Airport Planning Manual

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.

ISSUEDATE

DATEINSERTED

BYREVNo.

ISSUEDATE

DATEINSERTED

BY

AIRPORTPLANNING MANUAL

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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


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


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

0APM

0200

16B.

DG

N

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

0200

17A.

DG

N

A

(REF.)FUSLG ANGLE

B

CD

E

L

M

KJH

Ground ClearancesFigure 2.2


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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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EFFECTIVITY: ALL Section 2Page 2-9May 11/07

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


w-apm2259


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.


w-apm2259


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


90°

100 ft Radius(30 m)

100 ft Radius(30 m)

NOTE:

PATH OF MAIN LANDINGGEAR TIRE EDGE.


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


90°

100 ft Radius(30 m)

NOTE:



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)



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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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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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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3

12

20

14

1

456789

1011

13

1516171819

2122

2

ITEM DESCRIPTIONCOORD. Y

(mm)COORD. Z

(mm)COORD. X

(mm)

HEIGHTABOVE

GROUND(mm)


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


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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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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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


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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


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


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


Meters


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


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


Meters

Met

ers

DIS

TAN

CE

FRO

M A

IRPL

ANE

CL −

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)


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


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


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


0 5 10 15 20 25 30 35 40 45 50 55 60

0 2 4 6 8 10 12 14 16 18


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:

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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

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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

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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

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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

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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

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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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EFFECTIVITY: EMBRAER 175 LR ACFT MODEL Section 7Page 7-6Jun 29/06

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.


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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


kg (lb)38790 (85517)

38950 (85870)

34000 (74957)

22500 (49604)

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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

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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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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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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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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


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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EFFECTIVITY: EMBRAER 175 LR ACFT MODEL Section 7Page 7-17 / 18

Jun 29/06

8. POSSIBLE EMBRAER 175 DERIVATIVE AIRCRAFT8.1. NOT APPLICABLE


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EFFECTIVITY: ALL Section 8Page 8-1 / 2Jun 28/05

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



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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0

0 16 32 48 64

5 10 15 20 25 m

80 ft

ITEM DESCRIPTION

1

ITEM DESCRIPTION8

23

45

67

9101112

13









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



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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









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



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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









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









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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Documents

Airport Planning Manual