AIRPORT PLANNING MANUAL - Embraer · of Embraer or third parties and shall not be used or disclosed...
Transcript of AIRPORT PLANNING MANUAL - Embraer · of Embraer or third parties and shall not be used or disclosed...
AIRPORT PLANNINGMANUAL
APM-145/110030 MAY 1997
REVISION N - 29 JANUARY 2007
Copyright 2007 by EMBRAER - Empresa Brasileira de Aeronáutica S.A. All rights reserved. This document shall not becopied or reproduced, whether in whole or in part, in any form or by any means without the express written authorizationof Embraer. The information, technical data, designs and drawings disclosed in this document are proprietary information
of Embraer or third parties and shall not be used or disclosed to any third party without permission of Embraer.
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Original . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 30/97Revision A .. . . . . . . . . . . . . . . . . . . . . . . . . . . Feb 08/99Revision B .. . . . . . . . . . . . . . . . . . . . . . . . . . . Nov 18/99Revision C .. . . . . . . . . . . . . . . . . . . . . . . . . . May 18/00Revision D .. . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 18/00Revision E .. . . . . . . . . . . . . . . . . . . . . . . . . . . Apr 18/01Revision F .. . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 10/01Revision G .. . . . . . . . . . . . . . . . . . . . . . . . . . . Apr 30/02Revision H .. . . . . . . . . . . . . . . . . . . . . . . . . . . Oct 18/02Revision I . . . . . . . . . . . . . . . . . . . . . . . . . . . . May 30/03Revision J . . . . . . . . . . . . . . . . . . . . . . . . . . . . Dec 29/03Revision K .. . . . . . . . . . . . . . . . . . . . . . . . . . . Aug 05/04Revision L . . . . . . . . . . . . . . . . . . . . . . . . . . . . Sep 28/05Revision M .. . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 27/06Revision N .. . . . . . . . . . . . . . . . . . . . . . . . . . . Jan 29/07* Title . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. NList of Effective Pages* A .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. N* B .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. NTable of Contents
A .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. LB .. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G1-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G1-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C2-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. K
* 2-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. N2-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. H2-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G2-18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G3-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D3-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D3-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D3-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D
3-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D3-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D3-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D3-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D3-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G3-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-21 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J3-22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. J4-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C4-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. H4-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G4-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G5-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C5-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I5-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I6-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C6-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C
LIST OF EFFECTIVE PAGES
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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).
REV N
A
6-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C6-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L6-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. L7-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D7-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I7-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. I7-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C7-7 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D7-8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. D7-9 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-11 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-12 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-13 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-14 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-16 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-17 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-18 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-19 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-20 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-21 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-22 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-23 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-24 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-25 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-26 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-27 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-28 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-29 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-31 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-32 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-33 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-34 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-35 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-36 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-37 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G
7-38 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-39 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-40 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-41 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-42 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-43 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-44 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-45 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-46 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-47 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-48 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-49 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-50 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. H7-51 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. G7-52 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. H8-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C8-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C9-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C9-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C9-3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C9-4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C9-5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C9-6 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Rev. C
LIST OF EFFECTIVE PAGES
AIRPORTPLANNING MANUAL
Pages revised or added by the current revision are indicated by an asterisk (*). Pages deleted by the currentrevision are indicated by * (del).Pages deleted by the previous revision are indicated by (del).
REV N
B
1. INTRODUCTION ............................................................................................................... 1-11.1 Purpose ................................................................................................................... 1-11.2 Scope ...................................................................................................................... 1-1
2. AIRPLANE DESCRIPTION ............................................................................................... 2-12.1 General Airplane Characteristics ............................................................................. 2-12.2 Airplane Dimensions ............................................................................................... 2-22.3 Ground Clearances ................................................................................................. 2-62.4 Interior Arrangements .............................................................................................. 2-102.5 Passenger Cabin Cross-Section ............................................................................. 2-152.6 Lower Compartment Containers .............................................................................. 2-162.7 Door Clearances ..................................................................................................... 2-17
3. AIRPLANE PERFORMANCE ........................................................................................... 3-13.1 General Information ................................................................................................. 3-13.2 Payload x Range ..................................................................................................... 3-23.3 FAR Takeoff Runway Length Requirements ............................................................ 3-113.4 FAR Landing Runway Length Requirements ........................................................... 3-19
4. GROUND MANEUVERING ............................................................................................... 4-14.1 General Information ................................................................................................. 4-14.2 Turning Radii - No Slip Angle .................................................................................. 4-24.3 Minimum Turning Radii ........................................................................................... 4-44.4 Visibility from Cockpit in Static Position ................................................................... 4-74.5 Runway and Taxiway Turn Paths ............................................................................ 4-84.6 Runway Holding Bay ............................................................................................... 4-11
5. TERMINAL SERVICING ................................................................................................... 5-15.1 General Information ................................................................................................. 5-15.2 Air Terminal Operation - Turnaround Station ........................................................... 5-45.3 Air Terminal Operation - Enroute Station ................................................................. 5-55.4 Ground Servicing Connections EMB-145 ................................................................ 5-65.5 Engine Starting Pneumatic Requirements ............................................................... 5-125.6 Ground Pneumatic Power Requirements ................................................................ 5-145.7 Conditioned Air Requirements ................................................................................. 5-155.8 Ground Towing Requirements ................................................................................. 5-16
6. OPERATING CONDITIONS .............................................................................................. 6-16.1 Engine Exhaust Velocities and Temperatures .......................................................... 6-26.2 Airport and Community Noise ................................................................................. 6-86.3 Hazard Areas .......................................................................................................... 6-11
7. PAVEMENT DATA ............................................................................................................ 7-17.1 General Information ................................................................................................. 7-1
TABLE OF CONTENTS
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REV L
A
7.2 Footprint .................................................................................................................. 7-47.3 Maximum Pavement Loads ..................................................................................... 7-57.4 Landing Gear Loading on Pavement ....................................................................... 7-67.5 Flexible Pavement Requirements - US Army Corps of Engineers Design Method .. 7-107.6 Flexible Pavement Requirements - LCN Method .................................................... 7-167.7 Rigid Pavement Requirements - Portland Cement Association Design Method ...... 7-227.8 Rigid Pavement Requirements - LCN Method ........................................................ 7-287.9 ACN/PCN Reporting System - Flexible and Rigid Pavements ................................ 7-38
8. POSSIBLE EMB-145 DERIVATIVE AIRPLANE S ............................................................. 8-1
9. EMB-145 SCALE DRAWINGS ......................................................................................... 9-19.1 EMB-145 Scale: 1 Inch Equals 32 Feet .................................................................. 9-29.2 EMB-145 Scale: 1 Inch Equals 50 Feet .................................................................. 9-39.3 EMB-145 Scale: 1 Inch Equals 100 Feet ................................................................ 9-49.4 EMB-145 Scale: 1 to 500 ........................................................................................ 9-59.5 EMB-145 Scale: 1 to 1000 ...................................................................................... 9-6
TABLE OF CONTENTS
Section Page
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REV G
B
1. INTRODUCTION
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 Scope
This document complies with NAS3601, revision 6.It provides characteristics of the EMB-145EP, EMB-145ER, EMB-145EU, EMB-145MP, EMB-145MK,EMB-145LR, EMB-145LU, and EMB-145XR aircraft models for airport operators, airlines, and engineer-ing consultant organizations. Since the airplane changes and available options may alter the information,the data presented herein must be regarded as subject to change.For further information, contact:EMBRAER: Empresa Brasileira de Aeronáutica S/AAv. Brigadeiro Faria Lima, 2170P.O. Box 8050 - CEP 12227-901São José dos Campos, SP - BRASILAtt. Technical PublicationsPhone: ++ 55 12 3927-7517Fax: ++ 55 12 3927-7546e-mail: [email protected]
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2. AIRPLANE DESCRIPTION
2.1 General Airplane Characteristics
The airplane is an all-metal semimonocoque-type structure, low-winged, T-tailed, pressurized airplanefeaturing a retractable twin-wheeled, tricycle-type landing gear system and two high bypass ratiorear-mounted Rolls Royce AE 3007 turbofan engines. The airplane has convenient accommodations fora pilot, a copilot, and a flight observer. The typical passenger configuration consists of three seatsabreast, with front galley and rear toilet. Accommodation for a second flight attendant is available as anoption.
2.1.1 Definitions
Maximum Design Taxi Weight (MTW): Maximum weight for ground maneuver as limited by the aircraftstrength and airworthiness requirements. (It includes weight of taxi and run-up fuel).Maximum Design Landing Weight (MLW): Maximum weight for landing as limited by the aircraft strengthand airworthiness requirements.Maximum Design Takeoff Weight (MTOW): Maximum weight for takeoff as limited by the aircraft strengthand airworthiness requirements. (This is the maximum weight at the start of the takeoff run).Operating Empty Weight (OEW): Weight of the structure, power plant, furnishings, systems, unusablefuel, and other unusable propulsion agents, as well as other items of equipment that are considered anintegral part of a particular airplane configuration. Also included are certain standard units, crew and crewbaggage, catering, navigation kit, and suppliers necessary for full operations, excluding usable fuel andpayload.Maximum Design Zero Fuel Weight (MZFW): Maximum weight allowed before usable fuel and otherspecified usable agents are loaded in defined sections of the aircraft as limited by the strength andairworthiness requirements.Maximum Payload: Maximum design zero fuel weight minus operational empty weight.Maximum Seating Capacity: The maximum number of passengers specifically certified or anticipated forcertification.Maximum Cargo Volume: The maximum space available for cargo.Usable Fuel: Fuel available for the aircraft propulsion.
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Table 2.1.1.1 - EMB-145 Airplane General Characteristics
DESIGN WEIGHTS MODELSER EU EP LR LU MP MK XR
MaximumDesign TaxiWeight
lb 45636 44291 46495 48722 48700 46495 44291 53352
kg 20700 20090 21090 22100 22090 21090 20090 24200Maximum
Design LandingWeight [3]
lb 41226 41226 41226 42549 42549 42549 42549 44092
kg 18700 18700 18700 19300 19300 19300 19300 20000Maximum
Design TakeoffWeight [3]
lb 45415 44070 46275 48502 48480 46275 44070 53131
kg 20600 19990 20990 22000 21990 20990 19990 24100OperatingEmpty
Weight [1]
lb 26339 26339 26339 26707 26707 26539 26539 27758
kg 11947 11947 11947 12114 12114 12038 12038 12591Maximum
Design Zero FuelWeight [2] [3]
lb 37699 37699 37699 39463 39463 39463 39463 40786
kg 17100 17100 17100 17900 17900 17900 17900 18500MaximumPayload [1]
lb 11359 11359 11359 12755 12755 12923 12923 13027kg 5153 5153 5153 5786 5786 5862 5862 5909
MaximumSeatingCapacity
PAS-SEN-GERS
50 50 50 50 50 50 50 50
MaximumCargo Volume
ft3 325 325 325 325 325 325 325 325m3 9.2 9.2 9.2 9.2 9.2 9.2 9.2 9.2
UsableFuel [4]
lb 9202 9202 9202 11435 11435 9202 9202 13199kg 4173 4173 4173 5187 5187 4173 4173 6032
US GAL. 1360 1360 1360 1690 1690 1360 1360 1950LITERS 5146 5146 5146 6396 6396 5146 5146 7438
[1] Standard configuration (weights may vary according to optional equipment installed or interior layouts).
[2] For aircraft POST-MOD. S.B. 145-53-0064, consider MZFW = 17350 kg (38250 lb).
[3] For aircraft POST-MOD. S.B. 145-53-0068, consider MZFW = 18400 kg (40564 lb), MTOW= 22600 kg (49823 lb), and MLW= 19800kg (43651 lb).
[4] Adopted fuel density of 0.811 kg/l (6.77 lb/US gal.).
2.2 Airplane Dimensions
2.2.1 External Dimensions
Overall span (EMB-145EP/ER/EU/MP/MK/LR/LU) ................................................ 20.04 m (65 ft 9 in)Overall span (EMB-145XR) .................................................................................. 21.00 m (69 ft 11 in)Height (maximum) ................................................................................................... 6.75 m (22 ft 2 in)Overall length ........................................................................................................ 29.87 m (98 ft 0 in)
2.2.2 Wing
Reference area ........................................................................................................ 51.18 m2 (551 ft2)Reference aspect ratio .................................................................................................................... 7.8
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2.2.3 Fuselage
Total Length ........................................................................................................... 27.93 m (91 ft 8 in)Length of pressurized section ............................................................................... 23.22 m (76 ft 2 in)Outside diameter ....................................................................................................... 2.28 m (7 ft 6 in)
2.2.4 Horizontal Tail
Span ........................................................................................................................ 7.55 m (24 ft 9 in)Area ...................................................................................................................... 11.20 m2 (120.6 ft2)
2.2.5 Vertical Tail
Reference area ......................................................................................................... 7.20 m2 (77.5 ft2)
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27.93 m91 ft 8 in
47 ft 5 in
24 ft 9 in
14.44 m
65 ft 9 in
29.87 m98 ft 0 in
7.55 m
6.75 m
20.04 m
4.10 m
22 ft 2 in
13 ft 5 in
EMB-145 EP/ER/EU/MP/MK/LR/LU145APM000008.MCE A
Figure 2.2.1 - EMB-145 Airplane General Dimensions
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27.93 m91 ft 8 in
47 ft 5 in
24 ft 9 in
14.44 m
29.87 m98 ft 0 in
7.55 m
6.75 m22 ft 2 in
4.10 m13 ft 5 in
68 ft 11 in21.00 m
EMB−145XR
2.20 m7 ft 3 in
145APM020272.MCE A
Figure 2.2.2 - EMB-145 Airplane General Dimensions
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2.3 Ground Clearances
Figure 2.3.1 - Ground ClearancesSheet 1
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145APM020273.MCE
FUS ANGLE
(REF.)
24200kg53352lb -1.30
24200kg53352lb -1.14
24100kg53131lb -1.30 6.737m
21ft 10.7in
24100kg53131lb
20000kg44092lb
19300kg42549lb
17100kg37699lb
15500kg34172lb
13800kg30424lb
13800kg30424lb
12800kg28219lb
-1.14
-1.38
-1.15
-1.15
-1.10
12ft 5.3in
12ft 6.0in
12ft 7.0in
12ft 6.9in
-1.50
-1.54
-1.11
4ft 3.7in
4ft 3.8in
4ft 8.1in
4ft 6.0in
4ft 10.8in
4ft 11.3in
5ft 2.2in
5ft 0.9in
1ft 3.2in
1ft 2.0in
4ft 10.9in
4ft 11.5in
5ft 2.0in
5ft 1.0in
7ft 4.6in
7ft 5.4in
7ft 5.4in
NOSEANTENNA TAIL BOOMNACELLEDOORCGWEIGHT WING TIP
(%MAC)MAIN LDG
LC ED F H J K MA GB
EMB-145XR - GROUND CLEARANCE
7ft 5.9in
EMB-145XR
-1.37
FUS ANGLE(DEG.)
MAINDOOR
P
WINGLETTIP
MAINDOOR
(OPEN, 1ST STEP)
EMERG./SERVICEDOOR
EMERG.EXIT
N
TAILSKIDANGLETAIL BUMPER
BAGGAGEDOOR
20000kg44092lb
3.7372m12ft 3.1in
3.7467m12ft 3.5in
3.7377m12ft 3.2in
3.7472m12ft 3.5in
3.7592m12ft 4.0in
3.7724m12ft 4.5in
3.7775m12ft 4.7in
3.7998m12ft 5.6in
3.7929m
3.8111m
3.8361m
3.8337m
1.2890m4ft 2.8in
1.3318m4ft 4.4in
1.2893m4ft 2.8in
1.3322m4ft 4.5in
1.2950m4ft 3.0in
1.3550m4ft 5.4in
1.3597m4ft 5.5in
1.3922m4ft 6.8in
1.3057m
1.3148m
1.4257m
1.3718m
12.10
11.90
12.11
12.39
12.10
12.14
12.22
12.81
13.01
12.49
12.89
11.90
1.4591m4ft 9.4in
1.4877m4ft 10.6in
1.4595m4ft 9.5in
1.4882m4ft 10.6in
1.4719m4ft 10.0in
1.5120m4ft 11.5in
1.5169m4ft 11.7in
1.5450m5ft 8in
1.4925m
1.5054m
1.5798m
1.5478m
0.2666m10.5in
0.2952m11.6in
0.2670m10.5in
0.2956m11.6in
0.2795m11.0in
0.3195m1ft 0.6in
0.3243m1ft 0.8in
0.3525m1ft 1.9in
0.3001m11.8in
0.3130m1ft 3in
0.3872m
0.3553m
6.6729m21ft 10.7in
6.6343m21ft 9.2in
6.6350m21ft 9.2in
6.7178m22ft 0.5in
6.6635m21ft 10.3in
6.6692m21ft 10.6in
6.6769m21ft 10.9in
6.7850m22ft 3.1in
6.8165m24ft 4.4in
6.7171m22ft 0.5in
6.7893m22ft 3.3in
1.6360m5ft 4.4in
1.6090m5ft 3.4in
1.6370m5ft 4.5in
1.6370m5ft 4.5in
1.6430m5ft 4.7in
1.6540m5ft 5.1in
1.6100m5ft 3.4in
1.6760m5ft 6in
1.7350m5ft 8.3in
1.7640m5ft 9.4in
1.6930m5ft 6.7in
1.7480m5ft 8.8in
1.6870m5ft 6.4in
1.6647m5ft 5.5in
1.6877m5ft 6.4in
1.6654m5ft 5.6in
1.7242m5ft 7.9in
1.6927m5ft 6.6in
1.6983m5ft 6.9in
1.7109m5ft 7.4in
1.7801m5ft 10in
1.8071m5ft 11in
1.7498m5ft 8.9in
1.7967m5ft 10.7in
1.4593m4ft 9.5in
1.4842m4ft 10.4in
1.4597m4ft 9.5in
1.4847m4ft 10.5in
1.4739m4ft 10in
1.5088m4ft 11.4in
1.5137m4ft 11.6in
1.5407m5ft 0.7in
1.4970m
1.5109m
1.5758m
1.5495m
2.1832m7ft 2in
2.1832m7ft 2in
2.1837m7ft 2in
2.1837m7ft 2in
2.2097m7ft 3in
2.2096m7ft 3in
2.2148m7ft 3.2in
2.2342m7ft 4in
2.2501m
2.2709m
2.2713m
2.2836m
0.3235m1ft .74in
0.3199m1ft .60in
0.3241m1ft .76in
0.3205m1ft .62in
0.3517m1ft 1.9in
0.3466m1ft 1.7in
0.3518m1ft 1.9in
0.3702m1ft 2.6in
0.3946m1ft 3.5in
0.4164m1ft 4.4in
0.4076m1ft 4.0in
0.4255m1ft 4.8in
2.0098m6ft 7.1in
1.9988m6ft 6.7in
2.0104m6ft 7.1in
1.9994m6ft 6.7in
2.0415m6ft 8.4in
2.0260m6ft 7.8in
2.0314m6ft 8.0in
2.0475m6ft 8.6in
2.0895m6ft 10.3in
2.1133m6ft 11.2in
2.0855m6ft 10.1in
2.1148m6ft 11.3in
3.3968m11ft 1.7in
3.3844m11ft 1.2in
3.3975m11ft 1.8in
3.3849m11ft 1.3in
3.4293m11ft 3.0in
3.4116m11ft 2.3in
3.4170m11ft 2.5in
3.4327m11ft 3.2in
3.4784m11ft 4.9in
3.5026m11ft 5.9in
3.4708m11ft 4.7in
3.5025m11ft 5.9in
2.3333m7ft 7.9in
2.3135m7ft 7.0in
2.3340m7ft 7.9in
2.3141m7ft 7.1in
2.3693m7ft 9.3in
2.3413m7ft 8.2in
2.3468m7ft 8.4in
2.3602m7ft 8.9in
2.4235m7ft 11.4n
2.4498m8ft 0.5in
2.3989m7ft 10.4in
2.4420m8ft 0.14in
20.4%
38.0%
20.4%
38.0%
16.4%
39.3%
39.5%
43.0%
12.0%
12.0%
43.0%
30.5%
Q
A
B
C D E F G
HJ K L M N
P
Q
J L
Figure 2.3.1 - Ground ClearancesSheet 4
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2.4 Interior Arrangements
2.4.1 Standard Interior Arrangement
The standard interior arrangement provides accommodation for two pilots, one flight observer, one flightattendant, and 50 passengers. One additional flight attendant seat is available as an option.
2.4.2 Cockpit
The ″quiet and dark″ cockpit is designed to accommodate the pilots with comfort during all flight phases,with minimum workload and maximum safety. The cockpit is provided with two pilot seats, a foldable flightobserver seat, control columns and pedals, control pedestal, left, right, and aft consoles, as well as main,overhead, circuit breaker, and glareshield panel. A sun shade is provided for each pilot and thecompartment is separated from the passenger cabin by a partition with a lockable door.
2.4.3 Panels
The main instrument panel displays the main navigation, engine, and systems indications, through thePFD, MFD, and EICAS displays, ELT reset, the audio selection, and the landing gear and pedal electricadjustment controls. It also accommodates the standby instruments and displays reversionary functions.One of the different possible configurations of the main instrument panel includes radio managementunits.A glareshield panel is located over the main panel, including the master caution and master warninglights, flight control, display control, and lighting intensity controls. One of the different possibleconfigurations of the glareshield panel includes dual radar control panels.An overhead panel provides the hydraulic, electrical, powerplant, APU, fire protection, environmental,and external and internal lighting controls. The circuit breakers, in ordered and grouped positions, areplaced in a panel aft of the overhead panel.
2.4.4 Left and Right Consoles
The left and right consoles accommodate the nose wheel steering handle, ashtrays, holders for cups,headset, and microphone, oxygen masks and oxygen control, a waste container, rechargeable flashlight,and recesses for crew publications.
2.4.5 Control Pedestal
The control pedestal, located between the two pilots, presents the engine control levers, the engine thrustrating panel, the speed brake lever, the emergency/parking brake lever, flight control switches (includingflap selection), the pressurization control, the EICAS reversionary panel, radar control panel, HF control(optional), aileron/elevator disconnect handles, Autopilot control, SPS, T/O configuration switch, and anFMS control display unit. One of different possible configurations of the control pedestal includes radiomanagement units.
2.4.6 Pilot Seat
The pilot seat is provided with longitudinal, vertical (electrically actuated), seat back, and lumbaradjustments. The seat is attached to tracks which permit the horizontal adjustments.
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An extended longitudinal travel permits pilot rest during long cruise flights (pilot foot rests are providedat the bottom of the main instrument panel).
2.4.7 Passenger Cabin
A 0.43 m (17 in) wide aisle, with a recessed floor leaving a 1.82 m (6 ft) height, allows for stand-upwalking and the use of standard catering trolleys. The passenger cabin is 2.10 m (6 ft 11 in) wide and thestandard configuration accommodates 50 passengers in 16 double seats on the right side, and 18 singleseats on the left side, with a 31 in pitch. Different cabin layouts with increased capacity for galley andwardrobe are available as optional models.
2.4.8 Passenger Seat
The ergonomic reclining seats were designed for a 0.79 m (31 in) pitch, with comfortable leg room.Double seats incorporate fold-up center arm rests. All seats are offered with snack tables, magazinepouches, underseat life-vest stowage, seat belts, and an adequate underseat room for carry-on articles.
2.4.9 Passenger Service Unit
The passenger service unit contains gasper air outlets, reading lights, loudspeakers, attendant callingbuttons, warnings, and oxygen dispensing unit for each seat.
2.4.10 Overhead Bin
The overhead bin is divided into eleven sections and is installed on the right side of the cabin. The binshave a total volume of 1.90 m3 (67.1 ft3) and is designed for a 290 kg (639 lb) loading.
2.4.11 Wardrobe
A wardrobe with a 0.93 m3 (32.9 ft3) and 70 kg (154 lb) capacity is offered for carry-on articles on theforward right side of the passenger cabin between the galley and cockpit partition.
2.4.12 Stowage Compartment
A stowage compartment with a 0.45 m3 (16 ft3) and 40 kg (88 lb) capacity is also offered on the forwardright side of the passenger cabin, close to the service door. Such compartment is modular so that it canbe replaced by one or two half trolleys, as in the optional models.
2.4.13 Flight Attendant Station
The standard flight attendant station is positioned at the cockpit partition, close to the main door. The seatis of the fold-away type, to avoid interference with the door passageway. A seat for a second flightattendant is available, as an option, at the aft end of the aisle, standing in front of the lavatory door. Whennot in use, adequate mechanisms allow its sliding against the lavatory wall, behind the last double-seatrow.The attendant seats are made up of machined parts combined with flat sandwich panels of graphite andNomex honeycomb core.
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2.4.14 Lavatory
The lavatory is installed at the aft cabin and contains a washbasin, waste container, ashtray, mirror, paperdispenser, automatic fire extinguisher, smoke detection system, and a recirculating toilet unit. A toiletshroud and a ventilation system, at the cabinet and waste tank, assure an odorless environment.
2.4.15 Galley
The galley is installed in the forward passenger cabin.
2.4.16 Baggage Compartment
The baggage compartment complies with the FAR-25 ″class D″ requirements (standard) or FAR-25″class C″ (optional), presenting an available volume of 9.21 m3 (325 ft3) and maximum loading of 1200kg (2645 lb). The floor is designed for 390 kg/m2 (80 lb/ft2) uniform distributed loading, and is providedwith anchor plates for high-density load tie-down.
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Figure 2.4.1 - EMB-145 Interior Arrangements-Basic Configuration
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Figure 2.4.2 - EMB-145 Interior Arrangements-Optional Configuration
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2.5 Passenger Cabin Cross-Section
Figure 2.5.1 - EMB-145 Passenger Cabin Cross-Section
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2.6 Lower Compartment Containers
The EMB-145 aircraft does not have lower compartment containers.
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2.7 Door Clearances
Figure 2.7.1 - EMB-145 Door ClearancesSheet 1
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3. AIRPLANE PERFORMANCE
3.1 General Information
Section 3.2 presents payload x range information for a specific long range, cruise altitude, and the fuelreserve condition shown.Sections 3.3 and 3.4 represent FAR takeoff and landing runway length requirements for FAA certification.Standard day temperatures for the altitudes shown are tabulated below:
Table 3.1.1 - Standard Day Temperatures x Elevation
ELEVATION STANDARD DAY TEMPft m oF oC0 0 59 15
2000 610 51.9 11.64000 1220 44.7 7.16000 1830 37.6 3.18000 2440 30.5 -0.8
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3.2 Payload x Range
Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 1
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 2
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 3
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 4
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 5
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 6
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 7
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 8
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Figure 3.2.1 - Payload x Range for Long Range Cruise at 37,000 ft, Engine with ThrustReverserSheet 9
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3.3 FAR Takeoff Runway Length Requirements
FLAPS 9/22 T/O−1 MODE, NO ENGINE BLEED FORAIR CONDITIONING
4000
9000
5000
6000
7000
8000
10000
4800028000 32000 36000 40000 44000
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
ft
OPERATIONAL TAKEOFF WEIGHT − kg
OPERATIONAL TAKEOFF WEIGHT − lb
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
2600
2700
2800
2900
3000
12000 14000 16000 18000 20000 22000
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WINDISA
AE3007 A1 ENGINES
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
m
2438
(800
0)
SL
610
(200
0)
1219
(400
0)
1829
(600
0)
145APM030124.MCE E
Figure 3.3.1 - FAR Takeoff Runway Length Requirements - ISA ConditionsSheet 1
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FLAPS 9/22 T/O−1 MODE, NO ENGINE BLEED FORAIR CONDITIONING
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
m
OPERATIONAL TAKEOFF WEIGHT − kg
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WINDISA
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
2600
2700
2800
2900
3000
3100
3200
3300
3400
3500
12000 14000 16000 18000 20000 22000
AE3007 A1/1 ENGINES
2438
(800
0)
SL
610 (
2000
)
1219
(400
0)
1829
(600
0)
4800028000 32000 36000 40000 44000OPERATIONAL TAKEOFF WEIGHT − lb
4000
9000
5000
6000
7000
8000
10000
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
ft
11000
145APM030121.MCE E
Figure 3.3.1 - FAR Takeoff Runway Length Requirements - ISA ConditionsSheet 2
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12000 14000 16000 18000 20000 220001200
1400
1600
1800
2000
2200
2400
2600
2800
3000
FLAPS 18°
24000 26000
3200
FLAPS 9°
4800028000 32000 36000 40000 44000 52000 56000
AIRPORTELEVATION − m (ft)
SL61
0 (20
00)
1219
(400
0)
1829
(600
0)
2438
(800
0)
3048
(100
00)
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WIND
FLAPS 9/22 ET/O THRUST MODE, NO ENGINE BLEED FORAIR CONDITIONING
AE 3007 A1E ENGINES
ISA
4000
9000
5000
6000
7000
8000
10000
OPERATIONAL TAKEOFF WEIGHT − kg
OPERATIONAL TAKEOFF WEIGHT − (lb)
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
(ft)
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
m
Figure 3.3.1 - FAR Takeoff Runway Length Requirements - ISA ConditionsSheet 3
AIRPORTPLANNING MANUAL
wipapm
1100 REV J
3-13
FLAPS 9°
FLAPS 18°
FLAPS 22°
12000 14000 16000 18000 20000 22000 240001200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
145APM030380.MCE
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
m
4800028000 32000 36000 40000 44000 52000
2438
(800
0)
1829
(600
0)12
19 (4
000)
610
(200
0)SL
4000
9000
5000
6000
7000
8000
10000
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WIND
FLAPS 9/18/22 T/O MODE, NO ENGINE BLEED FORAIR CONDITIONING
AE 3007 A1P ENGINES
ISA
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
(ft)
OPERATIONAL TAKEOFF WEIGHT − kg
OPERATIONALTAKEOFF WEIGHT − (lb)
AIRPORTELEVATION− m (ft)
Figure 3.3.1 - FAR Takeoff Runway Length Requirements - ISA ConditionsSheet 4
AIRPORTPLANNING MANUAL
wipapm
1100REV J
3-14
FLAPS 9/22 T/O−1 MODE, NO ENGINE BLEED FORAIR CONDITIONING
OPERATIONAL TAKEOFF WEIGHT − kg
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
m
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WINDISA+15°C
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
2600
2700
2800
2900
3000
3100
3200
12000 14000 16000 18000 20000 22000
AE3007 A1 ENGINES
2438
(800
0)
SL610
(200
0)1219
(400
0)
1829
(600
0)
4800028000 32000 36000 40000 44000OPERATIONAL TAKEOFF WEIGHT − lb 145APM030125.MCE E
4000
9000
5000
6000
7000
8000
10000
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
ft
Figure 3.3.2 - FAR Takeoff Runway Length Requirements - ISA + 15oC ConditionsSheet 1
AIRPORTPLANNING MANUAL
wipapm
1100 REV J
3-15
FLAPS 9/22 T/O−1 MODE, NO ENGINE BLEED FORAIR CONDITIONING
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
m
OPERATIONAL TAKEOFF WEIGHT − kg
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WINDISA+15°C
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
2600
2700
2800
2900
3000
3100
3200
3300
3400
3500
12000 14000 16000 18000 20000 22000
AE3007 A1/1 ENGINES
2438
(800
0)
SL
610 (
2000
)
1219
(400
0)
1829
(600
0)
4800028000 32000 36000 40000 44000OPERATIONAL TAKEOFF WEIGHT − lb 145APM030122.MCE E
4000
9000
5000
6000
7000
8000
10000
FAR
TAK
EOFF
RU
NW
AY L
ENG
TH −
ft
11000
Figure 3.3.2 - FAR Takeoff Runway Length Requirements - ISA + 15oC ConditionsSheet 2
AIRPORTPLANNING MANUAL
wipapm
1100REV J
3-16
145APM030374.MCE B
12000 14000 16000 18000 20000 220001200
1400
1600
1800
2000
2200
2400
2600
2800
3000
FLAPS 18°
FLAPS 9°
24000 26000
3200
4800028000 32000 36000 40000 44000 52000 56000
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
m
3048
(100
00)
2438
(800
0)
1829
(600
0)12
19 (4
000)
610 (
2000
)
SL
AIRPORTELEVATION − m (ft)
4000
9000
5000
6000
7000
8000
10000
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WINDISA+15°C
FLAPS 9/22 ET/O THRUST MODE, NO ENGINE BLEED FORAIR CONDITIONING
AE 3007 A1E ENGINES
OPERATIONAL TAKEOFF WEIGHT − kg
OPERATIONAL TAKEOFF WEIGHT − (lb)
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
(ft)
Figure 3.3.2 - FAR Takeoff Runway Length Requirements - ISA + 15oC ConditionsSheet 3
AIRPORTPLANNING MANUAL
wipapm
1100 REV J
3-17
FLAPS 9°
FLAPS 18°
FLAPS 22°
12000 14000 16000 18000 20000 22000 240001200
1400
1600
1800
2000
2200
2400
2600
2800
3000
3200
145APM030379.MCE
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
m
610
(200
0)
1219
(400
0)
1829
(600
0)
2438
(800
0)
SL
AIRPORTELEVATION − m (ft)
4800028000 32000 36000 40000 44000 52000
TAKEOFF RUNWAY LENGTH REQUIREMENTS
DRY AND LEVELED RUNWAY, ZERO WINDISA+15°C
4000
9000
5000
6000
7000
8000
10000
FLAPS 9/18/22 T/O MODE, NO ENGINE BLEED FORAIR CONDITIONING
AE 3007 A1P ENGINES
OPERATIONAL TAKEOFF WEIGHT − kg
OPERATIONAL TAKEOFF WEIGHT − (lb)
FAR
TAK
EOFF
FIE
LD L
ENG
TH −
(ft)
Figure 3.3.2 - FAR Takeoff Runway Length Requirements - ISA + 15oC ConditionsSheet 4
AIRPORTPLANNING MANUAL
wipapm
1100REV J
3-18
3.4 FAR Landing Runway Length Requirements
Figure 3.4.1 - FAR Landing Runway Length Requirements - Flaps 45oSheet 1
AIRPORTPLANNING MANUAL
wipapm
1100 REV J
3-19
Figure 3.4.1 - FAR Landing Runway Length Requirements - Flaps 45oSheet 2
AIRPORTPLANNING MANUAL
wipapm
1100REV J
3-20
145APM030376.MCE B
12000900
1000
1100
1200
1300
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
10000 14000 16000 18000 20000 22000 24000 26000 28000
LAN
DIN
G F
IELD
LEN
GTH
− m
24000 48000 52000 56000 6000028000 32000 36000 40000 44000
2438
(800
0)
2133
(700
0)
1829
(600
0)
1524
(500
0)
1219
(400
0)
914 (
3000
)
610 (2000)
305 (1000)
SL
−305 (1000)
AIRPORT ELEVATION− m (ft)
3048
(100
00)
2743
(900
0)
AE 3007 A1E ENGINES
LANDING RUNWAY LENGTHDRY AND LEVELED RUNWAY
ZERO WIND, ISAFLAPS 45°
7000
7500
8000
6500
6000
5500
5000
4500
4000
3500
3000
LAN
DIN
G F
IELD
LEN
GTH
− (f
t)
OPERATIONAL LANDING WEIGHT − kg
OPERATIONAL LANDING WEIGHT − (lb)
Figure 3.4.1 - FAR Landing Runway Length Requirements - Flaps 45oSheet 3
AIRPORTPLANNING MANUAL
wipapm
1100 REV J
3-21
SL
900
1000
1100
1200
1300
1400
1500
1600
1700
1800
1900
2000
210001900017000150001300011000
145APM030381.MCE26000
LAN
DIN
G F
IELD
LEN
GTH
− m
30000 34000 38000 42000 46000
AIRPORT ELEVATION − m (ft)
2133
(700
0)
1219
(400
0)
914 (3000)
305 (1000)
610 (2000)
1524
(500
0)1829
(600
0)
2438
(800
0)
6500
6000
5500
5000
4500
4000
3500
3000
LANDING RUNWAY LENGTHDRY AND LEVELED RUNWAY
ZERO WIND, ISAFLAPS 45°
AE 3007 A1P ENGINES
OPERATIONAL LANDING WEIGHT − kg
OPERATIONAL LANDING WEIGHT − (lb)
LAN
DIN
G F
IELD
LEN
GTH
− (f
t)
Figure 3.4.1 - FAR Landing Runway Length Requirements - Flaps 45oSheet 4
AIRPORTPLANNING MANUAL
wipapm
1100REV J
3-22
4. GROUND MANEUVERING
4.1 General Information
This section provides the airplane turning capability and maneuvering characteristics. For ease ofpresentation, these data have been determined from theoretical limits imposed by the geometry of theaircraft.As such, they reflect the turning capability of the aircraft in favorable operating circumstances. Thesedata should be used only as guidelines for the method of determination of such parameters and for themaneuvering characteristics of the EMB-145.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. Airlineoperating techniques will vary, as far as the performance is concerned, over a wide range of operatingcircumstances throughout the world.Variations from standard aircraft operating patterns may be necessary to satisfy physical constants withinthe maneuvering area, such as adverse grades, limited area, or high risk of jet blast damage. For thesereasons, the ground maneuvering requirements should be coordinated with the using airline prior to thelayout planning.Section 4.2 presents the turning radii for various nose gear steering angles.Section 4.3 presents data on the minimum width of the pavement for 180o turn.Section 4.4 presents the pilot’s visibility from the cockpit and the limits of ambinocular vision through thewindows. Ambinocular vision is defined as the total field of vision seen by both eyes at the same time.Section 4.5 presents the performance of the EMB-145 on runway-to-taxiway and taxiway-to-taxiway turnpaths.Section 4.6 presents the runway holding bay configuration.
AIRPORTPLANNING MANUAL
wipapm
1100 REV C
4-1
4.2 Turning Radii - No Slip Angle
22.07 m
30.72 m
20.66 m
20.61 m
27.31 m
19.08 m
19.48 m
18.62 m
17.86 m
17.95 m
16.90 m
7.74 m
16.16 m
20.52 m
20.24 m
5.96 m
9.12 m
19.00 m
7.64 m
4.35 m
5.99 m
16.88 m
2.87 m
17.01 m
17.44 m
45˚35˚40˚
16.69 m
10.73 m 18.47 m 17.75 m
15.6 m
12.50 m
15.4 m
15.11 m
15.8 m
14.51 m
1.25 m
23.99 m
9.74 m
13.77 m
22.23 m
16.83 m
14.92 m
26.56 m
22.70 m
12.07 m 80 ft 6 in
19.60 m
25.41 m
24.55 m
14.84 m
22.37 m
23.02 m 18.25 m
24.68 m
27.64 m
R2
55˚60˚
65˚
R3
76˚
R6
R4
R5
70˚
35
40
45
50
55
60
65
70
76
19.11 m 17.45 m 7.00 m11.77 m 19.51 m 18.47 m57
STEERINGANGLE
NOSER1
NOSEGEAR
R2
OUTBOARDGEAR
R3
INBOARDGEAR
R4
RIGHTWINGTIP
R5
RIGHTTAILTIP
R6
1
1
2
2
TURNING CENTERS
POST-MOD S.B. 145-32-0002MAXIMUM STEERING ANGLE 76˚.
PRE-MOD S.B. 145-32-0002MAXIMUM STEERING ANGLE 57˚.
55 ft 9 in
57 ft 2 in
87 ft 2 in
78 ft 8 in
72 ft 5 in
67 ft 7 in
63 ft 11 in
62 ft 8 in
61 ft 1 in
58 ft 11 in
83 ft 4 in
74 ft 6 in
67 ft 9 in
62 ft 7 in
58 ft 7 in
57 ft 3 in
55 ft 5 in
53 ft 0 in
51 ft 2 in
49 ft 7 in
75 ft 6 in
64 ft 4 in
55 ft 3 in
47 ft 7 in
41 ft 0 in
38 ft 7 in
35 ft 2 in
29 ft 11 in
25 ft 1 in
19 ft 8 in
59 ft 10in
48 ft 8 in
39 ft 7 in
31 ft 11 in
25 ft 5 in
23 ft 0 in
19 ft 6 in
14 ft 3 in
9 ft 5 in
4 ft 1 in
100 ft 9 in
89 ft 7 in
72 ft 11 in
66 ft 5 in
64 ft 0 in
60 ft 7 in
55 ft 4 in
50 ft 7 in
45 ft 2 in
90 ft 8 in
80 ft 11 in
73 ft 4 in
67 ft 4 in
62 ft 4 in
60 ft 7 in
58 ft 3 in
54 ft 9 in
51 ft 10 in
48 ft 11 in
11.43 m37 ft 6 in
17.23 m
56 ft 6 in
50˚
R1
57˚
EMB-145 EP/ER/EU/MP/MK/LR/LU145APM000039.MCE A
Figure 4.2.1 - Turning Radii - No Slip AngleSheet 1
AIRPORTPLANNING MANUAL
wipapm
1100REV G
4-2
145APM040462.MCE
R1NOSE
R2GEARNOSE
R4 R5 R6R3
65˚
76˚
60˚
70˚
55˚50˚45˚40˚35˚
ANGLESTEERING
63ft 11in18.62 m19.48 m
61ft 1in
67ft 7in
17.95 m
20.61 m
58ft 11in
72ft 5in
17.44 m
22.07 m
57ft 2in
78ft 8in
17.01 m
23.99 m
55ft 9in
26.56 m 87ft 2in
58ft 7in16.90 m17.86 m
55ft 5in
62ft 7in
16.16 m
19.08 m
53ft 0in
67ft 9in20.66 m
51ft 2in
74ft 6in
15.11 m
22.70 m
49ft 7in
83ft 4in25.41 m
41ft 0in10.73 m12.50 m
35ft 2in
47ft 7in
9.12 m
14.51 m
29ft 1in
55ft 3in
7.64 m
16.83 m
25ft 1in
64ft 4in
5.99 m
19.60 m
19ft 8in
75ft 6in23.02 m
25ft 5in5.96 m7.74 m
31ft 11in
4.35 m
9.74 m39ft 7in
2.87 m
12.07 m
9ft 5in
48ft 8in
1.25 m
14.84 m
4ft 1in
18.25 m 59ft 10in
15.97 m
74ft 8in
47ft 0in14.33 m
82ft 3in
52ft 5in
68ft 2in
17.43 m 57ft 2in
22.77 m20.78 m
62ft 5in
25.08 m91ft 4in27.84 m
102ft 6in31.24 m
48ft 11in
62ft 4in
73ft 4in
16.69 m
27.64 m
17.75 m19.00 m
22.37 m
51ft 10in
24.68 m
54ft 9in
14.92 m
67ft 4in
90ft 8in80ft 11in
58ft 3in
20.52 m
19.02 m19ft 6in14ft 3in
OUTBOARD GEAR INBOARD GEAR RIGHT TAILTIPRIGHT WINGTIP
15.6 m 15.8 m
R
R 5.65m18ft 6in
14.89m48ft 10in
21.21m69ft 7in
(RUNWAY MINIMUM WIDTH)
R5
R3
R1
R2
R4
35˚40˚
45˚50˚
55˚60˚65˚
70˚76˚
R6
EMB-145XR
Figure 4.2.1 - Turning Radii - No Slip AngleSheet 2
AIRPORTPLANNING MANUAL
wipapm
1100 REV G
4-3
4.3 Minimum Turning Radii
1
11.43 m37 ft 6 in
17.23 m56 ft 6 in
R5
R3 R6
R4
R1
R2
Y
X
57˚
29.22 m95 ft 10 in
19.11 m 17.45 m 7.00 m11.77 m 19.51 m 18.47 m
STEERINGANGLE
NOSER1
NOSEGEAR
R2
OUTBOARDGEAR
R3
INBOARDGEAR
R4
RIGHTWINGTIP
R5
RIGHTTAILTIP
R6
1X Y NOTE:
14.45 m 9.38 m
PAVEMENT WIDTH FOR180˚ TURN
62 ft 8 in 57 ft 3 in 38 ft 7 in 23 ft 0 in 64 ft 0 in 60 ft 7 in
47 ft 5 in 30 ft 9 in
57˚
THE CORRECT OPERATING DATA WILL BEHIGHER THAN THE VALUES SHOWNBECAUSE TIRE SLIPPAGE IS NOTINCLUDED IN THIS CALCULATION.
EMB-145 EP/ER/EU/MP/MK/LR/LU145APM000040.MCE A
Figure 4.3.1 - Minimum Turning Radii - PRE-MOD. S.B. 145-32-0002
AIRPORTPLANNING MANUAL
wipapm
1100REV G
4-4
Y
X
76
R1
R2
R3
R5
R4
5.65 m18 ft 6 in
R6
21.21 m69 ft 7 in
1
14.89 m48 ft 10 in
17.01 m 15.11 m 1.25 m 13.77 m 14.92 m
STEERINGANGLE
NOSER1
NOSEGEAR
R2
OUTBOARDGEAR
R3
INBOARDGEAR
R4
RIGHTWINGTIP
R5
RIGHTTAILTIP
R6
1X Y NOTE:
14.45 m 3.6 m
PAVEMENT WIDTH FOR180˚ TURN
48 ft 11 in
47 ft 5 in 11 ft 10 in
76˚ 55 ft 9 in 49 ft 7 in 5.99 m 19 ft 8 in 4 ft 1 in 45 ft 2 in
THE CORRECT OPERATING DATA WILL BEHIGHER THAN THE VALUES SHOWNBECAUSE TIRE SLIPPAGE IS NOTINCLUDED IN THIS CALCULATION.
145APM000042.MCE B
EMB-145 EP/ER/EU/MP/MK/LR/LU
Figure 4.3.2 - Minimum Turning Radii - POST-MOD. S.B. 145-32-0002
AIRPORTPLANNING MANUAL
wipapm
1100 REV G
4-5
R1NOSE
R2GEARNOSE
R4 R5 R6R376°
ANGLESTEERING
17.01 m 55ft 9in 15.11 m 49ft 7in 5.99 m 19ft 8in 1.25 m 4ft 1in 47ft 0in14.33 m 48ft 11in14.92 m
OUTBOARD GEAR INBOARD GEAR RIGHT TAILTIPRIGHT WINGTIP
R
R 5.65m18ft 6in
14.89m48ft 10in
21.21m69ft 7in
(RUNWAY MINIMUM WIDTH)
R5
R3
R1
R2
R4
76°
R6
NOTE: ACTUAL OPERATING DATA WILL BEGREATER THAN VALUES SHOWNSINCE TIRE SLIPPAGE IS NOTCONSIDERED IN THIS CALCULATION.
1PAVEMENT WIDTHFOR 180° TURN
14.45 m(47ft 5in)
1
EMB−145XR
145APM040463.MCE A
Figure 4.3.3 - Minimum Turning Radii
AIRPORTPLANNING MANUAL
wipapm
1100REV G
4-6
4.4 Visibility from Cockpit in Static Position
23°
14°0.61 m
3.53 m
PILOT’S EYE POSITION
VISUAL ANGLES IN PLANEPARALLEL TO LONGITUDINALAXIS THROUGH PILOT’S EYEPOSITION
PILOT’S EYE POSITION
MAXIMUM AFT VISIONWITH HEAD ROTATEDABOUT SPINAL COLUMN
0.41 m
124°
VISUAL ANGLE IN PLANEPERPENDICULAR TO LONGITUDINALAXIS THROUGH PILOT’S EYE POSITION
PILOT’S EYE POSITION0.45 m
15°
33°
145APM000015.MCE A
10.43 m(12 ft 7 in)
(34 ft 3 in)
Figure 4.4.1 - Visibility from Cockpit in Static Position
AIRPORTPLANNING MANUAL
wipapm
1100 REV H
4-7
4.5 Runway and Taxiway Turn Paths
Figure 4.5.1 - More than 90o Turn - Runway to Taxiway
AIRPORTPLANNING MANUAL
wipapm
1100REV G
4-8
4.6 Runway Holding Bay
Figure 4.6.1 - Runway Holding Bay
AIRPORTPLANNING MANUAL
wipapm
1100 REV G
4-11
5. TERMINAL SERVICING
5.1 General Information
During turnaround at the air terminal, certain services must be performed on aircraft, usually within agiven time to meet flight schedules. This section shows service vehicle arrangements, schedules,locations of servicing points, and typical servicing requirements. The data presented herein reflect idealconditions for a single airplane. Servicing requirements may vary according to the airplane condition andairline procedure.This section provides the following information:
– Typical arrangements of ground support equipment during turnaround.
– Typical turnaround and enroute servicing times at an air terminal. These charts give typical schedulesfor performing servicing on the airplane within a given time. Servicing times could be rearranged tosuit availability of personnel, airplane configuration, and degree of servicing required.
– The locations of ground servicing connections in graphic and tabular forms. Typical capacities andservicing requirements are shown in the figures. Services with requirements that vary with conditionsare described in subsequent figures.
– Air conditioning requirements for heating and cooling the airplane, using low-pressure conditioned air.This conditioned air is supplied through an 8-inch GAC directly to the air distribution system,bypassing the air-cycle machines. Normally, a 36000 BTU/h source would be sufficient to meet the airconditioning requirements.
– Ground towing requirements for various towing conditions. Drawbar pull and total traction wheel loadmay be determined by considering airplane weight, pavement slope, coefficient of friction, and engineidle thrust.
AIRPORTPLANNING MANUAL
wipapm
1100 REV C
5-1
Figure 5.1.1 - EMB-145 Airplane Servicing ArrangementSheet 1
AIRPORTPLANNING MANUAL
wipapm
1100REV I
5-2
Figure 5.1.1 - EMB-145 Airplane Servicing ArrangementSheet 2
AIRPORTPLANNING MANUAL
wipapm
1100 REV I
5-3
5.2 Air Terminal Operation - Turnaround Station
CLEAR AIRPLANE FOR DEPARTURE
PASSENGERSERVICE
MIN
5 10 15 20TIME (MINUTES)
OPERATIONS
COCKPITCREWDUTIES
BAGGAGEAND
CARGO
OTHERSERVICE
SHUTDOWN ENGINES
DEPLANE PASSENGERS
SERVICE AIRPLANE INTERIOR
SERVICE GALLEY
SERVICE POTABLE WATER
ENPLANE PASSENGERS
UNLOAD BAGGAGE/CARGO
LOAD BAGGAGE/CARGO
SERVICE TOILET
1
2
4
6
7
5
5
6
8
10
7
NOTE: − TIME OF 18 MINUTES INCLUDES EQUIPMENT POSITIONING AND REMOVAL− 85% FUEL TANK CAPACITY REFUELING PRESSURE 50 psi (344 kPa) at 125 gpm (473 lpm)
12
FUEL AIRPLANE [ 1 ]
FUEL AIRPLANE [ 2 ]
14FUEL AIRPLANE [ 3 ]
[ 1 ] APPLICABLE TO EMB−145 ER/EU/EP/MR/MP[ 2 ] APPLICABLE TO EMB−145 LR/LU[ 3 ] APPLICABLE TO EMB−145 XR
145APM000001.MCE C
Figure 5.2.1 - Air Terminal Operation - Turnaround Station
AIRPORTPLANNING MANUAL
wipapm
1100REV I
5-4
5.3 Air Terminal Operation - Enroute Station
PASSENGERSERVICE
COCKPITCREW
DUTIES
BAGGAGEAND
CARGO
OTHERSERVICE SERVICE TOILET
LOAD BAGGAGE/CARGO
TIME (MINUTES)
MIN
1
2
5 10 15 20
3
3
5
3
4
6
UNLOAD BAGGAGE/CARGO
SERVICE POTABLE WATER
SERVICE GALLEY
SERVICE AIRPLANE INTERIOR
DEPLANE PASSENGERS
CLEAR AIRPLANE FOR DEPARTURE
SHUTDOWN ENGINES
OPERATIONS
25
4.5
5.5
NOTE: − TIME OF 12 MINUTES INCLUDES EQUIPMENT POSITIONING AND REMOVAL
145APM000002.MCE A
Figure 5.3.1 - Air Terminal Operation - Enroute Station
AIRPORTPLANNING MANUAL
wipapm
1100 REV I
5-5
5.4 Ground Servicing Connections EMB-145
Figure 5.4.1 - Ground Servicing Connections EMB-145 ER / MP
AIRPORTPLANNING MANUAL
wipapm
1100REV I
5-6
Table 5.4.1 - Ground Servicing Connections EMB-145 ER / MP
SYSTEMDISTANCE AFTOF NOSE
DISTANCE FROM AIRPLANECENTERLINE
HEIGHTABOVEGROUND
RIGHT SIDE LEFT SIDE MAXIMUMft-in m ft-in m ft-in m ft-in m
1. Hydraulic Power SystemThree Servicing Connections:A. Nose Servicing Panel ............................................ 6-3 1.90 2-8 0.81 - - 5-7 1.69B. LH and RH Servicing Panels ................................ 63-3 19.27 1-9 0.53 1-9 0.53 5-4 1.632. Electrical Power SystemOne External Power Supply Connection 28 V DC -1600 A ........................................................................ 7-5 2.26 - - 3-1 0.94 5-7 1.713. Oxygen SystemOne Servicing Panel .................................................. 12-11 3-93 2-8 0.81 - - 5-1 1.544. Fuel SystemA. Gravity Fuel Filler Port .......................................... 52-6 16.00 17-10 5.43 17-10 5.43 6-1 1.84B. Fuel Magnetic Stick ............................................... 49-8 15.15 8-11 2.73 8-11 2.73 4-3 1.31C. Fuel Magnetic Stick ............................................... 52-5 15.99 16-4 4.98 16-4 4.98 5-6 1.57D. Fuel Drain Valve .................................................... 48-11 14.91 3-6 1.06 3-6 1.06 4-6 1.37E. Fuel Dump Valve ................................................... 48-1 14.66 5-1 1.55 5-1 1.55 3-8 1.12F. Pressure Refueling/Defueling Panel ...................... 38-1 11.62 2-10 0.86 - - 4-11 1.515. Air Conditioning SystemOne Pressurization Ground Test Connection ............ 40-3 12.26 2-5 0.73 - - 5-2 1.57One Air Conditioning Ground Connection ................. 35-8 10.88 1-6 0.46 5-3 1.606. Potable Water SystemOne Servicing Panel .................................................. 66-0 20.12 0-2 0.10 - - 5-12 1.827. Lavatory SystemWaste Servicing Panel ............................................... 68-0 20.74 1-6 0.45 - - 5-3 1.618. PowerplantTwo Engine Oil Supply/Level Check Panels:A. LH Panel ................................................................ 74-7 22.73 - - 6-1 1.84 10-1 3.06B. RH Panel ............................................................... 74-7 22.73 7-8 2.35 - - 10-1 3.06Ground Connection for Engine Air Starting ............... 76-11 23.46 0-11 0.27 - - 5-2 1.57
AIRPORTPLANNING MANUAL
wipapm
1100 REV I
5-7
Table 5.4.2 - Ground Servicing Connections EMB-145 LR
SYSTEMDISTANCE AFTOF NOSE
DISTANCE FROM AIRPLANECENTERLINE
HEIGHTABOVEGROUND
RIGHT SIDE LEFT SIDE MAXIMUMft-in m ft-in m ft-in m ft-in m
1. Hydraulic Power SystemThree Servicing Connections:A. Nose Servicing Panel ............................................ 6-3 1.90 2-8 0.81 - - 5-7 1.69B. LH and RH Servicing Panels ................................ 63-3 19.27 1-9 0.53 1-9 0.53 5-4 1.632. Electrical Power SystemOne External Power Supply Connection 28 V DC -1600 A ........................................................................ 7-5 2.26 - - 3-1 0.94 5-7 1.713. Oxygen SystemOne Servicing Panel .................................................. 12-11 3-93 2-8 0.81 - - 5-1 1.544. Fuel SystemA. Gravity Fuel Filler Port .......................................... 52-6 16.00 17-10 5.43 17-10 5.43 6-1 1.84B. Fuel Magnetic Stick ............................................... 49-8 15.15 8-11 2.73 8-11 2.73 4-3 1.31C. Fuel Magnetic Stick ............................................... 52-5 15.99 16-4 4.98 16-4 4.98 5-6 1.57D. Fuel Magnetic Stick ............................................... 47-4 14.44 1-1 0.35 1-1 0.35 3-6 1.06E. Fuel Drain Valve .................................................... 48-11 14.91 3-6 1.06 3-6 1.06 4-6 1.37F. Fuel Drain Valve ..................................................... 49-2 14.98 1-4 0.41 1-4 0.41 3-6 1.06G. Fuel Dump Valve ................................................... 47-4 14.44 2-2 0.68 2-2 0.68 3-6 1.06H. Pressure Refueling/Defueling Panel ..................... 38-1 11.62 2-10 0.86 - - 4-11 1.515. Air Conditioning SystemOne Pressurization Ground Test Connection ............ 40-3 12.26 2-5 0.73 - - 5-2 1.57One Air Conditioning Ground Connection ................. 35-8 10.88 1-6 0.46 5-3 1.606. Potable Water SystemOne Servicing Panel .................................................. 66-0 20.12 0-2 0.10 - - 5-12 1.827. Lavatory SystemWaste Servicing Panel ............................................... 68-0 20.74 1-6 0.45 - - 5-3 1.618. PowerplantTwo Engine Oil Supply/Level Check Panels:A. LH Panel ................................................................ 74-7 22.73 - - 6-1 1.84 10-1 3.06B. RH Panel ............................................................... 74-7 22.73 7-8 2.35 - - 10-1 3.06Ground Connection for Engine Air Starting ............... 76-11 23.46 0-11 0.27 - - 5-2 1.57
AIRPORTPLANNING MANUAL
wipapm
1100 REV I
5-9
145APM050564.MCE
FUEL DUMP VALVE
FUEL DRAIN VALVE
FUEL MAGNETIC STICK
GRAVITY FUEL FILLER PORT
GROUNDING POINT (3 POSITIONS)
OXYGEN SERVICE PANEL
AIR CONDITIONING GROUND CONNECTION
PRESSURE REFUELING/DEFUELING PANEL
PRESSURIZATION GROUND TEST CONNECTION
FUEL DUMP VALVE
FUEL DRAIN VALVE
FUEL MAGNETIC STICK
GRAVITY FUEL FILLER PORT
ENGINE OIL TANK SIGHT GLASS
APU ACCESS PANEL
BATTERY COMPARTMENT ACCESS HATCH
FWD ELECTRONICCOMPT ACCESS HATCH
GROUNDING POINT (3 POSITIONS)EXTERNAL POWERSUPPLY CONNECTION &INTERPHONE JACK (2 POSITIONS)
MAIN DOOR CONTROL
COCKPIT UNDERFLOORACCESS HATCH
INTERPHONE JACK (2 POSITIONS)
FLIGHT CONTROLS ACCESS HATCH
ENGINE STARTING GROUND CONNECTION
GROUNDING POINT (3 POSITIONS)
NOSE HYDRAULIC COMPTSERVICING PANEL
POTABLE WATER SERVICING PANEL
WASTE SERVICING PANEL
REAR ELECTRONICACCESS HATCH
FUEL DRAIN VALVE
FUEL DUMP VALVE
FUEL DRAIN VALVE
FUEL DRAIN VALVE
FUEL DRAIN VALVELH/RH HYDRAULIC COMPTSERVICING PANEL
Figure 5.4.3 - Ground Servicing Connections EMB-145 XR
AIRPORTPLANNING MANUAL
wipapm
1100REV I
5-10
Table 5.4.3 - Ground Servicing Connections EMB-145 XR
SYSTEMDISTANCE AFTOF NOSE
DISTANCE FROM AIRPLANECENTERLINE
HEIGHTABOVEGROUND
RIGHT SIDE LEFT SIDE MAXIMUMft-in m ft-in m ft-in m ft-in m
1. Hydraulic Power SystemThree Servicing Connections:A. Nose Servicing Panel ............................................ 6-3 1.90 2-8 0.81 - - 5-7 1.69B. LH and RH Servicing Panels ................................ 63-3 19.27 1-9 0.53 1-9 0.53 5-4 1.632. Electrical Power SystemOne External Power Supply Connection 28 V DC -1600 A ........................................................................ 7-5 2.26 - - 3-1 0.94 5-7 1.713. Oxygen SystemOne Servicing Panel .................................................. 12-11 3-93 2-8 0.81 - - 5-1 1.544. Fuel SystemA. Gravity Fuel Filler Port .......................................... 52-6 16.00 17-10 5.43 17-10 5.43 6-2 1.88B. Fuel Magnetic Stick ............................................... 49-10 15.20 8-9 2.67 8-9 2.67 5-9 1.77C. Fuel Magnetic Stick ............................................... 52-6 16.00 16-4 4.98 16-4 4.98 5-6 1.88D. Fuel Drain Valve .................................................... 49-2 15.00 3-6 1.07 3-6 1.07 4-6 1.13E. Fuel Drain Valve .................................................... 56-10 17.33 0-2 0.06 0-2 0.06 3-5 1.05F. Fuel Dump Valve .................................................... 48-2 14.70 5-1 1.55 5-1 1.55 3-11 1.21G. Fuel Dump Valve ................................................... 57-8 17.58 - - - - 3-6 1.07H. Pressure Refueling/Defueling Panel ..................... 38-0 11.59 3-4 1.02 - - 4-7 1.425. Air Conditioning SystemOne Pressurization Ground Test Connection ............ 40-3 12.26 2-5 0.73 - - 5-2 1.57One Air Conditioning Ground Connection ................. 35-8 10.88 1-6 0.46 5-3 1.606. Potable Water SystemOne Servicing Panel .................................................. 66-0 20.12 0-2 0.05 - - 5-12 1.827. Lavatory SystemWaste Servicing Panel ............................................... 68-0 20.74 1-6 0.45 - - 5-3 1.618. PowerplantTwo Engine Oil Supply/Level Check Panels:A. LH Panel ................................................................ 74-1 22.59 - - 5-10 1.79 9-1 2.76B. RH Panel ............................................................... 74-1 22.59 8-2 2.49 - - 9-5 2.82Ground Connection for Engine Air Starting ............... 76-11 23.46 0-11 0.27 - - 5-7 1.70
AIRPORTPLANNING MANUAL
wipapm
1100 REV I
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5.5 Engine Starting Pneumatic Requirements
Figure 5.5.1 - Engine Starting Pneumatic Requirements - Airflow x Temperature
AIRPORTPLANNING MANUAL
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1100REV I
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Figure 5.5.2 - Engine Starting Pneumatic Requirements - Pressure x Temperature
AIRPORTPLANNING MANUAL
wipapm
1100 REV I
5-13
5.6 Ground Pneumatic Power Requirements
Figure 5.6.1 - Ground Pneumatic Power Requirements (APU Mode)
AIRPORTPLANNING MANUAL
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1100REV I
5-14
5.7 Conditioned Air Requirements
Figure 5.7.1 - Pre-conditioned Airflow Requirements
AIRPORTPLANNING MANUAL
wipapm
1100 REV I
5-15
5.8 Ground Towing Requirements
Figure 5.8.1 - Ground Towing Requirements
AIRPORTPLANNING MANUAL
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1100REV I
5-16
6. OPERATING CONDITIONS
This section presents graphics concerning:
– The EMB-145 aircraft Jet Engine Exhaust velocities and temperatures,
– The Airport and Community Noise levels and Hazard Areas.
AIRPORTPLANNING MANUAL
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1100 REV C
6-1
6.1 Engine Exhaust Velocities and Temperatures
Figure 6.1.1 - Jet Wake Velocity Profile (T/O-1 Thrust Mode)
AIRPORTPLANNING MANUAL
wipapm
1100REV C
6-2
Figure 6.1.2 - Jet Wake Temperature Profile (T/O-1 Thrust Mode)
AIRPORTPLANNING MANUAL
wipapm
1100 REV C
6-3
EM145APM060001B.DGN
K J H G F
FGHJK
ABCDE
ABCDE
A 50 B 75 C 100 D 125 E 150 F 175 G 200 H 225 J 250 K 274
LEVEL VELOCITY (ft/s)
20
15
10
0
5
6
5
4
3
2
1
15
10
0
5
4
3
2
1
METERS
METERSFT
FT
0
10 20
2 4 6
30 40
8 10 12
0
10
2 4 6
40
8 10 12 METERS
METERS
FEET
FEET
ELEVATION
PLAN
GROUND PLANE
C AIRPLANEL
ISA+15°C
DISTANCE FROM ENGINE EXHAUST
DISTANCE FROM ENGINE EXHAUST
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE
DIS
TAN
CE
FRO
M A
IRPL
ANE
C L
BREAKAWAY, STATIC, SEA LEVEL
Figure 6.1.3 - Jet Wake Velocity Profile (Breakaway)
AIRPORTPLANNING MANUAL
wipapm
1100REV L
6-4
EM145APM060002B.DGN
FJ
F
AB CD E
GHJ
AB CD E
GH
ISA+15°C
20
15
10
0
5
6
5
4
3
2
1
15
10
0
5
4
3
2
1
METERS
METERSFT
FT
0
10 20
2 4 6
30 40
8 10 12
0
10 20
2 4 6
30 40
8 10 12 METERS
METERS
FEET
FEET
ELEVATION
PLAN
GROUND PLANE
C AIRPLANEL
DISTANCE FROM ENGINE EXHAUST
DISTANCE FROM ENGINE EXHAUST
HEI
GH
T AB
OVE
GR
OU
ND
PLA
NE
DIS
TAN
CE
FRO
M A
IRPL
ANE
C L
TEMPERATURE (°C) (°F) A 16 60 B 21 70 C 27 80 D 32 90 E 38 100 F 43 110 G 49 120 H 54 130 J 60 140
BREAKAWAY, STATIC, SEA LEVEL
Figure 6.1.4 - Jet Wake Temperature Profile (Breakaway)
AIRPORTPLANNING MANUAL
wipapm
1100 REV L
6-5
Figure 6.1.5 - Jet Wake Velocity Profile (Idle Thrust Mode)
AIRPORTPLANNING MANUAL
wipapm
1100REV L
6-6
Figure 6.1.6 - Jet Wake Temperature Profile (Idle Thrust Mode)
AIRPORTPLANNING MANUAL
wipapm
1100 REV L
6-7
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, as such, is vital to its growth. However, the airport must alsobe a good neighbor, and this can be accomplished only 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, aredependent upon numerous factors. They include:
6.2.1 Operational Factors
6.2.1.1 Aircraft Weight
Aircraft weight is dependent on the distance to be traveled, en-route winds, payload, and anticipatedaircraft delay upon reaching the destination.
6.2.1.2 Engine Power Setting
The rates of ascent and descent and the noise levels emitted at the source are influenced by the powersetting used.
6.2.1.3 Airport Altitude
Higher airport altitude will affect the engine performance and thus can influence noise.
6.2.2 Atmospheric Conditions - Sound Propagation
6.2.2.1 Wind
With stronger headwinds, the aircraft can take off and climb more rapidly relative to the ground. Also,winds can influence the distribution of noise in the surrounding communities.
6.2.2.2 Temperature and Relative Humidity
The absorption of noise in the atmosphere along the transmission path between the aircraft and theground observer varies with both temperature and relative humidity.
6.2.3 Surface Condition - Shielding, Extra Ground Attenuation (EGA)
Terrain - If the ground slopes down after takeoff or up before landing, noise will be reduced since theaircraft will be at a higher altitude above the ground. Additionally, hills, shrubs, trees, and large buildingscan act as sound buffers.All of these factors can alter the shape and size of the contours appreciably. To demonstrate the effectof some of these factors, estimated noise level contours for two different operating conditions are shown
AIRPORTPLANNING MANUAL
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1100REV L
6-8
on figure 6.2.1. These contours reflect a given noise level upon a ground level plane at runway elevation.As indicated from these data, the contour size varies substantially with operating and atmosphericconditions. Most aircraft operations are, of course, conducted at less than the maximum gross weightsbecause the average flight distances are much shorter than the maximum aircraft range capability andthe average load factors are less than 100%. Therefore, in developing cumulative contours for planningpurposes, it is recommended that the airlines serving a particular city be contacted to provide operationalinformation.In addition, there are no universally accepted methods for developing aircraft noise contours for relatingthe acceptability of specific noise zones to specific land uses. It is therefore expected that the noisecontour data for a particular aircraft and the impact assessment methodology change. To ensure thatcurrently available information of this type is used in any planning study, it is recommended that it beobtained directly from the Office of Environmental Quality in the Federal Aviation Administration inWashington, D.C.It should be noted that the contours shown herein are only for illustrating the impact of the operating andatmospheric conditions and do not represent the single-event contour of the family of aircraft describedin this document. It is expected that the cumulative contours be developed as required by the plannersusing the data and methodology applicable to their specific study.
AIRPORTPLANNING MANUAL
wipapm
1100 REV L
6-9
6.3 Hazard Areas
1 WITH THE ENGINE RUNNING, THE ACCESS TO THIS AREAIS PERMITTED JUST WITH THE ENGINE IN IDLE SPEEDOR LESS.
145APM060022C.MCE
1ENGINE INLETINGESTIONDANGER AREA
ENGINEACCESSORIESCAUTION AREA
13,0 m( 42,6 ft )
25,0 m( 82,0 ft )
25,0 m
( 82,0 ft )50,0 m
( 164,0 ft )4.3 m
( 14,1 ft )7,0 m
( 23,0 ft )
3,0 m( 9,8 ft )
3,0 m( 9,8 ft )
AIRCRAFT STATIC − SEA LEVEL I.S.A − NO WIND
ENGINEEXHAUSTDANGER AREAAT IDLE THRUST
ENGINEEXHAUSTDANGER AREAAT MAX. THRUST
6,0 m( 19,7 ft )
2,0 m( 6,6 ft )
APUDANGERAREA
Figure 6.3.1 - Hazard Areas
AIRPORTPLANNING MANUAL
wipapm
1100 REV L
6-11
7. PAVEMENT DATA
7.1 General Information
Pavement or Pavement Structure 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 of
the subgrade soil is not exceeded. The subgrade soil is defined as the material on which the pavement
rests, whether embankment or excavation.
Several methods for design of airport pavements have been developed that differ considerably in their
approach.
Generally speaking, 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 the method, and all methods require a considerable amount of common sense and
judgment on the part of the engineer who applies them.
A brief description of the following pavement charts will be helpful in their use for airport planning. Each
airplane configuration is depicted with a minimum range of five loads imposed on the main landing gear
to aid in the interpolation between the discrete values shown. The tire pressure used for the 145 model
charts will produce the recommended tire deflection with the airplane loaded to its maximum ramp weight
and with center of gravity position. The tire pressure where specifically designated in tables and on charts
are values obtained under loaded conditions as certificated for commercial use.
Subsection 7.2 presents basic data on the landing gear footprint configuration, maximum design taxi
loads, and tire sizes and pressures.
Maximum pavement loads for certain critical conditions at the tire-ground interfaces are shown in
Subsection 7.3.
Pavement requirements for commercial airplanes are customarily derived from the static analysis of
loads imposed on the main landing gear struts. The chart in Subsection 7.4 is provided in order to
determine these loads throughout the stability limits of the airplane at rest on the pavement. These main
landing gear loads are used to enter the pavement design charts which follow, interpolating load values
where necessary.
The flexible pavement design curves (Subsection 7.5) are based on procedures set forth in Instruction
Report No. S-77-1, !Procedures for Development of CBR Design Curves!, dated June 1977, and as
modified according to the methods described in FAAAdvisory Circular 150/5320-6D, !Airport Pavement
Design and Evaluation!, dated July 7, 1995. Instruction Report No. S-77-1 was prepared by the USArmy
Corps of Engineers Waterways Experiment Station, Soils and Pavements Laboratory, Vicksburg,
Mississippi. The line showing 10,000 coverages is used to calculate Aircraft Classification Number
(ACN).
The LCN Method curves for flexible pavements (Subsection 7.6) have been built using procedures and
curves in the International Civil Aviation Organization (ICAO) Aerodrome Design Manual, Part 3 -
Pavements, Document 9157-AN/901, 1983.
The same chart includes the data of equivalent single-wheel load versus pavement thickness.
Rigid pavement design curves (Subsection 7.7) have been prepared with the use of the Westergaard
Equation in general accordance with the procedures outlined in the 1955 edition of !Design of Concrete
Airport Pavement! published by the Portland Cement Association, 33 W. GrandAve., Chicago 10, Illinois,
but modified to the new format described in the 1968 Portland Cement Association publication,
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!Computer Program for Concrete Airport Pavement Design! (Program PDILB) by Robert G. Packard.
The following procedure is used to develop rigid pavement design curves such as that shown in
Subsection 7.7.
1. Once the scale for the pavement thickness to the left and the scale for allowable working stress to
the right have been established, an arbitrary load line is drawn representing the main landing gear
maximum weight to be shown.
2. All values of the subgrade modulus (k-values) are then plotted.
3. Additional load lines for the incremental values of weight on the main landing gear are then
established on the basis of the curve for k = 300, already established.
The LCN conversion curves for rigid pavements (Subsection 7.8) have been built using procedures and
curves in (ICAO) Aerodrome Design Manual, Part 3 - Pavements, Document 9157-AN/901, 1983.
The same chart includes the data of equivalent single-wheel load versus radius of relative stiffness.
Radius of relative stiffness values is obtained from Subsections 7.8.1 and 7.8.2.
The ACN/PCN system as referenced in Amendment 35 to ICAO Annex 14, !Aerodromes!, 7th Edition,
June 1976, provides a standardized international airplane/pavement rating system replacing the various
S, T, TT, LCN, AUW, ISWL, etc., rating systems used throughout the world. ACN is the Aircraft
Classification Number and PCN is the corresponding Pavement Classification Number. An aircraft having
an ACN equal to or less than the PCN can operate without restriction on the pavement.
Numerically, the ACN is two times the derived single wheel load expressed in thousands of kilograms
where the derived single-wheel load is defined as the load on a single tire inflated to 1.25 Mpa (181 psi)
that would have the same pavement requirements as the aircraft. Computationally, the ACN/PCN system
uses PCA program PDILB for rigid pavements and S-77-1 for flexible pavements to calculate ACN
values. The method of pavement evaluation is left up to the airport with the results of their evaluation
presented as follows:
Table 7.1.1 - Pavement Evaluation
PAVEMENT TYPE SUBGRADE CATEGORY TIRE PRESSURE CATEGORY METHOD
R - Rigid A - High W - No Limit T - Technical
S - Flexible B - Medium X - to 1.5 Mpa (217 psi) U - Using acft
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 = Pavement Classification Number
R = Pavement Type: Rigid
B = Subgrade Category: Medium
X = Tire Pressure Category: Medium (limited to 1.5 Mpa)
T = Evaluation Method: Technical
AIRPORTPLANNING MANUAL
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7-2
Subsection 7.9.1 shows the aircraft ACN values for flexible pavements. The four subgrade categories
are:
A. High Strength - CBR 15
B. Medium Strength - CBR 10
C. Low Strength - CBR 6
D. Ultra Low Strength - CBR 3
Subsection 7.9.2 shows the aircraft ACN values for rigid pavements. The four subgrade categories are:
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)
AIRPORTPLANNING MANUAL
wipapm1100 REV I
7-3
7.2 Footprint
13.38 in0.34 m
47 ft 5 in14.44 m
13 ft 5 in4.10 m
18.11 in0.46 m
ER EU EP
MAXIMUM DESIGN TAXI WEIGHTlb
kg
45635 44290 46495 46495
20700 20090 21090 21090
PERCENT OF WEIGHT ON MAIN GEAR
19.5 x 6.75!8
NOSE TIRE PRESSUREpsi
kg/cm2
NOSE TIRE SIZE
82!0/+4
5.77!0/+0.28
MAIN GEAR TIRE SIZE 30 x 9.5!14
psi
kg/cm2
MAIN GEAR TIRE PRESSURE145!0/+5
10.19!0/+0.35
145!0/+5
10.19!0/+0.35
148!0/+5
10.40!0/+0.35
SEE SUBSECTION 7.4
48722
22100
84!2/+2
5.90!0/+0.28
H30 x 9.5!16
+!
+!
EMB!145 MODELS
LR / LU
145APM070044.MCE E
+!
+!
53352
24200
XR
11.25 0.28
160 4 175 4
12.30 0.28
MP / MK
+!150 3
+!10.55 0.21
Figure 7.2.1 - Footprint
AIRPORTPLANNING MANUAL
wipapm1100REV I
7-4
7.3 Maximum Pavement Loads
NG
MG
H=MAXIMUM HORIZONTAL GROUND LOAD FROM BRAKING
NOTE: ALL LOADS CALCULATED USING AIRPLANE MAXIMUM DESIGN TAXI WEIGHT
VNG
VMG
MODEL
MAXIMUMDESIGN
TAXIWEIGHT
STATIC AT MOSTFORWARD C.G.
MAXIMUM LOADOCCURINGAT STATICAFT C.G.
NGV
MGV (PER STRUT) (PER STRUT)H
lb lb kg lb kg lb kg lb kg lb kg
ATINSTANTANEOUSBRAKING (COEFF.OF FRICTION 0.8)
EMB-145 ER
EMB-145 EU
H
kg
44295 20090 20897 17722
45640 20700 21532 182624972 2255 6738 3056 9766 6381 2894 8283
4879 2213 6595 2991 9478 6193 2809 8038
EMB-145 EP
48725 22100 24255 19500
46499 21090 21938 186065027 2280 6824 3095 9950 6502 2949 8439
5170 2345 7055 3200 6835 310011000 8845EMB-145 LR
EMB-145 MR
EMB-145 LU
EMB-145 MP
EMB-145 MK
STATIC+BRAKING10 ft/sec
DECELERATION3,048m/sec
2
2
AT STEADYBRAKING10 ft/sec
DECELERATION3,048m/sec 2
2
44295 20090 4879 2213 20897 177226595 2991 9478 6193 2809 8038
46499 21090 21938 186065027 2280 6824 3095 9950 6502 2949 8439
48725 22100 24255 195005170 2345 7055 3200 6835 310011000 8845
48725 22100 24255 195005170 2345 7055 3200 6835 310011000 8845
145APM070045.MCE D
EMB-145 XR 53352 24200 5453 2473 26217 189567464 3385 7801 3538 859711890
LEGEND: V =MAXIMUM VERTICAL NOSE GEAR GROUND LOAD AT MOST FORWARD C.G.
V =MAXIMUM VERTICAL MAIN GEAR GROUND LOAD AT MOST FORWARD C.G.
Figure 7.3.1 - Maximum Pavement Loads
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-5
7.4 Landing Gear Loading on Pavement
Figure 7.4.1 - Landing Gear Loading on PavementSheet 1
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7-6
Weight on Main Gear (%)
24000
23000
22000
21000
12
87 88 89
14000
13000
12000
11000
10000
20000
19000
18000
17000
16000
15000
22000
43
% MAC
EMB-145XR
145APM070814.MCE
91 92 93 94 95
14000
12000
20000
18000
16000
90
WE
IGH
T O
N M
AIN
LA
ND
ING
GE
AR
- l
b
WE
IGH
T O
N M
AIN
LA
ND
ING
GE
AR
- k
g
AIR
PL
AN
E G
RO
SS
WE
IGH
T -
kg
AIR
PL
AN
E G
RO
SS
WE
IGH
T -
lb
24200
24000
23000
22000
21000
14000
13000
12000
11000
10000
20000
19000
18000
17000
16000
15000
Figure 7.4.1 - Landing Gear Loading on PavementSheet 4
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-9
7.5 Flexible Pavement Requirements - US Army Corps of Engineers Design Method
Figure 7.5.1 - Flexible Pavement Requirements - US Army Corps of Engineers DesignMethodSheet 1
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-10
Figure 7.5.1 - Flexible Pavement Requirements - US Army Corps of Engineers DesignMethodSheet 2
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-11
Figure 7.5.1 - Flexible Pavement Requirements - US Army Corps of Engineers DesignMethodSheet 3
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-12
Figure 7.5.1 - Flexible Pavement Requirements - US Army Corps of Engineers DesignMethodSheet 4
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-13
Figure 7.5.1 - Flexible Pavement Requirements - US Army Corps of Engineers DesignMethodSheet 5
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-14
145APM070815.MCE
10000 COVERAGES(USED FOR ACNCALCULATIONS)
ANNUALDEPARTURES
1200
3000
6000
15000
25000
MAXIMUM POSSIBLEMAIN GEAR LOAD AT
MAXIMUM DESIGNTAXI WEIGHT AND AFT CG.
SUBGRADE STRENGHT - CBR
NOTES: TIRES H30x9.5x16 16PR - TIRES PRESSURE AT 12.30kg/cm (175psi)2
13035 28737
16152 35609
18096 39894
22619 49866
FLEXIBLE PAVEMENT THICKNESS (in)
FLEXIBLE PAVEMENT THICKNESS (cm)
3 4 5 6 7 8 9 10 20 30
3 4 5 6 7 8 9 10 20 30
10 20 4030 50 6098 70 80
3 4 5 6 7 8 9 10 20 30
3 4 5 6 7 8 9 10 20 30
10 20 4030 50 6098 70 80
11774 25957
EMB-145 XR
WEIGHT ON MAINLANDING GEAR
(kg) (lb)
Figure 7.5.1 - Flexible Pavement Requirements - US Army Corps of Engineers DesignMethodSheet 6
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-15
7.6 Flexible Pavement Requirements - LCN Method
Figure 7.6.1 - Flexible Pavement Requirements, LCN MethodSheet 1
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-16
Figure 7.6.1 - Flexible Pavement Requirements, LCN MethodSheet 2
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-17
Figure 7.6.1 - Flexible Pavement Requirements, LCN MethodSheet 3
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-18
Figure 7.6.1 - Flexible Pavement Requirements, LCN MethodSheet 4
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-19
Figure 7.6.1 - Flexible Pavement Requirements, LCN MethodSheet 5
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-20
145APM070816.MCE
NOTE: EQUIVALENT SINGLE WHEEL LOADSARE DERIVED BY METHODS SHOWNIN I C A O AERODROME MANUAL.PART 2, PAR. 4.1.3
TIRES H30x9.5-16 16PR AT 12.30 kgf/cm (175psi)2
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L L
OA
D-lb
EQ
UIV
ALE
NT
SIN
GLE
WH
EE
L L
OA
D-k
g30000
20000
10000
9000
8000
7000
6000
5000
4000
6000
8000
10000
12000
4 5 6 7 8 9 10 20 30 40 50 60 70 4 5 6 7 8 9 10 20 30 40 50 60 70
LOAD CLASSIFICATION NUMBER-LCN
2 3 4 5 6 7 8 9 10 20 30
FLEXIBLE PAVEMENT THICKNESS- h (cm)
FLEXIBLE PAVEMENT THICKNESS- h (in)
EMB-145 XR
WEIGHT ON MAINLANDING GEAR
kg ( lb )
22619 (49866)
18096 (39844)
16152 (35609)
13035 (28737)
11771 (25957)
Figure 7.6.1 - Flexible Pavement Requirements, LCN MethodSheet 6
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-21
7.7 Rigid Pavement Requirements - Portland Cement Association Design Method
Figure 7.7.1 - Rigid Pavement Requirements - Portland Cement Association Design MethodSheet 1
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-22
Figure 7.7.1 - Rigid Pavement Requirements - Portland Cement Association Design MethodSheet 2
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-23
Figure 7.7.1 - Rigid Pavement Requirements - Portland Cement Association Design MethodSheet 3
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-24
Figure 7.7.1 - Rigid Pavement Requirements - Portland Cement Association Design MethodSheet 4
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-25
Figure 7.7.1 - Rigid Pavement Requirements - Portland Cement Association Design MethodSheet 5
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-26
145APM070817.MCE
0
5
10
15
20
25
30
35
40
45
50
0
2
4
6
8
10
12
14
16
18
20
0
5
10
15
20
25
30
35
40
50
45
700
0
650
600
550
500
450
400
350
300
250
200
150
100
50
THE VALUES OBTAINED BY USING THEMAXIMUM LOAD REFERENCE LINE ANDANY VALUE OF "K" ARE EXACT. FORLOADS LESS THAN MAXIMUM, THE CURVESARE EXACT FOR K=300 BUT DEVIATESLIGHTLY FOR OTHER VALUES OF "K".
NOTE:
NOTES: 30 x 9.5-16 16PR TIRES
% WEIGHT OR MAIN GEARS 93.47%TIRE PRESSURE 12.30 kgf/cm2 (175 psi) (LOADED)
k= 75 lb/in3
PA
VE
ME
NT
TH
ICK
NE
SS
- in
PA
VE
ME
NT
TH
ICK
NE
SS
- c
m
AL
LO
WA
BL
E W
OR
KIN
G S
TR
ES
S -
kg
f/cm
2
AL
LO
WA
BL
E W
OR
KIN
G S
TR
ES
S -
psi
RIGID PAVEMENT REQUIREMENTS - MODEL EMB-145 XR
REFERENCE: PORTLAND CEMENT ASSOCIATION METHOD.
k= 150 lb/in3
k= 300 lb/in3
k= 550 lb/in3
WEIG
HT
ON M
AIN
LANDIN
G G
EAR -
kg (l
b)
(SEE S
ECTI
ON 7
-4)
2261
9 (4
9868
)
1809
6 (3
9897
)
1615
2 (3
5610
)
13035 (28738)
11774 (25957)
MAXIM
UM
PO
SSIB
LE M
AIN
-GEAR
LOAD A
T M
AXIM
UM
DESIG
N
TAXI W
EIG
HT
AND A
FT C
.G.
Figure 7.7.1 - Rigid Pavement Requirements - Portland Cement Association Design MethodSheet 6
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-27
7.8 Rigid Pavement Requirements - LCN Method
To determine the airplane weight that can be accommodated on a particular rigid airport pavement, both
the LCN of the pavement and the radius of relative stiffness must be known.
7.8.1 Radius of Relative Stiffness
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-28
7.8.2 Radius of Relative Stiffness (other values)
The table of section 7.8.1 presents the (RRS) Radius of Relative Stiffness 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 of section 7.8.2 are
included.
For example, to find an RRS value based on an E of 3,000,000 psi, the !E! factor of 0.931 is multiplied
by the RRS value found in figure 7.8.1. The effect of the variations of µ on the RRS value is treated in
a similar manner.
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-30
Figure 7.8.2 - Radius of Relative Stiffness (other values)
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-31
7.8.3 Rigid Pavement Requirements - LCN Method
Figure 7.8.3 - Rigid Pavement Requirements - LCN MethodSheet 1
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-32
Figure 7.8.3 - Rigid Pavement Requirements - LCN MethodSheet 2
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-33
Figure 7.8.3 - Rigid Pavement Requirements - LCN MethodSheet 3
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-34
Figure 7.8.3 - Rigid Pavement Requirements - LCN MethodSheet 4
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-35
Figure 7.8.3 - Rigid Pavement Requirements - LCN MethodSheet 5
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-36
145APM070818.MCE
NOTE:
EQ
UIV
AL
EN
T S
ING
LE
WH
EE
L L
OA
D-lb
EQ
UIV
AL
EN
T S
ING
LE
WH
EE
L L
OA
D-k
g
LOAD CLASSIFICATION NUMBER-LCN
5000
6000
7000
8000
9000
10000
20000
30000
100908070605040 200 300 400 4 5 6 7 8 9 10 20 30 40
4000
6000
8000
10000
12000
WEIG
HT ON M
AIN
LANDING G
EAR
kg (lb) 22619 (49868)
RADIUS OF RELATIVE STIFFNESS - (cm)
RADIUS OF RELATIVE STIFFNESS - (in)
20 30 40 50 60 70 80 90100
EQUIVALENT SINGLE WHEEL LOADSARE DERIVED BY METHODS SHOWNIN ICAO AERODROME MANUAL.PART 2, PAR. 4.1.3
18096 (39897)
16152 (35610)
13035 (28738)
11774 (25957)
TIRES H 30x9.5-16 16PR AT 12.30 kgf/cm2 (175psi)
EMB-145 XR
Figure 7.8.3 - Rigid Pavement Requirements - LCN MethodSheet 6
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-37
7.9 ACN/PCN Reporting System - Flexible and Rigid Pavements
To determine the ACN of an aircraft on flexible or rigid pavement, both the aircraft gross weight and the
subgrade strength must be known. As an example, for an aircraft gross weight of 45,635 lb (EMB-145
ER) and High subgrade strength, the ACN for rigid pavement is 12.2. For the same gross weight and Low
subgrade strength, the ACN for rigid pavement is 13.6.
NOTE: An aircraft with an ACN equal to or less than the reported PCN can operate on the pavement
subject to any limitations on the tire pressure.
7.9.1 Aircraft Classification Number Flexible Pavement
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-38
Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 1
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-39
Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 2
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-40
Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 3
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-41
Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 4
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-42
Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 5
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-43
Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 6
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-44
Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 7
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-45
7.9.2 Aircraft Classification Number Rigid Pavement
Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 1
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-46
Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 2
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-47
Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 3
AIRPORTPLANNING MANUAL
wipapm1100REV G
7-48
Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 4
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-49
25000 30000 35000 40000 45000 50000
AIRCRAFT GROSS WEIGHT!lb
12000 2200013000 14000 15000 16000 17000 18000 19000 20000 2100011000 23000
AIRCRAFT GROSS WEIGHT!kg
4.0
6.0
8.0
10.0
12.0
14.0
16.0
AIR
CR
AF
T C
LA
SS
IFIC
AT
ION
NU
MB
ER!
AC
N
44291
MA
XIM
UM
RA
MP
WE
IGH
T
RIGID PAVEMENT SUBGRADES ! MODEL EMB!145 MK
NOTES:
% WEIGHT ON MAIN GEARS 93.8%
30 x 9.5!14!16PR TIRESTIRE PRESSURE 10.34kgf/cm (150 psi) (LOADED)
145APM070782.MCE A
3
3
ULTRA LOW
! k=
20 MN/m
(75 lb
/in )
3
3
LOW !
k=40 M
N/m (
150 lb/in
)
MEDIUM !
k=80 M
N/m (
300 lb/in
)
3
3
3
3
HIGH !
k=150 MN/m
(550 lb
/in )
Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 5
AIRPORTPLANNING MANUAL
wipapm1100REV H
7-50
Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 6
AIRPORTPLANNING MANUAL
wipapm1100 REV G
7-51
25000 30000 35000 40000 45000 50000
AIRCRAFT GROSS WEIGHT!lb
AIRCRAFT GROSS WEIGHT!kg
44290
12000 2200014000 16000 18000 20000 24000
55000
5.0
7.0
9.0
11.0
13.0
15.0
17.0
AIR
CR
AF
T C
LA
SS
IFIC
AT
ION
NU
MB
ER!
AC
N
NOTES:
% WEIGHT ON MAIN GEARS 93.47
MA
XIM
UM
RA
MP
WE
IGH
T
24200
SUBG
RAD
E STR
ENG
TH
TIRE PRESSURE 12,30 Kgf/cm" (175 psi)H30 x 9.5!16 16PR TIRES
FLEXIBLE PAVEMENT SUBGRADE STRENGTH MODEL EMB!145 XR
145APM070819.MCE A
3
3
ULTR
A LO
W !
k=20
MN/m
(75
lb/in
)
3
3
LOW
! k
=40 MN/m
(150 lb
/in )
3
3
MEDIU
M !
k=80 M
N/m (
300 lb/in
)
3
3
HIGH !
k=150 M
N/m (
550 lb/in
)
Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 7
AIRPORTPLANNING MANUAL
wipapm1100REV H
7-52
8. POSSIBLE EMB-145 DERIVATIVE AIRPLANES
No derivative versions of the EMB-145 are current planned.
AIRPORTPLANNING MANUAL
REV C8-1
9. EMB-145 SCALE DRAWINGS
This section provides EMB-145 plan views to the following scales:
• English1 inch = 32 feet1 inch = 50 feet1 inch = 100 feet
• Metric1:5001:1000
AIRPORTPLANNING MANUAL
wipapm
1100 REV C
9-1
9.1 EMB-145 Scale: 1 Inch Equals 32 Feet
Figure 9.1.1 - EMB-145 Scale: 1 Inch Equals 32 Feet
AIRPORTPLANNING MANUAL
REV C9-2
9.2 EMB-145 Scale: 1 Inch Equals 50 Feet
Figure 9.2.1 - EMB-145 Scale: 1 Inch Equals 50 Feet
AIRPORTPLANNING MANUAL
REV C9-3
9.3 EMB-145 Scale: 1 Inch Equals 100 Feet
Figure 9.3.1 - EMB-145 Scale: 1 Inch Equals 100 Feet
AIRPORTPLANNING MANUAL
REV C9-4