Embraer EMB-145 XR _ Airport Planning Manual

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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AIRPORTPLANNING MANUAL

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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


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


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

Section Page


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


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



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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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Figure 2.7.1 - EMB-145 Door ClearancesSheet 2


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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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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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FAR

TAK

EOFF

RU

NW

AY L

ENG

TH −

m



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



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145APM030375.MCE B

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)


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 − (lb)

FAR

TAK

EOFF

FIE

LD L

ENG

TH −

(ft)

FAR

TAK

EOFF

FIE

LD L

ENG

TH −

m



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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


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)


OPERATIONALTAKEOFF WEIGHT − (lb)

AIRPORTELEVATION− m (ft)



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FAR

TAK

EOFF

RU

NW

AY L

ENG

TH −

m


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


wipapm

1100 REV J

3-15


FAR

TAK

EOFF

RU

NW

AY L

ENG

TH −

m




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



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


4000

9000

5000

6000

7000

8000

10000



FLAPS 9/22 ET/O THRUST MODE, NO ENGINE BLEED FORAIR CONDITIONING

AE 3007 A1E ENGINES



FAR

TAK

EOFF

FIE

LD L

ENG

TH −

(ft)



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


4800028000 32000 36000 40000 44000 52000



4000

9000

5000

6000

7000

8000

10000

FLAPS 9/18/22 T/O MODE, NO ENGINE BLEED FORAIR CONDITIONING

AE 3007 A1P ENGINES



FAR

TAK

EOFF

FIE

LD L

ENG

TH −

(ft)



wipapm

1100REV J

3-18

3.4 FAR Landing Runway Length Requirements

Figure 3.4.1 - FAR Landing Runway Length Requirements - Flaps 45oSheet 1


wipapm

1100 REV J

3-19



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)



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)



wipapm

1100REV J

3-22

4. GROUND MANEUVERING


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.


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˚


Figure 4.2.1 - Turning Radii - No Slip AngleSheet 1


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


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.


Figure 4.3.1 - Minimum Turning Radii - PRE-MOD. S.B. 145-32-0002


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


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


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


wipapm

1100 REV H

4-7

4.5 Runway and Taxiway Turn Paths

Figure 4.5.1 - More than 90o Turn - Runway to Taxiway


wipapm

1100REV G

4-8

Figure 4.5.2 - 90o Turn - Runway to Taxiway


wipapm

1100 REV G

4-9

Figure 4.5.3 - 90o Turn - Taxiway to Taxiway


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1100REV G

4-10

4.6 Runway Holding Bay

Figure 4.6.1 - Runway Holding Bay


wipapm

1100 REV G

4-11

5. TERMINAL SERVICING


During turnaround at the air terminal, certain services must be performed on aircraft, usually within agiven time to meet flight schedules. This section shows service vehicle arrangements, schedules,locations of servicing points, and typical servicing requirements. The data presented herein reflect idealconditions for a single 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.


wipapm

1100 REV C

5-1

Figure 5.1.1 - EMB-145 Airplane Servicing ArrangementSheet 1


wipapm

1100REV I

5-2

Figure 5.1.1 - EMB-145 Airplane Servicing ArrangementSheet 2


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


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


wipapm

1100 REV I

5-5

5.4 Ground Servicing Connections EMB-145

Figure 5.4.1 - Ground Servicing Connections EMB-145 ER / MP


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


wipapm

1100 REV I

5-7

Figure 5.4.2 - Ground Servicing Connections EMB-145 LR


wipapm

1100REV I

5-8

Table 5.4.2 - Ground Servicing Connections EMB-145 LR



HEIGHTABOVEGROUND


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


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


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1100REV I

5-10

Table 5.4.3 - Ground Servicing Connections EMB-145 XR



HEIGHTABOVEGROUND


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


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1100 REV I

5-11

5.5 Engine Starting Pneumatic Requirements

Figure 5.5.1 - Engine Starting Pneumatic Requirements - Airflow x Temperature


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1100REV I

5-12

Figure 5.5.2 - Engine Starting Pneumatic Requirements - Pressure x Temperature


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1100 REV I

5-13

5.6 Ground Pneumatic Power Requirements

Figure 5.6.1 - Ground Pneumatic Power Requirements (APU Mode)


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1100REV I

5-14

5.7 Conditioned Air Requirements

Figure 5.7.1 - Pre-conditioned Airflow Requirements


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1100 REV I

5-15

5.8 Ground Towing Requirements

Figure 5.8.1 - Ground Towing Requirements


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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.


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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)


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1100REV C

6-2

Figure 6.1.2 - Jet Wake Temperature Profile (T/O-1 Thrust Mode)


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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


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)


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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



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)


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1100 REV L

6-5

Figure 6.1.5 - Jet Wake Velocity Profile (Idle Thrust Mode)


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1100REV L

6-6

Figure 6.1.6 - Jet Wake Temperature Profile (Idle Thrust Mode)


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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


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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.


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6-9

Figure 6.2.1 - Airport and Community Noise Levels


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6-10

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


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6-11

7. PAVEMENT DATA


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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7-1

!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


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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)


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


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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


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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



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7-7



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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



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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


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7-11



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7-13



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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)



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7-15

7.6 Flexible Pavement Requirements - LCN Method

Figure 7.6.1 - Flexible Pavement Requirements, LCN MethodSheet 1


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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)



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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


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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.



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


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7-28

Figure 7.8.1 - Radius of Relative Stiffness


wipapm1100 REV G

7-29

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.


wipapm1100REV G

7-30

Figure 7.8.2 - Radius of Relative Stiffness (other values)


wipapm1100 REV G

7-31

7.8.3 Rigid Pavement Requirements - LCN Method

Figure 7.8.3 - Rigid Pavement Requirements - LCN MethodSheet 1


wipapm1100REV G

7-32



wipapm1100 REV G

7-33



wipapm1100REV G

7-34



wipapm1100 REV G

7-35



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



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


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7-38

Figure 7.9.1 - Aircraft Classification Number Flexible PavementSheet 1


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7-39



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7-40



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7-41



wipapm1100REV G

7-42



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7-43



wipapm1100REV G

7-44



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7-45

7.9.2 Aircraft Classification Number Rigid Pavement

Figure 7.9.2 - Aircraft Classification Number Rigid PavementSheet 1


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7-46



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7-47



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7-48



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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 )



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7-50



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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

)



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7-52

8. POSSIBLE EMB-145 DERIVATIVE AIRPLANES

No derivative versions of the EMB-145 are current planned.


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


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


REV C9-2




REV C9-3




REV C9-4

9.4 EMB-145 Scale: 1 to 500

Figure 9.4.1 - EMB-145 Scale: 1 to 500


REV C9-5

9.5 EMB-145 Scale: 1 to 1000

Figure 9.5.1 - EMB-145 Scale: 1 to 1000


REV C9-6

Documents

Embraer EMB-145 XR _ Airport Planning Manual