e195 Apto Plan

AIRPORT PLANNINGMANUAL

APM-199728 JULY 2006

REVISION 4 - 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/062 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/06

List of Effective Pages

* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08Table of Contents

1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/072 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07

List of Tables

* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/06

List of Figures1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/062 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/073 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/074 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07

Section 11-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/06

* 1-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 1-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/081-4 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/06

Section 2

* 2-1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-4 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-5 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-6 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-7 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-8 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-9 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-10 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-11 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-12 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-13 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-14 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-15 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 2-16 Blank (rev) . . . . . . . . . . . . . . . . . . Oct 07/08Section 3(Not Available)Section 4

* 4-1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 4-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 4-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07

* 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/065-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/065-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/065-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/066-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07

* 6-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/086-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/076-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-12 Blank . . . . . . . . . . . . . . . . . . . . . . . . May 11/07

Section 77-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07

* 7-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 7-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08

* 7-4 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/087-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07


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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7-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/077-18 Blank . . . . . . . . . . . . . . . . . . . . . . . . May 11/07

Section 88-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/068-2 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/06

Section 99-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 28/069-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/079-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/079-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/079-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/079-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07


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 Arrangements ...................................................................................................... 2-92.5. Passenger Cabin Cross Section ..................................................................................... 2-122.6. Lower Compartment Containers ...................................................................................... 2-142.7. Door Clearances ............................................................................................................. 2-15

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 Apron .................................................................................................... 4-9

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 ......................................................................................... 6-96.3. Hazard Areas .................................................................................................................. 6-10


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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 195 DERIVATIVE AIRCRAFT

8. Possible EMBRAER 195 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 Ground Clearance — AR Aircraft Model ................................................ 02 8

2.5 Capacity for the Cargo Compartment .................................................... 02 11

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 Aircraft Ground Clearances................................................... 02 5

2.3 Interior Arrangements............................................................ 02 10

2.4 Economy Class Passenger Cabin Cross-Section................. 02 12

2.5 First Class Passenger Cabin Cross-Section......................... 02 13

2.6 Door Dimensions................................................................... 02 15

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 6

4.5 90° Turn - Runway to Taxiway .............................................. 04 7

4.6 90° Turn - Taxiway to Taxiway .............................................. 04 8

4.7 Runway Holding Bay............................................................. 04 9

5.1 Aircraft Servicing Arrangement With Passenger Bridge ....... 05 2

5.2 Aircraft Servicing Arrangement With Passenger Stairs ........ 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 X Tem-perature ................................................................................. 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...................... 1 of 2 06 6

6.5 Jet Wake Velocity Profile - Breakaway Power...................... 2 of 2 06 7

6.6 Jet Wake Temperature Profile - Breakaway Power .............. 06 8

6.7 Hazard Areas - Takeoff Power .............................................. 06 10

6.8 Hazard Areas - Ground Idle .................................................. 06 11

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 UnitAR Advanced RangeATTCS Automatic Takeoff-Thrust Control-SystemBOW Basic Operating WeightCBR California Bearing RatioECS Environmental Control SystemFAA Federal Aviation AdministrationFAR Federal Aviation Regulations


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Table 1.2 - List of Acronyms and Abbreviations used in the APM

ACRONYMS AND ABBREVIATIONS DESCRIPTIONFWD ForwardGEAE 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 CF34-10 with 82.3 kN (18500 lbf) maximum takeoffthrust (Sea Level, Static Condition and ISA) installed under the wings.The aircraft has three versions, with different ranges as a function of the difference between theMTOWs:

• The STD aircraft model - MTOW 48790 kg (107564 lb);

• The LR aircraft model - MTOW 50790 kg (111973 lb);

• The AR aircraft model - MTOW 52290 kg (115280 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 at which the aircraft may 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 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 AR

MRW 48950 kg (107916 lb) 50950 kg (112326 lb) 52450 kg (115632 lb)MTOW 48790 kg (107564 lb) 50790 kg (111973 lb) 52290 kg (115280 lb)MLW 45000 kg (99208 lb) 45800 kg (100972 lb)

BOW [2] 28970 kg (63868 lb)MZFW 42500 kg (93696 lb) 42600 kg (93917 lb)

MaximumPayload [2] 13800 kg (30424 lb) 13900 kg (30644 lb)

Maximum SeatingCapacity 118 passengers

MaximumCargo Volume[3] 25.66 m3 (906.17 ft3)

Usable Fuel [4] 13100 kg (28881 lb)16029 ! (4234 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 - 28.72 m (94 ft 3 in);

• Height (maximum) - 10.55 m (34 ft 7 in);

• Overall length - 38.67 m (126 ft 10 in).


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2.2.2. Wing

• Reference area - 92.50 m2 (996 ft2);

• Reference aspect ratio - 8.1

2.2.3. Fuselage

• Total Length - 38.65 m (126 ft 10 in);

• Length of pressurized section - 31.49 m (103 ft 4 in).

2.2.4. Horizontal Tail

• Span - 12.08 m (39 ft 8 in);

• Area - 26.00 m2 (280 ft2).

2.2.5. Vertical Tail

• Reference area - 16.20 m2 (174 ft2 54 in2)


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5.94 m(19 ft 6 in)

28.72 m(94 ft 3 in.)

(45 ft 4 in)

26,98 m

6.82 m(88 ft 6 in)

10.57 m(34 ft 8 in.)

14.64 m(48 ft)

38.67 m(126 ft 10 in)

12.09 m(39 ft 8 in.)

4.27 m(14 ft)

30.01 m(98 ft 5 in)

4.71 m(15 ft 5.4in)

30.01 m(98 ft 5 in)

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General Aircraft DimensionsFigure 2.1


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2.3. GROUND CLEARANCES

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J KH

L

M

G

A

BC

D

E

F

Aircraft Ground ClearancesFigure 2.2


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Table2.2-G

roundClearance—

STDAircraftModel

WEIGHT

CG(%MAC)

NOSE

(A)

FOR-

WARD

SERVICE

DOOR

(B)

FOR-

WARD

PASSEN-

GER

DOOR

(C)

FOR-

WARD

CARG

ODO

OR

(D)

NACELLE

(E)

WINGLET

(F)

EMER-

GENCY

EXIT

(G)

AFT

CARG

ODO

OR

(H)

AFT

SERVICE

DOOR

(J)

AFT

PASSEN-

GER

DOOR

(K)

VERTI-

CAL

TAIL

(L)

TAIL

SKID

ANGU-

LAR

CLEAR-

ANCE

(DEG

)(M)

48950kg

107916

lb11.3

2.07

m6ft9in

2.58

m8ft5in

2.59

m8ft6in

1.57

m5ft2in

0.49

m1ft7in

5.08

m16

ft8in

3.24

m10

ft7in

2.00

m6ft7in

3.03

m9ft11

in3.03

m9ft11

in10.41m

34ft2in

11.19

48950kg

107916

lb31.0

2.16

m7ft1in

2.65

m8ft8in

2.66

m8ft9in

1.62

m5ft4in

0.50

m1ft8in

5.04

m16

ft6in

3.24

m10

ft7in

1.94

m6ft4in

2.96

m9ft9in

2.96

m9ft9in

10.30m

33ft10

in10.82

48790kg

107563

lb11.3

2.06

m6ft9in

2.58

m8ft5in

2.59

m8ft6in

1.57

m5ft2in

0.49

m1ft8in

5.08

m16

ft8in

3.24

m10

ft7in

2.00

m6ft7in

3.04

m10

ft3.04

m10

ft10.41m

34ft2in

11.19

48790kg

107563

lb31.0

2.16

m7ft1in

2.65

m8ft8in

2.66

m8ft9in

1.62

m5ft4in

0.50

m1ft8in

5.04

m16

ft6in

3.24

m10

ft7in

1.94

m6ft4in

2.96

m9ft9in

2.96

m9ft9in

10.30m

33ft10

in10.83

45000kg

99208lb

7.0

2.07

m6ft9in

2.59

m8ft6in

2.60

m8ft6in

1.58

m5ft2in

0.50

m1ft8in

5.09

m16

ft8in

3.25

m10

ft8in

2.01

m6ft7in

3.05

m9ft2in

3.05

m9ft2in

10.43m

34ft3in

11.26

45000kg

99208lb

31.0

2.17

m7ft2in

2.66

m8ft9in

2.67

m8ft9in

1.63

m5ft4in

0.51

m1ft8in

5.05

m16

ft7in

3.25

m10

ft8in

1.95

m6ft5in

2.97

m9ft9in

2.97

m9ft9in

10.31m

33ft10

in10.88

42500kg

93696lb

7.0

2.08

m6ft9in

2.59

m8ft6in

2.60

m8ft9in

1.58

m5ft2in

0.51

m1ft9in

5.10

m16

ft9in

3.26

m10

ft8in

2.02

m6ft8in

3.06

m10

ft3.06

m10

ft10.45m

34ft3in

11.31

42500kg

93696lb

31.0

2.18

m7ft2in

2.67

m8ft9in

2.68

m8ft10

in1.64

m5ft5in

0.52

m1ft8in

5.06

m16

ft7in

3.26

m10

ft8in

1.96

m6ft5in

2.98

m9ft9in

2.98

m9ft9in

10.32m

33ft10

in10.92

29500kg

65036lb

18.4

2.15

m7ft1in

2.66

m8ft9in

2.67

m8ft9in

1.65

m5ft5in

0.57

m1ft11

in5.16

m16

ft11

in3.32

m10

ft11

in2.08

m6ft10

in3.12

m10

ft3in

3.12

m10

ft3in

10.49m

34ft5in

11.53


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Table2.3-G

roundClearance—

LRAircraftModel

WEIGHT

CG(%MAC)

NOSE

(A)

FOR-

WARD

SERVICE

DOOR

(B)

FOR-

WARD

PASSEN-

GER

DOOR

(C)

FOR-

WARD

CARG

ODO

OR

(D)

NACELLE

(E)

WINGLET

(F)

EMER-

GENCY

EXIT

(G)

AFT

CARG

ODO

OR

(H)

AFT

SERVICE

DOOR

(J)

AFT

PASSEN-

GER

DOOR

(K)

VERTI-

CAL

TAIL

(L)

TAIL

SKID

ANGU-

LAR

CLEAR-

ANCE

(DEG

)(M)

50950kg

112325

lb11.3

2.07

m6ft9in

2.58

m8ft5in

2.59

m8ft6in

1.57

m5ft2

in0.48

m1ft7in

5.07

m16

ft8in

3.23

m10

ft7in

1.98

m6ft6in

3.02

m9ft11

in3.02

m9ft11

in10.40m

34ft2in

11.12

50950kg

112325

lb31.0

2.16

m7ft1in

2.65

m8ft8in

2.65

m8ft8in

1.62

m5ft4

in0.49

m1ft7in

5.03

m16

ft6in

3.23

m10

ft7in

1.93

m6ft4in

2.95

m9ft8in

2.95

m9ft8in

10.29m

33ft9in

10.79

50790kg

111973

lb11.3

2.07

m6ft9in

2.58

m8ft5in

2.59

m8ft6in

1.57

m5ft2in

0.48

m1ft7in

5.07

m16

ft8in

3.23

m10

ft7in

1.98

m6ft6in

3.02

m9ft11

in3.02

m9ft11

in10.40m

34ft2in

11.13

50790kg

111973

lb31.0

2.16

m7ft1in

2.65

m8ft8in

2.65

m8ft8in

1.62

m5ft4in

0.50

m1ft8in

5.03

m16

ft6in

3.24

m10

ft7in

1.93

m6ft4in

2.95

m9ft8in

2.95

m9ft8in

10.29m

33ft9in

10.80

45000kg

99208lb

7.0

2.07

m6ft9in

2.59

m8ft6in

2.60

m8ft6in

1.58

m5ft2in

0.50

m1ft8in

5.09

m16

ft8in

3.25

m10

ft8in

2.01

m6ft7in

3.05

m9ft2in

3.05

m9ft2in

10.43m

34ft3in

11.26

45000kg

99208lb

31.0

2.17

m7ft2in

2.66

m8ft9in

2.67

m8ft9in

1.63

m5ft4in

0.51

m1ft8in

5.05

m16

ft7in

3.25

m10

ft8in

1.95

m6ft5in

2.97

m9ft9in

2.97

m9ft9in

10.31m

33ft10

in10.88

42500kg

93696lb

7.0

2.08

m6ft9in

2.59

m8ft6in

2.60

m8ft9in

1.58

m5ft2in

0.51

m1ft9in

5.10

m16

ft9in

3.26

m10

ft8in

2.02

m6ft8in

3.06

m10

ft3.06

m10

ft10.45m

34ft3in

11.31

42500kg

93696lb

31.0

2.18

m7ft2in

2.67

m8ft9in

2.68

m8ft10

in1.64

m5ft5in

0.52

m1ft8in

5.06

m16

ft7in

3.26

m10

ft8in

1.96

m6ft5in

2.98

m9ft9in

2.98

m9ft9in

10.32m

33ft10

in10.92

29500kg

65036lb

18.4

2.15

m7ft1in

2.66

m8ft9in

2.67

m8ft9in

1.65

m5ft5in

0.57

m1ft11

in5.16

m16

ft11

in3.32

m10

ft11

in2.08

m6ft10

in3.12

m10

ft3in

3.12

m10

ft3in

10.49m

34ft5in

11.53


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Table2.4-G

roundClearance—

ARAircraftModel

WEIGHT

CG(%MAC)

NOSE

(A)

FOR-

WARD

SERVICE

DOOR

(B)

FOR-

WARD

PASSEN-

GER

DOOR

(C)

FOR-

WARD

CARG

ODO

OR

(D)

NACELLE

(E)

WINGLET

(F)

EMER-

GENCY

EXIT

(G)

AFT

CARG

ODO

OR

(H)

AFT

SERVICE

DOOR

(J)

AFT

PASSEN-

GER

DOOR

(K)

VERTI-

CAL

TAIL

(L)

TAIL

SKID

ANGU-

LAR

CLEAR-

ANCE

(DEG

)(M)

52450kg

115632

lb11.3

2.07

m6ft9in

2.58

m8ft5in

2.59

m8ft6in

1.57

m5ft2

in0.48

m1ft7in

5.06

m16

ft7in

3.23

m10

ft7in

1.98

m6ft6in

3.01

m9ft11

in3.01

m9ft11

in10.38m

34ft1in

11.08

52450kg

115632

lb31.0

2.15

m7ft1in

2.64

m8ft8in

2.65

m8ft8in

1.62

m5ft4in

0.49

m1ft7in

5.03

m16

ft6in

3.23

m10

ft7in

1.93

m6ft4in

2.95

m9ft8in

2.95

m9ft8in

10.28m

33ft9in

10.77

52290kg

115280

lb11.3

2.07

m6ft9in

2.58

m8ft5in

2.59

m8ft6in

1.57

m5ft2in

0.48

m1ft7in

5.06

m16

ft7in

3.23

m10

ft7in

1.98

m6ft6in

3.01

m9ft11

in3.01

m9ft11

in10.38m

34ft1in

11.08

52290kg

115280

lb31.0

2.15

m7ft1in

2.64

m8ft8in

2.65

m8ft8in

1.61

m5ft3in

0.49

m1ft7in

5.03

m16

ft6in

3.23

m10

ft7in

1.93

m6ft4in

2.95

m9ft8in

2.95

m9ft8in

10.28m

33ft9in

10.78

45800kg

100972

lb7.0

2.07

m6ft9in

2.59

m8ft6in

2.59

m8ft6in

1.58

m5ft2in

0.50

m1ft8in

5.09

m16

ft8in

3.25

m10

ft8in

2.00

m6ft7in

3.05

m10

ft3.05

m10

ft10.43m

34ft3in

11.25

45800kg

100972

lb31.0

2.17

m7ft2in

2.65

m8ft8in

2.67

m8ft9in

1.63

m5ft4in

0.51

m1ft8in

5.05

m16

ft7in

3.25

m10

ft8in

1.95

m6ft5in

2.97

m9ft9in

2.97

m9ft9in

10.31m

33ft10

in10.87

42600kg

93917lb

7.0

2.08

m6ft9in

2.59

m8ft6in

2.60

m8ft9in

1.58

m5ft2in

0.51

m1ft8in

5.10

m16

ft9in

3.26

m10

ft8in

2.02

m6ft8in

3.06

m10

ft3.06

m10

ft10.45m

34ft3in

11.31

42600kg

93917lb

31.0

2.18

m7ft2in

2.67

m8ft9in

2.67

m8ft9

in1.64

m5ft5in

0.52

m1ft8in

5.06

m16

ft7in

3.26

m10

ft8in

1.96

m6ft5in

2.98

m9ft9in

2.98

m9ft9in

10.32m

33ft10

in10.92

29500kg

65036lb

18.4

2.15

m7ft1in

2.66

m8ft9in

2.67

m8ft9in

1.65

m5ft5in

0.57

m1ft11

in5.16

m16

ft11

in3.32

m10

ft11

in2.08

m6ft10

in3.12

m10

ft3in

3.12

m10

ft3in

10.49m

34ft5in

11.53


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2.4. INTERIOR ARRANGEMENTS

The interior arrangement provides accommodation for two pilots, one observer, three flight attendants,and 108 passengers in 32 in pitch standard configuration. One additional flight attendant seat isavailable as an option.


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3 4 5

8

9

3 4

6 1 2

10

1 7

52

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

3

3

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

8

1.82 m(5 ft 11 in.)

1.86 m(6 ft 4 in.)

0.90 m(2 ft 11.4 in.)

0.87 m(2 ft 10 in.)

0.78 m(2 ft 6.7 in.)

8 − CARGO COMPARTMENT

1.00 m(3 ft 11.06 in.)

0.79 m(2 ft 7.1 in.)

5.72 m(18 ft 9.2 in.)

8.64 m(28 ft 4.16 in.)

5.95 m(19 ft 6.3 in.)

8.8 m(28 ft 10.5 in.)

EM17

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2 − FWD RH LAVATORY

6 − AIRSTAIRS WARDROBE

32.05 m (105 ft 1.8 in)

25.66 m (906.17 ft )

Interior ArrangementsFigure 2.3


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2.4.1. Passenger Cabin

The passenger cabin accommodates 108 passengers in 27 double seats on both sides.As an option, the passenger cabin is also provided with some double first-class seats on the RH sideand some single first-class seats on the LH side.The main dimensions of passenger cabin are presented below:

• Height - 2.00 m (6 ft 7 in)

• Width - 2.74 m (9 ft)

• Aisle wide - 0.49 m (1 ft 7 in)

• Pitch - 0.82 m (32 in)

2.4.2. Cargo Compartments

Two cargo compartments are available, located underfloor, one forward of the wing, and another aft ofthe wing.The cargo compartments comply with the FAR-25/JAR-25/RBHA-25 “class C” compartment classifica-tion.The table below contain the capacity for the cargo compartment:

Table 2.5 - Capacity for the Cargo CompartmentCARGO COMPARTMENT LOADING VOLUME

FWD [1] 1900 kg (4188 lb) 12.71 m3 (448.85 ft3)Aft 1800 kg (3968 lb) 12.95 m3 (457.32 ft3)Total 3700 kg (8156 lb) 25.66 m3 (906.17 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 - to avoid damage due to cargo shifting (two for each cargo compartments).Also, there are provisions for two extra vertical nets in the forward cargo compartment and one in theaft cargo compartment;

• 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, which avoids harm to the flight crew.The cockpit is separated from the passenger cabin by a bulkhead with a lockable door. The cockpit dooris provided with lockable means operable only from the cockpit side, spy hole and escape mechanismon 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

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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

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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

0.87 m(2 ft 10 in.)

0.78 m(2 ft 6.7 in.)

1.36 m(4 ft 5.5 in.)

0.90 m(2 ft 11.4 in.)

1.82 m(5 ft 11.6 in.)

1.10 m(3 ft 7.3 in.)

0.99 m(3 ft 3 in.)

0.63 m(2 ft 0.8 in.)

0.63 m(2 ft 0.8 in.)

0.75 m(2 ft 6.7 in.)

SEE FIGURE 2.2FOR HEIGHT ABOVEGROUND

EM17

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NOTE: FOR DIMENSIONS OF ALL DOORS,CONSIDER THAT AIRCRAFT IS IN OPERATION,THAT IS, EQUIPPED WITH DOOR LININGS ANDDOOR SURROUNDS.

0.91 m(2 ft 11.8 in.)

1.71 m(5 ft 7.3 in.)

1.37 m(4 ft 5.9 in.)

0.51 m(1 ft 8.1 in.)

0.51 m(1 ft 8.1 in.)

0.61 m(2 ft)

Door DimensionsFigure 2.6


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EFFECTIVITY: ALL Section 2Page 2-15 / 16

Oct 07/08

4. GROUND MANEUVERING4.1. GENERAL INFORMATION

This section provides the aircraft turning capability and maneuvering characteristics. To facilitate thepresentation, these data have been determined from theoretical limits imposed by the geometry of theaircraft.As such, they reflect the turning capability of the aircraft in favorable operating circumstances. Thesedata should be used only as guidelines for the method of determination of 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 constantswithin 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 using airline priorto the layout planning.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 baysdimensions.

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 that the maximum nose landing gear steering angle is 76 degrees left andright.

• Data on the minimum width of the pavement for a 180° turn.


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76°

R = 18.61 m(61 ft 1 in)

R = 21.90 m(71 ft 10 in)

R = 6.66 m(21 ft 10 in)

R = 19.13 m(62 ft 9 in)

R = 15.10 m(49 ft 7 in)

R = 7.29 m(23 ft 11 in)

R = 15.39 m(50 ft 6 in)

22.68 m(74 ft 5 in)RUNWAYMINIMUM

WIDTH

ACTUAL OPERATING DATA MAY BE GREATER THAN VALUES SHOWN SINCE TIRE SLIPPAGE IS NOT CONSIDERED IN THESE CALCULATIONS.

NOTE:

1

1

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0400

15B.

DG

N

THEORETICAL CENTER OF TURN FOR MINIMUN RADIUS.SHOWS CONTINUOUS TURNING WITH ENGINE THRUST AS REQUIRED.NO DIFFERENTIAL BRAKING.

Turning Radii - No Slip AngleFigure 4.1


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4.3. MINIMUM TURNING RADII

R = 6.66 m(21 ft 10 in)

R = 15.10 m(49 ft 7 in)

R 6

R 5

R 3

R 1

R 2

R 4

76°

35°40°

45°50°

55°60°

65°70°

R 1STEERING

STEEL R 2 R 3OUTBOARD GEAR

R 4 R 5RIGHT WINGLET

R 6RIGHT TAILTIP

35°40°45°

55°50°

60°65°70°76°

NOSE NOSE GEAR INBOARD GEAR

28.26 m (92 ft 9 in)25.75 m (84 ft 6 in)23.90 m (78 ft 5 in)

22.50 m (73 ft 10 in)21.44 m (70 ft 4 in)20.62 m (67 ft 8 in)20.00 m (65 ft 7 in)19.52 m (64 ft 1 in)19.13 m (62 ft 9 in)

21.06 m (69 ft 1 in)19.45 m (63 ft 10 in)18.20 m (59 ft 9 in)17.23 m (56 ft 6 in)

15.89 m (52 ft 2 in)15.39 m (50 ft 6 in)


10.50 m (34 ft 5 in)8.99 m (29 ft 6 in)

7.29 m (23 ft 11 in)

17.52 m (57 ft 6 in)

11.18 m (36 ft 8 in)

6.75 m (22 ft 2 in)4.93 m (16 ft 2 in)

3.29 m (10 ft 10 in)1.78 m (5 ft 10 in)

29.50 m (96 ft 9 in)

25.13 m (82 ft 5 in)23.34 m (76 ft 7 in)21.73 m (71 ft 4 in)20.25 m (66 ft 5 in)18.61 m (61 ft 1 in)


25.92 m (85 ft)23.25 m (75 ft 11 in)

16.47 m (54 ft)


14.02 m (46 ft)

8.80 m (28 ft 10 in)

0.08 m (3 in)

35.77 m (117 ft 4 in)32.31 m (106 ft)

27.15 m (89 ft 1 in)

33.51 m (109 ft 11 in)30.75 m (100 ft 11 in)28.62 m (93 ft 11 in)26.94 m (88 ft 5 in)

25.57 m (83 ft 11 in)

21.90 m (71 ft 10 in)

22.68 m(74 ft 5 in)RUNWAYMINIMUM

WIDTH

NOTE:

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DATA PRESENTED IS BASED ON THEORETICAL CALCULATIONS.ACTUAL OPERATING DATA MAY BE GREATER THAN SHOWN SINCE TIRE SLIPPAGE IS NOT CONSIDERED IN THESE CALCULATIONS.

Minimum Turning RadiusFigure 4.2


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4.4. VISIBILITY FROM COCKPIT

REF. GROUND (BOW)

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°

0.53 m(1 ft 9 in.)

0.53 m(1 ft 9 in.)

15°

0.75 m(2 ft 6 in.)

14.58 m(47 ft 10 in.)

27.8°

C

3.91 m(12 ft 10 in.)

2.92 m(9 ft 7 in.)

PILOT’S EYE POSITION

L FUS HOR

0.53 m(1 ft 9 in.) PILOT’S EYE POSITION

EM17

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0400

10.D

GN

VISUAL ANGLE IN PLANEPARALLEL TO LONGITUDINALAXIS THROUGH PILOT’S EYEPOSITION

Visibility from Cockpit in Static PositionFigure 4.3


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EFFECTIVITY: ALL Section 4Page 4-4May 11/07

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

CODENUMBER

AIRCRAFT REFERENCEFIELD LENGTH

CODELETTER WING SPAN OUTER MAIN LANDING

GEAR WHEEL 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)

2 800 m (2624 ft 8 in) up to1200 m (3937 ft) B 15 m (49 ft 3 in) to

24 m (78 ft 9 in)4.5 m (14 ft 9 in) to6 m (19 ft 8 in)

3 1200 m (3937 ft) up to1800 m (5905 ft 6 in) C 24 m (78 ft 9 in) to

36 m (118 ft 1 in)6 m (19 ft 8 in) to9 m (29 ft 6 in)

4 1800 m(5905 ft 6 in) and over D 36 m (118 ft 1 in) to

52 m (170 ft 7 in)9 m (29 ft 6 in) to14 m (45 ft 11 in)

5 _ E 52 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 195STD and 195LR is 3C and thereference code for the EMBRAER 195AR is 4C.

NOTE:• Classification considering CF34-10E7 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 be not less than 30 m (98 ft 5 in);The width of a taxiway should be not 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 taxiwaycentre 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 shouldnot be less than 15 m (49 ft 3 in).

• For reference code 4C the limits are:The width of a runway should be not less than 45 m (147 ft 7.6 in);


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The width of a taxiway should be not 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 taxiwaycentre 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 shouldnot be less than 15 m (49 ft 3 in).


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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.)

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More than 90° Turn - Runway to TaxiwayFigure 4.4


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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°

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90° Turn - Runway to TaxiwayFigure 4.5


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NOTE:


15 m(49 ft 2 in.)

15 m(49 ft 2 in.)

100 ft Radius(30 m)

90°


3 m(9 ft 10 in.)

EM17

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0400

19A.

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90° Turn - Taxiway to TaxiwayFigure 4.6


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4.6. RUNWAY HOLDING APRON

75 m(246 ft)



30 m(98 ft 5 in.)

MINIMUMCLEARANCES

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

TAXIWAY

EM17

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0400

20A.

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Runway Holding BayFigure 4.7


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5. TERMINAL SERVICINGDuring turnaround at the air terminal, certain services must be performed on aircraft, usually within agiven 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 equipments 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

SERVICING ARRANGEMENT

01 − PASSENGER STAIRS02 − BAGGAGE LOADER03 − BAGGAGE / CARGO04 − GALLEY SERVICE05 − FUEL SERVICE06 − POTABLE WATER07 − LAVATORY SERVICE08 − PASSENGER BRIDGE

110

100

LEN

GTH

− ft

90

80

70

60

50

40

30

20

10

00

0

5

10

15

20

25

30

LEN

GTH

− m

0 10 20 30 40 50 60 70 80 90 100 110 120LENGTH − ft

5 10 15 20 25 30 35 40

130

45

140

LENGTH − m

3

6

8

4

3

5

7

422

1

EM17

0APM

0500

15A.

DG

N

Aircraft Servicing Arrangement With Passenger BridgeFigure 5.1


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SERVICING ARRANGEMENT

110

100

LEN

GTH

− ft

90

80

70

60

50

40

30

20

10

00

0

5

10

15

20

25

30

LEN

GTH

− m

0 10 20 30 40 50 60 70 80 90 100 110 120LENGTH − ft

5 10 15 20 25 30 35 40

130

45

140

LENGTH − m

3

6

1

4

3

5

7

422

1

01 − PASSENGER STAIRS02 − BAGGAGE LOADER03 − BAGGAGE / CARGO04 − GALLEY SERVICE05 − FUEL SERVICE06 − POTABLE WATER07 − LAVATORY SERVICE08 − AIR CONDITIONING09 − PNEUMATIC STARTER

98

EM17

0APM

0500

16A.

DG

N

Aircraft Servicing Arrangement With Passenger StairsFigure 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 performing servicing on 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)

FWD BAGGAGE/CARGO LOAD

AIRCRAFTSERVICING

FUEL SERVICE

POTABLE WATER SERVICE

TOILET SERVICE

TRUCK POSITIONING/REMOVAL/SETTINGS

1 3 7 9 11 13 17 19

THIS DATA ILUSTRATES THE GENERAL SCOPE AND TASKS INVOLVINGAIRPORT TERMINAL OPERATIONS.AIRLINE PARTICULAR PRACTICES AND OPERATING EXPERIENCE WILLRESULT IN DIFFERENT SEQUENCES AND INTERVALS.

GALLEY SERVICING−AFT

AFT BAGGAGE/CARGO LOAD

PAXSERVICES

1,0

GALLEY SERVICING−FWD

PASSENGERS DEPLANE 4.5

AIRPLANE INTERIOR SERVICES

PASSENGERS ENPLANE

6.8

6.8

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

11.7

6.9

7.2

0,5

4.2

4.4

LEGEND:

NOTE:

7,0

7,0

BRIDGE / STAIRS POSITIONING

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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

4

14

21

5

3

6

9 12

21 20

7 8

10

13

1516

18

11

1719

ITEM DESCRIPTION COORD. Y(mm)

COORD. Z(mm)

COORD. X(mm)

HEIGHTABOVE

GROUND(mm)

NOTE:

1827.36

123456789

10111213141516171819202122

−543.757803.787774.46 −310.92

−936.13 −1262.714136.97 −951.46 −1279.29

0.00−1979.71−1952.83−1744.672930.25

−1602.04−808.01−329.37 −1178.74−471.73 −605.30−449.47 −585.54

6562.14 1159.87 −961.05−691.60 −1611.45

−1611.45526.50−1602.04808.01−991.80349.20−590.09519.15

0.0057.25

−1339.534146.90

2852.853093.47

GRAVITY REFUELING PORT (LH)GRAVITY REFUELING PORT (RH)

18745.47 −7646.75 −308.24 3101.081844.50

4125.04 −2856.21 250.531333.271367.611667.43

18890.21 2970.00 −2977.05 435.84−2970.00

1853.302469.803096.183118.862195.821767.301767.301853.302675.813110.92

EXTERNAL POWER SUPPLY 28 VDC / 400A

EXTERNAL POWER SUPPLY 115 VAC −810.70 1767.34

22

THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 29800 kg (CG FWD 4.0% CMA)

FORWARD RAMP HEADSET

PRESSURE REFUELING PANEL

STEERING SWITCH DISENGAGEWHEEL JACK POINT − NLGAIR COND. GROUND CONNECTION

GROUNDING POINT (ELECTRICAL)

WATER SERVICING PANEL

WASTE SERVICING PANEL

HYD. SYS # 3 SERVICE PANEL

AFT RAMP HEADSETOXYGEN SERVICING PANEL / BOTTLE

ENGINE AIR STARTING (LOW PRESSURE UNIT)

WHEEL JACK POINT− MLG (RH)

WHEEL JACK POINT− MLG (LH)HYD. SYS # 1 SERVICE PANEL

FUEL TANK DRAIN VALVE (LH)FUEL TANK DRAIN VALVE (RH)HYD. SYS # 2 SERVICE PANEL

EM17

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0500

18E.

DG

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18129.75

18507.84

14081.3214441.8118865.08

18890.21 −2977.05 435.8420951.9630274.8332834.6532975.26

17257.70

20951.96

32811.86

17289.45

31197.01

4164.44

Ground Servicing ConnectionsFigure 5.4


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4

14

21

5

3

6

9 12

21 20

7 8

10

13

1516

18

11

1719

ITEM DESCRIPTION COORD. Y(mm)

COORD. Z(mm)

COORD. X(mm)

HEIGHTABOVE

GROUND(mm)

NOTE:

1924.81

123456789

10111213141516171819202122

−543.757803.787774.46 −310.92

−936.13 −1262.714136.97 −951.46 −1279.29

0.00−1979.71−1952.83−1744.672930.25

−1602.04−808.01−329.37 −1178.74−471.73 −605.30−449.47 −585.54

6562.14 1159.87 −961.05−691.60 −1611.45

−1611.45526.50−1602.04808.01−991.80349.20−590.09519.15

0.0057.25

−1339.534146.90

2841.203078.90

GRAVITY REFUELING PORT (LH)GRAVITY REFUELING PORT (RH)

18745.47 −7646.75 −308.24 3084.651941.74

4125.04 −2856.21 250.661353.031384.561649.89

18890.21 2970.00 −2977.05 436.07−2970.00

1819.482363.292969.772991.362274.381762.311762.721819.482562.132984.69

EXTERNAL POWER SUPPLY 28 VDC / 400A

EXTERNAL POWER SUPPLY 115 VAC −810.70 1864.70

22

FORWARD RAMP HEADSET

PRESSURE REFUELING PANEL

STEERING SWITCH DISENGAGEWHEEL JACK POINT − NLGAIR COND. GROUND CONNECTION

GROUNDING POINT (ELECTRICAL)

WATER SERVICING PANEL


HYD. SYS # 3 SERVICE PANEL

AFT RAMP HEADSETOXYGEN SERVICING PANEL / BOTTLE

ENGINE AIR STARTING (LOW PRESSURE UNIT)

WHEEL JACK POINT− MLG (RH)

WHEEL JACK POINT− MLG (LH)HYD. SYS # 1 SERVICE PANEL

FUEL TANK DRAIN VALVE (LH)FUEL TANK DRAIN VALVE (RH)HYD. SYS # 2 SERVICE PANEL

EM17

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0500

25A.

DG

N

18129.75

18507.84

14081.3214441.8118865.08

18890.21 −2977.05 436.0720951.9630274.8332834.6532975.26

17257.70

20951.96

32811.86

17289.45

THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 29800 kg (CG REAR 31.0% CMA)

4164.44

31197.01

Ground Servicing ConnectionsFigure 5.5


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5.5. ENGINE STARTING PNEUMATIC REQUIREMENTS

EM17

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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

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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

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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 within a given time at ambient conditions.

• The air conditioning requirements for heating and cooling to maintain a constant cabin air tempera-ture using low-pressure conditioned air. This conditioned air is supplied through a ground airconnection directly to the passenger cabin, bypassing the air cycle machines.


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LEGEND:

CABIN AT 24°C (74°F), 97 OCCUPANTS,BRIGHT DAY (SOLAR IRRADIATION),39°C (103°F) DAY.

SAME AS 1 EXCEPT CABIN 27°C (81°F)

SAME AS 1 EXCEPT CABIN 24°C (74°F),NO CABIN OCCUPANTS, FOUR CREWSMEMBERS ONLY.

CABIN AT 24°C (74°F),NO CABIN OCCUPANTS, FOUR CREWMEMBERS ONLY, OVERCAST DAY(NO SOLAR IRRADIATION),40°C (40°F) DAY.

SAME AS 4 EXCEPT −29°C (−20°F) DAY.

SAME AS 4 EXCEPT −18°C (−0°F) DAY.

NOTES:MAXIMUM ALLOWABLE TEMPERATURE 88°C (190°F)(UPPER LIMIT DURING PULL UP OPERATION). MAXIMUM ALLOWABLE PRESSURE AT GROUNDCONNECTION 406mmH20 (16 INCHES OF WATER).

1

2

3

4

5

6

1

5

10

12

16

TOTA

L AI

RFL

OW

1

2

3

4

56

0 0

20

40

60

80

10

20

30

40

100

50

120

14060

55

150

−5 0 5 10 15 20 25 30 35 40 45 50 55 [°C]

[°F]

PRE−CONDITIONED AIRFLOW REQUIREMENTS

PRES

SUR

E AT

GR

OU

ND

CO

NN

ECTI

ON

(IN

CH

ES O

F W

ATER

)

AIR SUPPLY TEMPERATURE

5030 70 90 110 120

[lbm/min]

[kg/min]

EM17

0MFE

P040

070A

.DG

N

Preconditioned Airflow RequirementsFigure 5.9


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5.8. GROUND TOWING REQUIREMENTS

NO

TES:

− 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

1000

(220

4)20

00(4

409)

3000

(661

4)40

00(8

818)

5000

(110

23)

060

00(1

3227

)70

00(1

5432

)N

UM

BER

OF

ENG

INES

BAC

KIN

G A

GAI

NST

IDLE

TH

RU

ST

10

12

34

02

PER

CEN

T SL

OPE

(%)

5

1000

(220

4)

3000

(661

4)

2000

(440

9) 0

TOWBAR PULL − kg (lb)

4000

(881

8)

5000

(110

23)

DRY CONCRETE OR

ASPHALT =0.8

WET ASPHALT =0.75

WET CONCRETE =0

.57

SNOW

CHAI

NS

=0.45

HARD

SNO

W

=0.

2

ICE

=

0.05

REFERENCE LINE

4700

0 (10

3617

)

4500

0 (99

208)

4300

0 (94

799)

4100

0 (90

390)

3900

0 (85

980)

3500

0 (77

162)

3300

0 (7

2753

)

3100

0 (6

8343

)

2900

0 (6

3934

)

3700

0 (81

571)

4900

0 (10

8027

)

5100

0 (11

2436

)

5300

0 (11

6845

)

5500

0 (12

1254

)

AIRCRAFT G

ROSS WEIG

HT − kg

(lb)

GRO

UND

TO

WIN

G R

EQUI

REM

ENTS

EM17

0MFE

P040

066B

.DG

NTOTA

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

ABCDEF

VELOCITY m/s (ft/s)MAX = 482.5 (1583)

15.2 (50)30.5 (100)60.9 (200)121.9 (400)243.8 (800)396.2 (1300)

NOTE:EXHAUST VELOCITY CONTOURS INCLUDE WORST CASE 20 kn HEADWIND WITH GROUND EFFECTS.

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

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

EM17

0MFE

P020

014A

.DG

N

TAKEOFF POWER, SEA LEVEL, Tamb = ISA +20°C, FNIN1 = 84347 N (18962 lbf)

Jet Wake Velocity Profile - Takeoff PowerFigure 6.1


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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


ABCDE

°F100150200400900

TOTAL TEMPERATUREMAX = 689°C (1273°F)

°C386693204582

NOTE:EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND. EM

170M

FEP0

2001

6B.D

GN

TAKEOFF POWER, SEA LEVEL, Tamb = ISA +20°C, FNIN1 = 84347 N (18962 lbf)

Jet Wake Temperature Profile - Takeoff PowerFigure 6.2


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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


VELOCITY m/s (ft/s)MAX = 89.0 (292)

(50)(100)(150)(190)

15.230.545.757.9

NOTE:EXHAUST VELOCITY CONTOURS INCLUDE WORST CASE 20 kn HEADWIND WITH GROUND EFFECTS. EM

170M

FEP0

2001

5A.D

GN

GROUND IDLE, SEA LEVEL, Tamb = ISA +15°C, FNIN1 = 2558 N (575 lbf)

Jet Wake Velocity Profile - Ground IdleFigure 6.3


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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

NOTE:EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND. EM

170M

FEP0

2001

7A.D

GN

GROUND IDLE, SEA LEVEL, Tamb = ISA +15°C, FNIN1 = 2558 N (575 lbf)

Jet Wake Temperature Profile - Ground IdleFigure 6.4


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1614

12

10

8

6

4

20

0 4 8 12 16 20 24 28 32 36 40 44 48 52 56 600

1

2

3

4

5

0 2 4 6 8 10 12 14 16 18

28

24

16

12

8

4

00 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60

18161412108640 2

0

1

2

3

4

5

6

7

8

E D C

B

A

HEI

GH

T AB

OVE

GR

OU

ND

PLA

NE,

Fee

t

Met

ers


Meters

Met

ers


Meters

NOTE:

DIS

TAN

CE

FRO

M A

IRPL

ANE

CL −

Feet

EXHAUST VELOCITY CONTOURS INCLUDE WORST CASE 20 knot HEADWIND WITH GROUND EFFECTS.

ABCDE

50100200300450

VELOCITY (ft/sec)MAX = 497

BREAKAWAY POWER, SEA LEVEL, Tamb = ISA +0°C, FNIN1 = 40660 N (9139 lbf)

E D C

B

A

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08A.

DG

N

Jet Wake Velocity Profile - Breakaway PowerFigure 6.5Sheet 1


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12

10

8

6

50

40

30

20

10

0

50

40

30

20

10

0

−10

−20

−30

−40

−50

12

10

8

6

4

0

−4

−6

−8

−10

−12

0 20 40 60 80 100 120 140 160 200 220 240

0 10 20 30 40 50 60 70

180


HEI

GH

T AB

OVE

GR

OU

ND

PLA

NE −

Feet

Met

ers

AXIAL DISTANCE BEHIND AIRPLANE

(Meters)

Feet

DIS

TAN

CE

FRO

M A

IRPL

ANE

CL −

Feet

75 MPH100 MPH

50 MPH

35 MPH

EM17

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0600

10A.

DG

N

100 MPH75 MPH

50 MPH

35 MPH

CL AIRPLANE

4

2

0

2

−2

Jet Wake Velocity Profile - Breakaway PowerFigure 6.5Sheet 2


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16

14

12

10

8

6

4

2

00 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60

0

1

2

3

4

5

0 2 4 6 8 10 12 14 16 18

AB

CDE

28

24

16

12

8

4

00 4 8 12 16 20 24 28 32 36 40 44 48 52 56 60

18161412108640 2

0

1

2

3

4

5

6

7

8

E D C

B A20

TOTAL TEMPERATUREMAX = 697 °F (369 °C)

°F °C

NOTE:

100150200400650

386693

204343

ABCDE

EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 knot HEADWIND.


Meters

Meters


Met

ers

HEI

GH

T AB

OVE

GR

OU

ND

PLA

NE −

Feet

Met

ers

EM17

0APM

0600

09A.

DG

N

DIS

TAN

CE

FRO

M A

IRPL

ANE

CL −

Feet


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

ENGINE EXHAUST HAZARD AREAVELOCITY = 65 mph OR GREATER = 29.0 m/s (95.3 ft/s)

NOTE:

2

2

1

144 m(474 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.

R= 5.23 m(17 ft)

1.9 m(6.2 ft)

EM17

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0600

04B.

DG

N

NO ACCESS TO ENGINE ACCESSORIES AT TAKEOFF POWER.

TAKEOFF POWER, SEA LEVEL, Tamb = ISA +15° C, FNIN1 = 91184 N (20499 lbf)

Hazard Areas - Takeoff PowerFigure 6.7


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17 m(55 ft)

1.0 m(3.3 ft)R=2.6 m

(8.5 ft)

ENGINE EXHAUST HAZARD AREAVELOCITY = 65 mph OR GREATER = 29.0 m/s (95.3 ft/s)

2

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.

EM17

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0600

05B.

DG

N

GROUND IDLE, SEA LEVEL, Tamb = ISA+15° C, FNIN1 = 3768 N (847 lbf)

Hazard Areas - Ground IdleFigure 6.8


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May 11/07

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

NOSE GEAR TIRE PRESSURE

MAIN GEAR TIRE SIZE

MAIN GEAR TIRE PRESSURE

0.87 m

14.64 m0.40 m

(1 ft 4 in.)

(19 ft 6 in.)5.94 m

AIRCRAFT MODELSLRSTD

(2 ft 10 in.)

48950 kg(107916 lb)

50950 kg

24 x 7.7 16PR

H41 x 16−20 22PR

(154 − 0/+10 psi)10.83 − 0/+0.7 kg/cm ²

8.56 − 0/+0.7 kg/cm ²(126 − 0/+10 psi)

52450 kg(115632 lb)(112326 lb)

(48 ft 0.4 in.)

EM17

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57B.

DG

N

AR

FootprintFigure 7.1


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7.3. MAXIMUM PAVEMENT LOADS

MODEL STATIC AT MOSTFORWARD C.G.

NGV MGV (PER STRUT) (PER STRUT)H

2

6006 kg(13241 lb)

6102 kg(13453 lb)

MAXIMUMRAMP

WEIGHT

8901 kg(19623 lb)

8889 kg(19597 lb)

23874 kg(52633 lb)

22936 kg(50565 lb)

6946 kg(15313 lb)

6675 kg(14716 lb)

16091 kg(35475 lb)

15451 kg(34064 lb)

LR

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

NG

MG H=MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING

NOTE: ALL LOADS CALCULATED USING AIRCRAFT MAXIMUM RAMP WEIGHT

V =MAXIMUM VERTICAL MAIN GEAR GROUND LOAD AT MOST FORWARD C.G.

LEGEND: V =MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST FORWARD C.G.

VNG VMG

H

48950 kg(107916 lb)

5962 kg(13144 lb)

8940 kg(19709 lb)

24578 kg(54185 lb)

7155 kg(15774 lb)

16570 kg(36531 lb)

52450 kg(115632 lb)

50950 kg(112326 lb)

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DG

N

AR

Maximum Pavement LoadsFigure 7.2


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7.4. LANDING GEAR LOADING ON PAVEMENT

54000

86 88 90 92 94

52450

90000

80000

70000

60000

50000

100000

110000

90000

80000

70000

60000

50000

WEI

GH

T O

N M

AIN

LAN

DIN

G G

EAR

(kg)

WEI

GH

T O

N M

AIN

LAN

DIN

G G

EAR

(lb)

PERCENT OF WEIGHT ON MAIN GEAR − (%)

AIR

CR

AFT

GR

OSS

WEI

GH

T −

(kg)

100000

110000

WEI

GH

T O

N M

AIN

LAN

DIN

G G

EAR

(lb)48950

50950

90000

80000

70000

60000

50000

100000

110000

90000

80000

70000

60000

50000

WEI

GH

T O

N M

AIN

LAN

DIN

G G

EAR

(kg)

WEI

GH

T O

N M

AIN

LAN

DIN

G G

EAR

(lb)

PERCENT OF WEIGHT ON MAIN GEAR − (%)

AIR

CR

AFT

GR

OSS

WEI

GH

T −

(kg)

100000

110000

WEI

GH

T O

N M

AIN

LAN

DIN

G G

EAR

(lb)

47500

52000

50000

48000

46000

44000

42000

40000

38000

36000

34000

32000

30000

28000

26000

24000

45000

42500

40000

37500

35000

32500

29500

95 96939187 89

% MAC31.0%11.3%

LEGEND

LR VERSIONSTD VERSION

AR VERSION

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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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10 20 309876543

FLEXIBLE PAVEMENT THICKNESS − in

FLEXIBLE PAVEMENT THICKNESS − cm20 30 40 50 60 708 9 10

10 20 309876543

10000 COVERAGES(USED FOR ACNCALCULATIONS)

ANNUALDEPARTURES

1200

3200

6000

15000

25000

WEIGHT ON MAINLANDING GEAR

(kg) (lb)47659 10513744909 9907242712 9422540596 8955727775 61274

NOTES: 2

SUBGRADE STRENGHT − CBR MODEL

TIRE SIZE: H41 x 16−20 22 PRTIRE PRESSURE: 10.62 kgf/cm (154 psi)

EM17

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61A.

DG

N

26650 58793

Flexible Pavement Requirements - US Army Corps of Engineers Design MethodFigure 7.4


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EFFECTIVITY: EMBRAER 195 LR ACFT MODEL Section 7Page 7-6May 11/07

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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NOTES:EQUIVALENT SINGLE WHEEL LOADSARE DERIVED BY METHODS SHOWNIN ICAO AERODROME MANUAL.PART 2, PAR. 4.1.3

EQU

IVAL

ENT

SIN

GLE

WH

EEL

LOAD

− (k

g)

LCN − LOAD CLASSIFICATION NUMBER

201053 30

EQU

IVAL

ENT

SIN

GLE

WH

EEL

LOAD

− (l

b)

8000

6000

10000

12000

14000

16000

180001900020000

6 7 8 9 30 40 50 60 70 8090 100

EQU

IVAL

ENT

SIN

GLE

WH

EEL

LOAD

− (l

b)

1010000

50000

20

20000

30000

40000

2010 30 40 50 60 70 8090100

27775 (61274)

40596 (89557)44909 (99072)47659 (105137)

42712 (94225)


kg (lb)

NOTES: 2TIRE SIZE: H41x16−20 22PRTIRE PRESSURE: 10.62 kgf/cm (154 psi)

FLEXIBLE PAVEMENT THICKNESS − (cm)

FLEXIBLE PAVEMENT THICKNESS − (in.)

EM17

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26650 (58793)

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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k=550 lb/ink=300 lb/in

k=150 lb/ink=75 lb/in

RIGID PAVEMENT REQUIREMENTS

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:

47659 (105137)

44909 (99072)

42712 (94225)

40596 (89557)

27775 (61274)

2NOTES: TIRE SIZE: H41 x 16−20 22PRTIRE PRESSURE: 10.62 kgf/cm (154 psi) (UNLOADED)

EM17

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67A.

DG

N

26650 (58793)

0

5

10

15

20

25

30

35

40

45

50

0

5

10

15

20

25

30

35

40

45

50

WEIGHT ON MAIN LANDING GEAR − kg (lb)

700

600

500

400

300

200

100

0

18

16

14

12

10

8

6

4

2

0

PAVE

MEN

T TH

ICKN

ESS

(in.)

PAVE

MEN

T TH

ICKN

ESS

(cm

)

ALLO

WAB

LE W

OR

KIN

G S

TRES

S −

psi

ALLO

WAB

LE W

OR

KIN

G S

TRES

S −

kgf/c

m

20

MAXIMUM POSSIBLE MAIN−GEARLOAD AT MAXIMUM DESIGN RAMPWEIGHT AND AFT C.G.

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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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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4059

6 (89

557)44

909 (

9907

2)

2777

5 (61

274)

NOTES: 2TIRE SIZE: H41 x 16−20 22 PRTIRE PRESSURE: 10.62 kgf/cm (154 psi)

NOTES:EQUIVALENT SINGLE WHEEL LOADSARE DERIVED BY METHODS SHOWNIN ICAO AERODROME MANUAL.PART 2, PAR. 4.1.3

EQU

IVAL

ENT

SIN

GLE

WH

EEL

LOAD

− (k

g)

LCN − LOAD CLASSIFICATION NUMBER

RADIUS OF RELATIVE STIFFNESS − (in.)

RADIUS OF RELATIVE STIFFNESS − (cm)

8000

6000

10000

12000

14000

16000

5030

180001900020000

EQU

IVAL

ENT

SIN

GLE

WH

EEL

LOAD

− (l

b)

2010 30 40 50 60 70 8090100

100 200

60 70 80 9010000

50000

20000

30000

40000


kg (lb)

100 200 300 4005040EM

170A

PM07

0070

A.D

GN

2665

0 (58

793)

4765

9 (10

5137

)

4271

2 (94

225)

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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30

40000 42000 44000 46000 48000 50000 52000

NOTES: 2TIRE SIZE: H41 x 16−20 22 PR

35

88000 92000 96000 100000 104000 108000 112000

AIR

CR

AFT

CLA

SSIF

ICAT

ION

NU

MBE

R−A

CN

10

15

20

25

28000 30000 32000 34000 36000 38000

64000 68000 72000 76000 80000 84000

AIRCRAFT GROSS WEIGHT−lb

AIRCRAFT GROSS WEIGHT−kg

MAX

IMU

M R

AMP

WEI

GH

T

FLEXIBLE PAVEMENT SUBGRADE

SBGRADE STRENGTH ULTRA LOW − CBR=3%LOW − CBR=6%MEDIUM−CBR=10%HIGH−CBR=15%

TIRE PRESSURE: 10.62 kgf/cm (154 psi) (UNLOADED)

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DG

N50950

ACN For Flexible PavementFigure 7.10


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30

40000 42000 44000 46000 48000 50000 52000

35

88000 92000 96000 100000 104000 108000 112000

AIR

CR

AFT

CLA

SSIF

ICAT

ION

NU

MBE

R−A

CN

10

15

20

25

28000 30000 32000 34000 36000 38000

64000 68000 72000 76000 80000 84000

AIRCRAFT GROSS WEIGHT−lb

AIRCRAFT GROSS WEIGHT−kg

MAX

IMU

M R

AMP

WEI

GH

T

NOTES: 2TIRE SIZE: H41 x 16−20 22 PR

RIGID PAVEMENT SUBGRADE

ULTRA LOW−k=20 MN/m (75 lb/in )

LOW−k=40 MN/m (150 lb/in )

MEDIUM−k=80 MN/m (300 lb/in )

HIGH−k=150 MN/m (550 lb/in )

3 3

3

3

33

3

3

TIRE PRESSURE: 10.62 kgf/cm (154 psi) (UNLOADED)

EM17

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0700

76A.

DG

N

50950

ACN For Rigid PavementFigure 7.11


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EFFECTIVITY: EMBRAER 195 LR ACFT MODEL Section 7Page 7-17 / 18

May 11/07

8. POSSIBLE EMBRAER 195 DERIVATIVE AIRCRAFT8.1. NOT APPLICABLE


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Jul 28/06

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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1

7

25

6

14

10

10

1413

8

9

1111

3 4

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


POTABLE WATER SERVICING PANELOXYGEN REFILL / REPLACE BOTTLE

GROUNDING POINT (RIGHT MLG)PRESSURE REFUELING / DEFUELING

CARGO DOORMAIN LANDING GEAR

NOSE LANDING GEARPASSENGER DOOR

14 SERVICE DOOR

0

0 16 32 48 64

5 10 15 20 25 m

80 ft

WING SPAN:28.72 m

(94 ft 3 in.)EM

170A

PM09

0011

A.D

GN

13

12

Scale: 1 Inch Equals 32 FeetFigure 9.1


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ITEM DESCRIPTION

1

ITEM DESCRIPTION8

23

45

67

9101112

13









14 SERVICE DOOR

WING SPAN:28.72 m

(94 ft 3 in.)

0 5 10 15 20 25 m

0 16 32 48 64 80 ft

1

7

2 5

6

14

10

10

1413

89

1111

3 4

13

EM17

0APM

0900

12A.

DG

N

12



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ITEM DESCRIPTION

1

ITEM DESCRIPTION8

23

45

67

9101112

13









14 SERVICE DOOR

0 5 10 15 20 25 m

0 16 32 48 64 80 ft

WING SPAN:28.72 m

(94 ft 3 in.)

2 5

6 101413

3

84

9

11

11

17

14

1013

12

EM17

0APM

0900

13A.

DG

N



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ITEM DESCRIPTION

1

ITEM DESCRIPTION8

23

45

67

9101112

13









14 SERVICE DOOR

WING SPAN:28.72 m

(94 ft 3 in.)

0 5 10 15 20 25 m

160 32 6448 80 ft

2

13

6 10

14

5

11 11

89

43

107

14

12

113

EM17

0APM

0900

14A.

DG

N

Scale: 1 to 500Figure 9.4


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50 m

ITEM DESCRIPTION

1

ITEM DESCRIPTION8

23

45

67

9101112

13









14 SERVICE DOOR

0 5 10 15 20

160 32 6448 80 ft

WING SPAN:28.72 m

(94 ft 3 in.)

25

2 5

6 101413

17

3 4

14

1013

12

89

11

11

EM17

0APM

0900

15A.

DG

N

Scale: 1 to 1000Figure 9.5


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e195 Apto Plan

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