)
3.35 m(11 ft 0 in.)
3.01 m(9 ft 11 in.)
0.05 m(2.0 in.)
1.66 m(5 ft 5 in.)
2.72 m(8 ft 11 in.)
0.75 m(2 ft 5 in.)
0.45 m(1 ft 6 in.)
EM17
0APM
0200
01A.
DG
N
Economy Class Passenger Cabin Cross-SectionFigure 2.4
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2.00 m(6 ft 7 in.)
1.44 m(4 ft 9 in.)
0.94 m(3 ft 1 in.)
2.74 m(9 ft)
3.35 m(11 ft 0 in.)
3.01 m(9 ft 11 in.)
1.66 m(5 ft 5 in.)
2.72 m(8 ft 11 in.)
0.75 m(2 ft 5 in.)
0.45 m(1 ft 6 in.)
0.86 m(3 ft)
0.51 m(1 ft 8 in.)
0.69 m(2 ft 3 in.)
0.20 m(8 in.)
0.07 m(3 in.)
0.6 m(1 ft 10 in.)
0.61 m(2 ft)
1.1 m(3 ft 8 in.)
EM17
0APM
0200
02A.
DG
N
First Class Passenger Cabin Cross-SectionFigure 2.5
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2.6. LOWER COMPARTMENT CONTAINERS
Not applicable
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2.7. DOOR CLEARANCES
1.36 m(4 ft 5.5 in.)
0.90 m(2 ft 11.4 in.)
0.87 m(2 ft 10 in.)
1.82 m(5 ft 11.6 in.)
0.78 m(2 ft 6.7 in.)
SEE FIGURE 2.2FOR HEIGHT ABOVEGROUND
EM17
0APM
0200
08C
.DG
N
NOTE: FOR DIMENSIONS OF ALL DOORS,CONSIDER THAT AIRCRAFT IS IN OPERATION,THAT IS, EQUIPPED WITH DOOR LININGS ANDDOOR SURROUNDS.
1.71 m(5 ft 7.3 in.)
1.37 m(4 ft 5.9 in.)
0.63 m(2 ft 0.8 in.)
0.99 m(3 ft 3 in.)
1.10 m(3 ft 7.3 in.)
0.61 m(2 ft 0 in.)
0.75 m(2 ft 6.7 in.) 0.63 m
(2 ft 0.8 in.)
Door DimensionsFigure 2.6
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4. GROUND MANEUVERING4.1. GENERAL INFORMATION
This section provides the aircraft turning capability and maneuvering characteristics. To facilitate thepresentation, data have been determined from theoretical limits imposed by the geometry of the aircraft.As such, they reflect the turning capability of the aircraft in favorable operating circumstances. Thesedata should be used only as a guideline for the method of determining such parameters and for themaneuvering characteristics of the aircraft.In the ground operating mode, varying airline practices may demand that more conservative turningprocedures be adopted, to avoid excessive tire wear and reduce possible maintenance problems.Variations from standard aircraft operating patterns may be necessary to satisfy physical constraintswithin the maneuvering area, such as adverse grades, limited area, or high risk of jet blast damage. Forthese reasons, the ground maneuvering requirements should be coordinated with the airline before thelayout is planned.This section is presented as follows:
• The turning radii for nose landing gear steering angles.
• The pilot’s visibility from the cockpit and the limits of ambinocular vision through the windows.Ambinocular vision is defined as the total field of vision seen by both eyes at the same time.
• The performance of the aircraft on runway-to-taxiway, taxiway-to-taxiway and runway holding baydimensions.
4.2. TURNING RADII
This subsection presents the following information:
• The turning radii for various nose landing gear steering angles. The minimum turning radius isdetermined, considering the maximum nose landing gear steering angle as 76 degrees left and right.
• Data on the minimum width of the pavement for a 180 degrees turn.
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0.23m 0ft 9.2in
35°
40°
45°
50°
55°
60°
65°
70°
76°
NOSE
R1
22.70m
20.83m
18.43m
17.65m
17.05m
16.60m
16.26m
15.8m
74ft 5.7in
68ft 4in
63ft 9.9in
60ft 5.4in
57ft 11in
55ft 11in
54ft 5.4in
53ft 4in
51ft 10in
R2
20.29m
18.13m
16.51m
15.26m
14.29m
13.53m
12.49m
12.12m
66ft 6.8in
59ft 6in
54ft 2in
50ft 1in
46ft 11in
44ft 4.8in
42ft 5.4in
41ft 0in
39ft 9in
OUTBOARD GEAR
R3
19.51m
16.80m
14.60m
11.16m
9.75m
7.30m
6.01m
64ft 0.1in
55ft 1.3in
47ft 11in
41ft 10in
36ft 7in
32ft 0in
27ft 9.6in
23ft 11in
19ft 8.7in
INBOARD GEAR
R4
13.26m
10.55m
8.35m
6.50m
2.23m
1.05m
43ft 6.2in
34ft 7.4in
27ft 4.8in
21ft 4in
16ft 1.3in
11ft 5.8in
7ft 3.7in
3ft 5.5in
RIGHT WINGLET
R5
29.64m
26.95m
24.78m
22.96m
21.38m
20.00m
18.75m
17.61m
16.58m
97ft 3in
88ft 5in
81ft 3.5in
75ft 3.8in
70ft 2in
65ft 7.4in
61ft 6.3in
57ft 9.1in
54ft 7.6in
RIGHT TAILTIP
R6
26.38m
24.23m
22.58m
21.27m
20.21m
19.33m
18.59m
17.96m
17.45m
86ft 6.5in
79ft 6in
74ft 1in
69ft 9.3in
66ft 3.5in
63ft 4.9in
61ft 0in
58ft 11in
57ft 2.8in
STEERING
STEEL
NOSE LANDINGGEAR
19.45m
12.75m
12.94m 8.47m
3.50m
4.91m
NOTE:
EM17
0APM
0400
21D
.DG
N
DATA PRESENTED IS BASED ON THEORETICAL CALCULATIONS.ACTUAL OPERATING DATA MAY BE GREATER THAN SHOWN SINCE TIRE SLIPPAGE IS NOT CONSIDERED IN THESE CALCULATIONS.
R4
R1
76°70°65°60°
55°
45°50°
40°35°
R5
R3R 5.49m18ft 0.1in
R2
R 11.83m38ft 9.7in
R6
Turning Radii - No Slip AngleFigure 4.1
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4.3. MINIMUM TURNING RADII
76°
NOSE
R1
15.8m
51ft 10in
R2
12.07m
OUTBOARD GEAR
R3
5.97m
R5
RIGHT TAILTIP
R6
STEERING
ANGLE
39ft 7in 19ft 7in
NOSE LANDINGGEAR RIGHT WINGLET
16.58m 54ft 7.6in 17.45m 57ft 2.8in
ACTUAL OPERATING DATA MAY BE GREATER THAN VALUES SHOWN SINCE TIRE SLIPPAGE IS NOT CONSIDERED IN THESE CALCULATIONS.
NOTE:
1
EM17
0APM
0400
22D
.DG
N
THEORETICAL CENTER OF TURN FOR MINIMUN RADIUS.SHOWS CONTINUOUS TURNING WITH ENGINE THRUST AS REQUIRED.NO DIFFERENTIAL BRAKING.
76°
18.0
4 m
59ft
2in
(RU
NW
AY M
INIM
UM
WID
TH)
R 11.78 m38ft 8in
R 5.45 m17ft 11in
R1
R3
R2
R5
R6
1
Minimum Turning RadiusFigure 4.2
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4.4. VISIBILITY FROM COCKPIT
VISUAL ANGLE IN PLANEPARALLEL TO LONGITUDINALAXIS THROUGH PILOT’S EYEPOSITION
27.8°
15°
REF. GROUND (BOW)
PILOT’S EYE POSITION
PILOT’S EYE POSITIONMAXIMUM AFT VISIONWITH HEAD ROTATEDABOUT SPINAL COLUMN
VISUAL ANGLE IN PLANEPERPENDICULAR TO LONGITUDINALAXIS THROUGH PILOT’S EYE POSITION
PILOT’S EYE POSITION
120.6°
27.5°
28.1°
L FUS HORC
3.91 m(12 ft 10 in.)
0.75 m(2 ft 6 in.)
2.92 m(9 ft 7 in.)
14.58 m(47 ft 10 in.)
0.53 m(1 ft 9 in.)
0.53 m(1 ft 9 in.)
EM17
0APM
0400
06C
.DG
N
Visibility from Cockpit in Static PositionFigure 4.3
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4.5. RUNWAY AND TAXIWAY DIMENSIONS
To determine the minimum dimensions for runway and taxiway where the aircraft can be operated, thereference code of the aircraft must be determined.The reference code of a specific aircraft is obtained in accordance with the Aerodrome Design andOperations - Volume 1, by the ICAO.The code is composed of two elements which are related to the aircraft performance characteristics anddimensions:
• Element 1 is a number based on the aircraft reference field length.
• Element 2 is a letter based on the aircraft wingspan and outer main landing gear wheel span.
The table below shows the reference codes:
Table 4.1 - Reference CodesCODE ELEMENT 1 CODE ELEMENT 2
CODE NUMBERAIRCRAFT REFER-ENCE FIELDLENGTH
CODE LETTER WING SPANOUTER MAINLANDING GEARWHEEL SPAN
1 Less than 800 m(2624 ft 8 in) A Up to 15 m
(49 ft 3 in)Up to 4.5 m(14 ft 9 in)
2800 m (2624 ft 8 in)up to1200 m (3937 ft)
B 15 m (49 ft 3 in) to24 m (78 ft 9 in)
4.5 m (14 ft 9 in) to6 m (19 ft 8 in)
31200 m (3937 ft) upto1800 m (5905 ft 6 in)
C 24 m (78 ft 9 in) to36 m (118 ft 1 in)
6 m (19 ft 8 in) to9 m (29 ft 6 in)
41800 m(5905 ft 6 in) andover
D36 m (118 ft 1 in)to52 m (170 ft 7 in)
9 m (29 ft 6 in) to14 m (45 ft 11 in)
E52 m (170 ft 7 in)to65 m (213 ft 3 in)
9 m (29 ft 6 in) to14 m (45 ft 11 in)
In accordance with the table, the reference code for the EMBRAER 175STD and 175LR is 3C.
NOTE:• Classification considering CF34-8E5A1 engines.• This classification may change depending on aircraft engine model and takeoff weight.
With the reference code it is possible to obtain the limits of the runway and taxiway where the aircraftcan be operated. For reference code 3C the limits are:
• The width of a runway should not be less than 30 m (98 ft 5 in).
• The width of a taxiway should not be less than 15 m (49 ft 2 in).
• The design of the curve in a taxiway should be such that, when the cockpit remains over the taxiwaycenter line marking, the clearance distance between the outer main landing gear wheels of theaircraft and the edge of the taxiway should not be less than 3 m (9 ft 10 in).
• The clearance between a parked aircraft and one moving along the taxiway in a holding bay should
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not be less than 15 m (49 ft 3 in).
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EM17
0APM
0400
02.D
GN
COORDINATE WITH AIRLINE OPERATORFOR THE SPECIFIC PLANNED OPERATINGPROCEDURE.
45°
100 ft Radius(30 m)
NOTE:
PATH OF MAIN LANDINGGEAR TIRE EDGE
NOSE LANDING GEAR STEERING ANGLE ISAPPROXIMATELY 15.
30 m(98 ft 5 in.)
15 m (49 ft 2 in.)
More than 90° Turn - Runway to TaxiwayFigure 4.4
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EM17
0APM
0400
03.D
GN
COORDINATE WITH AIRLINE OPERATORFOR THE SPECIFIC PLANNED OPERATINGPROCEDURE.
90°
100 ft Radius(30 m)
100 ft Radius(30 m)
NOTE:
PATH OF MAIN LANDINGGEAR TIRE EDGE.
NOSE LANDING GEAR STEERING ANGLE ISAPPROXIMATELY 30.
30 m(98 ft 5 in.)
15 m(49 ft 2 in.)
90° Turn - Runway to TaxiwayFigure 4.5
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EM17
0APM
0400
04.D
GN
COORDINATE WITH AIRLINE OPERATORFOR THE SPECIFIC PLANNED OPERATINGPROCEDURE.
90°
100 ft Radius(30 m)
NOTE:
PATH OF MAIN LANDINGGEAR TIRE EDGE.
NOSE LANDING GEAR STEERING ANGLE ISAPPROXIMATELY 28.
15 m(49 ft 2 in.)
15 m(49 ft 2 in.)
3 m(9 ft 10 in.)
90° Turn - Taxiway to TaxiwayFigure 4.6
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4.6. RUNWAY HOLDING BAY
EM17
0APM
0400
05.D
GN
RUNWAY
TAXIWAY
75 m(246 ft)
PATH OF MAIN LANDINGGEAR TIRE EDGE.
PATH OF MAIN LANDINGGEAR TIRE EDGE.
30 m(98 ft 5 in.)
MINIMUMCLEARENCES
15 m(49 ft 2 in.)
3 m(9 ft 10 in.)
3 m(9 ft 10 in.)
15 m(49 ft 2 in.)
Runway Holding BayFigure 4.7
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5. TERMINAL SERVICINGDuring turnaround at the air terminal, certain services must be performed on the aircraft, usually withina given time to meet flight schedules. This section shows service vehicle arrangements, schedules,locations of servicing points, and typical servicing requirements. The data presented herein reflect idealconditions for a single aircraft. Servicing requirements may vary according to the aircraft condition andairline operational (servicing) procedures.This section provides the following information:
• The typical arrangements of equipment during turnaround;
• The typical turnaround servicing time at an air terminal;
• The locations of ground servicing connections in graphic and tabular forms;
• The typical sea level air pressure and flow requirements for starting the engine;
• The air conditioning requirements;
• The ground towing requirements for various towing conditions. Towbar pull and total traction wheelload may be determined by considering aircraft weight, pavement slope, coefficient of friction, andengine idle thrust.
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5.1. AIRCRAFT SERVICING ARRANGEMENT
0 5 10 15 20 25 30 350
5
10
15
20
25
30
0
20
40
60
80
100
0 20 40 60 80 100 1201109070503010
10
30
50
70
90
110
(M)
40
130
LEN
GTH
− ft
LENGTH − ft
LENGTH − m
LEN
GTH
− m
4
6
53
3
5
4
8
2
7
02 − PASSENGER STAIRS
SERVICING ARRANGEMENT
07 − POTABLE WATER06 − FUEL SERVICE
03 − CARGO LOADER04 − BAGGAGE / CARGO TROLLEY AND TUG05 − GALLEY SERVICE VEHICLE
08 − LAVATORY SERVICE VEHICLE09 − AIR CONDITIONING UNIT10 − PNEUMATIC STARTER
EM17
0APM
0500
19A.
DG
N
35
2
1009
11 − GROUND POWER UNIT
11
Aircraft Servicing Arrangement With Passenger StairsFigure 5.1
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0 5 10 15 20 25 30 350
5
10
15
20
25
30
0
20
40
60
80
100
0 20 40 60 80 100 1201109070503010
10
30
50
70
90
110
(M)
40
130
LEN
GTH
− ft
LENGTH − ft
LENGTH − m
LEN
GTH
− m
4
6
53
3
5
4
8
2
7
SERVICING ARRANGEMENTEM
170A
PM05
0020
A.D
GN
1
01 − PASSENGER BRIDGE.02 − PASSENGER STAIRS.
06 − FUEL SERVICE.07 − POTABLE WATER.
09 − AIR CONDITIONING UNIT.10 − PNEUMATIC STARTER.
35
03 − CARGO LOADER.04 − BAGGAGE / CARGO TROLLEY AND TUG.05 − GALLEY SERVICE VEHICLE.
109
08 − LAVATORY SERVICE VEHICLE.
Aircraft Servicing Arrangement With Passenger BridgeFigure 5.2
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EFFECTIVITY: ALL Section 5Page 5-3Jun 28/05
5.2. TERMINAL OPERATIONS - TURNAROUND STATION
This section presents the typical turnaround servicing time at an air terminal. The chart gives typicalschedules for servicing the aircraft within a given time.The time of each service in the chart was calculated taking the following into consideration:
• Load factor - 100%;
• Passenger deplane - 24 pax/min;
• Passenger enplane - 16 pax/min;
• Baggages checked per passenger - 1,2;
• Refuel (fuel quantity) - 80%;
• Flow - 290 gpm;
• Potable water - 70% to be refilled (56 !);
• Galley service FWD and aft sequence - in parallel;
• Toilet type - vacuum;
• Baggages unloading/loading FWD/aft sequence - in parallel;
• Only FWD passenger door to be used to deplane and enplane passengers.
Servicing times could be rearranged to suit availability of personnel, aircraft configuration, and degree ofservicing required.The data illustrates the general scope and tasks involving airport terminal operations. Airline particularpractices and operating experience will result in different sequences and intervals.
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min.
5
OPERATIONS
ELAPSED TIME(MINUTES)
6,0
FWD BAGGAGE/CARGO LOAD
AIRCRAFTSERVICING
FUEL SERVICE
POTABLE WATER SERVICE
TOILET SERVICE
TRUCK POSITIONING/REMOVAL/SETTINGS
1 3 7 9 11 13 17 19
GALLEY SERVICING−AFT
AFT BAGGAGE/CARGO LOAD
PAXSERVICES
1,0
GALLEY SERVICING−FWD 6,0
PASSENGERS DEPLANE 3,3
AIRPLANE INTERIOR SERVICES
PASSENGERS ENPLANE
4,9
4,9
BRIDGE / STAIRS REMOVAL 1,0
2,0PUSH BACK / ENGINES START
2 4 8 10 126 14 15 16 18 20
FWD BAGGAGE / CARGO UNLOAD
REAR BAGGAGE / CARGO UNLOAD
TIME BETWEEN UNLOADING / LOADINGBAGGAGE& CARGO
5,0
3,0
8,5
4,4
5,8
0,5
2.7
3,6
LEGEND:
NOTE:
BRIDGE/STAIRS POSITIONING
THIS DATA ILLUSTRATES THE GENERAL SCOPE AND TASKS INVOLVINGAIRPORT TERMINAL OPERATIONS.AIRLINE PARTICULAR PRACTICES AND OPERATING EXPERIENCE WILLRESULT IN DIFFERENT SEQUENCES AND INTERVALS. EM
170A
PM05
0021
B.D
GN
Air Terminal Operation - Turnaround StationFigure 5.3
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5.3. TERMINAL OPERATIONS - EN ROUTE STATION
Not Applicable
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EFFECTIVITY: ALL Section 5Page 5-6Jun 28/05
5.4. GROUND SERVICING CONNECTIONS
1 2
1921
22
18
20
3
4 58 9
12
67
10 11 13 1415 16 17
EM17
0APM
0500
22C
.DG
N
NOTE:
3
12
20
14
1
456789
1011
13
1516171819
2122
2
ITEM DESCRIPTIONCOORD. Y
(mm)COORD. Z
(mm)COORD. X
(mm)
HEIGHTABOVE
GROUND(mm)
EXTERNAL POWER SUPPLY 115 VAC
GRAVITY REFUELING PORT (RH)GRAVITY REFUELING PORT (LH)
WHEEL JACK POINT− MLG (LH)WHEEL JACK POINT− MLG (RH)
FUEL TANK DRAIN VALVE (LH)FUEL TANK DRAIN VALVE (RH)
HYD. SYS # 1 SERVICE PANELHYD. SYS # 2 SERVICE PANEL
FORWARD RAMP HEADSETSTEERING SWITCH DISENGAGE
AIR COND. GROUND CONNECTION
GROUNDING POINT (ELECTRICAL)
WATER SERVICING PANEL
WASTE SERVICING PANELHYD. SYS # 3 SERVICE PANEL
AFT RAMP HEADSET
WHEEL JACK POINT − NLG
PRESSURE REFUELING PANEL
OXYGEN SERVICING PANEL / BOTTLE
ENGINE AIR STARTING (LOW PRESSURE UNIT)
4164.444136.97
−7413.99
−936.13−951.46
0.00
−329.37
−398.47
−1262.71
−623.30
−243.75−1339.53
−1279.29
−1178.74−605.30
−1413.71
1837.12
EXTERNAL POWER SUPPLY 28 VDC
14329.47 5702.96 2473.4115627.69 7413.99 −243.75 2852.5615627.69 2852.56
4146.90 −810.70 1760.30
1820.554125.94 −2849.07 250.76
11325.52 80.00 −1979.71 1117.9311617.00 4.28 −2010.20 1087.3415430.30 2560.25 −1343.60 1752.7815318.29 2600.00 −2683.95 412.4615318.29 −2600.00 −2683.95 412.4617398.37 −808.01 −1602.04 1493.7317398.37 −1602.04 1493.73808.0123302.83 1915.2225862.65 −471.73 2487.8726003.26 −449.47 −585.54 2507.59
7400.34 1159.87 −961.05 2137.7914191.00 398.47 −1413.71 1683.0514191.00 1683.0524225.01 349.20 −991.80 2101.8725839.86 519.15 −590.09 2503.09
THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 22500 kg (CG FWD 7.0% CMA)
Ground Servicing ConnectionsFigure 5.4
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EFFECTIVITY: ALL Section 5Page 5-7May 11/07
3
12
20
14
1
456789
1011
13
1516171819
2122
2
ITEM DESCRIPTIONCOORD. Y
(mm)COORD. Z
(mm)COORD. X
(mm)
HEIGHTABOVE
GROUND(mm)
EXTERNAL POWER SUPPLY 115 VAC
GRAVITY REFUELING PORT (RH)GRAVITY REFUELING PORT (LH)
WHEEL JACK POINT− MLG (LH)WHEEL JACK POINT− MLG (RH)
FUEL TANK DRAIN VALVE (LH)FUEL TANK DRAIN VALVE (RH)
HYD. SYS # 1 SERVICE PANELHYD. SYS # 2 SERVICE PANEL
FORWARD RAMP HEADSETSTEERING SWITCH DISENGAGE
AIR COND. GROUND CONNECTION
GROUNDING POINT (ELECTRICAL)
WATER SERVICING PANEL
WASTE SERVICING PANELHYD. SYS # 3 SERVICE PANEL
AFT RAMP HEADSET
WHEEL JACK POINT − NLG
PRESSURE REFUELING PANEL
OXYGEN SERVICING PANEL / BOTTLE
ENGINE AIR STARTING (LOW PRESSURE UNIT)
4146.904164.444136.97
5702.96
−7413.99−810.70 −936.13−951.46
80.004.28
−808.01808.01−329.37−471.73−449.471159.87
398.47−398.47349.20519.15
−1262.71
−585.54
−623.30
−243.75−1339.53
−1279.29
−1979.71−2010.20
−1602.04−1602.04−1178.74−605.30
−961.05−1413.71−1413.71−991.80−590.09
NOTE:
3
1 2
12
14
19
45
67
8 9
10 11 13 15
16 17
18
20
2122
1902.23
EXTERNAL POWER SUPPLY 28 VDC
EM17
0APM
0500
23A.
DG
N
14329.47 2466.0115627.69 7413.99 −243.75 2835.8915627.69 2835.89
1825.54
1885.864116.74 0.00 −2914.51 250.82
11325.52 1131.99
15430.30 2560.25 −1343.60 1737.5415317.37 2600.00 −2667.98 414.0315317.37 −2600.00 −2667.98 414.0317398.3717398.37
1464.461464.46
23302.83 1843.8325862.65 2398.2126003.26 2416.93
11617.00 1099.32
7400.34 2178.8214191.0014191.00
1676.651676.65
24225.01 2023.9125839.86 2413.60
THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 22500 kg (CG REAR 27.0% CMA)
Ground Servicing ConnectionsFigure 5.5
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EFFECTIVITY: ALL Section 5Page 5-8May 11/07
5.5. ENGINE STARTING PNEUMATIC REQUIREMENTS
EM17
0APM
0500
10.D
GN
200 210 220 230 240 250 260 270 280
MIN
IMUM
REQ
UIRE
D AI
RFLO
W A
T PO
RT -
kg/m
in
MIN
IMUM
REQ
UIRE
D AI
RFLO
W A
T PO
RT -
lb/m
in
GROUND CART CONNECTION TEMPERATURE - ˚C
GROUND CART CONNECTION TEMPERATURE - ˚F400 425 450 475 500 525 550
SEA LEVEL
2440 m(8000 ft)
25
30
35
40
45
50
55
60
65
70
75
80
85
90
95
Engine Starting Pneumatic Requirements - Airflow x TemperatureFigure 5.6
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GROUND CART CONNECTION TEMPERATURE − °F
GROUND CART CONNECTION TEMPERATURE − °C200 210 220 230 240 250 260 270 280
400 425 450 475 500 525 550
2.5
3.0
3.5
4.0
35
2
40
45
50
55
60
SEA LEVEL
2440 m(8000 ft)
MIN
IMU
M R
EQU
IRED
PR
ESSU
RE
AT P
OR
T −
PSI
MIN
IMU
M R
EQU
IRED
PR
ESSU
RE
AT P
OR
T −
kg/c
m
EM17
0APM
0500
09A.
DG
N
Engine Starting Pneumatic Requirements - Pressure x TemperatureFigure 5.7
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5.6. GROUND PNEUMATIC POWER REQUIREMENTS
HEATING Initial cabin temp: −32°C (−25°F)Outside air temp: −40°C (−40°F)Relative Humidity: 0%No crew or passengersNo other heat load
−20
−10
80
70
60
50
40
30
20
10
0
0 5 10 15 20 25 30
−30
−25
−20
−15
−10
−5
0
5
10
15
20
25
0 5 10 15 20 25 3060
70
80
90
100
110
120
20
25
30
35
40
45
COOLING Initial cabin temp: 47°C (116°F)Outside air temp: 40°C (104°F)Relative Humidity: 40%No crew or passengersNo other heat load
TIME TO HEAT CABIN − min.
TIME TO COOL CABIN − min.
Bleed air from APU:87 kg/min. (192.0 lb/min.)452 kPa (65.5 psia)2 operating packs (ECS)
Bleed air from APU:56 kg/min. (122.9 lb/min.)413 kPa (59.9 psia)2 operating packs (ECS)
CAB
IN T
EMPE
RAT
UR
E (°
F)
EM17
0APM
0500
07B.
DG
N
CAB
IN T
EMPE
RAT
UR
E (°
F)
CAB
IN T
EMPE
RAT
UR
E (°
C)
CAB
IN T
EMPE
RAT
UR
E (°
C)
Ground Pneumatic Power RequirementsFigure 5.8
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EFFECTIVITY: ALL Section 5Page 5-11May 11/07
5.7. PRECONDITIONED AIRFLOW REQUIREMENTS
This subsection presents the following information:
• The air conditioning requirements for heating and cooling using ground conditioned air. The curvesshow airflow requirements to heat or cool the aircraft at ambient conditions within a given time.
• The air conditioning heating and cooling requirements to maintain a constant cabin air temperatureusing low-pressure conditioned air. This conditioned air is supplied through a ground air connectiondirectly to the passenger cabin, bypassing the air cycle machines.
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EM17
0APM
0500
08.D
GN
AMBIENT TEMP
39
39
39
-40
-29
-18
103
103
103
-40
-20 0
CONDITIONS
1 2 3 4 5 6
20952
20952 0 0 0 0
ELECTRICALLOAD
(BTU/h)
12500
12500
12500 0 0 0
OCCUPANTS
75
75 4 4 4 4
75
80
70
75
75
75
CABIN TEMP
24
27
21
24
24
24
(˚C) (˚F) (˚C) (˚F)EXT LOAD
(BTU/h)
0
10
20
30
40
50
60
70
80
90
120
110
100
30 40 50 60 70 80 90 100 110 120 130
AIRF
LOW
- lb
/min
INLET TEMPERATURE - ˚F
PRESSURE AT GROUNDCONNECTION AT S.L.
2 2
PRE - CONDITIONED AIRFLOW REQUIREMENTS
1
2
3
4
5
6
203 mm H O (8 in H O)
IDEAL OPERATIONSETTING
AIRF
LOW
- Kg
/min
INLET TEMPERATURE - ˚C
0
5
10
15
20
25
30
35
40
45
50
55
0 5 10 15 20 25 30 35 40 45 50
Preconditioned Airflow RequirementsFigure 5.9
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5.8. GROUND TOWING REQUIREMENTS
1000
(220
4)
3000
(661
4)
2000
(440
9)
1000
(220
4)20
00(4
409)
3000
(661
4)40
00(8
818)
5000
(110
23)
NU
MBE
R O
FEN
GIN
ESBA
CKI
NG
AG
AIN
STID
LE T
HR
UST
− ST
RAIG
HT−L
INE
TOW
− UN
USUA
L BR
EAKA
WAY
CO
ND
ITIO
NS
NO
T SH
OW
N−
COEF
FICI
ENTS
OF
FR
ICTI
ON
( )
AR
E E
STIM
ATED
FO
R R
UBB
ER−T
IRED
TO
W
VEH
ICLE
S
3800
0 (83
775)
3600
0 (79
366)
3400
0 (74
957)
3200
0 (70
547)
3000
0 (6
6138
)
2800
0 (6
1729
)
2600
0 (5
7320
)
2400
0 (5
2910
)
2200
0 (4
8501
)
2000
0 (4
4092
)
AIRCRAFT
GROSS W
EIGHT −
kg (lb
)
NO
TES:
GRO
UND
TO
WIN
G R
EQUI
REM
ENTS
00
10
12
34
50
2
TOWBAR PULL − kg (lb)
WET ASPHALT =0.75
WET CONCRETE =0.5
7
SNOW CHAIN
S =0
.45
HARD
SNO
W
=0.
2
ICE
=
0.05
PER
CEN
T SL
OPE
(%)
REFERENCE LINE
DRY CONCRETE OR
ASPHALT =0.8
EM17
0APM
0500
04A.
DG
N
TOTA
L TR
ACTI
ON
WH
EEL −
kg (l
b)(D
RAW
BAR
PU
LL)
Ground Towing RequirementsFigure 5.10
AIRPORTPLANNING MANUAL
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6. OPERATING CONDITIONSThis section provides the following information:
• The jet engine exhaust velocities and temperatures.
• The airport and community noise levels.
• The hazard areas.
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6.1. ENGINE EXHAUST VELOCITIES AND TEMPERATURES
EM17
0MFE
P010
005.
DG
N
02468
10121416
0 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
AB
C
DEF
DISTANCE FROM CORE NOZZLE EXIT, Feet
0
1
2
3
4
5
00 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
4
8
12
16
20
24
0
1
2
3
4
5
6
7
F E
ABC
D
ABCDEF
Met
ers
Meters
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE,
Fee
t
Met
ers
DIS
TAN
CE
FRO
M A
IRPL
ANE
CL −
Feet
Meters
DISTANCE FROM CORE NOZZLE EXIT, Feet
TAKEOFF POWER, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 63685 N (14317 lbf)
VELOCITY m/s (ft/s)MAX = 482.5 (1583)
15.2 (50)30.5 (100)60.9 (200)121.9 (400)243.8 (800)457.2 (1500)
NOTE:EXHAUST VELOCITY CONTOURS INCLUDE WORST CASE 20 kn HEADWIND WITH GROUND EFFECTS.
Jet Wake Velocity Profile - Takeoff PowerFigure 6.1
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EM17
0MFE
P010
006.
DG
N
02468
10121416
0 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
A
B
CDE
0
1
2
3
4
5
00 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
4
8
12
16
20
24
0
1
2
3
4
5
6
7
E
A
B
CD
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
Met
ers
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE −
Feet
Met
ers
DIS
TAN
CE
FRO
M A
IRPL
ANE
CL −
Feet
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
TAKEOFF POWER, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 63685 N (14317 lbf)
ABCDE
°F100150200400900
TOTAL TEMPERATUREMAX = 689°C (1273°F)
°C386693204582
NOTE:EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND.
Jet Wake Temperature Profile - Takeoff PowerFigure 6.2
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EM17
0MFE
P010
007.
DG
N
02468
10121416
0 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
A
BCD
0
1
2
3
4
5
00 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
4
8
12
16
20
24
0
1
2
3
4
5
6
7A
BCD
ABCD
Met
ers
Met
ers
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE −
Feet
DIS
TAN
CE
FRO
M A
IRPL
ANE
CL −
Feet
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
GROUND IDLE, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 3785 N (851 lbf)
VELOCITY m/s (ft/s)MAX = 89.0 (292)
(50)(100)(150)(250)
15.230.545.776.2
NOTE:EXHAUST VELOCITY CONTOURS INCLUDE WORST CASE 20 kn HEADWIND WITH GROUND EFFECTS.
Jet Wake Velocity Profile - Ground IdleFigure 6.3
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EM17
0MFE
P010
008.
DG
N
02468
10121416
0 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
A
BCDE
0
1
2
3
4
5
00 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60
0 2 4 6 8 10 12 14 16 18
4
8
12
16
20
24
0
1
2
3
4
5
6
7
E
A
BCD
ABCDE
°F100150200400900
TOTAL TEMPERATUREMAX = 519°C (966°F)
°C386693204582
Met
ers
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE −
Feet
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
Met
ers
DIS
TAN
CE
FRO
M A
IRPL
ANE
CL −
Feet
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
GROUND IDLE, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 3785 N (851 lbf)
NOTE:EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND.
Jet Wake Temperature Profile - Ground IdleFigure 6.4
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VELOCITY m/s (ft/s)MAX = 230.8 (757.3)
NOTE:EXHAUST VELOCITY CONTOURS INCLUDE WORST CASE 20 kn HEADWIND WITH GROUND EFFECTS.
6
15
5
20
Meters
Met
ers
523010
B
C
D
30
25
20
15
10
5
00
2
4
6
8
10
10 15 20 25 30 35 40 45 50 55 600 4
DISTANCE FROM CORE NOZZLE EXIT, Feet
Meters
A
181614121086420
DIS
TAN
CE
FRO
M A
IRPL
ANE
CL −
Feet
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE,
Fee
t
0
10
0 20 40 60
0 2 4 6 8 10 12 14 16 18
AB
C
D
DISTANCE FROM CORE NOZZLE EXIT, Feet
0
1
2
3
4
5
C
EM17
0APM
0600
06A.
DG
N
Met
ers
ABCD
15.2 (50)30.5 (100)60.9 (200)121.9 (400)
Jet Wake Velocity Profile - Breakaway PowerFigure 6.5
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0 5 10 15 20 25 30 35 40 45 50 55 60
0 2 4 6 8 10 12 14 16 18
0
5
10
15
20
0
1
2
3
4
5
6
Met
ers
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE −
Feet
F E D
C
B A
DISTANCE FROM CORE NOZZLE EXIT − Feet
0 5 10 15 20 25 30 35 40 45 50 55 60
0 2 4 6 8 10 12 14 16 18
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
0
5
10
15
20
0
2
4
6
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE −
Feet
F
E
D C B
A
ABCDEF
NOTE:
EM17
0APM
0600
07A.
DG
N
Met
ers
Meters
EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND WITH GROUND EFFECTS.
TOTAL TEMPERATUREMAX = 495 °C (923 °F)
386693121149177
°C °F100150200250300350
Jet Wake Temperature Profile - Breakaway PowerFigure 6.6
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6.2. AIRPORT AND COMMUNITY NOISE
Aircraft noise is a major concern for the airport and community planner. The airport is a basic element inthe community’s transportation system and, thus, is vital to its growth. However, the airport must also bea good neighbor, and this can only be accomplished with proper planning. Since aircraft noise extendsbeyond the boundaries of the airport, it is vital to consider the noise impact on the surroundingcommunities.Many means have been devised to provide the planner with a tool to estimate the impact of airportoperations. Too often they oversimplify noise to the point where the results become erroneous. Noise isnot a simple matter; therefore, there are no simple answers.The cumulative noise contour is an effective tool. However, care must be exercised to ensure that thecontours, used correctly, estimate the noise resulting from aircraft operations conducted at an airport.The size and shape of the single-event contours, which are inputs into the cumulative noise contours,are dependent upon numerous factors. They include operational factors (aircraft weight, engine powersetting, airport altitude), atmospheric conditions (wind, temperature, relative humidity, surface condition),and terrain.
6.2.1. External Certification Noise Levels
The aircraft comply with the Stage 3 / Chapter 3 noise limits set forth in 14 CFR Part 36, ICAOAnnex 16,Volume 1, Chapter 3, Amendment 7 and CTA RBHA 36.
6.2.2. Ramp Noise Levels
The ramp noise will not exceed 80 dBA (maximum) and 77 dBA (average) on the rectangular perimeterof 20 m (65 ft 7 in) from the aircraft centerline, nose and tail, 90 dBA on the service positions and 80 dBAon the passenger entrance positions resulting from operation of the APU (if fitted), ECS, equipmentcooling fans and vent fans, in any combination.
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6.3. HAZARD AREAS
R=4.3 m(14 ft)
1.8 m(6 ft)
TAKEOFF POWER, SEA LEVEL, Tamb = ISA +16.7° C, FNIN1 = 63685 N (14317 lbf)
ENGINE EXHAUST HAZARD AREAVELOCITY = 65 mph OR GREATER = 29.0 m/s (95.3 ft/s)
NOTE:
2
2
1
132 m(433 ft)
1
EXHAUST HAZARD AREA − CONDITION: 20 kn HEADWIND WITH GROUND EFFECTS.
INLET HAZARD AREA − CONDITION: 20 kn HEADWIND/CROSSWIND BASED ON 12.2 m/s(40 ft/s) CRITICAL VELOCITY WITH 0.9 m (3 ft) CONTINGENCY FACTOR.
NO ACCESS TO ENGINE ACCESSORIES AT TAKEOFF POWER.
EM17
0MFE
P010
001A
.DG
N
Hazard Areas - Takeoff PowerFigure 6.7
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EM17
0MFE
P010
002.
DG
N
26 m(86 ft)
2.6 m(8.6 ft)R=2.5 m
(8.3 ft)
ENGINE EXHAUST HAZARD AREAVELOCITY = 65 mph OR GREATER = 29.0 m/s (95.3 ft/s)
2
1
1
2
EXHAUST HAZARD AREA − CONDITION: 20 kn HEADWIND WITH GROUND EFFECTS.
INLET HAZARD AREA − CONDITION: 20 kn HEADWIND/CROSSWIND/TAILWIND BASED ON 12.2 m/s (40 ft/s) CRITICAL VELOCITY WITH 0.9 m (3 ft) CONTINGENCY FACTOR.
GROUND IDLE, SEA LEVEL, Tamb = ISA+16.7° C, FNIN1 = 3785 N (851 lbf)
Hazard Areas - Ground IdleFigure 6.8
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7. PAVEMENT DATA7.1. GENERAL INFORMATION
Pavement is defined as a structure consisting of one or more layers of processed materials.The primary function of a pavement is to distribute concentrated loads so that the supporting capacity ofthe subgrade soil is not exceeded. The subgrade soil is defined as the material on which the pavementrests, whether embankment or excavation.Several methods for design of airport pavements have been developed that differ considerably in theirapproach.The design methods are derived from observation of pavements in service or experimental pavements.Thus, the reliability of any method is proportional to the amount of experimental verification behind themethod, and all methods require a considerable amount of common sense and judgment on the part ofthe engineer who applies them.A brief description of the following pavement charts will be helpful in their use for airport planning. Eachaircraft configuration is depicted with a minimum range of five loads imposed on the main landing gearto aid in the interpolation between the discrete values shown. The tire pressure used for the aircraftcharts will produce the recommended tire deflection with the aircraft loaded to its maximum ramp weightand with center of gravity position. The tire pressure, where specifically designated in tables and charts,are values obtained under loaded conditions as certified for commercial use.This section is presented as follows:
• The basic data on the landing gear footprint configuration, maximum design ramp loads, and tiresizes and pressures.
• The maximum pavement loads for certain critical conditions at the tire-ground interfaces.
• A chart in order to determine the loads throughout the stability limits of the aircraft at rest on thepavement. Pavement requirements for commercial aircraft are customarily derived from the staticanalysis of loads imposed on the main landing gear struts. These main landing gear loads are usedto enter the pavement design charts which follow, interpolating load values where necessary.
• The flexible pavement curves prepared in accordance with the US Army Corps of Engineers DesignMethod and the LCN Method.
• The rigid pavement design curves in accordance with the Portland Cement Association DesignMethod and the LCN Method.
• The aircraft ACN values for flexible and rigid pavements.
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7.2. FOOTPRINT
MAXIMUM RAMP WEIGHT
NOSE GEAR TIRE SIZE 24 x 7.7
NOSE GEAR TIRE PRESSURE
MAIN GEAR TIRE SIZE
MAIN GEAR TIRE PRESSURE
0.71 m(2 ft 4 in.)
11.40 m(37 ft 5 in.)
0.40 m(1 ft 4 in.)
(17 ft 1 in.)5.2 m
AIRCRAFT MODELSSTD
37660 kg(83026 lb)
38950 kg(85870 lb)
(102 − 0 / +10 psi)
H38 x 13−18
9.56 − 0 / + 0.7 kg/cm ²(136 − 0 / +10 psi)
LR
7.17 − 0 / + 0.7 kg/cm ²
EM17
0APM
0700
42A.
DG
N
FootprintFigure 7.1
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7.3. MAXIMUM PAVEMENT LOADS
NG
MG
VNG VMG
MODEL STATIC AT MOSTFORWARD C.G.
NGV MGV (PER STRUT) (PER STRUT)H
H
2
NOTE: ALL LOADS CALCULATED USING AIRCRAFT MAXIMUM RAMP WEIGHT
MAXIMUMRAMP
WEIGHT STATIC AT MOSTAFT C.G.
STEADYBRAKING
WITHDECELERATION OF
3,0 m/sec
INSTANTANEOUSBRAKING(FRICTION
COEF. OF 0.8)2
STEADYBRAKING
WITHDECELERATION OF
3,0 m/sec
STD 4732 kgf(10432 lbf)
4768 kgf(10432 lbf)
6896 kgf(15203 lbf)
6787 kgf(14963 lbf)
LR 18509 kgf(40805 lbf)
17922 kgf(39511 lbf)
5397 kgf(11898 lbf)
5225 kgf(11519 lbf)
12737 kgf(28080 lbf)
12328 kgf(27179 lbf)
EM17
0APM
0700
43A.
DG
N
LEGEND: V = MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST FORWARD C.G.
V = MAXIMUM VERTICAL MAIN GEAR GROUND LOAD AT MOST AFT C.G.
38950 kg(85870 lb)
37660 kg(83026 lb)
H = MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING
Maximum Pavement LoadsFigure 7.2
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7.4. LANDING GEAR LOADING ON PAVEMENT
LEGEND
STD AIRCRAFT MODEL
38950
37660
35000
32500
30000
27500
25000
22500MOW
18000
20000
22000
24000
26000
28000
30000
32000
34000
36000
38000
40000
85 86 87 88 89 90 91 92 93 94 95
AIR
CR
AFT
GR
OSS
WEI
GH
T −
(kg)
90000
80000
70000
60000
50000
40000
30000
2000020000
30000
40000
50000
60000
70000
80000
90000
EM17
0APM
0700
44B.
DG
NAI
RC
RAF
T G
RO
SS W
EIG
HT −
(lb)
LR AIRCRAFT MODEL
7.0% 27.0%% CMA
PERCENT OF WEIGHT ON MAIN LANDING GEARS − (%)
WEI
GH
T O
N M
AIN
LAN
DIN
G G
EAR
− (l
b)
WEI
GH
T O
N M
AIN
LAN
DIN
G G
EAR
S −
(kg)
Landing Gear Loading on PavementFigure 7.3
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7.5. FLEXIBLE PAVEMENT REQUIREMENTS, U.S. CORPS OF ENGINEERS DESIGNMETHOD
The flexible pavement curves are based on the procedures set forth in Instruction Report No. S-77-1,“Procedures for Development of CBR Design Curves”, dated June 1977, and modified according to themethods described in FAA Advisory Circular 150/5320-6D, “Airport Pavement Design and Evaluation”,dated July 7, 1995. Instruction Report No. S-77-1 was prepared by the US Army Corps of EngineersWaterways Experiment Station, Soils and Pavements Laboratory, Vicksburg, Mississippi. The lineshowing 10,000 coverages is used to calculate ACN.
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EM17
0APM
0700
46A.
DG
N
38790 (85517)38950 (85870)
34000 (74957)22500 (49604)
NOTES:
SUBGRADE STRENGHT − CBR MODEL
TIRE SIZE: H38 x 13−18 18 PRTIRE PRESSURE: 9.56 kgf/cm² (136 psi)
10000 COVERAGES(USED FOR ACNCALCULATIONS)
ANNUALDEPARTURES
WEIGHT ON MAINLANDING GEAR
(kg) (lb)
10 20 309876543FLEXIBLE PAVEMENT THICKNESS − in
FLEXIBLE PAVEMENT THICKNESS − cm20 30 40 50 60 708 9 10
10 20 309876543
1200
3200
6000
15000
25000
Flexible Pavement Requirements - US Army Corps of Engineers Design MethodFigure 7.4
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7.6. FLEXIBLE PAVEMENT REQUIREMENTS, LCN METHOD
The LCN method presents curves for flexible pavements. They have been built using procedures andcurves in the ICAO Aerodrome Design Manual, Part 3 - Pavements, Document 9157-AN/901, 1983. Thesame chart includes the data of equivalent single-wheel load versus pavement thickness.
AIRPORTPLANNING MANUAL
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10000
20000
30000
40000
4
EQU
IVAL
ENT
SIN
GLE
WH
EEL
LOAD
− (l
b)
8000
6000
10000
12000
1400016000
EQU
IVAL
ENT
SIN
GLE
WH
EEL
LOAD
− (k
g)
5010 20 30 40
LCN − LOAD CLASSIFICATION NUMBER
5 6 7 8 9 10 20 30 40 50 70 8090100
60
2 3 4 5 6 7 8 9 10 20 30
100
NOTES:EQUIVALENT SINGLE WHEEL LOADSARE DERIVED BY METHODS SHOWNIN ICAO AERODROME MANUAL.PART 2, PAR. 4.1.3
WEIGHT ON MAINLANDING GEAR
kg (lb)38790 (85517)
38950 (85870)
34000 (74957)
22500 (49604)
EM17
0APM
0700
48A.
DG
N
NOTES: TIRE SIZE: H38 x 13−18 18 PRTIRE PRESSURE: 9.56 kgf/cm² (136 psi)
FLEXIBLE PAVEMENT THICKNESS − (cm)
FLEXIBLE PAVEMENT THICKNESS − (in.)
Flexible Pavement Requirements - LCN MethodFigure 7.5
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7.7. RIGID PAVEMENT REQUIREMENTS, PORTLAND CEMENT ASSOCIATION DESIGNMETHOD
This method has a chart that has been prepared with the use of the Westergaard Equation in generalaccordance with the procedures outlined in the 1955 edition of “Design of Concrete Airport Pavement”published by the Portland Cement Association, 33 W. Grand Ave., Chicago 10, Illinois, but modified tothe new format described in the 1968 Portland Cement Association publication, “Computer Program forConcrete Airport Pavement Design” by Robert G. Packard. The following procedure is used to developrigid pavement design curves such as those shown in the chart:
• Once the scale for the pavement thickness to the left and the scale for allowable working stress to theright have been established, an arbitrary load line is drawn representing the main landing gearmaximum weight to be shown.
• All values of the subgrade modulus (k-values) are then plotted.
• Additional load lines for the incremental values of weight on the main landing gear are thenestablished on the basis of the curve for k=300, already established.
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MAXIMUM POSSIBLE MAIN−GEARLOAD AT MAXIMUM DESIGN RAMPWEIGHT AND AFT C.G.
NOTES: TIRE SIZE: H38 x 13−18 18PRTIRE PRESSURE: 9.56 kgf/cm² (136 psi) (UNLOADED)
RIGID PAVEMENT REQUIREMENTS
EM17
0APM
0700
50A.
DG
N
THE VALUES OBTAINED BY USING THEMAXIMUM LOAD REFERENCE LINE ANDANY VALUE OF "K" ARE EXACT. FORLOADS LESS THAN MAXIMUM, THE CURVESARE EXACT FOR K=300 BUT DEVIATESLIGHTLY FOR OTHER VALUES OF "K".
NOTE:
22500 (49604)
34000 (74957)
38790 (85517)38950 (85870)
38950 (85870)k=550 lb/in
k=300 lb/in
k=150 lb/in
k=75 lb/in
ALLO
WAB
LE W
OR
KIN
G S
TRES
S −
psi
ALLO
WAB
LE W
OR
KIN
G S
TRES
S −
kgf/c
m²
55
60 60
5522
24
750
800
850
WEIGHT ON MAIN LANDING GEAR − kg (lb)
0
5
10
15
20
25
30
35
40
45
50
0
50
100
150
200
250
300
350
400
450
500
550
600
650
700
0
5
10
15
20
25
30
35
40
45
50
PAVE
MEN
T TH
ICKN
ESS
(cm
)
0
2
4
6
8
10
12
14
16
18
20
PAVE
MEN
T TH
ICKN
ESS
(in.)
Rigid Pavement Requirements - Portland Cement Association Design MethodFigure 7.6
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EFFECTIVITY: EMBRAER 175 LR ACFT MODEL Section 7Page 7-10Jun 29/06
7.8. RIGID PAVEMENT REQUIREMENTS, LCN METHOD
This LCN Method presents curves for rigid pavements. They have been built using procedures andcurves in ICAO Aerodrome Design Manual, Part 3 - Pavements, Document 9157-AN/901, 1983. Thesame chart includes the data of equivalent single-wheel load versus radius of relative stiffness.To determine the aircraft weight that can be accommodated on a particular rigid airport pavement, boththe LCN of the pavement and the radius of relative stiffness must be known.The radius of relative stiffness values is obtained from a table. This table presents the radius of relativestiffness values based on Young’s modulus (E) of 4,000,000 psi and Poisson’s ratio (µ) of 0.15.For convenience in finding this radius based on other values of E and µ, the curves are included. Forexample, to find an RRS value based on an E of 3,000,000 psi, the “E” factor of 0.931 is multiplied bythe RRS value found in figure 7.6.3. The effect of the variations of µ on the RRS value is treated in asimilar manner.
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EM17
0APM
0700
07.D
GN
RADIUS OF RELATIVE STIFFNESS ( )VALUES IN INCHES
=4 Ed =24.16522
4 dk
33
6
3
12( 1− )k
WHERE: E = YOUNG’S MODULUS = 4 x 10 psi k = SUBGRADE MODULUS, lb/in.
d = RIGID−PAVEMENT THICKNESS. in. = POISSON’S RATIO = 0.15
d(in) k=75 k=100 k=150 k=200 k=250 k=300 k=350 k=400 k=500 k=550
6.06.57.0
7.58.08.5
9.09.5
10.0
10.511.011.5
12.012.513.0
13.514.014.5
15.015.516.0
16.517.017.5
18.018.519.0
19.520.020.5
21.021.522.0
22.523.023.5
24.024.525.0
31.4833.4335.34
37.2239.0640.88
42.6744.4346.18
47.9049.6051.28
52.9454.5956.22
57.8359.4361.02
62.5964.1565.69
67.2368.7570.26
71.7673.2574.73
76.2077.6679.11
80.5581.9983.41
84.8386.2487.64
89.0490.4391.81
29.3031.1132.89
34.6336.3538.04
39.7141.3542.97
44.5746.1647.72
49.2750.8052.32
53.8255.3156.78
58.2559.7061.13
62.5663.9865.38
66.7868.1769.54
70.9172.2773.62
74.9676.3077.63
78.9580.2681.56
82.8684.1585.44
26.4728.1129.72
31.2932.8534.37
35.8837.3638.83
40.2841.7143.12
44.5245.9047.27
48.6349.9851.31
52.6353.9455.24
56.5357.8159.08
60.3461.6062.84
64.0865.3066.52
67.7468.9470.14
71.3472.5273.70
74.8776.0477.20
24.6326.1627.65
29.1230.5731.99
33.3934.7736.14
37.4838.8140.13
41.4342.7243.99
45.2646.5147.75
48.9850.2051.41
52.6153.8054.98
56.1557.3258.48
59.6360.7761.91
63.0464.1665.28
66.3867.4968.59
69.6870.7671.84
23.3024.7426.15
27.5428.9130.25
31.5832.8934.17
35.4536.7137.95
39.1840.4041.61
42.8043.9845.16
46.3247.4748.62
49.7550.8852.00
53.1154.2155.31
56.3957.4758.55
59.6260.6861.73
62.7863.8364.86
65.9066.9267.95 64.92
63.9462.96
61.9760.9859.99
58.9857.9756.96
55.9454.9153.88
52.8451.8050.74
49.6848.6147.54
46.4545.3644.26
43.1542.0240.89
39.7538.6037.44
36.2635.0733.87
32.6531.4230.17
28.9127.6226.32
24.9923.6422.26 21.42
22.7424.04
25.3226.5827.81
29.0330.2331.42
32.5933.7534.89
36.0237.1438.25
39.3540.4441.51
42.5843.6444.70
45.7446.7747.80
48.8249.8450.84
51.8452.8453.83
54.8155.7856.75
57.7258.6859.63
60.5861.5262.46
20.7222.0023.25
24.4925.7026.90 25.44
24.3123.16
21.9920.8019.59 19.13
20.3121.47
22.61
28.0829.2430.39
31.5232.6433.74
34.8435.9236.99
38.0639.1140.15
41.1942.2143.23
44.2445.2446.23
47.2248.2049.17
50.1451.1052.06
53.0153.9554.89
55.8256.7557.67
58.5959.5060.41
23.7424.84
25.9327.0028.06
29.1130.1431.16
32.1733.1734.16
35.1436.1237.08
38.0338.9839.92
40.8541.7842.70
43.6144.5145.41
46.3047.1948.07
48.9549.8250.69
51.5552.4153.26
54.1154.9555.7957.14
56.2855.41
54.5453.6752.79
51.9151.0250.13
49.2348.3347.42
46.5145.5944.66
43.7242.7841.84
40.8839.9238.95
37.9736.9935.99
34.9933.9732.95
31.9130.8729.81
28.7427.6526.55
Radius of Relative StiffnessFigure 7.7
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EM17
0APM
0700
08.D
GN
0 1 2 3 4 5
0 0.05 0.10 0.15 0.20 0.250
0.995
1.000
1.005
1.010
1.015
0
1.10
1.05
1.00
0.95
0.90
0.85
0.80
E FACTOR
FACTOR
6E, YOUNG’S MODULUS (10 ,PSI)
EFFECT OF E ON −VALUES
BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THE −VALUES.NOTE:
EFFECT OF ON −VALUES
, POISSON’S RATIO
Radius of Relative Stiffness (other values)Figure 7.8
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200 300 10
EQU
IVAL
ENT
SIN
GLE
WH
EEL
LOAD
− (k
g)
40
8000
6000
10000
12000
14000
16000
40
EQU
IVAL
ENT
SIN
GLE
WH
EEL
LOAD
− (l
b)
20000
30000
10000
40000
3020
WEIGHT ON MAINLANDING GEAR
kg (lb)
50 60 70 80 90 100
RADIUS OF RELATIVE STIFFNESS − (in.)
RADIUS OF RELATIVE STIFFNESS − (cm)
20 30 40 50 60 70 80 90 100EM
170A
PM07
0052
A.D
GN
NOTES:EQUIVALENT SINGLE WHEEL LOADSARE DERIVED BY METHODS SHOWNIN ICAO AERODROME MANUAL.PART 2, PAR. 4.1.3
LCN − LOAD CLASSIFICATION NUMBER
NOTES: TIRE SIZE: H38 x 13−18 18 PRTIRE PRESSURE: 9.56 kgf/cm² (136 psi)
34000 (74957)
22500 (49604)
38790 (85517)38950 (85870)
Rigid Pavement Requirements - LCN MethodFigure 7.9
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7.9. ACN - PCN SYSTEM - FLEXIBLE AND RIGID PAVEMENTS
The ACN/PCN system as referenced in Amendment 35 to ICAO Annex 14, “Aerodromes”, provides astandardized international aircraft/pavement rating system.The PCN is an index rating of the mass that according to evaluation can be borne by the pavementwhen applied by a standard single wheel. The ACN is established for the particular pavement type andsubgrade category of the rated pavement, as well as for the particular aircraft mass and characteristics.An aircraft shall have an ACN equal to or less than the PCN to operate without restriction on thepavement.The method of pavement evaluation is left up to the airport, and the results of such evaluation arepresented as follows:
Table 7.1 - Pavement EvaluationPAVEMENTTYPE SUBGRADE CATEGORY TIRE PRESSURE CATEGORY METHOD
R – Rigid A – High W – No Limit T – TechnicalF – Flexible B – Medium X – to 1.5 Mpa (217 psi) U – Using aircraft
C – Low Y – to 1.0 Mpa (145 psi)D – Ultra Low Z – to 0.5 Mpa (73 psi)
Report example: PCN 80/R/B/X/T, where:80 = PCNR = Pavement Type: RigidB = Subgrade Category: MediumX = Tire Pressure Category: Medium (limited to 1.5 Mpa)T = Evaluation Method: Technical
The flexible pavements have four subgrade categories:
A. High Strength - CBR 15.
B. Medium Strength - CBR 10.
C. Low Strength - CBR 6.
D. Ultra Low Strength - CBR 3.The rigid pavements have four subgrade categories:
A. High Strength - Subgrade k = 150 MN/m3 (550 lb/in3).
B. Medium Strength - k = 80 MN/m3 (300 lb/in3).
C. Low Strength - k = 40 MN/m3 (150 lb/in3).
D. Ultra Low Strength - k = 20 MN/m3 (75 lb/in3).
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5
15
25
20
10
40000
86000
2400020000 22000 26000 30000 32000 34000 36000 3800028000
52000 56000 60000 64000 68000 72000 76000 80000 84000
AIRCRAFT GROSS WEIGHT−kg
AIRCRAFT GROSS WEIGHT−lb4800044000
AIR
CR
AFT
CLA
SSIF
ICAT
ION
NU
MBE
R−A
CN
FLEXIBLE PAVEMENT SUBGRADE
SBGRADE STRENGTH ULTRA LOW − CBR=3%LOW − CBR=6%MEDIUM−CBR=10%HIGH−CBR=15%
37660
MAX
IMU
M R
AMP
WEI
GH
T
EM17
0APM
0700
54A.
DG
N
30
NOTES:TIRE PRESSURE: 9.56 kgf/cm² (136 psi) (UNLOADED)TIRE SIZE: H38 x 13−18 18PR
ACN For Flexible PavementFigure 7.10
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MAX
IMU
M R
AMP
WEI
GH
T
5
15
25
38950
20
10
40000
86000
2400020000 22000 26000 30000 32000 34000 36000 3800028000
52000 56000 60000 64000 68000 72000 76000 80000 84000
AIRCRAFT GROSS WEIGHT−kg
AIRCRAFT GROSS WEIGHT−lb4800044000
AIR
CR
AFT
CLA
SSIF
ICAT
ION
NU
MBE
R−A
CN
EM17
0APM
0700
56A.
DG
N
30
SBGRADE STRENGTH ULTRA LOW − K=20 MN/m³ (75 lb/in³)LOW − K=40 MN/m³ (150 lb/in³)MEDIUM− K=80 MN/m³ (300 lb/in³)HIGH− K=150 MN/m³ (550 lb/in³)
RIGID PAVEMENT SUBGRADE
NOTES:TIRE PRESSURE: 9.56 kgf/cm² (136 psi) (UNLOADED)TIRE SIZE: H38 x 13−18 18PR
ACN For Rigid PavementFigure 7.11
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8. POSSIBLE EMBRAER 175 DERIVATIVE AIRCRAFT8.1. NOT APPLICABLE
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9. SCALED DRAWINGS9.1. GENERAL
This section provides plan views to the following scales:
• English/American Customary Weights and Measures1 inch = 32 feet1 inch = 50 feet1 inch = 100 feet
• Metric1:5001:1000
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0
0 16 32 48 64
5 10 15 20 25 m
80 ft
1
2
34
5
6
7
89
10
11
13 12
10
ITEM DESCRIPTION
1
ITEM DESCRIPTION8
23
45
67
9101112
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTINGAIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANELOXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)PRESSURE REFUELING / DEFUELING
CARGO DOORMAIN LANDING GEAR
NOSE LANDING GEARPASSENGER DOOR
13 14
14
11
WING SPAN:25.99 m
(85 ft 3 in.)
14 SERVICE DOOR
EM17
0APM
0900
16A.
DG
N
Scale: 1 Inch Equals 32 FeetFigure 9.1
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EFFECTIVITY: ALL Section 9Page 9-2Jun 28/05
0
0 16 32 48 64
5 10 15 20 25 m
80 ft
ITEM DESCRIPTION
1
ITEM DESCRIPTION8
23
45
67
9101112
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTINGAIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANELOXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)PRESSURE REFUELING / DEFUELING
CARGO DOORMAIN LANDING GEAR
NOSE LANDING GEARPASSENGER DOOR
1
2
34
5
6
7
89
1011
13
12
10
13 14
11
14
WING SPAN:25.99 m
(85 ft 3 in.)
14 SERVICE DOOR
EM17
0APM
0900
17A.
DG
N
Scale: 1 Inch Equals 50 FeetFigure 9.2
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0
0 16 32 48 64
5 10 15 20 25 m
80 ft
ITEM DESCRIPTION
1
ITEM DESCRIPTION8
23
45
67
9101112
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTINGAIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANELOXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)PRESSURE REFUELING / DEFUELING
CARGO DOORMAIN LANDING GEAR
NOSE LANDING GEARPASSENGER DOOR
1
2
34
5
6
7
89
10
11
1312
10
13 14
14
WING SPAN:25.99 m
(85 ft 3 in.)
14 SERVICE DOOR
11
EM17
0APM
0900
18A.
DG
N
Scale: 1 Inch Equals 100 FeetFigure 9.3
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EFFECTIVITY: ALL Section 9Page 9-4Jun 28/05
0
0 16 32 48 64
5 10 15 20 25 m
80 ft
ITEM DESCRIPTION
1
ITEM DESCRIPTION8
23
45
67
9101112
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTINGAIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANELOXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)PRESSURE REFUELING / DEFUELING
CARGO DOORMAIN LANDING GEAR
NOSE LANDING GEARPASSENGER DOOR
1
2
34
5
6
7
89
10
11
13
12
10
13
11
14
14
WING SPAN:25.99 m
(85 ft 3 in.)
14 SERVICE DOOR
EM17
0APM
0900
19A.
DG
N
Scale: 1 to 500Figure 9.4
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0
0 16 32 48 64
5 10 15 20
80 ft
50 m25
ITEM DESCRIPTION
1
ITEM DESCRIPTION8
23
45
67
9101112
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTINGAIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANELOXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)PRESSURE REFUELING / DEFUELING
CARGO DOORMAIN LANDING GEAR
NOSE LANDING GEARPASSENGER DOOR
1
2
34
5
6
7
89
10
11
1312
10
WING SPAN:25.99 m
(85 ft 3 in.)
13
14
14
11
14 SERVICE DOOR
EM17
0APM
0900
20A.
DG
N
Scale: 1 to 1000Figure 9.5
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