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Mob Crj2 W and B CRJ 200

WEIGHT AND BALANCE CRJ 200

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0% found this document useful (0 votes)

435 views170 pages

Mob Crj2 W and B CRJ 200

WEIGHT AND BALANCE CRJ 200

Uploaded by

Andres Carpena

We take content rights seriously. If you suspect this is your content, claim it here.

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C

WEIGHT AND BALANCE MANUAL

REVISION 11 − TRANSMITTAL LETTER

This package contains Revision 11 to the Canadair Regional Jet, Model CL−600−2B19, Weight
and Balance Manual for Air Nostrum, CSP A−041−023 dated Mar 10/06.
Please note that Revision 11, dated Mar 10/06, is not an incremental revision, but a complete
re−issue.
To bring your manual up to date, remove and discard the contents, except for the tab dividers,
Record of Revisions, Record of Temporary Revisions and valid Temporary Revisions (TRs).
Record the insertion of this revision on the Record of Revisions.
This package includes a List of Effective Temporary Revisions that identifies valid TRs.
TRs dated Mar 11/06 or later should be retained in your manual. Please update the Record of
Temporary Revisions accordingly.
NOTE: Please retain this Transmittal Letter for record purposes and insert it in the front of the
manual.

AIR NOSTRUM.
EFFECTIVITY: ALL Page 1
Transmittal Letter Mar 10/06
Model CL−600−2B19
Series 100/200/440

WEIGHT AND BALANCE MANUAL

CSP A−041-023

AIR NOSTRUM

BOMBARDIER INC.
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT
CUSTOMER SUPPORT

123 GARRATT BLVD., DOWNSVIEW, ONTARIO

CANADA M3K 1Y5

Copyright© 1994 by Bombardier Inc.

All rights reserved. No part of this work may be reproduced or copied

in any form or by any means without written permission
of Bombardier Inc.

The Bombardier logo and Canadair are registered

trademarks of Bombardier Inc.

Initial Issue: Sep 30/98

Revision 11: Mar 10/06
"The information, technical data and the designs disclosed herein are the
exclusive property of Bombardier Inc. or contain proprietary rights of others and
are not to be used or disclosed to others without the written consent of
Bombardier Inc. The recipient of this document, by its retention and use, agrees
to hold in confidence the technical data and designs contained herein. The
foregoing shall not apply to persons having proprietary rights to such information,
technical data or such designs to the extent that such rights exist."
Technical Publications
Manual Change Request
Name of Airline:
TO: MCR FOCAL, TECHNICAL PUBLICATIONS
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT
Bombardier Reference #:
DOWNSVIEW, ONTARIO, CANADA, M3K 1Y5
MAIL STOP: N42−25 FAX: (416) 375−4538
E−MAIL ADDRESS: mcrfocal@aero.bombardier.com Date:

All fields marked with an asterisk * are required

Contact Information
*Name: *Corporation Name: *Dept Name/Code:

Address: City: State/Province:

Zip / Postal Code: Country: *Telephone:

Mobile/Cell Phone: Fax Number: *E−Mail:

I would like to receive notification of actions on this request.

NOTE: Responses will only be sent by electronic mail.
Publication Information
*Aircraft Type: *Aircraft Model: *PSM/CSP:

Publication Name/Revision: Media Type: *Chapter/Section/Subject/Task (or) Page Block/Page Number:

Paper DVD
CD−ROM RACS
Originator’s Reference Number: Impact on other programs:

*Description of Change Request:

Reason for change:

Reference data provided: Yes No Description:

Please fold and mail to address on back of this page.

NOTE: Electronic submissions of MCRs are available on www.racs.bombardier.com Oct 15/2005

Bombardier Inc.
Bombardier Aerospace Regional Aircraft
Customer Support
Mailbox Stop N42−25
123 Garratt Blvd., Downsview
Ontario, Canada
M3K 1Y5

Attention: MCR Focal, Technical Publications

Technical Publications
Manual Change Request
Name of Airline:
TO: MCR FOCAL, TECHNICAL PUBLICATIONS
BOMBARDIER AEROSPACE REGIONAL AIRCRAFT
Bombardier Reference #:
DOWNSVIEW, ONTARIO, CANADA, M3K 1Y5
MAIL STOP: N42−25 FAX: (416) 375−4538
E−MAIL ADDRESS: mcrfocal@aero.bombardier.com Date:

All fields marked with an asterisk * are required

Contact Information
*Name: *Corporation Name: *Dept Name/Code:

Address: City: State/Province:

Zip / Postal Code: Country: *Telephone:

Mobile/Cell Phone: Fax Number: *E−Mail:

I would like to receive notification of actions on this request.

NOTE: Responses will only be sent by electronic mail.
Publication Information
*Aircraft Type: *Aircraft Model: *PSM/CSP:

Publication Name/Revision: Media Type: *Chapter/Section/Subject/Task (or) Page Block/Page Number:

Paper DVD
CD−ROM RACS
Originator’s Reference Number: Impact on other programs:

*Description of Change Request:

Reason for change:

Reference data provided: Yes No Description:

Please fold and mail to address on back of this page.

NOTE: Electronic submissions of MCRs are available on www.racs.bombardier.com Oct 15/2005

Bombardier Inc.
Bombardier Aerospace Regional Aircraft
Customer Support
Mailbox Stop N42−25
123 Garratt Blvd., Downsview
Ontario, Canada
M3K 1Y5

Attention: MCR Focal, Technical Publications

All fields marked with an asterisk * are required

Contact Information
*Name: *Corporation Name: *Dept Name/Code:

Address: City: State/Province:

Zip / Postal Code: Country: *Telephone:

Mobile/Cell Phone: Fax Number: *E−Mail:

I would like to receive notification of actions on this request.

NOTE: Responses will only be sent by electronic mail.
Publication Information
*Aircraft Type: *Aircraft Model: *PSM/CSP:

Publication Name/Revision: Media Type: *Chapter/Section/Subject/Task (or) Page Block/Page Number:

Paper DVD
CD−ROM RACS
Originator’s Reference Number: Impact on other programs:

*Description of Change Request:

Reason for change:

Reference data provided: Yes No Description:

Please fold and mail to address on back of this page.

NOTE: Electronic submissions of MCRs are available on www.racs.bombardier.com Oct 15/2005

Bombardier Inc.
Bombardier Aerospace Regional Aircraft
Customer Support
Mailbox Stop N42−25
123 Garratt Blvd., Downsview
Ontario, Canada
M3K 1Y5

Attention: MCR Focal, Technical Publications

WEIGHT AND BALANCE MANUAL

RECORD OF REVISIONS

Record the date you insert each revision in your manual.

Rev. Issue Date Rev. Issue Date Rev. Issue Date

By By By
No. Date Inserted No. Date Inserted No. Date Inserted
10 Apr 28/99 Apr 28/99 BCSG
11 Mar 10/06 Mar 10/06 BCSG

BCSG: Bombardier Customer Service Group Page 1

Mar 10/06
WEIGHT AND BALANCE MANUAL

SERVICE BULLETIN LIST

TBD

Mar 10/06
C
WEIGHT AND BALANCE MANUAL

INTRODUCTION

LIST OF EFFECTIVE PAGES

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
Intro − LEP 1* Mar 10/06
2* Mar 10/06
Intro − Contents 1* Mar 10/06
2* Mar 10/06
Introduction 1* Mar 10/06
2* Mar 10/06
3* Mar 10/06
4* Mar 10/06
5* Mar 10/06
6* Mar 10/06
7* Mar 10/06
8* Mar 10/06

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INTRODUCTION

TABLE OF CONTENTS

Chapter
Section
Subject Subject Page Effectivity

INTRODUCTION
General 1 −ALL
Correspondence
Translation of Manual
Aircraft Changes
Units for the WBM
Personnel Qualifications 2
Front Matter
Manual Front Matter
Chapter Front Matter
Organization of Manual 3
General
Group
Chapter/System 4
Section/Subsystem
Subject/Unit
Standard Numbering System 5
Illustrations
Measurements
Linear Conversions
Temperature Conversions 6
Abbreviations
Definition of Warning, Caution and Note 7
Revision

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INTRODUCTION

1. General
The Weight and Balance Manual (WBM), for the Canadair Regional Jet CL−600−2B19, agrees
with the Air Transport Association of America Specification No. 100 (ATA 100), Revision 26,
dated Apr 1/87. The WBM also includes items from subsequent ATA 100 revisions.
This manual contains information to help control how the loads are applied to the aircraft and
related operations for the Canadair Regional Jet Series 200ER aircraft.
Only information related to the aircraft during manufacture is included in this manual.
Information related to standard and optional changes and Bombardier Aerospace Regional
Aircraft −approved Service Bulletins will be included, as soon as possible, after the changes
or Service Bulletins have been released.

2. Correspondence
Send all correspondence about this manual to:
Bombardier Inc.
Bombardier Aerospace Regional Aircraft
Customer Support
Mail Stop N42−25
123 Garratt Blvd., Downsview
Ontario, Canada
M3K 1Y5

Attention: Director, Technical Publications

or send the Technical Manual Change Request form contained in this manual.

3. Translation of Manual
If all or part of the Canadair Regional Jet WBM is translated, the official version is the English
language version by Bombardier Aerospace Regional Aircraft.

4. Aircraft Changes
If the customer modifies the aircraft to which this WBM applies, Bombardier Aerospace
Regional Aircraft (BARA) can include the changes in the revisions of the WBM on agreement
between BARA and the customer. The changes must be correctly documented and approved
by BARA.
This does not include JAA, FAA, DOT or other mandatory changes for which the manual will
be revised to include the mandatory changes.

5. Units for the WBM

Bombardier Aerospace Regional Aircraft supplies the WBM in the units which agree with those
appearing on the aircraft to which the WBM is related.
If the units appearing on the aircraft are American they are shown in this manual as Standard.
To change the units from Standard to SI, refer to paragraph 11.

AIR NOSTRUM Page 1

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WEIGHT AND BALANCE MANUAL

If the units appearing on the aircraft are metric they are shown in this manual as SI. To change
the units from SI to Standard or from Standard to SI, refer to paragraph 11.
In this manual, some fuel−related data may also be shown in Imperial units. This is necessary
as the aircraft fuel supply may be available only in these units.

6. Personnel Qualifications
Only fully approved personnel must calculate the weight and balance and a load and trim
sheet as shown in this manual (CSP A−041).

7. Front Matter

A. Manual Front Matter

(1) Title Page

The title page contains the Canadair Regional Jet masthead, the identification and
the initial issue date of the manual.

(2) Record of Revisions

The Record of Revisions is found after the title page. This record must be completed
when a revision to the WBM is received.

(3) Record of Temporary Revisions

The Record of Temporary Revisions follows the Record of Revisions. The Record of
Temporary Revisions must be changed each time a temporary revision is added or
removed from the WBM.

(4) Service Bulletins

A numerical list of Service Bulletins follows the Record of Temporary Revisions.
This list shall be revised at the same time as the manual and shall contain the data
that follows:
− The revision number of the service bulletin(s)
− The date the service bulletin was included in the manual or the words no effect"
to show that no change to the manual is necessary for that service bulletin.

B. Chapter Front Matter

(1) Effective Pages

A list of effective pages is found at the front of each chapter. It identifies each page
by chapter/section/subject and also gives the number and the date of each page.

(2) Table of Contents

A table of contents, for each chapter, follows the effective pages. This table of
contents is identified by the chapter number and the word CONTENTS at the bottom
of the page.

AIR NOSTRUM
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WEIGHT AND BALANCE MANUAL

(3) Aircraft Effectivity

Aircraft serial numbers are used to give the effectivity of subjects and/or details
applicable to different configurations. Data that is applicable to all configurations will
not show effectivity.

8. Organization of Manual

A. General
The WBM is organized on four levels as specified by ATA 100. These levels are usually
referred to as group, chapter, section and subject. Each page contains the
chapter−section− subject number, the page number, the effectivity code of the page and
the revision date of the page.
The groups are divided into chapter/system; the chapter/system is divided into
section/subsystem and the section/subsystem is divided into subject/unit as follows:

Level 1 Group

Level 2 Chapter/System

Level 3 Section/Subsystem

Level 4 Subject/Unit

B. Group
Groups give a broad separation of the contents of the manual. The WBM is organized
into two groups. Each group contains subject matter usually known as chapters and are
divided as follows:

WBM

Group 1 Group 2

Chapter Chapter
1 2

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C. Chapter/System
This level is usually known as the chapter. It has inter-related components arranged to do
a specific function and is further divided into subsystems usually known as sections.
Each chapter is assigned its number and title by ATA 100 and is identified by the first
element in the standard numbering system.

CHAPTER
CHAPTER TITLE
NUMBER
CONTROL 1
AIRCRAFT REPORTS 2

D. Section/Subsystem
This level is usually known as the section. It permits the chapter to be divided into
subsystems and is identified by the second element in the standard numbering system
as follows:

CHAPTER/
CHAPTER/SECTION TITLE SECTION
NUMBER

CONTROL 1

General −00
Fuel −20
Fluids −30
Personnel −40
Ground Operations −80
AIRCRAFT REPORTS 2

E. Subject/Unit
This level is usually known as the subject. It permits the identification of individual
units in a system or section and is identified by the third element in the standard
numbering system.

AIR NOSTRUM
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WEIGHT AND BALANCE MANUAL

9. Standard Numbering System

The manual numbering system is specified by ATA 100. It is a three−element numbering
system that divides the manual material into chapter/section/subject. Each element has two
digits and is given as follows:
Elements Definition of Elements Example
1 2 3
01−00−00 Material applicable to the chapter as a whole
Chapter 01−40−00 Control

01−40−00 Material applicable to the section as a whole

Section 01−40−00 Personnel

01−40−40 Material applicable to a specific subject of the section

Unit 01−40−40 Compartment volumes

10. Illustrations
The standard orientation of illustrations is from the front−left−side, aerial view; but other views
are used for clarity.

11. Measurements
This manual uses different linear and temperature measurements. These measurements are
converted from SI to standard or from standard to SI as necessary.

A. Linear Conversions

(1) SI to Standard (refer to Figure 1)

To convert linear measurements from SI to Standard, use these measurements:

FROM: SI MEASUREMENT TO: STANDARD SYSTEM

1 kg 2.2046 lb
1L 0.2642 U.S. gal
1 mm 0.0394 in.

Linear Conversions − SI to Standard

Figure 1

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(2) Standard to SI (refer to Figure 2)

To convert linear measurements from Standard to SI, use these measurements:

FROM: STANDARD SYSTEM TO: SI MEASUREMENT

1 psi 6.8948 kPa
1 in. 25.4 mm
1 lb 0.4536 kg
1 U.S. gal 3.7854 L
Linear Conversions − Standard to SI
Figure 2

B. Temperature Conversions

(1) SI to Standard (refer to Figure 3)

To convert temperature values from SI to Standard, use these measurements:

STANDARD SYSTEM
Degrees Fahrenheit (°F)
Degrees °F = (°C x 1.8000) + 32
Temperature Conversion − SI to Standard
Figure 3

(2) Standard to SI (refer to Figure 4)

To convert temperature values from Standard to SI, use these measurements:

SI MEASUREMENT
Degrees Fahrenheit (°F)
Degrees °C = (_F−32) x 0.5556
Temperature Conversion − Standard to SI
Figure 4

C. Abbreviations (refer to Figure 5)

SI SYSTEM STANDARD SYSTEM

ABBREVIATION DEFINITION ABBREVIATION DEFINITION
°C Degrees Celsius °F Degrees Fahrenheit
m Meter ft Foot
L Liter U.S. gal U.S. gallon
mm Millimeter in. Inch
kg Kilogram lb Pound
Abbreviations
Figure 5

AIR NOSTRUM
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WEIGHT AND BALANCE MANUAL

12. Definition of Warning, Caution and Note

ATA 100 specifies warnings, cautions and notes as follows:

WARNING:
− Shows the use of materials, limits or procedures that must be done to avoid injury to
persons.

CAUTION:
− Shows procedures that must be done to prevent damage to equipment.
NOTE:
− Shows procedures that make the job easier.

13. Revision
The revision service for the WBM will be provided for one year after the supply of the last
aircraft to which the WBM applies. A revision service of the WBM depends on future
agreements between Bombardier Aerospace Regional Aircraft and the customer.

AIR NOSTRUM Page 7

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RECORD OF TEMPORARY REVISIONS

Record the date you insert each Temporary Revision in your manual.

SECTION AND ISSUE DATE INSERTED DATE REMOVED REVISION

TR NO.
PAGE NO. DATE INSERTED BY REMOVED BY INCORPORATED

AIR NOSTRUM
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WEIGHT AND BALANCE MANUAL

SECTION AND ISSUE DATE INSERTED DATE REMOVED REVISION

TR NO.
PAGE NO. DATE INSERTED BY REMOVED BY INCORPORATED

AIR NOSTRUM
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C
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CHAPTER 1 − CONTROL

LIST OF EFFECTIVE PAGES

Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
01 − LEP 1* Mar 10/06 01−00−70 1* Mar 10/06
2* Mar 10/06 2* Mar 10/06
01 − Contents 1* Mar 10/06 01−00−80 1* Mar 10/06
2* Mar 10/06 2* Mar 10/06
3* Mar 10/06
4* Mar 10/06 01−20−00 1* Mar 10/06
5* Mar 10/06 2* Mar 10/06
6* Mar 10/06 3* Mar 10/06
4* Mar 10/06
01−00−00 1* Mar 10/06
2* Mar 10/06 01−30−00 1* Mar 10/06
2* Mar 10/06
01−00−10 1* Mar 10/06
2* Mar 10/06 01−40−00 1* Mar 10/06
3* Mar 10/06 2* Mar 10/06
4* Mar 10/06 01−40−10 1* Mar 10/06
5* Mar 10/06 2* Mar 10/06
6* Mar 10/06 3* Mar 10/06
01−00−20 1* Mar 10/06 4* Mar 10/06
2* Mar 10/06 01−40−20 1* Mar 10/06
01−00−30 1* Mar 10/06 2* Mar 10/06
2* Mar 10/06 01−40−30 1* Mar 10/06
3* Mar 10/06 2* Mar 10/06
4* Mar 10/06
01−40−40 1* Mar 10/06
01−00−40 1* Mar 10/06 2* Mar 10/06
2* Mar 10/06 3* Mar 10/06
3* Mar 10/06 4* Mar 10/06
4* Mar 10/06 5* Mar 10/06
5* Mar 10/06 6* Mar 10/06
6* Mar 10/06
01−80−00 1* Mar 10/06
01−00−50 1* Mar 10/06 2* Mar 10/06
2* Mar 10/06
01−80−10 1* Mar 10/06
01−00−60 1* Mar 10/06 2* Mar 10/06
2* Mar 10/06 3* Mar 10/06
3* Mar 10/06 4* Mar 10/06
4* Mar 10/06 5* Mar 10/06
5* Mar 10/06 6* Mar 10/06
6* Mar 10/06
7* Mar 10/06 01−80−20 1* Mar 10/06
8* Mar 10/06 2* Mar 10/06
9* Mar 10/06
10* Mar 10/06 01−80−30 1* Mar 10/06
11* Mar 10/06 2* Mar 10/06
12* Mar 10/06

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Chapter Chapter
Section Section
Subject Config Page Date Subject Config Page Date
01−80−40 1* Mar 10/06 18* Mar 10/06
2* Mar 10/06
3* Mar 10/06 01−90−40 1* Mar 10/06
4* Mar 10/06 2* Mar 10/06
5* Mar 10/06 3* Mar 10/06
6* Mar 10/06 4* Mar 10/06
7* Mar 10/06 5* Mar 10/06
8* Mar 10/06 6* Mar 10/06
9* Mar 10/06 7* Mar 10/06
10* Mar 10/06 8* Mar 10/06
11* Mar 10/06 9* Mar 10/06
12* Mar 10/06 10* Mar 10/06
11* Mar 10/06
01−80−50 1* Mar 10/06 12* Mar 10/06
2* Mar 10/06
3* Mar 10/06
4* Mar 10/06
01−80−60 1* Mar 10/06
2* Mar 10/06
01−90−00 1* Mar 10/06
2* Mar 10/06
01−90−10 1* Mar 10/06
2* Mar 10/06
3* Mar 10/06
4* Mar 10/06
5* Mar 10/06
6* Mar 10/06
01−90−20 1* Mar 10/06
2* Mar 10/06
3* Mar 10/06
4* Mar 10/06
5* Mar 10/06
6* Mar 10/06
01−90−30 1* Mar 10/06
2* Mar 10/06
3* Mar 10/06
4* Mar 10/06
5* Mar 10/06
6* Mar 10/06
7* Mar 10/06
8* Mar 10/06
9* Mar 10/06
10* Mar 10/06
11* Mar 10/06
12* Mar 10/06
13* Mar 10/06
14* Mar 10/06
15* Mar 10/06
16* Mar 10/06
17* Mar 10/06

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CHAPTER 1 − CONTROL

TABLE OF CONTENTS

Chapter
Section
Subject Subject Page Effectivity

CONTROL−GENERAL 01−00−00
Description 1 −ALL
Dimensions and Areas
Definition of Terms
Aircraft Stations
Reference Datum Points
Maximum Weight Limits
Maximum Center of Gravity Limits
Balance Change Due to Operation
Takeoff Setting
DIMENSIONS AND AREAS − DESCRIPTION AND
OPERATION 01−00−10
General 1 −ALL
General Aircraft Data 3
DEFINITION OF TERMS − GENERAL 01−00−20
General 1 −ALL
Zero Fuel Weight (ZFW)
Drainable Fuel
Manufacturer’s Weight Empty (MWE)
Maximum Landing Weight (MLW)
Maximum Takeoff Weight (MTOW)
Maximum Ramp Weight (MRW)
Maximum Zero Fuel Weight (MZFW)
Maximum Payload
Minimum Flight Weight 2
Operational Weight Empty (OWE)
Operational Items
Payload (P/L)
Trapped Fuel
Unusable Fuel
Usable Fuel
Useful Load

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Chapter
Section
Subject Subject Page Effectivity

AIRCRAFT STATIONS − DESCRIPTION

AND OPERATION 01−00−30
General 1 −ALL
Abbreviations and Definitions
Fuselage Station (FS)
Wing Station (WS)
Vertical Stabilizer Station (VSS)
Horizontal Stabilizer Station (HSS)
Waterline (WL)
Buttock Line (BL)
Engine Station (ES)
Mass−Account Coding System
REFERENCE DATUM POINTS − GENERAL 01−00−40
Zero Reference Datum 1 −ALL
Weighing Datum
Mean Aerodynamic Chord 3
Nosewheel−Axle Center Line 5
Main−Landing−Gear−Wheel−Axle
Center Line
Forward Jacking Point
Aft Jacking Point
MAXIMUM WEIGHT LIMITS − GENERAL 01−00−50
General 1 −ALL
MAXIMUM CENTER OF GRAVITY
LIMITS − GENERAL 01−00−60
General 1 −ALL
BALANCE CHANGE DUE TO OPERATION
− GENERAL 01−00−70
General 1 −ALL
TAKEOFF SETTING − GENERAL 01−00−80
Stabilizer Setting for Takeoff 1 −ALL
FUEL − GENERAL 01−20−00
General 1 −ALL
Fuel Tank Configuration
Unusable Fuel
Trapped Fuel
Residual Fuel
Usable Fuel 3

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Chapter
Section
Subject Subject Page Effectivity

FLUIDS − GENERAL 01−30−00

General 1 −ALL
PERSONNEL − GENERAL 01−40−00
General 1 −ALL
Passenger and Crew Arrangement
Passenger and Crew Weights and
Center of Gravity
Balance Change Due to Movement
Compartment Volume
PASSENGER AND CREW ARRANGEMENT −
GENERAL 01−40−10
General 1 −ALL
Passenger and Crew Center of Gravity
PASSENGER/CREW WEIGHT AND CENTER
OF GRAVITY − GENERAL 01−40−20
General 1 −ALL
BALANCE CHANGE DUE TO MOVEMENT −
GENERAL 01−40−30
General 1 −ALL
COMPARTMENT VOLUME − GENERAL 01−40−40
General 1 −ALL
Compartment Volumes
Maximum Package Dimensions
Cargo Compartment
GROUND OPERATIONS 01−80−00
General 1 −ALL
Ground Balance Limits
Jacking Locations
Maximum Static Loads
Leveling and Weighing Procedure
Systems Fluids Lateral Center of Gravity
Weight and Balance of Primary Components
GROUND BALANCE LIMITS − GENERAL 01−80−10
General 1 −ALL
Stable Aircraft Inspection
Towing
Nose Landing Gear 4
Ground Limitations

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Chapter
Section
Subject Subject Page Effectivity

JACKING LOCATIONS − GENERAL 01−80−20

General 1 −ALL
MAXIMUM STATIC LOADS − GENERAL 01−80−30
General 1 −ALL
Cargo Compartment Floor Load
LEVELING AND WEIGHING PROCEDURE
− GENERAL 01−80−40
General 1 −ALL
Prepare the Aircraft to be Weighed
Weigh the Aircraft on Platform Scales
SI Example to Calculate the Aircraft CG in
XARM and %MAC 7
Weight the Aircraft on Jacks 9
LATERAL CENTER OF GRAVITY − GENERAL 01−80−50
General 1 −ALL
System Fluids − Lateral Center of Gravity
Main Fuel Tank − Lateral Center of Gravity
WEIGHT AND CENTER OF GRAVITY OF
PRIMARY COMPONENTS − GENERAL 01−80−60
General 1 −ALL
EXAMPLES AND FORMS − GENERAL 01−90−00
General 1 −ALL
Operational Loading Sheet with 37
Passengers
DOI with 29 Passengers
Load and Trim Sheet with 29
Passengers
Operational Loading Sheets
Full Load of Fuel
Full Load of Passengers
WEIGHT BUILDUP (PAYLOAD) − GENERAL 01−90−10
General 1 −ALL
Weight Buildup Sheet
DRY OPERATING INDEX − GENERAL 01−90−20
General 1 −ALL
Example of Calculations
Form to Calculate Your Own Data 4

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WEIGHT AND BALANCE MANUAL

Chapter
Section
Subject Subject Page Effectivity

LOAD AND TRIM SHEET WITH 29

PASSENGERS − GENERAL 01−90−30
General 1 −ALL
Terms and Abbreviations
Procedure 2
Given Data
Procedure
Make an Analysis of the Result 9
WEIGHT AND BALANCE DIAGRAMS
− GENERAL 01−90−40
General 1 −ALL
Weight and Balance Diagram − Full
Load of Fuel
Weight and Balance Diagram − Full
Load of Passengers 5

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CONTROL − GENERAL

1. Description
This section shows the general data applicable to the aircraft and includes:
− Dimensions and areas
− Definition of terms
− Aircraft stations
− Reference datum points
− Maximum weight limits
− Maximum center of gravity limits
− Balance change due to operation
− Takeoff setting.

2. Dimensions and Areas

The dimensions and areas show the exterior and principal dimensions and areas of the aircraft
(refer to 01−00−10).

3. Definition of Terms
The definition of terms shows the definitions of the important terms used in this manual (refer
to 01−00−20).

4. Aircraft Stations
The aircraft stations show the position of the aircraft stations and the number system used to
identify the aircraft stations (refer to 01−00−30).

5. Reference Datum Points

The reference datum points show the position of the zero reference datum and the relationship
of the balance arm to other specified stations (refer to 01−00−40).

6. Maximum Weight Limits

The maximum weight limits show important aircraft weight limits (refer to 01−00−50).

7. Maximum Center of Gravity Limits

The maximum center of gravity limits show important center of gravity limits related to aircraft
loads for flight (refer to 01−00−60).

8. Balance Change Due to Operation

The balance change due to operation shows the effect of the operation of some devices on
the aircraft center of gravity (refer to 01−00−70).

9. Takeoff Setting
The takeoff setting shows how the horizontal stabilizer is set in relation to the center of gravity
of the aircraft at takeoff (refer to 01−00−80).

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DIMENSIONS AND AREAS − DESCRIPTION AND OPERATION

1. General
This section gives dimension and area information for the Canadair Regional Jet Series 200ER
aircraft. Dimensions are measured in a parallel axis or a perpendicular axis to the fuselage
reference plane at WL97.5. Chord lines are measured as projections on the wing reference
plane. The wing reference plane passes through WL53.25 at the center line of the aircraft and
has a dihedral angle of +2.33 degrees with respect to the fuselage reference plane. The
overall dimensions are shown in Figure 1.

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5.84 m 1.45 m
3.708 m
2.90 m
1.676 m
2.286 m
21.23 m

9.30 m

2.69 m 4.27 m 6.20 m

NOTES
1 Maximum ramp weight is 23 247 kg.

2 Ground clearance is 0.10 m

with the passenger door down.
1.37 m
0.914 m 3.83 m

6.299 m
rwb0100100_001.dg, gd/pb, 03/05/95

1.524 m 1.727 m 1.270 m

2 1
24.38 m
26.77 m
Dimensions and Areas
Figure 1

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2. General Aircraft Data

The data shown here is related to the wings (refer to Figure 2), the empennage and tail (refer
to Figure 3), and the fuselage and the landing gear (refer to Figure 4).

WINGS
DEFINITION DIMENSION
Span (including winglets) 69.75 ft (21.23 m)
Root chord (fuselage center line) 16.84 ft (5.13 m)
Tip chord 4.16 ft (1.27 m)
Mean aerodynamic chord (MAC)
(MAC leading edge at FS493.793) 99.43 in. (2.53 m)
Aspect ratio (net wing) 8.85
Taper ratio (net wing) 0.34
Thickness ratio
− WS47.615 13.2%
− WS148.019 10.9%
− WS388.450 10.0%
Dihedral of wing reference plane +2.33 degrees
Sweepback (25% chord line) 24.76 degrees
Spar locations (% chord)
− Front 7.3
− Rear 60.0
Ailerons
− Span (% wing span)* 17.3
− Chord (% wing chord) 31.8
Flaps
− Type Double slotted
− Span (% wing span)* 57.4
− Chord (% wing chord)
− Outboard 33.6
− Inboard 33.6
*( Percentage of the wing span is calculated excluding winglet)
Wings
Figure 2 (Sheet 1)

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WINGS
DEFINITION DIMENSION
Spoilers (2 on each side)
− Ground lift dumping
Inboard
− Span (% wing span)* 10.5
− Chord (% wing chord at WS148.019) 10.9
Outboard
− Span (% wing span)* 9.3
− Chord (% wing chord at WS148.019) 10.9
Spoilers − Flight
− Span (% wing span)* 13.8
− Chord (% wing chord) 10.3
Spoileron
− Span (% wing span)* 10.5
− Chord (% wing chord) 8.2
*(Percentage of the wing span is calculated excluding winglet)
Wings
Figure 2 (Sheet 2)

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EMPENNAGE − TAIL
DEFINITION DIMENSION
Horizontal tail surface
− Span 20.33 ft (6.19 m)
− Root chord (theoretical − fuselage center
line leading edge at FS955.88) 7.42 ft (2.26 m)
Tip chord (theoretical) 2.73 ft (0.83 m)
Aspect ratio 4.069
Taper ratio 0.369
Airfoil section designation
− Root NACA 0010−64 MOD
− Tip NACA 0008−64 MOD
Thickness ratio
− Root 10%
− Tip 8%
− Sweepback (25% chord line) 28.74 degrees
− Location of elevator hinge line (% chord) 70
− Distance from 25% wing MAC to 25%
horizontal tail MAC 40.60 ft (12.37 m)
Vertical tail surface
− Span (WL102.5 to 242) 11.63 ft (3.54 m)
− Root chord (WL102.5) 12.50 ft (3.81 m)
− Tip chord (theoretical − WL254.00) 7.91 ft (2.41 m)
− Aspect ratio (geometric) 1.12
− Taper ratio 0.66
Airfoil section
− Root NACA 0011 MOD
− Tip NACA 0010 MOD
Thickness ratio
− Root 11%
− Tip 10%
− Sweepback (25% chord line) 41 degrees
− Location of rudder hinge line (% chord) 72.5
Empennage and Tail
Figure 3

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FUSELAGE
DEFINITION DIMENSION
Diameter 8.83 ft (2.69 m)
Length 80.00 ft (24.38 m)
Static ground angle 0 degree
LANDING GEAR
DEFINITION DIMENSION
Wheel size:
− Main gear 15 in. (0.381 m)
− Nose gear 10 in. (0.254 m)
Tire size:
− Main gear H29 x 9.00−15
− Nose gear 18 x 4.4,12 PR
Loaded (in−service) tire pressure (Series
200ER aircraft):
− Nose gear 146−153 psi (1004−1054 kPa)
− Main gear 169−177 psi (1162−1220 kPa)

NOTE: A loaded, or in−service, condition is

when the tire assembly is installed on the
aircraft and the weight of the aircraft is on the
tire (the aircraft is not on jacks).
Track:
− Main gear 10 ft 5 in. (3.175 m)
− Nose gear 11.5 in. (0.129 m)
Wheel base (max.) 37 ft. 4.5 in. (11.39 m)
Turning circle:
− Minimum Width for 180−degree Turn 75.00 ft (22.86 m)
The aircraft weight and center of gravity changes this value.
Fuselage and Landing Gear
Figure 4

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WEIGHT AND BALANCE MANUAL

DEFINITION OF TERMS − GENERAL

1. General
In this section, the terms used for the important weight and balance conditions are clearly
defined. This helps to prevent errors in the use of the data in the Weight and Balance Manual
(WBM). Many of the terms are shown as abbreviations and as arithmetic definitions.

2. Zero Fuel Weight (ZFW)

This is the operational weight empty (OWE) plus the payload (P/L). It must not be more than
the maximum zero fuel weight (MZFW).
ZFW = OWE + P/L

3. Drainable Fuel
This is the portion of the unusable fuel that can be removed from the fuel tanks. This can be
found when you subtract the trapped fuel from the unusable fuel.
Drainable fuel = unusable fuel − trapped fuel

4. Manufacturer’s Weight Empty (MWE)

This is the weight of the aircraft which includes only the components that are clearly part of the
aircraft (power plant, structure systems). It is a dry weight which includes only the fluids
contained in closed systems.

5. Maximum Landing Weight (MLW)

This is the maximum approved weight at which an aircraft can land.
MLW = maximum weight for landing

6. Maximum Takeoff Weight (MTOW)

This is the maximum weight at which an aircraft can start a takeoff run.
MTOW = MRW − fuel allowance for taxi

7. Maximum Ramp Weight (MRW)

This is the maximum weight at which an aircraft can move safely on the ground. It includes
the fuel for these displacements and the takeoff run.
MRW = MTOW + fuel allowance for taxi

8. Maximum Zero Fuel Weight (MZFW)

This is the maximum weight of an aircraft before the usable fuel is loaded on the aircraft.
MZFW= maximum weight before fueling

9. Maximum Payload
This is the weight which you get when you subtract the operational weight empty (OWE) from
the maximum zero fuel weight.

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Maximum payload = MZFW − OWE

10. Minimum Flight Weight

This is the minimum weight at which an aircraft can fly and land.

11. Operational Weight Empty (OWE)

This is the sum of the weight of the operational items added to the manufacturer’s weight
empty (MWE).

12. Operational Items

This is the weight which you get as you add the personnel, equipment and supplies necessary
for a specific operation.
Operational items = personnel + equipment + supplies

13. Payload (P/L)

This is the weight of the passengers, cargo, baggage and any additional load.
P/L = weight of passengers + cargo + baggage + additional load

14. Trapped Fuel

This is the fuel that is left after the usual fuel drain.
Trapped fuel = fuel left after defueling and draining

15. Unusable Fuel

This is the fuel that is left after the engines and the auxiliary power unit (APU) have run out of
fuel. This includes the drainable fuel and the trapped fuel.

16. Usable Fuel

This is the fuel available for the aircraft engines.

17. Useful Load

This is the weight found when you subtract the operational weight empty (OWE) from the ramp
weight. This includes the payload and usable fuel.
Useful load = ramp weight − OWE

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WEIGHT AND BALANCE MANUAL

AIRCRAFT STATIONS − DESCRIPTION AND OPERATION

1. General
To identify aircraft stations, five major components are shown in relation to their respective
reference planes. The fuselage and vertical stabilizer are shown in Figure 1. The horizontal
stabilizer, wing, and power plant detail are shown in Figure 2.

2. Abbreviations and Definitions

A. Fuselage Station (FS)

The fuselage stations are measured along the X datum line. The fuselage stations are
measured in inches and are perpendicular to the fuselage center line.

B. Wing Station (WS)

The wing stations are measured in inches and are perpendicular to the wing reference
plane and parallel to the center line of the fuselage.

C. Vertical Stabilizer Station (VSS)

The vertical stabilizer stations are measured in inches and are perpendicular to the center
line of the vertical stabilizer rear spar.

D. Horizontal Stabilizer Station (HSS)

The horizontal stabilizer stations are measured in inches and are perpendicular to the
center line of the horizontal stabilizer rear spar.

E. Waterline (WL)
The waterlines are measured in inches and are horizontal lines perpendicular to the
buttock line (BL) and parallel to the fuselage center line.

F. Buttock Line (BL)

The buttock lines are measured in inches. The buttock lines are vertical lines
perpendicular to the waterline (WL) and fuselage center line. The buttock lines are parallel
to the fuselage vertical center line.

G. Engine Station (ES)

The engine stations are measured along the X datum line. The engine stations are
measured in inches and are perpendicular to the center line of the engine.

3. Mass−Account Coding System

For weight and balance calculations, the aircraft stations have related values in the
X component of the mass−account coding system (refer to Figure 3).

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VSS242.00
VSS235.00
VSS231.00
VSS222.00
VSS158.70
VSS139.20
VSS128.20
VSS117.50
VSS103.10
67.5% REAR SPAR VSS86.10
VSS69.10
VERTICAL STABILIZER VSS52.10
VSS37.10
VSS23.10
FS886.00
FS864.00
VSS0.0 FS843.50
FS815.00
FS802.20 TAIL CONE
FS794.70
FS759.00
FS755.00
FS736.00
FS718.00
FS700.00

WL97.50
FS672.20 FS682.00
AFT FS654.50
FUSELAGE FS640.00
FS621.00 FS625.30
FS605.00
FS589.00
FS574.00
FS559.00 + 112
FS559.00 + 96
FS559.00 + 80
AFT FS559.00 + 64
EXTENSION FS559.00 + 48
FS559.00 + 32
FS559.00 + 16
FS559.00
FS544.00
FS529.00
FS513.00
MID FS499.00
FS484.00
FUSELAGE FS473.15
FS461.00
FS449.85
FS439.00
FS424.00
FS409.00 + 128
FS409.00 + 112
FS409.00 + 96
WL73.50

FWD FS409.00 + 80
FS409.00 + 64
EXTENSION FS409.00 + 48
FS409.00 + 32
FS409.00 + 16
FS409.00
FS394.00
FS379.00
FWD/MID FS364.00
FS349.00
FUSELAGE FS333.00
rwb0100300_001.dg, sb/gd, 05/07/94

FS319.70
FS310.00
FS295.00
FS280.00
WL79.50

FS265.00
FS250.00
FS235.00
FWD FS220.00
FUSELAGE FS210.00
FS193.00 FS202.75
FS169.00
FS144.00
Fuselage and Vertical Stabilizer
Figure 1

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FS411.00
FS511.25
FS585.00
FS652.26
FS843.80
FS886.00
FS903.00
FS943.00

FS863.00

FS437.00

FS409+98
C
L FUS WS0.00
16.50

AIR NOSTRUM
BL22.50 25.70
41.30

EFFECTIVITY: ALL
BL45.00 CL NAC 56.90
WS65.75 72.50
WS85.50 WS80.50 BL86.17 88.10
104.10
WS106.40 2 111.00
WS127.25 122.00
WS137.60 WS148.01
WS163.00
WS178.00
WS199.00
WS220.00
WS242.00
WS274.00 WS264.00
WS282.00
WS294.50
WS314.50
WS330.25
WS353.00 WS343.50

Figure 2
WS366.00
C

WS377.40
WS389.00
WS407.08
WEIGHT AND BALANCE MANUAL

FS625.30
FS652.26
FS674.73

CL FUS

WS389.00

Horizontal Stabilizer, Wing, and Power Plant

WS407.08

15
CL NAC
BL86.17

01−00−30
2

WGLTS0.00
WGLTS49.89
ES100.72
ES135.84
ES151.14
ES155.31
ES177.00
ES185.00
ES200.00
ES218.17
ES230.13

rwb0100300_002.dg, gd, 08/07/94

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Z

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EFFECTIVITY: ALL
XARM

16 41 152 281 409 559 671 867

67.5% R/S

FS169.00 FS409.00 FS559.00 FS755.00

Figure 3
FS144.00 FS280.00 FS409.00 +128.00 FS559.00 +112.00
C
WEIGHT AND BALANCE MANUAL

Mass−Account Coding System

NOTE
The relation between the aircraft reference axis system,

01−00−30
the fuselage stations and related locations is shown here.

rwb0100300_003.dg, sb/gd, 08/07/94

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WEIGHT AND BALANCE MANUAL

REFERENCE DATUM POINTS − GENERAL

1. Zero Reference Datum

The zero reference datum is found at the intersection of the fuselage center line of the aircraft
and the reference plane found 0.406 meters (16.00 inches) forward of the nose radome (refer
to Figure 1). The XARMS are measured aft of the zero reference datum.

2. Weighing Datum
The weighing datum is found on the bottom of the aircraft, forward of the wing fairing and on
the center line at XARM 9.525 meters (375.00 inches).

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MAC LEADING EDGE

MAC
12.542 m 2.526 m
(493.79 in.) (99.43 in.)

AIR NOSTRUM
METERS

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1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27

50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 850 900 950 1000 1050
INCHES
NOSE FORWARD FORWARD FORWARD MID AFT AFT
CONE FUSELAGE MID EXTENSION FUSELAGE EXTENSION FUSELAGE
FUSELAGE

1.041 m
3.861 m
7.137 m

0.406 m
22.022 m

17.043 m

10.389 m
14.199 m

(41.00 in.)

(16.00 in.)
(867.00 in.)

(409.00 in.)
(671.00 in.)

(281.00 in.)
(559.00 in.)

(152.00 in.)

Figure 1
C

Reference Datum Points

WEIGHT AND BALANCE MANUAL

TAIL CONE
NOSE
WHEEL

ZERO REFERENCE DATUM

AXLE FORWARD WEIGHING AFT
CENTER JACKING DATUM JACKING
LINE POINT POINTS

01−00−40
XARM XARM XARM XARM
2.550 m 3.810 m 9.525 m 13.825 m
(100.40 in.) (150.00 in.) (375.00 in.) (544.30 in.)
rwb0100400_001.dg, gd, 07/07/94

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WEIGHT AND BALANCE MANUAL

3. Mean Aerodynamic Chord

The mean aerodynamic chord (MAC) is parallel to the fuselage between the leading and
trailing edges of the wing. The leading edge of the MAC is at XARM 12.542 meters
(493.79 inches). The length of the MAC is 2.526 meters (99.43 inches).
For SI units, the XARM position in percentage of the MAC is shown in Figure 2 and is
calculated as follows:

(XARM * 12.54234)
− % MAC = 100
2.52552

PERCENTAGE MAC CONVERSION TABLE

XARM .000 .001 .002 .003 .004 .005 .006 .007 .008 .009
(m)
12.80 10.20 10.24 10.28 10.32 10.36 10.40 10.44 10.48 10.52 10.56
12.81 10.60 10.64 10.68 10.72 10.76 10.80 10.84 10.88 10.92 10.96
12.82 10.99 11.03 11.07 11.11 11.15 11.19 11.23 11.27 11.31 11.35
12.83 11.39 11.43 11.47 11.51 11.55 11.59 11.63 11.67 11.71 11.75
12.84 11.79 11.83 11.87 11.91 11.94 11.98 12.02 12.06 12.10 12.14
12.85 12.18 12.22 12.26 12.30 12.34 12.38 12.42 12.46 12.50 12.54
12.86 12.58 12.62 12.66 12.70 12.74 12.78 12.82 12.86 12.90 12.93
12.87 12.97 13.01 13.05 13.09 13.13 13.17 13.21 13.25 13.29 13.33
12.88 13.37 13.41 13.45 13.49 13.53 13.57 13.61 13.65 13.69 13.73
12.89 13.77 13.81 13.85 13.89 13.92 13.96 14.00 14.04 14.08 14.12
12.90 14.16 14.20 14.24 14.28 14.32 14.36 14.40 14.44 14.48 14.52
12.91 14.56 14.60 14.64 14.68 14.72 14.76 14.80 14.84 14.88 14.91
12.92 14.95 14.99 15.03 15.07 15.11 15.15 15.19 15.23 15.27 15.31
12.93 15.35 15.39 15.43 15.47 15.51 15.55 15.59 15.63 15.67 15.71
12.94 15.75 15.79 15.83 15.86 15.90 15.94 15.98 16.02 16.06 16.10
12.95 16.14 16.18 16.22 16.26 16.30 16.34 16.38 16.42 16.46 16.50
12.96 16.54 16.58 16.62 16.66 16.70 16.74 16.78 16.82 16.85 16.89
12.97 16.93 16.97 17.01 17.05 17.09 17.13 17.17 17.21 17.25 17.29
12.98 17.33 17.37 17.41 17.45 17.49 17.53 17.57 17.61 17.65 17.69
12.99 17.73 17.77 17.81 17.84 17.88 17.92 17.96 18.00 18.04 18.08
13.00 18.12 18.16 18.20 18.24 18.28 18.32 18.36 18.40 18.44 18.48
13.01 18.52 18.56 18.60 18.64 18.68 18.72 18.76 18.80 18.83 18.87
13.02 18.91 18.95 18.99 19.03 19.07 19.11 19.15 19.19 19.23 19.27
Percentage MAC Conversion (SI) − Data
Figure 2 (Sheet 1)

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PERCENTAGE MAC CONVERSION TABLE

XARM .000 .001 .002 .003 .004 .005 .006 .007 .008 .009
(m)
13.03 19.31 19.35 19.39 19.43 19.47 19.51 19.55 19.59 19.63 19.67
13.04 19.71 19.75 19.78 19.82 19.86 19.90 19.94 19.98 20.02 20.06
13.05 20.10 20.14 20.18 20.22 20.26 20.30 20.34 20.38 20.42 20.46
13.06 20.50 20.54 20.58 20.62 20.66 20.70 20.74 20.77 20.81 20.85
13.07 20.89 20.93 20.97 21.01 21.05 21.10 21.13 21.17 21.21 21.25
13.08 21.29 21.33 21.37 21.41 21.45 21.49 21.53 21.57 21.61 21.65
13.09 21.69 21.72 21.76 21.80 21.84 21.88 21.92 21.96 22.00 22.04
13.10 22.08 22.12 22.16 22.20 22.24 22.28 22.32 22.36 22.40 22.44
13.11 22.48 22.52 22.56 22.60 22.64 22.68 22.72 22.75 22.79 22.83
13.12 22.87 22.91 22.95 22.99 23.03 23.07 23.11 23.15 23.19 23.23
13.13 23.27 23.31 23.35 23.39 23.43 23.47 23.51 23.55 23.59 23.63
13.14 23.67 23.70 23.74 23.78 23.82 23.86 23.90 23.94 23.98 24.02
13.15 24.06 24.10 24.14 24.18 24.22 24.26 24.30 24.34 24.38 24.42
13.17 24.85 24.89 24.93 24.97 25.01 25.05 25.09 25.13 25.17 25.21
13.18 25.25 25.29 25.33 25.37 25.41 25.45 25.49 25.53 25.57 25.61
13.19 25.65 25.68 25.72 25.76 25.80 25.84 25.88 25.92 25.96 26.00
13.20 26.04 26.08 26.12 26.16 26.20 26.24 26.28 26.32 26.36 26.40
13.21 26.44 26.48 26.52 26.56 26.60 26.64 26.67 26.71 26.75 26.79
13.22 26.83 26.87 26.91 26.95 26.99 27.03 27.07 27.11 27.15 27.19
13.23 27.23 27.27 27.31 27.35 27.39 27.43 27.47 27.51 27.55 27.59
13.24 27.62 27.66 27.70 27.74 27.78 27.82 27.86 27.90 27.94 27.98
13.25 28.02 28.06 28.10 28.14 28.18 28.22 28,26 28.30 28.34 28.38
13.26 28.42 28.46 28.50 28.54 28.58 28.61 28.65 28.69 28.73 28.77
13.27 28.81 28.85 28.89 28.93 28.97 29.01 29.05 29.09 29.13 29.17
13.28 29.21 29.25 29.29 29.33 29.37 29.41 29.45 29.49 29.53 29.57
13.29 29.60 29.64 29.68 29.72 29.76 29.80 29.84 29.88 29.92 29.96
13.30 30.00 30.04 30.08 30.12 30.16 30.20 30.24 30.28 30.32 30.36
13.31 30.40 30.44 30.48 30.52 30.55 30.59 30.63 30.67 30.71 30.75
13.32 30.79 30.83 30.87 30.91 30.95 30.99 31.03 31.07 31.11 31.15
Percentage MAC Conversion (SI) − Data
Figure 2 (Sheet 2)

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PERCENTAGE MAC CONVERSION TABLE

XARM .000 .001 .002 .003 .004 .005 .006 .007 .008 .009
(m)
13.33 31.19 31.23 31.27 31.31 31.35 31.39 31.43 31.47 31.51 31.54
13.34 31.58 31.62 31.66 31.70 31.74 31.78 31.82 31.86 31.90 31.94
13.35 31.98 32.02 32.06 32.10 32.14 32.18 32.22 32.26 32.30 32.34
13.36 32.38 32.42 32.46 32.50 32.53 32.57 32.61 32.65 32.69 32.73
13.37 32.77 32.81 32.85 32.89 32.93 32.97 33.01 33.05 33.09 33.13
13.38 33.17 33.21 33.25 33.29 33.33 33.37 33.41 33.45 33.49 33.52
13.39 33.56 33.60 33.64 33.68 33.72 33.76 33.80 33.84 33.88 33.92
13.40 33.96 34.00 34.04 34.08 34.12 34.16 34.20 34.24 34.28 34.32
13.41 34.36 34.40 34.44 34.47 34.51 34.55 34.59 34.63 34.67 34.71
13.42 34.75 34.79 34.83 34.87 34.91 34.95 34.99 35.03 35.07 35.11
* EXAMPLE: XARM 13.054 meters = 20.260% MAC
Percentage MAC Conversion (SI) − Data
Figure 2 (Sheet 3)

4. Nosewheel−Axle Center Line

The center line of the nosewheel axle is found at XARM 2.550 meters (100.40 inches). The
center line location can be measured if the aircraft is weighed on platform scales (refer to
01−80−40).

5. Main−Landing−Gear−Wheel−Axle Center Line

The center line of the main−landing−gear wheel axle changes with the load put on the
main−landing−gear (refer to Figure 3). The center line location can be measured if the
aircraft is weighed on platform scales (refer to 01−80−40).

6. Forward Jacking Point

The forward jacking point of the aircraft is at XARM 3.810 meters (150.00 inches).

7. Aft Jacking Point

The aft jacking points of the aircraft are at XARM 13.825 meters (544.30 inches).

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13
GROUND LOAD PER MAIN LANDING GEAR (x 1000 kg)

12 555 kg MAX GEAR LOAD

6
5 351 kg MIN GEAR LOAD
5
13.920 13.925 13.930 13.935 13.940 13.945 13.950 13.955

APPROXIMATE MAIN WHEEL AXLE CENTERLINE LOCATION (meters)

rwb0100400_002.dg, gd/pm, 01/03/99

NOTE
Inflation pressure for each main landing−gear
shock−absorber at the fully extended position is 36.13 bar.
The wheel axle centerline must be measured
as the aircraft is weighed.

Main Landing−Gear Center Line

Figure 3

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MAXIMUM WEIGHT LIMITS − GENERAL

1. General
The aircraft is approved for operation at specific weight limits. Refer to Figure 1 for
Series100ER aircraft and Figure 2 for Series 100LR aircraft.

AIRCRAFT CONDITION WEIGHT LIMIT

MINIMUM FLIGHT WEIGHT 13 608 kg (30 000 lb)
MAXIMUM RAMP WEIGHT 23 247 kg (51 250 lb)
MAXIMUM TAKEOFF WEIGHT (MTOW) 23 133 kg (51 000 lb)
MAXIMUM LANDING WEIGHT (MLW) 21 319 kg (47 000 lb)
MAXIMUM ZERO FUEL WEIGHT (MZFW) 19 958 kg (44 000 lb)
MAXIMUM PAYLOAD
NOTE: MZFW − OWE (the value changes as the OWE changes for each flight).
Maximum Weight Limits − Series 100ER
Figure 1

AIRCRAFT CONDITION WEIGHT LIMIT

MINIMUM FLIGHT WEIGHT 13 608 kg (30 000 lb)
MAXIMUM RAMP WEIGHT 24 154 kg (53 250 lb)
MAXIMUM TAKEOFF WEIGHT (MTOW) 23 995 kg (52 900 lb)
MAXIMUM LANDING WEIGHT (MLW) 21 319 kg (47 000 lb)
MAXIMUM ZERO FUEL WEIGHT (MZFW) 19 958 kg (44 000 lb)
MAXIMUM PAYLOAD
NOTE: MZFW − OWE (the value changes as the OWE changes for each flight).
Maximum Weight Limits − Series 100LR
Figure 2

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MAXIMUM CENTER OF GRAVITY LIMITS − GENERAL

1. General
The center of gravity limits data and the related graph are shown for Series 100ER aircraft in
Figure 1 and Figure 2. For Series 100LR aircraft, this data and the related graph are shown in
Figure 3 and Figure 4 The lateral payload should be divided as symmetrically as possible
along the center line of the aircraft (refer to the AFM (CSP A−012) for lateral center of gravity
restrictions).

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CENTER OF GRAVITY LIMITS − SERIES 100ER

FORWARD LIMIT AFT LIMIT
GROSS XARM MOMENT % MAC XARM MOMENT % MAC
WEIGHT (m) (1000 kg*m) (m) (1000 kg*m)
(kg)
13 608 12.820 174.5 11.00 13.350 181.7 32.00
14 000 12.820 179.5 11.00 13.350 186.9 32.00
14 100 12.820 180.8 11.00 13.350 188.2 32.00
14 200 12.820 182.0 11.00 13.350 189.6 32.00
14 300 12.820 183.3 11.00 13.350 190.9 32.00
14 400 12.820 184.6 11.00 13.350 192.2 32.00
14 500 12.820 185.9 11.00 13.350 193.6 32.00
14 600 12.820 187.2 11.00 13.350 194.9 32.00
14 700 12.820 188.5 11.00 13.350 196.2 32.00
14 800 12.820 189.7 11.00 13.350 197.6 32.00
14 900 12.820 191.0 11.00 13.350 198.9 32.00
15 000 12.820 192.3 11.00 13.350 200.3 32.00
15 100 12.820 193.6 11.00 13.350 201.6 32.00
15 200 12.820 194.9 11.00 13.350 202.9 32.00
15 300 12.820 196.1 11.00 13.350 204.3 32.00
15 400 12.820 197.4 11.00 13.350 205.6 32.00
15 422 12.820 197.7 11.00 13.350 205.9 32.00
15 500 12.816 198.6 *10.83 13.357 207.0 32.26
15 600 12.810 199.8 *10.61 13.365 208.5 32.59
15 700 12.804 201.0 *10.39 13.374 210.0 32.92
15 800 12.799 202.2 *10.17 13.382 211.4 33.25
15 900 12.793 203.4 *9.95 13.390 212.9 33.58
16 000 12.788 204.6 *9.73 13.399 214.4 33.91
Center of Gravity Limits (SI) − Data (Series 100ER Aircraft)
Figure 1 (Sheet 1)

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CENTER OF GRAVITY LIMITS − SERIES 100ER

FORWARD LIMIT AFT LIMIT
GROSS XARM MOMENT % MAC XARM MOMENT % MAC
WEIGHT (m) (1000 kg*m) (m) (1000 kg*m)
(kg)
16 100 12.783 205.8 *9.51 13.407 215.9 34.24
16 200 12.776 207.0 *9.26 13.415 217.3 34.57
16 300 12.771 208.2 *9.06 13.424 218.8 34.90
16 329 12.770 208.5 *9.00 13.426 219.2 35.00
16 400 12.766 209.4 *8.85 13.432 220.3 *35.24
16 500 12.759 210.5 *8.63 13.441 221.8 *35.57
16 600 12.753 211.7 *8.40 13.449 223.3 *35.90
16 700 12.748 212.9 *8.18 13.457 224.7 *36.23
16 800 12.742 214.1 *7.96 13.466 226.2 *36.56
16 900 12.737 215.3 *7.74 13.474 227.7 *36.89
16 933 12.735 215.6 *7.67 13.477 228.2 *37.00
17 000 12.731 216.4 *7.52 13.477 229.1 *37.00
17 100 12.726 217.6 *7.30 13.477 230.5 *37.00
17 200 12.720 218.8 *7.08 13.477 231.8 *37.00
17 237 12.718 219.2 *7.00 13.477 232.3 *37.00
17 300 12.718 220.0 *7.00 13.477 233.1 *37.00
17 400 12.718 221.3 *7.00 13.477 234.5 *37.00
17 500 12.718 222.6 *7.00 13.477 235.8 *37.00
17 600 12.718 223.8 *7.00 13.477 237.2 *37.00
17 700 12.718 225.1 *7.00 13.477 238.5 *37.00
17 800 12.718 226.4 *7.00 13.477 239.9 *37.00
17 900 12.718 227.7 *7.00 13.477 241.2 *37.00
18 000 12.718 228.9 *7.00 13.477 242.6 *37.00
18 100 12.718 230.2 *7.00 13.477 243.9 *37.00
18 200 12.718 231.5 *7.00 13.477 245.3 *37.00
18 300 12.718 232.7 *7.00 13.477 246.6 *37.00
18 400 12.718 234.0 *7.00 13.477 248.0 *37.00
18 500 12.718 235.3 *7.00 13.477 249.3 *37.00
18 600 12.718 236.6 *7.00 13.477 250.7 *37.00
18 700 12.718 237.8 *7.00 13.477 252.0 *37.00
Center of Gravity Limits (SI) − Data (Series 100ER Aircraft)
Figure 1 (Sheet 2)

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CENTER OF GRAVITY LIMITS − SERIES 100ER

FORWARD LIMIT AFT LIMIT
GROSS XARM MOMENT % MAC XARM MOMENT % MAC
WEIGHT (m) (1000 kg*m) (m) (1000 kg*m)
(kg)
18 800 12.718 239.1 *7.00 13.477 253.4 *37.00
18 900 12.718 240.4 *7.00 13.477 254.7 *37.00
19 000 12.718 241.7 *7.00 13.477 256.1 *37.00
19 100 12.718 242.9 *7.00 13.477 257.4 *37.00
19 200 12.718 244.2 *7.00 13.477 258.8 *37.00
19 300 12.718 245.5 *7.00 13.477 260.1 *37.00
19 400 12.718 246.7 *7.00 13.477 261.4 *37.00
19 500 12.718 248.0 *7.00 13.477 262.8 *37.00
19 600 12.718 249.3 *7.00 13.477 264.1 *37.00
19 700 12.718 250.5 *7.00 13.477 265.5 *37.00
19 800 12.718 251.8 *7.00 13.477 266.8 *37.00
19 900 12.718 253.1 *7.00 13.477 268.2 *37.00
20 000 12.718 254.4 *7.00 13.477 269.5 *37.00
20 100 12.718 255.6 *7.00 13.477 270.9 *37.00
20 200 12.718 256.9 *7.00 13.477 272.2 *37.00
20 300 12.718 258.2 *7.00 13.477 273.6 *37.00
20 400 12.718 259.4 *7.00 13.477 274.9 *37.00
20 500 12.718 260.7 *7.00 13.477 276.3 *37.00
20 600 12.718 262.0 *7.00 13.477 277.6 *37.00
20 700 12.718 263.3 *7.00 13.477 279.0 *37.00
20 800 12.718 264.5 *7.00 13.477 280.3 *37.00
20 900 12.718 265.8 *7.00 13.477 281.7 *37.00
21 000 12.718 267.1 *7.00 13.477 283.0 *37.00
21 100 12.718 268.4 *7.00 13.477 284.4 *37.00
21 200 12.718 269.6 *7.00 13.477 285.7 *37.00
21 300 12.718 270.9 *7.00 13.477 287.1 *37.00
21 400 12.718 272.2 *7.00 13.477 288.4 *37.00
21 500 12.718 273.4 *7.00 13.477 289.8 *37.00
Center of Gravity Limits (SI) − Data (Series 100ER Aircraft)
Figure 1 (Sheet 3)

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CENTER OF GRAVITY LIMITS − SERIES 100ER

FORWARD LIMIT AFT LIMIT
GROSS XARM MOMENT % MAC XARM MOMENT % MAC
WEIGHT (m) (1000 kg*m) (m) (1000 kg*m)
(kg)
21 600 12.718 274.7 *7.00 13.477 291.1 *37.00
21 700 12.718 276.0 *7.00 13.477 292.4 *37.00
21 800 12.718 277.3 *7.00 13.477 293.8 *37.00
21 900 12.718 278.5 *7.00 13.477 295.1 *37.00
22 000 12.718 279.8 *7.00 13.477 296.5 *37.00
22 100 12.718 281.1 *7.00 13.477 297.8 *37.00
22 200 12.718 282.3 *7.00 13.477 299.2 *37.00
22 300 12.718 283.6 *7.00 13.477 300.5 *37.00
22 400 12.718 284.9 *7.00 13.477 301.9 *37.00
22 500 12.718 286.2 *7.00 13.477 303.2 *37.00
22 600 12.718 287.4 *7.00 13.477 304.6 *37.00
22 700 12.718 288.7 *7.00 13.477 305.9 *37.00
22 800 12.718 290.0 *7.00 13.477 307.3 *37.00
22 900 12.718 291.2 *7.00 13.477 308.6 *37.00
23 000 12.718 292.5 *7.00 13.477 310.0 *37.00
23 100 12.718 293.8 *7.00 13.477 311.3 *37.00
23 109 12.718 293.9 *7.00 13.477 311.4 *37.00
23 200 12.718 295.1 *7.00 13.477 312.7 *37.00
23 247 12.718 295.7 *7.00 13.477 313.3 *37.00
* Enroute limit.
Center of gravity limitations shown above include an allowance for in−flight movement.
The allowance is intended to cover any reasonable movement in flight of passengers and
crew (examples of which are shown in section 01−40−30 page 1) and aircraft systems
(examples of which are shown in section 01−00−70 page 1).
Center of Gravity Limits (SI) − Data (Series 100ER Aircraft)
Figure 1 (Sheet 4)

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12.69

12.74

12.80

12.85

12.90

12.95

13.00

13.05

13.10

13.15

13.20

13.25

13.30

13.35

13.40

13.45

13.50
METERS AFT OF THE ZERO REFERENCE DATUM
25

24
23 247 kg MAX RAMP WEIGHT

23 23 133 kg MAX TAKEOFF WEIGHT

T/O, APPROACH & LANDING

FWD C of G LIMIT
IN−FLIGHT ONLY

21 21 319 kg MAX LANDING WEIGHT

IN−FLIGHT ONLY
AFT C of G LIMIT
AIRCRAFT WEIGHT (x 1000 kg)

20
19 958 kg MAX ZERO FUEL WEIGHT
19

17
7.0% 37.0%
16
9.0% 35.0%

14
13 608 kg MIN IN−FLIGHT WEIGHT
13

10
6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38
POSITION (%MAC)
rwb0100600_001.dg, gd, 12/06/97

Center of Gravity Limits (SI) − Graph (Series 100 ER Aircraft)

Figure 2

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CENTER OF GRAVITY LIMITS − SERIES 100LR

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CENTER OF GRAVITY LIMITS − SERIES 100LR

AIR NOSTRUM
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CENTER OF GRAVITY LIMITS − SERIES 100LR

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CENTER OF GRAVITY LIMITS − SERIES 100LR

FORWARD LIMIT AFT LIMIT
GROSS XARM MOMENT % MAC XARM MOMENT % MAC
WEIGHT (m) (1000 kg*m) (m) (1000 kg*m)
(kg)
21 600 12.718 274.7 *7.00 13.477 291.1 *37.00
21 700 12.718 276.0 *7.00 13.477 292.4 *37.00
21 800 12.718 277.3 *7.00 13.477 293.8 *37.00
21 900 12.718 278.5 *7.00 13.477 295.1 *37.00
22 000 12.718 279.8 *7.00 13.477 296.5 *37.00
22 100 12.718 281.1 *7.00 13.477 297.8 *37.00
22 200 12.718 282.3 *7.00 13.477 299.2 *37.00
22 300 12.718 283.6 *7.00 13.477 300.5 *37.00
22 400 12.718 284.9 *7.00 13.477 301.9 *37.00
22 500 12.718 286.2 *7.00 13.477 303.2 *37.00
22 600 12.718 287.4 *7.00 13.477 304.6 *37.00
22 700 12.718 288.7 *7.00 13.477 305.9 *37.00
22 800 12.718 290.0 *7.00 13.477 307.3 *37.00
22 900 12.718 291.2 *7.00 13.477 308.6 *37.00
23 000 12.718 292.5 *7.00 13.477 310.0 *37.00
23 100 12.718 293.8 *7.00 13.477 311.3 *37.00
23 200 12.718 295.1 *7.00 13.477 312.7 *37.00
23 300 12.718 296.4 *7.00 13.477 314.0 *37.00
23 400 12.718 297.6 *7.00 13.477 315.4 *37.00
23 404 12.718 297.7 *7.00 13.477 315.4 *37.00
23 500 12.718 298.9 *7.00 13.435 315.7 *35.33
Center of Gravity Limits (SI) − Data (Series 100LR Aircraft)
Figure 3 (Sheet 4)

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CENTER OF GRAVITY LIMITS − SERIES 100LR

FORWARD LIMIT AFT LIMIT
GROSS XARM MOMENT % MAC XARM MOMENT % MAC
WEIGHT (m) (1000 kg*m) (m) (1000 kg*m)
(kg)
23 519 12.718 299.1 *7.00 13.426 315.8 *35.00
23 600 12.718 300.2 *7.00 13.391 316.0 *33.60
23 700 12.718 301.4 *7.00 13.347 316.3 *31.86
23 800 12.718 302.7 *7.00 13.303 316.6 *30.13
23 900 12.718 304.0 *7.00 13.260 316.9 *28.40
23 995 12.718 305.2 *7.00 13.218 317.2 *26.75
24 000 12.718 305.3 *7.00 13.216 317.2 *26.67
24 095 12.718 306.5 *7.00 13.174 317.4 *25.02
24 154 12.718 307.2 *7.00 13.148 317.6 *24.00
* Enroute limit.
Center of gravity limitations shown above include an allowance for in−flight movement.
The allowance is intended to cover any reasonable movement in flight of passengers and
crew (examples of which are shown in section 01−40−30 page 1) and aircraft systems
(examples of which are shown in section 01−00−70 page 1).
Center of Gravity Limits (SI) − Data (Series 100LR Aircraft)
Figure 3 (Sheet 5)

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12.69

12.74

12.80

12.85

12.90

12.95

13.00

13.05

13.10

13.15

13.20

13.25

13.30

13.35

13.40

13.45

13.50
METERS AFT OF THE ZERO REFERENCE DATUM
25
24 154 kg MAX RAMP WEIGHT
24
23 995 kg MAX TAKEOFF WEIGHT
23
T/O, APPROACH & LANDING

T/O, APPROACH & LANDING

22
FWD C of G LIMIT
IN−FLIGHT ONLY

IN−FLIGHT ONLY
AFT C of G LIMIT
21 21 319 kg MAX LANDING WEIGHT

20
19 958 kg MAX ZERO FUEL WEIGHT
AIRCRAFT WEIGHT (x 1000 kg)

17
7.0%
37.0%
16 35.0%
9.0%

14 13 608 kg MIN FLIGHT WEIGHT

10
6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38
rwb0100600_021.dg, pm/lr, 07/03/06

POSITION (%MAC)

Center of Gravity Limits (SI) − Graph (Series 100 LR Aircraft)

Figure 4

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BALANCE CHANGE DUE TO OPERATION − GENERAL

1. General
The operation of some systems changes the center of gravity of the aircraft during flight,
ground service operations, and landing/takeoff. Their effect on the aircraft center of gravity is
shown in Figure 1.

AIRCRAFT D MOMENT FOR SYSTEMS THAT CHANGE

SYSTEM
FROM FULLY DEPLOYED TO FULLY STOWED POSITION
MAIN LANDING GEARS (1) −73.2 kg*m −6356 lb*in.
NOSE LANDING GEAR −42.2 kg*m −3660 lb*in.
OUTBOARD FLAPS −10.3 kg*m −890 lb*in.
INBOARD FLAPS −20.9 kg*m −1813 lb*in.
THRUST REVERSER +49.4 kg*m +4286 lb*in.
(1) Aircraft Δ moment for main landing gears that change from typical on ground"
position to fully stowed position is −151.6 kg*m (−13 156.0 lb*in.).
Balance Change Due to Operation
Figure 1

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TAKEOFF SETTING − GENERAL

1. Stabilizer Setting for Takeoff

The adjustment of the horizontal stabilizer trim at the time of takeoff must agree with the
related center of gravity of the aircraft.
Refer to Figure 1.

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10
EICAS STABILIZER TRIM UNITS

GREEN BAND
8

1
rwb0100800_001.dg, sb, 17/03/94

0
0 5 10 15 20 25 30 35 40

CG − % MAC

Horizontal Stabilizer Settings for Takeoff

Figure 1

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FUEL − GENERAL

1. General
This section shows data on the fuel tank configuration. It also shows data on the unusable
and usable fuel in the main and center fuel tanks.
For the definition of other fuel−related terms, refer to 01−00−20.

2. Fuel Tank Configuration

The aircraft has two standard fuel tanks. The standard fuel tanks are found in each wing, and
the optional fuel tank is found in the lower part of the center fuselage. The standard fuel tanks
are identified as the main tanks and the optional fuel tank is identified as the center tank (refer
to Figure 2).
The correct refuel/defuel procedures are found in the Aircraft Maintenance Manual (refer to
AMM 12−11−28).

3. Unusable Fuel
The unusable fuel includes the two types of fuel that follow (refer to Figure 1):

A. Trapped Fuel
This is the unusable fuel left after the usual defueling and draining.

B. Residual Fuel
This is the unusable fuel that can be removed through drain points with the
usual procedures.

VOLUME WEIGHT XARM

TRAPPED FUEL 28.4 7.5 6.2 22.7 50.1 12.56 494.3

− MAIN TANKS (24.3) (6.4) (5.3) (19.5) (42.9) (12.70) (500.0)

− CENTER TANK (4.1) (1.1) (0.9) (3.2) (7.2) (11.68) (460.0)
RESIDUAL FUEL 26.5 7.0 5.8 21.3 46.9 12.56 494.3

− MAIN TANKS (22.7) (6.0) (5.0) (18.3) (40.2) (12.70) (500.0)

− CENTER TANK (3.8) (1.0) (0.8) (3.0) (6.7) (11.68) (460.0)
UNUSABLE FUEL 54.9 14.5 12.1 44.0 97.0 12.56 494.3

− MAIN TANKS (47.1) (12.4) (10.4) (37.7) (83.1) (12.70) (500.0)

− CENTER TANK (7.8) (2.1) (1.7) (6.3) (13.9) (11.68) (460.0)
* BASED ON: 0.8028 kg/L (6.70 lb/U.S. gallon)
Unusable Fuel
Figure 1

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WS314.00

BL45.00
C
BL45.00

WS314.00

C CENTER TANK

R RIGHT MAIN TANK

rwb0120000_001.dg, gd, 17/03/94

L LEFT MAIN TANK

Fuel Tank Configuration

Figure 2

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WEIGHT AND BALANCE MANUAL

4. Usable Fuel
The usable fuel volumes, weights, arms and moments are shown in Figure 3 (SI).
NOTE: The normal fuel burn sequence is as follows:

1. 254 kilograms (560 pounds) (6%) from the main tanks

2. Total center tank fuel
3. Remaining main tank fuel (4000 kilograms) (8820 pounds).

*Assuming a fuel weight of 0.8028 kg/L (6.7 lb/U.S. gallon)

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MAIN TANKS CENTER TANK

VOLUME WEIGHT (5300 liters) (2782 liters)
(L) (kg) XARM MOMENT XARM MOMENT
(m) (kg*m/1000) (m) (kg*m/1000)
227 182 12.04 2.2 11.58 2.1
400 321 12.09 3.9 11.64 3.7
600 482 12.14 5.8 11.69 5.6
800 642 12.17 7.8 11.70 7.5
1000 803 12.21 9.8 11.71 9.4
1200 963 12.24 11.8 11.71 11.3
1400 1124 12.27 13.8 11.71 13.2
1600 1285 12.30 15.8 11.71 15.0
1800 1445 12.33 17.8 11.71 16.9
2000 1606 12.36 19.8 11.71 18.8
2200 1766 12.39 21.9 11.71 20.7
2400 1927 12.42 23.9 11.69 22.5
2600 2087 12.45 26.0 11.67 24.4
2782 2234 − − 11.64 26.0
2800 2248 12.48 28.1 − −
3000 2409 12.51 30.1 − −
3200 2569 12.54 32.2 − −
3400 2730 12.57 34.3 − −
3600 2890 12.59 36.4 − −
3800 3051 12.62 38.5 − −
4000 3211 12.65 40.6 − −
4200 3372 12.68 42.7 − −
4400 3532 12.70 44.9 − −
4600 3693 12.73 47.0 − −
4800 3854 12.76 49.2 − −
5000 4014 12.78 51.3 − −
5200 4175 12.82 53.5 − −
5300 4255 12.84 54.6 − −
Usable Fuel (SI)
Figure 3

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FLUIDS − GENERAL

1. General
This section includes the volume and the weight and balance information on the engine oil, the
three hydraulic systems, the potable water, and the chemical fluid used for the lavatory system
(refer to Figure 1).

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SYSTEM VOLUME WEIGHT XARM

U.S. qt U.S. gal L lb kg in. m
ENGINE OIL AT 15.6 _C
(60 _F):
FULL
− PER ENGINE TANK 6.8 1.70 6.44 13.7 6.21 757.35 19.24
− OIL REPLENISHMENT TANK 6.0 1.50 5.68 12.1 5.48 841.00 21.36
− REPLENISHMENT LINES 3.7 0.93 3.52 7.5 3.40 799.84 20.32
AND INTERNAL ENGINE OIL

TOTAL PER AIRCRAFT 23.3 5.83 22.08 47.0 21.32 785.67 19.96

HYDRAULIC SYSTEM FLUID

AT 25.0 _C (77 _F)
(PHOSPHATE ESTER−BASED
HYDRAULIC FLUIDS)

LO−DENSITY:
1.01 kg/L (MAXIMUM)
(8.43 lb/U.S. gal (MAXIMUM))
− SYSTEM 1 2.16 8.2 18.3 8.3 742* 8.85*
− SYSTEM 2 3.20 12.1 27.0 12.2 681* 17.30*
− SYSTEM 3 5.50 20.8 46.3 21.0 502* 12.75*

TOTAL PER AIRCRAFT 10.86 41.1 91.6 41.5 603* 15.32*

HI−DENSITY:
1.06 kg/L (MAXIMUM)
(8.86 lb/US gal (MAXIMUM))
− SYSTEM 1
2.16 8.2 19.2 8.7 742* 18.85*
− SYSTEM 2
3.20 12.1 28.4 12.9 681* 17.30*
− SYSTEM 3
5.50 20.8 48.7 22.1 502* 12.75*
TOTAL PER AIRCRAFT
10.86 41.1 96.3 43.7 603* 15.32*

POTABLE WATER AT
15.6 _C (60 _F):
FULL
− AFT LAVATORY TANK 5.00 18.9 41.7 18.9 709.0 18.01
− FORWARD GALLEY TANK 5.00 18.9 41.7 18.9 213.0 5.41
CHEMICAL TOILET FLUID AT
2.3 8.7 19.2 8.7 660.0 16.76
15.6 _C (60_F)
* ESTIMATED CENTER OF GRAVITY
Aircraft Fluids
Figure 1

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PERSONNEL − GENERAL

1. General
This section shows the effect of personnel (passengers and crew) weights, position and
movement on the center of gravity of the aircraft. It also shows the dimensions and volumes
of the storage compartments. This section includes:
− The passenger and crew arrangement
− The passenger and crew weights and center of gravity
− The balance change due to movement
− The storage compartment volumes.

2. Passenger and Crew Arrangement

The passenger and crew arrangement shows the position of the seats, bulkheads, cargo
compartments, galleys, and the emergency exits (refer to 01−40−10).

3. Passenger and Crew Weights and Center of Gravity

The passenger and crew weights and center of gravity shows the center of gravity of the
passengers and crew while they are in their seats at takeoff (refer to 01−40−20).

4. Balance Change Due to Movement

The balance change due to movement shows examples of center of gravity shift caused by the
passenger and crew movement between the seats, galley, and lavatory (refer to 01−40−30).

5. Compartment Volume
The compartment volume shows the basic dimensions and volumes of different storage
compartments (refer to 01−40−40).

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PASSENGER AND CREW ARRANGEMENT − GENERAL

1. General
The basic interior configuration of the aircraft shows the position of the galley, lavatory, cargo
compartment, seats, bulkheads, and emergency exits. These are the usual positions of the
passengers and the crew in the aircraft (refer to Figure 1).

2. Passenger and Crew Center of Gravity

During flight, the crew and passengers are usually in their specified seat positions. The center
of gravity related to these positions is shown in Figure 2.

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INTERIOR LAYOUT
50 PASSENGER CONFIGURATION

A PILOT SEAT
B COPILOT SEAT
A B
C OBSERVER SEAT
D PILOT AND COPILOT BULKHEAD
E WARDROBE
E C
F FORWARD GALLEY (G1)
G FORWARD ATTENDANT SEAT
G H AFT GALLEY (G2)
PASSENGER DOOR J AFT ATTENDANT SEAT
D
0.91 m X 1.78 m K AFT LAVATORY
(36.00 in. X 70.00 in.) L AFT CABIN BULKHEAD
F M CARGO COMPARTMENT

1 22 SEATS WITH 0.787 m (31.00 in.) PITCH

1
2 24 SEATS WITH 0.787 m (31.00 in.) PITCH
3 0.940 m (37.00 in.) PITCH

EMERGENCY EXIT 3 EMERGENCY EXIT

0.51 m X 0.97 m 0.51 m X 0.97 m
(20.00 in. X 38.00 in.) (20.00 in. X 38.00 in.)

K
rwb0140100_028.dg, jp, 21/08/98

CARGO
COMPARTMENT L
DOOR
1.09 m X 0.84 m
(43.00 in. X 33.00 in.) M

Basic Interior Configuration

Figure 1

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C
NOTE
Passengers and crew are
in the upright seated position.
ROW 1

ROW 2
XARM XARM
ROW 3 LOCATION
(METERS) (INCHES)

ROW 4
A 3.226 127
ROW 5 B 3.759 148
C 4.623 182
ROW 6 D 16.307 642
ROW 1 6.426 253
ROW 7 ROW 2 7.214 284
ROW 3 8.001 315
ROW 8 ROW 4 8.788 346
ROW 9 ROW 5 9.576 377
ROW 6 10.363 408
ROW 10 ROW 7 11.151 439
ROW 8 12.090 476
ROW 11 ROW 9 12.878 507
ROW 10 13.665 538
ROW 12 ROW 11 14.453 569
ROW 12 15.240 600
ROW 13 ROW 13 16.027 631

D
Identified as ROW 14 on the aircraft.
rwb0140100_014.dg, pt/jp, 03/03/99

Passenger and Crew Center of Gravity

Figure 2

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NOTES
A
1. Passengers and crew are
B in the upright seated position.
2. All examples are based upon
C 48 passenger configuration.

ROW 1

ROW 2
XARM XARM
ROW 3 LOCATION
(METERS) (INCHES)
ROW 4
A 3.226 127
ROW 5 B 3.759 148
C 4.623 182
ROW 6 D 16.307 642
ROW 1 6.426 253
ROW 7 ROW 2 7.214 284
ROW 3 8.001 315
ROW 8 ROW 4 8.788 346
ROW 5 9.576 377
ROW 9 ROW 6 10.363 408
ROW 7 11.151 439
ROW 10
ROW 8 12.090 476
ROW 11 ROW 9 12.878 507
ROW 10 13.665 538
ROW 12 ROW 11 14.453 569
ROW 12 15.240 600
ROW 13 ROW 13 16.027 631

D
rwb0140100_058.dg, sw/lr, 05/08/05

Passenger and Crew Center of Gravity − 50 Passenger Configuration

Figure 3

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PASSENGER/CREW WEIGHT AND CENTER OF GRAVITY − GENERAL

1. General
During flight, each passenger and crew member has a specified seat position related to a
specific center of gravity. The data for the usual passenger/crew weight and center of gravity,
in their usual position in their seats, is shown in Figure 1.

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STATION UNIT WEIGHT QTY TOTAL WEIGHT XARM MOMENT

1000 1000
CREW lb kg lb kg in. m
lb*in. kg*m
PILOT 185 84 1 185 84 127 3.23 23.52 0.27
COPILOT 185 84 1 185 84 127 3.23 23.52 0.27
OBSERVER 185 84 1 185 84 148 3.76 27.41 0.32
FORWARD
185 84 1 185 84 182 4.62 33.67 0.39
ATTENDANT
AFT
185 84 1 185 84 642 16.31 118.89 1.37
ATTENDANT
CREW
18 8 5 88 40 665 16.89 58.52 0.68
BAGGAGE
TOTAL CREW AND BAGGAGE 1014 460 281 7.16 285.53 3.29

1000 1000
PASSENGERS lb kg lb kg in. m
lb*in. kg*m
ROW1 185 84 2 370 168 253 6.43 93.70 1.08
ROW2 185 84 4 741 336 284 7.21 210.37 2.42
ROW3 185 84 4 741 336 315 8.00 233.42 2.69
ROW4 185 84 4 741 336 346 8.79 256.30 2.95
ROW4 185 84 4 741 336 346 8.79 256.30 2.95
ROW5 185 84 4 741 336 377 9.58 279.26 3.22
ROW6 185 84 4 741 336 408 10.36 302.23 3.48
ROW7 185 84 4 741 336 439 11.15 325.19 3.75
ROW8 185 84 4 741 336 476 12.09 352.60 4.06
ROW9 185 84 4 741 336 507 12.88 375.56 4.33
ROW10 185 84 4 741 336 538 13.67 398.53 4.59
ROW11 185 84 4 741 336 569 14.45 421.49 4.86
ROW12 185 84 4 741 336 600 15.24 444.45 5.12
ROW13* 185 84 4 741 336 631 16.03 467.42 5.39
PASSENGER
44 20 50 2205 1000 699 17.75 1541.60 17.75
BAGGAGE
* Identified as ROW 14 on the aircraft.
TOTAL PASSENGERS AND BAGGAGE 11 464 5200 497 12.63 5701.04 65.68

TOTAL CREW, PASSENGERS, AND

12 478 5660 480 12.19 5986.57 68.97
BAGGAGE
Usual Passenger/Crew Weight and Center of Gravity
Figure 1

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BALANCE CHANGE DUE TO MOVEMENT − GENERAL

1. General
The movement of the crew, passengers, or a trolley during flight causes changes in the center
of gravity of the aircraft. These changes are related to the quantity and direction of the
movement and weight of the crew members, passengers or trolley (refer to Figure 1).

SOURCE OF
FROM TO WEIGHT D MOMENT
CG CHANGE
lb kg lb*in. kg*m
AFT SEAT FORWARD
185.2 84.0 −81 682 −943
ATTENDANT POSITION GALLEY
FORWARD SEAT AFT
185.2 84.0 +89 075 +1028
ATTENDANT POSITION LAVATORY
FULL HALF SIZE FORWARD
ROW 13* 132.3 60.0 +60 197 +693
TROLLEY GALLEY
FIRST AFT
PASSENGER 185.2 84.0 +75 953 +877
ROW LAVATORY
Balance Change Due to Movement
Figure 1

* Identified as ROW 14 on the aircraft.

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COMPARTMENT VOLUME − GENERAL

1. General
The passenger compartment is found between the flight compartment bulkhead at FS280.00
and the aft passenger compartment bulkhead at FS559.00+84.00. This area has a volume of
50.9 m3 (1797.2 ft3) and contains the passenger area and the storage compartments in the
galley (refer to Figure 1).

2. Compartment Volumes
Many storage compartments are installed in different parts of the aircraft. These
compartments include the overhead bins, underseat storage, the wardrobe storage and the
cargo compartment. Refer to Figure 2 and Figure 3 for their volumes and dimensions.
NOTE: See the effectivity block on the page for applicable aircraft seral numbers.

3. Maximum Package Dimensions

In order to determine whether it is possible to stow a rectangular package of a certain
dimension in the cargo compartment, the table in Figure 4 may be used.
The tables should be entered in the relevant column and on the relevant line, the intersection
box of column and line shows the maximum package length in centimeters. No attempt has
been made to calculate the number of packages per compartment, nor to determine the
progressive reduction in compartment size due to loading. Therefore, the figures shown in the
table apply to empty compartments only and packages stored flat on the floor.

4. Cargo Compartment
The limiting dimensions are as follows:
− Largest* rectangular ended package: 109.2 X 76.2 X 217.2 cm (43.0 X 30.0 X 85.5 in.)
− Largest* square ended package: 76.2 X 76.2 X 217.2 cm (30.0 X 30.0 X 85.5 in.)
− Longest package with square end of 53.3 X 7.6 cm (21.0 X 3.0 in.).

* in volume

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CL CL
A B

0.390 m
(15.35 in.)

INTERIOR (TRIM TO TRIM) VIEW OF CABIN GALLEY

2.480 m (LOOKING AFT)
(97.65 in.) ON FS349.00

TYPICAL PASSENGER COMPARTMENT

CROSS SECTION
C

A OVERHEAD STORAGE BINS

B INTERIOR LINING H
C STOWAGE COMPARTMENT D

D STOWAGE COMPARTMENT H
E STOWAGE COMPARTMENT
F
F ICE BUCKET
J
G STANDARD CONTAINER (2)
G
H STANDARD CONTAINER (3)
J STANDARD HALF−SIZE MEAL CART (2)
rwb0140400_029.dg, jp, 27/08/98

E
AFT GALLEY − 2

Passenger Compartment Cross Section

Figure 1 (Sheet 1)

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B
A

C
E

GALLEY 1
VIEW LOOKING FWD

A WATER SYSTEM CONTROL PANEL

B OVEN CONTROLLER (2)
rwb0140400_030.dg, jp, 19/08/98

C OVEN (2)
D WASTE CART (1)
E COFFEE MAKER
F STANDARD HALF−SIZE MEAL CART (5)

Passenger Compartment Cross Section

Figure 1 (Sheet 2)

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TYPICAL OVERHEAD
STORAGE BIN

0.25 m
1.14 m (10.0 in.)
(45.0 in.)

0.20 m
(8.0 in.)

0.41 m
(16.0 in.)

UNIT VOLUME (APPROXIMATELY) TOTAL VOLUME (APPROXIMATELY)

m3 ft 3 m3 ft 3
0.11 4.0 2.02 71.4

UNDER SEAT
CARGO SPACE

0.18 m
(7.0 in.)

0.81 m
(32.0 in.)
0.36 m
(14.0 in.)
rwb0140400_002.dg, gd, 29/03/94

Remaining space between the floor and the life vest.

UNIT VOLUME (APPROXIMATELY) TOTAL VOLUME (APPROXIMATELY)
m3 ft 3 m3 ft 3
0.05 1.8 1.28 45.2

Overhead Bin/Underseat Storage − Compartment Volumes

Figure 2

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WARDROBE 0.21 m
STORAGE (8.3 in.) 0.14 m
(5.5 in.)

A 1.32 m A STANDARD CONTAINER

(52.01 in.) B STOWAGE
B

0.53 m TOTAL VOLUME

0.30 m (21.0 in.) m3 ft 3
(12.0 in.)
0.23 8.0

CARGO
COMPARTMENT
1.42 m
(56.0 in.)

CARGO
COMPARTMENT RADIUS
DOOR 1.25 m
2.03 m (49.13 in.)
(85.4 in.)
2.17 m

(80.0 in.) 0.84 m

0.61 m
(33.00 in.)
(23.91 in.)

2.25 m CARGO
(31.11 in.)

(10.61 in.)
0.79 m

(88.5 in.) COMPARTMENT

0.27 m

CARGO FLOOR
rwb0140400_003.dg, gd gw, 17/02/95

COMPARTMENT DOOR
VIEW LOOKING FORWARD
1.10 m
(43 in.)
TOTAL VOLUME
VIEW LOOKING DOWN m3 ft 3
6.48 228.8

Wardrobe Storage/Cargo Compartment − Compartment Volumes

Figure 3

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CM HEIGHT
7.6 15.2 20.3 25.4 30.5 35.6 40.6 45.7 48.3 53.3 63.5 76.2 83.8
WIDTH MAXIMUM LENGTH
7.6 248.9 248.9 248.9 248.9 248.9 248.9 248.9 248.9 248.9 248.9 246.4 245.1 30.5
15.2 241.3 241.3 241.3 241.3 241.3 241.3 241.3 241.3 241.3 241.3 241.3 236.2 30.5
20.3 238.8 238.8 238.8 238.8 238.8 238.8 238.8 238.8 238.8 238.8 236.2 231.1 30.5
30.5 231.1 231.1 231.1 231.1 231.1 231.1 231.1 231.1 231.1 231.1 218.4 217.2 30.5
38.1 218.4 218.4 218.4 218.4 218.4 218.4 218.4 218.4 218.4 218.4 217.2 217.2 30.5
45.7 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
50.8 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
55.9 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
63.5 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
76.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
83.8 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
88.9 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
101.6 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
109.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 217.2 30.5
Maximum Package Dimension
Figure 4

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GROUND OPERATIONS − GENERAL

1. General
This section shows the ground operations data that is applicable to the aircraft. The data that
is included in this section is as follows:
− Ground balance limits
− Jacking locations
− Maximum static loads
− Leveling and weighing procedure
− Systems fluids lateral center of gravity
− Weight and balance of primary components.

2. Ground Balance Limits

The ground balance limits show the usual stable aircraft configuration and the effects of
changes to it. It also shows the ground static envelope for the nose landing gear (refer
to 01−80−10).

3. Jacking Locations
The jacking locations show the correct points to put the three jacks that are necessary to
safely lift the aircraft (refer to 01−80−20).

4. Maximum Static Loads

The maximum static loads show the aircraft loads as it is lifted on jacks and the maximum
loads that can be put on the floor of the cargo compartment (refer to 01−80−30).

5. Leveling and Weighing Procedure

The leveling and weighing procedure shows the preparation steps and the procedures that are
necessary to level and weigh the aircraft (refer to 01−80−40).

6. Systems Fluids Lateral Center of Gravity

The systems fluids lateral center of gravity shows the data on system fluids volumes and the
related center of gravity (refer to 01−80−50).

7. Weight and Balance of Primary Components

The weight and balance of primary components show weight and balance data on important
components of the aircraft (refer to 01−80−60).

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GROUND BALANCE LIMITS − GENERAL

1. General
When the aircraft is supplied, it has a configuration that helps to prevent accidental tipover
(refer to Figure 1). The aircraft may be put into a possible tipover condition if any change is
done to the basic configuration of the aircraft. The changes can include one or more of those
that follow:
− Add equipment
− Remove equipment
− Move equipment
− Unusual ground operations.

2. Stable Aircraft Inspection

Before you perform any change to the aircraft, do the steps that follow to make sure the
aircraft will remain stable.
A. Make an analysis of the aircraft weight and balance moment for the desired configuration
(refer to the equipment checklist in 02−00−00).

B. Check the weight and center of gravity of the aircraft (from the analysis in step A) (refer to
Figure 1).

C. Ballast the aircraft if minimal margin exists to tipover. Rework steps A, B, and C for any
future changes. The ballast should be installed at FS300.00 without exceeding the floor
loading limits of 744 kg/m (500 lb/ft) parallel to the fuselage plane.
NOTE: Additional precautions must be taken if the conditions that follow occur:
(a) Fresh fallen snow on the horizontal stabilizer and pylons
(b) Aircraft located on an inclined surface.

The tables shown in Figure 2 and Figure 3 may be used for weight and balance calculations
for static stability.

3. Towing
CAUTION: THE MINIMUM LOAD OF 680 KG (1500 LB) ON THE NOSEWHEEL IS LIMITED
BY CENTER OF GRAVITY ENVELOPE AND MUST NOT BE DECREASED. IT IS
ALSO LIMITED BY THE STRUCTURE OF THE STEERING CAMS FOR THE
NOSEWHEEL. IF THE AIRCRAFT IS TOWED OR TAXIED WITH A NOSEWHEEL
LOAD LESS THAN 680 KG (1500 LB), POSSIBLE PROBLEMS CAN OCCUR
AFFECTING THE STEERING CAMS AND SO AFFECT THE SHOCK
ABSORBERS FOR THE NOSEWHEEL.
When the aircraft is towed, keep a minimum load of 680 kg (1500 lb) on the nosewheel. If the
load on the nosewheel is not sufficient, add ballast on the floor of the passenger compartment
(ballast as per paragraph 2.).

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FOR NORMAL GROUND STATIC OPERATIONS

24
23 247 kg MAX RAMP WEIGHT
22

20
AIRCRAFT WEIGHT (x 1000 kg)

STATIC STABILITY TIP OVER

12
11 558 kg MIN OPERATING WEIGHT EMPTY

10
13.925 13.930 13.935 13.940 13.945 13.950

AIRCRAFT CENTER OF GRAVITY (meters)

rwb0180100_001.dg, gd/jp, 10/03/99

NOTE
Inflation pressure for each main landing−gear
shock−absorber at the fully extended position is 36.13 bar.
To be used with the aircraft on a leveled surface only.
(Refer to 1−80−10, page 1, paragraph 2 for inclined
surface correction).

Balance Limit (SI)

Figure 1

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SNOW
MOMENT
DEPTH WEIGHT
mm in. kg lb lb*in. kg*m
0 0 0 0 0 0
50 2 90 202 187 997 2132
100 4 180 404 375 994 4264
150 6 270 606 563 990 6396
200 8 360 807 751 987 8527
250 10 451 1009 939 984 10 659
300 12 541 1211 1 127 981 12 791
350 14 631 1413 1 315 977 14 923
400 16 721 1615 1 503 974 17 055
450 18 811 1817 1 691 971 19 187
500 20 901 2019 1 879 968 21 318
Fresh Fallen Snow On Horizontal Stabilizer and Pylons
Figure 2
NOTE: Assuming snow density of 128.15 kg/m3 (8 lb/ft3).

RAMP
ANGLE AIRCRAFT WEIGHT (kg)
(degree)
11 558 12 000 14 000 16 000 18 000 20 000 22 000 23 247
MOMENT (kg*m)
0 0 0 0 0 0 0 0 0
1 482 500 583 667 750 833 917 969
2 963 1000 1167 1333 1500 1667 1833 1937
3 1444 1499 1749 1999 2249 2499 2749 2905
4 1925 1999 2332 2665 2998 3331 3664 3872
5 2405 2497 2913 3329 3746 4162 4578 4838
6 2885 2995 3494 3993 4492 4991 5491 5802
Aircraft On Inclined Surface
Figure 3
NOTE: Nose up: positive moments.
Nose down: negative moments.

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4. Nose Landing Gear

The ground static load envelope for the nose landing gear is shown in Figure 4.

5. Ground Limitations
The aircraft CG must always remain forward of 47% MAC (FS540.50) to minimize the risk of tail
tipping (tipover). In the event of high wind conditions (in excess of 60 knots) it is
recommended that you observe one of the procedures that follow:
A. Secure the aircraft at the appropriate picketing points (refer to CSP−A−001−002 and
CSP−A−035), or
B. Park the aircraft in a closed hanger, or
C. Add ballast to the nose of the aircraft to make sure that there is sufficient tipover
protection.
Particular care should be taken with aircraft that are in a lightweight/aft CG configuration
(i.e. low fuel/highly loaded cargo compartment/no passenger/no crew).

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% MAC 44 42 40 38 36 34 3230 28 26 24 22 20 18 16 14 12 10 8 6
AIRCRAFT WEIGHT (x 1000 kg)

10
0 500 1000 1500 2000 2500 3000
rwb0180100_003.dg, gd, 15/03/94

NOSE LANDING GEAR LOAD (kg)

Ground Static Load Envelope (SI)

Figure 4

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JACKING LOCATIONS − GENERAL

1. General
There are three points that are used to jack the aircraft. Two are found below the wing at each
rear spar. The third is found aft of the nose landing gear below the forward fuselage. For data
on the maximum permitted jacking load, refer to 01−80−30. When the aircraft is jacked, the
installation of a tail steady helps to make the aircraft stable and helps to prevent an accidental
tipover (refer to Figure 1).
NOTE: When the aircraft is weighed, the tail steady must not touch the aircraft.

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TAIL STEADY

FORWARD JACKING AFT JACKING XARM 22.02 m

POINT POINT (867.00 in.)
XARM 3.810 m XARM 13.825 m
(150.00 in.) (544.30 in.)

WS143.75 WS143.75
rwb0180200_001.dg, gd, 24/03/94

Jacking Locations
Figure 1

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MAXIMUM STATIC LOADS − GENERAL

1. General
The maximum permitted jacking weight of the aircraft is 16 873 kg (37 200 lb). The aircraft has
three jacking locations. The maximum permitted load for each of the two wing jacking
locations is 8437 kg (18 600 lb). The maximum permitted load for the nose jacking location is
2871 kg (6330 lb).

2. Cargo Compartment Floor Load

The cargo compartment floor load must be evenly divided and correctly divided with respect to
the floor panels, floor structure and fuselage specifications (refer to Figure 1).
NOTE: See the effectivity block on the page for applicable aircraft serial numbers.

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CARGO COMPARTMENT FLOOR LOADING

AFT LAVATORY
ATTENDANT C
SEAT

CREW
STOWAGE
B

18.618
16.600

17.000
16.400

16.800

18.400
18.600
16.370
16.586

17.196

17.800

18.200
17.200

17.600

18.000
17.400

METERS

DESCRIPTION ZONES
A B C TOTAL
CARGO FLOOR MAXIMUM LOADING
kg / m 2 366.2 366.2 366.2 366.2
(lb / ft 2) (75.0) (75.0) (75.0) (75.0)
FUSELAGE STRUCTURE MAXIMUM LOADING
(PARALLEL TO FUSELAGE LONGITUDINAL AXIS)
kg / m 92.3 270.8 744.1 744.1
(lb / ft) (62.0) (182.0) (500.0) (500.0)
MAXIMUM LOAD ABILITY PER AREA
kg 19.7 162.6 1042.0 1224.7
(lb) (43.3) (358.4) (2297.3) (2700.0)
NOTE
rwb0180300_005.dg, gd, 29/08/94

The maximum allowable loading for any localized area of the floor is 366.2 kg/m2 (cargo floor
maximum loading). This maximum is applicable for all loading cases except those cases for
which the maximum load per linear meter (along the fuselage longitudinal axis) is greater than
the fuselage structure maximum loading (i.e. 92.3 kg/m for Zone A, 270.8 kg/m for Zone B and
744.1 kg/m for Zone C). For these unusual cases, the maximum allowable loading for the cargo
floor is limited by the fuselage structure maximum loading restrictions.
The crew baggage is to be stowed in the shaded region of Zone B.
Cargo Compartment Floor Load
Figure 1

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LEVELING AND WEIGHING PROCEDURE − GENERAL

1. General
The leveling and weighing procedure permits you to make the aircraft level and find its weight
and its center of gravity in a static parked position". This is done in two steps as follows:
A. Prepare the aircraft to be weighed.
B. Level, weigh and calculate the center of gravity of the aircraft with one of the two
procedures that follow:
− With the landing gear on platform scales
− With the aircraft lifted on jacks and weighed with load cells.

2. Prepare the Aircraft to be Weighed

Prepare the aircraft to have the configuration that follows:
A. Drain the aircraft fuel system.
NOTE: Make sure that the collector tanks also are fully drained.
B. Make sure that:
− The oil and hydraulic systems are full
− The potable water tank and the wash water tank are drained
− The chemical toilet fluid is drained.
C. Make sure that:
− The aircraft interior and exterior are clean and dry
NOTE: If the aircraft is wet or covered with ice or snow, let the aircraft dry.
− The flaps are in the retracted position
− The thrust reversers are in the retracted position
− All the seats are placed in the takeoff position
− The doors and access panels are closed
− Any equipment not related to the aircraft such as tools, work lights, and ground
handling equipment are removed from the aircraft.
D. Put all the flight controls in the neutral position.

3. Weigh the Aircraft on Platform Scales

The equipment and materials that follow are recommended:
− Weighing kit − commercial
− Leveling kit, Part Number G601R082202−1
− Chocks − commercial.

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WARNING: MAKE THE AIRCRAFT LEVEL IN A CLOSED HANGAR. IF THE AIRCRAFT IS

MADE LEVEL IN AN OPEN AREA, THE WIND CAN CAUSE INCORRECT
RESULTS. THE STEP TO WEIGH AND CALCULATE THE CENTER OF GRAVITY
OF THE AIRCRAFT CAN ONLY BE ACCURATE IF THE AIRCRAFT IS MADE
LEVEL CORRECTLY. IF THIS IS NOT CORRECTLY MONITORED, THE
AIRCRAFT MAY NOT BE IN A SAFE BALANCED CONDITION FOR TAKEOFF,
FLIGHT AND LANDING.

WARNING: MAKE SURE THAT NO PERSON IS ON OR IN THE AIRCRAFT WHEN YOU

WEIGH IT. THIS WILL PREVENT INJURIES TO PERSONS AND DAMAGE TO
THE AIRCRAFT. PERSONS ON BOARD CAN ALSO GIVE INCORRECT DATA
DURING THIS STEP.
A. Prepare the aircraft as follows (refer to paragraph 2.):
(1) Align the three platform scales and ramps with the main and nose landing gears on
the aircraft.
NOTE: If you use electronic scales, let them warm up, and follow the
manufacturer’s instructions.
(2) Use the equipment checklist and make sure that the aircraft is in its basic
configuration as follows:
(a) Compare the components on the aircraft with those in the checklist.
(b) Write any difference and correct the aircraft weight and center of gravity as
necessary (refer to 02−00−00 in Weight and Balance Report that is applicable
to the tail number of the aircraft).
(3) Place the chocks on the scales and set the scales to zero. Remove the chocks from
the scales.
(4) Roll the aircraft up the ramps and on the scales.

CAUTION: DO NOT CHANGE THE CHOCKS THAT YOU USED ON THE SCALES
WHEN YOU SET THE SCALES TO ZERO. IF YOU CHANGE THE CHOCKS,
YOU MUST PLACE THE NEW CHOCKS ON THE SCALES AND SET THEM
TO ZERO AGAIN.
(5) Put the chocks in front and behind the wheels.
NOTE: Do not set the parking brake.
(6) Open the aft equipment compartment−door.

CAUTION: THE PLUMB BOB MUST HANG APPROXIMATELY 1.27 CM (0.50 IN.) ABOVE
THE TARGET. IF THE PLUMB BOB IS SET AT A LARGER DISTANCE, YOU
WILL NOT GET ACCURATE RESULTS.
(7) Attach the screw and the plumb bob from the leveling kit to the bracket at the top of
the frame at FS718.75 and BL8.00 (to the left).

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B. Level and weigh the aircraft as follows (refer to Figure 1):

(1) Level the aircraft as follows:

(a) Adjust the oleo or tire pressure until the plumb bob is directly above the center
of the leveling target (refer to AMM 08−20−00 and AMM 12−12−32).
(2) Weigh the aircraft and write the weight data at each platform scale.
(3) Remove the leveling kit and the chocks, and roll the aircraft off the scales and down
the ramps.
(4) Do a visual check of the zero on each of the three channel displays on the platform
scales. If the displays are set to zero, no change to the weight data is necessary. If
the displays do not read zero, change the weight data as follows:
(a) If you read a positive value, subtract it from the weight data written in step
B. (2).
(b) If you read a negative value, add it to the weight data written in step B. (2).
C. Calculate the center of gravity as follows:
− Find the data you need to calculate the center of gravity
− Calculate the center of gravity.
NOTE: Examples of the calculations are found in paragraph 4.
(1) Find the data you need to calculate the XARM (refer to Figure 2):

(a) Read the nose−landing−gear weight from the scale. Write the result as R1.
(b) Read the main−landing−gear weight from each main−landing−gear scale.
NOTE: The left main−landing−gear gives R (left) and the right
main−landing−gear gives R (right).
(c) Add R (left) and R (right). Write the result as R2.
(d) Divide R2 by 2. Write the result as L.
(e) Add R1 and R2. Write the result as W.

CAUTION: MAKE SURE THAT YOU ACCURATELY MEASURE THE DIMENSIONS

B AND D. IF YOU DO NOT DO THIS, YOU MAY GET AN INCORRECT
VALUE.
(f) Measure the distance between the weighing datum point and the
main−landing−gear center line, and write the result as B. Ensure that this
dimension is correctly measured, as its accuracy will affect CG calculations.
Refer to Figure 2 and Figure 4. Use a plumb bob, and drop a line from the
weighing datum point to the ground. Mark this point on the floor with chalk.
Again drop the plumb bob line from each main landing gear wheel centerline to
the surface of the platform scale, and mark these points with chalk. Next, use a
chalk line and connect the two main landing gear centerlines. Now, measure
the distance parallel to the fuselage centerline from the weighing datum point to
the line connecting main landing gear wheel chalk marks. This distance is B".

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ZERO
REFERENCE
DATUM

AIRCRAFT CENTER
OF GRAVITY
AIRCRAFT CG (XARM)

R1 R2
F

MAIN LANDING GEAR

WHEEL AXLE CENTERLINE rwb0180400_001.dg, jp, 26/03/97

Aircraft Weighed on Platform Scales

Figure 1

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ZERO
REFERENCE
DATUM

AIRCRAFT CENTER
OF GRAVITY
AIRCRAFT CG (XARM)

0.406 m
(16.00 in.)

WEIGHING
DATUM W
POINT
F D B

9.525 m (375.00 in.)

rwb0180400_003.dg, gd, 21/07/94

Platform−Scales Weighing Dimension

Figure 2

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(g) Measure the distance between the weighing datum point and the
nose−landing−gear center line, and write the result as D. Make sure that this
dimension is correctly measured, as its accuracy will affect CG calculations.
Refer to Figure 2 and Figure 4. Use a plumb bob and drop a line from the nose
landing gear wheel centerline to the surface of the platform scale, and mark this
point with chalk. Next, measure the distance from this chalk mark to the
weighing datum point chalk mark. This distance is D".
(h) Calculate E as follows:
9.525 meters (375.00 inches) + B.
(i) Make sure that the value of E is correct as follows (refer to Figure 4):
1 Locate L on the ground load per main−landing−gear scale.
2 The value shown is an example of what you calculate.
3 Draw a horizontal line to the curve.
4 Draw a perpendicular line from this point on the curve and read the
wheel−axle center line location such as point E.
NOTE: Make sure that the value for E is correct. This value should be
the same as the E value measured in Figure 2.
(j) Calculate F as follows:
9.525 m (375.00 in.) − D
(2) Calculate the aircraft XARM with the value specified in paragraph (1) as follows:
(a) Calculate the necessary value:
For SI units (R1, R2, and W are in kilograms and E and F are in meters):
AIRCRAFT CG (XARM) = (F R1) ) (E R2)
W
(b) Convert this value to % MAC:
For SI units (R1, R2, and W are in kilograms and E and F are in meters):

(XARM * 12.542)
AIRCRAFT CG (% MAC) = 100
2.526

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4. SI Example to Calculate the Aircraft CG in XARM and %MAC

This metric (SI) example calculates the aircraft center of gravity. Each value, the procedure to
find the value, the formula to use, and an example of the result are shown in Figure 3.

IDENTIFICATION HOW VALUE IS

FORMULA TO USE EXAMPLE OF RESULT
OF VALUE FOUND
R1 Read the display − 1360.78 kg
R (left) Read the display − 10 663.96 kg
R (right) Read the display − 10 654.88 kg
R2 Calculate R (left) + R (right) 21 318.84 kg
L Calculate R2/2 10 659.42 kg
W Calculate R1 + R2 22 679.62 kg
B Measure − 4.422 m
D Measure − 6.975 m
E Calculate 9.525 + B 13.947 m
F Calculate 9.525 − D 2.550 m
AIRCRAFT CG (F x R1) + (E x R2)
Calculate
(XARM) W
AIRCRAFT CG (XARM − 12.542) x 100
Calculate
(%MAC) 2.526
Aircraft CG in XARM and % MAC Example − Steps
Figure 3

Compare the values calculated and measured.

AIRCRAFT CG (METERS) = (F R1) ) (E R2)
W

= (2.550 1360.78) ) (13.947 21318.84)

22679.62
= 13.263 meters

(XARM * 12.542)
AIRCRAFT CG (% MAC) = 100
2.526

(13.263 * 12.542)
= 100
2.526

= 28.54 % MAC

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DISTANCE AFT OF REFERENCE DATUM

13
GROUND LOAD PER MAIN LANDING GEAR (x 1000 kg)

12 555 kg MAX GEAR LOAD

11
L
10

6
5 351 kg MIN GEAR LOAD
5
13.920 13.925 13.930 13.935 13.940 13.945 E 13.950 13.955

WHEEL AXLE CENTERLINE LOCATION (meters)

NOTE
rwb0180400_004.dg, gd, 21/07/94

Inflation pressure for each main landing−gear

shock−absorber at the fully extended position is 36.13 bar.
The wheel axle centerline must be measured
as the aircraft is weighed.

Main−Landing−Gear Position (SI)

Figure 4

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5. Weigh the Aircraft on Jacks

The equipment and materials that follow are recommended:
− Weighing kit − commercial
− Leveling kit Part Number G601R082202−1
− One 5−ton forward−fuselage jack − commercial
− Two 10−ton wing jacks − commercial
− Jacking pads G601R071001−1.

WARNING: MAKE THE AIRCRAFT LEVEL IN A CLOSED HANGAR. IF THE AIRCRAFT IS

WARNING: MAKE SURE THAT NO PERSON IS ON OR IN THE AIRCRAFT WHEN YOU

WEIGH IT. THIS WILL PREVENT INJURIES TO PERSONS AND DAMAGE TO
THE AIRCRAFT. PERSONS ON BOARD CAN ALSO GIVE INCORRECT DATA
DURING THIS STEP.

WARNING: DO NOT SET THE PARKING BRAKE OR CHOCKS AT ANY STAGE OF THE
LIFTING AND/OR LOWERING OF THE AIRCRAFT. IF THE PARKING BRAKE OR
CHOCKS IS SET, THE AIRCRAFT MAY FALL OFF THE JACKS AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO THE AIRCRAFT AND EQUIPMENT.
A. Prepare the aircraft as follows (refer to paragraph 2):
NOTE: Make sure the tail steady is removed.
(1) Prepare the weighing kit for installation and allow it sufficient time to warm up (refer
to the weighing kit manufacturer’s instructions).
(2) Remove the nylon plugs and install the jack pads in the two aft jacking points and
the forward jacking point (the jack pads screw into the fuselage jacking points).
(3) Put the jacks under the aircraft jack pads.

CAUTION: MAKE SURE THAT THERE IS NO SIDE LOAD ON THE LOAD CELLS WHEN
JACKING AIRCRAFT. SIDE LOADS WILL CAUSE INCORRECT READINGS,
CELL FAILURE AND POSSIBLE DAMAGE TO THE AIRCRAFT.
(4) Put the load cells correctly on the jacks and operate jacks manually until load cells
lightly touch jacking pads (refer to Figure 5).
(5) Open the aft equipment−bay compartment−door.

CAUTION: THE PLUMB BOB MUST HANG APPROXIMATELY 1.27 CM (0.50 IN.) ABOVE
THE TARGET. IF THE PLUMB BOB IS SET AT A LARGER DISTANCE, YOU
WILL NOT GET ACCURATE RESULTS.
(6) Attach the screw and the plumb bob from the leveling kit to the bracket at the top of
the frame at FS718.75 and BL8.00 (to the left).

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WING

LOAD PATH JACK PAD

LOAD CELL

PIN CONTACT

JACK AIR GAP

THE CORRECT PROCEDURE

WING

LOAD PATH JACK PAD

LOAD CELL rwb0180400_011.dg, ik, 08/02/00

PIN AIR GAP

JACK
CONTACT

THE INCORRECT PROCEDURE

Load Cell, Jack and Jacking Pad Arrangement

Figure 5

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B. Level and weigh the aircraft as follows (refer to Figure 6):

(1) Set the instruments to zero.
NOTE: Make sure that there is no weight on the load cells.
(2) Lift the aircraft (refer to AMM 07−11−01).
NOTE: Make sure that the landing gear is fully extended.
(3) Adjust the jack heights until the plumb bob is directly above the center of the leveling
target (refer to AMM 08−20−00).
(4) Find the value for R1 as follows:
Get the nose−landing−gear weight data from the load cell.
(5) Find the value for R2 as follows:
Get the sum of each main−landing−gear weight data from the load cells.
(6) Find the weight (W) of the aircraft as follows:
Get the sum of R1 and R2.
(7) Lower the aircraft until there is no load on the jacks and load cells.
(8) Do a visual check of the zero on each of the three channel displays. If the displays
are set to zero, no change to the weight data is necessary. If the displays do not
read zero, change the weight data as follows:
(a) If you read a positive value, subtract it from the weight data found in steps B.
(4) and B. (5).
(b) If you read a negative value, add it to the weight data found in steps B. (4) and
B. (5).
(9) Repeat steps 5.B.1 to 8 to make sure your readings are accurate.
(10) Remove the load cells and the jacks from below the aircraft.
C. Calculate the center of gravity as follows:
NOTE: Examples of the calculations are found in paragraph 4.
(1) Calculate the aircraft center of gravity (XARM) with the data found in paragraph B.:
For SI units (R1, R2, and W are in kilograms):
− XARM = (3.81 R1) ) (13.825 R2) ) 78.3
W
Where 78.3 is the Δ moment (kg*m) for the main landing gears displacement from the
fully extended position to the typical "on ground" position.
(2) Convert this value to % MAC:
For SI units (R1, R2 and W are in kilograms and E and F are in meters):

(XARM * 12.542)
AIRCRAFT CG (% MAC) = 100
2.526

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ZERO
REFERENCE
DATUM

AIRCRAFT CENTER
OF GRAVITY
AIRCRAFT CG (XARM)

R1 W R2

rwb0180400_002.dg, gd, 24/03/94

Aircraft Weighed on Jacks

Figure 6

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LATERAL CENTER OF GRAVITY − GENERAL

1. General
This section gives information on system fluids and the related lateral center of gravity of these
fluids. The level of fuel in each main fuel tank also has an effect on the lateral center of gravity.

2. System Fluids − Lateral Center of Gravity

The volume and the lateral center of gravity of system fluids are as shown in Figure 1.

3. Main Fuel Tank − Lateral Center of Gravity

The center of gravity of the aircraft changes with the quantity of fuel in each main fuel tank
(refer to Figure 2).

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LATERAL CENTER LOCATION

OF GRAVITY ABOUT
SYSTEM VOLUME
ABOUT AIRCRAFT AIRCRAFT
CENTER LINE CENTER LINE
U.S. qt U.S. gal L in. m
ENGINE OIL TANK (LEFT) 6.8 1.70 6.44 95.0 2.41 LEFT
ENGINE OIL TANK (RIGHT) 6.8 1.70 6.44 77.0 1.96 RIGHT
OIL REPLENISHMENT TANK 6.0 1.50 5.68 0 0 CENTER
HYDRAULIC RESERVOIR
− SYSTEM 1 3.12 0.78 2.95 29.5 0.75 LEFT
− SYSTEM 2 4.16 1.04 3.94 29.5 0.75 RIGHT
− SYSTEM 3 11.96 2.99 11.31 0 0 CENTER
POTABLE WATER
(15.6 _C, 60 _F)
− AFT LAVATORY TANK 20.0 5.0 18.9 48.9 1.24 RIGHT
− FORWARD LAVATORY
20.0 5.0 18.9 22.1 0.56 RIGHT
TANK
CHEMICAL TOILET FLUID
9.20 2.3 8.7 36.0 0.91 RIGHT
(15.6 _C, 60 _F)
LEFT MAIN TANK (FULL) 700 2649.8 126.3 3.21 LEFT
RIGHT MAIN TANK (FULL) 700 2649.8 126.3 3.21 RIGHT
CENTER TANK (FULL) 735 2782.3 0 0 CENTER
NOTE: The fuel in the main tanks is usually loaded equally on either side of the aircraft cen-
ter line. When this is done, the general fuel lateral center of gravity along the center
line of the aircraft is sufficiently small that it is not important for weight and center of
gravity calculations. Refer to AMM 12−11−28 for the correct procedure to refuel the
aircraft.
Refer to Figure 2 for the main fuel tank lateral center of gravity related to the
fuel volume.
System Fluids − Lateral Center of Gravity
Figure 1

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3.5

3.21 m
FULL :
2649.8 liters
3
TANK LATERAL CG (meters)

2.5

1.5

1.14 m
1
0 500 1000 1500 2000 2500 3000

FUEL VOLUME (liters)

rwb0180500_001.dg, gd, 17/03/94

NOTE
This graph is used for the right main tank or the left main tank.
The total volume in one main tank is 2649.8 liters.
Fuel volume includes usable fuel and unusable fuel.

Main Fuel Tank − Lateral Center of Gravity

Figure 2

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WEIGHT AND CENTER OF GRAVITY OF PRIMARY COMPONENTS − GENERAL

1. General
This section gives information on the approximate weight and balance of some of the primary
components (refer to Figure 1).

WEIGHT WEIGHT XARM XARM

COMPONENT
(kg) (lb) (m) (in.)
FUSELAGE 7406 16 328 11.06 435.5
WINGS 2607 5747 13.40 527.4
HORIZONTAL STABILIZER 247 545 25.69 1011.3
VERTICAL STABILIZER 403 888 23.84 938.5
NACELLES (2) 563 1241 19.04 749.8
ENGINES (2) 1628 3589 19.44 765.2
MAIN LANDING GEAR (2) 640 1411 13.77 542.0
NOSE LANDING GEAR 88 195 2.43 95.5
Weight and Center of Gravity of the Primary Components
Figure 1

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EXAMPLES AND FORMS − GENERAL

1. General
This section shows examples and forms that are necessary to correctly load and calculate the
weight and center of gravity for the aircraft. The examples include the procedure to write the
data as well as the necessary forms. This section contains the examples that follow:
− Operational loading sheet with 37 passengers
− Dry operating index (DOI) with 29 passengers
− Load and trim sheet with 29 passengers
− Two different operational loading sheets, one with a full load of fuel and the other with a full
load of passengers.
Two copies of the load and trim sheet and of the operational loading sheet must be written for
each flight (refer to 01−90−10).
NOTE: The operational loading sheet is not necessary to write a load and trim sheet.
The usual procedure is to complete and supply the load and trim sheet and the operational
loading sheet to the correct authority. The load and trim sheet and the operational loading
sheet copies are sent as follows:
− Original: in the aircraft
− Copy: to the station trip file.

2. Operational Loading Sheet with 37 Passengers

The operational loading sheet shows the weight build−up from the manufacturer’s weight
empty (MWE) to the maximum ramp weight (refer to 01−90−10).

3. DOI with 29 Passengers

The DOI must be found before you write the load and trim sheet. The DOI is closely related to
the center of gravity of the aircraft. The DOI is calculated with the index and the correction
formulas (refer to 01−90−20).

4. Load and Trim Sheet with 29 Passengers

The load and trim sheet is written to find the weight and the center of gravity of the aircraft as
the loads are divided into the aircraft. The load and trim sheet data is used to verify that the
aircraft is correctly loaded and balanced before takeoff (refer to 01−90−30).

5. Operational Loading Sheets

The operational loading sheets show the weight build−ups and vectors for the full load of fuel
and for the full load of passengers (refer to 01−90−40).

A. Full Load of Fuel

This example shows the build−up and operational loading sheet when a full load of fuel is
put in the aircraft. In this example, the maximum number of passengers is limited to 21.
B. Full Load of Passengers
This example shows the build−up and operational loading sheet with 50 passengers on
the aircraft. When the aircraft has this configuration, only a partial load of fuel can be
used.

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WEIGHT BUILDUP (PAYLOAD) − GENERAL

1. General
The weight buildup shows how the various internal loads are added to the manufacturer’s
weight empty (MWE). The result is the ramp weight and center of gravity of the aircraft. This
example shows an aircraft loaded with 37 passengers.
To do the buildup, start with the MWE and add the various operational and payload items.
Add the weight of the baggage, passengers, and the necessary fuel to calculate the ramp
weight.

2. Weight Buildup Sheet

The weight buildup sheet shows the weight, the center of gravity (XARM) and the related
moment (refer to Figure 1).
NOTE: The examples in this section is for illustrative purposes and contain references to the
design weights for the CRJ200 ER. This method is also applicable to the CRJ200
LR. Where applicable the design weights for the CRJ200 LR may be substituted.

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WEIGHT CG (XARM) MOMENT CG

kg*m lb*in. %
kg lb m in.
/1000 /1000 MAC
MANUFACTURER’S
13 662 30 120 13.51 532.0 184.61 16 023.8 38.4
WEIGHT EMPTY
OPERATIONAL ITEMS (CAN BE REMOVED FROM THE GALLEY)
FORWARD GALLEY
HALF SIZE EMPTY 68.0 150.0 4.49 176.8 0.31 26.5
TROLLEYS (4)
FORWARD GALLEY
HALF SIZE EMPTY 34.0 75.0 4.49 176.8 0.15 13.3
WASTE CARTS (2)
AFT GALLEY HALF
SIZE EMPTY 34.0 75.0 5.94 234.0 0.20 17.6
TROLLEYS (2)
STANDARD EMPTY
14.0 30.8 6.07 239.0 0.08 7.4
CONTAINERS (5)
OVEN (2) 53.7 118.4 4.32 170.0 0.23 20.1
COFFEE BREWER 7.8 17.3 4.65 183.0 0.04 3.2
TYPICAL CONTENT
OF FORWARD
90.7 200.0 4.49 176.8 0.41 35.4
GALLEY HALF SIZE
TROLLEY
TYPICAL CONTENT
OF STANDARD 38.6 85.0 6.07 239.0 0.23 20.3
CONTAINER
Weight Buildup − 37 Passengers
Figure 1 (Sheet 1)

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WEIGHT CG (XARM) MOMENT CG

kg*m lb*in. %
kg lb m in.
/1000 /1000 MAC
OPERATIONAL ITEMS (CREW)
PILOT 84.0 185.2 3.23 127.0 0.27 23.5
COPILOT 84.0 185.2 3.23 127.0 0.27 23.5
FORWARD
84.0 185.2 4.62 182.0 0.39 33.7
ATTENDANT
AFT ATTENDANT 84.0 185.2 16.31 642.0 1.37 118.9
CREW BAGGAGE 32.0 70.5 16.89 665.0 0.54 46.9
FLIGHT MANUALS 31.8 70.0 3.68 145.0 0.12 10.2

FLUIDS
POTABLE WATER
(FORWARD 18.9 41.7 5.41 213.0 0.10 8.9
GALLEY)
WASH WATER
18.9 41.7 18.01 709.0 0.34 29.6
(AFT LAVATORY)
WASH WATER
18.9 41.7 18.01 709.0 0.34 29.5
(AFT LAVATORY)
CHEMICAL TOILET
8.7 19.2 16.76 660.0 0.15 12.7
FLUID
UNUSABLE FUEL 44.0 97.0 12.56 494.5 0.55 48.0
ENGINE OIL 21.3 47.0 19.96 785.7 0.43 36.9

OPERATING
14 560 32 099 13.12 516.6 191.06 16 583.8 23.0
WEIGHT EMPTY
OPERATING
14 434 31 820 13.13 516.8 189.5 16 444.6 23.8
WEIGHT EMPTY
Weight Buildup − 37 Passengers
Figure 1 (Sheet 2)

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WEIGHT CG (XARM) MOMENT CG

kg*m lb*in. %
kg lb m in.
/1000 /1000 MAC
PAYLOAD ITEMS (PASSENGERS)
SEAT ROW 1
(2 PASSENGERS @ 168.0 370.4 6.43 253.0 1.08 93.7
84 kg (185 lb))
SEAT ROW 2
(3 PASSENGERS @ 252.0 555.6 7.21 284.0 1.82 157.8
84 kg (185 lb))
SEAT ROW 3
(2 PASSENGERS @ 168.0 370.4 8.00 315.0 1.34 116.7
84 kg (185 lb))
SEAT ROW 4
(2 PASSENGERS @ 168.0 370.4 8.79 346.0 1.48 128.2
84 kg (185 lb))
SEAT ROW 5
(3 PASSENGERS @ 252.0 555.6 9.58 377.0 2.41 209.4
84 kg (185 lb))
SEAT ROW 6
(2 PASSENGERS @ 168.0 370.4 10.36 408.0 1.74 151.1
84 kg (185 lb))
SEAT ROW 7
(4 PASSENGERS @ 336.0 740.8 11.15 439.0 3.75 325.2
84 kg (185 lb))
SEAT ROW 8
(3 PASSENGERS @ 252.0 555.6 12.09 476.0 3.05 264.4
84 kg (185 lb))
SEAT ROW 9
(4 PASSENGERS @ 336.0 740.8 12.88 507.0 4.33 375.6
84 kg (185 lb))
SEAT ROW 10
(3 PASSENGERS @ 252.0 555.6 13.67 538.0 3.44 298.9
84 kg (185 lb))
SEAT ROW 11
(3 PASSENGERS @ 252.0 555.6 14.45 569.0 3.64 316.1
84 kg (185 lb))
Weight Buildup − 37 Passengers
Figure 1 (Sheet 3)

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WEIGHT CG (XARM) MOMENT CG

kg*m lb*in. %
kg lb m in.
/1000 /1000 MAC
SEAT ROW 12
(2 PASSENGERS @ 168.0 370.4 15.24 600.0 2.56 222.2
84 kg (185 lb))
SEAT ROW 13*
(4 PASSENGERS @ 336.0 740.7 16.03 631.0 5.39 467.4
84 kg (185 lb))

BAGGAGE IN AFT
740.0 1631.4 17.75 698.8 13.13 1140.0
COMPARTMENT
FUEL WEIGHT
−MAIN TANKS 4254.7 9380.0 12.84 505.6 54.64 4742.5
−CENTER TANK 584.3 1287.2 11.70 460.5 6.83 592.7

RAMP WEIGHT 23 247 51 250 12.98 510.9 301.69 26 185.7 17.2

RAMP WEIGHT 23 247 51 250 12.98 510.9 301.69 26 185.7 17.2
NOTE:
Landing−gear−down configuration. Includes customer options, emergency
equipment and ballast provision.
The maximum baggage load for the aircraft is 1225 kg (2700 lb)
20 kg/passenger (44 lb/passenger).
Hand luggage included.
Calculated with 0.80284 kg/liters ( 6.7 lb/U.S. gallons). All three fuel tanks are
full with 8082 liters (2135 U.S. gallons).
The main fuel tanks are full with 5300 liters (1400 U.S. gallons).
The center fuel tank is full with 2782 liters (735 U.S. gallons).
NOTE:
Example based on CRJ200 ER.
Weight Buildup − 37 Passengers
Figure 1 (Sheet 4)

* Identified as ROW 14 on the aircraft.

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DRY OPERATING INDEX − GENERAL

1. General
A. This section shows how the dry operating index (DOI) is calculated with the index formula
and the correction formula. The example shows an aircraft loaded with 29 passengers
and 2 crew members. There is also a form which can be used to calculate your own data.

2. Example of Calculations
A. The example sheet (shown in Figure 2) shows the input items and the results, in bold
italic, that are calculated with the formulas.
B. To calculate the DOI continue as follows:
(1) Identify the data that follows (refer to Figure 2):
− The item
− The weight of the item
− The center of gravity (XARM) of the item
− The formula type.
(2) Calculate the correct DOI formula type for the item. The correct formula must agree
with your use of SI (metric) or Standard (U.S.) units (refer to Figure 1).
(3) Put the result from the formula in the related index/correction column (refer to Figure
2).
(4) Add the weight of all the items and write the result in (12) of the load and trim sheet
(refer to 01−90−30).
(5) Add the index/correction values for all the items and write the result in (64) of the
load and trim sheet (refer to 01−90−30).

Formula Identification Formula Type Formula

W (XARM − 13.2) + 50
A (SI) Index
280
W (XARM − 520) + 50
A (Standard) Index
23 000
W (XARM − 13.2)
B (SI) Correction
280
W (XARM − 520)
B (Standard) Correction
23 000
NOTE: W is the weight.
XARM is the center of gravity.
Dry Operating Index Formulas
Figure 1

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CENTER OF
INDEX/ FORMULA
ITEM WEIGHT(W) GRAVITY
CORRECTION IDENTIFICATION
(XARM)
kg lb m in. SI Standard
WEIGHED
13 662 30 120 13.49 531.0 64.02 64.41 A
AIRCRAFT
OPERATIONAL ITEMS (IF NOT INCLUDED AT WEIGHING)
FORWARD GALLEY
HALF SIZE EMPTY 68.0 150.0 4.49 176.8 −2.12 −2.24 B
TROLLEYS (4)
FORWARD GALLEY
HALF SIZE EMPTY 34.0 75.0 4.49 176.8 −1.06 −1.12 B
WASTE CARTS (2)
AFT GALLEY HALF
SIZE EMPTY 34.0 75.0 5.94 234.0 −0.88 −0.93 B
TROLLEYS (2)
STANDARD EMPTY
14.0 30.8 6.07 239.0 −0.36 −0.38 B
CONTAINERS (5)
OVEN (2) 53.7 118.4 4.32 170.0 −1.70 −1.80 B
COFFEE BREWER 7.8 17.3 4.65 183.0 −0.24 −0.25 B
TYPICAL CONTENT
OF FORWARD
90.7 200.0 4.49 176.8 −2.82 −2.98 B
GALLEY HALF SIZE
TROLLEY
TYPICAL CONTENT
OF AFT GALLEY
45.4 100.0 5.94 234.0 −1.18 −1.24 B
HALF SIZE
TROLLEY
TYPICAL CONTENT
OF STANDARD 38.6 85.0 6.07 239.0 −0.98 −1.04 B
CONTAINER
Example of Calculations
Figure 2 (Sheet 1)

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CENTER OF
INDEX/ FORMULA
ITEM WEIGHT (W) GRAVITY
CORRECTION IDENTIFICATION
(XARM)
kg lb m in. SI Standard
OPERATIONAL ITEMS (CREW)
PILOT 84.0 185.2 3.23 127.0 −2.99 −3.16 B
COPILOT 84.0 185.2 3.23 127.0 −2.99 −3.16 B
THIRD FLIGHT
CREW 0.0 0.0 3.76 148.0 0.00 0.00 B
(OBSERVER)
FORWARD
84.0 185.2 4.62 182.0 −2.57 −2.72 B
ATTENDANT
AFT ATTENDANT 84.0 185.2 16.31 642.0 0.93 0.98 B
FLIGHT MANUALS 31.8 70.0 3.68 145.0 −1.08 −1.14 B
POTABLE WATER
(FORWARD 18.9 41.7 5.41 213.0 −0.53 −0.56 B
GALLEY)
WASH WATER
18.9 41.7 18.01 709.0 0.32 0.34 B
(AFT LAVATORY)
CHEMICAL TOILET
8.7 19.2 16.76 660.0 0.11 0.12 B
FLUID
UNUSABLE FUEL 44.0 97.0 12.56 494.3 −0.10 −0.11 B
ENGINE OIL 21.3 47.0 19.96 785.7 0.51 0.54 B
ITEMS (ADD OR
SUBTRACT)
B
B
B
CREW BAGGAGE 32.0 70.5 16.89 665.0 0.42 0.44 B
SUBTOTAL 14 546.1 32 068.7 44.71 44.00
DRY OPERATING
14 546.1 32 068.7 44.71 44.00
INDEX
Example of Calculations
Figure 2 (Sheet 2)

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3. Form to Calculate Your Own Data

The form to calculate your own data is shown in Figure 3.

CENTER OF
INDEX/ FORMULA
WEIGHT GRAVITY
ITEM CORRECTION IDENTIFICATION
(XARM)
kg lb m in. SI Standard
WEIGHED AIRCRAFT A
OPERATIONAL ITEMS (IF NOT INCLUDED AT WEIGHING)
FORWARD GALLEY
HALF SIZE EMPTY 4.49 176.8 B
TROLLEYS (4)
FORWARD GALLEY
HALF SIZE EMPTY 4.49 176.8 B
WASTE CARTS (2)
AFT GALLEY HALF
SIZE EMPTY 5.94 234.0 B
TROLLEYS (2)
STANDARD EMPTY
6.07 239.0 B
CONTAINERS (5)
OVEN (2) 4.32 170.0 B
COFFEE BREWER 4.65 183.0 B
TYPICAL CONTENT
OF FORWARD
4.49 176.8 B
GALLEY HALF SIZE
TROLLEY
TYPICAL CONTENT
OF AFT GALLEY 5.94 234.0 B
HALF SIZE TROLLEY
TYPICAL CONTENT
OF STANDARD 6.07 239.0 B
CONTAINER
Form for Calculations
Figure 3 (Sheet 1)

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CENTER OF
INDEX/ FORMULA
ITEM WEIGHT GRAVITY
CORRECTION IDENTIFICATION
(XARM)
kg lb m in. SI Standard
OPERATIONAL ITEMS (CREW)
FORWARD
4.62 182.0 B
ATTENDANT
AFT ATTENDANT 16.31 642.0 B
PILOT 84.0 185.2 3.23 127.0 −2.99 −3.16 B
COPILOT 84.0 185.2 3.23 127.0 −2.99 −3.16 B
THIRD CREW
MEMBER 3.76 148.0
(OBSERVER)
CREW BAGGAGE 16.89 665.0 B
FLIGHT MANUALS 3.68 145.0 B
FLUIDS
POTABLE WATER
5.41 213.0 B
(FORWARD GALLEY)
WASH WATER (AFT
18.01 709.0 B
LAVATORY)
CHEMICAL TOILET
16.76 660.0 B
FLUID
UNUSABLE FUEL 12.56 494.3 B
ENGINE OIL 19.96 785.7 B
SUBTOTAL
ITEMS (ADD OR
SUBTRACT)
B
B
B
DRY OPERATING
INDEX
Form for Calculations
Figure 3 (Sheet 2)

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LOAD AND TRIM SHEET WITH 29 PASSENGERS − GENERAL

1. General
This section gives the necessary data to complete a load and trim sheet and make an analysis
of the results. The load and trim sheet shows if the aircraft has the correct weight and center
of gravity for safe takeoff, flight, and landing conditions.
The example of the load and trim sheet uses a configuration of 29 passengers (refer to
Figure 4). A load and trim sheet form and a fuel curve stencil are given for you to use for the
CRJ Series 200ER (refer to Figure 2 and Figure 5). The load and trim sheet example and form
and the fuel curve stencil are in metric (SI) units. The data represented by the fuel curve
stencil is given in Figure 3.
For CRJ Series 200 LR refer to Figure 3 and Figure 6.

2. Terms and Abbreviations

The specific terms and abbreviations used on the load and trim sheet and are specified in
Figure 1.

TERM/ABBREVIATION DEFINITION
A/C Aircraft
ALLOWED TRAFFIC Weight capacity available for a specific flight sector
LOAD
UNDERLOAD Remaining weight capacity available after the aircraft is
loaded
DEST Destination
DOI Dry Operating Index
REG Registration
TOW Takeoff Weight
MAC Mean Aerodynamic Chord
LDM Load Data Manifest
LMC Last Minute Changes (shortly before departure)
PAX Passenger
CL/CPT Class/Compartment
TR Transit or Trip
B Baggage
C Cargo
M Mail
Terms and Abbreviations
Figure 1

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3. Procedure

WARNING: ONLY AUTHORIZED PERSONS CAN PREPARE THE LOAD AND TRIM SHEET.
AN ERROR IN THE LOAD AND TRIM SHEET CAN GIVE AN INCORRECT
CALCULATED WEIGHT AND CENTER OF GRAVITY. THIS CAN MAKE THE
AIRCRAFT NOT SAFE FOR TAKEOFF, FLIGHT, AND LANDING.
NOTE: The examples in this section is for illustrative purposes and contain references to
the design weights for the CRJ200 ER. This method is also applicable to the
CRJ200 LR. Where appplicable the design weights for the CRJ 200 LR may be
substituted.

A. Given Data
− The maximum weight for the zero fuel weight (MZFW) is given as 19 958 kg (13)
− The maximum weight for landing (MLW) is given as 21 319 kg (14)
− The weight limit for the cargo compartment is given as 1225 kg (65B).

B. Procedure
(1) Write the data for locations (1) to (11) as follows:
(a) The priority and teletype address for the load message (1)
NOTE: This data is optional.
(b) The teletype address of the preparing station (2)
(c) The airline code to charge teletype fees to third parties (3)
NOTE: This data is optional.
(d) The file time of the load message (4)
NOTE: This data is optional.
(e) The initials (5)
NOTE: This data is optional.
(f) The message identifier for the load message (6)
(g) The flight number and date (7)
(h) The aircraft registration (8)
(i) The number of crew members in the flight and passenger compartment (10)
(j) The date this form is written (local time, month in 3−letter code) (11).

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FUEL
WEIGHT (kg)

6488 FULL CENTER

6400
CENTER TANK

6000
5600
5200
4800
4400 4255 FULL MAIN
4000
3600
3200
MAIN TANKS

2800
2400
2000
1600
1200
800
400
0

NOTE
1. The dashed line indicates the
defueling sequence.
2. Refer to the ”FUEL INDEX
CONNECTION TABLE”
for additional data,
section 1−90−30, page 8. rwb0190300_003.dg, gd/kms, 31/03/99

Fuel Curve Stencil

Figure 2

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FUEL INDEX CORRECTION

VOLUME WEIGHT MAIN TANKS CENTER TANK
L Imp. gal U.S. gal kg lb Index SI Index Imp. Index SI Index Imp.
227.0 50.0 60.0 182.0 402.0 −0.76 −0.80 −1.06 −1.12
454.0 100.0 120.0 365.0 804.0 −1.43 −1.51 −2.00 −2.12
681.0 150.0 180.0 547.0 1206.0 −2.04 −2.17 −2.94 −3.12
908.0 200.0 240.0 729.0 1608.0 −2.63 −2.79 −3.89 −4.13
1136.0 250.0 300.0 912.0 2010.0 −3.16 −3.36 −4.85 −5.15
1363.0 300.0 360.0 1094.0 2412.0 −3.66 −3.90 −5.81 −6.17
1590.0 350.0 420.0 1276.0 2814.0 −4.11 −4.38 −6.78 −7.20
1817.0 400.0 480.0 1459.0 3216.0 −4.52 −4.82 −7.75 −8.23
2044.0 450.0 540.0 1641.0 3618.0 −4.88 −5.20 −8.74 −9.28
2271.0 500.0 600.0 1823.0 4020.0 −5.19 −5.54 −9.74 −10.34
2502.0 550.0 661.0 2009.0 4429.0 −5.46 −5.83 −10.88 −11.55
2729.0 600.0 721.0 2191.0 4831.0 −5.68 −6.07 −12.14 −12.89
2782.0 612.0 735.0 2234.0 4925.0 −−− −−− −12.47 −13.24
2956.0 650.0 781.0 2374.0 5233.0 −5.87 −6.28 −−− −−−
3184.0 700.0 841.0 2556.0 5635.0 −6.02 −6.44 −−− −−−
3411.0 750.0 901.0 2738.0 6037.0 −6.16 −6.59 −−− −−−
3638.0 800.0 961.0 2921.0 6439.0 −6.27 −6.72 −−− −−−
3865.0 850.0 1021.0 3103.0 6841.0 −6.33 −6.78 −−− −−−
4092.0 900.0 1081.0 3285.0 7243.0 −6.31 −6.77 −−− −−−
4319.0 950.0 1141.0 3468.0 7645.0 −6.32 −6.78 −−− −−−
4546.0 1000.0 1201.0 3650.0 8047.0 −6.22 −6.68 −−− −−−
4773.0 1050.0 1261.0 3832.0 8449.0 −6.11 −6.57 −−− −−−
5001.0 1100.0 1321.0 4015.0 8851.0 −6.00 −6.46 −−− −−−
5228.0 1150.0 1381.0 4197.0 9253.0 −5.55 −5.99 −−− −−−
5300.0 1166.0 1400.0 4255.0 9380.0 −5.44 −5.88 −−− −−−
Fuel−Curve−Stencil Data Table
Figure 3

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(2) Write and/or calculate the data for locations (12) to (20) as follows:
(a) The dry operating weight (DOW) (12) (refer to 1−90−20)
(b) The takeoff fuel weight (TOF) (15)
(c) The trip fuel weight (TF) (16)
(d) Compare the values in (17A), (17B) and (17C).
NOTE: Use the column that has lowest value from (17A), (17B) and (17C) to
do the next calculations.
(e) Calculate the sum of the DOW (12) and TOF (15). Write the result in operating
weight (19).
(f) Calculate the allowed traffic load as follows:
1 Subtract the operating weight (19) from one of the three values in (17A),
(17B) and (17C). Write the result in allowed traffic load (20).
(3) Write and/or calculate the data for locations (24) to (35) as follows:
(a) The three−letter code of the destination station (for multisector flights) (24)
(b) The number of transit passengers (25)
(c) The total weight of the transit load (26)
(d) The weight of the transit load for each compartment identified as OA, OB, OC,
OD and 1 (27) as follows:
1 Write the load found in compartment 1 under the distribution weight
identified as 1.
NOTE: Loads found in compartment 1 are written under the distribution
weight 1 area.
2 Write the loads found in compartments O under the distribution weight
identified as O.
NOTE: Loads found in the OA, OB, OC and OD compartments are
written under the distribution weight O area.
(e) The number of transit passengers (28)
(f) The total number of new passengers (29)
(g) The total weights for baggage in (30A), cargo in (30B) and mail in (30C)
(h) The weight of the baggage in (31A), cargo in (31B), and mail in (31C) as
follows:
1 Write the load found in compartment 1 under the distribution weight
identified as 1.
NOTE: Loads found in compartment 1 are written under the distribution
weight 1 area.

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2 Write the loads found in compartments O under the distribution weight

identified as O.
NOTE: Loads found in the OA, OB, OC and OD compartments are
written under the distribution weight O area.
(i) The number of new passengers (32)
(j) The total loads for the LDM, if necessary(33)
(k) The total loads for the LDM, if necessary (34)
(l) The total loads for the LDM, if necessary (35).
(4) Write remarks about changes to the load data from 26, 30, 27, 31, 45, and 35 in
location (36).
(5) Calculate the data for locations (37) to (40) as follows:
(a) The total for (37) as follows:
1 Calculate the sum of the number of transit passengers (25) and the
number of new passengers (29).
2 Write the result in (37) as follows:
(b) The total for (38) as follows:
1 Calculate the sum of the weight of the transit load (26) and the total
weights for baggage (B) in (30A), cargo (C) in (30B) and mail (M) in (30C).
2 Write the result in (38).
(c) The total for (39) as follows:
1 Calculate the sum of the weight of the transit load for each compartment
(27) and the weight of the baggage (B) in (31A), the cargo (C) in (31B) and
the mail (M) in (31C).
2 Write the result in (39).
(d) The total for (40) as follows:
1 Calculate the sum of the number of transit passengers (28) and the
number of new passengers (32).
2 Write the result in (40).
(6) Write and/or calculate the data for locations (41) to (51) as follows:
(a) The total passenger weight (41)
(b) Calculate the sum of the total weight for transit, baggage, cargo and mail (38),
and the total passenger weight (41). Write the result in total traffic load (42)
and (21).
(c) The dry operating weight from (12) in (43)
WARNING: MAKE SURE THAT THE ZERO FUEL WEIGHT (ZFW) IS NOT MORE
THAN THE MZFW. IF IT IS, THE AIRCRAFT IS HEAVIER THAN THE
MAXIMUM DESIGN LIMITS AND NOT SAFE FOR TAKEOFF AND
LANDING.
(d) Calculate the sum of the total traffic load (42) and the DOW (43). Write the
result in ZFW (45).
(e) The takeoff fuel (TOF) (46)

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WARNING: MAKE SURE THAT THE TOW IS NOT MORE THAN THE MTOW. IF IT
IS, THE AIRCRAFT IS HEAVIER THAN THE MAXIMUM DESIGN LIMITS
AND NOT SAFE FOR TAKEOFF.
(f) Calculate the sum of the ZFW (45) and the TOF (46). Write the result in
TOW (48).
(g) The trip fuel (TF) (49)

WARNING: MAKE SURE THAT THE LANDING WEIGHT IS NOT MORE THAN THE
MLW. IF IT IS, THE AIRCRAFT IS HEAVIER THAN THE MAXIMUM
DESIGN LIMITS AND NOT SAFE TO LAND.
(h) Calculate the TOW (48) minus the TF(49). Write the result in landing
weight (51).
(7) Write the data for location (52), if necessary.
(8) Write the data for location (22) as follows:
(a) Calculate the allowed traffic load (20) minus the total traffic load (21). Write the
result in underload before LMC (22).
(9) Write any notes for location (23), if necessary, as follows:
(a) Changes to the DOI (64), DOW (12), and passenger configuration (29).
(10) Write the data for locations (53) and (54) as follows:
(a) Printed and signed identification of the weight and balance agent (53)
(b) Printed and signed identification of the agent authorized to approve the load
and trim sheet (54).
(11) The three−letter code of the destination station (55)
(12) Write the specification (56) as follows:
(a) Use one of the load categories to write the change:
1 PAX for passengers
2 B for baggage
3 C for cargo
4 M for mail.
(13) Write the compartment for passengers or load position for baggage (B), cargo (C),
or mail (M) (57).
(14) Write the load category shown as a plus sign (for more load weight) or minus (for
less load weight) in (58).
NOTE: The usual weight of a passenger and baggage is set at 92 kilograms when
the exact number of baggage items cannot be identified.
(a) The total change in weight (with a plus or minus sign) (59)
(b) The weight of TOF adjustment (with a plus or minus sign) (60)
(c) The total weight of the written changes (with a plus or minus sign) (61).

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(15) Write the data for locations (62) to (69) as follows:

(a) The registration number of the aircraft(s) to which this load and trim sheet
applies (62)
(b) The number of flight−compartment crew members (63)
(c) The dry operating index (DOI) (64) (refer to 1−90−20).

WARNING: MAKE SURE THAT THE WEIGHT IN THE CARGO COMPARTMENT IS

NOT MORE THAN 1225 KILOGRAMS (65B) WITH CORRECT FLOOR
LOADING. IF IT IS, THE FLOOR LOADING WILL BE MORE THAN THE
MAXIMUM DESIGN LIMITS FOR THE CARGO COMPARTMENT AND
THE AIRCRAFT MAY NOT BE SAFE FOR OPERATION.
(d) The weight of the cargo in compartment 1 (65A)
(e) The number of passengers in compartment OA (66)
(f) The number of passengers in compartment OB (67)
(g) The number of passengers in compartment OC (68)
(h) The number of passengers in compartment OD (69).
(16) Find the data and trace the related lines for locations (70) to (75) as follows:
(a) Make a mark on the scale (70) at the location that relates to the value from the
DOI (64). Make a vertical line from this point to the middle of the next scale
below (71).
(b) From the line on the scale (71), move to the right to the point that relates to the
weight shown in (65A). Make a vertical line on the scale to the middle of the
next scale below (72).
NOTE: Each division on this scale represents 100kg.
(c) From the line on the scale (72), move to the left to the point that relates to the
number of passengers shown in (66). Make a vertical line on the scale to the
middle of the next scale below (73).
(d) From the line on the scale (73), move to the left to the point that relates to the
number of passengers shown in (67). Make a vertical line on the scale through
the empty scale (74) to the middle of the scale (75).
NOTE: The scale (74) is not used because the loads in the OC division of the
passenger compartment have no important effect on the aircraft
balance.
(e) From the line on the scale (75), move to the right to the point that relates to the
number of passengers shown in (69). Make a vertical line on the scale to the
middle of the next scale below (76).
(17) Trace the %MAC graph reference lines as follows:
(a) Trace the DOI line as follows:
1 From the vertical line in location (76), make a vertical line completely
through the MAC graph (77) to the dry operating index scale (78).

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(b) Trace the ZFW line as follows:

1 Find the point that relates to the ZFW value (45) on the aircraft weight
scale.
NOTE: The aircraft weight scale is on the left side of the graph.
2 Make a horizontal line from this point through the MAC graph (77).

WARNING: THE FUEL CURVE STENCIL MUST NOT BE USED IF THE MAIN FUEL
TANKS ARE NOT SYMMETRICALLY LOADED (REFER TO AMM 12−11−28).
AN INCORRECT FUEL LOAD OR BURN CAN BE DANGEROUS FOR
TAKEOFF, FLIGHT, AND LANDING.
(18) Find and write the data for the aircraft center of gravity (%MAC) at ramp weight as
follows:
(a) Trace the MAC graph curve (77) with the fuel curve stencil as follows (refer to
Figure 2):
NOTE: The position of the center of gravity is shown as a percentage of
the MAC. The maximum permitted range for the weights and
center of gravity values are shown by the loading envelope
pattern.

WARNING: MAKE SURE THAT THE STENCIL REFERENCE LINES ON THE

FUEL CURVE STENCIL ARE PARALLEL TO THE REFERENCE
LINES ON THE GRAPH. IF YOU DO NOT DO THIS, YOU CAN
GET AN INCORRECT CURVE. THE ERROR PRODUCED BY
THIS LINE CAN MAKE THE AIRCRAFT NOT SAFE FOR
TAKEOFF, FLIGHT, AND LANDING.
1 Place the lowest point of the opening from the fuel curve stencil where the
horizontal line for ZFW and the DOI vertical line intersect.
2 Start from the intersection point and make a line up to the related fuel load
that is in the aircraft.
NOTE: The point on the curve that indicates the fuel load on the aircraft
is the %MAC at TOW.
3 Write the value of the %MAC at TOW (79).
(19) Make an analysis of the results (refer to paragraph 4).

4. Make an Analysis of the Result

WARNING: ONLY AUTHORIZED PERSONS CAN MAKE AN ANALYSIS OF THE RESULTS

FROM THE LOAD AND TRIM SHEET. AN ERROR IN THE LOAD AND TRIM
SHEET CAN GIVE AN INCORRECT CALCULATED WEIGHT AND CENTER OF
GRAVITY WHICH MAKES THE AIRCRAFT UNSAFE FOR TAKEOFF, FLIGHT, AND
LANDING.
A. Make an analysis of the results as follows:
(1) Make sure that the fuel curve that you traced fits in the limits of the MAC graph
(aircraft weight related to center of gravity (%MAC)) on the load and trim sheet.

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Area A Forward Limit Curtailment for Zone Loading − Imperial

Zone # Row # Pax Pax Actual Avg Delta Actual Index Delta
CG m CG m CG m Moment Index Esti- Index
mate
A 1 2 253.0
2 2 284.0 268.5 299.5 −23870 −8.42 −7.38 −1.04
3 315.0
4 346.0
B 5 2 377.0
6 2 408.0 392.5 408.0 −11935 −4.27 −3.75 −0.52
7 439.0
C 8 2 471.0
9 2 502.0 486.5 502.0 −11935 −1.12 −0.60 −0.52
10 533.0
D 11 2 564.0
12 595.0 564.0 588.8 −9548 0.74 1.15 −0.42
13 626.0
Total −57288 −13.07 −10.58 −2.49

Weight lb % MAC CG in Moment Moment Moment CG in % MAC

lb−in lb−in lb−in Zone A Zone A
Delta Zone A
30000 11.0 504.7 15141909 57288 15199197 506.6 12.9
32500
34000
36000
37500
40000
42500
45000
47500
50000
52500
53000
53250

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The example of the load and trim sheet uses a configuration of 29 passengers (refer to
Figure 4). A load and trim sheet form and a fuel curve stencil are given for you to use for the
CRJ Series 200ER (refer to Figure 5 and Figure 2). The load and trim sheet example and form
and the fuel curve stencil are in metric (SI) units. The data represented by the fuel curve
stencil is given in Figure 3.
The locations for the data on the load and trim sheet are shown in Figure 4. The data that
follows is given specifically for use with the CRJ Series 200ER aircraft load and trim sheet:
− The aircraft version is given as CRJ Series 200ER (9)
− The maximum allowed weight for the takeoff weight (MTOW) is given as
23 133 kg (17B)
(a) Calculate the sum of MZFW (13) and TOF (15). Write the result in allowed
weight for takeoff in (17A).
(b) Calculate the sum of MLW (14) and TF (16). Write the result in allowed weight
for takeoff (17C).

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R

NOT TO BE UPDATED
1
Load & Trim Sheet − Example
2 3 4 5 6
62

7 8 9 10 11
2

12 14546 13 TAKEOFF
14
15 55 00 15 5 500 + 50 00 PITCH =
Takeoff Fuel +
16 Identified as ROW 14 on aircraft
B 63 64
17A 17B 17C
for Takeoff or
44.7
2 5 4 5 8 2 3 3 3 2 6 3 19 70 10 20 30 40 50 60 70
19 200 4 6 19 2 00 46
= −− 65A
1 5 8 0 71
65B
23 20 30 87
66 7
14
21 67 8
−− 12
3 0 1 6 8
68 74
22 12
7 1 69 6 75
12
DRY OPERATING 76
10 20 30 40 50 60 70
INDEX
26
25 27 28
30A 31A 32 %MAC
29 58 0 580 0 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37
24 29 30B 31B 24
30C 31C 36 23 247 MAX RAMP WEIGHT

33 34 35 23 133 MAX TAKEOFF WEIGHT

77
22

21 319 MAX LANDING WEIGHT

20
19 958 MAX ZERO FUEL WEIGHT
37 29 38 580 39 0 40 79 15.3%
580
41 243 6
42 18
3016 55 56 57 58
43
14 546
44 17 56 2
45
16
Takeoff Fuel 46
AIRCRAFT WEIGHT (x1000 kg)

55 00
TAKEOFF WEIGHT
47
48 2306 2 59
60
49 5 00 0 14
61
13 608 MINIMUM FLIGHT WEIGHT
50
51 18 06 2
53

52 12
54 5 10 20 78 30 40 50 60 70
DRY OPERATING INDEX

DISTRIBUTION: CAPTAIN ORIGINAL + 1. COPY: STATION FILE 2. COPY

rwb0190300_083.dg, pt/jp, 02/12/99 Figure 4 01−90−30 Mar 10/06 Page 13
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NOT TO BE UPDATED
Load & Trim Sheet − Form

TAKEOFF

PITCH =
Takeoff Fuel
Identified as ROW 14 on aircraft
B
for Takeoff or
10 20 30 40 50 60 70

−−
1
1 2 2 5

−− 12

12
DRY OPERATING 10 20 30 40 50 60 70
INDEX

%MAC
7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37
24
23 247 MAX RAMP WEIGHT

23 133 MAX TAKEOFF WEIGHTM

21 319 MAX LANDING WEIGHT

20
19 958 MAX ZERO FUEL WEIGHT

16
Takeoff Fuel
AIRCRAFT WEIGHT (x1000 kg)

TAKEOFF FUEL

−− 14
+/− 13 608 MINIMUM FLIGHT WEIGHT

12
5 10 20 30 40 50 60 70
DRY OPERATING INDEX

DISTRIBUTION: CAPTAIN ORIGINAL + 1. COPY; STATION FILE 2. COPY

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NOT TO BE UPDATED
Load & Trim Sheet − Form
1

TAKEOFF
3 19
PITCH =
Takeoff Fuel
B
for Takeoff or 2 3 9 9 5
10 20 30 40 50 60 70
−−
1
1 2 2 5

−− 12

FUEL INDEX
TRIM UNITS FOR TAKE−OFF 8 7 6 5 4
%MAC 24 154 MAXIMUM RAMP WEIGHT
7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37
24
23 995 MAXIMUM TAKEOFF WEIGHT

21 319 MAXIMUM LANDING WEIGHT

20
19 958 MAXIMUM ZERO FUEL WEIGHT

MAC at ZFW

16
Takeoff Fuel
AIRCRAFT WEIGHT (x 1000 kg)

TAKEOFF FUEL
2 3 9M9 5
−− 14
+/− 13 608 MINIMUM FLIGHT WEIGHT

3 1 9

12
5 10 20 30 40 50 60 70
DRY OPERATING INDEX

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WEIGHT AND BALANCE DIAGRAMS − GENERAL

1. General
The aircraft can be fully loaded with passengers or fully loaded with fuel but it cannot have a
full load of passengers and fuel at the same time. The data for the weight and balance
diagrams is different for each of these load conditions.
The two examples that follow show the data for the weight and balance diagrams when either
the quantity of fuel or the number of passengers is at the permitted limit.

2. Weight and Balance Diagram − Full Load of Fuel

NOTE: The examples in this section is for illustrative purposes and contain references to the
design weights for the CRJ200 ER. This method is also applicable to the CRJ200
LR. Where applicable the design weights for the CRJ 200 LR
The maximum number of passengers that can be loaded in the aircraft under these conditions
is 32 passengers.
The weight buildup sheet is used to calculate the weight and center of gravity of all the loads
in the aircraft. To complete the weight buildup sheet, start with the manufacturer’s weight
empty (MWE) and add the various operational and payload items. Add the weight of the
baggages and the necessary fuel to calculate the ramp weight.
NOTE: See the effectivity on the page for applicable aircraft serial numbers.
The weight buildup sheet shows the weight, the center of gravity (XARM), and the moment of
the aircraft (refer to Figure 1). The weight and balance graph shows the vectors related to the
buildup loads (refer to Figure 2).

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WEIGHT CG (XARM) MOMENT CG

kg lb m in. kg*m/1000 lb*in./1000 %MAC
MANUFACTURER’S
13 662 30 120 13.51 532.0 184.61 16 023.8 38.4
WEIGHT EMPTY
OPERATIONAL ITEMS (CAN BE REMOVED FROM THE GALLEY)
FORWARD GALLEY
HALF SIZE EMPTY 68.0 150.0 4.49 176.8 0.31 26.5
TROLLEYS (4)
FORWARD GALLEY
HALF SIZE EMPTY 34.0 75.0 4.49 176.8 0.15 13.3
WASTE CARTS (2)
AFT GALLEY HALF
SIZE EMPTY 34.0 75.0 5.94 234.0 0.20 17.6
TROLLEYS (2)
STANDARD EMPTY
14.0 30.8 6.07 239.0 0.08 7.4
CONTAINERS (5)
OVEN (2) 53.7 118.4 4.32 170.0 0.23 20.1
COFFEE BREWER 7.8 17.3 4.65 183.0 0.04 3.2
TYPICAL CONTENT
OF FORWARD
90.7 200.0 4.49 176.8 0.41 35.4
GALLEY HALF SIZE
TROLLEY
TYPICAL CONTENT
OF FORWARD
90.7 200.0 4.43 174.4 0.40 34.9
GALLEY HALF SIZE
MEAL CARTS
TYPICAL CONTENT
OF AFT GALLEY 45.4 100.0 5.94 234.0 0.27 23.4
HALF SIZE TROLLEY
TYPICAL CONTENT
OF STANDARD 38.6 85.0 6.07 239.0 0.23 20.3
CONTAINER
Weight Buildup
Full Load of Fuel (21 Passengers) − Data
Figure 1 (Sheet 1)

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WEIGHT CG (XARM) MOMENT CG

kg lb m in. kg*m/1000 lb*in./1000 %MAC
OPERATIONAL ITEMS (CREW)
PILOT 84.0 185.2 3.23 127.0 0.27 23.5
COPILOT 84.0 185.2 3.23 127.0 0.27 23.5
FORWARD
84.0 185.2 4.62 182.0 0.39 33.7
ATTENDANT
AFT ATTENDANT 84.0 185.2 16.31 642.0 1.37 118.9
CREW BAGGAGE 32.0 70.5 16.89 665.0 0.54 46.9
FLIGHT MANUALS 31.8 70.0 3.68 145.0 0.12 10.2

FLUIDS
POTABLE WATER
18.9 41.7 5.41 213.0 0.10 8.9
(FORWARD GALLEY)
WASH WATER
18.9 41.7 18.01 709.0 0.34 29.6
(AFT LAVATORY)
CHEMICAL
8.7 19.2 16.76 660.0 0.15 12.7
TOILET FLUID
UNUSABLE FUEL 44.0 97.0 12.56 494.5 0.55 48.0
ENGINE OIL 21.3 47.0 19.96 785.7 0.43 36.9

Weight Buildup
Full Load of Fuel (21 Passengers) − Data
Figure 1 (Sheet 2)
OPERATING
14 560 32 099 13.12 516.6 191.06 16 584 23.0
WEIGHT EMPTY

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WEIGHT CG (XARM) MOMENT CG

kg lb m in. kg*m/1000 lb*in./1000 %MAC
PAYLOAD ITEMS (PASSENGERS)
SEAT ROW 1
(2 PASSENGERS @ 168.0 370.4 6.43 253.0 1.08 93.7
84 kg (185 lb))
SEAT ROW 2
(2 PASSENGERS @ 168.0 370.4 7.21 284.0 1.21 105.2
84 kg (185 lb))
SEAT ROW 3
(2 PASSENGERS @ 168.0 370.4 8.00 315.0 1.34 116.7
84 kg (185 lb))
SEAT ROW 4
(1 PASSENGERS @ 84.0 185.2 8.79 346.0 0.74 64.1
84 kg (185 lb))
SEAT ROW 5
(2 PASSENGERS @ 168.0 370.4 9.58 377.0 1.61 139.6
84 kg (185 lb))
SEAT ROW 6
(2 PASSENGERS @ 168.0 370.4 10.36 408.0 1.74 151.1
84 kg (185 lb))
SEAT ROW 7
(1 PASSENGERS @ 84.0 185.2 11.15 439.0 0.94 81.3
84 kg (185 lb))
SEAT ROW 8
(1 PASSENGERS @ 84.0 185.2 12.09 476.0 1.02 88.1
84 kg (185 lb))
SEAT ROW 9
(2 PASSENGERS @ 168.0 370.4 12.88 507.0 2.16 187.8
84 kg (185 lb))
SEAT ROW 10
(1 PASSENGERS @ 84.0 185.2 13.67 538.0 1.15 99.6
84 kg (185 lb))
SEAT ROW 11
(2 PASSENGERS @ 168.0 370.4 14.45 569.0 2.43 210.7
84 kg (185 lb))
Weight Buildup
Full Load of Fuel (21 Passengers) − Data
Figure 1 (Sheet 3)

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WEIGHT CG (XARM) MOMENT CG

kg lb m in. kg*m/1000 lb*in./1000 %MAC
SEAT ROW 12
(1 PASSENGERS @ 84.0 185.2 15.24 600.0 1.28 111.1
84 kg (185 lb))
SEAT ROW 13*
(2 PASSENGERS @ 168.0 370.4 16.03 631.0 2.69 233.7
84 kg (185 lb))

BAGGAGE IN AFT
CARGO 420.0 925.9 17.75 698.8 7.45 647.0
COMPARTMENT
FUEL WEIGHT
− MAIN TANKS 4254.8 9380.0 12.84 505.6 54.64 4742.5
− CENTER TANK 2233.9 4925.0 11.64 458.1 25.99 2256.1

RAMP WEIGHT 23 233 51 219 12.85 505.9 298.5 25 912 12.2

NOTE:
Landing−gear−down configuration. Includes customer options, emergency
equipment and ballast provision.
The maximum baggage load for the aircraft is 1225 kg (2700 lb)
20 kg/passenger (44 lb/passenger).
Hand luggage included.
Calculated with 0.80284 kg/liters ( 6.7 lb/U.S. gallons). All three fuel tanks are full
with 8082 liters (2135 U.S. gallons).
The main fuel tanks are full with 5300 liters (1400 U.S. gallons).
The center fuel tank is full with 2782 liters (735 U.S. gallons).

Weight Buildup
Full Load of Fuel (21 Passengers) − Data
Figure 1 (Sheet 4)

3. Weight and Balance Diagram − Full Load of Passengers

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WEIGHT AND BALANCE DIAGRAM EXAMPLE
(FULL FUEL, 21 PASSENGERS)

AIR NOSTRUM
EFFECTIVITY: ALL
% MAC
7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37
24
23 247 kg MAX RAMP WEIGHT

FUEL IN 21 PASSENGERS 23 133 kg MAX TAKEOFF WEIGHT

CENTER TANK BAGGAGE
22

FUEL IN CENTER 21 319 kg MAX LANDING WEIGHT

TANK (OPTIONAL)
20
19 958 kg MAX ZERO FUEL WEIGHT

Figure 2
C

Weight and Balance

FUEL IN MAIN TANK
WEIGHT AND BALANCE MANUAL

21 PASSENGERS

AIRCRAFT WEIGHT (x 1000 kg)

16 FUEL IN

Full Load of Fuel (21 Passengers) − SI Graph

MAIN TANKS

OPERATING BAGGAGE
14 WEIGHT EMPTY

13 608 kg MIN FLIGHT WEIGHT MANUFACTURER’S

01−90−40
WEIGHT EMPTY
OPERATIONAL ITEMS
12

10 20 30 40 50 60 70
rwb0190400_012.dg, pm, 20/02/95

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* Identified as ROW 14 on the aircraft.

The weight buildup sheet is used to calculate the weight and CG of all the loads in the aircraft.
To complete the weight buildup sheet, start with the MWE and add the various operational and
payload items. Add the weight of the baggage and the necessary fuel to calculate the ramp
weight.
The weight buildup sheet shows the weight, center of gravity (XARM), and moment of the
aircraft (refer to Figure 3). The weight and balance graph shows the vectors related to the
buildup loads (refer to Figure 4).

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WEIGHT CG (XARM) MOMENT

kg lb m in. kg*m/1000 lb*in./1000 %MAC
MANUFACTURER’S
13 662 30 120 13.51 532.0 184.61 16 023.8 38.4
WEIGHT EMPTY
OPERATIONAL ITEMS (CAN BE REMOVED FROM THE GALLEY)
FORWARD GALLEY
HALF SIZE EMPTY 68.0 150.0 4.49 176.8 0.31 26.5
TROLLEYS (4)
FORWARD GALLEY
HALF SIZE EMPTY 34.0 75.0 4.49 176.8 0.15 13.3
WASTE CARTS (2)
AFT GALLEY HALF
SIZE EMPTY 34.0 75.0 5.94 234.0 0.20 17.6
TROLLEYS (2)
STANDARD EMPTY
14.0 30.8 6.07 239.0 0.08 7.4
CONTAINERS (5)
OVEN (2) 53.7 118.4 4.32 170.0 0.23 20.1
COFFEE BREWER 7.8 17.3 4.65 183.0 0.04 3.2
TYPICAL CONTENT
OF FORWARD
90.7 200.0 4.49 176.8 0.41 35.4
GALLEY HALF SIZE
TROLLEY
TYPICAL CONTENT
OF AFT GALLEY 45.4 100.0 5.94 234.0 0.27 23.4
HALF SIZE TROLLEY
TYPICAL CONTENT
OF STANDARD 38.6 85.0 6.07 239.0 0.23 20.3
CONTAINER
Weight Buildup
Full Load of Passengers (Partial Load of Fuel) − Data
Figure 3 (Sheet 1)

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WEIGHT CG (XARM) MOMENT

FLUIDS
POTABLE WATER
18.9 41.7 5.41 213.0 0.10 8.9
(FORWARD GALLEY)
WASH WATER
18.9 41.7 18.01 709.0 0.34 29.5
(AFT LAVATORY)
CHEMICAL
8.7 19.2 16.76 660.0 0.15 12.7
TOILET FLUID
UNUSABLE FUEL 44.0 97.0 12.56 494.3 0.55 47.9

OPERATING
14 560 32 099 13.12 516.6 191.06 16 584 23.0
WEIGHT EMPTY
Weight Buildup
Full Load of Passengers (Partial Load of Fuel) − Data
Figure 3 (Sheet 2)

AIR NOSTRUM Page 9

EFFECTIVITY: ALL
01−90−40 Mar 10/06
C
WEIGHT AND BALANCE MANUAL

WEIGHT CG (XARM) MOMENT

kg lb m in. kg*m/1000 lb*in./1000 %MAC
PAYLOAD ITEMS (PASSENGERS)
SEAT ROW 1
(2 PASSENGERS @ 168.0 370.4 6.43 253.0 1.08 93.7
84 kg (185 lb))
SEAT ROW 2
(4 PASSENGERS @ 336.0 740.8 7.21 284.0 2.42 210.4
84 kg (185 lb))
SEAT ROW 3
(4 PASSENGERS @ 336.0 740.8 8.00 315.0 2.69 233.3
84 kg (185 lb))
SEAT ROW 4
(4 PASSENGERS @ 336.0 740.8 8.79 346.0 2.95 256.3
84 kg (185 lb))
SEAT ROW 5
(4 PASSENGERS @ 336.0 740.8 9.58 377.0 3.22 279.3
84 kg (185 lb))
SEAT ROW 6
(4 PASSENGERS @ 336.0 740.8 10.36 408.0 3.48 302.2
84 kg (185 lb))
SEAT ROW 7
(4 PASSENGERS @ 336.0 740.8 11.15 439.0 3.75 325.2
84 kg (185 lb))
SEAT ROW 8
(4 PASSENGERS @ 336.0 740.8 12.09 476.0 4.06 352.6
84 kg (185 lb))
SEAT ROW 9
(4 PASSENGERS @ 336.0 740.8 12.88 507.0 4.33 375.6
84 kg (185 lb))
SEAT ROW 10
(4 PASSENGERS @ 336.0 740.8 13.67 538.0 4.59 398.5
84 kg (185 lb))
SEAT ROW 11
(4 PASSENGERS @ 336.0 740.7 14.45 569.0 4.86 421.5
84 kg (185 lb))
Weight Buildup
Full Load of Passengers (Partial Load of Fuel) − Data
Figure 3 (Sheet 3)

AIR NOSTRUM
Page 10
EFFECTIVITY: ALL
01−90−40 Mar 10/06
C
WEIGHT AND BALANCE MANUAL

WEIGHT CG (XARM) MOMENT

kg lb m in. kg*m/1000 lb*in./1000 %MAC
SEAT ROW 12
(4 PASSENGERS @ 336.0 740.8 15.24 600.0 5.12 444.5
84 kg (185 lb))
SEAT ROW 13*
(4 PASSENGERS @ 336.0 740.8 16.03 631.0 5.39 467.4
84 kg (185 lb))

BAGGAGE IN AFT
CARGO 1000.0 2204.6 17.75 698.8 17.75 1540.6
COMPARTMENT
FUEL WEIGHT
− MAIN TANKS 3487.0 7686.4 12.7 499.8 44.27 3841.3
− CENTER TANK 0.00 0.00 0.00 0.00

RAMP WEIGHT 23 247 51 250 12.95 509.8 301.0 26 126 16.1

Weight Buildup
Full Load of Passengers (Partial Load of Fuel) − Data
Figure 3 (Sheet 4)

* Identified as ROW 14 on the aircraft.

AIR NOSTRUM Page 11

EFFECTIVITY: ALL
01−90−40 Mar 10/06
WEIGHT AND BALANCE DIAGRAM EXAMPLE
(50 PASSENGERS)

AIR NOSTRUM
%MAC

EFFECTIVITY: ALL
7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37

24
23 247 kg MAX RAMP WEIGHT
23 133 kg MAX TAKEOFF WEIGHT
50 PASSENGERS
22

FUEL IN 21 319 kg MAX LANDING WEIGHT

MAIN TANKS
20
19 958 kg MAX ZERO
BAGGAGE FUEL WEIGHT

Figure 4
C

Weight and Balance

50 PASSENGERS
WEIGHT AND BALANCE MANUAL

FUEL IN
MAIN TANKS
16

AIRCRAFT WEIGHT (x 1000 kg)

OPERATING
BAGGAGE
WEIGHT EMPTY

Full Load of Passengers (Partial Load of Fuel) − SI Graph

14
13 608 kg MIN FLIGHT WEIGHT MANUFACTURER’S
WEIGHT EMPTY
OPERATIONAL ITEMS

01−90−40
12

rwb0190400_001.dg, gd/kms, 31/03/99

Page 12
Mar 10/06

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C

WEIGHT AND BALANCE MANUAL

REVISION 11 − TRANSMITTAL LETTER

WEIGHT AND BALANCE MANUAL

123 GARRATT BLVD., DOWNSVIEW, ONTARIO

Copyright© 1994 by Bombardier Inc.

All rights reserved. No part of this work may be reproduced or copied

The Bombardier logo and Canadair are registered

Initial Issue: Sep 30/98

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NOTE: Electronic submissions of MCRs are available on www.racs.bombardier.com Oct 15/2005

Attention: MCR Focal, Technical Publications

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Record the date you insert each revision in your manual.

Rev. Issue Date Rev. Issue Date Rev. Issue Date

BCSG: Bombardier Customer Service Group Page 1

SERVICE BULLETIN LIST

LIST OF EFFECTIVE PAGES

This page is intentionally left blank

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Attention: Director, Technical Publications

5. Units for the WBM

AIR NOSTRUM Page 1

A. Manual Front Matter

(1) Title Page

(2) Record of Revisions

(3) Record of Temporary Revisions

(4) Service Bulletins

B. Chapter Front Matter

(1) Effective Pages

(2) Table of Contents

(3) Aircraft Effectivity

AIR NOSTRUM Page 3

9. Standard Numbering System

01−40−00 Material applicable to the section as a whole

01−40−40 Material applicable to a specific subject of the section

(1) SI to Standard (refer to Figure 1)

FROM: SI MEASUREMENT TO: STANDARD SYSTEM

Linear Conversions − SI to Standard

AIR NOSTRUM Page 5

(2) Standard to SI (refer to Figure 2)

FROM: STANDARD SYSTEM TO: SI MEASUREMENT

(1) SI to Standard (refer to Figure 3)

(2) Standard to SI (refer to Figure 4)

Publication Name/Revision: Media Type: *Chapter/Section/Subject/Task (or) Page Block/Page Number:

Publication Name/Revision: Media Type: *Chapter/Section/Subject/Task (or) Page Block/Page Number:

Publication Name/Revision: Media Type: *Chapter/Section/Subject/Task (or) Page Block/Page Number: