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AIRPORT PLANNINGMANUAL
APM-190115 AUGUST 2005
REVISION 8 - 06 OCTOBER 2011
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 © 2011 by Embraer S.A. All rights reserved.The information, technical data, designs and drawings in this document are proprietary information of
Embraer or third parties and shall not be used or disclosed to any third party nor copied or reproduced,whether in whole or in part, in any form or by any means whatsoever without the express written authorization of Embraer.
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TitleTRList
1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/072 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/07
SBList1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/062 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
List of Effective Pages
* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11
* 2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11Table of Contents
* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/112 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
List of Tables1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/072 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
List of Figures1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
* 2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/113 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/074 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
Section 11-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/06
* 1-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11
* 1-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/111-4 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
Section 22-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/062-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/062-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/052-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/062-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/072-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/052-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/052-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
* 2-14 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11Section 3
3-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/063-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/063-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
3-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-21 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/073-24 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
Section 44-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/054-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/074-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/074-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/054-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/074-10 Blank . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
Section 55-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
* 5-2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/115-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/055-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/055-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/055-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
* 5-9 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11
* 5-10 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11
* 5-11 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11
* 5-12 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11
* 5-13 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11
* 5-14 Blank (rev) . . . . . . . . . . . . . . . . . . Oct 06/11Section 6
6-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/056-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/056-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/08
AIRPORTPLANNING MANUAL
Pages revised or added by the current revision are indicated by an asterisk (*). Pages deleted by the currentrevision are indicated by * (del). Pages deleted by the previous revision are indicated by (del).
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6-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/056-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/056-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/076-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/076-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/106-12 Blank . . . . . . . . . . . . . . . . . . . . . . . . May 11/07
Section 77-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/057-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
* 7-3 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/117-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/057-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/057-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/107-18 Blank . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-19 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-20 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-21 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-22 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-23 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/067-24 Blank (del) . . . . . . . . . . . . . . . . . . Dec 18/06
Section 88-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/058-2 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
Section 99-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/059-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/059-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/059-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/059-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/059-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 15/05
AIRPORTPLANNING MANUAL
Pages revised or added by the current revision are indicated by an asterisk (*). Pages deleted by the currentrevision are indicated by * (del). Pages deleted by the previous revision are indicated by (del).
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TABLE OF CONTENTS
SECTION 1 - SCOPE
1. Scope .............................................................................................................................. 1-11.1. Purpose ........................................................................................................................... 1-11.2. Introduction ..................................................................................................................... 1-11.3. Abbreviations .................................................................................................................. 1-2
SECTION 2 - AIRCRAFT DESCRIPTION
2. Aircraft Description .......................................................................................................... 2-12.1. Aircraft Characteristics .................................................................................................... 2-12.2. General Aircraft Dimensions ............................................................................................ 2-22.3. Ground Clearances ......................................................................................................... 2-52.4. Interior Arrangements ...................................................................................................... 2-82.5. Passenger Cabin Cross Section ..................................................................................... 2-112.6. Lower Compartment Containers ...................................................................................... 2-132.7. Door Clearances ............................................................................................................. 2-14
SECTION 3 - AIRCRAFT PERFORMANCE
3. Aircraft Performance ....................................................................................................... 3-13.1. General Information ......................................................................................................... 3-13.2. Payload X Range ............................................................................................................ 3-23.3. Takeoff Field Lengths ...................................................................................................... 3-113.4. Landing Fields Lengths ................................................................................................... 3-20
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 ........................................................................ 5-105.7. Preconditioned Airflow Requirements .............................................................................. 5-125.8. Ground Towing Requirements ......................................................................................... 5-14
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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
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, US 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 190 DERIVATIVE AIRCRAFT
8. Possible EMBRAER 190 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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1. SCOPE
1.1. 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 Arrangement
ARRANGEMENTS 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.
• Queries concerning any printed material, including purchasing, copying, shipping and handling,complaints, or compliments may be addressed to:Technical Publications Distribution:Embraer S.A.Attention of: Technical Publications DepartmentP.O. BOX 8050CEP. 12.227-901- São José dos Campos - SP - BrazilPhone: (55 12) 3927-7517FAX: (55 12) 3927-7546http://www.embraer.come-mail: [email protected]
• For support regarding technical information contained in non-operational publication, please contact:Routine Issues: Contact Embraer Customer Support ServiceAOG Issues: Contact Embraer AOG group directly
• For Digital Technical Publications support:[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 APM
ACRONYMS AND ABBREVIATIONS DESCRIPTION°C Degree Celsius°F Degree Fahrenheit� LiterACN Aircraft Classification NumberAFM Airplane Flight ManualAOM Airplane Operations Manual
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Table 1.2 - List of Acronyms and Abbreviations used in the APM
ACRONYMS AND ABBREVIATIONS DESCRIPTIONAPM 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 RegulationsFWD 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 DESCRIPTION
2.1. 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 47790 kg (105359 lb);
• The LR aircraft model - MTOW 50300 kg (110892 lb);
• The AR aircraft model - MTOW 51800 kg (114199 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 47950 kg (105712 lb) 50460 kg (111245 lb) 51960 kg (114552 lb)MTOW 47790 kg (105359 lb) 50300 kg (110892 lb) 51800 kg (114199 lb)MLW 43000 kg (94799 lb) 44000 kg (97003 lb)
BOW [2] 27900 kg (61509 lb)MZFW 40800 kg (89949 lb) 40900 kg (90169 lb)
Maximum Payload [2] 12900 kg (28440 lb) 13000 kg (28660 lb)Maximum Seating
Capacity106 passengers
Maximum CargoVolume[3] 22.63 m3 (799.18 ft3)
UsableFuel [4]
13000 kg (28660 lb)16029 � (4234 gal.)
1. Applicable for standard models. For further information, refer to AFM and AOM.2. Typical 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 - 36.24 m (118 ft 11 in.)
2.2.2. Wing
• Reference area - 92.50 m2 (996 ft2)
• Reference aspect ratio - 8.1
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2.2.3. Fuselage
• Total Length - 36.24 m (118 ft 11 in.)
• Length of pressurized section - 29.08 m (95 ft 5 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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10.57 m(34 ft 8 in.)
EM
170A
PM
0200
11B
.DG
N
4.13 m(13 ft 6 in.)
24.57 m(80 ft 10 in.)
6.82 m(45 ft 4 in.)
13.81 m(45 ft 4 in.)
36.24 m(118 ft 11 in.)
27.60 m(90 ft 7 in.)
4.27 m(14 ft)
4.71 m(15 ft 5.4in.)
27.60 m(90 ft 7 in.)
12.08 m(39 ft 8 in.)
28.72 m(94 ft 3 in.)
5.94 m(19 ft 6 in.)
20.04 m(65 ft 9 in.)
General Aircraft DimensionsFigure 2.1
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2.3. GROUND CLEARANCES
B
C
D
E H K L
M
N
AFUSLG ANGLE (REF.)
F
G
J
EM
170M
FE
P02
0013
B.D
GN
Aircraft Ground ClearancesFigure 2.2
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Tabl
e2.
2-
Gro
und
Cle
aran
ce-
ST
DA
ircra
ftM
odel
WE
IGH
TC
G
(%M
AC
)
FU
S
AN
GLE
(DE
G)
(A)
NO
SE
(B)
FO
R-
WA
RD
SE
RV
ICE
DO
OR
(C)
FO
R-
WA
RD
PAS
SE
N-
GE
R
DO
OR
(D)
FO
R-
WA
RD
CA
RG
O
DO
OR
(E)
NA
-
CE
LLE
(F)
WIN
GLE
T
(G)
EM
ER
-
GE
NC
Y
EX
IT
(H)
AF
T
CA
RG
O
DO
OR
(J)
AF
T
SE
RV
ICE
DO
OR
(K)
AF
T
PAS
SE
N-
GE
R
DO
OR
(L)
VE
RT
I-
CA
L
TAIL
(M)
TAIL
SK
ID
AN
GU
-
LAR
CLE
AR
-
AN
CE
(DE
G)
(N)
4795
0kg
1057
12lb
5.6
-1.1
2.07
m
6ft
9in.
2.59
m
8ft
6in.
2.60
m
8ft
6in.
1.58
m
5ft2
in.
0.49
m
1ft
7in.
5.09
m
16ft
8in.
3.24
m
10ft
8in.
1.98
m
6ft
6in
.
3.02
m
9ft
11in
.
3.02
m
9ft
11in
.
10.4
0m
34ft2
in.
12.6
4795
0kg
1057
12lb
29.0
-0.8
2.15
m
7ft
2.65
m
8ft
8in.
2.66
m
8ft
9in.
1.62
m
5ft
4in
.
0.50
m
1ft
8in.
5.05
m
16ft
7in.
3.24
m
10ft
8in.
1.93
m
6ft
4in.
2.95
m
9ft
8in.
2.95
m
9ft
8in.
10.3
0m
33ft
9in.
12.3
4779
0kg
1053
59lb
5.6
-1.1
2.07
m
6ft
9in.
2.59
m
8ft
6in.
2.60
m
8ft
6in.
1.58
m
5ft2
in.
0.49
m
1ft
7in.
5.09
m
16ft
8in.
3.24
m
10ft
8in.
1.98
m
6ft
6in
.
3.02
m
9ft
11in
.
3.02
m
9ft
11in
.
10.4
0m
34ft
2in
.12
.6
4779
0kg
1053
59lb
29.0
-0.7
2.15
m
7ft
2.65
m
8ft
8in.
2.66
m
8ft
9in.
1.62
m
5ft
4in
.
0.50
m
1ft
8in.
5.05
m
16ft
7in.
3.24
m
10ft
8in.
1.93
m
6ft
4in.
2.96
m
9ft
8in.
2.96
m
9ft
8in.
10.3
0m
33ft
10
in.
12.3
4651
0kg
1025
37lb
4.0
-1.1
2.07
m
6ft
9in.
2.59
m
8ft
6in.
2.60
m
8ft
6in
.
1.58
m
5ft2
in.
0.49
m
1ft
7in
.
5.10
m
16ft
9in.
3.25
m
10ft
8in.
1.99
m
6ft
6in
.
3.03
m
9ft
11in
.
3.03
m
9ft
11in
.
10.4
2m
34ft
2in
.12
.7
4651
0kg
1025
37lb
29.0
-0.8
2.16
m
7ft
1in.
2.65
m
8ft
8in.
2.66
m
8ft
9in.
1.63
m
5ft4
in.
0.50
m
1ft
8in.
5.05
m
16ft
7in.
3.25
m
10ft
8in.
1.93
m
6ft
4in.
2.96
m
9ft
9in.
2.96
m
9ft
9in.
10.3
1m
33ft
10in
.12
.3
4300
0kg
9479
9lb
4.0
-1.1
2.07
m
6ft
9in.
2.60
m
8ft
6in.
2.61
m
8ft
7in.
1.59
m
5ft3
in.
0.50
m
1ft
8in
.
5.11
m
16ft9
in.
3.26
m
10ft8
in.
2.00
m
6ft
7in.
3.05
m
9ft
12in
.
3.05
m
9ft
12in
.
10.4
4m
34ft
3in
.12
.8
4300
0kg
9479
9lb
29.0
-0.7
2.16
m
7ft
2in.
2.66
m
8ft
9in.
2.67
m
8ft
9in.
164
m
5ft4
in.
0.52
m
1ft
8in
.
5.07
m
16ft
8in.
3.26
m
10ft8
in.
1.95
m
6ft
5in.
2.98
m
9ft
9in.
2.98
m
9ft
9in.
10.3
2m
33ft
10in
.12
.4
4080
0kg
8994
9lb
4.0
-1.1
2.08
m
6ft
9in.
2.60
m
8ft
6in.
2.61
m
8ft
7in.
1.60
m
5ft
3in.
0.51
m
1ft
8in.
5.12
m
16ft
10in
.
3.27
m
10ft
9in.
2.02
m
6ft
7in.
3.06
m
10ft
3.06
m
10ft
10.4
5m
34ft
4in.
12.8
4080
0kg
8994
9lb
29.0
-0.8
2.17
m
7ft
2in.
2.67
m
8ft
9in.
2.67
m
8ft
9in.
1.64
m
5ft
5in.
0.52
m
1ft
9in.
5.08
m
16ft
8in.
3.27
m
10ft
9in.
1.96
m
6ft
5in
.
2.99
m
9ft
10in
.
2.99
m
9ft
10in
.
10.3
4m
33ft
11
in.
12.4
2880
0kg
6349
3lb
4.0
-1.3
2.10
m
6ft
9in.
2.64
m
8ft
8in.
2.65
m
8ft
8in.
1.64
m
5ft
4in.
0.57
m
1ft
11in
.
5.29
3.33
m
10ft
11in
.
5.29
m
17ft
1in.
2.11
m
6ft
11in
.
3.16
m
10ft
4in.
3.16
m
10ft
4in.
10.5
7m
34ft
8in.
13.3
2880
0kg
6349
3lb
24.0
-1.0
2.18
m
7ft
2in.
2.69
m
8ft
10in
.
2.70
m
8ft
10in
.
1.68
m
5ft6
in.
0.58
m
1ft1
1in.
3.33
m
10ft1
1in.
5.17
m
16ft1
1in.
2.06
m
6ft9
in.
3.09
m
10ft2
in.
3.09
m
10ft2
in.
10.4
7m
34ft4
in.
13.0
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Tabl
e2.
3-
Gro
und
Cle
aran
ce-
LRA
ircra
ftM
odel
WE
IGH
TC
G
(%M
AC
)
FU
S
AN
GLE
(DE
G)
(A)
NO
SE
(B)
FO
R-
WA
RD
SE
RV
ICE
DO
OR
(C)
FO
R-
WA
RD
PAS
SE
N-
GE
R
DO
OR
(D)
FO
R-
WA
RD
CA
RG
O
DO
OR
(E)
NA
-
CE
LLE
(F)
WIN
GLE
T
(G)
EM
ER
-
GE
NC
Y
EX
IT
(H)
AF
T
CA
RG
O
DO
OR
(J)
AF
T
SE
RV
ICE
DO
OR
(K)
AF
T
PAS
SE
N-
GE
R
DO
OR
(L)
VE
RT
I-
CA
L
TAIL
(M)
TAIL
SK
ID
AN
GU
-
LAR
CLE
AR
-
AN
CE
(DE
G)
(N)
5046
0kg
1112
45lb
8.8
-1.0
02.
07m
6ft
9in.
2.59
m
8ft
6in.
2.60
m
8ft
7in.
1.58
m
5ft2
in.
0.48
m
1ft
7in.
5.09
m
16ft
8in.
3.23
m
10ft
7in.
1.96
m
6ft
5in.
3.00
2m
9ft
10in
.
3.00
m
9ft
10in
.
10.3
8m
34ft1
in.
12.5
5046
0kg
1112
45lb
29.0
-0.7
2.15
m
7ft
2.64
m
8ft
8in.
2.65
m
8ft
8in.
1.62
m
5ft
4in
.
0.49
m
1ft
7in.
5.05
m
16ft
7in.
3.23
m
10ft
7in.
1.92
m
6ft
4in.
2.94
m
9ft
8in.
2.94
m
9ft
8in.
10.2
9m
33ft
9in.
12.2
5030
0kg
1108
92lb
8.8
-1.0
2.07
m
6ft
9in.
2.59
m
8ft
6in.
2.60
m
8ft
6in.
1.58
m
5ft2
in.
0.48
m
1ft
7in.
5.09
m
16ft
8in.
3.23
m
10ft
7in.
1.96
m
6ft
5in.
3.00
m
9ft
10in
.
3.00
m
9ft
10in
.
10.3
8m
34ft
1in.
12.5
5030
0kg
1108
92lb
29.0
-0.8
2.15
m
7ft
2.65
m
8ft
8in.
2.65
m
8ft
8in.
1.62
m
5ft
4in
.
0.49
m
1ft
7in.
5.05
m
16ft
7in.
3.24
m
10ft
7in.
1.92
m
6ft
4in.
2.95
m
9ft
8in.
2.95
m
9ft
8in.
10.2
9m
33ft
9in.
12.2
4651
0kg
1025
37lb
4.0
-1.1
2.07
m
6ft
9in.
2.59
m
8ft
6in.
2.60
m
8ft
6in
.
1.58
m
5ft2
in.
0.49
m
1ft
7in
.
5.10
m
16ft
9in.
3.25
m
10ft
8in.
1.99
m
6ft
6in
.
3.03
m
9ft
11in
.
3.03
m
9ft
11in
.
10.4
2m
34ft
2in
.12
.7
4651
0kg
1025
37lb
29.0
-0.8
2.16
m
7ft
1in.
2.65
m
8ft
8in.
2.66
m
8ft
9in.
1.63
m
5ft4
in.
0.50
m
1ft
8in.
5.05
m
16ft
7in.
3.25
m
10ft
8in.
1.93
m
6ft
4in.
2.96
m
9ft
9in.
2.96
m
9ft
9in.
10.3
1m
33ft
10in
.12
.3
4300
0kg
9479
9lb
4.0
-1.1
2.07
m
6ft
9in.
2.60
m
8ft
6in.
2.61
m
8ft
7in.
1.59
m
5ft3
in.
0.50
m
1ft
8in
.
5.11
m
16ft9
in.
3.26
m
10ft8
in.
2.00
m
6ft
7in.
3.05
m
9ft
12in
.
3.05
m
9ft
12in
.
10.4
4m
34ft
3in
.12
.8
4300
0kg
9479
9lb
29.0
-0.8
2.16
m
7ft
2in.
2.66
m
8ft
9in.
2.67
m
8ft
9in.
164
m
5ft4
in.
0.52
m
1ft
8in
.
5.07
m
16ft
8in.
3.26
m
10ft8
in.
1.95
m
6ft
5in.
2.98
m
9ft
9in.
2.98
m
9ft
9in.
10.3
2m
33ft
10in
.12
.4
4080
0kg
8994
9lb
4.0
-1.1
2.08
m
6ft
9in.
2.60
m
8ft
6in.
2.61
m
8ft
7in.
1.60
m
5ft
3in.
0.51
m
1ft
8in.
5.12
m
16ft
10in
.
3.27
m
10ft
9in.
2.02
m
6ft
7in.
3.06
m
10ft
3.06
m
10ft
10.4
5m
34ft
4in.
12.8
4080
0kg
8994
9lb
29.0
-0.8
2.17
m
7ft
2in.
2.67
m
8ft
9in.
2.67
m
8ft
9in.
1.64
m
5ft
5in.
0.52
m
1ft
9in.
5.08
m
16ft
8in.
3.27
m
10ft
9in.
1.96
m
6ft
5in
.
2.99
m
9ft
10in
.
2.99
m
9ft
10in
.
10.3
4m
33ft
11
in.
12.4
2880
0kg
6349
3lb
4.0
-1.3
2.10
m
6ft
9in.
2.64
m
8ft
8in.
2.65
m
8ft
8in.
1.64
m
5ft
4in.
0.57
m
1ft
11in
.
5.29
3.33
m
10ft
11in
.
5.29
m
17ft
1in.
2.11
m
6ft
11in
.
3.16
m
10ft
4in.
3.16
m
10ft
4in.
10.5
7m
34ft
8in.
13.3
2880
0kg
6349
3lb
24.0
-1.0
2.18
m
7ft
2in.
2.69
m
8ft
10in
.
2.70
m
8ft
10in
.
1.68
m
5ft6
in.
0.58
m
1ft1
1in.
3.33
m
10ft1
1in.
5.17
m
16ft1
1in.
2.06
m
6ft9
in.
3.09
m
10ft2
in.
3.09
m
10ft2
in.
10.4
7m
34ft4
in.
13.0
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2.4. INTERIOR ARRANGEMENTS
The interior arrangement provides accommodation for two pilots, one observer, three flight attendants,and 98 passengers in 32 in pitch standard configuration. One additional flight attendant seat is availableas an option.
2.4.1. Passenger Cabin
The passenger cabin accommodates 98 passengers in 24 double seats on both sides, in 32 in pitchstandard configuration.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.)
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3 4 5
8
9
3 4
6 1 2
10
1 7
52
2 − WARDROBE 7 − AFT LAVATORY
9 − OVERHEAD BIN
OVERHEAD BIN
UNDERSEAT VOLUME
0.06 m / pax (2.0 ft / pax)
0.04 m / pax (1.4 ft / pax)
3 3
3
3
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 6 − FWD LAVATORY
8
1.82 m(5 ft 11 in.)
1.86 m(6 ft 4 in.)
4.17 m(13 ft 8 in.)
4.82 m(15 ft 10 in.)
25.91 m (85 ft)
0.81 m(2 ft 8 in.)
7.16(23 ft 6 in.)
7.77(25 ft 6 in.)
1.48 m(4 ft 10 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
22.63 m (799.18 ft )
EM
170A
PM
0200
13B
.DG
N
Typical Interior ArrangementsFigure 2.3
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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 2.4 - Capacity for the Cargo Compartment
CARGO COMPARTMENT LOADING VOLUMEFWD [1] 1850 kg (4078 lb) 12.41 m3 (438.26 ft3)
Aft 1650 kg (3638 lb) 10.22 m3 (360.92 ft3)Total 3500 kg (7716 lb) 22.63 m3 (799.18 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.)
EM
170A
PM
0200
01A
.DG
N
Economy Class Passenger Cabin Cross-SectionFigure 2.4
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2.00 m(6 ft 7 in.)
1.44 m(4 ft 9 in.)
0.94 m(3 ft 1 in.)
2.74 m(9 ft)
3.35 m(11 ft 0 in.)
3.01 m(9 ft 11 in.)
1.66 m
(5 ft 5 in.)
2.72 m
(8 ft 11 in.)
0.75 m
(2 ft 5 in.)
0.45 m(1 ft 6 in.)
0.86 m(3 ft)
0.51 m(1 ft 8 in.)
0.69 m(2 ft 3 in.)
0.20 m(8 in.)
0.07 m(3 in.)
0.6 m(1 ft 10 in.)
0.61 m(2 ft)
1.1 m(3 ft 8 in.)
EM
170A
PM
0200
02A
.DG
N
First Class Passenger Cabin Cross-SectionFigure 2.5
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2.6. LOWER COMPARTMENT CONTAINERS
Not Applicable
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2.7. DOOR CLEARANCES
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
EM
170A
PM
0200
14C
.DG
N
NOTE: FOR DIMENSIONS OF ALL DOORS,CONSIDER THAT AIRCRAFT IS IN OPERATION,THAT IS, EQUIPPED WITH DOOR LININGS ANDDOOR SURROUNDS.
1.71 m(5 ft 7.3 in.)
1.37 m(4 ft 5.9 in.)
0.61 m(2 ft)
0.98 m(3 ft 2.6 in.)
0.53 m(1 ft 8.9 in.)
0.53 m(1 ft 8.9 in.)
Door DimensionsFigure 2.6
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3. AIRCRAFT PERFORMANCE
3.1. GENERAL INFORMATION
The performance of the aircraft and engine depends on the generation of forces by the interactionbetween the aircraft or engine and the air mass through which it flies. The atmosphere has a pro-nounced effect on the temperature, pressure and density of the air.The ICAO establishes standard basics for estimating and comparing aircraft and engine performance.Some ICAO standard basics are shown below:
1. Sea level standard day:Standard Temperature To = 15 °C (288.15 K)Standard Pressure Po = 101.3 kPa (29.92 inHg)Standard Density ρo = 0.002377 slug per cubic feet
2. ISA
Table 3.1 - ISA
ALTITUDE TEMPERATUREm ft °C °F0 0 15.0 59.0
305 1000 13.0 55.4610 2000 11.0 51.9915 3000 9.1 48.31220 4000 7.1 44.71524 5000 5.1 41.23049 10000 -4.8 23.34573 15000 -14.7 5.56098 20000 -24.6 -12.37622 25000 -34.5 -30.29146 30000 -44.4 -48.011003 36089 -56.5 -69.712195 40000 -56.5 -69.7
NOTE: The performance data shown in this section must not be used for operations.
NOTE: For further information about performance, refer to AOM and AFM.
Tire speed limits are not applicable to this specific aircraft.This section provides the following information:
• The payload x range charts.
• The takeoff field length charts.
• The landing field length charts.
NOTE: For other charts containing payload x ranges, takeoff field lengths and/or landing fieldlengths with conditions different from those presented in this section, Embraer should becontacted so that these charts can be obtained.
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3.2. PAYLOAD X RANGE
The Payload x Range charts are based on the following conditions:
• CF34 - 10E engine models;
• Aircraft carrying passengers at 100 kg (220 lb) each one;
• Flight level 350, that represents the cruising altitude equal to 10668 m (35000 ft);
• Atmosphere according to ISA or ISA + 10 °C conditions;
• MTOW.
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PAYLOAD VS RANGE
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:47790 kg (105359 lb)
40800 kg (89948 lb)27900 kg (61509 lb)13000 kg (28660 lb)
CF34 −10E5, −10E5A1, −10E6, −10E6A1 & −10E7 ENGINES
ISARESERVE : 100 nm ALTERNATE + 45 min FLIGHT
EM
170A
PM
0300
30D
.DG
N
FLIGHT LEVEL 370
0 500 1000 1500 2000 2500 30000
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000
PA
YLO
AD
− k
g
0.78 MA
CH
MA
X C
RU
ISE
LON
G R
AN
GE
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
98 PAX @ 100 kg
RANGE − nm
MTOW = 47790 kg (105359 lb)
Payload x Range - ISA ConditionsFigure 3.1
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PAYLOAD VS RANGECF34 −10E5, −10E5A1, −10E6, −10E6A1 & −10E7 ENGINES
RESERVE : 100 nm ALTERNATE + 45 min FLIGHTMTOW = 47790 kg (105359 lb)
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:47790 kg (105359 lb)
40800 kg (89948 lb)27900 kg (61509 lb)13000 kg (28660 lb)
FLIGHT LEVEL 370ISA + 10°C
EM
170A
PM
0300
31D
.DG
N
0
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000
PA
YLO
AD
− k
g
0 500 1000 1500 2000 2500 3000
RANGE − nm
98 PAX @ 100 kg
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
LON
G R
AN
GE
0.78
MA
CH
MA
X C
RU
ISE
Payload x Range - ISA + 10 °C ConditionsFigure 3.2
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EM
170A
PM
0300
82A
.DG
N
PAYLOAD VS RANGE
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:
27900 kg (61509 lb)13000 kg (28660 lb)
ISARESERVE : 100 nm ALTERNATE + 45 min FLIGHT
0 500 1000 1500 2000 2500 30000
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000
PA
YLO
AD
− k
g
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
RANGE − nm
CF34 −10E5, −105A1, −10E6, −10E6A1 & −10E7 ENGINESFLIGHT LEVEL 350
MTOW = 50000 kg (110231 lb)
50000 kg (110231 lb)40800 kg (89948 lb)
98 PAX @ 220 lb
MAX CRUISE
LONG RANGE
0.78 MACH
Payload x Range - ISA ConditionsFigure 3.3
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EM
170A
PM
0300
83A
.DG
N
PAYLOAD VS RANGE
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:
27900 kg (61509 lb)13000 kg (28660 lb)
RESERVE : 100 nm ALTERNATE + 45 min FLIGHT
0 500 1000 1500 2000 2500 30000
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000
PA
YLO
AD
− k
g
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
RANGE − nm
CF34 −10E5, −105A1, −10E6, −10E6A1 & −10E7 ENGINESFLIGHT LEVEL 350
MTOW = 50000 kg (110231 lb)
50000 kg (110231 lb)40800 kg (89948 lb)
98 PAX @ 220 lb
LONG RANGE
0.78 MACH
ISA + 10°C
MAX CRUISE
Payload x Range - ISA + 10 °C ConditionsFigure 3.4
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PAYLOAD VS RANGECF34 −10E5, −10E5A1, −10E6, −10E6A1 & −10E7 ENGINES
RESERVE : 100 nm ALTERNATE + 45 min FLIGHTMTOW = 50300 kg (110893 lb)
FLIGHT LEVEL 360
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:50300 kg (110893 lb)
40800 kg (89949 lb)27900 kg (61509 lb)13000 kg (28660 lb)
ISA
EM
170A
PM
0300
32C
.DG
N
LON
G R
AN
GE
0.78
MA
CH
MA
X C
RU
ISE
0
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000P
AY
LOA
D −
kg
0 500 1000 1500 2000 2500 3000
98 PAX @ 100 kg
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
RANGE − nm
Payload x Range - ISA ConditionsFigure 3.5
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PAYLOAD VS RANGECF34 −10E5, −10E5A1, −10E6, −10E6A1 & −10E7 ENGINES
RESERVE : 100 nm ALTERNATE + 45 min FLIGHTMTOW = 50300 kg (110893 lb)
FLIGHT LEVEL 360
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:50300 kg (110893 lb)
40800 kg (89949 lb)27900 kg (61509 lb)13000 kg (28660 lb)
ISA + 10°C
EM
170A
PM
0300
33C
.DG
N
0
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000
PA
YLO
AD
− k
g
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
98 PAX @ 100 kg
MA
X C
RU
ISE
0.78
MA
CH
LON
G R
AN
GE
0 500 1000 1500 2000 2500 3000
RANGE − nm
Payload x Range - ISA + 10 °C ConditionsFigure 3.6
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PAYLOAD VS RANGE
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:51800 kg (114199 lb)
40900 kg (90169 lb)27900 kg (61509 lb)13000 kg (28660 lb)
CF34 −10E5, −10E5A1, −10E6, −10E6A1 & −10E7 ENGINES
ISARESERVE : 100 nm ALTERNATE + 45 min FLIGHT
FLIGHT LEVEL 370
MTOW = 51800 kg (114199 lb)
0 500 1000 1500 2000 2500 30000
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000
PA
YLO
AD
− k
g
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
98 PAX @ 100 kg
RANGE − nm
LON
G R
AN
GE
MA
X C
RU
ISE
0.78
MA
CH
EM
170A
PM
0300
60B
.DG
N
Payload x Range - ISA ConditionsFigure 3.7
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PAYLOAD VS RANGE
MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL
NOTES:51800 kg (114199 lb)
40900 kg (90169 lb)27900 kg (61509 lb)13000 kg (28660 lb)
CF34 −10E5, −10E5A1, −10E6, −10E6A1 & −10E7 ENGINES
RESERVE : 100 nm ALTERNATE + 45 min FLIGHT
FLIGHT LEVEL 350
MTOW = 51800 kg (114199 lb)
EM
170A
PM
0300
61B
.DG
N
0 500 1000 1500 2000 2500 30000
1000
2000
3000
4000
5000
6000
7000
8000
9000
10000
11000
12000
13000
14000
PA
YLO
AD
− k
g
PA
YLO
AD
− lb
0
2000
4000
6000
8000
10000
12000
14000
16000
18000
20000
22000
24000
26000
28000
30000
98 PAX @ 100 kg
RANGE − nm
LON
G R
AN
GE
MA
X C
RU
ISE
0.78
MA
CH
ISA+10
Payload x Range - ISA + 10 °C ConditionsFigure 3.8
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3.3. TAKEOFF FIELD LENGTHS
The takeoff performance is based on the requirements of JAR 25, Change 14, plus amendment 25/96/1.The takeoff field lengths charts provide data about the maximum takeoff weights for compliance with theoperating regulations relating to takeoff field lengths.Data are presented according to the following associated conditions:
• CF34 - 10E engine models;
• Takeoff Mode: 1;
• ATTCS positioning: ON and OFF;
• Flaps setting position: 1, 2 and 4;
• Pavement conditions: dry, hard paved and level runway surface with no obstacles;
• Zero wind and atmosphere according to ISA or ISA + 10 °C conditions;
• Pack OFF: No engine bleed extraction for air conditioning packs was considered in the takeoff andlanding charts.
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
36C
.DG
N
CF 34−10E5 ENGINE@T/O−1 MODE
ATTCS OFF
FLAP4
FLAP3
FLAP2
FLAP1
1000
1200
2000
2200
3000
4000
5000
6000
7000
8000
9000
FIE
LD L
EN
GT
H −
m
800
1400
1600
1800
2400
2600
FIE
LD L
EN
GT
H −
ft
60000 70000 80000 90000 100000 110000
25000 30000 35000 40000 45000 50000 55000
120000
WEIGHT − kg
WEIGHT − lb
SEA LEVEL
610
(200
0)
1219
(400
0)
1829
(600
0)
2438
(800
0)
3048
(100
00)
3658
(120
00)
4267
(140
00)
AIRPORT P
RESSURE ALT
ITUDE −
m (f
t)
ISA
Takeoff Field Lengths - ISA ConditionsFigure 3.9
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
37C
.DG
N
CF 34−10E5 ENGINE@T/O−1 MODEATTCS OFF
FLAP4
FLAP3
FLAP2
FLAP1
1000
1200
2000
2200
3000
4000
5000
6000
7000
8000
9000
FIE
LD L
EN
GT
H −
m
800
1400
1600
1800
2400
2600
2800
FIE
LD L
EN
GT
H −
ft
25000 30000 35000 40000 45000 50000 55000
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
SEA LEVEL
610
(200
0)
1219
(400
0)
1829
(600
0)
2438
(800
0)
3048
(100
00)
3658
(120
00)
4267
(140
00)
2000
AIRPORT P
RESSURE ALT
ITUDE −
m (f
t)
ISA + 10°C
Takeoff Field Lengths - ISA + 10 °C ConditionsFigure 3.10
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
38C
.DG
N
CF 34−10E5 ENGINE@T/O−1 MODE
ATTCS ON
FLAP4
FLAP3
FLAP2
FLAP1
1000
1200
2000
2200
3000
3000
4000
5000
6000
7000
8000
9000
FIE
LD L
EN
GT
H −
m
800
1400
1600
1800
2400
2600
2800
FIE
LD L
EN
GT
H −
ft
25000 30000 35000 40000 45000 50000 55000
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
SEA LEVEL
610
(200
0)
1219
(400
0)
1829
(600
0)
2438
(800
0)
AIRPORT P
RESSURE ALTIT
UDE − m
(ft)
3048
(100
00)
3658
(120
00)
4267
(140
00)
ISA
Takeoff Field Lengths - ISA ConditionsFigure 3.11
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
CF 34−10E5 ENGINE@T/O−1 MODE
EM
170A
PM
0300
39C
.DG
N
ATTCS ON
FLAP4
FLAP3
FLAP2
FLAP1
1000
1200
2000
2200
3000
3000
4000
5000
6000
7000
8000
9000
10000
FIE
LD L
EN
GT
H −
m
800
1400
1600
1800
2400
2600
2800
FIE
LD L
EN
GT
H −
ft
25000 30000 35000 40000 45000 50000 55000
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
SEA LEVEL
610
(200
0)
1219
(400
0)
1829
(600
0)
2438
(800
0)
3048
(100
00)
3658
(120
00)
4267
(140
00)
AIRPORT P
RESSURE ALT
ITUDE −
m (f
t)
ISA + 10°C
Takeoff Field Lengths - ISA + 10 °C ConditionsFigure 3.12
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
34B
.DG
N
60000 70000 80000 90000 100000 110000
25000 30000 35000 40000 45000 50000 55000
120000
1000
1200
2000
2200
3000
3000
4000
5000
6000
7000
8000
9000
FIE
LD L
EN
GT
H −
m
800
1400
1600
1800
2400
2600
2800
WEIGHT − kg
WEIGHT − lb
FIE
LD L
EN
GT
H −
ft
FLAP4
FLAP3
FLAP2
FLAP142
67 (1
4000
)36
58 (1
2000
)30
48 (1
0000
)24
38 (8
000)
1829
(600
0)12
19 (4
000)
610
(200
0)
SEA LEVEL
AIRPORT P
RESSURE ALT
ITUDE −
m (f
t)
CF34−10E7 ENGINE@T/O−1 MODE − ATTCS OFFCF34−10E5A1 & 10E6A1 ENGINES@T/O−1 MODE
ISA
Takeoff Field Lengths - ISA ConditionsFigure 3.13
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
35B
.DG
N
FLAP4
FLAP3
FLAP2
FLAP1
1000
1200
2000
2200
3000
3000
4000
5000
6000
7000
8000
9000
FIE
LD L
EN
GT
H −
m
800
1400
1600
1800
2400
2600
2800
FIE
LD L
EN
GT
H −
ft
25000 30000 35000 40000 45000 50000 55000
WEIGHT − kg
SEA LEVEL
610
(200
0)
1219
(400
0)
1829
(600
0)
2438
(800
0)
3048
(100
00)
3658
(120
00)
4267
(140
00)
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
AIRPORT P
RESSURE ALT
ITUDE −
m (f
t)
ISA + 10°C
CF34−10E7 ENGINE@T/O−1 MODE − ATTCS OFFCF34−10E5A1 & 10E6A1 ENGINES@T/O−1 MODE
Takeoff Field Lengths - ISA + 10 °C ConditionsFigure 3.14
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
40B
.DG
N
FLAP4
FLAP3
FLAP2
FLAP1
1000
1200
2000
2200
3000
3000
4000
5000
6000
7000
8000
9000
10000
FIE
LD L
EN
GT
H −
m
800
1400
1600
1800
2400
2600
2800
FIE
LD L
EN
GT
H −
ft
3200
25000 30000 35000 40000 45000 50000 55000
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
AIRPORT P
RESSURE ALTIT
UDE − m (f
t)
SEA LEVEL
610 (
2000
)
1219
(400
0)
1829
(600
0)
2438
(800
0)
3048
(100
00)
3658
(120
00)
4267
(140
00)
ISA
CF 34−10E7 ENGINE@T/O−1 MODEATTCS ON
Takeoff Field Lengths - ISA ConditionsFigure 3.15
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TAKEOFF FIELD LENGTH
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
41B
.DG
N
FLAP4
FLAP3
FLAP2
FLAP1
25000 30000 35000 40000 45000 50000 55000
1000
1200
2000
2200
3000
800
1400
1600
1800
2400
2600
2800
3200
3000
4000
5000
6000
7000
8000
9000
10000
FIE
LD L
EN
GT
H −
m
FIE
LD L
EN
GT
H −
ft
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
AIRPORT P
RESSURE ALTIT
UDE − m
(ft)
SEA LEVEL
610
(200
0)
1219
(400
0)
2438
(800
0)18
29 (6
000)
3048
(100
00)
3658
(120
00)
4267
(140
00)
ISA + 10°C
CF 34−10E7 ENGINE@T/O−1 MODEATTCS ON
Takeoff Field Lengths - ISA + 10 °C ConditionsFigure 3.16
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3.4. LANDING FIELDS LENGTHS
The landing field lengths charts provide data about the maximum landing weights for compliance withthe operating regulations relating to landing field lengths.Data is presented according to the following associated conditions:
• Landing gear: down;
• Flaps setting position: 5 or full;
• Pavement conditions: dry, hard paved and level runway surface with no obstacles;
• Zero wind and atmosphere according to ISA conditions;
• Pack OFF: No engine bleed extraction for air conditioning packs was considered in the takeoff andlanding charts.
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DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
EM
170A
PM
0300
46B
.DG
N
LANDING FIELD LENGTH
FLAP 5ISA
25000 30000 35000 40000 45000 50000 550001000
1200
2000
1400
1600
1800
4000
5000
6000
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
4267
(140
00)
3658
(120
00)
2438
(800
0)
1829
(600
0)
1219
(400
0)
610
(200
0)
AIRPORT P
RESSURE ALTITUDE − m
(ft)
LAN
D F
IELD
LE
NG
TH
− m
LAN
D F
IELD
LE
NG
TH
− ft
3048
(100
00)
MLW
= 4
4000
kg
(970
00 lb
)
SEA LEVEL
CF 34−10E5−10E5A1−10E6 & −10E6A1 ENGINES
Landing Field Lengths - Flaps 5Figure 3.17
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DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
LANDING FIELD LENGTH
EM
170A
PM
0300
47B
.DG
N
FLAP FULLISA
25000 30000 35000 40000 45000 50000 55000
1000
1200
1400
1600
1800
3658
(120
00)
3048
(100
00)
2438
(800
0)
1829 (6000)
610 (2000)
AIRPORT PRESSURE ALTITUDE − m
(ft)
MLW
= 4
4000
kg
(970
00 lb
)
4000
5000
LAN
D F
IELD
LE
NG
TH
− m
LAN
D F
IELD
LE
NG
TH
− ft
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
800
3000
SEA LEVEL1219 (4000)
CF34−10E5−10E5A1−10E6 & −10E6A1 ENGINES
4267
(140
00)
Landing Field Lengths - Flaps FullFigure 3.18
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25000 30000 35000 40000 45000 50000 550001000
1200
2000
1400
1600
1800
4000
5000
6000
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
4267
(140
00)
3658
(120
00)
2438
(800
0)
1829
(600
0)
1219
(400
0)
610
(200
0)
AIRPORT P
RESSURE ALTITUDE − m
(ft)
LAN
D F
IELD
LE
NG
TH
− m
LAN
D F
IELD
LE
NG
TH
− ft
3048
(100
00)
MLW
= 4
4000
kg
(970
00 lb
)
SEA LEVEL
EM
170A
PM
0300
62A
.DG
N
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
LANDING FIELD LENGTHCF 34−10E7 ENGINE
FLAP 5ISA
Landing Field Lengths - Flaps 5Figure 3.19
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EM
170A
PM
0300
63A
.DG
N
DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY
LANDING FIELD LENGTH
25000 30000 35000 40000 45000 50000 550001000
1200
2000
1400
1600
1800
4000
5000
6000
WEIGHT − kg
60000 70000 80000 90000 100000 110000 120000
WEIGHT − lb
4267
(140
00)
3658
(120
00)
2438
(800
0)
1829 (6000)
1219 (4000)
610 (2000)
AIRPORT PRESSURE ALTITUDE − m
(ft)
LAN
D F
IELD
LE
NG
TH
− m
LAN
D F
IELD
LE
NG
TH
− ft
3048
(100
00)
MLW
= 4
4000
kg
(970
00 lb
)SEA LEVEL
FLAP FULLISA
CF 34−10E7 ENGINE
Landing Field Lengths - Flaps FullFigure 3.20
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4. GROUND MANEUVERING
4.1. 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 determining such parameters and for themaneuvering characteristics of the aircraft.In the ground operating mode, varying airline practices may demand that more conservative turningprocedures be adopted, to avoid excessive tire wear and reduce possible maintenance problems.Variations from standard aircraft operating patterns may be necessary to satisfy physical 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°70°65°60°55°50°45°40°35°
R14.07m46ft 2 in
R1R2
R4
R6
R5
R3
R6.44 m21ft 2 in
NOTE:DATA PRESENTED IS BASED ON THEORETICAL CALCULATIONS.ACTUAL OPERATING DATA MAY BE GREATER THAN SHOWN SINCE TIRE SLIPPAGE IS NOT CONSIDERED IN THESE CALCULATIONS.
EM
170A
PM
0400
08B
.DG
N
35°
40°
45°
50°
55°
60°
65°
70°
76°
26.53 m
24.21 m
22.50 m
21.22 m
20.24 m
19.49 m
18.91 m
18.48 m
18.12 m
79 ft 5 in
73 ft 10 in69 ft 7 in
66 ft 5 in
63 ft 11 in
60 ft 8 in59 ft 5 in
87 ft
63 ft
70 ft 10 in
79 ft 3 in
64 ft 5 in
59 ft 6 in
55 ft 9 in
52 ft 9 in
50 ft 5 in
48 ft 7 in
47 ft 1 in
23.28 m
20.03 m
17.38 m
15.17 m
13.25 m
11.56 m
10.03 m8.62 m
7.04 m
76 ft 5 in
49 ft 9 in
43 ft 6 in
28 ft 3 in
23 ft 1 in
65 ft 9 in
57 ft
37 ft 11 in
32 ft 11 in
16.08 m
12.82 m
10.18 m7.96 m
6.05 m
4.35 m
2.82 m
1.41 m
0.17 m
52 ft 9 in
26 ft 1 in
4 ft 8 in
42 ft 1 in35 ft 5 in
19 ft 10 in14 ft 3 in
9 ft 3 in
7 in
34.35 m
31.13 m
28.52 m
26.33 m
24.45 m
22.79 m
21.30 m
19.93 m
18.39 m
102 ft 2 in
93 ft 7 in86 ft 5 in
80 ft 3 in
74 ft 9 in
65 ft 5 in
60 ft 4 in
112 ft 8 in
69 ft 10 in
31.50 m
28.91 m
26.90 m
25.32 m
24.02 m
22.95 m
22.05 m
21.29 m
20.51 m
83 ft 1 in
88 ft 3 in
78 ft 10 in
75 ft 4 in
72 ft 4 in
103 ft 4 in
94 ft 10 in
69 ft 10 in67 ft 3 in
STEERINGSTEEL
NOSER1
NOSE GEARR2
OUTBOARD GEARR3
INBOARD GEARR4 R5
RIGHT TAILTIPR6
RIGHT WINGLET
24.16 m
21.58 m
19.64 m
18.14 m
16.98 m
16.07 m
15.36 m
14.82 m
14.36 m
Turning Radii - No Slip AngleFigure 4.1
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4.3. MINIMUM TURNING RADII
R14. 07 m46 ft 2 in
R6.44 m21 ft 1 in
R14.36 m47 ft 1 in
21.4
0 m
70ft
3 in
(RU
NW
AY
MIN
IMU
M W
IDT
H)
76°
R5
R6
R3R1
ACTUAL OPERATING DATA MAY BE GREATER THAN VALUES SHOWN SINCE TIRE SLIPPAGE IS NOT CONSIDERED IN THESE CALCULATIONS.
NOTE:
1
1
EM
170A
PM
0400
09B
.DG
N
THEORETICAL CENTER OF TURN FOR MINIMUN RADIUS.SHOWS CONTINUOUS TURNING WITH ENGINE THRUST AS REQUIRED.NO DIFFERENTIAL BRAKING.
76° 18.12 m 59 ft 5 in 47 ft 1 in 7.04 m 23 ft 1 in 0.17 m 7 in 18.39 m 60 ft 4 in 20.51 m 67 ft 3 in
STEERINGSTEEL
NOSER1
NOSE GEARR2
OUTBOARD GEARR3
INBOARD GEARR4 R5
RIGHT TAILTIPR6
RIGHT WINGLET
14.36 m
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
EM
170A
PM
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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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 Codes
CODE ELEMENT 1 CODE ELEMENT 2CODE
NUMBERAIRCRAFT REFERENCE
FIELD LENGTHCODE
LETTERWING SPAN
OUTER MAIN LANDINGGEAR WHEEL SPAN
1less than 800 m
(2624 ft 8 in)A
Up to 15 m(49 ft 3 in)
Up to 4.5 m(14 ft 9 in)
2800 m (2624 ft 8 in) up to
1200 m (3937 ft)B
15 m (49 ft 3 in) to24 m (78 ft 9 in)
4.5 m (14 ft 9 in) to6 m (19 ft 8 in)
31200 m (3937 ft) up to1800 m (5905 ft 6 in)
C24 m (78 ft 9 in) to36 m (118 ft 1 in)
6 m (19 ft 8 in) to9 m (29 ft 6 in)
41800 m
(5905 ft 6 in) and overD
36 m (118 ft 1 in) to52 m (170 ft 7 in)
9 m (29 ft 6 in) to14 m (45 ft 11 in)
5 _ E52 m (170 ft 7 in) to
65 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 190STD, 190LR and 190AR is 3C.
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 2 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.
15 m (49 ft 2 in.)
45 m
(147 ft 7.6 in.)
EM
170A
PM
0400
11A
.DG
N
More than 90° Turn - Runway to TaxiwayFigure 4.4
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COORDINATE WITH AIRLINE OPERATORFOR THE SPECIFIC PLANNED OPERATINGPROCEDURE.
100 ft RADIUS(30 m)
100 ft RADIUS(30 m)
NOTE:
PATH OF MAIN LANDINGGEAR TIRE EDGE.
NOSE LANDING GEAR STEERING ANGLE ISAPPROXIMATELY 30.
15 m(49 ft 2 in.)
90°
45 m
(147 ft 7.6 in.)
EM
170A
PM
0400
12A
.DG
N
90° Turn - Runway to TaxiwayFigure 4.5
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COORDINATE WITH AIRLINE OPERATORFOR THE SPECIFIC PLANNED OPERATINGPROCEDURE.
NOTE:
NOSE LANDING GEAR STEERING ANGLE ISAPPROXIMATELY 28.
EM
170A
PM
0400
13.D
GN
15 m(49 ft 2 in.)
15 m(49 ft 2 in.)
100 ft Radius(30 m)
90°
PATH OF MAIN LANDINGGEAR TIRE EDGE.
3 m(9 ft 10 in.)
90° Turn - Taxiway to TaxiwayFigure 4.6
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4.6. RUNWAY HOLDING APRON
75 m(246 ft)
PATH OF MAIN LANDINGGEAR TIRE EDGE.
PATH OF MAIN LANDINGGEAR TIRE EDGE.
MINIMUMCLEARENCES
15 m(49 ft 2 in.)
3 m(9 ft 10 in.)
3 m(9 ft 10 in.)
15 m(49 ft 2 in.)
RUNWAY
TAXIWAY
45 m
(147 ft 7.6 in.)
EM
170A
PM
0400
14A
.DG
N
Runway Holding BayFigure 4.7
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5. TERMINAL SERVICING
During 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
110
100
LEN
GT
H −
ft
90
80
70
60
50
40
30
20
10
0
0
0
5
10
15
20
25
30
LEN
GT
H −
m
0 10 20 30 40 50 60 70 80 90 100 110 120
LENGTH − ft
5 10 15 20 25 30 35 40
130
45
140
LENGTH − m
5
3
42
3
7
24
1
98
1
6
SERVICING ARRANGEMENT
01 − PASSENGER STAIRS02 − BAGGAGE LOADER03 − BAGGAGE / CARGO04 − GALLEY SERVICE05 − FUEL SERVICE06 − POTABLE WATER07 − LAVATORY SERVICE08 − AIR CONDITIONING09 − PNEUMATIC STARTER
EM
170A
PM
0500
11A
.DG
N
Aircraft Servicing Arrangement With Passenger StairsFigure 5.1
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EM
170A
PM
0500
12.D
GN
110
100
LEN
GT
H −
ft
90
80
70
60
50
40
30
20
10
0
0 10 20 30 40 50 60 70 80 90 100 110 120
0 5 10 15 20 25 30 35
0
5
10
15
20
25
30
3
5
4 2
3 7
4
2
8
1
6
01 − PASSENGER STAIRS02 − BAGGAGE LOADER03 − BAGGAGE / CARGO04 − GALLEY SERVICE05 − FUEL SERVICE06 − POTABLE WATER07 − LAVATORY SERVICE08 − PASSENGER BRIDGE
SERVICING ARRANGEMENT
LENGTH − ft
LENGTH − m
LEN
GT
H −
m
40 45
130 140
Aircraft Servicing Arrangement With Passenger BridgeFigure 5.2
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5.2. TERMINAL OPERATIONS - TURNAROUND STATION
This section presents the typical turnaround servicing time at an air terminal. The chart gives typicalschedules for 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 4.1
AIRPLANE INTERIOR SERVICES
PASSENGERS ENPLANE
6.1
6.1
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
5.8
7.1
0,5
3.5
4.3
LEGEND:
NOTE:
7,0
7,0
BRIDGE / STAIRS POSITIONING
EM
170A
PM
0500
13A
.DG
N
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
EM
170A
PM
0500
14E
.DG
N
ITEM DESCRIPTIONCOORD. Y
(mm)COORD. Z
(mm)COORD. X
(mm)
HEIGHTABOVE
GROUND(mm)
NOTE:
1825.31
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
−543.7517316.95
17695.04
7803.78
7774.46 −310.92
−936.13 −1262.71
4136.97 −951.46 −1279.29
0.00
13268.52 −1979.71
13629.01 −1952.83
18052.28 −1744.672930.25
20139.16 −1602.04−808.01
27861.83 −329.37 −1178.74
30421.65 −471.73 −605.30
30562.26 −449.47 −585.54
6562.14 1159.87 −961.05
16444.90 −691.60 −1611.45
16476.65 −1611.45526.50
20139.16 −1602.04808.01
28784.01 −991.80349.20
30398.86 −590.09519.15
0.00
57.25
−1339.534146.90
2862.76
3104.19
GRAVITY REFUELING PORT (LH)
GRAVITY REFUELING PORT (RH)
17932.67 −7646.75 −308.24 3112.32
1842.51
4125.32 −2854.38 250.36
1334.39
1369.51
1679.01
18078.03 2970.00 −2988.86 435.73
18078.03 −2970.00 −2988.86 435.73
1869.43
2469.64
3101.60
3124.58
2109.06
1775.35
1776.08
1869.43
2677.66
3116.29
EXTERNAL POWER SUPPLY 28 VDC / 400A
EXTERNAL POWER SUPPLY 115 VAC −810.70 1765.31
22
THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 29500 kg (CG FWD 4.0% CMA)
FORWARD RAMP HEADSET
PRESSURE REFUELING PANEL
STEERING SWITCH DISENGAGE
WHEEL JACK POINT − NLG
AIR COND. GROUND CONNECTION
GROUNDING POINT (ELECTRICAL)
WATER SERVICING PANEL
WASTE SERVICING PANEL
HYD. SYS # 3 SERVICE PANEL
AFT RAMP HEADSET
OXYGEN 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
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 DESCRIPTIONCOORD. Y
(mm)COORD. Z
(mm)COORD. X
(mm)
HEIGHTABOVE
GROUND(mm)
NOTE:
1907.92
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
−543.7517316.95
17695.04
7803.78
7774.46 −310.92
4146.44 −936.13 −1262.71
4136.97 −951.46 −1279.29
0.00
13268.52 −1979.71
13629.01 −1952.83
18052.28 −1744.672930.25
20139.16 −1602.04−808.01
27861.83 −329.37 −1178.74
30421.65 −471.73 −605.30
30562.26 −449.47 −585.54
6562.14 1159.87 −961.05
16444.90 −691.60 −1611.45
16476.65 −1611.45526.50
20139.16 −1602.04808.01
28784.01 −991.80349.20
30398.86 −590.09519.15
0.00
57.25
−1339.534146.90
2849.66
3088.37
GRAVITY REFUELING PORT (LH)
GRAVITY REFUELING PORT (RH)
17932.67 −7646.75 −308.24 3094.78
1924.92
4125.32 −2854.38 250.48
1350.51
1383.02
1660.39
18077.02 2970.00 −2969.64 428.34
18077.02 −2970.00 −2969.64 428.34
1835.66
2379.79
2993.22
3015.18
2264.08
1768.43
1768.43
1835.66
2581.13
3008.07
EXTERNAL POWER SUPPLY 28 VDC / 400A
EXTERNAL POWER SUPPLY 115 VAC −810.70 1847.84
22
FORWARD RAMP HEADSET
PRESSURE REFUELING PANEL
STEERING SWITCH DISENGAGE
WHEEL JACK POINT − NLG
AIR COND. GROUND CONNECTION
GROUNDING POINT (ELECTRICAL)
WATER SERVICING PANEL
WASTE SERVICING PANEL
HYD. SYS # 3 SERVICE PANEL
AFT RAMP HEADSET
OXYGEN 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
EM
170A
PM
0500
24.D
GN
THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 29500 kg (CG REAR 29.0% CMA)
Ground Servicing ConnectionsFigure 5.5
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5.5. ENGINE STARTING PNEUMATIC REQUIREMENTS
Altitudeft
AmbientTemp °F
MinimumPressure psia
MinimumTemp °F
SLSLSL
900090009000
13,00013,00013,00015,00015,00015,000
48.043.740.737.730.028.936.027.226.732.925.324.4
349443505350409474352399458352392446
95.182.073.774.557.353.471.352.249.666.649.046.1
EM
170A
PM
0500
30A
.DG
N
MinimumFlow lb/min
TABLE 1 − PNEUMATIC ENGINE START REQUIREMENTS
−4059
120−402386
−401271
−405
59
Engine Starting Pneumatic RequirementsFigure 5.6
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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)
CA
BIN
TE
MP
ER
AT
UR
E (
°F)
EM
170A
PM
0500
07B
.DG
N
CA
BIN
TE
MP
ER
AT
UR
E (
°F)
CA
BIN
TE
MP
ER
AT
UR
E (
°C)
CA
BIN
TE
MP
ER
AT
UR
E (
°C)
Ground Pneumatic Power RequirementsFigure 5.7
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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.
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
TO
TA
L A
IRF
LOW
1
2
3
4
56
0 0
20
40
60
80
10
20
30
40
100
50
120
140
60
55
150
−5 0 5 10 15 20 25 30 35 40 45 50 55 [°C]
[°F]
PRE−CONDITIONED AIRFLOW REQUIREMENTS
PR
ES
SU
RE
AT
GR
OU
ND
CO
NN
EC
TIO
N (
INC
HE
S O
F W
AT
ER
)
AIR SUPPLY TEMPERATURE
5030 70 90 110 120
[lbm/min]
[kg/min]
EM
170M
FE
P04
0070
B.D
GN
CABIN AT 24°C (74°F),NO CABIN OCCUPANTS, FOUR CREWMEMBERS ONLY, OVERCAST DAY(NO SOLAR IRRADIATION),−40°C (−40°F) DAY.
Preconditioned Airflow RequirementsFigure 5.8
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5.8. GROUND TOWING REQUIREMENTS
NO
TE
S:
− S
TR
AIG
HT
−LI
NE
TO
W−
UN
US
UA
L B
RE
AK
AW
AY
CO
ND
ITIO
NS
NO
T S
HO
WN
− C
OE
FF
ICIE
NT
S O
F F
RIC
TIO
N (
)
AR
E E
ST
IMA
TE
D F
OR
RU
BB
ER
−T
IRE
D T
OW
V
EH
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
BE
R O
FE
NG
INE
SB
AC
KIN
G A
GA
INS
TID
LE T
HR
US
T
10
12
34
02
PE
RC
EN
T S
LOP
E (
%)
5
1000
(220
4)
3000
(661
4)
2000
(440
9) 0
TOWBAR PULL − kg (lb)
4000
(881
8)
5000
(110
23)
DRY CONCRETE O
R
ASPHALT =0.8
WET ASPHALT
=0.75
WET C
ONCRETE =
0.57
SNO
W C
HAINS
=
0.45
HA
RD
SN
OW
=
0.2
ICE
=
0.05
REFERENCE LINE
4700
0 (1
0361
7)
4500
0 (9
9208
)
4300
0 (9
4799
)
4100
0 (9
0390
)
3900
0 (8
5980
)
3500
0 (7
7162
)
3300
0 (7
2753
)
3100
0 (6
8343
)
2900
0 (6
3934
)
3700
0 (8
1571
)
4900
0 (1
0802
7)
5100
0 (1
1243
6)
5300
0 (1
1684
5)
5500
0 (1
2125
4)
AIRCRAFT G
ROSS WEIG
HT − kg
(lb)
GR
OU
ND
TO
WIN
G R
EQ
UIR
EM
EN
TS
EM
170M
FE
P04
0066
B.D
GNTO
TA
L T
RA
CT
ION
WH
EE
L −
kg
(lb)
(DR
AW
BA
R P
ULL
)
Ground Towing RequirementsFigure 5.9
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6. OPERATING CONDITIONS
This 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.
0
2468
101214
16
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
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
A
B
C
D
Met
ers
Meters
HE
IGH
T A
BO
VE
GR
OU
ND
PLA
NE
, Fee
t
Met
ers
DIS
TA
NC
E F
RO
M A
IRP
LAN
E C
L −
Fee
t
DISTANCE FROM CORE NOZZLE EXIT, Feet
Meters
EM
170M
FE
P02
0014
A.D
GN
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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0
2468
101214
16
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
HE
IGH
T A
BO
VE
GR
OU
ND
PLA
NE
− F
eet
Met
ers
DIS
TA
NC
E F
RO
M A
IRP
LAN
E C
L −
Fee
t
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
ABCDE
°F100150200400900
TOTAL TEMPERATUREMAX = 689°C (1273°F)
°C386693204582
NOTE:EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND. E
M17
0MF
EP
0200
16B
.DG
N
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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0
2468
101214
16
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
7
A
BCD
ABCD
Met
ers
Met
ers
HE
IGH
T A
BO
VE
GR
OU
ND
PLA
NE
− F
eet
DIS
TA
NC
E F
RO
M A
IRP
LAN
E C
L −
Fee
t
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
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. E
M17
0MF
EP
0200
15A
.DG
N
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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0
2468
101214
16
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
HE
IGH
T A
BO
VE
GR
OU
ND
PLA
NE
− F
eet
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
Met
ers
DIS
TA
NC
E F
RO
M A
IRP
LAN
E C
L −
Fee
t
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
NOTE:EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND. E
M17
0MF
EP
0200
17A
.DG
N
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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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
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
HE
IGH
T A
BO
VE
GR
OU
ND
PLA
NE
, Fee
t
Met
ers
DISTANCE FROM CORE NOZZLE EXIT, Feet
Meters
Met
ers
DISTANCE FROM CORE NOZZLE EXIT, Feet
Meters
NOTE:
DIS
TA
NC
E F
RO
M A
IRP
LAN
E C
L −
Fee
t
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
EM
170A
PM
0600
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
BREAKAWAY POWER, SEA LEVEL, Tamb = ISA +0°C, FNIN1 = 40660 N (9139 lbf)
HE
IGH
T A
BO
VE
GR
OU
ND
PLA
NE
− F
eet M
eter
s
AXIAL DISTANCE BEHIND AIRPLANE
(Meters)
Feet
DIS
TA
NC
E F
RO
M A
IRP
LAN
E C
L −
Fee
t
75 MPH100 MPH
50 MPH
35 MPH
EM
170A
PM
0600
10A
.DG
N
100 MPH
75 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
BA
20
TOTAL TEMPERATUREMAX = 697 °F (369 °C)
°F °C
NOTE:
100150200400650
386693
204343
ABCDE
EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 knot HEADWIND.
DISTANCE FROM CORE NOZZLE EXIT − Feet
Meters
Meters
DISTANCE FROM CORE NOZZLE EXIT − Feet
Met
ers
HE
IGH
T A
BO
VE
GR
OU
ND
PLA
NE
− F
eet
Met
ers
EM
170A
PM
0600
09A
.DG
N
DIS
TA
NC
E F
RO
M A
IRP
LAN
E C
L −
Fee
tBREAKAWAY POWER, SEA LEVEL, Tamb = ISA +0°C, FNIN1 = 40660 N (9139 lbf)
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, ICAO Annex 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)
EM
170A
PM
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.
EM
170A
PM
0600
05C
.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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7. PAVEMENT DATA
7.1. 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 oncharts, are values obtained under loaded conditions as certificated 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
13.83 m
(45 ft 4 in.)0.40 m(1 ft 4 in.)
(19 ft 6 in.)
5.94 m
AIRCRAFT MODELS
LRSTD
(2 ft 10 in.)
EM
170A
PM
0700
27B
.DG
N
47950 kg(105712 lb)
50460 kg
24 x 7.7 16PR
H41 x 16−20 22PR
(147 − 0/+10 psi)10.34 − 0/+0.7 kg/cm ²
9.21 − 0/+0.7 kg/cm ²(131 − 0/+10 psi)
AR
51960 kg(114552 lb)(111245 lb)
FootprintFigure 7.1
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7.3. MAXIMUM PAVEMENT LOADS
MODELSTATIC AT MOSTFORWARD C.G.
NGV MGV (PER STRUT) (PER STRUT)H
2
6424 kg(14162 lb)
6470 kg(14264 lb)
MAXIMUMRAMP
WEIGHT
8917 kg(19659 lb)
8820 kg(19445 lb)
23301 kg(51370 lb)
22213 kg(48971 lb)
6814 kg(15022 lb)
6494 kg(14317 lb)
16138 kg(35578 lb)
15376 kg(33898 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
47950 kg(105712 lb)
6347 kg(13993 lb)
8927 kg(19681 lb)
23952 kg(52805 lb)
7005 kg(15443 lb)
16593 kg(36581 lb)
51960 kg(114552 lb)AR
14807 kg(32644 lb)
21181 kg(46696 lb)
8498 kg(18735 lb)
6229 kg(13732 lb)
46150 kg(101743 lb)SR
50460 kg(111245 lb)
6255 kg(13790 lb)
EM
170A
PM
0700
28D
.DG
N
Maximum Pavement LoadsFigure 7.2
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7.4. LANDING GEAR LOADING ON PAVEMENT
EM
170A
PM
0700
29B
.DG
N
LEGEND
LR AIRCRAFT MODEL
STD AIRCRAFT MODEL
50000
45000
40000
35000
30000
25000
2000084 86 88 90 92 94
50460
90000
80000
70000
60000
50000
100000
110000
90000
80000
70000
60000
50000
WE
IGH
T O
N M
AIN
LA
ND
ING
GE
AR
(kg
)
WE
IGH
T O
N M
AIN
LA
ND
ING
GE
AR
(lb
)
PERCENT OF WEIGHT ON MAIN GEAR − (%)
AIR
CR
AF
T G
RO
SS
WE
IGH
T −
(kg
)
100000
110000
WE
IGH
T O
N M
AIN
LA
ND
ING
GE
AR
(lb
)
6.0 % 29.0 %%MAC
47950
42500
37500
32500
29500
35000
40000
45000
51960
AR AIRCRAFT MODEL
Landing Gear Loading on PavementFigure 7.3
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7.5. FLEXIBLE PAVEMENT REQUIREMENTS, US CORPS OF ENGINEERS DESIGNMETHOD
The flexible pavement curves that are based on procedures set forth in Instruction Report No. S-77-1,“Procedures for Development of CBR Design Curves”, dated June 1977, and as modified according tothe methods described in FAA Advisory Circular 150/5320-6D, “Airport Pavement Design and Evalua-tion”, dated July 7, 1995. Instruction Report No. S-77-1 was prepared by the US Army Corps ofEngineers Waterways Experiment Station, Soils and Pavements Laboratory, Vicksburg, Mississippi. Theline showing 10,000 coverages is used to calculate ACN.
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EM
170A
PM
0700
31A
.DG
N
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)
46806 103190
44046 97105
39988 88158
37832 83405
26302 57986
NOTES: 2
SUBGRADE STRENGHT − CBR MODEL
TIRE SIZE: H41 x 16−20 22 PRTIRE PRESSURE: 10.34 kgf/cm (147 psi)
Flexible Pavement Requirements - US Army Corps of Engineers Design MethodFigure 7.4
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7.6. FLEXIBLE PAVEMENT REQUIREMENTS, LCN METHOD
The LCN Method curves for flexible pavements. They have been built using procedures and curves inthe ICAO Aerodrome Design Manual, Part 3 - Pavements, Document 9157-AN/901, 1983. The samechart 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
EM
170A
PM
0700
33A
.DG
NE
QU
IVA
LEN
T S
ING
LE W
HE
EL
LOA
D −
(kg
)
LCN − LOAD CLASSIFICATION NUMBER
201053 30
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L LO
AD
− (
lb)
8000
6000
10000
12000
14000
16000
180001900020000
6 7 8 9 30 40 50 60 70 8090 100
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L LO
AD
− (
lb)
1010000
50000
20
20000
30000
40000
2010 30 40 50 60 70 8090100
26302 (57986)
37832 (83405)
44046 (97105)46806 (103190)
39988 (88158)
WEIGHT ON MAINLANDING GEAR
kg (lb)
NOTES: 2TIRE SIZE: H41x16−20 22PRTIRE PRESSURE: 10.34 kgf/cm (147 psi)
FLEXIBLE PAVEMENT THICKNESS − (cm)
FLEXIBLE PAVEMENT THICKNESS − (in.)
Flexible Pavement Requirements - LCN MethodFigure 7.5
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7.7. RIGID PAVEMENT REQUIREMENTS, PORTLAND CEMENT ASSOCIATION DESIGNMETHOD
This method has a chart that have 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 that 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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80
70
60
50
40
30
20
10
0E
M17
0AP
M07
0035
A.D
GN
22
20
18
16
14
12
10
8
6
4
2
0
24
26
28
30
80
70
60
50
40
30
20
10
0
ALL
OW
AB
LE W
OR
KIN
G S
TR
ES
S −
kgf
/cm
ALL
OW
AB
LE W
OR
KIN
G S
TR
ES
S −
psi
PA
VE
ME
NT
TH
ICK
NE
SS
(cm
)
PA
VE
ME
NT
TH
ICK
NE
SS
(in
.) 800
700
600
500
400
300
200
100
0
900
1000
1100
k=550 lb/in
k=300 lb/in
k=150 lb/ink=75 lb/in
WEIGHT ON MAIN LANDING GEAR − kg (lb)
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:
46806 (103190)
44046 (97105)
39988 (88158)
37832 (85405)
26302 (57986)
2
2NOTES: TIRE SIZE: H41 x 16−20 22PRTIRE PRESSURE: 10.34 kgf/cm (147 psi) (UNLOADED)
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 that are 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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EM
170A
PM
0700
07.D
GN
RADIUS OF RELATIVE STIFFNESS ( )VALUES IN INCHES
=4 Ed
=24.16522
4 d
k
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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EM
170A
PM
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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EM
170A
PM
0700
37A
.DG
N
3998
8 (8
8158
)
3783
2 (8
3405
)
4404
6 (9
7104
)
4680
6 (1
0319
0)
2630
2 (5
7985
)
NOTES: 2TIRE SIZE: H41 x 16−20 22 PRTIRE PRESSURE: 10.34 kgf/cm (147 psi)
NOTES:EQUIVALENT SINGLE WHEEL LOADSARE DERIVED BY METHODS SHOWNIN ICAO AERODROME MANUAL.PART 2, PAR. 4.1.3
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L LO
AD
− (
kg)
LCN − LOAD CLASSIFICATION NUMBER
RADIUS OF RELATIVE STIFFNESS − (in.)
RADIUS OF RELATIVE STIFFNESS − (cm)
8000
6000
10000
12000
14000
16000
5030
180001900020000
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L LO
AD
− (
lb)
2010 30 40 50 60 70 8090100
100 200
60 70 80 9010000
50000
20000
30000
40000
WEIGHT ON MAINLANDING GEAR
kg (lb)
100 200 300 4005040
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 which an evaluation shows can be borne by the pavement whenapplied by a standard single wheel. The ACN established for the particular pavement type and subgradecategory of the rated pavement as well as for the particular aircraft mass and characteristics.An aircraft shall be 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 with the results of their evaluation presentedas follows:
Table 7.1 - Pavement Evaluation
PAVEMENTTYPE
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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EM
170A
PM
0700
39A
.DG
N
30
40000 42000 44000 46000 48000 50000 52000
NOTES: 2TIRE SIZE: H41 x 16−20 22 PR
50460
35
88000 92000 96000 100000 104000 108000 112000
AIR
CR
AF
T C
LAS
SIF
ICA
TIO
N N
UM
BE
R−
AC
N
10
15
20
25
28000 30000 32000 34000 36000 38000
64000 68000 72000 76000 80000 84000
AIRCRAFT GROSS WEIGHT−lb
AIRCRAFT GROSS WEIGHT−kg
MA
XIM
UM
RA
MP
WE
IGH
T
FLEXIBLE PAVEMENT SUBGRADE
SBGRADE STRENGTH ULTRA LOW − CBR=3%LOW − CBR=6%MEDIUM−CBR=10%HIGH−CBR=15%
TIRE PRESSURE: 10.34 kgf/cm (147 psi) (UNLOADED)
ACN For Flexible PavementFigure 7.10
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EM
170A
PM
0700
41A
.DG
N
30
40000 42000 44000 46000 48000 50000 5200050460
35
88000 92000 96000 100000 104000 108000 112000
AIR
CR
AF
T C
LAS
SIF
ICA
TIO
N N
UM
BE
R−
AC
N
10
15
20
25
28000 30000 32000 34000 36000 38000
64000 68000 72000 76000 80000 84000
AIRCRAFT GROSS WEIGHT−lb
AIRCRAFT GROSS WEIGHT−kgM
AX
IMU
M R
AM
P W
EIG
HT
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: 10.34 kgf/cm (147 psi) (UNLOADED)
ACN For Rigid PavementFigure 7.11
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8. POSSIBLE EMBRAER 190 DERIVATIVE AIRCRAFT
8.1. NOT APPLICABLE
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9. SCALED DRAWINGS
9.1. GENERAL
This section provides plan views to the following scales:
• English/American Customary Weights and Measures1 inch = 32 feet1 inch = 50 feet1 inch = 100 feet
• Metric1:5001:1000
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0
0 16 32 48 64
5 10 15 20 25 m
80 ft
ITEM DESCRIPTION
1
ITEM DESCRIPTION
8
2
3
4
5
6
7
9
10
11
12
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTING
AIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANEL
OXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)
PRESSURE REFUELING / DEFUELING
CARGO DOOR
MAIN LANDING GEAR
NOSE LANDING GEAR
PASSENGER DOOR
WING SPAN:28.72 m
(94 ft 3 in.)
14 SERVICE DOOR
1
7
3
8
4
9
25
6
EM
170A
PM
0900
06.D
GN
14
10
1111
10
1413
Scale: 1 Inch Equals 32 FeetFigure 9.1
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ITEM DESCRIPTION
1
ITEM DESCRIPTION
8
2
3
4
5
6
7
9
10
11
12
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTING
AIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANEL
OXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)
PRESSURE REFUELING / DEFUELING
CARGO DOOR
MAIN LANDING GEAR
NOSE LANDING GEAR
PASSENGER DOOR
14 SERVICE DOOR
1
7
3
8
4
9
2 5
6
14
10
1111
10
1413
WING SPAN:28.72 m
(94 ft 3 in.)
0 5 10 15 20 25 m
0 16 32 48 64 80 ft
13
12
EM
170A
PM
0900
07.D
GN
Scale: 1 Inch Equals 50 FeetFigure 9.2
AIRPORTPLANNING MANUAL
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EFFECTIVITY: ALL Section 9
Page 9-3
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ITEM DESCRIPTION
1
ITEM DESCRIPTION
8
2
3
4
5
6
7
9
10
11
12
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTING
AIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANEL
OXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)
PRESSURE REFUELING / DEFUELING
CARGO DOOR
MAIN LANDING GEAR
NOSE LANDING GEAR
PASSENGER DOOR
14 SERVICE DOOR
17
3
8
49
2 5
6
14
10
11
11
101413
0 5 10 15 20 25 m
0 16 32 48 64 80 ft
13
12
WING SPAN:28.72 m
(94 ft 3 in.)
EM
170A
PM
0900
08.D
GN
Scale: 1 Inch Equals 100 FeetFigure 9.3
AIRPORTPLANNING MANUAL
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pm19
01
EFFECTIVITY: ALL Section 9
Page 9-4
Aug 15/05
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ITEM DESCRIPTION
1
ITEM DESCRIPTION
8
2
3
4
5
6
7
9
10
11
12
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTING
AIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANEL
OXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)
PRESSURE REFUELING / DEFUELING
CARGO DOOR
MAIN LANDING GEAR
NOSE LANDING GEAR
PASSENGER DOOR
14 SERVICE DOOR
1
7
3
8
4
9
2 5
6
14
10
1111
10
1413
WING SPAN:28.72 m
(94 ft 3 in.)
0 5 10 15 20 25 m
160 32 6448 80 ft
13
12
EM
170A
PM
0900
09.D
GN
Scale: 1 to 500Figure 9.4
AIRPORTPLANNING MANUAL
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EFFECTIVITY: ALL Section 9
Page 9-5
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50 m
ITEM DESCRIPTION
1
ITEM DESCRIPTION
8
2
3
4
5
6
7
9
10
11
12
13
EXTERNAL POWER SUPPLY 115 VAC
EXTERNAL POWER SUPPLY 28 VDC
ENGINE AIR STARTING
AIR CONDITIONING LOW PRESSURE
WASTE SERVICING PANEL
POTABLE WATER SERVICING PANEL
OXYGEN REFILL / REPLACE BOTTLE
GROUNDING POINT (RIGHT MLG)
PRESSURE REFUELING / DEFUELING
CARGO DOOR
MAIN LANDING GEAR
NOSE LANDING GEAR
PASSENGER DOOR
14 SERVICE DOOR
17
3
8
4
9
2 5
6
14
10
11
11
10
1413
0 5 10 15 20
160 32 6448 80 ft
13
12
WING SPAN:28.72 m
(94 ft 3 in.)
25
EM
170A
PM
0900
10.D
GN
Scale: 1 to 1000Figure 9.5
AIRPORTPLANNING MANUAL
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pm19
01
EFFECTIVITY: ALL Section 9
Page 9-6
Aug 15/05