AIRPORT PLANNING MANUAL - Embraer · TO: HOLDERS OF PUBLICATION No. APM-1346 -″AIRPORT PLANNING...

AIRPORT PLANNINGMANUAL

APM-134608 DECEMBER 2003

REVISION 17 - 09 OCTOBER 2015

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 © 2015 by EMBRAER S.A. All rights reserved.

In connection with the use of this document, Embraer does not provide any express or implied warranties andexpressly disclaims any warranty of merchantability or fitness for a particular purpose.

This document contains trade secrets, confidential, proprietary information of Embraer and technical datasubject to U.S. Export Administration Regulation (″EAR″) and other countries export control laws andregulations. Diversion contrary to the EAR and other laws regulations is strictly forbidden. The aboverestrictions may apply to data on all pages of this document.

TO: HOLDERS OF PUBLICATION No. APM-1346 - ″AIRPORT PLANNING MANUAL ″.

FRONT MATTER - REVISION No. 17 DATED OCTOBER 09/2015

Pages which have been added, revised, or deleted by the current revision are indicated by an asterisk,on the List of Effective Pages.This issue incorporates all preceding Temporary Revisions (if any).Modifications introduced by this revision are all editorial in nature, with no technical implications, theynot being therefore highlighted and no substantiation source being presented herein.

EMBRAER S.A.AV. BRIGADEIRO FARIA LIMA, 2.170 - CAIXA POSTAL 8050 - TELEFONE (55) 12 39277517

FAX (55) 12 39277546 - CEP 12.227-901 - SÃO JOSÉ DOS CAMPOS - SÃO PAULO - BRASILe-mail: [email protected] - http://www.embraer.com

HIGHLIGHTS Page 1 of 2

Oct 09/15

REVNo.

ISSUEDATE

DATEINSERTED

BYREVNo.

ISSUEDATE

DATEINSERTED

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AIRPORTPLANNING MANUAL

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RECORD OF REVISIONS

The user must update the Record of Revisions when a revision is put into the manual.

RETAIN THIS RECORD IN THE FRONT OF MANUAL OR CHAPTER.ON RECEIPT OF REVISIONS, INSERT REVISED PAGES IN THE MANUAL, AND ENTER REVISION NUMBER, DATEINSERTED AND INITIALS.

TemporaryRev. No.

PageNumber

IssuedDate By Date

Removed By


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RECORD OF TEMPORARY REVISIONS

TEMPORARY REVISION STATUS REPORT

This list is intended to show the operator which temporary revisions are applicable to his fleet.The list consists of the temporary revision number, the related issue date, the incorporation date, andthe affected subject.


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EFFECTIVITY: ALL TR STATUS REPORT

Page 1 / 2

Oct 22/07

S* INDICATES TR HAS BEEN SUPERSEDED BY THE TR REFERRED TO.

LIST OF SERVICE BULLETINS

This list is intended to let the operator know which Service Bulletins are incorporated to the APM.

The list consists of the Service Bulletin numbers and the respective revisions (if applicable), the affectedsection (s) (APM Section Number), information on whether the Service Bulletin affects the manual, theaircraft (Effectivity) affected by the Service Bulletins and the incorporation date.

A revision bar is placed on the left margin of the list whenever data are inserted or revised.

NOTE: The effectivity is indicated by means of two numerical groups separated by a dash. The firstgroup presented in the effectivity column corresponds to the last digits of the lowest aircraftdesignation number to indicate the beginning of the effectivity, and the second group corre-sponds to the last digits of the highest aircraft designation number to indicate the end of theeffectivity.

SERVICE BULLETINNUMBER

APM SECTIONNUMBER

INCORPORATIONDATE EFFECTIVITY

SB 170-53-0080/00 02-1 Oct 07/2014 170:00007-00029,00045-00047


LIST OF SERVICE BULLETINSPage 1 / 2

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TitleBLOCK PAGE REVISIONTRList

1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/072 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 22/07

SBList

* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 09/152 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/06

List of Effective Pages

* 1 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 09/15

* 2 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 09/15Table of Contents

1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/122 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/06

List of Tables1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/062 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/03

List of Figures1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/122 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/124 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/03

Section 11-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/061-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/111-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/111-4 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/03

Section 22-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/112-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/072-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/032-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/062-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/062-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/06

* 2-9 (rev) . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 09/152-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/082-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jun 29/062-15 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-16 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-17 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-18 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-19 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/042-20 (del) . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/04

Section 33-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/063-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/063-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/143-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/123-20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 31/12

Section 44-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/054-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/084-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/034-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/034-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/034-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/034-10 Blank . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/03

Section 55-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/035-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/035-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/035-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/035-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/035-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 11/075-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/115-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/115-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/115-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/115-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/115-14 Blank . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11

Section 6


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).

EFFECTIVITY: ALL LIST OF EFFECTIVE PAGESREV. 17 Page 1

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6-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/036-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/036-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/036-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/036-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/036-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/066-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/066-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 18/066-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 09/066-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/106-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/106-12 Blank . . . . . . . . . . . . . . . . . . . . . . . . Oct 07/10

Section 77-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/057-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/057-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/057-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/057-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/057-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/057-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jul 01/057-19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/037-21 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/117-22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/117-23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/117-24 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/117-25 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/117-26 Blank . . . . . . . . . . . . . . . . . . . . . . . . Oct 06/11

Section 88-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/038-2 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/03

Section 99-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/039-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/039-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/039-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/039-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/03

9-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 08/03


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 ............................................................................................ 2-32.3. Ground Clearances ......................................................................................................... 2-52.4. Interior Arrangement ........................................................................................................ 2-82.5. Passenger Cabin Cross Section ..................................................................................... 2-112.6. Lower Compartment Containers ...................................................................................... 2-132.7. Door Clearances ............................................................................................................. 2-14

SECTION 3 - AIRCRAFT PERFORMANCE

3. Aircraft Performance ....................................................................................................... 3-13.1. General Information ......................................................................................................... 3-13.2. Payload X Range ............................................................................................................ 3-23.3. Takeoff Field Lengths ...................................................................................................... 3-73.4. Landing Field Lengths ..................................................................................................... 3-16

SECTION 4 - GROUND MANEUVERING

4. Ground Maneuvering ....................................................................................................... 4-14.1. General Information ......................................................................................................... 4-14.2. Turning Radii ................................................................................................................... 4-14.3. Minimum Turning Radii ................................................................................................... 4-34.4. Visibility From Cockpit ..................................................................................................... 4-44.5. Runway and Taxiway Dimensions ................................................................................... 4-54.6. Runway Holding Bay ....................................................................................................... 4-9

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 .............................................................................. 5-115.8. Ground Towing Requirements ......................................................................................... 5-13


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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 ......................................................................................... 6-86.3. Hazard Areas .................................................................................................................. 6-9

SECTION 7 - PAVEMENT DATA

7. Pavement Data ............................................................................................................... 7-17.1. General Information ......................................................................................................... 7-17.2. Footprint .......................................................................................................................... 7-27.3. Maximum Pavement Loads ............................................................................................. 7-37.4. Landing Gear Loading on Pavement ............................................................................... 7-47.5. Flexible Pavement Requirements, U.S. Corps of Engineers Design Method .................. 7-57.6. Flexible Pavement Requirements, LCN Method .............................................................. 7-87.7. Rigid Pavement Requirements, Portland Cement Association Design Method ............... 7-117.8. Rigid Pavement Requirements, LCN Method .................................................................. 7-147.9. ACN - PCN System - Flexible and Rigid Pavements ...................................................... 7-19

SECTION 8 - POSSIBLE EMBRAER 170 DERIVATIVE AIRCRAFT

8. Possible EMBRAER 170 Derivative Aircraft .................................................................... 8-18.1. Not Applicable ................................................................................................................. 8-1

SECTION 9 - SCALED DRAWINGS

9. Scaled Drawings ............................................................................................................. 9-19.1. General ........................................................................................................................... 9-1


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LIST OF TABLES

TABLE TITLE SECTION PAGE

1.1 APM Arrangement .................................................................................. 01 1

2.1 Aircraft General Characteristics ............................................................. 02 2

2.2 Aircraft General Characteristics ............................................................. 02 2

2.3 Ground Clearance - STD Aircraft Model ................................................ 02 6

2.4 Ground Clearance - LR, SU or SE Aircraft Models ............................... 02 7

2.5 Capacity of the Cargo Compartment ..................................................... 02 10

3.1 ISA .......................................................................................................... 03 1

4.1 Reference Codes.................................................................................... 04 5

7.1 Pavement Evaluation.............................................................................. 07 19


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EFFECTIVITY: ALL LIST OF TABLESPage 1 / 2

Dec 18/06

LIST OF FIGURES

FIGURE TITLE SHEET SECTION PAGE

2.1 General Aircraft Dimensions ................................................. 02 4

2.2 Ground Clearances ............................................................... 02 5

2.3 Typical Interior Arrangements ............................................... 02 9

2.4 Economy Class Passenger Cabin Cross-Section................. 02 11

2.5 First Class Passenger Cabin Cross-Section......................... 02 12

2.6 Door Dimensions................................................................... 02 14

3.1 Payload x Range - ISA Conditions ....................................... 03 3

3.2 Payload x Range - ISA + 10 °C Conditions ......................... 03 4

3.3 Payload x Range - ISA Conditions ....................................... 03 5

3.4 Payload x Range - ISA + 10 °C Conditions ......................... 03 6

3.5 Takeoff Field Lengths - ISA Conditions ................................ 03 8

3.6 Takeoff Field Lengths - ISA + 15 °C Conditions................... 03 9







3.13 Landing Field Lengths - Flaps 5 ........................................... 03 17

3.14 Landing Field Lengths - Flaps Full ....................................... 03 18

3.15 Landing Field Lengths - Flaps 5 ........................................... 03 19

3.16 Landing Field Lengths - Flaps Full ....................................... 03 20

4.1 Turning Radii - No Slip Angle ............................................... 04 2

4.2 Minimum Turning Radius ...................................................... 04 3

4.3 Visibility from Cockpit in Static Position................................ 04 4

4.4 More than 90° Turn - Runway to Taxiway ............................ 04 6

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

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


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EFFECTIVITY: ALL LIST OF FIGURESPage 1

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

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

5.2 Aircraft Servicing Arrangement With Passenger Bridge ....... 05 3

5.3 Air Terminal Operation - Turnaround Station ........................ 05 5

5.4 Ground Servicing Connections ............................................. 05 7

5.5 Ground Servicing Connections ............................................. 05 8

5.6 Engine Starting Pneumatic Requirements ............................ 05 9

5.7 Ground Pneumatic Power Requirements ............................. 05 10

5.8 Preconditioned Airflow Requirements ................................... 05 12

5.9 Ground Towing Requirements............................................... 05 13

6.1 Jet Wake Velocity Profile - Takeoff Power ............................ 06 2

6.2 Jet Wake Temperature Profile - Takeoff Power .................... 06 3

6.3 Jet Wake Velocity Profile - Ground Idle................................ 06 4

6.4 Jet Wake Temperature Profile - Ground Idle ........................ 06 5

6.5 Jet Wake Velocity Profile - Breakaway Power...................... 06 6

6.6 Jet Wake Temperature Profile - Breakaway Power .............. 06 7

6.7 Hazard Areas - Takeoff Power .............................................. 06 9

6.8 Hazard Areas - Ground Idle .................................................. 06 10

6.9 Hazard Areas - Breakaway Power........................................ 06 11

7.1 Footprint ................................................................................ 07 2

7.2 Maximum Pavement Loads................................................... 07 3

7.3 Landing Gear Loading on Pavement .................................... 07 4

7.4 Flexible Pavement Requirements - US Army Corps of En-gineers Design Method ......................................................... 07 6

7.5 Flexible Pavement Requirements - US Army Corps of En-gineers Design Method ......................................................... 07 7

7.6 Flexible Pavement Requirements - LCN Method ................. 07 9

7.7 Flexible Pavement Requirements - LCN Method ................. 07 10

7.8 Rigid Pavement Requirements - Portland Cement Associa-tion Design Method ............................................................... 07 12


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EFFECTIVITY: ALL LIST OF FIGURESPage 2

Oct 31/12


7.9 Rigid Pavement Requirements - Portland Cement Associa-tion Design Method ............................................................... 07 13

7.10 Radius of Relative Stiffness .................................................. 07 15

7.11 Radius of Relative Stiffness (other values)........................... 07 16

7.12 Rigid Pavement Requirements - LCN Method ..................... 07 17

7.13 Rigid Pavement Requirements - LCN Method ..................... 07 18

7.14 ACN For Flexible Pavement ................................................. 07 20



7.17 ACN For Rigid Pavement...................................................... 07 23



9.1 Scale: 1 Inch Equals 32 Feet................................................ 09 2

9.2 Scale: 1 Inch Equals 50 Feet................................................ 09 3

9.3 Scale: 1 Inch Equals 100 Feet.............................................. 09 4

9.4 Scale: 1 to 500...................................................................... 09 5

9.5 Scale: 1 to 1000.................................................................... 09 6


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EFFECTIVITY: ALL LIST OF FIGURESPage 3 / 4

Oct 31/12

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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EFFECTIVITY: ALL Section 1

Page 1-1

Jan 09/06

• 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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Page 1-2

Oct 06/11

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

ACRONYMS AND ABBREVIATIONS DESCRIPTIONAPM Airport Planning ManualAPU Auxiliary Power UnitATTCS Automatic Takeoff-Thrust Control-SystemBOW Basic Operating WeightCBR California Bearing RatioECS Environmental Control SystemFAA Federal Aviation AdministrationFAR Federal Aviation RegulationsFWD 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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Page 1-3 / 4

Oct 06/11

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 CF34–8E with 63.2 kN (14200 lbf) maximum takeoffthrust (sea level, static and ISA + 15 °C) installed under the wings.The aircraft has two versions, with different ranges as a function of the difference between the MTOWs:

• The STD aircraft model - MTOW 35990 kg (79344 lb)

• The LR, SU or SE aircraft models - MTOW 37200 kg (82012 lb)

2.1.1. Definitions

MRW

It is the maximum allowed aircraft weight for taxiing or maneuvering on the ground.

MLW

It is the maximum allowed weight with which the aircraft can normally be landed.

MTOW

It is the maximum allowed total loaded aircraft weight at the start of the takeoff run.

BOW

It is the weight of the structure, powerplant, instruments, flight controls, hydraulic, electronic, electrical,air conditioning, oxygen, anti-icing and pressurization systems, interior furnishings, portable and emer-gency equipment and other items of equipment that are an integral part of the aircraft configuration. Italso includes unusable fuel, total engine and APU oil, total hydraulic fluid, toilet fluid and water, potablewater, crew and crew baggage, navigation kit (manuals, charts), catering (beverages and food) andremovable service equipment for the galley.

MZFW

It is the maximum allowed weight without usable fuel in the tanks.


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Page 2-1

Oct 07/08

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 CharacteristicsEFFECTIVITY: ON ACFT 170:00001-00006 00030-00044 00048-00058 00060-00065 OR PRE-MOD SB 170-53-0080

DESIGN WEIGHTS[1] AIRCRAFT MODELSSTD LR, SU or SE

MRW 36150 kg (79697 lb) 37360 kg (82365 lb)MTOW 35990 kg (79344 lb) 37200 kg (82012 lb)MLW 32800 kg (72311 lb)

BOW [2] 20700 kg (45636 lb)MZFW 29600 kg (65257 lb)

Maximum Payload [2] 9100 kg (20062 lb)MOW - Minimum Operating Weight 21800 kg (48060 lb)

Maximum Seating Capacity 78 passengers70 passengers (SE)76 passengers (SU)78 passengers (LR)

Maximum Cargo Volume [3] 14.39 m3 (508.18 ft3)UsableFuel [4]

9428 kg (20785 lb)11625 � (3071 gal.)

1. Applicable for standard models. For further information, refer to AFM and AOM.2. Standard configuration (weights may vary according to optional equipment installed or interior layouts).3. Standard configuration (volume may vary according to optional equipment installed).4. Adopted fuel density of 0.811 kg/� (6.77 lb/gal.).

Table 2.2 - Aircraft General CharacteristicsEFFECTIVITY: ON ACFT 170:00059-00059 00066-99999 OR POST-MOD SB 170-53-0080


MRW 36150 kg (79697 lb) 37360 kg (82365 lb)MTOW 35990 kg (79344 lb) 37200 kg (82012 lb)

1. Applicable for standard models. Forfurther information, refer to AFM and

AOM.


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Page 2-2

Oct 06/11

Table 2.2 - Aircraft General Characteristics (Continued)EFFECTIVITY: ON ACFT 170:00059-00059 00066-99999


MLW [2] 32800 kg (72311 lb)BOW [3] 20700 kg (45636 lb)MZFW 30140 kg (66447 lb)

MaximumPayload [3] 9640 kg (21252 lb)

MOW - Minimum Operating Weight 21800 kg (48060 lb)

Maximum Seating Capacity 78 passengers70 passengers (SE)76 passengers (SU)78 passengers (LR)

Maximum Cargo Volume [4] 14.39 m3 (508.18 ft3)UsableFuel [5]

9428 kg (20785 lb)11625 � (3071 gal.)

1. Applicable for standard models. For further information, refer to AFM and AOM.2. For aircraft POST-MOD. S.B. 170-00-0003, consider MLW = 33300 kg (73414 lb).3. Standard configuration (weights may vary according to optional equipment installed or interior layouts).4. Standard configuration (volume may vary according to optional equipment installed).5. Adopted fuel density of 0.811 kg/� (6.77 lb/gal.).

2.2. GENERAL AIRCRAFT DIMENSIONS

2.2.1. External Dimensions

• Span over winglets - 26.00 m (85 ft 4 in.)

• Height (maximum) - 9.85 m (32 ft 3 in.)

• Overall length - 29.90 m (98 ft 1 in.)

2.2.2. Wing

• Reference area - 72.72 m2 (783 ft2)

• Reference aspect ratio - 8.6

2.2.3. Fuselage

• Total Length - 29.90 m (98 ft 1 in.)

• Length of pressurized section - 22.74 m (74 ft 7 in.)

2.2.4. Horizontal Tail

• Span - 10.00 m (32 ft 9 in)

• Area - 23.25 m2 (250 ft2 37 in2)

2.2.5. Vertical Tail

• Reference area - 16.20 m2 (174 ft2 55 in2)


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Page 2-3

Oct 07/08

5.20 m(17 ft)

18.23 m(59 ft 9.7 in.)

6.82 m(22 ft 4.5 in.)

10.60 m(34 ft 9 in.)

29.90 m(98 ft 1 in.)

4.71 m(15 ft 5.4 in.)

21.26 m(69 ft 9 in.)

10.00 m(32 ft 9 in.)

26.00 m(85 ft 4 in.)

4.27 m(14 ft )

21.26 m(69 ft 9 in.)

4.13 m(13 ft 6 in.)

16.62 m(54 ft 6 in.)

9.85 m(32 ft 3 in.)

EM

170A

PM

0200

03C

.DG

N

General Aircraft DimensionsFigure 2.1


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Page 2-4

May 11/07

2.3. GROUND CLEARANCES

EM

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PM

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A

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Ground ClearancesFigure 2.2


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Page 2-5

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Page 2-6

Jan 09/06

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m

8ft

1in

.

9.62

m

31ft

7in

.12

.5

2180

0kg

4806

1lb

70

2.15

m

7ft

1in

.

2.58

m

8ft

6in

.

2.58

m

8ft

6in

.

1.52

m

4ft

11in

.

0.56

m

1ft

10in

.

4.62

m

15ft

2in

.

1.60

m

5ft

3in

.

2.59

m

8ft

6in

.

2.59

m

8ft

6in

.

9.83

m

32ft

3in

.13

.4

2180

0kg

4806

1lb

270.

42.

24m

7ft

5in

.

2.64

m

8ft

8in

.

2.63

m

8ft

7in

.

1.56

m

5ft

1in

.

0.57

m

1ft

10in

.

4.58

m

15ft

1.55

m

5ft

1in

.

2.52

m

8ft

3in

.

2.52

m

8ft

3in

.

9.71

m

31ft

10in

.12

.9


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Page 2-7

Jan 09/06

2.4. INTERIOR ARRANGEMENT

The interior arrangement provides accommodation for two pilots, one observer, two flight attendants,and 70 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 70 passengers in 17 double seats on the LH side, and 18 doubleseats on the RH side.As an option, the passenger cabin can be provided with double first-class seats on the RH side andsingle first-class seats on the LH side.The main dimensions of the passenger cabin are presented below:

• Height - 2.00 m (6 ft 7 in.)

• Width - 2.74 m (9 ft)

• Aisle width - 0.49 m (1 ft 7 in.)

• Pitch - 0.82 m (32 in.)


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Page 2-8

Jan 09/06

2 − WARDROBE

7 − AFT LAVATORY

9 − OVERHEAD BIN

11 − AIRSTAIR STOWAGE

OVERHEAD BIN

UNDERSEAT VOLUME

0.06 m / pax (2.0 ft / pax)

0.04 m / pax (1.4 ft / pax)

6 1 2

3 4 105

71

8

8

34 5

11

3

3

3

3

9

8 − CARGO COMPARTMENT

CARGO COMPARTMENT

10 − PASSENGER SEAT

3 − FWD RH G1 GALLEY

4 − FWD RH G2 GALLEY

5 − AFT RH GALLEY

6 − FWD LAVATORY

CARGO/BAGGAGE VOLUME

1 − FLIGHT ATTENDANT SEAT

1.82 m 2.41 m 1.85 m

14.39 m (508.18 ft )3 3

19.44 m(63 ft 9 in.)

5.41 m(17 ft 9 in.)

0.81 m(2 ft 8 in.)

(7 ft 11.4 in.)(5 ft 11.7 in)

0.90 m(2 ft 11.4 in.)

0.88 m(2 ft 10.6 in.)

0.78 m(2 ft 6.7 in.)

1.31 m

(4 ft 3.6 in.)

4.30 m(14 ft 1.3 in.)

EM

170A

PM

0200

04D

.DG

N

(6 ft 07 in.)

Typical Interior ArrangementsFigure 2.3


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Page 2-9

Oct 09/15

2.4.2. Cargo Compartments

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

Table 2.5 - Capacity of the Cargo Compartment

CARGO COMPARTMENT LOADING VOLUMEFWD [1] 1370 kg (3020 lb) 8.59 m3 (303.35 ft3)

AFT 1030 kg (2270 lb) 5.80 m3 (204.83 ft3)Total 2400 kg (5290 lb) 14.39 m3 (508.18 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;

• Door net at each cargo door.

2.4.3. Cockpit

The cockpit is acoustically and thermally insulated for appearance and durability. It follows the worldwidetrend of rounded edges to avoid harm to the flight crew.The cockpit is separated from the passenger cabin by a bulkhead provided with a lockable door. Thecockpit door has a locking system, which can only be opened from the cockpit side, a peep hole and anescape mechanism on the cockpit side.


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Page 2-10

Oct 07/08

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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Page 2-11

Dec 18/04

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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46


Page 2-12

Dec 18/04

2.6. LOWER COMPARTMENT CONTAINERS

Not applicable


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46


Page 2-13

Dec 18/04

2.7. DOOR CLEARANCES

1.36 m(4 ft 5.5 in.)

0.90 m(2 ft 11.4 in.)

0.87 m(2 ft 10 in.)

1.82 m(5 ft 11.6 in.)

0.78 m(2 ft 6.7 in.)

SEE FIGURE 2.2FOR HEIGHT ABOVEGROUND

EM

170A

PM

0200

08C

.DG

N

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

1.71 m(5 ft 7.3 in.)

1.37 m(4 ft 5.9 in.)

0.63 m(2 ft 0.8 in.)

0.99 m(3 ft 3 in.)

1.10 m(3 ft 7.3 in.)

0.61 m(2 ft 0 in.)

0.75 m(2 ft 6.7 in.)

0.63 m(2 ft 0.8 in.)

Door DimensionsFigure 2.6


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Page 2-14

Jun 29/06

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 apronounced 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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Page 3-1

Jan 09/06

3.2. PAYLOAD X RANGE

The payload x range charts are based on the following conditions;

• CF34 - 8E5 and CF34 - 8E5A1 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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Page 3-2

Jan 09/06

CF34 − 8E5A1 & − 8E5 ENGINESFLIGHT LEVEL 350

RESERVE : 100 nm ALTERNATE + 45 min FLIGHT

RANGE − nm

MAX TAKEOFF WEIGHTMAX ZERO FUEL WEIGHTBASIC OPERATING WEIGHTMAX USABLE FUEL

ISA

PAYLOAD VS RANGE

MTOW = 35990 kg (79344 lb)

NOTES:

1000

00

2000

3000

4000

5000

6000

7000

8000

9000

10000

500 1000 1500 2000 2500 3000

0.78 MACH

LONG RANGE

MAX CRUISE

PA

YLO

AD

− k

g

PA

YLO

AD

− lb

0

2000

1000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

15000

16000

17000

18000

19000

20000

21000

22000

70 PAX @ 100 kg

35990 kg (79344 lb)30140 kg (66447 lb)20736 kg (45715 lb)9428 Kg (20785 lb) E

M17

0AP

M03

0003

D.D

GN

Payload x Range - ISA ConditionsFigure 3.1


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46

EFFECTIVITY: EMBRAER 170 STD ACFTMODEL

Section 3

Page 3-3

Oct 31/12




PAYLOAD VS RANGE

ISA + 10°C

MTOW = 35990 kg (79344 lb)

NOTES:

1000

00

2000

3000

4000

5000

6000

7000

8000

9000

10000

PA

YLO

AD

− k

g

PA

YLO

AD

− lb

0

2000

1000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

15000

16000

17000

18000

19000

20000

21000

22000

500 1000 1500 2000 2500 3000

LONG RANGE

0.78 MACH

MAX CRUISE

70 PAX @ 100 kg

RANGE − nm

35990 kg (79344 lb)30140 kg (66447 lb)20736 kg (45715 lb)9428 Kg (20785 lb) E

M17

0AP

M03

0004

D.D

GN

Payload x Range - ISA + 10 °C ConditionsFigure 3.2


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Section 3

Page 3-4

Oct 31/12




ISA

PAYLOAD VS RANGE

MTOW = 37200 kg (82012 lb)

NOTES:37200 kg (82012 lb)

9428 Kg (20785 lb)

30140 kg (66447 lb)20736 kg (45715 lb)

RANGE − nm

1000

00

2000

3000

4000

5000

6000

7000

8000

9000

10000

PA

YLO

AD

− k

g

PA

YLO

AD

− lb

0

2000

1000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

15000

16000

17000

18000

19000

20000

21000

22000

500 1000 1500 2000 2500 3000

0.78 MACH

LONG RANGE

MAX CRUISE

70 PAX @ 100 kg

EM

170A

PM

0300

02D

.DG

N

Payload x Range - ISA ConditionsFigure 3.3


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46

EFFECTIVITY: EMBRAER 170 LR ACFT MODEL Section 3

Page 3-5

Oct 31/12


ISA + 10°CRESERVE : 100 nm ALTERNATE + 45 min FLIGHT


PAYLOAD VS RANGE

37200 kg (82012 lb)

MTOW = 37200 kg (82012 lb)

9428 Kg (20785 lb)

NOTES:

1000

00

2000

3000

4000

5000

6000

7000

8000

9000

10000

PA

YLO

AD

− k

g

PA

YLO

AD

− lb

0

2000

1000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

15000

16000

17000

18000

19000

20000

21000

22000

500 1000 1500 2000 2500 3000

MAX CRUISE

LONG RANGE

0.78 MACH

70 PAX @ 100 kg

RANGE − nm

30140 kg (66447 lb)20736 kg (45715 lb)

EM

170A

PM

0300

01C

.DG

N

Payload x Range - ISA + 10 °C ConditionsFigure 3.4


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46

EFFECTIVITY: EMBRAER 170 LR ACFT MODEL Section 3

Page 3-6

Oct 31/12

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 length 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 - 8E5 and CF34 - 8E5A1 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 + 15 °C conditions;

• Pack OFF: No engine bleed extraction for air conditioning packs was considered in the takeoff andlanding charts.


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Page 3-7

Oct 31/12

DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY ISA

FIE

LD L

EN

GT

H −

m

FIE

LD L

EN

GT

H −

ft

3000

5000

14000

4000

6000

8000

10000

12000

85000

WEIGHT − kg

WEIGHT − lb45000 49000 53000 57000 61000 65000 69000 73000 77000 81000

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

TAKEOFF FIELD LENGTH

AIRPORT PRESSUREALTITUDE m (ft)

SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000) 1219

(4000)

609(2000)

EM

170A

PM

0300

09H

.DG

N

CF 34−8E5 ENGINE@T/O−1 MODEATTCS: ON / ECS: OFF

Takeoff Field Lengths - ISA ConditionsFigure 3.5


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Page 3-8

Oct 07/14


DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY

ISA+15°CF

IELD

LE

NG

TH

− m

WEIGHT − kg

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

FIE

LD L

EN

GT

H −

ft

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

85000 WEIGHT − lb

45000 49000 53000 57000 61000 65000 69000 73000 77000 81000 89000 93000


SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000)

1219(4000)

609(2000)

EM

170A

PM

0300

13I.D

GN

CF 34−8E5 ENGINE@T/O−1 MODEATTCS: ON / ECS: OFF

Takeoff Field Lengths - ISA + 15 °C ConditionsFigure 3.6


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Page 3-9

Oct 07/14



FIE

LD L

EN

GT

H −

m

WEIGHT − kg

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

FIE

LD L

EN

GT

H −

ft

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

85000 WEIGHT − lb

45000 49000 53000 57000 61000 65000 69000 73000 77000 81000 89000 93000


SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000)

1219(4000)

609(2000)

EM

170A

PM

0300

94B

.DG

N

CF 34−8E5 ENGINE@T/O−1 MODEATTCS: OFF / ECS: OFF



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46


Page 3-10

Oct 07/14


DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAYF

IELD

LE

NG

TH

− m

WEIGHT − kg

ISA+15°C

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

FIE

LD L

EN

GT

H −

ft

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

85000 WEIGHT − lb

45000 49000 53000 57000 61000 65000 69000 73000 77000 81000 89000 93000


SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000)

1219(4000)

609(2000)

EM

170A

PM

0300

95B

.DG

N

CF 34−8E5 ENGINE@T/O−1 MODEATTCS: OFF / ECS: OFF



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46


Page 3-11

Oct 07/14



400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

FIE

LD L

EN

GT

H −

m

FIE

LD L

EN

GT

H −

ft

WEIGHT − kg

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

85000 WEIGHT − lb

45000 49000 53000 57000 61000 65000 69000 73000 77000 81000 89000 93000


SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000)

1219(4000)

609(2000)

EM

170A

PM

0300

05I.D

GN

CF 34−8E5A1 ENGINE@T/O−1 MODEATTCS: ON / ECS: OFF



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46


Page 3-12

Oct 07/14


DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAY

ISA+15°CF

IELD

LE

NG

TH

− m

WEIGHT − kg

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

FIE

LD L

EN

GT

H −

ft

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

FIE

LD L

EN

GT

H −

ft

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

85000 WEIGHT − lb

45000 49000 53000 57000 61000 65000 69000 73000 77000 81000 89000 93000


SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000)

1219(4000)

609(2000)

CF 34−8E5A1 ENGINE@T/O−1 MODEATTCS: ON / ECS: OFF

EM

170A

PM

0300

06I.D

GN



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46


Page 3-13

Oct 07/14



FIE

LD L

EN

GT

H −

m

WEIGHT − kg

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

FIE

LD L

EN

GT

H −

ft

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

85000 WEIGHT − lb

45000 49000 53000 57000 61000 65000 69000 73000 77000 81000 89000 93000


SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000)

1219(4000)

609(2000)

EM

170A

PM

0300

96B

.DG

N

CF 34−8E5A1 ENGINE@T/O−1 MODEATTCS: OFF / ECS: OFF



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46


Page 3-14

Oct 07/14


DRY, SMOOTH, HARD PAVED AND LEVEL RUNWAYF

IELD

LE

NG

TH

− m

WEIGHT − kg

ISA+15°C

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

20000 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 42000

FIE

LD L

EN

GT

H −

ft

3000

5000

10000

4000

6000

7000

2000

8000

9000

11000

12000

13000

85000 WEIGHT − lb

45000 49000 53000 57000 61000 65000 69000 73000 77000 81000 89000 93000

SEA LEVEL

FLAP 4FLAP 4

FLAP 2

FLAP 1

3048(10000)

−570(−1870)

2438(8000)

1829(6000)

1219(4000)

609(2000)


CF 34−8E5A1 ENGINE@T/O−1 MODEATTCS: OFF / ECS: OFF

EM

170A

PM

0300

97B

.DG

N



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46


Page 3-15

Oct 07/14

3.4. LANDING FIELD LENGTHS

The landing field length charts provide data about the maximum landing weights, for compliance with theoperating regulations relating to landing field lengths.Data are presented according to the following associated conditions:

• Landing gear: down;

• Flaps setting position: 5 and 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;

• For EASA Certification, Landing Field Lengths are factored as per EU OPS 1.515 (a) (1) - Landing;

• For FAA Certification, Landing Field Lengths are factored as per FAR Part 121, Paragraph 121.195(b) - Airplanes.


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Page 3-16

Oct 31/12

DRY, SMOOTH, HARD PAVED AND LEVELLED RUNWAYFLAP 5

LANDING FIELD LENGTH

8500035000 40000

3000

3500

4000

4500

5000

45000 50000 55000 60000 65000 70000 75000 80000

WEIGHT − kg

WEIGHT − lb

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

ft

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

m

5500

6000

4000015000 20000 25000 30000 35000900

1100

1300

1500

WEIGHT − kg

1700

SEA LEVEL

1900

100020

003000

5000

6000

8000

9000

1000

0

7000

4000

−1000

−1870


3400

0 kg

(74

957

lb)

EM

170A

PM

0300

14H

.DG

N

Landing Field Lengths - Flaps 5Figure 3.13


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EFFECTIVITY: FAA-CERTIFIED ACFT Section 3

Page 3-17

Oct 31/12

DRY, SMOOTH, HARD PAVED AND LEVELLED RUNWAY

FLAPS FULL


8500035000 40000 45000 50000 55000 60000 65000 70000 75000 80000

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

ft

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

m

WEIGHT − kg

WEIGHT − lb

4000015000 20000 25000 30000 35000800

1000

1200

1400

1600

5000

4500

4000

3500

3000

5500

EM

170A

PM

0300

15G

.DG

N

1000

0

9000

8000

7000

6000

5000

4000

3000

2000

1000

SEA LEVEL

−1000

−1870


3400

0 kg

(74

957

lb)

Landing Field Lengths - Flaps FullFigure 3.14


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EFFECTIVITY: FAA-CERTIFIED ACFT Section 3

Page 3-18

Oct 31/12


FLAP 5


35000 45000 50000 600005500040000 65000 7500070000

3000

3500

4000

4500

5000

5500

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

ft

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

m

WEIGHT − kg

WEIGHT − lb

4000015000 20000 25000 30000 35000900

1100

1300

1500

1700

1900

3400

0 kg

(74

957

lb)

EM

170A

PM

0300

28D

.DG

N

1000

0

9000

8000

7000

6000

5000

4000

3000

2000

1000

SEA LEVEL

−1000

−1870


Landing Field Lengths - Flaps 5Figure 3.15


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EFFECTIVITY: EASA-CERTIFIED ACFT Section 3

Page 3-19

Oct 31/12


FLAPS FULL


EM

170A

PM

0300

29D

.DG

N

80000 8500035000 45000 50000 600005500040000 65000 7500070000

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

ft

FA

R L

AN

DIN

G R

UN

WA

Y L

EN

GT

H −

m

WEIGHT − lb

WEIGHT − kg

5000

4500

4000

3500

3000

5500

2000

4000

4000015000 20000 25000 30000 35000800

1000

1200

1400

1600


SEA LEVEL1000

3000

5000

6000

8000

9000

1000

0

7000

−1000

−187034

000

kg (

7495

7 lb

)

Landing Field Lengths - Flaps FullFigure 3.16


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EFFECTIVITY: EASA-CERTIFIED ACFT Section 3

Page 3-20

Oct 31/12

4. GROUND MANEUVERING


This section provides the aircraft turning capability and maneuvering characteristics. To facilitate thepresentation, the 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 a guideline for the method of determining such parameters and for themaneuvering characteristics of the aircraft.In the ground operating mode, varying airline practices may demand that more conservative turningprocedures be adopted, to avoid excessive tire wear and reduce possible maintenance problems.Variations from standard aircraft operating patterns may be necessary to satisfy physical constraintswithin the maneuvering area, such as adverse grades, limited area, or high risk of jet blast damage. Forthese reasons, the ground maneuvering requirements should be coordinated with the airline before thelayout is planned.This section is presented as follows:

• The turning radii for nose landing gear steering angles.

• The pilot’s visibility from the cockpit and the limits of ambinocular vision through the windows.Ambinocular vision is defined as the total field of vision seen by both eyes at the same time.

• The performance of the aircraft on runway-to-taxiway, taxiway-to-taxiway and runway holding baydimensions.

4.2. TURNING RADII

This subsection presents the following information:

• The turning radii for various nose landing gear steering angles. The minimum turning radius isdetermined, considering the maximum nose landing gear steering angle as 76 degrees left and right.

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


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Page 4-1

Oct 07/08

R3

R5 R6

R1

76°70°65°60°

55°50°

40°35°

R2

R4

45°

R 10.97 m(35 ft 11 in.)

R 5.28 m(17 ft 4 in.)

NOTE:

EM

170A

PM

0400

07C

.DG

N

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

STEERINGSTEEL

NOSE

R1 R2

OUTBOARD GEAR

R3 R4

INBOARD GEAR RIGHT WINGLET

R5

RIGHT TAILTIP

R6

NOSE LANDINGGEAR

21.19 m

19.47 m

18.21 m

17.26 m

63 ft 10 in.

36 ft 11 in.

51 ft 10 in.

22 ft 11 in.

6 ft 0 in.

2 ft 5 in. 56 ft 10 in.

62 ft 11 in.

57 ft 11 in.

16.55 m

16.00 m

15.58 m

15.28 m

15.02 m

18.76 m

16.78 m

15.28 m

14.14 m

13.25 m

12.55 m

12.01 m

11.60 m

11.25 m

24.91 m

22.92 m

21.38 m

20.17 m

19.18 m

18.35 m

17.66 m

17.07 m

16.48 m

28.45 m

25.98 m

23.96 m

22.28 m

20.83 m

19.54 m

18.39 m

17.33 m

16.17 m

18.31 m

15.80 m

13.76 m

12.05 m

10.57 m

9.26 m

8.08 m

6.99 m

5.80 m

12.06 m

9.55 m

7.51 m

5.80 m

4.32 m

3.02 m

1.84 m

0.75 m

35°

40°

45°

50°

55°

60°

65°

70°

76°

69 ft 6 in.

59 ft 9 in.

56 ft 8 in.

54 ft 3 in.

52 ft 6 in.

51 ft 2 in.

50 ft 1 in.

49 ft 3 in.

61 ft 6 in.

55 ft 0 in.

50 ft 2 in.

46 ft 5 in.

43 ft 6 in.

41 ft 2 in.

39 ft 5 in.

38 ft 1 in.

60 ft 1 in.

45 ft 2 in.

39 ft 6 in.

34 ft 8 in.

30 ft 5 in.

26 ft 6 in.

19 ft 0 in.

39 ft 7 in.

31 ft 4 in.

24 ft 8 in.

19 ft 0 in.

14 ft 2 in.

9 ft 11 in.

93 ft 5 in.

85 ft 3 in.

78 ft 7 in.

73 ft 1 in.

68 ft 4 in.

64 ft 1 in.

60 ft 4 in.

53 ft 1 in.

81 ft 9 in.

75 ft 2 in.

70 ft 2 in.

66 ft 2 in.

60 ft 3 in.

56 ft 0 in.

54 ft 1 in.1 ft 5.5 in.0.445 m

Turning Radii - No Slip AngleFigure 4.1


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Page 4-2

Oct 07/08

4.3. MINIMUM TURNING RADII

76°

STEERINGANGLE

NOSE

R1

36 ft 11 in.76° 15.02 m

R2

11.25 m

OUTBOARD GEAR

R3

RIGHT WINGLET

R5

RIGHT TAILTIP

R6

16.48 m16.17 m5.80 m

R6R5

R3

R1

R217.05 m(55 ft 11 in.)

(RUNWAY MINIMUM WIDTH)

R 10.97 m(35 ft 12 in.)

NOSE LANDINGGEAR

R 5.28 m(17 ft 4 in.)

49 ft 3 in. 19 ft 0 in. 53 ft 1 in. 54 ft 1 in.

NOTE:

1

1

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

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

M17

0AP

M04

0001

A.D

GN

Minimum Turning RadiusFigure 4.2


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Page 4-3

Oct 07/08

4.4. VISIBILITY FROM COCKPIT

VISUAL ANGLE IN PLANEPARALLEL TO LONGITUDINALAXIS THROUGH PILOT’S EYEPOSITION

27.8°

15°

REF. GROUND (BOW)

PILOT’S EYE POSITION

PILOT’S EYE POSITIONMAXIMUM AFT VISIONWITH HEAD ROTATEDABOUT SPINAL COLUMN

VISUAL ANGLE IN PLANEPERPENDICULAR TO LONGITUDINALAXIS THROUGH PILOT’S EYE POSITION

PILOT’S EYE POSITION

120.6°

27.5°

28.1°

L FUS HORC

3.91 m(12 ft 10 in.)

0.75 m(2 ft 6 in.)

2.92 m(9 ft 7 in.)

14.58 m(47 ft 10 in.)

0.53 m(1 ft 9 in.)

0.53 m(1 ft 9 in.)

EM

170A

PM

0400

06C

.DG

N

Visibility from Cockpit in Static PositionFigure 4.3


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Page 4-4

Jul 01/05

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)

__ __ 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 170STD and 170LR is 3C.

NOTE:• Classification considering CF34-8E5A1 engines.• This classification may change depending on aircraft engine model and takeoff weight.

With the reference code it is possible to obtain the limits of the runway and taxiway where the aircraftcan be operated. For reference code 3C the limits are:

• The width of a runway should not be less than 30 m (98 ft 5 in).

• The width of a taxiway should not be less than 15 m (49 ft 2 in).

• The design of the curve in a taxiway should be such that, when the cockpit remains over the taxiwaycenter line marking, the clearance distance between the outer main landing gear wheels of theaircraft and the edge of the taxiway should not be less than 3 m (9 ft 10 in).

• The clearance between a parked aircraft and one moving along the taxiway in a holding bay shouldnot be less than 15 m (49 ft 3 in).


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Page 4-5

Oct 07/08

EM

170A

PM

0400

02.D

GN

COORDINATE WITH AIRLINE OPERATORFOR THE SPECIFIC PLANNED OPERATINGPROCEDURE.

45°

100 ft Radius(30 m)

NOTE:

PATH OF MAIN LANDINGGEAR TIRE EDGE

NOSE LANDING GEAR STEERING ANGLE ISAPPROXIMATELY 15.

30 m(98 ft 5 in.)

15 m (49 ft 2 in.)

More than 90° Turn - Runway to TaxiwayFigure 4.4


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Page 4-6

Dec 08/03

EM

170A

PM

0400

03.D

GN


90°

100 ft Radius(30 m)

100 ft Radius(30 m)

NOTE:

PATH OF MAIN LANDINGGEAR TIRE EDGE.


30 m(98 ft 5 in.)

15 m(49 ft 2 in.)

90° Turn - Runway to TaxiwayFigure 4.5


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Page 4-7

Dec 08/03

EM

170A

PM

0400

04.D

GN


90°

100 ft Radius(30 m)

NOTE:



15 m(49 ft 2 in.)

15 m(49 ft 2 in.)

3 m(9 ft 10 in.)

90° Turn - Taxiway to TaxiwayFigure 4.6


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Page 4-8

Dec 08/03

4.6. RUNWAY HOLDING BAY

EM

170A

PM

0400

05.D

GN

RUNWAY

TAXIWAY

75 m(246 ft)



30 m(98 ft 5 in.)

MINIMUMCLEARENCES

15 m(49 ft 2 in.)

3 m(9 ft 10 in.)

3 m(9 ft 10 in.)

15 m(49 ft 2 in.)

Runway Holding BayFigure 4.7


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Page 4-9 / 10

Dec 08/03

5. TERMINAL SERVICING

During turnaround at the air terminal, certain services must be performed on the aircraft, usually withina given time to meet flight schedules. This section shows service vehicle arrangements, schedules,locations of servicing points, and typical servicing requirements. The data presented herein reflect idealconditions for a single aircraft. Servicing requirements may vary according to the aircraft condition andairline operational (servicing) procedures.This section provides the following information:

• The typical arrangements of equipment during turnaround;

• The typical turnaround servicing time at an air terminal;

• The locations of ground servicing connections in graphic and tabular forms;

• The typical sea level air pressure and flow requirements for starting the engine;

• The air conditioning requirements;

• The ground towing requirements for various towing conditions. Towbar pull and total traction wheelload may be determined by considering aircraft weight, pavement slope, coefficient of friction, andengine idle thrust.


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Page 5-1

Dec 08/03

5.1. AIRCRAFT SERVICING ARRANGEMENT

0 5 10 15 20 25 30 35 40

0 10 20 30 5040 60 70 80 90 100 110 120 130

0 0

10

20

30

40

50

60

70

80

90

110

100

5

10

15

20

25

30

02 − PASSENGER STAIRS

SERVICING ARRANGEMENT

07 − POTABLE WATER

2

109

2

7

8

44 6

5

33

5

LENGTH − m

LENGTH − ft

LEN

GT

H −

ft

LEN

GT

H −

m

35

06 − FUEL SERVICE

EM

170A

PM

0500

01.D

GN

03 − CARGO LOADER

11

11 − GROUND POWER UNIT

04 − BAGGAGE / CARGO TROLLEY AND TUG

05 − GALLEY SERVICE VEHICLE

08 − LAVATORY SERVICE VEHICLE

09 − AIR CONDITIONING UNIT

10 − PNEUMATIC STARTER

Aircraft Servicing Arrangement With Passenger StairsFigure 5.1


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Page 5-2

Dec 08/03

0 5 10 15 20 25 30 35 40

0 10 20 30 5040 60 70 80 90 100 110 120 130

0 0

10

20

30

40

50

60

70

80

90

110

100

5

10

15

20

25

30

01 − PASSENGER BRIDGE

SERVICING ARRANGEMENT

06 − FUEL SERVICE

7

8

44

6

5

33

5

LENGTH − m

LENGTH − ft

LEN

GT

H −

ft

LEN

GT

H −

m

35

1

07 − POTABLE WATER

03 − CARGO LOADER

109

05 − GALLEY SERVICE VEHICLE

08 − LAVATORY SERVICE VEHICLE

09 − AIR CONDITIONING UNIT

04 − BAGGAGE / CARGO TROLLEY AND TUG

10 − PNEUMATIC STARTER

EM

170A

PM

0500

02.D

GN

Aircraft Servicing Arrangement With Passenger BridgeFigure 5.2


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Page 5-3

Dec 08/03

5.2. TERMINAL OPERATIONS - TURNAROUND STATION

This section presents the typical turnaround servicing time at an air terminal. The chart gives typicalschedules for servicing the aircraft within a given time.The time of each service in the chart was calculated taking the following into consideration:

• Load factor - 100%;

• Passenger deplane - 24 pax/min;

• Passenger enplane - 16 pax/min;

• Baggages checked per passenger - 1,2;

• Refuel (fuel quantity) - 80%;

• Flow - 290 gpm;

• Potable water - 70% to be refilled (56 �);

• Galley service FWD and aft sequence - in parallel;

• Toilet type - vacuum;

• Baggages unloading/loading FWD/aft sequence - in parallel;

• Only FWD passenger door to be used to deplane and enplane passengers.

Servicing times could be rearranged to suit availability of personnel, aircraft configuration, and degree ofservicing required.The data illustrates the general scope and tasks involving airport terminal operations. Airline particularpractices and operating experience will result in different sequences and intervals.


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Page 5-4

Dec 08/03

min.

5

OPERATIONS

ELAPSED TIME(MINUTES)

6,0

FWD BAGGAGE/CARGO LOAD

AIRCRAFTSERVICING

FUEL SERVICE

POTABLE WATER SERVICE

TOILET SERVICE

TRUCK POSITIONING/REMOVAL/SETTINGS

1 3 7 9 11 13 17 19

GALLEY SERVICING−AFT

AFT BAGGAGE/CARGO LOAD

PAXSERVICES

1,0

GALLEY SERVICING−FWD 6,0

PASSENGERS DEPLANE 2.9

AIRPLANE INTERIOR SERVICES

PASSENGERS ENPLANE

4,4

4,4

BRIDGE / STAIRS REMOVAL 1,0

2,0PUSH BACK / ENGINES START

2 4 8 10 126 14 15 16 18 20

FWD BAGGAGE / CARGO UNLOAD

REAR BAGGAGE / CARGO UNLOAD

TIME BETWEEN UNLOADING / LOADINGBAGGAGE& CARGO

5,0

3,0

8,5

3,7

5,5

0,5

2,2

3,4

LEGEND:

NOTE:

BRIDGE/STAIRS POSITIONING

EM

170A

PM

0500

03B

.DG

N

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

Air Terminal Operation - Turnaround StationFigure 5.3


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Page 5-5

May 11/07

5.3. TERMINAL OPERATIONS - EN ROUTE STATION

Not Applicable


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Page 5-6

Dec 08/03

5.4. GROUND SERVICING CONNECTIONS

3

12

20

14

1

4

5

6

7

8

9

10

11

13

15

16

17

18

19

21

22

2

EM

170A

PM

0500

05D

.DG

N

ITEM DESCRIPTIONCOORD. Y

(mm)COORD. Z

(mm)COORD. X

(mm)

HEIGHTABOVE

GROUND(mm)

EXTERNAL POWER SUPPLY 115 VAC

GRAVITY REFUELING PORT (RH)

GRAVITY REFUELING PORT (LH)

WHEEL JACK POINT− MLG (LH)

WHEEL JACK POINT− MLG (RH)

FUEL TANK DRAIN VALVE (LH)

FUEL TANK DRAIN VALVE (RH)

HYD. SYS # 1 SERVICE PANEL


FORWARD RAMP HEADSET

STEERING SWITCH DISENGAGE

AIR COND. GROUND CONNECTION

GROUNDING POINT (ELECTRICAL)

WATER SERVICING PANEL

WASTE SERVICING PANEL


AFT RAMP HEADSET

WHEEL JACK POINT − NLG

PRESSURE REFUELING PANEL

OXYGEN SERVICING PANEL / BOTTLE

ENGINE AIR STARTING (LOW PRESSURE UNIT)

13491.27

14789.49

14789.49

4146.90

4164.44

4136.97

4121.90

10487.32

10778.80

14592.10

14476.67

16560.17

16560.17

21524.83

24084.65

24225.26

6562.14

13352.80

22447.01

24061.86

14476.67

5702.96

7413.99

−7413.99

−810.70

−936.13

−951.46

0.00

80.00

4.28

2560.25

2600.00

−808.01

808.01

−329.37

−471.73

−449.47

1159.87

398.47

−398.47

349.20

519.15

−1262.71

−585.54

−623.30

−243.75

−243.75

−1339.53

−1279.29

−2877.81

−1979.71

−2010.20

−1343.60

−2679.11

−1602.04

−1602.04

−1178.74

−605.30

−961.05

−1413.71

−1413.71

−991.80

−590.09

2469.26

2848.49

217.06

413.20

2848.49

1755.33

1815.58

1113.60

1083.03

1748.70

−2600.00 −2679.11 413.20

1489.76

1489.76

2499.87

2098.55

2484.65

2504.39

1911.84

2133.22

1678.89

1678.8913352.80

NOTE:

3

1 2

12

14

19

45

67

89

10 11 13 15

16 17

18

20

21

22

1832.15

EXTERNAL POWER SUPPLY 28 VDC

THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 21800 kg (CG FWD 7.0% CMA)

Ground Servicing ConnectionsFigure 5.4


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Page 5-7

May 11/07

3

12

20

14

1

4

5

6

7

8

9

10

11

13

15

16

17

18

19

21

22

2

ITEM DESCRIPTIONCOORD. Y

(mm)COORD. Z

(mm)COORD. X

(mm)

HEIGHTABOVE

GROUND(mm)


GRAVITY REFUELING PORT (RH)

GRAVITY REFUELING PORT (LH)

WHEEL JACK POINT− MLG (LH)

WHEEL JACK POINT− MLG (RH)

FUEL TANK DRAIN VALVE (LH)

FUEL TANK DRAIN VALVE (RH)



FORWARD RAMP HEADSET

STEERING SWITCH DISENGAGE

AIR COND. GROUND CONNECTION

GROUNDING POINT (ELECTRICAL)

WATER SERVICING PANEL



AFT RAMP HEADSET

WHEEL JACK POINT − NLG

PRESSURE REFUELING PANEL

OXYGEN SERVICING PANEL / BOTTLE

ENGINE AIR STARTING (LOW PRESSURE UNIT)

13491.27

14789.49

14789.49

4146.90

4164.44

4136.97

10487.32

10778.80

14592.10

16560.17

16560.17

21524.83

24084.65

24225.26

6562.14

13352.80

22447.01

24061.86

5702.96

7413.99

−7413.99

−810.70

−936.13

−951.46

0.00

80.00

4.28

2600.00

−808.01

808.01

−329.37

−471.73

−449.47

1159.87

398.47

−398.47

349.20

519.15

−1262.71

−585.54

−623.30

−243.75

−243.75

−1339.53

−1279.29

−1979.71

−2010.20

−1343.60

−1602.04

−1602.04

−1178.74

−605.30

−961.05

−1413.71

−1413.71

−991.80

−590.09

−2600.00

13352.80

NOTE:

3

1 2

12

14

19

45

67

89

10 11 13 15

16 17

18

20

21

22

1896.25


EM

170A

PM

0500

06A

.DG

N

2461.54

2830.76

2830.76

1819.58

4112.77 −2942.27 217.16

1129.04

1096.23

2560.25 1732.52

14475.49 −2662.17 414.90

14475.49 −2662.17 414.90

1458.44

1458.44

1842.28

2395.36

2414.01

2178.86

1672.25

1672.25

2021.88

2410.75

1879.90

THE GROUND CLEARANCES IN THE TABLE REFER TO THE AIRCRAFT WITH THE MINIMUMOPERATING WEIGHT (MOW) = 21800 kg (CG REAR 27.0% CMA)

Ground Servicing ConnectionsFigure 5.5


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Page 5-8

May 11/07

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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Page 5-9

Oct 06/11

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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Page 5-10

Oct 06/11

5.7. PRECONDITIONED AIRFLOW REQUIREMENTS

This subsection presents the following information:

• The air conditioning requirements for heating and cooling using ground conditioned air. The curvesshow airflow requirements to heat or cool the aircraft at ambient conditions within a given time.

• The air conditioning heating and cooling requirements to maintain a constant cabin air temperatureusing low-pressure conditioned air. This conditioned air is supplied through a ground air connectiondirectly to the passenger cabin, bypassing the air cycle machines.


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Page 5-11

Oct 06/11

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:

TO

TA

L A

IRF

LOW

1

5

10

12

16

1

2

3

4

5

6

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

0069

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.

MAXIMUM ALLOWABLE TEMPERATURE 88°C (190°F)(UPPER LIMIT DURING PULL UP OPERATION). MAXIMUM ALLOWABLE PRESSURE AT GROUNDCONNECTION 203mmH20 (8 INCHES OF WATER).

Preconditioned Airflow RequirementsFigure 5.8


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Page 5-12

Oct 06/11

5.8. GROUND TOWING REQUIREMENTS

1000

(220

4)

3000

(661

4)

2000

(440

9)

1000

(220

4)20

00(4

409)

3000

(661

4)40

00(8

818)

5000

(110

23)

NU

MB

ER

OF

EN

GIN

ES

BA

CK

ING

AG

AIN

ST

IDLE

TH

RU

ST

− 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

3800

0 (8

3775

)

3600

0 (7

9366

)

3400

0 (7

4957

)

3200

0 (7

0547

)

3000

0 (6

6138

)

2800

0 (6

1729

)

2600

0 (5

7320

)

2400

0 (5

2910

)

2200

0 (4

8501

)

2000

0 (4

4092

)

AIRCRAFT

GRO

SS WEIG

HT −

kg (l

b)

NO

TE

S:

GR

OU

ND

TO

WIN

G R

EQ

UIR

EM

EN

TS

00

10

12

34

50

2

TOWBAR PULL − kg (lb)

WET ASPHALT =0.75

WET C

ONCRETE =

0.57

SNOW

CHAIN

S =

0.45

HA

RD

SN

OW

=

0.2

ICE

=

0.05

PE

RC

EN

T S

LOP

E (

%)

REFERENCE LINE

DRY CONCRETE OR

ASPHALT =0.8

EM

170A

PM

0500

04A

.DG

N

TO

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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Page 5-13 / 14

Oct 06/11

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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Page 6-1

Dec 08/03

6.1. ENGINE EXHAUST VELOCITIES AND TEMPERATURES

EM

170M

FE

P01

0005

.DG

N

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

ABCDEF

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

Meters


TAKEOFF POWER, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 63685 N (14317 lbf)

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

15.2 (50)30.5 (100)60.9 (200)121.9 (400)243.8 (800)457.2 (1500)

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

Jet Wake Velocity Profile - Takeoff PowerFigure 6.1


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Page 6-2

Dec 08/03

EM

170M

FE

P01

0006

.DG

N

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


TAKEOFF POWER, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 63685 N (14317 lbf)

ABCDE

°F100150200400900

TOTAL TEMPERATUREMAX = 689°C (1273°F)

°C386693204582

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

Jet Wake Temperature Profile - Takeoff PowerFigure 6.2


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46


Page 6-3

Dec 08/03

EM

170M

FE

P01

0007

.DG

N

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


Meters


GROUND IDLE, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 3785 N (851 lbf)

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

(50)(100)(150)(250)

15.230.545.776.2


Jet Wake Velocity Profile - Ground IdleFigure 6.3


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46


Page 6-4

Dec 08/03

EM

170M

FE

P01

0008

.DG

N

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


Meters

Met

ers

DIS

TA

NC

E F

RO

M A

IRP

LAN

E C

L −

Fee

t


Meters

GROUND IDLE, SEA LEVEL, Tamb = ISA +16.7°C, FNIN1 = 3785 N (851 lbf)

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

Jet Wake Temperature Profile - Ground IdleFigure 6.4


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Page 6-5

Dec 08/03

VELOCITY m/s (ft/s)MAX = 230.8 (757.3)


6

15

5

20

Meters

Met

ers

523010

B

C

D

30

25

20

15

10

5

00

2

4

6

8

10

10 15 20 25 30 35 40 45 50 55 600 4


Meters

A

181614121086420

DIS

TA

NC

E F

RO

M A

IRP

LAN

E C

L −

Fee

tH

EIG

HT

AB

OV

E G

RO

UN

D P

LAN

E, F

eet

0

10

0 20 40 60

0 2 4 6 8 10 12 14 16 18

A

B

C

D


0

1

2

3

4

5

C

EM

170A

PM

0600

06A

.DG

N

Met

ers

ABCD

15.2 (50)30.5 (100)60.9 (200)121.9 (400)

Jet Wake Velocity Profile - Breakaway PowerFigure 6.5


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Page 6-6

Jan 09/06

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

0 2 4 6 8 10 12 14 16 18

0

5

10

15

20

0

1

2

3

4

5

6

Met

ers

HE

IGH

T A

BO

VE

GR

OU

ND

PLA

NE

− F

eet

F E D

C

B A


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

0 2 4 6 8 10 12 14 16 18


Meters

0

5

10

15

20

0

2

4

6

HE

IGH

T A

BO

VE

GR

OU

ND

PLA

NE

− F

eet

F

E

D C B

A

ABCDEF

NOTE:

EM

170A

PM

0600

07A

.DG

N

Met

ers

Meters

EXHAUST TEMPERATURE CONTOURS INCLUDE WORST CASE 20 kn HEADWIND WITH GROUND EFFECTS.

TOTAL TEMPERATUREMAX = 495 °C (923 °F)

386693121149177

°C °F100150200250300350

Jet Wake Temperature Profile - Breakaway PowerFigure 6.6


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Page 6-7

Jan 09/06

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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Page 6-8

Dec 18/06

6.3. HAZARD AREAS

R=4.3 m(14 ft)

1.8 m(6 ft)

TAKEOFF POWER, SEA LEVEL, Tamb = ISA +16.7° C, FNIN1 = 63685 N (14317 lbf)

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

NOTE:

2

2

1

132 m(433 ft)

1

EXHAUST HAZARD AREA − CONDITION: 20 kn HEADWIND WITH GROUND EFFECTS.

INLET HAZARD AREA − CONDITION: 20 kn HEADWIND/CROSSWIND BASED ON 12.2 m/s(40 ft/s) CRITICAL VELOCITY WITH 0.9 m (3 ft) CONTINGENCY FACTOR.

NO ACCESS TO ENGINE ACCESSORIES AT TAKEOFF POWER.

EM

170M

FE

P01

0001

A.D

GN

Hazard Areas - Takeoff PowerFigure 6.7


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Page 6-9

Jan 09/06

26 m(86 ft)

2.6 m(8.6 ft)R=2.5 m

(8.3 ft)

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

2

1

1

2

EXHAUST HAZARD AREA − CONDITION: 20 kn HEADWIND WITH GROUND EFFECTS.

INLET HAZARD AREA − CONDITION: 20 kn HEADWIND/CROSSWIND/TAILWIND BASED ON 12.2 m/s (40 ft/s) CRITICAL VELOCITY WITH 0.9 m (3 ft) CONTINGENCY FACTOR.

GROUND IDLE, SEA LEVEL, Tamb = ISA+16.7° C, FNIN1 = 3785 N (851 lbf)

EM

170M

FE

P01

0002

A.D

GN

Hazard Areas - Ground IdleFigure 6.8


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Page 6-10

Oct 07/10

NOTE:

2

2

1

121 m(397 ft)

1

1.8 m(6.0 ft)

Eng

ine

Exh

aust

Haz

ard

Are

aV

eloc

ity =

65

MP

H o

r gr

eate

r=

29.

0 M

/sec

(95

.3 ft

/sec

)

R= 4.3 m(14.0 ft)

NO ACCESS TO ENGINE ACCESSORIES AT BREAKAWAY POWER.

EXHAUST HAZARD AREA − CONDITION: 20 knot HEADWIND WITH GROUND EFFECTS.

INLET HAZARD AREA − CONDITION: 20 knot HEADWIND/CROSSWIND BASED ON 40 ft/secCRITICAL VELOCITY WITH 0.9 m (3 ft) CONTINGENCY FACTOR. E

M17

0AP

M06

0011

A.D

GN

BREAKAWAY POWER, SEA LEVEL, Tamb = ISA +16.7° C, FNIN1 = 2328 DAN (5233 lbf)

Hazard Areas - Breakaway PowerFigure 6.9


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Page 6-11 / 12

Oct 07/10

7. PAVEMENT DATA


Pavement is defined as a structure consisting of one or more layers of processed materials.The primary function of a pavement is to distribute concentrated loads so that the supporting capacity ofthe subgrade soil is not exceeded. The subgrade soil is defined as the material on which the pavementrests, whether embankment or excavation.Several methods for design of airport pavements have been developed that differ considerably in theirapproach.The design methods are derived from observation of pavements in service or experimental pavements.Thus, the reliability of any method is proportional to the amount of experimental verification behind themethod, and all methods require a considerable amount of common sense and judgment on the part ofthe engineer who applies them.A brief description of the following pavement charts will be helpful in their use for airport planning. Eachaircraft configuration is depicted with a minimum range of five loads imposed on the main landing gearto aid in the interpolation between the discrete values shown. The tire pressure used for the aircraftcharts will produce the recommended tire deflection with the aircraft loaded to its maximum ramp weightand with center of gravity position. The tire pressure, where specifically designated in tables and charts,are values obtained under loaded conditions as certified for commercial use.This section is presented as follows:

• The basic data on the landing gear footprint configuration, maximum design ramp loads, and tiresizes and pressures.

• The maximum pavement loads for certain critical conditions at the tire-ground interfaces.

• A chart in order to determine the loads throughout the stability limits of the aircraft at rest on thepavement. Pavement requirements for commercial aircraft are customarily derived from the staticanalysis of loads imposed on the main landing gear struts. These main landing gear loads are usedto enter the pavement design charts which follow, interpolating load values where necessary.

• The flexible pavement curves prepared in accordance with the US Army Corps of Engineers DesignMethod and the LCN Method.

• The rigid pavement design curves in accordance with the Portland Cement Association DesignMethod and the LCN Method.

• The aircraft ACN values for flexible and rigid pavements.


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Page 7-1

Dec 08/03

7.2. FOOTPRINT

MAXIMUM RAMP WEIGHT

NOSE GEAR TIRE SIZE 24 x 7.7

NOSE GEAR TIRE PRESSURE

MAIN GEAR TIRE SIZE H38 x 13−18

MAIN GEAR TIRE PRESSURE

36150 kg(79697 lb)

37360 kg(82365 lb)

8.86 ± 0.7 kg/cm ²(126 ± 10 psi)

9.14 ± 0.7 kg/cm ²(130 ± 10 psi)

7.24 ± 0.21 kg/cm ²(103 ± 3 psi)

0.71 m(2 ft 4 in.)

10.62 m(34 ft 10 in.)

0.40 m(1 ft 4 in.)

(17 ft 1 in.)5.2 m

AIRCRAFT MODELS

STD

EM

170A

PM

0700

02C

.DG

N

LR, SU OR SE

FootprintFigure 7.1


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Page 7-2

Jul 01/05

7.3. MAXIMUM PAVEMENT LOADS

NG

MG H=MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING

VNG

VMG

MODELSTATIC AT MOSTFORWARD C.G.

NGV MGV (PER STRUT) (PER STRUT)H

H

2

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.

37360 kg(82365 lb)

36150 kg(79697 lb)

4888 kg(10776 lb)

4922 kg(10851 lb)

MAXIMUMRAMP

WEIGHT

6994 kg(15419 lb)

6961 kg(15346 lb)

17546 kg(38682 lb)

16976 kg(37426 lb)

5090 kg(11221 lb)

4924 kg(10855 lb)

11870 kg(26169 lb)

11480 kg(25309 lb)

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

EM

170A

PM

0700

13C

.DG

NLR, SUOR SE

Maximum Pavement LoadsFigure 7.2


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Page 7-3

Jul 01/05

7.4. LANDING GEAR LOADING ON PAVEMENT

LEGEND

82 83 84 85 86 87 88 89 90 91 92 93 94 95

PERCENT OF WEIGHT ON MAIN GEAR − (%)

10000

15000

20000

25000

30000

35000

40000

15000

20000

25000

30000

35000

40000

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(lb

)

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(kg

)

20000

30000

40000

50000

60000

70000

80000

90000

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

(lb

)

AIR

CR

AF

T G

RO

SS

WE

IGH

T −

(kg

)

90000

80000

70000

60000

50000

40000

30000

20000

11.3 %7 % 27 %

% CMA

MOW

STD AIRCRAFT MODEL

EM

170A

PM

0700

14C

.DG

NLR, SU OR SE AIRCRAFT MODELS

Landing Gear Loading on PavementFigure 7.3


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Page 7-4

Jul 01/05

7.5. FLEXIBLE PAVEMENT REQUIREMENTS, U.S. CORPS OF ENGINEERS DESIGNMETHOD

The flexible pavement curves are based on the procedures set forth in Instruction Report No. S-77-1,“Procedures for Development of CBR Design Curves”, dated June 1977, and modified according to themethods described in FAA Advisory Circular 150/5320-6D, “Airport Pavement Design and Evaluation”,dated July 7, 1995. Instruction Report No. S-77-1 was prepared by the US Army Corps of EngineersWaterways Experiment Station, Soils and Pavements Laboratory, Vicksburg, Mississippi. The lineshowing 10,000 coverages is used to calculate ACN.


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Page 7-5

Dec 08/03

EM

170A

PM

0700

17.D

GN

SUBGRADE STRENGHT - CBR

2NOTES: H 38x13-18 TIRE SIZE - TIRES PRESSURE AT 8.86 kgf/cm (126 psi)

ANNUALDEPARTURES

1200

3000

6000

15000

25000

10000 COVERAGES(USED FOR ACNCALCULATIONS)

31400 (69225)

WEIGHT ON MAINLANDING GEAR

(kg) (lb)33064 (72894)

29336 (64675)

26892 (59287)

19398 (42765)

3 4 5 6 7 8 9 10 20 30

3 4 5 6 7 8 9 10 20 30

FLEXIBLE PAVEMENT THICKNESS (cm)

50403020 60 70 808 9 10

FLEXIBLE PAVEMENT THICKNESS (in.)

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


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Section 7

Page 7-6

Dec 08/03

SUBGRADE STRENGHT − CBR

2NOTES: H38 X 13−18 TIRE SIZE − TIRES PRESSURE AT 9.14 kgf/cm (130 psi)

32300 (71209)


(kg) (lb)

ANNUALDEPARTURES

1200

3000

6000

15000

25000

10000 COVERAGES(USED FOR ACNCALCULATIONS)

34008 (74975)

29328 (64657)

27062 (59661)

19388 (42743)

3 4 5 6 7 8 9 10 20 30

FLEXIBLE PAVEMENT THICKNESS (cm)

3 4 5 6 7 8 9 10 20 30

50403020 60 70 808 9 10

FLEXIBLE PAVEMENT THICKNESS (in.)

EM

170A

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0700

01A

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N

Flexible Pavement Requirements - US Army Corps of Engineers Design MethodFigure 7.5


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EFFECTIVITY: EMBRAER 170 LR OR SU OR SEACFT MODEL

Section 7

Page 7-7

Jul 01/05

7.6. FLEXIBLE PAVEMENT REQUIREMENTS, LCN METHOD

The LCN method presents curves for flexible pavements. They have been built using procedures andcurves in the ICAO Aerodrome Design Manual, Part 3 - Pavements, Document 9157-AN/901, 1983. Thesame chart includes the data of equivalent single-wheel load versus pavement thickness.


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Page 7-8

Dec 08/03

EM

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18.D

GN

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

TIRES H38x13-18 AT 8.86 kg/cm (126 psi)2

FLEXIBLE PAVEMENT THICKNESS - h (cm)

2 3 4 5 6 7 8 9 10 20 30

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

- (

lb)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

- (

kg)

LCN - LOAD CLASSIFICATION NUMBER

8000

6000

10000

12000

14000

16000

FLEXIBLE PAVEMENT THICKNESS - h (in.)

1004 5 6 7 8 9 10 20 30 40 50 60 70 80 90

1003


kg (lb)

33064 (72894)

31400 (69225)

29336 (64675)

26892 (59287)

19398 (42765)

10000

20000

30000

40000

10 20 30 40

Flexible Pavement Requirements - LCN MethodFigure 7.6


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Section 7

Page 7-9

Dec 08/03


EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

− (

lb)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

− (

kg)

FLEXIBLE PAVEMENT THICKNESS − h (cm)100

LCN − LOAD CLASSIFICATION NUMBER

2 3 4 5 6 7 8 9 10 20 30

8000

6000

10000

12000

14000

16000

TIRES H38x13−18 AT 9.14 kg/cm (130 psi)2

10000

20000

30000

40000

4 5 6 7 8 9 10 20 30 40 50 60 70 8090100

10 20 30 40 50


kg (lb)

19388 (42743)

27062 (59661)29328 (64657)

32300 (71209)

34008 (74975)

FLEXIBLE PAVEMENT THICKNESS − h (in.)

EM

170A

PM

0700

12A

.DG

N

Flexible Pavement Requirements - LCN MethodFigure 7.7


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Section 7

Page 7-10

Jul 01/05

7.7. RIGID PAVEMENT REQUIREMENTS, PORTLAND CEMENT ASSOCIATION DESIGNMETHOD

This method has a chart that has been prepared with the use of the Westergaard Equation in generalaccordance with the procedures outlined in the 1955 edition of “Design of Concrete Airport Pavement”published by the Portland Cement Association, 33 W. Grand Ave., Chicago 10, Illinois, but modified tothe new format described in the 1968 Portland Cement Association publication, “Computer Program forConcrete Airport Pavement Design” by Robert G. Packard. The following procedure is used to developrigid pavement design curves such as those shown in the chart:

• Once the scale for the pavement thickness to the left and the scale for allowable working stress to theright have been established, an arbitrary load line is drawn representing the main landing gearmaximum weight to be shown.

• All values of the subgrade modulus (k-values) are then plotted.

• Additional load lines for the incremental values of weight on the main landing gear are thenestablished on the basis of the curve for k=300, already established.


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Page 7-11

Dec 08/03

05101520253035404550 PAVEMENT THICKNESS (cm)

02468101214161820

05101520253035404550

ALLOWABLE WORKING STRESS - kgf/cm

0

ALLOWABLE WORKING STRESS - psi

2

50100

150

200

250

300

350

400

450

500

550

600

650

700

2N

OT

ES

:T

IRE

S H

38 x

13-

18

TH

E V

ALU

ES

OB

TA

INE

D B

Y U

SIN

G T

HE

MA

XIM

UM

LO

AD

RE

FE

RE

NC

E L

INE

AN

DA

NY

VA

LUE

OF

"K

" A

RE

EX

AC

T. F

OR

LOA

DS

LE

SS

TH

AN

MA

XIM

UM

, TH

E C

UR

VE

SA

RE

EX

AC

T F

OR

K=

300

BU

T D

EV

IAT

ES

LIG

HT

LY F

OR

OT

HE

R V

ALU

ES

OF

"K

".

NO

TE

:

TIR

E P

RE

SS

UR

E 8

.86

kgf/c

m (

126

psi)

(UN

LOA

DE

D)

750

5555

RIG

ID P

AV

EM

EN

T R

EQ

UIR

EM

EN

TS

PAVEMENT THICKNESS (in.)

3306

4 (7

2894

)

3140

0 (6

9225

)

2933

6 (6

4675

)

2689

2 (5

9287

)

1939

8 (4

2765

)

60

800

850

60

22

k= 7

5 lb

/in3

k= 1

50 lb

/in3

k= 3

00 lb

/in3

k= 5

50 lb

/in3

MA

XIM

UM

PO

SS

IBLE

MA

IN-G

EA

R

LOA

D A

T M

AX

IMU

M D

ES

IGN

RA

MP

WE

IGH

T A

ND

AFT

C.G

.

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

- kg

(lb)

EM170APM070020.DGNRigid Pavement Requirements - Portland Cement Association Design Method

Figure 7.8


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Section 7

Page 7-12

Dec 08/03

EM170APM070010.DGN

05101520253035404550 PAVEMENT THICKNESS (cm)

02468101214161820

05101520253035404550

ALLOWABLE WORKING STRESS (kgf/cm )

0

ALLOWABLE WORKING STRESS (psi)

2

50100

150

200

250

300

350

400

450

500

550

600

650

700

2N

OT

ES

:T

IRE

S H

38 x

13-

18

TH

E V

ALU

ES

OB

TA

INE

D B

Y U

SIN

G T

HE

MA

XIM

UM

LO

AD

RE

FE

RE

NC

E L

INE

AN

DA

NY

VA

LUE

OF

"K

" A

RE

EX

AC

T. F

OR

LOA

DS

LE

SS

TH

AN

MA

XIM

UM

, TH

E C

UR

VE

SA

RE

EX

AC

T F

OR

K=

300

BU

T D

EV

IAT

ES

LIG

HT

LY F

OR

OT

HE

R V

ALU

ES

OF

"K

".

NO

TE

:

TIR

E P

RE

SS

UR

E 9

.14

kgf/c

m (

130

psi)

(UN

LOA

DE

D)

750

5555

RIG

ID P

AV

EM

EN

T R

EQ

UIR

EM

EN

TS

PAVEMENT THICKNESS (in.)

3400

8 (7

4975

)

3230

0 (7

1209

)

2932

8 (6

4657

)

2706

2 (5

9661

)

1938

8 (4

2743

)

60

800

850

60

22

k= 7

5 lb

/in3

k= 1

50 lb

/in3

k= 3

00 lb

/in3

k= 5

50 lb

/in3

MA

XIM

UM

PO

SS

IBLE

MA

IN-G

EA

R

LOA

D A

T M

AX

IMU

M D

ES

IGN

RA

MP

WE

IGH

T A

ND

AFT

C.G

.

WE

IGH

T O

N M

AIN

LA

ND

ING

GE

AR

- kg

(lb)

Rigid Pavement Requirements - Portland Cement Association Design MethodFigure 7.9


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Section 7

Page 7-13

Jul 01/05

7.8. RIGID PAVEMENT REQUIREMENTS, LCN METHOD

This LCN Method presents curves for rigid pavements. They have been built using procedures andcurves in ICAO Aerodrome Design Manual, Part 3 - Pavements, Document 9157-AN/901, 1983. Thesame chart includes the data of equivalent single-wheel load versus radius of relative stiffness.To determine the aircraft weight that can be accommodated on a particular rigid airport pavement, boththe LCN of the pavement and the radius of relative stiffness must be known.The radius of relative stiffness values is obtained from a table. This table presents the radius of relativestiffness values based on Young’s modulus (E) of 4,000,000 psi and Poisson’s ratio (µ) of 0.15.For convenience in finding this radius based on other values of E and µ, the curves are included. Forexample, to find an RRS value based on an E of 3,000,000 psi, the “E” factor of 0.931 is multiplied bythe RRS value found in figure 7.6.3. The effect of the variations of µ on the RRS value is treated in asimilar manner.


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Page 7-14

Dec 08/03

EM

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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 7.10


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Page 7-15

Dec 08/03

EM

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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 7.11


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Page 7-16

Dec 08/03




kg (lb)


20 30 40 7050 60 80 90 100

RADIUS OF RELATIVE STIFFNESS − (cm)

RADIUS OF RELATIVE STIFFNESS − (in.)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

− (

lb)

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

− (

kg)

6000

5000

7000

8000

10000

20000

30000

40000

9000

10000

13000

15000

17000

40 50 60 70 80 90 100 20030 300

33064 (72894)

31400 (69225)

29336 (64675)

26892 (59287)

19398 (42765)

10 20 30 40

EM

170A

PM

0700

19A

.DG

N

Rigid Pavement Requirements - LCN MethodFigure 7.12


b-ap

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46


Section 7

Page 7-17

Dec 08/03


EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

− (

kg)


40 50 60 70 80 90 100 200 300 10 20 30 40

20 30 40 50 60 7080 90 100


RADIUS OF RELATIVE STIFFNESS − (in.)

RADIUS OF RELATIVE STIFFNESS − (cm)

8000

6000

10000

12000

14000

16000

EQ

UIV

ALE

NT

SIN

GLE

WH

EE

L LO

AD

− (

lb)

20000

30000

10000

40000


kg (lb)

34008 (74975)

32300 (71209)

29328 (64657)

27062 (59661)

19388 (42743)

EM

170A

PM

0700

11A

.DG

N

Rigid Pavement Requirements - LCN MethodFigure 7.13


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Section 7

Page 7-18

Jul 01/05

7.9. ACN - PCN SYSTEM - FLEXIBLE AND RIGID PAVEMENTS

The ACN/PCN system as referenced in Amendment 35 to ICAO Annex 14, “Aerodromes”, provides astandardized international aircraft/pavement rating system.The PCN is an index rating of the mass that according to evaluation can be borne by the pavementwhen applied by a standard single wheel. The ACN is established for the particular pavement type andsubgrade category of the rated pavement, as well as for the particular aircraft mass and characteristics.An aircraft shall have an ACN equal to or less than the PCN to operate without restriction on thepavement.The method of pavement evaluation is left up to the airport, and the results of such evaluation arepresented as follows:

Table 7.1 - Pavement 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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Page 7-19

Dec 08/03

52000 56000 60000 64000 68000 72000 76000 80000 84000

AIRCRAFT GROSS WEIGHT−kg

AIRCRAFT GROSS WEIGHT−lb

4800044000

FLEXIBLE PAVEMENT SUBGRADE

NOTES: H38 x 13−18 TIRE SIZE 2TIRE PRESSURE 8.86 kgf/cm (126 psi) (UNLOADED)

2400020000 22000 26000 30000 32000 34000 36000 38000280000

AIR

CR

AF

T C

LAS

SIF

ICA

TIO

N N

UM

BE

R−

AC

N

5

10

15

20

25

MA

XIM

UM

RA

MP

WE

IGH

T

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

36150

30

EM

170A

PM

0700

16A

.DG

N

ACN For Flexible PavementFigure 7.14


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Section 7

Page 7-20

Dec 08/03

H38 x 13−18 TIRE SIZE 2

24000

52000 56000 60000 64000 68000 72000 76000 80000 84000

20000 22000 26000 30000 32000 34000 36000 3800028000



AIR

CR

AF

T C

LAS

SIF

ICA

TIO

N N

UM

BE

R−

AC

N

4800044000

MA

XIM

UM

RA

MP

WE

IGH

T

TIRE PRESSURE 9.14 kgf/cm (130 psi) (UNLOADED)

45

40

35

25

20

15

10

5

0

NOTES:

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


37360

EM

170A

PM

0700

04A

.DG

N



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Section 7

Page 7-21

Oct 06/11

EM

170A

PM

0700

96A

.DG

N2400020000 22000 26000 30000 32000 34000 3600028000

MA

XIM

UM

RA

MP

WE

IGH

T

45

40

35

25

20

15

10

5

0

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

H38 x 13−18 TIRE SIZE 2NOTES:



38760

52000 56000 60000 64000 68000 72000 76000 80000 840004800044000

AC

N −

FL

EX

IBL

E P

AV

EM

EN

T



38000

86000

39000



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46

EFFECTIVITY: EMBRAER 170 AR ACFT MODEL Section 7

Page 7-22

Oct 06/11

52000 56000 60000 64000 68000 72000 76000 80000 84000



4800044000

AIR

CR

AF

T C

LAS

SIF

ICA

TIO

N N

UM

BE

R−

AC

N

NOTES: H38 x 13−18 TIRE SIZE 2TIRE PRESSURE 8.86 kgf/cm (126 psi) (UNLOADED)

RIGID PAVEMENT SUBGRADES

2400020000 22000 26000 30000 32000 34000 36000 3800028000M

AX

IMU

M R

AM

P W

EIG

HT

36150

0

5

10

15

20

25

30

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

33

3

3

3

3

EM

170A

PM

0700

15A

.DG

N

ACN For Rigid PavementFigure 7.17


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Section 7

Page 7-23

Oct 06/11

52000 56000 60000 64000 68000 72000 76000 80000 84000

NOTES: H38 x 13−18 TIRE SIZE 2



AIR

CR

AF

T C

LAS

SIF

ICA

TIO

N N

UM

BE

R−

AC

N

4800044000



2400020000 22000 26000 30000 32000 34000 36000 3800028000

25

20

15

10

5

0

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

MA

XIM

UM

RA

MP

WE

IGH

T

37360

EM

170A

PM

0700

03A

.DG

N



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Section 7

Page 7-24

Oct 06/11

NOTES: H38 x 13−18 TIRE SIZE 2



2400020000 22000 26000 30000 32000 34000 3600028000M

AX

IMU

M R

AM

P W

EIG

HT

45

40

25

20

15

10

5

0

38760

52000 56000 60000 64000 68000 72000 76000 80000 840004800044000

AC

N −

FL

EX

IBL

E P

AV

EM

EN

T



38000

86000

39000

30

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

EM

170A

PM

0700

97A

.DG

N



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EFFECTIVITY: EMBRAER 170 AR ACFT MODEL Section 7

Page 7-25 / 26

Oct 06/11

8. POSSIBLE EMBRAER 170 DERIVATIVE AIRCRAFT

8.1. NOT APPLICABLE


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Page 8-1 / 2

Dec 08/03

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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Page 9-1

Dec 08/03

EM

170A

PM

0900

01.D

GN

0

0 16 32 48 64

5 10 15 20 25 m

80 ft

1

2

34

5

6

7

89

10

11

13 12

10

ITEM DESCRIPTION

1

ITEM DESCRIPTION

8

2

3

4

5

6

7

9

10

11

12

13



ENGINE AIR STARTING

AIR CONDITIONING LOW PRESSURE


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

13 14

14

11

WING SPAN:25.99 m

(85 ft 3 in.)

14 SERVICE DOOR

Scale: 1 Inch Equals 32 FeetFigure 9.1


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Page 9-2

Dec 08/03

EM

170A

PM

0900

02.D

GN

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



ENGINE AIR STARTING







CARGO DOOR

MAIN LANDING GEAR

NOSE LANDING GEAR

PASSENGER DOOR

1

2

34

5

6

7

89

10

11

1312

10

13 14

11

14

WING SPAN:25.99 m

(85 ft 3 in.)

14 SERVICE DOOR



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Page 9-3

Dec 08/03

EM

170A

PM

0900

03.D

GN

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



ENGINE AIR STARTING







CARGO DOOR

MAIN LANDING GEAR

NOSE LANDING GEAR

PASSENGER DOOR

1

2

34

5

6

7

89

10

11

1312

10

1314

14

WING SPAN:25.99 m

(85 ft 3 in.)

14 SERVICE DOOR

11



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Page 9-4

Dec 08/03

EM

170A

PM

0900

04.D

GN

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



ENGINE AIR STARTING







CARGO DOOR

MAIN LANDING GEAR

NOSE LANDING GEAR

PASSENGER DOOR

1

2

3

4

5

6

7

89

10

11

13

12

10

13

11

14

14

WING SPAN:25.99 m

(85 ft 3 in.)

14 SERVICE DOOR

Scale: 1 to 500Figure 9.4


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Page 9-5

Dec 08/03

EM

170A

PM

0900

05.D

GN

0

0 16 32 48 64

5 10 15 20

80 ft

50 m25

ITEM DESCRIPTION

1

ITEM DESCRIPTION

8

2

3

4

5

6

7

9

10

11

12

13



ENGINE AIR STARTING







CARGO DOOR

MAIN LANDING GEAR

NOSE LANDING GEAR

PASSENGER DOOR

1

2

34

5

6

7

89

10

11

13

12

10

WING SPAN:25.99 m

(85 ft 3 in.)

13

14

1411

14 SERVICE DOOR

Scale: 1 to 1000Figure 9.5


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Page 9-6

Dec 08/03

AIRPORT PLANNING MANUAL - Embraer · TO: HOLDERS OF PUBLICATION No. APM-1346 -″AIRPORT PLANNING...

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Transcript of AIRPORT PLANNING MANUAL - Embraer · TO: HOLDERS OF PUBLICATION No. APM-1346 -″AIRPORT PLANNING...