D043U544-GPR1 (747-412/4H6)

747-400BCF GUGGENHEIM AVIATION PARTNERS WEIGHT AND BALANCE CONTROL AND LOADING MANUAL MODEL 747-412/4H6

Boeing Commercial Airplane Group Weight Engineering Organization P.O. Box 3707 Seattle, Washington 98124

Boeing Document No. D043U544-GPR1

WEIGHT AND BALANCE CONTROL AND LOADING MANUAL Guggenheim Aviation Partners

747-400BCF

INTRODUCTION The data presented in this manual are in compliance with Federal Aviation Regulations Part 25, Paragraphs 25.29; 25.471 (b); 25.1519 and 25.1583 (c); and are provided for the purpose of establishing the Model 747-400BCF weight and balance requirements and allowables. This manual presents all the weight and balance information necessary to ensure safe airplane operation. In addition, information is provided to allow the operator to efficiently plan loading procedures in such a manner that maximum payload capability is safely distributed for any type of operation. The Weight and Balance Manual is organized following the guidelines of the Air Transport Association (ATA) Specification No. 100, “Specification for Manufacturers' Technical Data”. Accordingly, the weight and balance data is presented in two chapters.

CHAPTER 1 - CONTROL Control contains all weight and balance data specifically related to the customer aircraft. The data presented in this chapter is modular, with groups of related information provided in discreet subject packages, each of which is uniquely identified by a three element Chapter-Section-Subject number (CHP-SEC-SUB). Major data groupings for the Chapter-Sections are as follows: CHAPTER - SECTION

MAJOR DATA GROUPING

1- 00 through 1- 09

General

1- 20 through 1- 29

Fuel

1- 30 through 1- 39

Fluids

1- 40 through 1- 49

Personnel

1- 60 through 1- 69

Cargo

1- 80 through 1- 89

Ground Operations

1- 90 through 1- 99

Examples

The two digit section (SEC) element allows for ten distinct topics within each major group of data (e.g. 20 through 29 for Fuel). The subject (SUB) element is primarily used to uniquely identify topically identical data for varying aircraft configurations. However, in some cases the subject (SUB) element is used to further subdivide topical information. The Chapter 1 document includes only those topics that apply to the airplanes called out in the “Airplane Configuration” section of the document. The CHP-SEC-SUB number, page numbering, revision date and document number appear on the lower outside corner of each page. Changes within a revised CHP-SEC-SUB are identified with a solid bar in the outside margin, adjacent to the change. The date for the CHP-SEC-SUB will be revised and the changes will be noted in the revision highlights. To determine if you have received a complete document, check each section listed in the “Table of Contents” and confirm that the section is included in this document. The total number of pages for each section is specified at the bottom of every page contained within it (e.g. “Page 1 of 4”, where “4” represents the total number of pages in the section).

APPLICABLE CONFIGURATIONS All

Introduction Page 1 of 2 Mar 2/2005 D043U544-GPR1


747-400BCF

INTRODUCTION (Continued) MANAGING AIRCRAFT CONFIGURATIONS The “Airplane Configuration” section of this document lists all aircraft covered in this document, along with the allowable configurations associated with each aircraft. Restrictions and limitations for each association of a configuration with a specific aircraft serial number are defined in the same section under the heading “Configuration Qualifications”. The data presented within each CHP-SEC-SUB module apply to the aircraft configuration(s) listed in the “Applicable Configurations” box at the bottom of each page. The word “All” signifies that the data is applicable to all configurations listed in the “Airplane Configuration” section of this document, whereas data that is applicable to specific aircraft configurations will list only the appropriate configuration letter(s) in the “Applicable Configurations” box.

DOCUMENT NUMBERING For all 747-400BCF Chapter 1 Manuals, document numbering will use the following convention: D043U5[Y][Z]-[ccc][X] where

[Y] = Minor Model Designator (e.g. “4” for a -400 Minor Model) [Z] = Derivative Designator (0=Passenger, 1=Combi, 2=Freighter, 3=Convertible, 4=Special Freighter) [ccc] = Airline 3-Letter Designator (As per Boeing Standard Designators - CCID) [X] = Document Serial Number (This will always be “1” unless an airline has multiple Weight & Balance Manuals for a given derivative model.)

CHAPTER 2 - AIRCRAFT REPORTS The Aircraft Report (covered in a separate document) contains weight and balance data specifically related to each delivered aircraft of the customer's fleet. The data includes: make, model, serial number, registration identification, actual weighing data, and inventory list for the delivery configuration of each aircraft.

Introduction Page 2 of 2 Mar 2/2005 D043U544-GPR1



747-400BCF

Highlights Revision No: 10 This revision adds cargo tiedown load factors and allowable loads to reflect 2g up load for Serial Number 24066 (RT506) per Master Change 2553MK4170. This requires incorporation of Boeing Service Bulletin 747-25-3473. TABLE OF CONTENTS Updated for this revision.

AIRPLANE CONFIGURATION Assigned Configuration “B” to Serial Number 24066 per Master Change 2553MK4170. Configuration Qualification [11] added.

INTERIOR EFFECTIVITY Updated for this revision.


Revisions Page 1 of 1 Jan 21/2008 D043U544-GPR1


747-400BCF

Highlights Revision No: 9 This revision adds Serial Number 24066 (RT506) which is being transferred from manual D043U540-SIA1 and converted to a freighter per Master Change 0100MK4043. This requires incorporation of Boeing Service Bulletin 747-00-2057. TABLE OF CONTENTS Updated for this revision.

AIRPLANE CONFIGURATION Added Serial Number 24066. Assigned Configuration “A” to Serial Number 24066 per Master Change 0100MK4043. Configuration Qualification [10] added.

INTERIOR EFFECTIVITY Added Serial Number 24066. Added LOPA-747SF-2802 to Serial Number 24066.


Revisions Page 1 of 1 Jan 14/2008 D043U544-GPR1


747-400BCF

Highlights Revision No: 8 This revision adds Serial Number 24405 (RT022) which is being transferred from manual D043U541MAS1 and converted to a freighter per Master Change 0100MK4070. This requires incorporation of Boeing Service Bulletin 747-00-2070. In addition, miscellaneous changes are being made to the manual. Detailed descriptions of the changes to each section are listed below. GENERAL Added Model 4H6 Designation. Added Section 1-02-011 to manual. Added Section 1-20-003 to manual. Added Section 1-24-002 to manual. Added Section 1-30-002 to manual. Added Section 1-86-063 to manual. Added Configuration “E” per Master Change 0100MK4070. Added LOPA-747SF-1001 to Section 1-42-007 per Master Change 0100MK4070.

TITLE PAGE Model changed from 747-412 to 747-412/4H6.

TABLE OF CONTENTS Updated for this revision.

AIRPLANE CONFIGURATION Added Serial Number 24405. Assigned Configuration “E” to Serial Number 24405 per Master Change 0100MK4070. Configuration Qualification [9] added.

INTERIOR EFFECTIVITY Added Serial Number 24405. Added LOPA-747SF-1001. Added LOPA-747SF-1001 to Serial Number 24405.

1-02-011 Applicable Configuration(s) set to “E”.

1-02-900 Changed Applicable Configuration(s) from “All” to “A, B, C, D”.







Revisions Page 1 of 2 Dec 12/2007 D043U544-GPR1


HIGHLIGHTS REVISION NO: 8 (Continued) 1-42-007 Added data for LOPA 747 SF-1001.

1-63-001 Added data referencing TSO-C90.

1-63-021 Added data referencing TSO-C90.

1-63-901 Added data referencing TSO-C90, and added a sentence about non-approved unit load devices.

1-64-201 Changed Applicable Configuration(s) from “D” to “D, E”.

1-64-802 Changed Applicable Configuration(s) from “A, B, C” to “A, B, C, E”.



1-66-802 Changed Applicable Configuration(s) from “A, B, C” to “A, B, C, E”.

1-68-001 Added list of requirements for tying down non-approved unit load devices.

1-68-901 Updated General Information on page 1. Changed Applicable Configuration(s) from “A, C, D” to “A, C, D, E”.

1-68-902 Updated General Information on page 1.



Revisions Page 2 of 2 Dec 12/2007 D043U544-GPR1


747-400BCF


747-400BCF

Highlights Revision No: 7 This revision adds cargo tiedown load factors and allowable loads to reflect 2g up load for Serial Number 24226 (RT507) per Master Change 2553MK4170. This requires incorporation of Boeing Service Bulletin 747-25-3473. TABLE OF CONTENTS Updated for this revision.




Revisions Page 1 of 1 Sep 28/2007 D043U544-GPR1


747-400BCF

Highlights Revision No: 6 This revision adds Serial Number 24226 (RT507) which is being transferred from manual D043U540-SIA1 and converted to a freighter per Master Change 0100MK4043. This requires incorporation of Boeing Service Bulletin 747-00-2063. TABLE OF CONTENTS Updated for this revision.

AIRPLANE CONFIGURATION Removed registry numbers. Added Serial Number 24226. Assigned Configuration “A” to Serial Number 24226 per Master Change 0100MK4043. Configuration Qualification [7] added.





747-400BCF

Highlights Revision No: 5 This revision adds double headed pallet retention data for the forward and aft cargo compartments for Serial Number 27137 (RT520) per Master Change 2553MK4171. This requires incorporation of Boeing Service Bulletin 747-25-3530. In addition, miscellaneous changes are being made to the manual, including renumbering some of the cargo sections. Detailed descriptions of the changes to each section are listed below. GENERAL Added Section 1-64-201 to manual. Added Section 1-64-801 to manual. Added Section 1-66-001 to manual. Added Section 1-66-201 to manual. Added Section 1-66-801 to manual. Added Configuration “D” per Master Change 2553MK4171.


AIRPLANE CONFIGURATION Assigned Configuration “D” to Serial Number 27137 per Master Change 2553MK4171. Configuration Qualification [6] added.


1-20-004 Changed Applicable Configuration(s) from “C” to “C, D”.

1-24-001 Revised fuel tables to equal the usable fuel quantities listed on page 3 of CHP-SEC 1-20-00x.



1-60-001 Section number reference changed from “1-60-04x” to “1-60-40x” and “1-60-06x to 1-60-60x”.

1-60-201 Section number changed from “1-60-021” to “1-60-201” and the section number reference changed from “1-60-

04x” to “1-60-40x” and “1-60-06x to 1-60-60x”.

1-60-401 Section number changed from “1-60-041” to “1-60-401”.






747-400BCF

HIGHLIGHTS REVISION NO: 5 (Continued) 1-62-601 Section number changed from “1-62-061” to “1-62-601”.



10x” to “1-68-90x”.


12x” to “1-64-9xx”.

1-64-201 Applicable Configuration(s) set to “D”.

1-64-202 Section number changed from “1-64-022” to “1-64-202”. Changed Applicable Configuration(s) from “All” to “A, B, C”.






1-66-003 Changed Applicable Configuration(s) from “All” to “A, B, C”.









747-400BCF

HIGHLIGHTS REVISION NO: 5 (Continued) 1-66-901 Section number changed from “1-66-121” to “1-66-901”.

1-68-001 Section number reference changed from “1-60-02x” to “1-60-20x”.


12x” to “1-68-95x” and “1-68-1xx to 1-68-90x”. Changed Applicable Configuration(s) from “A, C” to “A, C, D”.


12x” to “1-68-95x” and “1-68-1xx to 1-68-90x”.


1-69-041 Section number reference changed from “1-60-04x” to “1-60-40x” and “1-60-06x to 1-60-60x”.

1-84-001 Added a note under towing and tipping considerations and added a bullet under tipping considerations.

1-90-001 Revised ordering information.




747-400BCF

Highlights Revision No: 4 This revision adds Serial Number 27137 (RT520) which is being transferred from manual D043U540-SIA1 and converted to a freighter per Master Change 0100MK4043. This requires incorporation of Boeing Service Bulletin 747-00-2034. GENERAL Added Section 1-20-004 to manual. Added Configuration “C” per Master Change 0100MK4043. Added LOPA-747SF-2803 to Section 1-42-007 per Master Change 0100MK4043.


AIRPLANE CONFIGURATION Added Serial Number 27137. Assigned Configuration “C” to Serial Number 27137 per Master Change 0100MK4043. Configuration Qualification [5] added.

INTERIOR EFFECTIVITY Added Serial Number 27137. Added LOPA-747SF-2803. Added LOPA-747SF-2803 to Serial Number 27137.

1-20-001 Changed Applicable Configuration(s) from “All” to “A, B”.

1-20-004 Applicable Configuration(s) set to “C”.

1-42-007 Added data for LOPA 747 SF-2803.

1-68-101 Changed Applicable Configuration(s) from “A” to “A, C”.


Revisions Page 1 of 1 Mar 09/2007 D043U544-GPR1


747-400BCF

Highlights Revision No: 3 This revision adds Serial Number 24975 (RT509) which is being transferred from manual D043U540-SIA1 and converted to a freighter per Master Change 0100MK4043. This requires incorporation of Boeing Service Bulletin 747-00-2029. In addition, cargo tiedown load factors and allowable loads to reflect 2g up load for Serial Number 24975 (RT509) are provided per Master Change 2553MK4170 (requires incorporation of Boeing Service Bulletin 747-25-3473). TABLE OF CONTENTS Updated for this revision.

AIRPLANE CONFIGURATION Added Serial Number 24975. Assigned Configuration “A” to Serial Number 24975 per Master Change 0100MK4043. Assigned Configuration “B” to Serial Number 24975 per Master Change 2553MK4170. Configuration Qualification [3] added. Configuration Qualification [4] added.



Revisions Page 1 of 1 Feb 13/2007 D043U544-GPR1


747-400BCF

Highlights Revision No: 2 This revision adds cargo tiedown load factors and allowable loads to reflect 2g up load for Serial Number 24061 (RT501), per Master Change 2553MK4170. This requires incorporation of Boeing Service Bulletin 747-25-3473. GENERAL Added Section 1-68-102 to manual. Added Configuration “B” per Master Change 2553MK4170.




1-68-101 Changed Applicable Configuration(s) from “All” to “A”.

1-68-102 Applicable Configuration(s) set to “B”.


Revisions Page 1 of 1 Nov 17/2006 D043U544-GPR1


747-400BCF

Highlights Revision No: 1 This revision corrects the crew baggage tiedown allowable loads for the Up restraint direction for Serial Number 24061 (RT501). TABLE OF CONTENTS Updated for this revision.

AIRPLANE CONFIGURATION Updated for this revision.


1-60-001 Corrected kilogram value on page 6.

1-68-101 Corrected crew baggage tiedown fitting allowable loads for Up restraint direction.


Revisions Page 1 of 1 Nov 16/2006 D043U544-GPR1


747-400BCF

Highlights Revision No: Original Release




747-400BCF

TABLE OF CONTENTS TITLE

CHP-SEC-SUB

DATE/PAGE CONFIGURATION

PREFACE INTRODUCTION

3/2/2005 1 2 2 2

All

HIGHLIGHTS REVISION NO: 10 HIGHLIGHTS REVISION NO: 9 HIGHLIGHTS REVISION NO: 8 HIGHLIGHTS REVISION NO: 7 HIGHLIGHTS REVISION NO: 6 HIGHLIGHTS REVISION NO: 5 HIGHLIGHTS REVISION NO: 4 HIGHLIGHTS REVISION NO: 3 HIGHLIGHTS REVISION NO: 2 HIGHLIGHTS REVISION NO: 1 HIGHLIGHTS REVISION NO: ORIGINAL RELEASE

1/21/2008 1/14/2008 12/12/2007 9/28/2007 9/20/2007 9/5/2007 3/9/2007 2/13/2007 11/17/2006 11/16/2006 9/27/2006

All All All All All All All All All All All

AIRPLANE CONFIGURATION

1/21/2008 1 1

All

1/21/2008 1

All

1-00-001

6/27/2005 1 6 6

All

1-00-021

6/27/2005 1

All

1-00-041

6/27/2005 1 1 1 1

All

1-02-001

12/14/2005 1 1 2

All

Chapter 1 - Control Managing Aircraft Configurations Document Numbering Chapter 2 - Aircraft Reports

Configuration Assignment Configuration Qualifications

INTERIOR EFFECTIVITY Upper Cabin

GENERAL GENERAL INFORMATION Weight and Balance Definitions Abbreviations Conversion Factors

AIRPLANE DIMENSIONS General Arrangement and Primary Dimensions

BALANCE REFERENCE SYSTEM Balance Arms / Body Stations Mean Aerodynamic Chord Body Buttock Line Water Line

FACTORS AFFECTING PERFORMANCE AND OPERATIONAL LIMITATIONS Interpolation of Certified Center of Gravity Limits Operational Weight and Center of Gravity Requirements Commonwealth of Independent States (CIS) Requirements


Table of Contents Page 1 of 8 Jan 21/2008 D043U544-GPR1

747-400BCF


TABLE OF CONTENTS (Continued) TITLE

CHP-SEC-SUB

CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS

1-02-011

3/21/2007 1 1 2 3

E

1-02-900

4/25/2006 1 1 3 4 5 6 7 8

A, B, C, D

1-04-001

6/27/2005 1 2 3

All

1-05-001

4/20/2006 1 1 2

All

1-06-001

6/27/2005 1 2 3 4

All

1-08-001

6/27/2005 1 1

All

1-20-001

6/27/2005 1 2 3 4

A, B

1-20-003

4/20/2006 1 2 3 4

E

Certified Weight Limits - MTW 873000 LB (395986 KG) Limitations C.G. Limits - MTW 873000 LB, MLW 652000 LB, MZFW 610000 LB C.G. Limits - MTW 395986 KG, MLW 295742 KG, MZFW 276691 KG

CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS Certified Weight Limits - MTW 873000 LB (395986 KG) Limitations C.G. Limits - MTW 873000 LB, MLW 652000 LB, MZFW 610000 LB C.G. Limits - MTW 395986 KG, MLW 295742 KG, MZFW 276691 KG C.G. Limits - MTW 873000 LB, MLW 652000 LB, MZFW 610000 LB C.G. Limits - MTW 395986 KG, MLW 295742 KG, MZFW 276691 KG C.G. Limits - MTW 873000 LB, MLW 652000 LB, MZFW 610000 LB C.G. Limits - MTW 395986 KG, MLW 295742 KG, MZFW 276691 KG

AIRPLANE LATERAL IMBALANCE LIMITS Lateral Imbalance Lateral Imbalance Limitations (Pounds) Lateral Imbalance Limitations (Kilograms)

AIRPLANE GROSS WEIGHT VERSUS FUEL DENSITY LIMITATION Fuel Density Limitations Fuel Density Limitations (Pounds) Fuel Density Limitations (Kilograms)

TAKEOFF HORIZONTAL STABILIZER TRIM SETTING English Units - Multiple Green Band Metric Units - Multiple Green Band English Units - Multiple Green Band Metric Units - Multiple Green Band

LANDING GEAR AND FLAP MOVEMENT BALANCE EFFECT


Landing Gear Retraction Moment Flaps Retraction Moment

FUEL FUEL TANK ARRANGEMENT AND CAPACITIES Fuel Tank Locations Maximum Allowable Fuel Weight Usable Fuel Quantities and Locations Unusable Fuel Quantities and Locations

FUEL TANK ARRANGEMENT AND CAPACITIES Fuel Tank Locations Maximum Allowable Fuel Weight Usable Fuel Quantities and Locations Unusable Fuel Quantities and Locations




747-400BCF


CHP-SEC-SUB

FUEL TANK ARRANGEMENT AND CAPACITIES

1-20-004

3/9/2007 1 2 3 4

C, D

1-22-001

9/27/2006 1 1 5 6 10

All

1-24-001

8/27/2007 1 3 5 9

A, B, C, D

1-24-002

8/23/2007 1 3 5 9

E

1-24-011

8/23/2007 1 2

All

1-24-021

8/23/2007 1 4

All

1-30-002

4/20/2006 1 1 2 2 2

E

1-30-003

4/25/2006 1 1 2 2 2

A, B, C, D

Fuel Tank Locations Maximum Allowable Fuel Weight Usable Fuel Quantities and Locations Unusable Fuel Quantities and Locations

FUEL MANAGEMENT Airplane Configuration Fuel Loading Procedures Lateral Fuel Imbalance Fuel Usage Procedures APU Fuel Usage

FUEL TANK QUANTITIES AND BALANCE ARMS Combined Main Tanks 1 And 4 in U.S. Gallons Combined Main Tanks 1 And 4 in Liters Combined Main Tanks 2 And 3 in U.S. Gallons Combined Main Tanks 2 And 3 in Liters

FUEL TANK QUANTITIES AND BALANCE ARMS Combined Main Tanks 1 And 4 in U.S. Gallons Combined Main Tanks 1 And 4 in Liters Combined Main Tanks 2 And 3 in U.S. Gallons Combined Main Tanks 2 And 3 in Liters

FUEL TANK QUANTITIES AND BALANCE ARMS Combined Reserve Tanks 2 & 3 in U.S. Gallons Combined Reserve Tanks 2 & 3 in Liters

FUEL QUANTITIES AND BALANCE ARMS - CENTER TANK


Center Tanks in U.S. Gallons Center Tank in Liters

FLUIDS SYSTEM FLUIDS Engine System Oil (GEneral Electric CF6-80C2 Engines) Integrated Drive Generator Oil Hydraulic System Fluid Landing Gear System Fluid Operating System Fluid

SYSTEM FLUIDS Engine System Oil (Pratt & Whitney PW400 Engines) Integrated Drive Generator Oil Hydraulic System Fluid Landing Gear System Fluid Operating System Fluid



747-400BCF



CHP-SEC-SUB

POTABLE WATER SYSTEM

1-32-001

6/27/2005 1

All

1-34-001

6/27/2005 1

All

1-40-001

12/21/2005 1

All

1-42-007

12/11/2007 1 2 3 4

All

1-60-001

7/9/2007 1 3 4 5 6

All

1-60-201

7/9/2007 1 2

All

1-60-401

7/9/2007 1

All

1-60-601

7/9/2007 1

All

1-62-001

7/20/2006 1

All

1-62-401

7/9/2007 1 1 2

All

1-62-601

7/9/2007 1 1 2

All

Tank Quantities and Locations

WASTE DISPOSAL SYSTEM


Tank Quantities and Locations

PERSONNEL CREW, OCCUPANT, AND BAGGAGE WEIGHT ALLOWANCES FAA Advisory Circular 120-27E Allowances

INTERIOR ARRANGEMENT - UPPER DECK Flight Deck Upper Cabin - 14C Arrangement (Zero Occupancy) Upper Cabin - 8C Arrangement (Zero Occupancy) Upper Cabin - 8C Arrangement

CARGO CARGO COMPARTMENT LOAD LIMITS Maximum Allowable Weights Maximum Combined Linear Load Limits Main Deck Unsymmetrical Payload - Linear Load Limits Main Deck Centerline Load Limits Allowable main deck running load versus center wing tank fuel

CERTIFIED UNIT LOAD DEVICE WEIGHTS BY POSITION Unit Load Device Positions - Lower Deck Unit Load Device Positions - Main Deck

FORWARD BODY CUMULATIVE LOADS Cumulative Load Check

AFT BODY CUMULATIVE LOADS Cumulative Load Check

CARGO COMPARTMENTS General Location and Arrangement

FORWARD CARGO COMPARTMENTS Forward Cargo Compartment Volumes Forward Cargo Compartment Cross Sections Cargo Door Dimensions and Allowable Package Sizes

AFT CARGO COMPARTMENTS Aft Cargo Compartment Volumes Aft Cargo Compartment Cross Sections Cargo Door Dimensions and Allowable Package Sizes




747-400BCF


CHP-SEC-SUB

BULK CARGO COMPARTMENT

1-62-801

7/9/2007 1 2 4

All

1-62-901

7/9/2007 1 2

All

1-63-001

12/5/2007 1 2 3

All

1-63-021

12/5/2007 1 2 3

All

1-63-901

12/12/2007 1 1 3

All

1-64-001

6/27/2005 1 2

All

1-64-201

7/9/2007 1 2

D, E

1-64-202

7/9/2007 1

A, B, C

1-64-601

7/9/2007 1 2

All

1-64-801

7/9/2007 1 2

D

1-64-802

7/9/2007 1 2

A, B, C, E

Bulk Cargo Compartment Volume Bulk Cargo Compartment Cross Sections Cargo Door Dimensions and Allowable Package Sizes

MAIN DECK CARGO COMPARTMENT Main Deck Cargo Compartment Volume Main Deck Cargo Door Dimensions and Allowable Package Sizes

UNIT LOAD DEVICES - LOWER DECK Size Codes K, L, & P Volumes and Center of Gravity Limits Dimensions and Lateral Positions

UNIT LOAD DEVICES - LOWER DECK Size Codes A, M & N Volumes and Center of Gravity Limits Dimensions and Lateral Positions

UNIT LOAD DEVICES - MAIN DECK Size Codes A, B, F, G, M & R Volumes and Center of Gravity Limits Dimensions and Lateral Positions

FORWARD COMPARTMENT UNIT LOAD DEVICE LOCATIONS Size Codes K & L Size Code P

FORWARD COMPARTMENT UNIT LOAD DEVICE LOCATIONS Size Code A Size Codes M & N

FORWARD COMPARTMENT UNIT LOAD DEVICE LOCATIONS Size Code A

AFT COMPARTMENT UNIT LOAD DEVICE LOCATIONS Size Codes K & L Size Code P

AFT COMPARTMENT UNIT LOAD DEVICE LOCATIONS Size Code A Size Codes M & N

AFT COMPARTMENT UNIT LOAD DEVICE LOCATIONS Size Code A Size Codes M & N




747-400BCF



CHP-SEC-SUB

MAIN DECK UNIT LOAD DEVICE LOCATIONS

1-64-901

7/9/2007 1 4

All

1-66-001

6/27/2005 1 2

D, E

1-66-003

4/25/2006 1 2

A, B, C

1-66-201

7/9/2007 1 2

D, E

1-66-202

7/9/2007 1 2

A, B, C

1-66-601

7/9/2007 1 2

All

1-66-801

7/9/2007 1 2

D

1-66-802

7/9/2007 1 2

A, B, C, E

1-66-901

7/9/2007 1

All

1-68-001

12/5/2007 1 2 12 13

All

1-68-041

6/27/2005 1

All

1-68-061

6/27/2005 1

All

1-68-081

7/20/2006 1

All

General Main Deck Unit Load Devices

FORWARD COMPARTMENT UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size Codes K, L, & P Load Limits - Size Codes K, L, & P

FORWARD COMPARTMENT UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size Codes K, L, & P Load Limits - Size Codes K, L, & P

FORWARD COMPARTMENT UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size Codes A, M, & N Double Locks Load Limits - Size Codes A, M, & N Double Locks

FORWARD COMPARTMENT UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size CodeS A, M, & N Single Locks Load Limits - Size CodeS A, M, & N Single Locks

AFT COMPARTMENT UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size Codes K, L, & P Load Limits - Size Codes K, L, & P

AFT COMPARTMENT UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size Codes A, M, & N Double Locks Load Limits - Size Codes A, M, & N Double Locks

AFT COMPARTMENT UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size Codes A, M, & N Single Locks Load Limits - Size Codes A, M, & N Single Locks

MAIN DECK UNIT LOAD DEVICE LOAD LIMITS Cargo Restraint System - Size Codes A, B & M

CARGO TIEDOWNS - LOWER DECK General Information Tiedown Allowables Tiedown Calculation Tiedown Example

TIEDOWN FITTING LOCATIONS - FORWARD COMPARTMENTS Fitting Locations

TIEDOWN FITTING LOCATIONS - AFT COMPARTMENTS Fitting Locations

TIEDOWN FITTING LOCATIONS - AFT COMPARTMENTS Fitting Locations





747-400BCF


CHP-SEC-SUB

CARGO TIEDOWNS - MAIN DECK

1-68-901

12/5/2007 1 2 11

A, C, D, E

1-68-902

12/5/2007 1 2 13

B

1-68-951

7/9/2007 1

All

1-69-001

6/27/2005 1 2 3 3 4

All

1-69-021

6/27/2005 1 2 2

All

1-69-041

7/9/2007 1 2

All

1-69-121

6/23/2006 1 2 8 12

All

1-80-001

6/27/2005 1 2 3

All

General Information Tiedown Allowables Tiedown Calculation

CARGO TIEDOWNS - MAIN DECK General Information Tiedown Allowables Tiedown Calculation

TIEDOWN FITTING LOCATIONS - MAIN DECK Fitting Locations

CARGO LATERAL IMBALANCE CONTROL Procedure for Calculation of Imbalance Lower Deck Main Deck Operator Convenience Sample Problem

INCREASED UNIT LOAD DEVICE LOAD LIMITS - SIZE CODES A & M Unit Load Device Load Limits Unit Load Device Load Limits (Pounds) Unit Load Device Load Limits (Kilograms)

NON-APPROVED UNIT LOAD DEVICES - LOWER HOLDS Size Codes A, K, L, M & P Maximum Allowable Load

TALL RIGID CARGO


Introduction Load Plan Calculation Sample Problem No. 1 Sample Problem No. 2

GROUND OPERATIONS AIRPLANE JACKING Jack Point Locations Maximum Allowable Jacking Loads Limitations Envelopes



747-400BCF



CHP-SEC-SUB

AIRPLANE WEIGHING PROCEDURE

1-82-001

12/14/2005 1 1 1 2 3 3 5

All

1-84-001

8/23/2007 1 1 1 3 4

All

1-86-001

6/27/2005 1

All

1-86-011

6/27/2005 1

All

1-86-021

6/27/2005 1

All

1-86-031

6/27/2005 1

All

1-86-041

6/27/2005 1 2

All

1-86-051

6/27/2005 1

All

1-86-062

4/25/2006 1

A, B, C, D

1-86-063

4/20/2006 1

E

1-90-001

4/12/2007 1 2

All

General Information Weighing Facilities and Equipment Preparation for Airplane Weighing Weighing Operation Weighing Procedure Using Platform Scales Weighing Procedure Using Electronic Load Cells Non-Level Weighing

TOWING AND TIPPING LIMITATIONS Towing and Tipping Considerations Towing Considerations Tipping Considerations Towing and Tipping Limits (English) Towing and Tipping Limits (Metric)

COMPONENT WEIGHTS AND BALANCE ARMS Wing Components

COMPONENT WEIGHTS AND BALANCE ARMS Horizontal Stabilizer Components

COMPONENT WEIGHTS AND BALANCE ARMS Vertical Fin Components

COMPONENT WEIGHTS AND BALANCE ARMS Body Components

COMPONENT WEIGHTS AND BALANCE ARMS Main Gear Components - Body Gear Main Gear Components - Wing Gear

COMPONENT WEIGHTS AND BALANCE ARMS Nose Gear Components

COMPONENT WEIGHTS AND BALANCE ARMS Nacelle And Power plant Components

COMPONENT WEIGHTS AND BALANCE ARMS


Nacelle And Power plant Components

EXAMPLES LOADING SCHEDULE DEVELOPMENT Introduction Ordering Instructions



747-400BCF


AIRPLANE CONFIGURATION The engineering data and FAA certification provided by this document are applicable and valid only for the airplane as defined in the Type Design at delivery, and as modified by the incorporation of any Boeing Supplemental Type Certificate (STC) or Service Bulletin. With respect to any third party STC configuration, either pre-delivery or post-delivery, it shall be the responsibility of the buyer to obtain the data and appropriate regulatory agency approval.

CONFIGURATION ASSIGNMENT The table shown below correlates each airplane serial number to the currently allowed configuration(s) for that airplane. Each configuration is designated by a different letter. Configuration qualifications are listed following the table and indicate the change authorization involved for airplanes with multiple allowable configurations. Because there may be multiple configuration letters applicable to any serial number, and also multiple configuration qualifications listed for any configuration letter, care should be exercised when determining the configuration letter which correctly reflects the applicable configuration of the airplane. LINE NUMBER

SERIAL NUMBER

VARIABLE NUMBER

CONFIGURATION

717

24061

RT501

A[1]

B[2]

791

24066

RT506

A[10]

B[11]

809

24226

RT507

A[7]

B[8]

745

24405

RT022

E[9]

838

24975

RT509

A[3]

B[4]

990

27137

RT520

C[5]

D[6]

CONFIGURATION QUALIFICATIONS [1] Upon incorporation of Boeing Service Bulletin 747-00-2001 (Administrative General - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Passenger Airplane to a 747-400 Special Freighter (SF) Airplane - Collector Service Bulletin). Note: for FAA certification. [2] Upon incorporation of both Boeing Service Bulletin 747-00-2001 and Boeing Service Bulletin 747-253473 (Equipment/Furnishings - Containerized Cargo Compartments - Weight and Balance Manual Revision). Note: for EASA certification. [3] Upon incorporation of Boeing Service Bulletin 747-00-2029 (Administrative General - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Passenger Airplane to a 747-400 Special Freighter (SF) Airplane - Collector Service Bulletin). Note: for FAA certification. [4] Upon incorporation of both Boeing Service Bulletin 747-00-2029 and Boeing Service Bulletin 747-253473. Note: for EASA certification. [5] Upon incorporation of Boeing Service Bulletin 747-00-2034 (Administrative General - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Passenger Airplane to a 747-400 Special Freighter (SF) Airplane - Collector Service Bulletin). Note: for FAA certification. [6] Upon incorporation of Boeing Service Bulletin 747-00-2034 and Boeing Service Bulletin 747-25-3530 (Equipment/Furnishings - Containerized Cargo Compartments - Change Forward and Aft Cargo Floor Restraint Configurations). APPLICABLE CONFIGURATIONS All

Airplane Configuration Page 1 of 2 Jan 21/2008 D043U544-GPR1


747-400BCF

AIRPLANE CONFIGURATION (Continued) [7] Upon incorporation of Boeing Service Bulletin 747-00-2063 (Administrative General - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Passenger Airplane to a 747-400 Special Freighter (SF) Airplane - Collector Service Bulletin). Note: for FAA certification. [8] Upon incorporation of Boeing Service Bulletin 747-00-2063 and Boeing Service Bulletin 747-25-3473. Note: for EASA certification. [9] Upon incorporation of Boeing Service Bulletin 747-00-2070 (Administrative General - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Combi Airplane to a 747-400 Special Freighter (SF) Airplane - Collector Service Bulletin). [10] Upon incorporation of Boeing Service Bulletin 747-00-2057 (Administrative General - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Passenger Airplane to a 747-400 BCF Airplane - Collector Service Bulletin). Note: for FAA certification. [11] Upon incorporation of Boeing Service Bulletin 747-00-2057 and Boeing Service Bulletin 747-25-3473. Note: for EASA certification.

Airplane Configuration Page 2 of 2 Jan 21/2008 D043U544-GPR1


747-400BCF


INTERIOR EFFECTIVITY The tabular data shown below correlates each airplane serial number to the passenger arrangement(s) certified for that airplane. Each passenger arrangement is designated by drawing number and revision letter. To locate a particular passenger arrangement(s), refer to the interior section listed below. Drawing numbers are listed beside each interior drawing in the interior section.

UPPER CABIN Weight and balance data for each drawing identified in the following table are provided in Section 1-42-007 of this manual.

-

24066

LOPA-747SF-2802

-

24226

LOPA-747SF-2802

-

24405

LOPA-747SF-1001

-

24975

LOPA-747SF-2802

-

27137

LOPA-747SF-2803

-


DRAWING #

REV

LOPA-747SF-2802

DRAWING #

REV

24061

DRAWING #

REV

DRAWING #

REV

PASSENGER ARRANGEMENT EFFECTIVITY - UPPER CABIN

SERIAL NUMBER

Interior Effectivity Page 1 of 1 Jan 21/2008 D043U544-GPR1


747-400BCF

GENERAL INFORMATION WEIGHT AND BALANCE DEFINITIONS The following definitions are provided to assist operators in having a better understanding of the terms used throughout the Weight and Balance Manual.

General Terms and Acronyms Balance Arm (B.A.)

A true measure of distance from foward to aft, in inches, from a fixed datum. The fixed datum is selected by the airplane manufacturer. Balance Arms are used in weight and balance calculations. To see the relationship between B.A. and B.S., refer to CHP-SEC-SUB 100-04x of this manual.

Body Station (B.S.)

A manufacturing location on the airplane. For first of an airplane model, B.S. are continuous from the front to the aft of the airplane. For later versions that are either stretched (i.e. fuselage inserts added) or shrunk (i.e. fuselage sections removed), B.S. becomes discontinuous, for manufacturing reasons. To see the relationship between B.A. and B.S., refer to CHP-SEC-SUB 1-00-04x of this manual.

Layout of Passenger Arrangement A Boeing internal drawing the depicts the interior layout. (LOPA) Layout of Passenger Systems (LOPS)

A Boeing internal drawing that depicts the interior layout.

Weight Terms Basic Empty Weight (BEW)

Standard Basic Empty Weight plus or minus weight of standard item variations.

Delivery Empty Weight (DEW)

Manufacturer's Empty Weight, less any shortages, plus those standard items and operational items in aircraft at time of delivery.

Fleet Empty Weight (FEW)

Average Basic Empty Weight used for a fleet or group of aircraft of the same model and configuration. (The weight of any fleet member shall not vary more than the tolerance established by government regulations.)

Guaranteed Weight

Weight the manufacturer clearly defines and guarantees, subject to contractual tolerances and adjustments.

Manufacturer's Empty Weight (MEW)

Weight of structure, powerplant, furnishings, systems and other items of equipment that are an integral part of a particular aircraft configuration. (It is essentially a “dry” weight, including only those fluids contained in closed systems.)

Maximum Payload

Maximum Zero Fuel Weight minus Operational Empty Weight.

Operational Empty Weight (OEW)

Basic Empty Weight or Fleet Empty Weight plus operational items.


1-00-001 Page 1 of 6 Jun 27/2005 D043U544-GPR1


747-400BCF

GENERAL INFORMATION (Continued) Operational Items

Personnel, equipment and supplies necessary for a particular operation but not included in Basic Empty Weight. These items may vary for a particular aircraft and may include, but are not limited to, the following:

Crew and Baggage

Manuals and navigational equipment

Removable service equipment for cabin and galley

Food and beverage

Usable fluids other than those in useful load

Life rafts, life vests and emergency transmitters

Aircraft unit load devices

Operational Landing Weight (OLW)

Maximum authorized weight for landing. (It is subject to airport, operational and related restrictions. It must not exceed maximum certified landing weight.)

Operational Takeoff Weight (OTOW)

Maximum authorized weight for takeoff. (It is subject to airport, operational and related restrictions. This is the weight at start of takeoff run and must not exceed maximum certified takeoff weight.)

Payload

Weight of the cargo.

Standard Basic Empty Weight (SBEW)

Manufacturer's Empty Weight plus standard items.

Standard Items

Equipment and fluids not considered an integral part of a particular aircraft and not a variation for the same type of aircraft. These items may include, but are not limited to, the following:

Unusable fuel and other unusable fluids

Engine oil

Toilet fluid and chemical

Fire extinguishers, pyrotechnics and emergency oxygen equipment

Structure in galley

Supplementary electronic equipment

Useful Load

Difference between takeoff weight and Operational Empty Weight. (It includes payload, usable fuel and other usable fluids not included as operational items.)

Zero Fuel Weight

Operational Empty Weight plus payload. (This weight must not exceed Maximum Zero Fuel Weight.)

1-00-001 Page 2 of 6 Jun 27/2005 D043U544-GPR1



747-400BCF

GENERAL INFORMATION (Continued) Weight Limitation Terms Maximum Fuel Transfer Weight (MFTW)

The weight above which Reserve Tanks 2 and 3 must be full.

Maximum Landing Weight (MLW)

Maximum weight for landing as limited by aircraft strength and airworthiness requirements.

Maximum Takeoff Weight (MTOW)

Maximum weight at brake release as limited by aircraft strength and airworthiness requirements.

Maximum Taxi Weight (MTW)

Maximum weight for ground maneuver as limited by aircraft strength and airworthiness requirements. (It includes weight of taxi and runup fuel.)

Maximum Zero Fuel Weight (MZFW)

Maximum weight allowed before usable fuel must be loaded in the aircraft as limited by strength and airworthiness requirements.

Minimum Flight Weight (MFW)

Minimum weight for flight as limited by aircraft strength and airworthiness requirements.

Fuel Terms Unusable Fuel

Fuel remaining after a fuel runout test has been completed in accordance with government regulations. (It includes drainable unusable fuel plus unusable portion of trapped fuel.)

Drainable Unusable Fuel

Unusable fuel minus unusable portion of trapped fuel.

Trapped Unusable Fuel

Unusable fuel remaining when aircraft is defueled by normal means using the procedures and attitudes specified for draining the tanks.

Usable Fuel

Fuel available for aircraft propulsion.

Drainable Usable Fuel

Usable fuel that can be drained from the aircraft by normal means using the procedures and attitudes specified for draining the tanks.

Trapped Usable Fuel

Usable fuel remaining in the fuel feed and engine lines after standard tank defueling.

Curtailments Cargo Location Variation

Operational margin placed within the certified center of gravity limits to compensate for the effect of reasonable variations in cargo location when partially unrestricted cargo placement is permitted.

Fuel Density Variation

Operational margin placed within the certified center of gravity limits to compensate for the effect of fuel density variation.

Fuel Usage

Operational margin placed within the certified center of gravity limits to compensate for the effect of fuel management during the critical portions of flight.


1-00-001 Page 3 of 6 Jun 27/2005 D043U544-GPR1


747-400BCF

GENERAL INFORMATION (Continued) In-flight Movement

Operational margin placed within the certified center of gravity limits to compensate for the effect of reasonable crew movement during flight.

Loading Schedule

A hardcopy or computerized form used to record the aircraft’s weight, load distribution and other appropriate information; to calculate and check the weight and balance conditions of the aircraft against operational limitations; and to establish the stabilizer trim setting for takeoff.

Operational Empty Weight Variation

Operational margin placed within the certified center of gravity limits to compensate for the known variations in the standard and operational items.

Seating Variation

Operational margin placed within the certified center of gravity limits to compensate for the effect of reasonable variations in crew center of gravity when unrestricted seating is permitted.

Balance Terms Fleet Center-of-Gravity

Average Basic Empty Weight center of gravity used for a fleet or group of aircraft of the same model and configuration. (The center of gravity of any fleet member shall not vary more than the maximum tolerance established by government regulations.)

Lateral Imbalance

The offset of the airplane center of gravity from the airplane centerline. It is usually expressed as a moment (LB-IN. or KG-IN.) about the airplane centerline.

Cargo Terms and Definitions Approved ULD

A unit load device that has been manufactured in accordance to and received approval by the appropriate governmental airworthiness authority indicating the airplane ULD meets their safety requirements.

Container

A rigid structure that performs the function of a ULD without the use of a restraining net.

Frangible Cargo

Cargo consisting of items which will progressively conform to the airplane contour when subjected to loads up to limit load.

g

The expression used to show the magnitude of a force in terms of the standard earth gravitational unit.

Igloo

A bottomless rigid shell made of fiberglass, metal or other suitable material. Its shape conforms to the contours of cargo aircraft envelopes. It covers the maximum usable area of an aircraft pallet to which it is secured during flight.

1-00-001 Page 4 of 6 Jun 27/2005 D043U544-GPR1



747-400BCF

GENERAL INFORMATION (Continued) Limit Loads

Limit loads are the maximum loads to be expected in service. Limit loads must be supported without detrimental permanent deformation or interference with safe operation.

NAS 3610

A document which defines test conditions for approval of ULDs per TSO-C90c.

Non-Approved ULD

A unit load device that has not received approval by the appropriate governmental airworthiness authority indicating the airplane ULD meets their safety requirements.

Pallet

An item of equipment consisting of a flat platform with a flat undersurface of standard dimensions on which goods are assembled and secured before being loaded as a unit onto the airplane.

Rigid Cargo

Cargo consisting of an item or items which will not progressively conform to the airplane contour when subjected to loads up to limit load. Examples include machine tools, pipes, large motors or generators, etc.

Tiedown Fitting

An attachment device designed to transfer forces between a load bearing device (typically a net, strap, rope or bar) and a cargo track.

TSO-C90c

Technical Standard Order for the approval of ULDs. NAS 3610 is the minimum performance standard.

ULD

Unit Load Device. An assembly of components comprising either of the following: aircraft pallet and pallet net, straps, igloo aircraft container The purpose of the unit load device is to enable individual pieces of cargo to be assembled into a standardized sized unit to facilitate rapid loading/unloading onto aircraft having compatible handling and restraint systems which interface directly with the unit.

ULD Position

A volume in the cargo compartment which is designated and equipped to be occupied, during flight, by a ULD of specified type.

Ultimate Load

Ultimate loads are limit loads multiplied by prescribed factors of safety.


1-00-001 Page 5 of 6 Jun 27/2005 D043U544-GPR1

747-400BCF


GENERAL INFORMATION (Continued) ABBREVIATIONS The following terms, when necessary, will be abbreviated as shown below. UNIT

ABBREVIATION

UNIT

ABBREVIATION

Pounds

LB

Inches

IN.

Kilograms

KG

Feet

FT

U. S. Gallons

U.S. GAL.

Square Feet

SQ FT

Liters

L

Cubic Feet

CU FT

Number

NO.

Inboard

INBD

Forward

FWD

Outboard

OUTBD

Balance Arm

B.A.

Mean Aerodynamic Chord

MAC

Body Buttock Line

B.B.L.

Leading Edge of the MAC

LEMAC

Water Line

W.L.

Center of Gravity

C.G.

CONVERSION FACTORS The data in this manual is provided in both English and Metric units. Unless otherwise stated, the conversions listed below are used throughout this manual. MULTIPLY

BY

TO OBTAIN

Pounds

0.45359237

Kilograms

U. S. Gallons

3.78541180

Liters

When totals or summations are required the English values are summed separately from the metric values. Differences may occur when comparing the English totals with the metric totals due to round off. All metric values are converted from English values. When using the conversion factors in this manual, all resultants will be rounded except when the value is a weight limitation. For minimum or maximum weight limitations the resultant metric values will be rounded up or truncated, whichever is more conservative.

1-00-001 Page 6 of 6 Jun 27/2005 D043U544-GPR1


747-400BCF


AIRPLANE DIMENSIONS GENERAL ARRANGEMENT AND PRIMARY DIMENSIONS The following figure shows the 747-400SF general arrangement and primary dimensions.

21 FT 4 IN.

63 FT 8 IN.

84 FT 0 IN. 25 FT 5 IN. 225 FT 2 IN. 231 FT 10 IN. 72 FT 9 IN.

12 FT 7 IN. 36 FT 1 IN. 211 FT 5 IN.


1-00-021 Page 1 of 1 Jun 27/2005 D043U544-GPR1

747-400BCF


BALANCE REFERENCE SYSTEM BALANCE ARMS / BODY STATIONS Longitudinal location of all airplane component centers of gravity identified throughout this manual will be referred to as Balance Arms. The Balance Arm is a true measure in inches from the reference datum 90.0 IN. forward of the airplane nose. Balance Arms are equivalent to Body Stations (B.S.).

90.0

464.0 0

1295.0

690.0

200

400

615.0

830.0

600

800

2261.0

1694.0 1850.0

1865.0 2007.0 1000

1200

1400

1600

1800

2000

2792.0 2200

2400

2600

2800

BALANCE ARM (IN.)

MEAN AERODYNAMIC CHORD The Mean Aerodynamic Chord, as used in this manual, is a wing reference distance with a length of 327.8 IN. The Leading Edge of the Mean Aerodynamic Chord is at Balance Arm 1258.0 IN. Conversion of the airplane center of gravity from Balance Arm, in inches, to a percentage of Mean Aerodynamic Chord is derived using the following formula: ( B.A. – 1258.0 ) × 100.0 %MAC = --------------------------------------------------------------327.8 The reverse conversion of the airplane center of gravity from a percentage of Mean Aerodynamic Chord to Balance Arm, in inches, is derived using the following formula: ( 327.8 × %MAC ) B.A. = ---------------------------------------------- + 1258.0 100.0

BODY BUTTOCK LINE The Body Buttock Line is a vertical line or a vertical plane parallel to the centerline of the airplane used to locate points or planes to the left or right of the airplane centerline.

WATER LINE The Water Line is a horizontal reference line or a horizontal plane parallel to the main deck floor used to locate points or planes vertically. The Water Line is measured from the reference datum 199.8 IN. below the top of the main deck floor. APPLICABLE CONFIGURATIONS All

1-00-041 Page 1 of 1 Jun 27/2005 D043U544-GPR1


747-400BCF

FACTORS AFFECTING PERFORMANCE AND OPERATIONAL LIMITATIONS INTERPOLATION OF CERTIFIED CENTER OF GRAVITY LIMITS CHP-SEC 1-02-xxx presents the certified weight and center of gravity limits by identifying inflection points (end points) for each limit in terms of weight and %MAC. Intermediate points between the inflection points must be determined by interpolating the weight and moment, not the weight and %MAC. The moment is calculated for any given weight and %MAC by using the following formula: ( 327.8x%MAC ) Moment = Weight × ------------------------------------------ + 1258.0 100.0 Weight versus moment grids can be presented in various ways. The Loading Schedule Substantiation documents referenced in CHP-SEC 1-90-00x typically show weight and center of gravity limits converted to a weight versus index. The index values on these grids are an alternate way of displaying moment and are calculated using an index equation. Interpolating intermediate points using weight and index is equivalent to weight and moment.

OPERATIONAL WEIGHT AND CENTER OF GRAVITY REQUIREMENTS To comply with the performance and operational limitations of the Federal Aviation Regulations, the allowable takeoff weight and the landing weight may be restricted to less than the Maximum Takeoff Weight and the Maximum Landing Weight respectively. The Operational Takeoff Weight may be limited by the most restrictive of the following requirements:

Operational Takeoff Weight for altitude and temperature Takeoff field length requirements Tire speed and brake energy limits Tire pressure Obstacle clearance, enroute and landing requirements Noise requirements Lateral Imbalance

The Operational Landing Weight may be limited by the most restrictive of the following requirements:

Landing field length requirements Maximum approach and landing climb weight for altitude and temperature Noise requirements

These may not be all of the limitations; see the Airplane Flight Manual for further information. To ensure that the airplane center of gravity remains within the center of gravity limits, airplane balance must be accounted for with all load conditions during all taxi, takeoff, flight and landing operations. Appropriate constraints must be established and applied to the center of gravity limits as required to account for such changes in the airplane balance condition as due to: Cargo location variation Fuel density variation Fuel usage In-flight movement The data in the remainder of this manual will allow the operator to develop these constraints. For guidance in accunting for these items, refer to Advisory Circular 120-27E.


1-02-001 Page 1 of 2 Dec 14/2005 D043U544-GPR1


747-400BCF

FACTORS AFFECTING PERFORMANCE AND OPERATIONAL LIMITATIONS COMMONWEALTH OF INDEPENDENT STATES (CIS) REQUIREMENTS Airplanes operating under the regulatory agency of the Commonwealth of Independent States (CIS) are required to be in compliance with NLGS-3 (comparable to FAR Part 25). Aviation Register (AR) Specialists identified changes to some Boeing procedural documents that would be necessary to be in compliance with NLGS-3 and operate in the CIS.

Continuous Cold Weather Operations Boeing document number D6-81416-4, “The Aviation Register Requirements for Operation in the Commonwealth of Independent States, defines a procedure for airplanes operating continuously in cold weather (i.e. ground temperatures below the freezing point). When these conditions exist, ice builds up in the interior of the airplane. The Maintenance Manual Section of document D6-81416-4 defines the prescribed maximum flight hours before removal of interior ice is required.

1-02-001 Page 2 of 2 Dec 14/2005 D043U544-GPR1


747-400BCF


CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS CERTIFIED WEIGHT LIMITS - MTW 873000 LB (395986 KG) The Maximum Certified Gross Weights and Center of Gravity Limits are shown graphically on pages 2 & 3. These Center of Gravity Limits are for taxi, takeoff, flight and landing unless otherwise specified, and are the absolute limits which must not be exceeded by the airplane center of gravity in any taxi, takeoff, flight, or landing configuration. CERTIFIED GROSS WEIGHTS LB

KG

Maximum Taxi Weight

(MTW)

873000

395986

Maximum Takeoff Weight

(MTOW)

870000

394625

Maximum Fuel Transfer Weight (MFTW)

785000

356070

Maximum Weight with Landing Flaps (Flap Detents 25 and 30)

670000

303906

Maximum Landing Weight

(MLW)

652000

295742

Maximum Zero Fuel Weight

(MZFW)

610000

276691

Minimum Flight Weight

(MFW)

367500

166696

LIMITATIONS The following limitations must be met in order to use the certified gross weight and center of gravity limits:

Minimum Tire Size Required

Nose Gear - 49X17/32 Ply Rating

Main Gear - H49X19-22/32 Ply Rating

See CHP-SEC 1-05-xxx for fuel density restrictions

All limits based on gear and flaps down.

Added reference to Airplane Maintenance Manual Section 12-15-06 for tire pressure requirements.

APPLICABLE CONFIGURATIONS E

1-02-011 Page 1 of 3 Mar 21/2007 D043U544-GPR1

747-400BCF


CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS (Continued) C.G. LIMITS - MTW 873000 LB, MLW 652000 LB, MZFW 610000 LB The following diagram represents the certified Center of Gravity Limits in English units: 867600 LB 857000 LB

890000

at 12.8%

853000 LB

870000

at 11.0%

MAXIMUM TAXI WEIGHT - 873000 LB

MAXIMUM TAKEOFF

850000

834000 LB

WEIGHT - 870000 LB

803000 LB 830000

24.8%

20.0%

at 17.6%

at 33.0%

at 8.5%

810000 1

Forw ard Tax i and

790000

778000 LB

778000 LB

Takeoff Limit w ith Zero

770000

at 11.0%

at 15.5%

Fuel Weight greater than 545000 LB

750000 730000

2

Forw ard Tax i and Takeoff Limit w ith

710000

Increased Aft 690000

2

1

Cumulativ e Loads

GROSS WEIGHT - LB

670000

MAXIMUM LANDING WEIGHT - 652000 LB

650000 16.8%

600000 LB

630000

MAXIMUM ZERO FUEL WEIGHT - 610000 LB

at 8.5%

610000

600000 LB

590000 580000 LB

570000

at 11.0% 550000

564000 LB

530000

When operating in this region

at 13.0%

510000

use the "Low Gross Weight, Aft C.G. Takeoff Procedure"

526500 LB

490000

found in section 3 of the

at 13.0%

486000 LB

Airplane Flight Manual

470000 450000

Do not operate in this

430000

shaded area during takeoff

410000 390000

24.2%

370000

28.3%

350000 5.0

10.0

15.0

20.0

25.0

30.0

35.0

CENTER OF GRAVITY - % MAC

WARNING REFER TO PAGE 1 OF THIS SUBJECT FOR LIMITATIONS TO THE C.G. LIMITS.

1-02-011 Page 2 of 3 Mar 21/2007 D043U544-GPR1


40.0

747-400BCF


CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS (Continued) C.G. LIMITS - MTW 395986 KG, MLW 295742 KG, MZFW 276691 KG The following diagram represents the certified Center of Gravity Limits in Metric units: 393536 KG

410000

388728 KG

400000

386914 KG

at 17.6%

MAXIMUM TAXI WEIGHT - 395986 KG 378296 KG

WEIGHT - 394625 KG

364234 KG

380000

24.8%

MAXIMUM TAKEOFF

at 11.0%

390000

20.0%

at 12.8%

at 33.0%

at 8.5% 370000 1

360000 350000

Forw ard Tax i and

352894 KG

352894 KG


at 11.0%

at 15.5%

Fuel Weight greater than 247207 KG

340000 2

330000


1

320000

2

Increased Aft Cumulativ e Loads

310000

GROSS WEIGHT - KG

300000

MAXIMUM LANDING WEIGHT - 295742 KG

290000

16.8%

272155 KG 280000

MAXIMUM ZERO FUEL WEIGHT - 276691 KG

at 8.5%

270000

272155 KG

263083 KG

260000

at 11.0%


250000 255826 KG

use the "Low Gross Weight,

240000

at 13.0%

Aft C.G. Takeoff Procedure"

230000

238816 KG

found in section 3 of the Airplane Flight Manual

at 13.0%

220000

220445 KG

210000 200000

Do not operate in this shaded area during takeoff

190000 180000 170000

24.3%

28.4%

160000 5.0

10.0

15.0

20.0

25.0

30.0

35.0

40.0




1-02-011 Page 3 of 3 Mar 21/2007 D043U544-GPR1

747-400BCF


CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS CERTIFIED WEIGHT LIMITS - MTW 873000 LB (395986 KG) The Maximum Certified Gross Weights and Center of Gravity Limits are shown graphically on pages 3 through 8. These Center of Gravity Limits are for taxi, takeoff, flight and landing unless otherwise specified, and are the absolute limits which must not be exceeded by the airplane center of gravity in any taxi, takeoff, flight, or landing configuration.

CERTIFIED GROSS WEIGHTS LB

KG

Maximum Taxi Weight

(MTW)

873000

395986

Maximum Takeoff Weight

(MTOW)

870000

394625

Maximum Fuel Transfer Weight (MFTW)

785000

356070

Maximum Weight with Landing Flaps (Flap Detents 25 and 30)

670000

303906

Maximum Landing Weight

(MLW)

652000

295742

Maximum Zero Fuel Weight

(MZFW)

610000

276691

Minimum Flight Weight

(MFW)

367500

166696

LIMITATIONS The following limitations must be met in order to use the certified gross weight and center of gravity limits:

Minimum Tire Size Required

Nose Gear - 49X17/32 Ply Rating

Main Gear - H49X19-22/32 Ply Rating

See CHP-SEC 1-05-xxx for fuel density restrictions

All limits based on gear and flaps down.

Refer to the Airplane Maintenance Manual Section 12-15-06 for minimum tire pressure requirements.

Pratt & Whitney has a new PW4056 Ring Case Configuration (RCC) HPC engine as a replacement for the current Segmented Case Configuration (SCC) HPC engines. One characteristic of the new engine is a noticeable difference in engine acceleration time. This characteristic when combined with some RCC/SCC engine intermix combinations can result in thrust asymmetries during takeoff power set. Certain engine intermix configurations result in thrust asymmetries requiring restrictions to the light weight, aft center of gravity portion of the gross weight/center of gravity envelope for takeoff. These restrictions will be required as long as RCC/SCC engine intermixes exist in the fleet. The retrofit of an SCC engine to an RCC engine is per SB 747-71-2305, POWER PLANT (PW4000) COOLING TUBE AND CASE RING SUPPORT BRACKET REPLACEMENT. The RCC engine may also be installed in production.

APPLICABLE CONFIGURATIONS A, B, C, D

1-02-900 Page 1 of 8 Apr 25/2006 D043U544-GPR1


747-400BCF

CERTIFIED WEIGHT AND CENTER OF GRAVITY LIMITS (Continued) The CG limits on pages 3 through 8 of this section are applicable per the RCC/SCC engine intermix chart shown below. Valid CG limit charts are noted with an "X".

ENGINE LOCATION #1 #2 #3 #4 SCC SCC SCC SCC RCC SCC SCC SCC SCC RCC SCC SCC SCC SCC RCC SCC SCC SCC SCC RCC RCC RCC SCC SCC RCC SCC RCC SCC RCC SCC SCC RCC SCC RCC RCC SCC SCC RCC SCC RCC SCC SCC RCC RCC RCC RCC RCC SCC RCC RCC SCC RCC RCC SCC RCC RCC SCC RCC RCC RCC RCC RCC RCC RCC RCC = PW4056 Ring Case Configuration HPC SCC = PW4056 Segmented Case Configuration HPC

1-02-900 Page 2 of 8 Apr 25/2006 D043U544-GPR1

C.G. LIMITS PAGE PAGE 3,4 PAGE 5,6 PAGE 7,8 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X


747-400BCF



890000

at 12.8%

853000 LB

870000

at 11.0%


MAXIMUM TAKEOFF

850000

834000 LB

WEIGHT - 870000 LB

803000 LB 830000

24.8%

20.0%

at 17.6%

at 33.0%

at 8.5%

810000 1

Forw ard Tax i and

790000

778000 LB

778000 LB


770000

at 11.0%

at 15.5%


750000 730000

2


710000


1

2

Cumulativ e Loads

GROSS WEIGHT - LB

670000


650000 630000

16.8%

600000 LB


at 8.5%

610000

600000 LB

590000 580000 LB

570000

at 11.0% 550000

564000 LB

530000


at 13.0%

510000

use the "Low Gross Weight, Aft C.G. Takeoff Procedure"

526500 LB

490000

found in section 3 of the

at 13.0%

486000 LB


470000 450000

Do not operate in this

430000

shaded area during takeoff

410000 390000

24.2%

370000

28.3%

350000 5.0

10.0

15.0

20.0

25.0

30.0

35.0

40.0




1-02-900 Page 3 of 8 Apr 25/2006 D043U544-GPR1

747-400BCF



410000

388728 KG

400000

386914 KG

at 17.6%


WEIGHT - 394625 KG

364234 KG

380000

24.8%

MAXIMUM TAKEOFF

at 11.0%

390000

20.0%

at 12.8%

at 33.0%

at 8.5% 370000 1

360000 350000

Forw ard Tax i and

352894 KG

352894 KG


at 11.0%

at 15.5%


340000 2

330000


1

320000

2

Increased Aft Cumulativ e Loads

310000

GROSS WEIGHT - KG

300000


290000

16.8%

272155 KG 280000


at 8.5%

270000

272155 KG

263083 KG

260000

at 11.0%


250000 255826 KG

use the "Low Gross Weight,

240000

at 13.0%

Aft C.G. Takeoff Procedure"

230000

238816 KG

found in section 3 of the Airplane Flight Manual

at 13.0%

220000

220445 KG

210000 200000

Do not operate in this shaded area during takeoff

190000 180000 170000

24.3%

28.4%

160000 5.0

10.0

15.0

20.0

25.0

30.0

35.0



1-02-900 Page 4 of 8 Apr 25/2006 D043U544-GPR1


40.0

747-400BCF



890000

at 12.8%

853000 LB

870000

at 11.0%


MAXIMUM TAKEOFF

850000

834000 LB

WEIGHT - 870000 LB

803000 LB 830000

24.8%

20.0%

at 17.6%

at 33.0%

at 8.5%

810000 1

Forw ard Tax i and

790000

778000 LB

778000 LB


770000

at 11.0%

at 15.5%


750000 730000

1

2

2


710000


Cumulativ e Loads

GROSS WEIGHT - LB

670000


650000 630000

16.8%

600000 LB


at 8.5%

610000

657000 LB

590000 580000 LB

570000

at 11.0% 550000

When operating in this region use the

564000 LB

530000

"Low Gross Weight, Aft C.G. Takeoff

at 13.0%

510000

Procedure" found in section 3 of the

490000

514000 LB


526500 LB at 13.0%

486000 LB When operating in this region

470000

use the "Low Gross Weight, Aft

450000

C.G. Takeoff Procedure - 30%

430000

Derate" found in section 3 of the

410000


Do not operate in this shaded area

390000 22.2%

370000

during takeoff

27.2%

28.3%

350000 5.0

10.0

15.0

20.0

25.0

30.0

35.0

40.0




1-02-900 Page 5 of 8 Apr 25/2006 D043U544-GPR1

747-400BCF



410000

388728 KG

400000

at 17.6%

386914 KG


WEIGHT - 394625 KG

364234 KG

380000

24.8%

MAXIMUM TAKEOFF

at 11.0%

390000

20.0%

at 12.8%

at 33.0%

at 8.5% 370000 1

360000 350000

Forw ard Tax i and

352894 KG

352894 KG


at 11.0%

at 15.5%


340000 2

330000

Forw ard Tax i and Takeoff Limit w ith Increased Aft

2

1

320000

Cumulativ e Loads 310000

GROSS WEIGHT - KG

300000


290000

16.8%

272155 KG 280000

298010 KG


at 8.5%

270000 263083 KG

260000

at 11.0%


250000 255826 KG 240000

at 13.0%

230000

238816 KG

"Low Gross Weight, Aft C.G. Takeoff Procedure" found in section 3 of the 233146 KG


at 13.0%

220000 210000

220445 KG When operating in this region use the "Low Gross Weight, Aft

200000


190000


Do not operate


180000

in this shaded area

170000

22.3%

27.3%

during takeoff

28.4%

160000 5.0

10.0

15.0

20.0

25.0

30.0

35.0



1-02-900 Page 6 of 8 Apr 25/2006 D043U544-GPR1


40.0

747-400BCF



890000

at 12.8%

853000 LB

870000

at 11.0%


MAXIMUM TAKEOFF

850000

834000 LB

WEIGHT - 870000 LB

803000 LB 830000

24.8%

20.0%

at 17.6%

at 33.0%

at 8.5%

810000 790000

778000 LB

778000 LB

770000

at 11.0%

at 15.5%

1

Forw ard Tax i and Takeoff Limit w ith Zero Fuel Weight greater than 545000 LB

750000

743000 LB

730000

2

Takeoff Limit w ith

2

1

710000

Forw ard Tax i and Increased Aft

690000

Cumulativ e Loads

GROSS WEIGHT - LB

670000


650000 630000

16.8%

600000 LB


at 8.5%

610000

600000 LB

590000 580000 LB

570000

at 11.0% 550000


564000 LB

530000

at 13.0%

510000

526500 LB

490000

"Low Gross Weight, Aft C.G. Takeoff Procedure" found in section 3 of the Airplane Flight Manual

at 13.0%

486000 LB


470000


450000


430000


410000


Do not operate in this shaded area

390000 19.2%

370000

24.2%

during takeoff

28.3%

350000 5.0

10.0

15.0

20.0

25.0

30.0

35.0

40.0




1-02-900 Page 7 of 8 Apr 25/2006 D043U544-GPR1

747-400BCF



410000

388728 KG

400000

20.0%

at 17.6%

386914 KG

378296 KG

WEIGHT - 394625 KG

364234 KG

380000

MAXIMUM TAXI WEIGHT - 395986 KG

MAXIMUM TAKEOFF

at 11.0%

390000

24.8%

at 12.8%

at 33.0%

at 8.5% 370000 1

360000 350000

Forw ard Tax i and

352894 KG

352894 KG


at 11.0%

at 15.5%


340000 2

330000

2

1

337019 KG

Forw ard Tax i and Takeoff Limit w ith Increased Aft

320000

Cumulativ e Loads 310000

GROSS WEIGHT - KG

300000


290000

16.8%

272155 KG 280000


at 8.5%

270000

272155 KG

263083 KG

260000

at 11.0%


250000 255826 KG 240000

at 13.0%

230000

238816 KG

"Low Gross Weight, Aft C.G. Takeoff Procedure" found in section 3 of the Airplane Flight Manual

at 13.0% When operating in this region

220000

220445 KG


210000


200000


190000


Do not operate

180000

in this shaded area

170000

19.3%

24.3%

during takeoff

28.4%

160000 5.0

10.0

15.0

20.0

25.0

30.0

35.0



1-02-900 Page 8 of 8 Apr 25/2006 D043U544-GPR1


40.0


747-400BCF

AIRPLANE LATERAL IMBALANCE LIMITS LATERAL IMBALANCE The airplane should be loaded symmetrically. When off center loading of payload and/or fuel does occur, the airplane can be operated if the following gross weight and lateral imbalance limits are not exceeded. The lateral balance arms of ULD’s can be found in CHP-SEC 1-69-00x. Random Imbalance is the lateral movement of the airplane center of gravity about the airplane centerline due to the attempt to symmetrically load cargo and fuel about the airplane centerline. It is expressed as a moment about the airplane centerline.


1-04-001 Page 1 of 3 Jun 27/2005 D043U544-GPR1

747-400BCF


AIRPLANE LATERAL IMBALANCE LIMITS (Continued) LATERAL IMBALANCE LIMITATIONS (POUNDS) The following chart presents Lateral Imbalance data in Pounds.

950000

Allowable Random Imbalance Increment 3.0

900000

15.4 873000

850000 20.0

400

761900

750000

700000

Maintenance Operations

Flight Limit at 10.0

GROSS WEIGHT - LB

801000

793900

800000

650000

600000

20.0

30.0 640800 622300

550000

Ground Operations

Taxi and Flight

497800

500000

450000

400000 0

5

10

15

20

25

LATERAL IMBALANCE - 1000000 LB-IN

1-04-001 Page 2 of 3 Jun 27/2005 D043U544-GPR1


30

35

747-400BCF


AIRPLANE LATERAL IMBALANCE LIMITS (Continued) LATERAL IMBALANCE LIMITATIONS (KILOGRAMS) The following chart presents Lateral Imbalance data in Kilograms. 420000

Allowable Random Imbalance Increment

1.3 400000

6.9 395986

380000

9.0

345592

340000

Maintenance Operations

320000 9.0 300000

Flight Limit at 4.5

GROSS WEIGHT - KG

363327

360106

360000

280000

260000

13.6

290661 282270

240000

Taxi and Flight

Ground Operations 225798

220000

200000

180000 0

2

4

6

8

10

12

14

LATERAL IMBALANCE - 1000000 KG-IN


1-04-001 Page 3 of 3 Jun 27/2005 D043U544-GPR1

747-400BCF


AIRPLANE GROSS WEIGHT VERSUS FUEL DENSITY LIMITATION FUEL DENSITY LIMITATIONS The fuel density must be between the minimum fuel density of 6.0 LB/GAL. (0.7190 KG/L) and the maximum allowable fuel density of 7.1 LB/GAL. (0.8507 KG/L) unless limited by gross weight as shown below:

FUEL DENSITY LIMITATIONS (POUNDS) The following chart presents Fuel Density Limitations in Pounds.

880000 Operation in in the shaded area Operation the shaded area requires takeoff aftaft ofof requiresa a takeoffc.g. c.g. atat 820000 LBLB 19.1%MAC MAC 820000 870000 19.1% tapering linearly 19.5% tapering linearlytoto 19.5% MAC atat 850000 LBLB tapering MAC 850000 tapering lineary to to 20.0% MAC at at linearly 20.0% MAC 860000 870000 LB. 870000 LB.Refer RefertotoCHPCHP-SEC SEC 1-02-xxx 1-02-xxx

870000 LB at 6.43

850000

AIRPLANE TAKEOFF WEIGHT - LB

400

7.1

850000 LB at 6.43

840000

830000 820000 LB at 6.0

820000

810000

800000

790000

780000 5.80

6.00

6.20

6.40

6.60

6.80

7.00

7.20

FUEL DENSITY (LB/U.S. GAL.)


1-05-001 Page 1 of 2 Apr 20/2006 D043U544-GPR1

747-400BCF


AIRPLANE GROSS WEIGHT VERSUS FUEL DENSITY LIMITATION (Continued) FUEL DENSITY LIMITATIONS (KILOGRAMS) The following chart presents Fuel Density Limitations in Kilograms.

400000

Operation in the shaded area Operation shaded requiresinathe takeoff c.g.area aft of requires takeoff c.g. aftLB of 19.1%a MAC at 820000 19.1% MAClinearly at 371945 KG tapering to 19.5% tapering to LB 19.5% MAC linearly at 850000 tapering lineary to 20.0% at MAC at 385553 KG MAC tapering 870000 LB. Refer linearly to 20.0% MACtoatCHPSEC KG. 1-02-xxx 394625 Refer to CHP-SEC 1-02-xxx

395000

390000

394625 KG at 0.77

AIRPLANE TAKEOFF WEIGHT - KG

400

385000

0.85

385553 KG at 0.77

380000 371945 KG at 0.72

375000

370000

365000

360000

355000

350000 0.7

0.72

0.74

0.76

0.78

0.8

0.82

FUEL DENSITY (KG/LITER)

1-05-001 Page 2 of 2 Apr 20/2006 D043U544-GPR1


0.84

0.86

747-400BCF


TAKEOFF HORIZONTAL STABILIZER TRIM SETTING ENGLISH UNITS - MULTIPLE GREEN BAND The following diagram provides Takeoff Trim Settings versus Airplane Center of Gravity in Pounds.

Full Thrust to 15% Thrust Derate 0 1

GREENBANDS

2

A N D

STABILIZER TRIM TRIM UNITS. UNITS STABILIZER

3

400*

450*

* 550 600*

500*

4 5

M I D

6

* 650

7

* 700

* 800

0* 100

* 900

8

A N U

9 10

*GROSS WEIGHT - 1000 LB

11 12 5

10

15

20

25

30

35


The following table provides inflection point data for the Takeoff Trim Settings versus Airplane Center of Gravity Diagram above. TAKEOFF TRIM SETTING INFLECTION POINTS (Gross Weight - 1000 LB)

13.0 3.4 13.0 4.2 13.0 5.4

8.5 7.6

8.5 8.6

23.7 2.0 27.3 2.0 30.4 2.0

8.5 9.1

8.5 9.4

8.5 9.5 9.8 9.5

8.5 9.5

TRIM

C.G.

1000 TRIM

C.G.

900 TRIM

C.G.

800 TRIM

C.G.

700 TRIM

C.G.

650 TRIM

C.G.

600 TRIM

C.G.

550 TRIM

C.G.

500 TRIM

C.G.

450 TRIM

C.G.

400

8.5 9.5

11.1 9.5 12.3 9.5

33.0 2.0 33.0 2.0 33.0 2.0 33.0 2.1 33.0 2.4 33.0 2.8 33.0 3.2 33.0 3.6 33.0 3.8 33.0 4.0 The above values are for full rated engine thrust to 15% thrust derate. For engine thrust derate at or greater than 15% see page 3. For intermediate values, use linear interpolation.


1-06-001 Page 1 of 4 Jun 27/2005 D043U544-GPR1

747-400BCF


TAKEOFF HORIZONTAL STABILIZER TRIM SETTING (Continued) METRIC UNITS - MULTIPLE GREEN BAND The following diagram provides Takeoff Trim Settings versus Airplane Center of Gravity in Kilograms.

Full Thrust to 15% Thrust Derate 0 1

GREENBANDS

2

A N D

STABILIZER TRIM UNITS. UNITS STABILIZER

3

200*

180*

2 20

* 240

*

4 5

M I D

6

* 260

280

*

* 300

* 00* 360 4

* 320

* 440

7 8

A N U

9 10

*GROSS WEIGHT - 1000 KG

11 12 5

10

15

20

25

30

35


The following table provides inflection point data for the Takeoff Trim Settings versus Airplane Center of Gravity Diagram above. TAKEOFF TRIM SETTING INFLECTION POINTS (Gross Weight - 1000 KG)

23.4 2.0 26.7 2.0 29.6 2.0 32.2 2.0

8.5 8.1

8.5 8.8

8.5 9.1

8.5 9.4

8.5 9.5

8.5 9.5

TRIM

C.G.

440 TRIM

C.G.

400 TRIM

C.G.

360 TRIM

C.G.

320 TRIM

C.G.

300 TRIM

C.G.

280 TRIM

C.G.

13.0 3.3 13.0 4.1 13.0 5.0 13.0 6.1

C.G.

260 TRIM

240 TRIM

C.G.

220 TRIM

C.G.

200 TRIM

C.G.

180

8.5 9.5

9.7 9.5 10.9 9.5 11.9 9.5

33.0 2.0 33.0 2.0 33.0 2.0 33.0 2.0 33.0 2.2 33.0 2.5 33.0 2.9 33.0 3.2 33.0 3.6 33.0 3.8 33.0 4.0 The above values are for full rated engine thrust to 15% thrust derate. For engine thrust derate at or greater than 15% see page 4. For intermediate values, use linear interpolation.

1-06-001 Page 2 of 4 Jun 27/2005 D043U544-GPR1


747-400BCF


TAKEOFF HORIZONTAL STABILIZER TRIM SETTING (Continued) ENGLISH UNITS - MULTIPLE GREEN BAND The following diagram provides Takeoff Trim Settings versus Airplane Center of Gravity in Pounds.

15% to 30% Thrust Derate 0

GREENBANDS 1

A N D

2

STABILIZER TRIM UNITS. UNITS STABILIZER

3 4

500* 550* 600*

* 450

* 400

5

M I D

6 7

650

*

700

* 800

*

* 900

0* 100

8

A N U

9 10

*GROSS WEIGHT - 1000 LB

11 12 5

10

15

20

25

30

35


The following table provides inflection point data for the Takeoff Trim Settings versus Airplane Center of Gravity Diagram above. TAKEOFF TRIM SETTING INFLECTION POINTS (Gross Weight - 1000 LB)

13.0 5.0 13.0 6.2 13.0 6.9

8.5 8.2

8.5 9.2

30.6 2.0

8.5 9.5

8.5 9.5

8.9 9.5 10.2 9.5

8.5 9.5

C.G.

8.5 9.5

TRIM

1000 TRIM

C.G.

900 TRIM

C.G.

800 TRIM

C.G.

700 TRIM

C.G.

650 TRIM

C.G.

600 TRIM

C.G.

550 TRIM

C.G.

500 TRIM

C.G.

450 TRIM

C.G.

400

8.5 9.5

11.5 9.5 12.9 9.5 14.2 9.5

33.0 2.0 33.0 2.1 33.0 2.7 33.0 2.9 33.0 3.1 33.0 3.3 33.0 3.6 33.0 3.9 33.0 4.1 33.0 4.3 The above values are for 15% to 30% thrust derate. For intermediate values, use linear interpolation.


1-06-001 Page 3 of 4 Jun 27/2005 D043U544-GPR1

747-400BCF


TAKEOFF HORIZONTAL STABILIZER TRIM SETTING (Continued) METRIC UNITS - MULTIPLE GREEN BAND The following diagram provides Takeoff Trim Settings versus Airplane Center of Gravity in Kilograms.

15% to 30% Thrust Derate 0 1

GREENBANDS

2

A N D

STABILIZER TRIM UNITS UNITS.

3 4 5 M I D

6 7

280

* 260

* 300

*

* 240

* 220

* 200

* 180

320

*

* 360

* 400

* 440

8

A N U

9 10

*GROSS WEIGHT - 1000 KG

11 12 5

10

15

20

25

30

35


The following table provides inflection point data for the Takeoff Trim Settings versus Airplane Center of Gravity Diagram above. TAKEOFF TRIM SETTING INFLECTION POINTS (Gross Weight - 1000 KG)

30.4 2.0 32.8 2.0

8.5 8.7

8.5 9.3

8.5 9.5

8.5 9.5

8.5 9.5

8.5 9.5

TRIM

C.G.

440 TRIM

C.G.

400 TRIM

C.G.

360 TRIM

C.G.

320 TRIM

C.G.

300 TRIM

C.G.

280 TRIM

C.G.

13.0 4.9 13.0 6.0 13.0 6.6 13.0 7.1

C.G.

260 TRIM

240 TRIM

C.G.

220 TRIM

C.G.

200 TRIM

C.G.

180

8.5 9.5

9.2 9.5 10.2 9.5 11.4 9.5 12.6 9.5 13.8 9.5

33.0 2.0 33.0 2.0 33.0 2.5 33.0 2.8 33.0 2.9 33.0 3.1 33.0 3.4 33.0 3.6 33.0 3.9 33.0 4.0 33.0 4.3 The above values are for 15% to 30% thrust derate. For intermediate values, use linear interpolation.

1-06-001 Page 4 of 4 Jun 27/2005 D043U544-GPR1


747-400BCF


LANDING GEAR AND FLAP MOVEMENT BALANCE EFFECT LANDING GEAR RETRACTION MOMENT The following table provides airplane moment changes caused by retraction of the landing gear from the taxi position (extended, gear down) to the flight position (retracted, gear up). MOMENT

GEAR

LB-IN.

KG-IN.

Nose (Down to Up)

-167900

-76200

Body (Down to Up)

-545600

-247500

-493900

-224000

-1207400

-547700

Wing (Down to Up) Total Moment Change

FLAPS RETRACTION MOMENT The following table provides airplane moment changes caused by retraction of the leading edge (L.E.) and the trailing edge (T.E.) flaps. FLAP POSITION

MOMENT LB-IN.

FROM

TO

30

30

30

20

30

10

-110000

0

30

5

-238000

0

30

0

-498000

+40000

-458000

NOTE

T.E. FLAPS

L.E. FLAPS

MOMENT KG-IN. TOTAL

L.E. FLAPS

TOTAL

0 -20000

0

-20000

0 -9100

0

-110000

-49900

0

-49900

-238000

-108000

0

-108000

-225900

+18100

-207800

-9100

A forward movement of airplane center of gravity is a negative moment. An aft movement of airplane center of gravity is a positive moment.


T.E. FLAPS

1-08-001 Page 1 of 1 Jun 27/2005 D043U544-GPR1


747-400BCF

FUEL TANK ARRANGEMENT AND CAPACITIES FUEL TANK LOCATIONS The following diagram shows the fuel tank arrangement:

SURGE TANK

RESERVE TANK 3

MAIN TANK 4

MAIN TANK 3

CENTER TANK

MAIN TANK 2

MAIN TANK 1

RESERVE TANK 2

SURGE TANK

APPLICABLE CONFIGURATIONS A, B

1-20-001 Page 1 of 4 Jun 27/2005 D043U544-GPR1

747-400BCF


FUEL TANK ARRANGEMENT AND CAPACITIES (Continued) MAXIMUM ALLOWABLE FUEL WEIGHT The maximum allowable usable tank quantities shown in the following table are based on a fuel density of 7.1 LB/U.S. GAL. (0.8507 KG/L). MAXIMUM VOLUME

LOCATION

U.S. GAL.

L

MAXIMUM WEIGHT LB

KG

Main Tank 1 or 4

4482

16966

31822

14432

Main Tank 2 or 3

12546

47491

89076

40400

1322

5004

9386

4256

17164

64972

121864

55271

Reserve Tank 2 or 3 Center Tank

1-20-001 Page 2 of 4 Jun 27/2005 D043U544-GPR1


747-400BCF


FUEL TANK ARRANGEMENT AND CAPACITIES (Continued) USABLE FUEL QUANTITIES AND LOCATIONS The following tables provide volume and center of gravity data for usable fuel. For definitions of “usable”, “drainable usable” and “trapped usable”, refer to General Information (CHP-SEC 1-00-00x). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

Under Wing Fueling FUEL CATEGORY

FUEL LOCATION

Drainable Usable

B.A. - IN. L

GROUND

FLIGHT

Main Tank 1

4482

16966

1490

1488

Main Tank 2

12546

47492

1212

1213

Main Tank 3

12546

47492

1212

1213

Main Tank 4

4482

16966

1490

1488

Reserve Tank 2

1322

5004

1730

1727

Reserve Tank 3

1322

5004

1730

1727

17164

64973

Center Tank Refuel Manifold Total Drainable

78[a]

295[a]

1250

1250

1340

1340

Lines[b]

33[a]

125[a]

1340

1340

Total Trapped

43[a]

163[a]

1340

1340

1250

1250

TOTAL USABLE

204192

1106 1340

38[a]

Feed

53942

1106 1340

10[a]

Engines

Trapped Usable

VOLUME U.S. GAL.

53985

204355

[a] These volumes are not gauged. [b] All fuel in lines between boost pump check valves and engine pump inlets, bypass valves, defuel valves, and APU fuel control. Pump inlet line volume included in tank volume.

Over Wing Fueling FUEL CATEGORY Drainable Usable

VOLUME U.S. GAL.

L

GROUND

FLIGHT

Main Tank 1

4237

16039

1485

1481

Main Tank 2

12300

46561

1211

1213

Main Tank 3

12300

46561

1211

1213

Main Tank 4

4237

16039

1485

1481

33074

125200

1281

1282

TOTAL USABLE


B.A. - IN.

FUEL LOCATION

1-20-001 Page 3 of 4 Jun 27/2005 D043U544-GPR1

747-400BCF


FUEL TANK ARRANGEMENT AND CAPACITIES (Continued) UNUSABLE FUEL QUANTITIES AND LOCATIONS The following table provides volume and center of gravity data for unusable fuel. For definitions of “unusable”, “drainable unusable” and “trapped unusable”, refer to General Information (CHP-SEC 1-00-00x). The ground balance arms are representative of the wing in a nominal ground deflected position. FUEL CATEGORY

Drainable Unusable[a]

FUEL LOCATION

U.S. GAL.

B.A. - IN. L

GROUND

Main Tank 1

30.1

113.9

1418

Main Tank 2

33.1

125.3

1078

Main Tank 3

33.1

125.3

1078

Main Tank 4

30.1

113.9

1418

0.2

0.8

1681

Reserve Tank 2 Reserve Tank 3

0.2

0.8

1681

39.9

151.0

1080

166.7

631.0

1203

Main Tank 1

2.4

9.1

1362

Main Tank 2

1.3

4.9

1057

Main Tank 3

1.3

4.9

1057

Main Tank 4

2.4

9.1

1362

Reserve Tank 2

0.5

1.9

1598

Center Tank Total Drainable

Trapped Unusable[a]

VOLUME

Reserve Tank 3

0.5

1.9

1598

Center Tank

7.7

29.1

1063

Lines[b]

43.6[b]

165.0[b]

1252[b]

Total Trapped

59.7

225.9

1234

226.4

856.9

1211

TOTAL UNUSABLE

[a] Based on an airplane nominal ground attitude of 0.5 degrees nose down and 0 degrees roll. [b] All fuel in lines between boost pump check valves and engine pump inlets, bypass valves, defuel valves and APU fuel control; APU feed line; engines. Pump inlet line volume included in tank volume.

1-20-001 Page 4 of 4 Jun 27/2005 D043U544-GPR1



747-400BCF


SURGE TANK

RESERVE TANK 3

DRY BAY MAIN TANK 4

MAIN TANK 3

CENTER TANK

MAIN TANK 2

MAIN TANK 1 DRY BAY

RESERVE TANK 2

SURGE TANK


1-20-003 Page 1 of 4 Apr 20/2006 D043U544-GPR1

747-400BCF



LOCATION

U.S. GAL.

L

MAXIMUM WEIGHT LB

KG

Main Tank 1 or 4

4372

16550

31041

14079

Main Tank 2 or 3

12546

47491

89076

40400

1322

5004

9386

4256

17164

64972

121864

55271


1-20-003 Page 2 of 4 Apr 20/2006 D043U544-GPR1


747-400BCF




FUEL LOCATION

Drainable Usable

B.A. - IN. L

GROUND

FLIGHT

Main Tank 1

4372

16550

1488

1486

Main Tank 2

12546

47492

1212

1213

Main Tank 3

12546

47492

1212

1213

Main Tank 4

4372

16550

1488

1486

Reserve Tank 2

1322

5004

1730

1727

Reserve Tank 3

1322

5004

1730

1727

17164

64973


78[a]

295[a]

1249

1249

1340

1340

Lines[b]

33[a]

125[a]

1340

1340

Total Trapped

43[a]

163[a]

1340

1340

1249

1249

TOTAL USABLE

203360

1106 1340

38[a]

Feed

53722

1106 1340

10[a]

Engines

Trapped Usable

VOLUME U.S. GAL.

53765

203523



VOLUME U.S. GAL.

L

GROUND

FLIGHT

Main Tank 1

4070

15407

1482

1476

Main Tank 2

12300

46561

1211

1213

Main Tank 3

12300

46561

1211

1213

Main Tank 4

4070

15407

1482

1476

32740

123936

1278

1278

TOTAL USABLE


B.A. - IN.

FUEL LOCATION

1-20-003 Page 3 of 4 Apr 20/2006 D043U544-GPR1

747-400BCF




FUEL LOCATION

U.S. GAL.

B.A. - IN. L

GROUND

Main Tank 1

30.1

113.9

1418

Main Tank 2

33.1

125.3

1078

Main Tank 3

33.1

125.3

1078

Main Tank 4

30.1

113.9

1418

0.2

0.8

1681


0.2

0.8

1681

39.9

151.0

1080

166.7

631.0

1203

Main Tank 1

2.4

9.1

1362

Main Tank 2

1.3

4.9

1057

Main Tank 3

1.3

4.9

1057

Main Tank 4

2.4

9.1

1362

Reserve Tank 2

0.5

1.9

1598


Trapped Unusable[a]

VOLUME

Reserve Tank 3

0.5

1.9

1598

Center Tank

7.7

29.1

1063

Lines[b]

43.6[b]

165.0[b]

1252[b]

Total Trapped

59.7

225.9

1234

226.4

856.9

1211

TOTAL UNUSABLE


1-20-003 Page 4 of 4 Apr 20/2006 D043U544-GPR1



747-400BCF


SURGE TANK

RESERVE TANK 3

MAIN TANK 4

MAIN TANK 3

CENTER TANK

MAIN TANK 2

MAIN TANK 1

RESERVE TANK 2

SURGE TANK

APPLICABLE CONFIGURATIONS C, D

1-20-004 Page 1 of 4 Mar 9/2007 D043U544-GPR1

747-400BCF



LOCATION

U.S. GAL.

L

MAXIMUM WEIGHT LB

KG

Main Tank 1 or 4

4482

16966

31822

14432

Main Tank 2 or 3

12546

47491

89076

40400

1322

5004

9386

4256

17164

64972

121864

55271


1-20-004 Page 2 of 4 Mar 9/2007 D043U544-GPR1


747-400BCF




FUEL LOCATION

Drainable Usable

B.A. - IN. L

GROUND

FLIGHT

Main Tank 1

4482

16966

1490

1488

Main Tank 2

12546

47492

1212

1213

Main Tank 3

12546

47492

1212

1213

Main Tank 4

4482

16966

1490

1488

Reserve Tank 2

1322

5004

1730

1727

Reserve Tank 3

1322

5004

1730

1727

17164

64973


78[a]

295[a]

1250

1250

1340

1340

Lines[b]

33[a]

125[a]

1340

1340

Total Trapped

43[a]

163[a]

1340

1340

1250

1250

TOTAL USABLE

204192

1106 1340

38[a]

Feed

53942

1106 1340

10[a]

Engines

Trapped Usable

VOLUME U.S. GAL.

53985

204355



VOLUME U.S. GAL.

L

GROUND

FLIGHT

Main Tank 1

4237

16039

1485

1481

Main Tank 2

12300

46561

1211

1213

Main Tank 3

12300

46561

1211

1213

Main Tank 4

4237

16039

1485

1481

33074

125200

1281

1282

TOTAL USABLE


B.A. - IN.

FUEL LOCATION

1-20-004 Page 3 of 4 Mar 9/2007 D043U544-GPR1

747-400BCF




FUEL LOCATION

U.S. GAL.

B.A. - IN. L

GROUND

Main Tank 1

30.1

113.9

1418

Main Tank 2

33.1

125.3

1078

Main Tank 3

33.1

125.3

1078

Main Tank 4

30.1

113.9

1418

0.2

0.8

1681


0.2

0.8

1681

20.2

76.5

1080

147.0

556.5

1219

Main Tank 1

2.4

9.1

1362

Main Tank 2

1.3

4.9

1057

Main Tank 3

1.3

4.9

1057

Main Tank 4

2.4

9.1

1362

Reserve Tank 2

0.5

1.9

1598


Trapped Unusable[a]

VOLUME

Reserve Tank 3

0.5

1.9

1598

Center Tank

7.7

29.1

1063

Lines[b]

43.6[b]

165.0[b]

1252[b]

Total Trapped

59.7

225.9

1234

206.7

782.4

1223

TOTAL UNUSABLE


1-20-004 Page 4 of 4 Mar 9/2007 D043U544-GPR1



747-400BCF

FUEL MANAGEMENT AIRPLANE CONFIGURATION For purposes of the data included in this CHP-SEC-SUB, three different groups of airplanes are defined as described below.

Group A (IDS-502)

L/N 696 thru 1326 and 1328 prior to incorporation of Boeing Service Bulletin 74731A2340, 747-31A2341 or 747-31A2342

L/N 696 thru 1326 and 1328 upon incorporation of Boeing Service Bulletin 747-31A2350, 747-31A2351 or 747-31A2352 configured with EICAS Interface Unit Program Pin 2

Group B (IDS-503)

L/N 1327 and 1329 thru 1342 prior to incorporation of Boeing Service Bulletin 74731A2350, 747-31A2351 or 747-31A2352

L/N 696 thru 1326 and 1328 upon incorporation of Boeing Service Bulletin 747-31A2340, 747-31A2341 or 747-31A2342

L/N 696 thru 1342 upon incorporation of Boeing Service Bulletin 747-31A2350, 74731A2351 or 747-31A2352 configured with EICAS Interface Unit Program Pin 0

Group C (IDS-504 and on)

L/N 1343 and on configured with EICAS Interface Program Pin 1

FUEL LOADING PROCEDURES Fuel loading limitations and procedures are detailed below.

Loading Limitations The following fuel loading limitations must be observed:

Fuel density must be between the minimum allowable fuel density of 6.0 LB/GAL. (0.7190 KG/L) and the maximum allowable fuel density of 7.1 LB/GAL. (0.8507 KG/L). Gross weight may be restricted due to fuel density (refer to CHP-SEC 1-05-xxx for additional information).

Each main tank must contain sufficient fuel for engine start, taxi, takeoff and landing.

When Main Tanks 1 and 4 are not full, and the actual taxi weight is greater than the Maximum Zero Fuel Weight (MZFW), then the required minimum weight of fuel in Main Tanks 1 and 4 plus Reserve Tanks 2 and 3 must equal one-half the difference between the Actual Taxi Weight and the certified MZFW. ( actual taxi weight – MZFW ) Minimum Fuel (Main Tanks 1 and 4 and Reserve Tanks 2 and 3) = ---------------------------------------------------------------------------2

Reserve Tanks 2 and 3 must be full when the actual takeoff weight is above the certified Maximum Fuel Transfer Weight (MFTW) shown in CHP-SEC 1-02-xxx.

Fuel in the center tank is allowed only when all main and reserve tanks are full, except when center tank fuel is considered as payload.

For Group B airplanes, the center tank must contain a minimum of 4000 LB (1814 KG) of fuel if the center tank override/jettison pumps are to be used on the flight. APPLICABLE CONFIGURATIONS

All

1-22-001 Page 1 of 10 Sep 27/2006 D043U544-GPR1


747-400BCF

FUEL MANAGEMENT (Continued) Payload Fuel Payload fuel, or fuel in lieu of payload, is fuel which may be loaded as a substitute for payload. Ballast fuel is fuel in lieu of payload which is specifically loaded for longitudinal balance control. Mission fuel is fuel loaded for normal usage throughout the course of the flight. Fuel considered as payload is exempt from the normal sequence of fuel loading and usage. Fuel may be substituted for payload in any quantity up to an aircraft zero fuel weight of 565000 LB (256279 KG) or the capacity of the tank, provided that the effect on airplane center of gravity is taken into account. Payload fuel may also be burned at the operator’s discretion, subject only to balance considerations. NOTE

When more fuel is carried on a flight than is needed to complete the flight (i.e. tankering fuel), it is preferable to load all of the fuel using the normal fuel loading procedures and land with fuel distribution that would result after following normal fuel usage procedures (i.e. landing with remaining fuel in the main tanks). It is not required or preferred to load this extra fuel in the center tank and consider it as payload fuel. An exception may occur when the quantitiy of tankered fuel and the conditions at the destination may promote frost or ice formation on the upper wing surface.

Ballast Fuel Limitations and procedures for operations with ballast fuel are detailed below.

Ballast fuel is fuel in lieu of payload which is specifically loaded for longitudinal balance control.

The simulatenous loading of ballast and mission fuel in the center tank is not allowed because there is no indication to the flight crew when to turn off the center tank pumps. WARNING FOR GROUP B AIRPLANES, EXTREME CARE SHOULD BE TAKEN IN CARRYING ANY BALLAST FUEL BECAUSE EICAS MESSAGES “FUEL OVD CTR L,R” MAY APPEAR. DO NOT TURN ON THE CENTER TANK PUMPS.

The center tank scavenge system must be deactivated when carrying ballast fuel in the center tank.

Scavenge System The center tank scavenge system is one of three types:

An electric system installed on L/N 696 thru 971. It operates at a rate of approximately 1700 LB (771 KG) per hour for two hours afer the center tank pumps are turned off. If the center tank pumps are turned off when the center tank has approximately 3000 LB (1361 KG), all of this center tank fuel will be scavenged into Main Tank 2 and no fuel should be considered as unusable.

A hydro-mechanical system installed on L/N 972 thru 1320 and 1323. It operates at a rate of approximately 1500 LB (680 KG) per hour when the Main Tanks 2 and 3 are less than 60000 LB (27216 KG) per side and the center tank has less than approximately 3000 LB

1-22-001 Page 2 of 10 Sep 27/2006 D043U544-GPR1



747-400BCF

FUEL MANAGEMENT (Continued) (1361 KG). If the center tank pumps are turned off when the center tank has approximately 3000 LB (1361 KG), it is likely the scavenge pumps will activate but not until later in the flight and some or all of the remaining center tank fuel may not scavenge. In the absence of fleet or individual airplane or route data, the 3000 LB (1361 KG) should be considered unusable. The fuel is scavenged into Main Tanks 2 and 3.

A hydro-mechancial system with the center wing float deactivated or removed on L/N 1321, 1322, and 1324 and on, or by incorporation of Boeing Service Bulletin 747-28-2255. It operates at a rate of approximately 1500 LB (680 KG) per hour when Main Tanks 2 and 3 are less than 60000 LB (27216 KG) per side. If the center tank pumps are turned off when the center tank has approximately 3000 LB (1361 KG), all of this center tank fuel will be scavenged into Main Tank 2 and 3. No fuel should be considered as unusable.

Any of the scavenge systems can be deactivated by following the procedures in the Maintenance Manual Section 12-11-05.

Loading Procedures The 747-400 is equipped with an automatic fuel loading system that will automatically distribute fuel into the appropriate fuel tanks based on the fuel loading procedure listed below. Fuel loading may also be controlled manually. NOTE

The recommended loading procedure reflects the final dispatch fuel distribution, not a loading sequence. Fuel tanks may be loaded individually, simultaneously or in any sequence.

Use the following procedures for loading fuel: 1. Load Main Tanks 1, 2, 3 and 4 equally until Main Tanks 1 and 4 are full. 2. Load Main Tanks 2 and 3 equally until Main Tanks 2 and 3 equal 6500 gallons (24605 liters) per side. 3. Load Reserve Tanks 2 and 3 equally until full. 4. Load Main Tanks 2 and 3 equally until full. 5. Load center tank until full. For Group B airplanes the center tank must contain a minimum of 4000 LB (1814 KG) of fuel if the center tank override/jettison pump(s) are to be used on the flight.


1-22-001 Page 3 of 10 Sep 27/2006 D043U544-GPR1


747-400BCF

FUEL MANAGEMENT (Continued) When the automated fuel loading system is not used, opposite wing tanks should be monitored during the fueling process. Lateral roll must be controlled or fuel may enter the surge tank, which will discontinue fueling. The following wing tank lateral imbalance values should not be exceeded: Reserve Tanks 2 and 3

2000 LB

Main Tanks 1 and 4

6000 LB (2721 KG)

Main Tanks 2 and 3

12000 LB (5443 KG)

NOTE

The automatic fuel loading system will discontinue fueling if any of the above imbalance values are reached during the fuel loading process.

1-22-001 Page 4 of 10 Sep 27/2006 D043U544-GPR1

(907 KG)



747-400BCF

FUEL MANAGEMENT (Continued) Ground Transfer Procedure If a flight is to be made without refueling, and the fuel load does not comply with the fuel load limitations prior to taxi for takeoff, a ground transfer of fuel is required. Follow the procedure described below for ground transfer of fuel 1. Prior to defueling any fuel tanks, perform a lamp test of the respective Fuel Pump Low Pressure indication lights. When defueling, the Fuel Pump Low Pressure indication lights must be monitored and the fuel pumps positioned to “off” at the first indication of fuel pump low pressure. 2. When defueling with passengers on board, fuel pump switches must be selected to “off” at or above 7000 LB (3200 KG) for the center tank or 3000 LB (1400 KG) for each main tank. 3. Open defuel valves and manual valves in the refuel adapters. 4. Turn on any or all pumps in the tank(s) from which fuel is to be transferred. 5. Open associated crossfeed valve when transferring from a main tank. When fuel transfer is complete, turn off all pumps and close fueling, crossfeed, ground transfer valves. WARNING DO NOT OPEN JETTISON NOZZLE VALVES, OR FUEL SPILL WILL RESULT.

WARNING MONITOR THE QUANTITIES IN THE TANKS TO AVOID OVERFILLING THE TANKS AS FUEL IS TRANSFERRED.

LATERAL FUEL IMBALANCE For normal operation, the lateral fuel imbalance between the left and right wing should be scheduled to be 0.0 inch-pounds. If the fuel distribution is not symmetrical, the maximum taxi weight is limited as shown in CHP-SEC 1-04-xxx. The variations in symmetry due to fuel gauging, automatic shut off tolerances, and the effects of airplane ground attitude are considered part of the allowable random imbalance moment, shown in CHP-SEC 1-04-xxx. The following limitations for main tank lateral imbalance apply to all operations except fuel loading:

Lateral fuel imbalance must not exceed 3000 LB (1360 KG) for Main Tanks 1 and 4.

Lateral fuel imbalance must not exceed 6000 LB (2721 KG) for Main Tanks 2 and 3.


1-22-001 Page 5 of 10 Sep 27/2006 D043U544-GPR1


747-400BCF

FUEL MANAGEMENT (Continued) FUEL USAGE PROCEDURES Fuel usage design criteria, recommended fuel usage procedures based on mission length, and fuel usage and transfer rates are detailed below.

Usage Design Criteria The 747-400 is equipped with a semiautomatic fuel usage system which, under normal conditions, will control fuel usage in conformance with the design criteria listed below.

If fuel is available in the center tank and trailing edge flaps are retracted, the fuel feed is center tank to all engines.

If fuel is available in the center tank and trailing edge flaps are extended, the fuel feed is center tank to outboard engines and Main Tanks 2 and 3 to respective inboard engines.

With less than 10000 LB (4535 KG) of fuel in the center tank, no more than 4000 LB (1814 KG) can be consumed from each Main Tank 1 or 4.

If fuel is not available in the center tank and Main Tanks 2 and 3 are greater than Mains 1 and 4, the fuel feed is Main Tanks 2 and 3 to all engines. Each Main Tank 1 and 4 must be no more than 4000 LB (1814 KG) less than full.

Reserve Tanks 2 and 3 must remain full above the Maximum Fuel Transfer Weight shown in CHP-SEC 1-02-xxx.

If Main Tanks 2 and 3 are less than or equal to Main Tanks 1 and 4, fuel feed is main tank to respective engine.

Usage Prior to Taxi The semiautomatic fuel usage system will control valves and pumps based on the fuel usage design criteria described above. Prior to taxi, all crossfeed valves must be operable and open and all fuel pumps in tanks with fuel must be operable and turned on unless otherwise stated. In the following sections, recommended fuel usage is described for long range missions, medium range missions, and short range missions. For these following discussions, fuel is not considered payload.

Usage Procedures for Long Range Missions for Group A Airplanes This long range mission fuel management is defined as all operations with any center tank mission fuel at the start of taxi. 1. Use center tank to all engines for ground operations with the trailing edge flaps retracted. 2. Use center tank to outboard engines and Main Tanks 2 and 3 to respective inboard engines for ground operations with trailing edge flaps in the takeoff range. NOTE

The semiautomatic fuel usage system will automatically close Crossfeed Valves 2 and 3 when the trailing edge flaps are in the takeoff range.

1-22-001 Page 6 of 10 Sep 27/2006 D043U544-GPR1



747-400BCF

FUEL MANAGEMENT (Continued) 3. Use center tank to all engines following takeoff, after the trailing edge flaps have been retracted. NOTE

The semiautomatic fuel usage system will automatically open Crossfeed Valves 2 and 3 when the trailing edge flaps are not in the takeoff range.

4. Continue to use center tank to all engines until the first center tank pump low pressure message is displayed on EICAS. 5. Use Main Tanks 2 and 3 to all engines. NOTES

• The semiautomatic fuel usage system will automatically start the Main Tank 2

and 3 override/jettison pumps when the center tank pump low pressure message is displayed on EICAS. The pilot must manually turn off both center tank pumps. • The semiautomatic fuel system will automatically transfer Reserve Tanks 2 and

3 into Main Tanks 2 and 3 when the fuel in Main Tanks 2 and 3 equals 6000 gallons (22712 liters) per side. 6. Use main tank to respective engine following equalization (i.e. when the fuel in Main Tanks 2 and 3 equals the fuel in Main Tanks 1 and 4). NOTE

At equalization, the EICAS message “FUEL TANK/ENG” appears. The pilot must manually close Crossfeed Valves 1 and 4 and turn off Main Tank 2 and 3 override/ jettison pumps. These actions initiate the Main Tank to respective engine fuel feed.

Landing will occur using the flight fuel feed management in effect at that time.

Usage Procedures for Long Range Missions for Groups B and C Airplanes This long range mission fuel management is defined as all operations with 17000 LB (7711 KG) or more center tank mission fuel at the start of taxi. 1. Use center tank to all engines for ground operations with the trailing edge flaps retracted. 2. Use center tank to outboard engines and Main Tanks 2 and 3 to respective inboard engines for ground operations with trailing edge flaps in the takeoff range. NOTE

The semiautomatic fuel usage system will automatically close Crossfeed Valves 2 and 3 when the trailing edge flaps are in the takeoff range.

3. Use center tank to all engines following takeoff, after the trailing edge flaps have been retracted. NOTE

The semiautomatic fuel usage system will automatically open Crossfeed Valves 2 and 3 when the trailing edge flaps are not in the takeoff range.


1-22-001 Page 7 of 10 Sep 27/2006 D043U544-GPR1


747-400BCF

FUEL MANAGEMENT (Continued) 4. Continue to use center tank fuel to all engines until the low fuel message “FUEL LOW CTR L, R” is indicated on EICAS (there will be approximately 7000 LB (3200 KG) in the center tank if the airplane is in climb attitude or approximately 3000 LB (1400 KG) if the airplane is in cruise attitude). Once in stabilized cruise, all fuel in the center tank that is greater than 3000 LB (1400 KG) must be used. At this point, and with the center tank pumps off to prevent dry running of the pumps, all remaining center tank fuel may be usuable depending upon the scavenge pump configuration. Refer to “Scavenge System” on page 2 for details on the operation of the scavenge system. 5. Use Main Tanks 2 and 3 to all engines. NOTES

• The semiautomatic fuel usage system will automatically start the Main Tank 2

and 3 override/jettison pumps when the center tank pump low pressure message is displayed on EICAS. • The semiautomatic fuel system will automatically transfer Reserve Tanks 2 and

3 into Main Tanks 2 and 3 when the fuel in Main Tanks 2 and 3 equals 6000 gallons (22712 liters) per side. 6. Use main tank to respective engine following equalization (i.e. when the fuel in Main Tanks 2 and 3 equals the fuel in Main Tanks 1 and 4). NOTE

At equalization, the EICAS message “FUEL TANK/ENG” appears. The pilot must manually close Crossfeed Valves 1 and 4 and turn off Main Tank 2 and 3 override/ jettison pumps. These actions initiate the main tank to respective engine fuel feed.


Usage Procedures for Medium Range Missions for Group A Airplanes See below for procedures to be used without center tank fuel and when the quantity in Main Tanks 2 and 3 is greater than the fuel quantity in Main Tanks 1 and 4 at the start of taxi. This medium range mission fuel management is defined as all operations without center tank fuel and when the quantity in Main Tanks 2 and 3 is greater than the fuel quantity in Main Tanks 1 and 4 at the start of taxi. 1. Use Main Tanks 2 and 3 to all engines until equalization (i.e. when the fuel in Main Tanks 2 and 3 equals the fuel in Main Tanks 1 and 4). NOTES

• The semiautomatic fuel usage system will automatically close Crossfeed

Valves 2 and 3 when the trailing edge flaps are in the takeoff range, and open Crossfeed Valves 2 and 3 when the trailing edge flaps are not in the takeoff range. However, fuel feed will continue as Main Tanks 2 and 3 to all engines. • The semiautomatic fuel system will automatically transfer Reserve Tanks 2 and

3 (if fueled) into Main Tanks 2 and 3 when the fuel in Main Tanks 2 and 3 equals 6000 gallons (22712 liters) per side.

1-22-001 Page 8 of 10 Sep 27/2006 D043U544-GPR1



747-400BCF

FUEL MANAGEMENT (Continued) 2. Use main tank to respective engine following equalization (i.e. when the fuel in Main Tanks 2 and 3 equals the fuel in Main Tanks 1 and 4). NOTE

At equalization, the EICAS message “FUEL TANK/ENG” appears. The pilot must manually close Crossfeed Valves 1 and 4 and turn off Main Tank 2 and 3 override/ jettison pumps. These actions initiate the main tank to respective engine fuel feed.


Usage Procedures for Medium Range Missions for Groups B and C Airplanes This medium range mission fuel management is defined as all operations with less than 17000 LB (7711 KG) in the center tank and when the quantity in Main Tanks 2 and 3 is greater than the fuel quantity in Main Tanks 1 and 4 at the start of taxi. For operations without a full wing, all of the fuel in the center tank must be loaded as payload fuel. Refer to “Payload Fuel” on page 2. 1. Use Main Tanks 2 and 3 to all engines until equalization. The center tank pumps must be off for operations with less than 17000 LB (7711 KG) in the center tank for takeoff. NOTES

• The semiautomatic fuel usage system will automatically close Crossfeed

Valves 2 and 3 when the trailing edge flaps are extended, and open Crossfeed Valves 2 and 3 when the trailing edge flaps are retracted. However, fuel feed will continue as Main Tanks 2 and 3 to all engines. • The semiautomatic fuel system will automatically transfer Reserve Tanks 2 and

3 (if fueled) into Main Tanks 2 and 3 when the fuel in Main Tanks 2 and 3 equals 6000 gallons (22712 liters) per side. 2. Once in stabilized cruise, all fuel in the center tank that is greater than 3000 LB (1400 KG) must be used. At this point, and with the center tank pumps off to prevent dry running of the pumps, all remaining center tank fuel may be usable depending on the scavenge system configuration. Refer to “Scavenge System” on page 2 for details on the operation of the scavenge system. 3. Use main tank to respective engine following equalization (i.e. when the fuel in Main Tanks 2 and 3 equals the fuel in Main Tanks 1 and 4). NOTE

At equalization, the EICAS message “FUEL TANK/ENG” appears. The pilot must manually close Crossfeed Valves 1 and 4 and turn off Main Tank 2 and 3 override/ jettison pumps. These actions initiate the Main Tank to respective engine fuel feed.


1-22-001 Page 9 of 10 Sep 27/2006 D043U544-GPR1


747-400BCF

FUEL MANAGEMENT (Continued) Usage Procedures for Short Range Missions The short range mission fuel management is defined for all operations when the quantity in Main Tanks 2 and 3 is equal to or less than the fuel quantity in Main Tanks 1 and 4 at the start of taxi. The Main Tank 2 and 3 override/jettison pumps must be off and Crossfeed Valves 1 and 4 are closed. 1. Use main tank to respective engine for all operations. NOTE

The semiautomatic fuel usage system will automatically close Crossfeed Valves 2 and 3 when the trailing edge flaps are extended, and open Crossfeed Valves 2 and 3 when the trailing edge flaps are retracted. However, fuel feed will continue as main tank to respective engine.


Fuel Usage and Tank Transfer Rates The following values are approximate and should only be used to determine typical fuel usage vectors for weight and balance purposes. The airplane (all engines) fuel usage rate during cruise is approximately 22500 LB/HR (10200 KG/HR) and during climb is approximately 50000 LB/HR (22700 KG/HR). The transfer rate for both Reserve Tanks 2 and 3 equals 45000 LB/HR (20400 KG/HR).

APU FUEL USAGE Fuel consumption should be accounted for during APU operation per instructions in the Operations Manual.

1-22-001 Page 10 of 10 Sep 27/2006 D043U544-GPR1



747-400BCF

FUEL TANK QUANTITIES AND BALANCE ARMS COMBINED MAIN TANKS 1 AND 4 IN U.S. GALLONS The following table provides usable, gauged fuel data in U.S. gallons. For each of the volumes listed, the volume is split equally between Main Tank 1 and Main Tank 4 (for example, the 1000 gallon entry represents 500 gallons in Main Tank 1 and 500 gallons in Main Tank 4, each at B.A. 1425.0 for ground and B.A. 1415.8 for flight). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

U.S. GALLONS COMBINED MAIN TANKS 1 & 4 B.A. INCHES VOLUME U.S. GAL. GROUND FLIGHT

B.B.L. (GROUND)

COMBINED MAIN TANKS 1 & 4 B.A. INCHES VOLUME U.S. GAL. GROUND FLIGHT

B.B.L. (GROUND)

100

1420.4

1422.0

±486.9

2600

1440.9

1425.1

±543.0

200

1418.3

1418.1

±493.2

2700

1441.8

1425.6

±544.5

300

1418.6

1417.1

±496.9

2800

1442.7

1426.2

±545.9

400

1418.9

1416.2

±500.6

2900

1443.6

1426.7

±547.2

500

1420.0

1415.7

±503.8

3000

1444.5

1427.2

±548.5

600

1421.0

1415.2

±507.0

3100

1445.3

1427.8

±549.8

700

1422.0

1415.3

±509.3

3200

1446.2

1428.3

±551.1

800

1423.0

1415.5

±511.7

3300

1447.0

1428.9

±552.4

900

1424.0

1415.6

±514.0

3400

1447.9

1429.4

±553.7

1000

1425.0

1415.8

±516.2

3500

1448.7

1429.9

±555.0

1100

1426.0

1416.3

±518.1

3600

1449.6

1430.4

±556.3

1200

1427.0

1416.8

±520.1

3700

1450.4

1430.9

±557.5

1300

1428.0

1417.4

±522.0

3800

1451.3

1431.5

±558.7

1400

1429.0

1417.9

±523.9

3900

1452.1

1432.0

±559.9

1500

1430.0

1418.5

±525.6

4000

1452.9

1432.5

±561.2

1600

1431.0

1419.1

±527.4

4100

1453.7

1433.0

±562.4

1700

1432.1

1419.7

±529.1

4200

1454.6

1433.5

±563.6

1800

1433.1

1420.3

±530.8

4300

1455.4

1434.2

±564.8

1900

1434.1

1420.9

±532.4

4400

1456.2

1434.8

±566.1

2000

1435.2

1421.5

±534.1

4500

1457.0

1435.6

±567.3

2100

1436.2

1422.1

±535.7

4600

1457.8

1436.4

±568.5

2200

1437.1

1422.7

±537.2

4700

1458.6

1437.1

±569.6

2300

1438.1

1423.3

±538.7

4800

1459.4

1437.9

±570.8

2400

1439.0

1423.9

±540.1

4900

1460.1

1438.7

±572.0

2500

1439.9

1424.5

±541.6

5000

1460.9

1439.4

±573.2


1-24-001 Page 1 of 12 Aug 27/2007 D043U544-GPR1

747-400BCF


FUEL TANK QUANTITIES AND BALANCE ARMS (Continued) U.S. GALLONS (Continued) COMBINED MAIN TANKS 1 & 4 B.A. INCHES

VOLUME U.S. GAL. GROUND

FLIGHT

B.B.L. (GROUND)

COMBINED MAIN TANKS 1 & 4 B.A. INCHES VOLUME U.S. GAL. GROUND FLIGHT

B.B.L. (GROUND)

5100

1461.7

1440.3

±574.3

7600

1478.9

1468.7

±601.8

5200

1462.4

1441.1

±575.5

7700

1479.6

1470.0

±603.0

5300

1463.2

1442.1

±576.7

7800

1480.4

1471.3

±604.2

5400

1464.0

1443.1

±577.8

7900

1481.1

1472.7

±605.4

5500

1464.7

1444.1

±579.0

8000

1481.9

1474.2

±606.6

5600

1465.4

1445.1

±580.1

8100

1482.7

1475.6

±607.8

5700

1466.1

1446.1

±581.1

8200

1483.5

1477.0

±609.0

5800

1466.7

1447.1

±582.2

8300

1484.3

1478.4

±610.3

5900

1467.4

1448.1

±583.3

8400

1485.2

1479.8

±611.6

6000

1468.0

1449.1

±584.3

8500

1486.0

1481.3

±612.9

6100

1468.7

1450.3

±585.4

8600

1486.8

1482.8

±614.2

6200

1469.3

1451.4

±586.4

8700

1487.7

1484.3

±615.6

6300

1470.0

1452.5

±587.5

8800

1488.6

1485.8

±617.0

6400

1470.6

1453.7

±588.6

8900

1489.5

1487.3

±618.4

6500

1471.3

1454.8

±589.6

8964

1490.1

1488.2

±619.4

6600

1471.9

1456.0

±590.7

6700

1472.6

1457.2

±591.8

6800

1473.3

1458.4

±592.9

6900

1474.0

1459.7

±594.0

7000

1474.7

1460.9

±595.1

7100

1475.3

1462.2

±596.2

7200

1476.0

1463.4

±597.3

7300

1476.7

1464.7

±598.4

7400

1477.4

1466.1

±599.5

7500

1478.1

1467.4

±600.6

1-24-001 Page 2 of 12 Aug 27/2007 D043U544-GPR1


747-400BCF


FUEL TANK QUANTITIES AND BALANCE ARMS (Continued) COMBINED MAIN TANKS 1 AND 4 IN LITERS The following table provides usable, gauged fuel data in liters. For each of the volumes listed, the volume is split equally between Main Tank 1 and Main Tank 4 (for example, the 4000 liter entry represents 2000 liters in Main Tank 1 and 2000 liters in Main Tank 4, each at B.A. 1425.5 for ground and B.A. 1416.1 for flight). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

LITERS COMBINED MAIN TANKS 1 & 4 B.A. INCHES

VOLUME L

GROUND

400

1420.2

COMBINED MAIN TANKS 1 & 4 B.A. INCHES

FLIGHT

B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

1421.8

±487.3

12400

1446.8

1428.7

±552.1

800

1418.3

1418.0

±493.6

12800

1447.7

1429.3

±553.4

1200

1418.7

1417.0

±497.5

13200

1448.6

1429.8

±554.8

1600

1419.2

1416.1

±501.4

13600

1449.5

1430.4

±556.2

2000

1420.2

1415.5

±504.7

14000

1450.4

1430.9

±557.5

2400

1421.3

1415.2

±507.8

14400

1451.3

1431.5

±558.8

2800

1422.4

1415.4

±510.3

14800

1452.2

1432.0

±560.0

3200

1423.4

1415.6

±512.7

15200

1453.0

1432.6

±561.3

3600

1424.5

1415.7

±515.1

15600

1453.9

1433.1

±562.6

4000

1425.5

1416.1

±517.3

16000

1454.8

1433.7

±563.9

4400

1426.6

1416.6

±519.3

16400

1455.7

1434.4

±565.2

4800

1427.7

1417.2

±521.3

16800

1456.5

1435.1

±566.5

5200

1428.7

1417.8

±523.4

17200

1457.4

1435.9

±567.8

5600

1429.8

1418.4

±525.2

17600

1458.2

1436.7

±569.1

6000

1430.9

1419.0

±527.1

18000

1459.0

1437.5

±570.3

6400

1432.0

1419.6

±528.9

18400

1459.8

1438.4

±571.5

6800

1433.1

1420.2

±530.7

18800

1460.6

1439.2

±572.8

7200

1434.2

1420.9

±532.5

19200

1461.4

1440.0

±574.0

7600

1435.3

1421.5

±534.2

19600

1462.2

1440.9

±575.2

8000

1436.3

1422.2

±535.9

20000

1463.1

1441.9

±576.5

8400

1437.3

1422.8

±537.5

20400

1463.9

1443.0

±577.7

8800

1438.3

1423.5

±539.0

20800

1464.6

1444.0

±578.9

9200

1439.3

1424.1

±540.6

21200

1465.4

1445.1

±580.1

9600

1440.3

1424.7

±542.1

21600

1466.1

1446.1

±581.2

10000

1441.3

1425.3

±543.6

22000

1466.8

1447.2

±582.3

10400

1442.3

1425.9

±545.2

22400

1467.5

1448.3

±583.4

10800

1443.2

1426.4

±546.6

22800

1468.2

1449.4

±584.6

11200

1444.1

1427.0

±548.0

23200

1468.9

1450.6

±585.7

11600

1445.0

1427.6

±549.3

23600

1469.5

1451.8

±586.8

12000

1445.9

1428.2

±550.7

24000

1470.2

1453.0

±587.9


1-24-001 Page 3 of 12 Aug 27/2007 D043U544-GPR1

747-400BCF


FUEL TANK QUANTITIES AND BALANCE ARMS (Continued) LITERS (Continued) COMBINED MAIN TANKS 1 & 4 B.A. INCHES

VOLUME L

GROUND

24400


FLIGHT

B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

1470.9

1454.2

±589.0

32400

1486.5

1482.2

±613.7

24800

1471.6

1455.4

±590.2

32800

1487.4

1483.7

±615.1

25200

1472.3

1456.7

±591.3

33200

1488.4

1485.3

±616.6

25600

1473.0

1458.0

±592.5

33600

1489.3

1486.9

±618.1

26000

1473.8

1459.3

±593.6

33932

1490.1

1488.2

±619.4

26400

1474.5

1460.6

±594.8

26800

1475.2

1461.9

±596.0

27200

1475.9

1463.3

±597.1

27600

1476.6

1464.6

±598.3

28000

1477.4

1466.0

±599.4

28400

1478.2

1467.4

±600.7

28800

1479.0

1468.8

±601.9

29200

1479.7

1470.2

±603.2

29600

1480.5

1471.6

±604.4

30000

1481.3

1473.1

±605.7

30400

1482.1

1474.6

±606.9

30800

1483.0

1476.1

±608.2

31200

1483.8

1477.6

±609.6

31600

1484.7

1479.1

±610.9

32000

1485.6

1480.6

±612.3

1-24-001 Page 4 of 12 Aug 27/2007 D043U544-GPR1


747-400BCF


FUEL TANK QUANTITIES AND BALANCE ARMS (Continued) COMBINED MAIN TANKS 2 AND 3 IN U.S. GALLONS The following table provides usable, gauged fuel data in U.S. gallons. For each of the volumes listed, the volume is split equally between Main Tank 2 and Main Tank 3 (for example, the 1000 gallon entry represents 500 gallons in Main Tank 2 and 500 gallons in Main Tank 3, each at B.A. 1120.7 for ground and B.A. 1145.9 for flight). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

U.S. GALLONS COMBINED MAIN TANKS 2 & 3 B.A. INCHES


VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

100

1084.3

1148.0

±134.6

2600

1137.3

1152.6

±163.2

200

1096.1

1146.7

±137.5

2700

1138.1

1153.1

±164.0

300

1101.1

1145.9

±139.3

2800

1138.9

1153.5

±164.7

400

1106.1

1145.0

±141.1

2900

1139.6

1154.0

±165.5

500

1109.9

1145.0

±142.7

3000

1140.3

1154.4

±166.2

600

1113.7

1145.1

±144.4

3100

1140.9

1154.9

±166.8

700

1115.5

1145.1

±145.5

3200

1141.5

1155.3

±167.5

800

1117.3

1145.2

±146.7

3300

1142.2

1155.7

±168.1

900

1119.0

1145.5

±147.9

3400

1142.8

1156.2

±168.8

1000

1120.7

1145.9

±149.0

3500

1143.4

1156.6

±169.4

1100

1122.4

1146.3

±150.2

3600

1144.0

1157.0

±170.1

1200

1124.0

1146.6

±151.3

3700

1144.6

1157.5

±170.7

1300

1125.1

1147.0

±152.2

3800

1145.2

1157.9

±171.4

1400

1126.2

1147.3

±153.2

3900

1145.8

1158.3

±172.0

1500

1127.3

1147.7

±154.1

4000

1146.4

1158.7

±172.7

1600

1128.4

1148.2

±155.0

4100

1147.0

1159.1

±173.3

1700

1129.5

1148.6

±155.9

4200

1147.6

1159.6

±174.0

1800

1130.6

1149.1

±156.9

4300

1148.1

1160.0

±174.5

1900

1131.6

1149.5

±157.7

4400

1148.6

1160.4

±175.1

2000

1132.6

1149.9

±158.6

4500

1149.1

1160.8

±175.7

2100

1133.4

1150.4

±159.4

4600

1149.6

1161.2

±176.2

2200

1134.2

1150.8

±160.2

4700

1150.1

1161.7

±176.8

2300

1135.0

1151.3

±160.9

4800

1150.6

1162.1

±177.4

2400

1135.7

1151.7

±161.7

4900

1151.1

1162.5

±178.0

2500

1136.5

1152.2

±162.4

5000

1151.6

1162.9

±178.5


1-24-001 Page 5 of 12 Aug 27/2007 D043U544-GPR1

747-400BCF



VOLUME US GAL.

GROUND

5100


FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

1152.1

1163.2

±179.1

8600

1167.2

1176.0

±196.8

5200

1152.6

1163.6

±179.7

8700

1167.6

1176.3

±197.3

5300

1153.1

1164.0

±180.2

8800

1168.0

1176.6

±197.7

5400

1153.6

1164.4

±180.8

8900

1168.4

1177.0

±198.2

5500

1154.1

1164.8

±181.4

9000

1168.8

1177.3

±198.7

5600

1154.6

1165.2

±181.9

9100

1169.2

1177.6

±199.1

5700

1155.1

1165.6

±182.5

9200

1169.6

1177.9

±199.6

5800

1155.5

1166.0

±183.0

9300

1169.9

1178.3

±200.1

5900

1156.0

1166.3

±183.5

9400

1170.3

1178.6

±200.5

6000

1156.4

1166.7

±184.0

9500

1170.6

1178.9

±200.9

6100

1156.8

1167.1

±184.5

9600

1171.0

1179.3

±201.4

6200

1157.3

1167.5

±185.0

9700

1171.3

1179.6

±201.8

6300

1157.7

1167.9

±185.6

9800

1171.7

1179.9

±202.2

6400

1158.2

1168.3

±186.1

9900

1172.0

1180.2

±202.7

6500

1158.6

1168.6

±186.6

10000

1172.4

1180.6

±203.1

6600

1159.0

1169.0

±187.1

10100

1172.7

1180.9

±203.5

6700

1159.5

1169.3

±187.6

10200

1173.1

1181.2

±204.0

6800

1159.9

1169.7

±188.1

10300

1173.5

1181.5

±204.4

6900

1160.4

1170.0

±188.6

10400

1173.8

1181.8

±204.8

7000

1160.8

1170.4

±189.2

10500

1174.2

1182.1

±205.2

7100

1161.2

1170.8

±189.7

10600

1174.5

1182.5

±205.7

7200

1161.7

1171.1

±190.2

10700

1174.9

1182.8

±206.1

7300

1162.1

1171.5

±190.7

10800

1175.2

1183.1

±206.5

7400

1162.5

1171.8

±191.2

10900

1175.6

1183.4

±207.0

7500

1162.9

1172.2

±191.6

11000

1175.9

1183.7

±207.4

7600

1163.3

1172.5

±192.1

11100

1176.3

1184.0

±207.8

7700

1163.7

1172.9

±192.6

11200

1176.6

1184.3

±208.3

7800

1164.1

1173.2

±193.0

11300

1177.0

1184.6

±208.7

7900

1164.5

1173.6

±193.5

11400

1177.3

1184.9

±209.1

8000

1164.9

1174.0

±194.0

11500

1177.7

1185.2

±209.6

8100

1165.3

1174.3

±194.5

11600

1178.0

1185.5

±210.0

8200

1165.6

1174.7

±194.9

11700

1178.3

1185.8

±210.4

8300

1166.0

1175.0

±195.4

11800

1178.7

1186.1

±210.8

8400

1166.4

1175.3

±195.9

11900

1179.0

1186.4

±211.2

8500

1166.8

1175.6

±196.3

12000

1179.3

1186.7

±211.6

1-24-001 Page 6 of 12 Aug 27/2007 D043U544-GPR1


747-400BCF



VOLUME US GAL.

GROUND

12100


FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

1179.7

1187.0

±212.0

15600

1190.8

1196.6

±226.2

12200

1180.0

1187.3

±212.4

15700

1191.1

1196.8

±226.6

12300

1180.3

1187.6

±212.8

15800

1191.4

1197.1

±227.0

12400

1180.6

1187.9

±213.2

15900

1191.7

1197.3

±227.4

12500

1181.0

1188.2

±213.6

16000

1192.0

1197.6

±227.8

12600

1181.3

1188.5

±214.0

16100

1192.4

1197.9

±228.2

12700

1181.6

1188.8

±214.5

16200

1192.7

1198.1

±228.6

12800

1182.0

1189.1

±214.9

16300

1193.0

1198.4

±229.0

12900

1182.3

1189.3

±215.3

16400

1193.3

1198.6

±229.4

13000

1182.6

1189.6

±215.7

16500

1193.6

1198.9

±229.8

13100

1182.9

1189.9

±216.1

16600

1193.9

1199.1

±230.2

13200

1183.3

1190.2

±216.5

16700

1194.2

1199.4

±230.6

13300

1183.6

1190.4

±216.9

16800

1194.4

1199.6

±230.9

13400

1183.9

1190.7

±217.3

16900

1194.7

1199.9

±231.3

13500

1184.2

1191.0

±217.7

17000

1194.9

1200.1

±231.7

13600

1184.6

1191.3

±218.1

17100

1195.2

1200.4

±232.0

13700

1184.9

1191.5

±218.5

17200

1195.4

1200.6

±232.4

13800

1185.2

1191.8

±218.9

17300

1195.7

1200.9

±232.8

13900

1185.6

1192.1

±219.3

17400

1195.9

1201.1

±233.1

14000

1185.9

1192.4

±219.7

17500

1196.1

1201.4

±233.5

14100

1186.2

1192.6

±220.1

17600

1196.4

1201.6

±233.8

14200

1186.5

1192.9

±220.6

17700

1196.6

1201.8

±234.2

14300

1186.8

1193.2

±221.0

17800

1196.9

1202.0

±234.6

14400

1187.1

1193.5

±221.4

17900

1197.1

1202.2

±234.9

14500

1187.4

1193.7

±221.8

18000

1197.4

1202.4

±235.3

14600

1187.7

1194.0

±222.2

18100

1197.6

1202.6

±235.7

14700

1188.0

1194.3

±222.6

18200

1197.9

1202.8

±236.0

14800

1188.3

1194.5

±223.0

18300

1198.1

1203.0

±236.4

14900

1188.7

1194.8

±223.4

18400

1198.4

1203.2

±236.7

15000

1189.0

1195.1

±223.8

18500

1198.6

1203.4

±237.1

15100

1189.3

1195.3

±224.2

18600

1198.9

1203.6

±237.5

15200

1189.6

1195.6

±224.6

18700

1199.1

1203.8

±237.8

15300

1189.9

1195.8

±225.0

18800

1199.4

1204.0

±238.2

15400

1190.2

1196.1

±225.4

18900

1199.6

1204.2

±238.5

15500

1190.5

1196.3

±225.8

19000

1199.9

1204.4

±238.9


1-24-001 Page 7 of 12 Aug 27/2007 D043U544-GPR1

747-400BCF



VOLUME US GAL.

GROUND

19100


FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

1200.1

1204.5

±239.3

22600

1206.9

1210.1

±250.6

19200

1200.4

1204.7

±239.6

22700

1207.0

1210.2

±250.9

19300

1200.6

1204.9

±240.0

22800

1207.2

1210.4

±251.3

19400

1200.8

1205.1

±240.3

22900

1207.4

1210.5

±251.6

19500

1201.0

1205.3

±240.6

23000

1207.5

1210.6

±251.9

19600

1201.2

1205.5

±241.0

23100

1207.7

1210.7

±252.2

19700

1201.4

1205.7

±241.3

23200

1207.9

1210.8

±252.5

19800

1201.6

1205.9

±241.6

23300

1208.0

1210.9

±252.9

19900

1201.8

1206.1

±241.9

23400

1208.2

1211.1

±253.2

20000

1202.0

1206.3

±242.3

23500

1208.4

1211.2

±253.5

20100

1202.2

1206.5

±242.6

23600

1208.6

1211.3

±253.8

20200

1202.4

1206.6

±242.9

23700

1208.7

1211.4

±254.1

20300

1202.6

1206.8

±243.2

23800

1208.9

1211.5

±254.5

20400

1202.8

1206.9

±243.5

23900

1209.1

1211.6

±254.9

20500

1203.0

1207.1

±243.9

24000

1209.4

1211.8

±255.3

20600

1203.2

1207.2

±244.2

24100

1209.7

1211.9

±255.8

20700

1203.4

1207.4

±244.5

24200

1209.9

1212.0

±256.2

20800

1203.6

1207.5

±244.8

24300

1210.2

1212.1

±256.7

20900

1203.8

1207.7

±245.1

24400

1210.5

1212.3

±257.1

21000

1204.0

1207.8

±245.5

24500

1210.7

1212.4

±257.6

21100

1204.1

1208.0

±245.8

24600

1211.0

1212.6

±258.0

21200

1204.3

1208.1

±246.1

24700

1211.3

1212.7

±258.5

21300

1204.5

1208.3

±246.4

24800

1211.6

1212.8

±258.9

21400

1204.7

1208.4

±246.8

24900

1211.8

1213.0

±259.4

21500

1204.9

1208.6

±247.1

25000

1212.1

1213.1

±259.8

21600

1205.1

1208.7

±247.4

25092

1212.3

1213.2

±260.2

21700

1205.3

1208.9

±247.7

21800

1205.5

1209.0

±248.0

21900

1205.7

1209.2

±248.4

22000

1205.8

1209.3

±248.7

22100

1206.0

1209.5

±249.0

22200

1206.2

1209.6

±249.3

22300

1206.4

1209.8

±249.7

22400

1206.5

1209.9

±250.0

22500

1206.7

1210.0

±250.3

1-24-001 Page 8 of 12 Aug 27/2007 D043U544-GPR1


747-400BCF




COMBINED MAIN TANKS 2 & 3 B.A. INCHES VOLUME L GROUND FLIGHT

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

B.B.L. (GROUND)

400

1085.0

1147.9

±134.7

12400

1142.0

1155.6

±168.0

800

1096.7

1146.6

±137.7

12800

1142.6

1156.1

±168.7

1200

1101.9

1145.7

±139.6

13200

1143.3

1156.6

±169.4

1600

1106.9

1145.0

±141.5

13600

1143.9

1157.0

±170.0

2000

1111.0

1145.1

±143.2

14000

1144.6

1157.5

±170.7

2400

1114.3

1145.1

±144.8

14400

1145.2

1157.9

±171.4

2800

1116.2

1145.2

±146.0

14800

1145.9

1158.3

±172.1

3200

1118.1

1145.4

±147.2

15200

1146.5

1158.8

±172.8

3600

1119.9

1145.7

±148.5

15600

1147.1

1159.2

±173.5

4000

1121.7

1146.1

±149.7

16000

1147.7

1159.7

±174.1

4400

1123.4

1146.5

±150.9

16400

1148.2

1160.1

±174.7

4800

1124.8

1146.9

±151.9

16800

1148.8

1160.6

±175.3

5200

1125.9

1147.2

±152.9

17200

1149.3

1161.0

±175.9

5600

1127.1

1147.7

±153.9

17600

1149.8

1161.4

±176.5

6000

1128.2

1148.1

±154.9

18000

1150.4

1161.9

±177.1

6400

1129.4

1148.6

±155.8

18400

1150.9

1162.3

±177.7

6800

1130.5

1149.0

±156.8

18800

1151.4

1162.7

±178.3

7200

1131.6

1149.5

±157.8

19200

1152.0

1163.1

±178.9

7600

1132.7

1150.0

±158.7

19600

1152.5

1163.5

±179.5

8000

1133.5

1150.4

±159.5

20000

1153.0

1164.0

±180.1

8400

1134.3

1150.9

±160.3

20400

1153.6

1164.4

±180.7

8800

1135.1

1151.4

±161.1

20800

1154.1

1164.8

±181.3

9200

1136.0

1151.9

±161.9

21200

1154.6

1165.2

±181.9

9600

1136.8

1152.3

±162.7

21600

1155.1

1165.6

±182.5

10000

1137.6

1152.8

±163.5

22000

1155.6

1166.0

±183.0

10400

1138.4

1153.3

±164.3

22400

1156.0

1166.4

±183.6

10800

1139.2

1153.7

±165.1

22800

1156.5

1166.8

±184.1

11200

1140.0

1154.2

±165.9

23200

1157.0

1167.2

±184.7

11600

1140.7

1154.7

±166.6

23600

1157.4

1167.6

±185.2

12000

1141.4

1155.2

±167.3

24000

1157.9

1168.0

±185.8


1-24-001 Page 9 of 12 Aug 27/2007 D043U544-GPR1

747-400BCF




B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

24400

1158.4

1168.4

±186.3

38400

1172.9

1181.0

±203.7

24800

1158.8

1168.8

±186.8

38800

1173.3

1181.4

±204.2

25200

1159.3

1169.2

±187.4

39200

1173.7

1181.7

±204.6

25600

1159.8

1169.5

±187.9

39600

1174.0

1182.0

±205.1

26000

1160.2

1169.9

±188.5

40000

1174.4

1182.3

±205.5

26400

1160.7

1170.3

±189.0

40400

1174.8

1182.7

±206.0

26800

1161.2

1170.7

±189.6

40800

1175.1

1183.0

±206.4

27200

1161.6

1171.1

±190.1

41200

1175.5

1183.3

±206.9

27600

1162.1

1171.4

±190.6

41600

1175.9

1183.6

±207.4

28000

1162.5

1171.8

±191.2

42000

1176.3

1184.0

±207.8

28400

1162.9

1172.2

±191.6

42400

1176.6

1184.3

±208.3

28800

1163.3

1172.6

±192.1

42800

1177.0

1184.6

±208.7

29200

1163.7

1172.9

±192.6

43200

1177.4

1184.9

±209.2

29600

1164.2

1173.3

±193.1

43600

1177.7

1185.2

±209.6

30000

1164.6

1173.7

±193.6

44000

1178.1

1185.6

±210.1

30400

1165.0

1174.1

±194.1

44400

1178.4

1185.9

±210.5

30800

1165.4

1174.4

±194.6

44800

1178.8

1186.2

±210.9

31200

1165.8

1174.8

±195.1

45200

1179.1

1186.5

±211.4

31600

1166.2

1175.1

±195.6

45600

1179.5

1186.9

±211.8

32000

1166.6

1175.5

±196.1

46000

1179.8

1187.2

±212.2

32400

1167.0

1175.8

±196.6

46400

1180.2

1187.5

±212.6

32800

1167.5

1176.2

±197.1

46800

1180.5

1187.8

±213.1

33200

1167.9

1176.5

±197.6

47200

1180.9

1188.1

±213.5

33600

1168.3

1176.9

±198.1

47600

1181.2

1188.4

±213.9

34000

1168.7

1177.2

±198.6

48000

1181.6

1188.7

±214.4

34400

1169.1

1177.6

±199.1

48400

1181.9

1189.0

±214.8

34800

1169.5

1177.9

±199.6

48800

1182.2

1189.3

±215.2

35200

1169.9

1178.3

±200.0

49200

1182.6

1189.6

±215.7

35600

1170.3

1178.6

±200.5

49600

1182.9

1189.9

±216.1

36000

1170.7

1179.0

±201.0

50000

1183.3

1190.2

±216.5

36400

1171.0

1179.3

±201.4

50400

1183.6

1190.5

±217.0

36800

1171.4

1179.7

±201.9

50800

1184.0

1190.8

±217.4

37200

1171.8

1180.0

±202.3

51200

1184.3

1191.0

±217.8

37600

1172.2

1180.3

±202.8

51600

1184.7

1191.3

±218.2

38000

1172.5

1180.7

±203.2

52000

1185.0

1191.6

±218.7

1-24-001 Page 10 of 12 Aug 27/2007 D043U544-GPR1


747-400BCF




B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

52400

1185.4

1191.9

±219.1

66400

1196.2

1201.5

±233.6

52800

1185.7

1192.2

±219.5

66800

1196.5

1201.7

±234.0

53200

1186.0

1192.5

±220.0

67200

1196.8

1201.9

±234.4

53600

1186.4

1192.8

±220.4

67600

1197.0

1202.1

±234.8

54000

1186.7

1193.1

±220.8

68000

1197.3

1202.3

±235.2

54400

1187.0

1193.4

±221.2

68400

1197.6

1202.5

±235.5

54800

1187.3

1193.7

±221.7

68800

1197.8

1202.7

±235.9

55200

1187.7

1193.9

±222.1

69200

1198.1

1202.9

±236.3

55600

1188.0

1194.2

±222.5

69600

1198.4

1203.1

±236.7

56000

1188.3

1194.5

±222.9

70000

1198.6

1203.3

±237.1

56400

1188.6

1194.8

±223.4

70400

1198.9

1203.6

±237.5

56800

1189.0

1195.1

±223.8

70800

1199.1

1203.8

±237.8

57200

1189.3

1195.4

±224.2

71200

1199.4

1204.0

±238.2

57600

1189.6

1195.6

±224.6

71600

1199.7

1204.2

±238.6

58000

1189.9

1195.9

±225.1

72000

1199.9

1204.4

±239.0

58400

1190.3

1196.2

±225.5

72400

1200.2

1204.6

±239.4

58800

1190.6

1196.4

±225.9

72800

1200.5

1204.8

±239.7

59200

1190.9

1196.7

±226.3

73200

1200.7

1205.0

±240.1

59600

1191.3

1197.0

±226.8

73600

1200.9

1205.2

±240.4

60000

1191.6

1197.2

±227.2

74000

1201.1

1205.4

±240.8

60400

1191.9

1197.5

±227.6

74400

1201.3

1205.6

±241.1

60800

1192.2

1197.8

±228.0

74800

1201.5

1205.8

±241.5

61200

1192.6

1198.0

±228.5

75200

1201.7

1206.0

±241.8

61600

1192.9

1198.3

±228.9

75600

1201.9

1206.3

±242.2

62000

1193.2

1198.5

±229.3

76000

1202.2

1206.4

±242.5

62400

1193.5

1198.8

±229.7

76400

1202.4

1206.6

±242.8

62800

1193.9

1199.1

±230.2

76800

1202.6

1206.8

±243.2

63200

1194.1

1199.3

±230.6

77200

1202.8

1206.9

±243.5

63600

1194.4

1199.6

±230.9

77600

1203.0

1207.1

±243.9

64000

1194.7

1199.9

±231.3

78000

1203.2

1207.2

±244.2

64400

1194.9

1200.1

±231.7

78400

1203.4

1207.4

±244.5

64800

1195.2

1200.4

±232.1

78800

1203.6

1207.6

±244.9

65200

1195.5

1200.7

±232.5

79200

1203.8

1207.7

±245.2

65600

1195.7

1200.9

±232.9

79600

1204.0

1207.9

±245.6

66000

1196.0

1201.2

±233.2

80000

1204.2

1208.0

±245.9


1-24-001 Page 11 of 12 Aug 27/2007 D043U544-GPR1

747-400BCF




B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

80400

1204.4

1208.2

±246.2

90400

1209.1

1211.6

±254.8

80800

1204.6

1208.4

±246.6

90800

1209.4

1211.7

±255.3

81200

1204.8

1208.5

±246.9

91200

1209.6

1211.9

±255.7

81600

1205.0

1208.7

±247.3

91600

1209.9

1212.0

±256.2

82000

1205.2

1208.8

±247.6

92000

1210.2

1212.2

±256.7

82400

1205.4

1209.0

±247.9

92400

1210.5

1212.3

±257.2

82800

1205.6

1209.1

±248.3

92800

1210.8

1212.4

±257.6

83200

1205.8

1209.3

±248.6

93200

1211.1

1212.6

±258.1

83600

1206.0

1209.5

±249.0

93600

1211.4

1212.7

±258.6

84000

1206.2

1209.6

±249.3

94000

1211.6

1212.9

±259.1

84400

1206.3

1209.8

±249.6

94400

1211.9

1213.0

±259.5

84800

1206.5

1209.9

±250.0

94800

1212.2

1213.2

±260.0

85200

1206.7

1210.0

±250.3

94984

1212.3

1213.2

±260.2

85600

1206.9

1210.1

±250.7

86000

1207.1

1210.3

±251.0

86400

1207.2

1210.4

±251.3

86800

1207.4

1210.5

±251.7

87200

1207.6

1210.6

±252.0

87600

1207.8

1210.8

±252.4

88000

1208.0

1210.9

±252.7

88400

1208.1

1211.0

±253.0

88800

1208.3

1211.1

±253.4

89200

1208.5

1211.2

±253.7

89600

1208.7

1211.4

±254.0

90000

1208.8

1211.5

±254.4

1-24-001 Page 12 of 12 Aug 27/2007 D043U544-GPR1


747-400BCF


FUEL TANK QUANTITIES AND BALANCE ARMS COMBINED MAIN TANKS 1 AND 4 IN U.S. GALLONS The following table provides usable, gauged fuel data in U.S. gallons. For each of the volumes listed, the volume is split equally between Main Tank 1 and Main Tank 4 (for example, the 1000 gallon entry represents 500 gallons in Main Tank 1 and 500 gallons in Main Tank 4, each at B.A. 1425.0 for ground and B.A. 1415.8 for flight). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.


VOLUME U.S. GAL. GROUND

FLIGHT

B.B.L. (GROUND)

B.A. INCHES VOLUME U.S. GAL GROUND FLIGHT

B.B.L. (GROUND)

100

1420.4

1422.0

±486.9

2600

1440.9

1425.1

±543.0

200

1418.3

1418.1

±493.2

2700

1441.8

1425.6

±544.5

300

1418.6

1417.1

±496.9

2800

1442.7

1426.2

±545.9

400

1418.9

1416.2

±500.6

2900

1443.6

1426.7

±547.2

500

1420.0

1415.7

±503.8

3000

1444.5

1427.2

±548.5

600

1421.0

1415.2

±507.0

3100

1445.3

1427.8

±549.8

700

1422.0

1415.3

±509.3

3200

1446.2

1428.3

±551.1

800

1423.0

1415.5

±511.7

3300

1447.0

1428.9

±552.4

900

1424.0

1415.6

±514.0

3400

1447.9

1429.4

±553.7

1000

1425.0

1415.8

±516.2

3500

1448.7

1429.9

±555.0

1100

1426.0

1416.3

±518.1

3600

1449.6

1430.4

±556.3

1200

1427.0

1416.8

±520.1

3700

1450.4

1430.9

±557.5

1300

1428.0

1417.4

±522.0

3800

1451.3

1431.5

±558.7

1400

1429.0

1417.9

±523.9

3900

1452.1

1432.0

±559.9

1500

1430.0

1418.5

±525.6

4000

1452.9

1432.5

±561.2

1600

1431.0

1419.1

±527.4

4100

1453.7

1433.0

±562.4

1700

1432.1

1419.7

±529.1

4200

1454.6

1433.5

±563.6

1800

1433.1

1420.3

±530.8

4300

1455.4

1434.2

±564.8

1900

1434.1

1420.9

±532.4

4400

1456.2

1434.8

±566.1

2000

1435.2

1421.5

±534.1

4500

1457.0

1435.6

±567.3

2100

1436.2

1422.1

±535.7

4600

1457.8

1436.4

±568.5

2200

1437.1

1422.7

±537.2

4700

1458.6

1437.1

±569.6

2300

1438.1

1423.3

±538.7

4800

1459.3

1437.9

±570.8

2400

1439.0

1423.9

±540.1

4900

1460.1

1438.7

±571.9

2500

1439.9

1424.5

±541.6

5000

1460.8

1439.4

±573.1


COMBINED MAIN TANKS 1 & 4

1-24-002 Page 1 of 12 Aug 23/2007 D043U544-GPR1

747-400BCF


FUEL TANK QUANTITIES AND BALANCE ARMS (Continued) U.S. GALLONS (Continued) COMBINED MAIN TANKS 1 & 4 B.A. INCHES VOLUME U.S. GAL. GROUND FLIGHT

B.B.L. (GROUND)

COMBINED MAIN TANKS 1 & 4 B.A. INCHES VOLUME U.S. GAL GROUND FLIGHT

B.B.L. (GROUND)

5100

1461.6

1440.3

±574.2

7600

1478.3

1468.7

±600.6

5200

1462.3

1441.1

±575.4

7700

1479.0

1470.0

±601.8

5300

1463.1

1442.1

±576.5

7800

1479.8

1471.3

±602.9

5400

1463.9

1443.1

±577.6

7900

1480.5

1472.8

±604.1

5500

1464.6

1444.1

±578.7

8000

1481.2

1474.2

±605.2

5600

1465.3

1445.1

±579.8

8100

1482.1

1475.6

±606.5

5700

1465.9

1446.1

±580.8

8200

1482.9

1477.0

±607.8

5800

1466.5

1447.1

±581.9

8300

1483.8

1478.6

±609.1

5900

1467.1

1448.1

±582.9

8400

1484.6

1480.2

±610.4

6000

1467.8

1449.1

±583.9

8500

1485.5

1481.7

±611.7

6100

1468.4

1450.3

±584.9

8600

1486.4

1483.3

±613.1

6200

1469.0

1451.4

±585.9

8700

1487.3

1485.0

±614.5

6300

1469.6

1452.5

±586.9

8744

1487.7

1485.7

±615.1

6400

1470.3

1453.7

±587.9

6500

1470.9

1454.8

±588.9

6600

1471.5

1456.0

±590.0

6700

1472.2

1457.2

±591.0

6800

1472.8

1458.4

±592.1

6900

1473.5

1459.7

±593.1

7000

1474.1

1460.9

±594.1

7100

1474.8

1462.2

±595.2

7200

1475.4

1463.4

±596.2

7300

1476.1

1464.7

±597.3

7400

1476.8

1466.0

±598.4

7500

1477.5

1467.3

±599.5

1-24-002 Page 2 of 12 Aug 23/2007 D043U544-GPR1


747-400BCF




B.A. INCHES VOLUME L GROUND FLIGHT

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

400

1420.2

1421.8

±487.3

12400

1446.8

1428.7

±552.1

800

1418.3

1418.0

±493.6

12800

1447.7

1429.3

±553.4

1200

1418.7

1417.0

±497.5

13200

1448.6

1429.8

±554.8

1600

1419.2

1416.1

±501.4

13600

1449.5

1430.4

±556.2

2000

1420.2

1415.5

±504.7

14000

1450.4

1430.9

±557.5

2400

1421.3

1415.2

±507.8

14400

1451.3

1431.5

±558.7

2800

1422.4

1415.4

±510.3

14800

1452.2

1432.0

±560.0

3200

1423.4

1415.6

±512.7

15200

1453.0

1432.6

±561.3

3600

1424.5

1415.7

±515.1

15600

1453.9

1433.1

±562.6

4000

1425.5

1416.1

±517.3

16000

1454.8

1433.7

±563.9

4400

1426.6

1416.6

±519.3

16400

1455.6

1434.4

±565.2

4800

1427.7

1417.2

±521.3

16800

1456.5

1435.1

±566.5

5200

1428.7

1417.8

±523.4

17200

1457.4

1435.9

±567.8

5600

1429.8

1418.4

±525.2

17600

1458.2

1436.7

±569.0

6000

1430.9

1419.0

±527.1

18000

1459.0

1437.5

±570.2

6400

1432.0

1419.6

±528.9

18400

1459.8

1438.4

±571.4

6800

1433.1

1420.2

±530.7

18800

1460.6

1439.2

±572.7

7200

1434.2

1420.9

±532.5

19200

1461.4

1440.0

±573.9

7600

1435.3

1421.5

±534.2

19600

1462.2

1440.9

±575.1

8000

1436.3

1422.2

±535.9

20000

1463.0

1441.9

±576.3

8400

1437.3

1422.8

±537.5

20400

1463.8

1443.0

±577.5

8800

1438.3

1423.5

±539.0

20800

1464.5

1444.0

±578.7

9200

1439.3

1424.1

±540.6

21200

1465.3

1445.1

±579.8

9600

1440.3

1424.7

±542.1

21600

1465.9

1446.1

±580.9

10000

1441.3

1425.3

±543.6

22000

1466.6

1447.2

±582.0

10400

1442.3

1425.9

±545.2

22400

1467.2

1448.3

±583.0

B.B.L. (GROUND)

10800

1443.2

1426.4

±546.6

22800

1467.9

1449.4

±584.1

11200

1444.1

1427.0

±548.0

23200

1468.6

1450.6

±585.2

11600

1445.0

1427.6

±549.3

23600

1469.2

1451.8

±586.2

12000

1445.9

1428.2

±550.7

24000

1469.9

1453.0

±587.3



1-24-002 Page 3 of 12 Aug 23/2007 D043U544-GPR1

747-400BCF




B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

24400

1470.5

1454.2

±588.4

30400

1481.5

1474.6

±605.6

24800

1471.2

1455.4

±589.5

30800

1482.4

1476.1

±607.0

25200

1471.9

1456.7

±590.6

31200

1483.3

1477.7

±608.3

25600

1472.6

1458.0

±591.7

31600

1484.2

1479.3

±609.7

26000

1473.3

1459.3

±592.8

32000

1485.1

1481.0

±611.1

26400

1474.0

1460.6

±593.9

32400

1486.0

1482.7

±612.6

26800

1474.7

1461.9

±595.0

32800

1487.0

1484.4

±614.0

27200

1475.3

1463.2

±596.0

33100

1487.7

1485.7

±615.1

27600

1476.1

1464.6

±597.2

28000

1476.8

1466.0

±598.3

28400

1477.6

1467.4

±599.5

28800

1478.3

1468.8

±600.7

29200

1479.1

1470.2

±601.9

29600

1479.9

1471.6

±603.2

30000

1480.7

1473.1

±604.4

1-24-002 Page 4 of 12 Aug 23/2007 D043U544-GPR1


747-400BCF


FUEL TANK QUANTITIES AND BALANCE ARMS (Continued) COMBINED MAIN TANKS 2 AND 3 IN U.S. GALLONS The following table provides usable, gauged fuel data in U.S. gallons. For each of the volumes listed, the volume is split equally between Main Tank 2 and Main Tank 3 (for example, the 1000 gallon entry represents 500 gallons in Main Tank 2 and 500 gallons in Main Tank 3, each at B.A. 1120.7 for ground and B.A. 1145.9 for flight). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.


B.A. INCHES

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

100

1084.3

1148.0

±134.6

2600

1137.3

1152.6

±163.2

200

1096.1

1146.7

±137.5

2700

1138.1

1153.1

±164.0

300

1101.1

1145.9

±139.3

2800

1138.9

1153.5

±164.7

400

1106.1

1145.0

±141.1

2900

1139.6

1154.0

±165.5

500

1109.9

1145.0

±142.7

3000

1140.3

1154.4

±166.2

600

1113.7

1145.1

±144.4

3100

1140.9

1154.9

±166.8

700

1115.5

1145.1

±145.5

3200

1141.5

1155.3

±167.5

800

1117.3

1145.2

±146.7

3300

1142.2

1155.7

±168.1

900

1119.0

1145.5

±147.9

3400

1142.8

1156.2

±168.8

1000

1120.7

1145.9

±149.0

3500

1143.4

1156.6

±169.4

1100

1122.4

1146.3

±150.2

3600

1144.0

1157.0

±170.1

1200

1124.0

1146.6

±151.3

3700

1144.6

1157.5

±170.7

1300

1125.1

1147.0

±152.2

3800

1145.2

1157.9

±171.4

1400

1126.2

1147.3

±153.2

3900

1145.8

1158.3

±172.0

1500

1127.3

1147.7

±154.1

4000

1146.4

1158.7

±172.7

1600

1128.4

1148.2

±155.0

4100

1147.0

1159.1

±173.3

1700

1129.5

1148.6

±155.9

4200

1147.6

1159.6

±174.0

1800

1130.6

1149.1

±156.9

4300

1148.1

1160.0

±174.5

1900

1131.6

1149.5

±157.7

4400

1148.6

1160.4

±175.1

2000

1132.6

1149.9

±158.6

4500

1149.1

1160.8

±175.7

2100

1133.4

1150.4

±159.4

4600

1149.6

1161.2

±176.2

2200

1134.2

1150.8

±160.2

4700

1150.1

1161.7

±176.8

2300

1135.0

1151.3

±160.9

4800

1150.6

1162.1

±177.4

2400

1135.7

1151.7

±161.7

4900

1151.1

1162.5

±178.0

2500

1136.5

1152.2

±162.4

5000

1151.6

1162.9

±178.5



1-24-002 Page 5 of 12 Aug 23/2007 D043U544-GPR1

747-400BCF



VOLUME US GAL.

GROUND

5100


FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

1152.1

1163.2

±179.1

8600

1167.2

1176.0

±196.8

5200

1152.6

1163.6

±179.7

8700

1167.6

1176.3

±197.3

5300

1153.1

1164.0

±180.2

8800

1168.0

1176.6

±197.7

5400

1153.6

1164.4

±180.8

8900

1168.4

1177.0

±198.2

5500

1154.1

1164.8

±181.4

9000

1168.8

1177.3

±198.7

5600

1154.6

1165.2

±181.9

9100

1169.2

1177.6

±199.1

5700

1155.1

1165.6

±182.5

9200

1169.6

1177.9

±199.6

5800

1155.5

1166.0

±183.0

9300

1169.9

1178.3

±200.1

5900

1156.0

1166.3

±183.5

9400

1170.3

1178.6

±200.5

6000

1156.4

1166.7

±184.0

9500

1170.6

1178.9

±200.9

6100

1156.8

1167.1

±184.5

9600

1171.0

1179.3

±201.4

6200

1157.3

1167.5

±185.0

9700

1171.3

1179.6

±201.8

6300

1157.7

1167.9

±185.6

9800

1171.7

1179.9

±202.2

6400

1158.2

1168.3

±186.1

9900

1172.0

1180.2

±202.7

6500

1158.6

1168.6

±186.6

10000

1172.4

1180.6

±203.1

6600

1159.0

1169.0

±187.1

10100

1172.7

1180.9

±203.5

6700

1159.5

1169.3

±187.6

10200

1173.1

1181.2

±204.0

6800

1159.9

1169.7

±188.1

10300

1173.5

1181.5

±204.4

6900

1160.4

1170.0

±188.6

10400

1173.8

1181.8

±204.8

7000

1160.8

1170.4

±189.2

10500

1174.2

1182.1

±205.2

7100

1161.2

1170.8

±189.7

10600

1174.5

1182.5

±205.7

7200

1161.7

1171.1

±190.2

10700

1174.9

1182.8

±206.1

7300

1162.1

1171.5

±190.7

10800

1175.2

1183.1

±206.5

7400

1162.5

1171.8

±191.2

10900

1175.6

1183.4

±207.0

7500

1162.9

1172.2

±191.6

11000

1175.9

1183.7

±207.4

7600

1163.3

1172.5

±192.1

11100

1176.3

1184.0

±207.8

7700

1163.7

1172.9

±192.6

11200

1176.6

1184.3

±208.3

7800

1164.1

1173.2

±193.0

11300

1177.0

1184.6

±208.7

7900

1164.5

1173.6

±193.5

11400

1177.3

1184.9

±209.1

8000

1164.9

1174.0

±194.0

11500

1177.7

1185.2

±209.6

8100

1165.3

1174.3

±194.5

11600

1178.0

1185.5

±210.0

8200

1165.6

1174.7

±194.9

11700

1178.3

1185.8

±210.4

8300

1166.0

1175.0

±195.4

11800

1178.7

1186.1

±210.8

8400

1166.4

1175.3

±195.9

11900

1179.0

1186.4

±211.2

8500

1166.8

1175.6

±196.3

12000

1179.3

1186.7

±211.6

1-24-002 Page 6 of 12 Aug 23/2007 D043U544-GPR1


747-400BCF



VOLUME US GAL.

GROUND

12100

B.A. INCHES

FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

1179.7

1187.0

±212.0

15600

1190.8

1196.6

±226.2

12200

1180.0

1187.3

±212.4

15700

1191.1

1196.8

±226.6

12300

1180.3

1187.6

±212.8

15800

1191.4

1197.1

±227.0

12400

1180.6

1187.9

±213.2

15900

1191.7

1197.3

±227.4

12500

1181.0

1188.2

±213.6

16000

1192.0

1197.6

±227.8

12600

1181.3

1188.5

±214.0

16100

1192.4

1197.9

±228.2

12700

1181.6

1188.8

±214.5

16200

1192.7

1198.1

±228.6

12800

1182.0

1189.1

±214.9

16300

1193.0

1198.4

±229.0

12900

1182.3

1189.3

±215.3

16400

1193.3

1198.6

±229.4

13000

1182.6

1189.6

±215.7

16500

1193.6

1198.9

±229.8

13100

1182.9

1189.9

±216.1

16600

1193.9

1199.1

±230.2

13200

1183.3

1190.2

±216.5

16700

1194.2

1199.4

±230.6

13300

1183.6

1190.4

±216.9

16800

1194.4

1199.6

±230.9

13400

1183.9

1190.7

±217.3

16900

1194.7

1199.9

±231.3

13500

1184.2

1191.0

±217.7

17000

1194.9

1200.1

±231.7

13600

1184.6

1191.3

±218.1

17100

1195.2

1200.4

±232.0

13700

1184.9

1191.5

±218.5

17200

1195.4

1200.6

±232.4

13800

1185.2

1191.8

±218.9

17300

1195.7

1200.9

±232.8

13900

1185.6

1192.1

±219.3

17400

1195.9

1201.1

±233.1

14000

1185.9

1192.4

±219.7

17500

1196.1

1201.4

±233.5

14100

1186.2

1192.6

±220.1

17600

1196.4

1201.6

±233.8

14200

1186.5

1192.9

±220.6

17700

1196.6

1201.8

±234.2

14300

1186.8

1193.2

±221.0

17800

1196.9

1202.0

±234.6

14400

1187.1

1193.5

±221.4

17900

1197.1

1202.2

±234.9

14500

1187.4

1193.7

±221.8

18000

1197.4

1202.4

±235.3

14600

1187.7

1194.0

±222.2

18100

1197.6

1202.6

±235.7

14700

1188.0

1194.3

±222.6

18200

1197.9

1202.8

±236.0

14800

1188.3

1194.5

±223.0

18300

1198.1

1203.0

±236.4

14900

1188.7

1194.8

±223.4

18400

1198.4

1203.2

±236.7

15000

1189.0

1195.1

±223.8

18500

1198.6

1203.4

±237.1

15100

1189.3

1195.3

±224.2

18600

1198.9

1203.6

±237.5

15200

1189.6

1195.6

±224.6

18700

1199.1

1203.8

±237.8

15300

1189.9

1195.8

±225.0

18800

1199.4

1204.0

±238.2

15400

1190.2

1196.1

±225.4

18900

1199.6

1204.2

±238.5

15500

1190.5

1196.3

±225.8

19000

1199.9

1204.4

±238.9



1-24-002 Page 7 of 12 Aug 23/2007 D043U544-GPR1

747-400BCF



VOLUME US GAL.

GROUND

19100


FLIGHT

B.B.L. (GROUND)

VOLUME US GAL.

GROUND

FLIGHT

B.B.L. (GROUND)

1200.1

1204.5

±239.3

22600

1206.9

1210.1

±250.6

19200

1200.4

1204.7

±239.6

22700

1207.0

1210.2

±250.9

19300

1200.6

1204.9

±240.0

22800

1207.2

1210.4

±251.3

19400

1200.8

1205.1

±240.3

22900

1207.4

1210.5

±251.6

19500

1201.0

1205.3

±240.6

23000

1207.5

1210.6

±251.9

19600

1201.2

1205.5

±241.0

23100

1207.7

1210.7

±252.2

19700

1201.4

1205.7

±241.3

23200

1207.9

1210.8

±252.5

19800

1201.6

1205.9

±241.6

23300

1208.0

1210.9

±252.9

19900

1201.8

1206.1

±241.9

23400

1208.2

1211.1

±253.2

20000

1202.0

1206.3

±242.3

23500

1208.4

1211.2

±253.5

20100

1202.2

1206.5

±242.6

23600

1208.6

1211.3

±253.8

20200

1202.4

1206.6

±242.9

23700

1208.7

1211.4

±254.1

20300

1202.6

1206.8

±243.2

23800

1208.9

1211.5

±254.5

20400

1202.8

1206.9

±243.5

23900

1209.1

1211.6

±254.9

20500

1203.0

1207.1

±243.9

24000

1209.4

1211.8

±255.3

20600

1203.2

1207.2

±244.2

24100

1209.7

1211.9

±255.8

20700

1203.4

1207.4

±244.5

24200

1209.9

1212.0

±256.2

20800

1203.6

1207.5

±244.8

24300

1210.2

1212.1

±256.7

20900

1203.8

1207.7

±245.1

24400

1210.5

1212.3

±257.1

21000

1204.0

1207.8

±245.5

24500

1210.7

1212.4

±257.6

21100

1204.1

1208.0

±245.8

24600

1211.0

1212.6

±258.0

21200

1204.3

1208.1

±246.1

24700

1211.3

1212.7

±258.5

21300

1204.5

1208.3

±246.4

24800

1211.6

1212.8

±258.9

21400

1204.7

1208.4

±246.8

24900

1211.8

1213.0

±259.4

21500

1204.9

1208.6

±247.1

25000

1212.1

1213.1

±259.8

21600

1205.1

1208.7

±247.4

25092

1212.3

1213.2

±260.2

21700

1205.3

1208.9

±247.7

21800

1205.5

1209.0

±248.0

21900

1205.7

1209.2

±248.4

22000

1205.8

1209.3

±248.7

22100

1206.0

1209.5

±249.0

22200

1206.2

1209.6

±249.3

22300

1206.4

1209.8

±249.7

22400

1206.5

1209.9

±250.0

22500

1206.7

1210.0

±250.3

1-24-002 Page 8 of 12 Aug 23/2007 D043U544-GPR1


747-400BCF





VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

400

1085.0

1147.9

±134.7

12400

1142.0

1155.6

±168.0

800

1096.7

1146.6

±137.7

12800

1142.6

1156.1

±168.7

1200

1101.9

1145.7

±139.6

13200

1143.3

1156.6

±169.4

1600

1106.9

1145.0

±141.5

13600

1143.9

1157.0

±170.0

2000

1111.0

1145.1

±143.2

14000

1144.6

1157.5

±170.7

2400

1114.3

1145.1

±144.8

14400

1145.2

1157.9

±171.4

2800

1116.2

1145.2

±146.0

14800

1145.9

1158.3

±172.1

3200

1118.1

1145.4

±147.2

15200

1146.5

1158.8

±172.8

3600

1119.9

1145.7

±148.5

15600

1147.1

1159.2

±173.5

4000

1121.7

1146.1

±149.7

16000

1147.7

1159.7

±174.1

4400

1123.4

1146.5

±150.9

16400

1148.2

1160.1

±174.7

4800

1124.8

1146.9

±151.9

16800

1148.8

1160.6

±175.3

5200

1125.9

1147.2

±152.9

17200

1149.3

1161.0

±175.9

5600

1127.1

1147.7

±153.9

17600

1149.8

1161.4

±176.5

6000

1128.2

1148.1

±154.9

18000

1150.4

1161.9

±177.1

6400

1129.4

1148.6

±155.8

18400

1150.9

1162.3

±177.7

6800

1130.5

1149.0

±156.8

18800

1151.4

1162.7

±178.3

7200

1131.6

1149.5

±157.8

19200

1152.0

1163.1

±178.9

7600

1132.7

1150.0

±158.7

19600

1152.5

1163.5

±179.5

8000

1133.5

1150.4

±159.5

20000

1153.0

1164.0

±180.1

8400

1134.3

1150.9

±160.3

20400

1153.6

1164.4

±180.7

8800

1135.1

1151.4

±161.1

20800

1154.1

1164.8

±181.3

9200

1136.0

1151.9

±161.9

21200

1154.6

1165.2

±181.9

9600

1136.8

1152.3

±162.7

21600

1155.1

1165.6

±182.5

10000

1137.6

1152.8

±163.5

22000

1155.6

1166.0

±183.0

10400

1138.4

1153.3

±164.3

22400

1156.0

1166.4

±183.6

B.B.L. (GROUND)

10800

1139.2

1153.7

±165.1

22800

1156.5

1166.8

±184.1

11200

1140.0

1154.2

±165.9

23200

1157.0

1167.2

±184.7

11600

1140.7

1154.7

±166.6

23600

1157.4

1167.6

±185.2

12000

1141.4

1155.2

±167.3

24000

1157.9

1168.0

±185.8



1-24-002 Page 9 of 12 Aug 23/2007 D043U544-GPR1

747-400BCF




B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

24400

1158.4

1168.4

±186.3

38400

1172.9

1181.0

±203.7

24800

1158.8

1168.8

±186.8

38800

1173.3

1181.4

±204.2

25200

1159.3

1169.2

±187.4

39200

1173.7

1181.7

±204.6

25600

1159.8

1169.5

±187.9

39600

1174.0

1182.0

±205.1

26000

1160.2

1169.9

±188.5

40000

1174.4

1182.3

±205.5

26400

1160.7

1170.3

±189.0

40400

1174.8

1182.7

±206.0

26800

1161.2

1170.7

±189.6

40800

1175.1

1183.0

±206.4

27200

1161.6

1171.1

±190.1

41200

1175.5

1183.3

±206.9

27600

1162.1

1171.4

±190.6

41600

1175.9

1183.6

±207.4

28000

1162.5

1171.8

±191.2

42000

1176.3

1184.0

±207.8

28400

1162.9

1172.2

±191.6

42400

1176.6

1184.3

±208.3

28800

1163.3

1172.6

±192.1

42800

1177.0

1184.6

±208.7

29200

1163.7

1172.9

±192.6

43200

1177.4

1184.9

±209.2

29600

1164.2

1173.3

±193.1

43600

1177.7

1185.2

±209.6

30000

1164.6

1173.7

±193.6

44000

1178.1

1185.6

±210.1

30400

1165.0

1174.1

±194.1

44400

1178.4

1185.9

±210.5

30800

1165.4

1174.4

±194.6

44800

1178.8

1186.2

±210.9

31200

1165.8

1174.8

±195.1

45200

1179.1

1186.5

±211.4

31600

1166.2

1175.1

±195.6

45600

1179.5

1186.9

±211.8

32000

1166.6

1175.5

±196.1

46000

1179.8

1187.2

±212.2

32400

1167.0

1175.8

±196.6

46400

1180.2

1187.5

±212.6

32800

1167.5

1176.2

±197.1

46800

1180.5

1187.8

±213.1

33200

1167.9

1176.5

±197.6

47200

1180.9

1188.1

±213.5

33600

1168.3

1176.9

±198.1

47600

1181.2

1188.4

±213.9

34000

1168.7

1177.2

±198.6

48000

1181.6

1188.7

±214.4

34400

1169.1

1177.6

±199.1

48400

1181.9

1189.0

±214.8

34800

1169.5

1177.9

±199.6

48800

1182.2

1189.3

±215.2

35200

1169.9

1178.3

±200.0

49200

1182.6

1189.6

±215.7

35600

1170.3

1178.6

±200.5

49600

1182.9

1189.9

±216.1

36000

1170.7

1179.0

±201.0

50000

1183.3

1190.2

±216.5

36400

1171.0

1179.3

±201.4

50400

1183.6

1190.5

±217.0

36800

1171.4

1179.7

±201.9

50800

1184.0

1190.8

±217.4

37200

1171.8

1180.0

±202.3

51200

1184.3

1191.0

±217.8

37600

1172.2

1180.3

±202.8

51600

1184.7

1191.3

±218.2

38000

1172.5

1180.7

±203.2

52000

1185.0

1191.6

±218.7

1-24-002 Page 10 of 12 Aug 23/2007 D043U544-GPR1


747-400BCF




B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

52400

1185.4

1191.9

±219.1

66400

1196.2

1201.5

±233.6

52800

1185.7

1192.2

±219.5

66800

1196.5

1201.7

±234.0

53200

1186.0

1192.5

±220.0

67200

1196.8

1201.9

±234.4

53600

1186.4

1192.8

±220.4

67600

1197.0

1202.1

±234.8

54000

1186.7

1193.1

±220.8

68000

1197.3

1202.3

±235.2

54400

1187.0

1193.4

±221.2

68400

1197.6

1202.5

±235.5

54800

1187.3

1193.7

±221.7

68800

1197.8

1202.7

±235.9

55200

1187.7

1193.9

±222.1

69200

1198.1

1202.9

±236.3

55600

1188.0

1194.2

±222.5

69600

1198.4

1203.1

±236.7

56000

1188.3

1194.5

±222.9

70000

1198.6

1203.3

±237.1

56400

1188.6

1194.8

±223.4

70400

1198.9

1203.6

±237.5

56800

1189.0

1195.1

±223.8

70800

1199.1

1203.8

±237.8

57200

1189.3

1195.4

±224.2

71200

1199.4

1204.0

±238.2

57600

1189.6

1195.6

±224.6

71600

1199.7

1204.2

±238.6

58000

1189.9

1195.9

±225.1

72000

1199.9

1204.4

±239.0

58400

1190.3

1196.2

±225.5

72400

1200.2

1204.6

±239.4

58800

1190.6

1196.4

±225.9

72800

1200.5

1204.8

±239.7

59200

1190.9

1196.7

±226.3

73200

1200.7

1205.0

±240.1

59600

1191.3

1197.0

±226.8

73600

1200.9

1205.2

±240.4

60000

1191.6

1197.2

±227.2

74000

1201.1

1205.4

±240.8

60400

1191.9

1197.5

±227.6

74400

1201.3

1205.6

±241.1

60800

1192.2

1197.8

±228.0

74800

1201.5

1205.8

±241.5

61200

1192.6

1198.0

±228.5

75200

1201.7

1206.0

±241.8

61600

1192.9

1198.3

±228.9

75600

1201.9

1206.3

±242.2

62000

1193.2

1198.5

±229.3

76000

1202.2

1206.4

±242.5

62400

1193.5

1198.8

±229.7

76400

1202.4

1206.6

±242.8

62800

1193.9

1199.1

±230.2

76800

1202.6

1206.8

±243.2

63200

1194.1

1199.3

±230.6

77200

1202.8

1206.9

±243.5

63600

1194.4

1199.6

±230.9

77600

1203.0

1207.1

±243.9

64000

1194.7

1199.9

±231.3

78000

1203.2

1207.2

±244.2

64400

1194.9

1200.1

±231.7

78400

1203.4

1207.4

±244.5

64800

1195.2

1200.4

±232.1

78800

1203.6

1207.6

±244.9

65200

1195.5

1200.7

±232.5

79200

1203.8

1207.7

±245.2

65600

1195.7

1200.9

±232.9

79600

1204.0

1207.9

±245.6

66000

1196.0

1201.2

±233.2

80000

1204.2

1208.0

±245.9



1-24-002 Page 11 of 12 Aug 23/2007 D043U544-GPR1

747-400BCF




B.B.L. (GROUND)

VOLUME L

GROUND

FLIGHT

B.B.L. (GROUND)

80400

1204.4

1208.2

±246.2

90400

1209.1

1211.6

±254.8

80800

1204.6

1208.4

±246.6

90800

1209.4

1211.7

±255.3

81200

1204.8

1208.5

±246.9

91200

1209.6

1211.9

±255.7

81600

1205.0

1208.7

±247.3

91600

1209.9

1212.0

±256.2

82000

1205.2

1208.8

±247.6

92000

1210.2

1212.2

±256.7

82400

1205.4

1209.0

±247.9

92400

1210.5

1212.3

±257.2

82800

1205.6

1209.1

±248.3

92800

1210.8

1212.4

±257.6

83200

1205.8

1209.3

±248.6

93200

1211.1

1212.6

±258.1

83600

1206.0

1209.5

±249.0

93600

1211.4

1212.7

±258.6

84000

1206.2

1209.6

±249.3

94000

1211.6

1212.9

±259.1

84400

1206.3

1209.8

±249.6

94400

1211.9

1213.0

±259.5

84800

1206.5

1209.9

±250.0

94800

1212.2

1213.2

±260.0

85200

1206.7

1210.0

±250.3

94984

1212.3

1213.2

±260.2

85600

1206.9

1210.1

±250.7

86000

1207.1

1210.3

±251.0

86400

1207.2

1210.4

±251.3

86800

1207.4

1210.5

±251.7

87200

1207.6

1210.6

±252.0

87600

1207.8

1210.8

±252.4

88000

1208.0

1210.9

±252.7

88400

1208.1

1211.0

±253.0

88800

1208.3

1211.1

±253.4

89200

1208.5

1211.2

±253.7

89600

1208.7

1211.4

±254.0

90000

1208.8

1211.5

±254.4

1-24-002 Page 12 of 12 Aug 23/2007 D043U544-GPR1



747-400BCF

FUEL TANK QUANTITIES AND BALANCE ARMS COMBINED RESERVE TANKS 2 & 3 IN U.S. GALLONS The following table provides usable, gauged fuel data in U.S. gallons. For each of the volumes listed, the volume is split equally between Reserve Tank 2 and Reserve Tank 3 (for example, the 1000 gallon entry represents 500 gallons in Reserve Tank 2 and 500 gallons in Reserve Tank 3, each at B.A. 1713.9 for ground and B.A. 1682.3 for flight). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

U.S. GALLONS COMBINED RESERVE TANKS 2 & 3 B.A. INCHES VOLUME B.B.L. U.S. GAL. GROUND FLIGHT (GROUND) 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300 2400 2500 2600 2644

1699.0 1697.2 1699.1 1700.9 1703.1 1705.3 1707.5 1709.7 1711.8 1713.9 1715.7 1717.5 1719.0 1720.6 1721.6 1722.7 1723.6 1724.6 1725.3 1726.1 1726.8 1727.4 1728.0 1728.6 1729.3 1729.9 1730.3


1663.7 1665.9 1668.5 1671.0 1672.9 1674.8 1676.5 1678.3 1680.3 1682.3 1684.6 1686.8 1689.2 1691.6 1694.2 1696.7 1699.3 1701.9 1704.7 1707.5 1710.5 1713.4 1716.5 1719.5 1722.8 1726.0 1727.4

±856.5 ±869.6 ±875.7 ±881.8 ±886.6 ±891.5 ±895.7 ±899.9 ±903.5 ±907.2 ±910.3 ±913.4 ±916.0 ±918.7 ±920.6 ±922.5 ±924.2 ±925.8 ±927.3 ±928.8 ±930.1 ±931.5 ±932.8 ±934.1 ±935.6 ±937.0 ±937.8

1-24-011 Page 1 of 2 Aug 23/2007 D043U544-GPR1


747-400BCF

FUEL TANK QUANTITIES AND BALANCE ARMS (Continued) COMBINED RESERVE TANKS 2 & 3 IN LITERS The following table provides usable, gauged fuel data in liters. For each of the volumes listed, the volume is split equally between Reserve Tank 2 and Reserve Tank 3 (for example, the 4000 liter entry represents 2000 liters in Reserve Tank 2 and 2000 liters in Reserve Tank 3, each at B.A. 1714.9 for ground and B.A. 1683.6 for flight). The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

LITERS COMBINED RESERVE TANKS 2 & 3 GROUND

FLIGHT

B.B.L. (GROUND)

400

1698.9

1663.9

±857.3

800

1697.4

1666.2

±870.3

1200

1699.4

1668.9

±876.7

1600

1701.4

1671.4

±882.9

2000

1703.7

1673.5

±888.0

2400

1706.0

1675.4

±892.9

2800

1708.4

1677.2

±897.3

3200

1710.7

1679.2

±901.5

3600

1712.9

1681.3

±905.4

4000

1714.9

1683.6

±909.0

4400

1716.9

1686.0

±912.3

4800

1718.6

1688.5

±915.2

5200

1720.2

1691.0

±918.0

5600

1721.4

1693.6

±920.2

6000

1722.6

1696.3

±922.2

6400

1723.6

1699.1

±924.0

6800

1724.5

1701.8

±925.8

7200

1725.3

1704.8

±927.3

7600

1726.1

1707.7

±928.9

8000

1726.8

1710.9

±930.3

8400

1727.5

1714.0

±931.7

8800

1728.2

1717.2

±933.1

9200

1728.8

1720.5

±934.5

9600

1729.5

1723.9

±936.2

10000

1730.3

1727.3

±937.9

10008

1730.3

1727.4

±937.8

1-24-011 Page 2 of 2 Aug 23/2007 D043U544-GPR1

B.A. INCHES

VOLUME L


747-400BCF


FUEL QUANTITIES AND BALANCE ARMS - CENTER TANK CENTER TANKS IN U.S. GALLONS The following table provides usable, gauged fuel data in U.S. gallons. The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

U.S. GALLONS CENTER TANK

CENTER TANK

B.A. INCHES GROUND

FLIGHT

VOLUME U.S. GAL

GROUND

FLIGHT

100

1063.0

1144.6

3100

1103.8

1121.6

200

1065.2

1143.6

3200

1104.2

1121.5

300

1067.3

1142.5

3300

1104.5

1121.3

400

1069.5

1141.5

3400

1104.9

1121.1

500

1071.6

1140.5

3500

1105.2

1121.0

600

1073.8

1139.5

3600

1105.5

1120.8

700

1076.0

1138.4

3700

1105.8

1120.6

800

1078.1

1137.4

3800

1106.0

1120.5

900

1080.3

1136.4

3900

1106.2

1120.3

1000

1082.4

1135.4

4000

1106.4

1120.2

1100

1084.6

1134.3

4100

1106.6

1120.0

1200

1086.7

1133.3

4200

1106.8

1119.8

1300

1088.9

1132.3

4300

1107.0

1119.7

1400

1091.1

1131.3

4400

1107.2

1119.6

1500

1093.0

1130.2

4500

1107.3

1119.5

1600

1093.9

1129.2

4600

1107.5

1119.4

1700

1094.7

1128.2

4700

1107.7

1119.3

1800

1095.5

1127.2

4800

1107.9

1119.3

1900

1096.4

1126.1

4900

1108.0

1119.2

2000

1097.2

1125.7

5000

1108.1

1119.1

2100

1098.0

1125.3

5100

1108.3

1119.0

2200

1098.9

1124.9

5200

1108.4

1118.9

2300

1099.7

1124.6

5300

1108.5

1118.8

2400

1100.5

1124.2

5400

1108.6

1118.7

2500

1101.4

1123.8

5500

1108.7

1118.7

2600

1102.1

1123.4

5600

1108.8

1118.6

2700

1102.5

1123.1

5700

1109.0

1118.5

2800

1102.8

1122.7

5800

1109.1

1118.5

2900

1103.2

1122.3

5900

1109.2

1118.4

3000

1103.5

1121.9

6000

1109.3

1118.4


B.A. INCHES

VOLUME U.S. GAL.

1-24-021 Page 1 of 6 Aug 23/2007 D043U544-GPR1

747-400BCF


FUEL QUANTITIES AND BALANCE ARMS - CENTER TANK (Continued) U.S. GALLONS (Continued) CENTER TANK

CENTER TANK

B.A. INCHES

B.A. INCHES

VOLUME U.S. GAL.

GROUND

FLIGHT

VOLUME U.S. GAL

GROUND

FLIGHT

6100

1109.4

1118.3

9600

1111.5

1117.2

6200

1109.5

1118.3

9700

1111.6

1117.2

6300

1109.5

1118.2

9800

1111.6

1117.1

6400

1109.6

1118.1

9900

1111.6

1117.1

6500

1109.7

1118.1

10000

1111.7

1117.1

6600

1109.8

1118.0

10100

1111.7

1117.1

6700

1109.9

1118.0

10200

1111.8

1117.1

6800

1110.0

1118.0

10300

1111.8

1117.1

6900

1110.0

1117.9

10400

1111.8

1117.1

7000

1110.1

1117.9

10500

1111.9

1117.0

7100

1110.2

1117.9

10600

1111.9

1117.0

7200

1110.2

1117.8

10700

1111.9

1117.0

7300

1110.3

1117.8

10800

1112.0

1117.0

7400

1110.4

1117.7

10900

1112.0

1117.0

7500

1110.4

1117.7

11000

1112.0

1117.0

7600

1110.5

1117.7

11100

1112.1

1117.0

7700

1110.6

1117.6

11200

1112.1

1116.9

7800

1110.6

1117.6

11300

1112.1

1116.9

7900

1110.7

1117.6

11400

1112.2

1116.9

8000

1110.8

1117.5

11500

1112.2

1116.9

8100

1110.8

1117.5

11600

1112.2

1116.9

8200

1110.9

1117.5

11700

1112.3

1116.9

8300

1110.9

1117.5

11800

1112.3

1116.9

8400

1111.0

1117.4

11900

1112.3

1116.9

8500

1111.0

1117.4

12000

1112.3

1116.9

8600

1111.1

1117.4

12100

1112.4

1116.8

8700

1111.1

1117.4

12200

1112.4

1116.8

8800

1111.2

1117.3

12300

1112.4

1116.8

8900

1111.2

1117.3

12400

1112.5

1116.8

9000

1111.3

1117.3

12500

1112.5

1116.7

9100

1111.3

1117.3

12600

1112.5

1116.6

9200

1111.4

1117.3

12700

1112.5

1116.6

9300

1111.4

1117.2

12800

1112.6

1116.5

9400

1111.4

1117.2

12900

1112.6

1116.4

9500

1111.5

1117.2

13000

1112.6

1116.4

1-24-021 Page 2 of 6 Aug 23/2007 D043U544-GPR1


747-400BCF


FUEL QUANTITIES AND BALANCE ARMS - CENTER TANK (Continued) U.S. GALLONS (Continued) CENTER TANK

CENTER TANK

B.A. INCHES GROUND

FLIGHT

VOLUME U.S. GAL

GROUND

FLIGHT

13100

1112.6

1116.3

15600

1110.9

1111.9

13200

1112.7

1116.2

15700

1110.7

1111.6

13300

1112.7

1116.2

15800

1110.5

1111.4

13400

1112.7

1116.1

15900

1110.3

1111.1

13500

1112.7

1116.0

16000

1110.1

1110.8

13600

1112.7

1115.8

16100

1109.8

1110.4

13700

1112.7

1115.7

16200

1109.6

1110.1

13800

1112.7

1115.5

16300

1109.3

1109.8

13900

1112.6

1115.4

16400

1109.0

1109.4

14000

1112.6

1115.2

16500

1108.7

1109.1

14100

1112.6

1115.1

16600

1108.4

1108.7

14200

1112.5

1115.0

16700

1108.1

1108.3

14300

1112.5

1114.8

16800

1107.7

1107.9

14400

1112.4

1114.6

16900

1107.3

1107.5

14500

1112.4

1114.4

17000

1106.9

1107.1

14600

1112.4

1114.2

17100

1106.6

1106.6

14700

1112.2

1114.0

17164

1106.3

1106.3

14800

1112.1

1113.8

14900

1112.0

1113.6

15000

1111.8

1113.4

15100

1111.7

1113.2

15200

1111.6

1113.0

15300

1111.4

1112.7

15400

1111.3

1112.4

15500

1111.1

1112.2


B.A. INCHES

VOLUME U.S. GAL.

1-24-021 Page 3 of 6 Aug 23/2007 D043U544-GPR1

747-400BCF


FUEL QUANTITIES AND BALANCE ARMS - CENTER TANK (Continued) CENTER TANK IN LITERS The following table provides usable, gauged fuel data in liters. The ground balance arms are representative of the wing in a nominal ground deflected position. The flight balance arms are representative of the wing in a nominal flight deflected position.

LITERS CENTER TANK

CENTER TANK

B.A. INCHES

VOLUME L

GROUND

400 800

B.A. INCHES

FLIGHT

VOLUME L

GROUND

FLIGHT

1063.1

1144.5

12400

1104.4

1121.3

1065.4

1143.4

12800

1104.8

1121.2

1200

1067.7

1142.4

13200

1105.1

1121.0

1600

1070.0

1141.3

13600

1105.5

1120.8

2000

1072.2

1140.2

14000

1105.8

1120.6

2400

1074.5

1139.1

14400

1106.0

1120.5

2800

1076.8

1138.0

14800

1106.2

1120.3

3200

1079.1

1136.9

15200

1106.4

1120.1

3600

1081.4

1135.9

15600

1106.6

1119.9

4000

1083.6

1134.8

16000

1106.8

1119.8

4400

1085.9

1133.7

16400

1107.0

1119.7

4800

1088.2

1132.6

16800

1107.2

1119.6

5200

1090.5

1131.5

17200

1107.4

1119.5

5600

1092.6

1130.5

17600

1107.6

1119.4

6000

1093.7

1129.4

18000

1107.8

1119.3

6400

1094.6

1128.3

18400

1108.0

1119.2

6800

1095.5

1127.2

18800

1108.1

1119.1

7200

1096.4

1126.1

19200

1108.2

1119.0

7600

1097.3

1125.6

19600

1108.3

1118.9

8000

1098.1

1125.2

20000

1108.5

1118.8

8400

1099.0

1124.8

20400

1108.6

1118.7

8800

1099.9

1124.5

20800

1108.7

1118.7

9200

1100.8

1124.1

21200

1108.8

1118.6

9600

1101.6

1123.7

21600

1109.0

1118.5

10000

1102.3

1123.3

22000

1109.1

1118.5

10400

1102.6

1122.9

22400

1109.2

1118.4

10800

1103.0

1122.5

22800

1109.3

1118.4

11200

1103.3

1122.1

23200

1109.4

1118.3

11600

1103.7

1121.7

23600

1109.5

1118.2

12000

1104.1

1121.5

24000

1109.6

1118.2

1-24-021 Page 4 of 6 Aug 23/2007 D043U544-GPR1


747-400BCF


FUEL QUANTITIES AND BALANCE ARMS - CENTER TANK (Continued) LITERS (Continued) CENTER TANK

CENTER TANK

B.A. INCHES GROUND

FLIGHT

VOLUME L

GROUND

FLIGHT

24400

1109.7

1118.1

38400

1111.7

1117.1

24800

1109.7

1118.1

38800

1111.8

1117.1

25200

1109.8

1118.0

39200

1111.8

1117.1

25600

1109.9

1118.0

39600

1111.8

1117.0

26000

1110.0

1117.9

40000

1111.9

1117.0

26400

1110.1

1117.9

40400

1111.9

1117.0

26800

1110.2

1117.9

40800

1112.0

1117.0

27200

1110.2

1117.8

41200

1112.0

1117.0

27600

1110.3

1117.8

41600

1112.0

1117.0

28000

1110.4

1117.7

42000

1112.1

1117.0

28400

1110.4

1117.7

42400

1112.1

1116.9

28800

1110.5

1117.7

42800

1112.1

1116.9

29200

1110.6

1117.6

43200

1112.2

1116.9

29600

1110.6

1117.6

43600

1112.2

1116.9

30000

1110.7

1117.6

44000

1112.2

1116.9

30400

1110.8

1117.5

44400

1112.3

1116.9

30800

1110.8

1117.5

44800

1112.3

1116.9

31200

1110.9

1117.5

45200

1112.3

1116.9

31600

1110.9

1117.5

45600

1112.4

1116.8

32000

1111.0

1117.4

46000

1112.4

1116.8

32400

1111.0

1117.4

46400

1112.4

1116.8

32800

1111.1

1117.4

46800

1112.4

1116.8

33200

1111.1

1117.3

47200

1112.5

1116.7

33600

1111.2

1117.3

47600

1112.5

1116.6

34000

1111.2

1117.3

48000

1112.5

1116.6

34400

1111.3

1117.3

48400

1112.6

1116.5

34800

1111.3

1117.3

48800

1112.6

1116.4

35200

1111.4

1117.2

49200

1112.6

1116.4

35600

1111.4

1117.2

49600

1112.6

1116.3

36000

1111.5

1117.2

50000

1112.7

1116.2

36400

1111.5

1117.2

50400

1112.7

1116.2

36800

1111.6

1117.2

50800

1112.7

1116.1

37200

1111.6

1117.1

51200

1112.7

1115.9

37600

1111.6

1117.1

51600

1112.7

1115.8

38000

1111.7

1117.1

52000

1112.7

1115.6


B.A. INCHES

VOLUME L

1-24-021 Page 5 of 6 Aug 23/2007 D043U544-GPR1

747-400BCF


FUEL QUANTITIES AND BALANCE ARMS - CENTER TANK (Continued) LITERS (Continued) CENTER TANK

CENTER TANK

B.A. INCHES

B.A. INCHES

VOLUME L

GROUND

FLIGHT

VOLUME L

GROUND

FLIGHT

52400

1112.7

1115.5

60400

1110.1

1110.9

52800

1112.6

1115.3

60800

1109.9

1110.6

53200

1112.6

1115.2

61200

1109.7

1110.2

53600

1112.5

1115.0

61600

1109.4

1109.9

54000

1112.5

1114.9

62000

1109.1

1109.5

54400

1112.5

1114.7

62400

1108.7

1109.1

54800

1112.4

1114.5

62800

1108.4

1108.7

55200

1112.4

1114.3

63200

1108.1

1108.3

55600

1112.2

1114.0

63600

1107.7

1107.9

56000

1112.1

1113.8

64000

1107.3

1107.5

56400

1112.0

1113.6

64400

1106.9

1107.0

56800

1111.8

1113.4

64800

1106.5

1106.5

57200

1111.7

1113.2

64973

1106.3

1106.3

57600

1111.5

1112.9

58000

1111.4

1112.6

58400

1111.3

1112.4

58800

1111.1

1112.1

59200

1110.8

1111.8

59600

1110.6

1111.5

60000

1110.4

1111.2

1-24-021 Page 6 of 6 Aug 23/2007 D043U544-GPR1


747-400BCF


SYSTEM FLUIDS ENGINE SYSTEM OIL (GENERAL ELECTRIC CF6-80C2 ENGINES) The following table lists total engine system oil (including trapped oil): FLUID CATEGORY

Drainable Oil

Trapped Oil

NOTE

VOLUME

WEIGHT

TANK LOCATION

U.S. GAL.

L

LB

KG

B.A. IN.

No. 1

9.6

36.3

80.2

36.3

1461

No. 2

9.6

36.3

80.2

36.3

1100

No. 3

9.6

36.3

80.2

36.3

1100

No. 4

9.6

36.3

80.2

36.3

1461

Total

38.4

145.2

320.8

145.2

1281

No. 1

1.7

6.4

14.2

6.4

1505

No. 2

1.7

6.4

14.2

6.4

1145

No. 3

1.7

6.4

14.2

6.4

1145

No. 4

1.7

6.4

14.2

6.4

1505

Total

6.8

25.6

56.8

25.6

1325

Oil density used is 8.35 LB/U.S. GAL. (1.001 KG/L).

INTEGRATED DRIVE GENERATOR OIL The following table lists the integrated drive generator oil: VOLUME

WEIGHT

TANK LOCATION

U.S. GAL.

L

LB

KG

B.A. IN.

No. 1

0.9

3.4

7.5

3.4

1469

No. 2

0.9

3.4

7.5

3.4

1109

No. 3

0.9

3.4

7.5

3.4

1109

No. 4

0.9

3.4

7.5

3.4

1469

Total

3.6

13.6

30.0

13.6

1289

NOTE



1-30-002 Page 1 of 2 Apr 20/2006 D043U544-GPR1

747-400BCF


SYSTEM FLUIDS (Continued) HYDRAULIC SYSTEM FLUID The following table provides the hydraulic system fluid totals: FLUID CATEGORY

Hydraulic System Fluid

Hydraulic Reservoir Fluid

NOTE

VOLUME

LOCATION

U.S. GAL.

WEIGHT L

LB

KG

B.A. IN.

No. 1

60

227

501

227

1525

No. 2

34

129

284

129

1551

No. 3

33

125

276

125

1582

No. 4

51

193

426

193

1595

Total

178

674

1487

674

1561

No. 1

11

42

92

42

1638

No. 2

7

26

58

26

1331

No. 3

7

26

58

26

1331

No. 4

11

42

92

42

1638

Total

36

136

300

136

1518

Hydraulic fluid density used is 8.35 LB/U.S. GAL. (1.001 KG/L).

LANDING GEAR SYSTEM FLUID The following table lists the landing gear system hydraulic fluid totals: VOLUME

WEIGHT

U.S. GAL.

L

LB

KG

B.A. IN.

Nose Gear Oleo

8

30

57

26

390

Wing Gear Oleo

44

167

313

142

1343

Body Gear Oleo

29

110

206

94

1463

FLUID LOCATION

NOTE


OPERATING SYSTEM FLUID The following table provides operating systems fluid totals: SYSTEM Pneumatic Starter Oil Auxiliary Power Unit Air Conditioning (3-Pack) NOTE

VOLUME U.S. GAL. L 0.3 1.2 4.2 15.9 0.2 0.8

LB 2.5 35.1 1.7

KG 1.2 15.9 0.8


1-30-002 Page 2 of 2 Apr 20/2006 D043U544-GPR1

WEIGHT


B.A. IN. 1322 2682 1054

747-400BCF


SYSTEM FLUIDS ENGINE SYSTEM OIL (PRATT & WHITNEY PW400 ENGINES) The following table lists total engine system oil (including trapped oil): FLUID CATEGORY

Drainable Oil

Trapped Oil

NOTE

VOLUME

WEIGHT

TANK LOCATION

U.S. GAL.

L

LB

KG

B.A. IN.

No. 1

9.6

36.3

80.2

36.3

1486

No. 2

9.6

36.3

80.2

36.3

1125

No. 3

9.6

36.3

80.2

36.3

1125

No. 4

9.6

36.3

80.2

36.3

1486

Total

38.4

145.2

320.8

145.2

1306

No. 1

3.9

14.8

32.6

14.8

1505

No. 2

3.9

14.8

32.6

14.8

1145

No. 3

3.9

14.8

32.6

14.8

1145

No. 4

3.9

14.8

32.6

14.8

1505

Total

15.6

59.2

130.4

59.2

1325


INTEGRATED DRIVE GENERATOR OIL The following table lists the integrated drive generator oil: VOLUME

WEIGHT

TANK LOCATION

U.S. GAL.

L

LB

KG

B.A. IN.

No. 1

0.9

3.4

7.5

3.4

1469

No. 2

0.9

3.4

7.5

3.4

1109

No. 3

0.9

3.4

7.5

3.4

1109

No. 4

0.9

3.4

7.5

3.4

1469

Total

3.6

13.6

30.0

13.6

1289

NOTE



1-30-003 Page 1 of 2 Apr 25/2006 D043U544-GPR1

747-400BCF


SYSTEM FLUIDS (Continued) HYDRAULIC SYSTEM FLUID The following table provides the hydraulic system fluid totals: FLUID CATEGORY

Hydraulic System Fluid

Hydraulic Reservoir Fluid

NOTE

VOLUME

LOCATION

U.S. GAL.

WEIGHT L

LB

KG

B.A. IN.

No. 1

60

227

501

227

1525

No. 2

34

129

284

129

1551

No. 3

33

125

276

125

1582

No. 4

51

193

426

193

1595

Total

178

674

1487

674

1561

No. 1

11

42

92

42

1638

No. 2

7

26

58

26

1331

No. 3

7

26

58

26

1331

No. 4

11

42

92

42

1638

Total

36

136

300

136

1518

Hydraulic fluid density used is 8.35 LB/U.S. GAL. (1.001 KG/L).

LANDING GEAR SYSTEM FLUID The following table lists the landing gear system hydraulic fluid totals: VOLUME

WEIGHT

U.S. GAL.

L

LB

KG

B.A. IN.

Nose Gear Oleo

8

30

57

26

390

Wing Gear Oleo

44

167

313

142

1343

Body Gear Ole

29

110

206

94

1463

FLUID LOCATION

NOTE


OPERATING SYSTEM FLUID The following table provides operating systems fluid totals: SYSTEM Pneumatic Starter Oil Auxiliary Power Unit Air Conditioning (3-Pack) NOTE

VOLUME U.S. GAL. L 0.3 1.2 4.2 15.9 0.2 0.8

LB 2.5 35.1 1.7

KG 1.2 15.9 0.8


1-30-003 Page 2 of 2 Apr 25/2006 D043U544-GPR1

WEIGHT


B.A. IN. 1322 2682 1054

747-400BCF


POTABLE WATER SYSTEM TANK QUANTITIES AND LOCATIONS The drinking, washing and lavatory rinse water system has one storage tank per airplane. The total usable potable water and supply lines are listed in the table below. VOLUME

WEIGHT KG

B.A. IN.

916.3

415.6

987.0

37.8

83.3

37.7

987.0

454.1

999.6

453.3

987.0

SYSTEM

U.S. GAL.

Water Tank (1)

110.0

416.3

Lines

10.0

Total

120.0

NOTE

L

Density used is 8.33 LB/U.S. GAL. (0.998 KG/L).


LB

1-32-001 Page 1 of 1 Jun 27/2005 D043U544-GPR1

747-400BCF


WASTE DISPOSAL SYSTEM TANK QUANTITIES AND LOCATIONS The volume of the aft waste storage tank has a capacity of 65 U.S. Gallons (246 Liters). An initial charge of disinfectant is located in the waste tank listed below. VOLUME SYSTEM Aft Tank (1)

NOTE

WEIGHT

U.S. GAL.

L

LB

KG

7.0

26.4

58.3

26.3

B.A. IN. 2107.0

Density used is 8.33 LB/U.S. GAL. (0.998 KG/L).

The weight of waste disinfectant can be reduced when a dry chemical or a lower volume, higher concentrate wet precharge is utilized.


1-34-001 Page 1 of 1 Jun 27/2005 D043U544-GPR1


747-400BCF

CREW, OCCUPANT, AND BAGGAGE WEIGHT ALLOWANCES FAA ADVISORY CIRCULAR 120-27E ALLOWANCES The following crew, occupant and baggage weights meet or exceed the Federal Aviation Administration (FAA) Advisory Circular 120-27E, dated June 10, 2005.

Flight Crew For flight crew members:

Flight crew member

190 LB (86.2 KG)

Pilot flight bag

20 LB (9.1 KG)

Crewmember roller bag

30 LB (13.6 KG)

Occupants For occupants (includes carry-on baggage):

Male occupants

220 LB (99.8 KG)

Female occupants

200 LB (90.7 KG)

Baggage Typical baggage weight is 30 LB (13.6 KG) per person. However, a considerable variation will exist between various routes depending on such items as overnight stay requirements.


1-40-001 Page 1 of 1 Dec 21/2005 D043U544-GPR1


747-400BCF

INTERIOR ARRANGEMENT - UPPER DECK FLIGHT DECK The flight crew balance arms are defined as 6 IN. in front of the Seat Reference Point (SRP). The SRP is defined as the intersection of the seat bottom and the seat back. The crew locations represent the crew seated at takeoff positions. Flight Deck (2 Observers) FLIGHT CREW (TWO OBSERVERS) LOCATION

B.A. IN.

Captain

307

First Officer

307

First Observer

351

Second Observer

354

APPLICABLE CONFIGURATIONS Refer to the Interior Effectivity section of this manual to correlate certified Passenger Arrangements with specific aircraft serial numbers.

1-42-007 Page 1 of 4 Dec 11/2007 D043U544-GPR1

747-400BCF


INTERIOR ARRANGEMENT - UPPER DECK (Continued) UPPER CABIN - 14C ARRANGEMENT (ZERO OCCUPANCY) The upper cabin 14C arrangement (Zero Occupancy) shown below is the basis for the subsequent passenger and cabin crew center of gravity data.

300

Reference Drawing(s): LOPA 747 SF-2802

400

500

600

Galley Structure

BALANCE ARM - IN.

700

800

Passenger Locations The center of gravity of each passenger location for the main cabin arrangement above is listed in the following table. The class designations are as follows: First Class (F), Business Class (C) and Tourist Class (Y). Unless otherwise noted, the passenger balance arms are defined as 8 IN. aft of the forward seat pin, relative to the seat. The balance arms represent the passengers seated in an upright position.

1-42-007 Page 2 of 4 Dec 11/2007 D043U544-GPR1

CLASS

ROW

C

1 2 3 4 5 6 7

PASSENGERS LEFT RIGHT B.A. B.A. NO. NO. IN. IN. 2 465 2 530 2 558 2 588 2 614 2 646 2 736


747-400BCF


INTERIOR ARRANGEMENT - UPPER DECK (Continued) UPPER CABIN - 8C ARRANGEMENT (ZERO OCCUPANCY) The upper cabin 8C arrangement (Zero Occupancy) shown below is the basis for the subsequent passenger and cabin crew center of gravity data.

300


400

500

600

Galley Structure

BALANCE ARM - IN.

700

800


CLASS

ROW

C

1 2 3 4

PASSENGERS LEFT RIGHT B.A. B.A. NO. NO. IN. IN. 2 477 2 542 2 577 2 607


1-42-007 Page 3 of 4 Dec 11/2007 D043U544-GPR1

747-400BCF


INTERIOR ARRANGEMENT - UPPER DECK (Continued) UPPER CABIN - 8C ARRANGEMENT The upper cabin 8C arrangement shown below is the basis for the subsequent passenger and cabin crew center of gravity data.

300


400

500

600

Galley Structure

BALANCE ARM - IN.

700

800


1-42-007 Page 4 of 4 Dec 11/2007 D043U544-GPR1

CLASS

ROW

C

1 2 3 4

PASSENGERS LEFT RIGHT B.A. B.A. NO. NO. IN. IN. 2 477 2 542 2 577 2 607


747-400BCF


CARGO COMPARTMENT LOAD LIMITS MAXIMUM ALLOWABLE WEIGHTS This section provides upper deck, main deck, and lower deck cargo compartment loading. These values are the maximum allowable weights that can be sustained by the basic monocoque structure. The following illustration shows the configuration of the cargo compartments.

200.0

400.0

780.0

2365.0

1280.0 BULK HOLD

AFT CARGO HOLD UPPER CABIN

MAIN DECK CARGO COMPARTMENT

FWD CARGO HOLD 464.0 0

200

400

970.0 600

800

1000

.

1920.0

1484.0 1200

1400

1600

1800

2000

2160.0 2200

2400

2600

2800

BALANCE ARM - IN. Five basic structural limitations that must be observed when loading payload are compartment, linear loading, floor loading, net loading and cumulative load limitations. Cumulative load limitations are discussed in CHP-SEC 1-60-40x (forward body) and CHP-SEC 1-60-60x (aft body).


1-60-001 Page 1 of 6 Jul 9/2007 D043U544-GPR1

747-400BCF


CARGO COMPARTMENT LOAD LIMITS (Continued)

Maximum allowable compartment weights, and maximum allowable linear and floor loading are provided in the following table: MAXIMUM ALLOWABLE WEIGHT TOTAL WEIGHT FLOOR LOADING LB KG LB/IN. KG/IN. LB/SQ FT KG/SQ FT

COMPARTMENT Upper Cabin B.A. 400.0 to B.A. 780.0 Main Deck Cargo[b] B.A. 200.0 to B.A. 525.0 B.A. 525.0 to B.A. 1000.0 B.A. 1000.0 to B.A. 1480.0 B.A. 1480.0 to B.A. 2218.0 B.A. 2218.0 to B.A. 2365.0 Forward Cargo Hold[c] B.A. 464.0 to B.A. 970.0 Aft Cargo Hold[c] B.A. 1484.0 to B.A. 1920.0 Bulk Hold B.A. 1920.0 to B.A. 2160.0 Maximum Load Distribution Between Net Locations B.A. 1920.0 to 1980.0 B.A. 1980.0 to 2060.0 B.A. 2060.0 to 2160.0

31.8[a]

14.4[a]

100.0

45.3

19500 71250 139200 125460 4500

8845 32318 63140 56907 2041

60.0 150.0 290.0 170.0 36.0

27.2 68.0 131.5 77.1 16.3

100.0 200.0 400.0 400.0 100.0

45.3 90.7 181.4 181.4 45.3

58400

26489

116.0

52.6

200.0

90.7

50570

22938

116.0

52.6

200.0

90.7

150.0

68.0

14880[d]

6749[d]

5160

2340

5390 4330

2444 1964

Varies[e]

[a] The upper cabin allowable load includes the weight of supernumeraries, supernumeraries seats, and supernumeraries carry-on baggage stowed under the seats. [b] The main deck limitations include the weight of cargo and the unit load devices (ULDs). [c] The lower hold limitations include the weight of cargo and the unit load devices (ULDs). [d] The bulk cargo net at B.A. 1920.0 must be installed or the maximum allowable weight is 0 LB (0 KG). [e] 94.0 LB/IN. (42.6 KG/IN.) at B.A. 1920.0 decreasing linearly to 30.0 LB/IN. (13.6 KG/IN.) at B.A. 2160.0

CAUTION THESE LOADS MAY BE FURTHER LIMITED BY CUMULATIVE LOAD LIMITATIONS.

1-60-001 Page 2 of 6 Jul 9/2007 D043U544-GPR1


747-400BCF


CARGO COMPARTMENT LOAD LIMITS (Continued) MAXIMUM COMBINED LINEAR LOAD LIMITS

1480.0

200.0 (90.7)

200.0 (90.7)

176.0 (79.8)

120 110 100 90 80

170.0 (77.1)

70 60 50 2365.0

200.0

970.0

150.0 (68.0)

60.0 (27.2)

40 30

LINEAR LOAD - (KG/IN.)

130 2160.0 2218.0

1000.0

290.0 (131.5)

525.0

464.0

300 280 260 240 220 200 180 160 140 120 100 80 60 40 20 0

20 10

36.0 (16.3)

2500

2400

2300

2200

2100

2000

1900

1800

1700

1600

1500

1400

1300

1200

1100

1000

900

800

700

600

500

400

300

200

0

0 100

LINEAR LOAD - LB/IN.

Total loading for the main deck and lower deck cargo must not exceed the combined linear loading limits shown in the following diagram:

BALANCE ARM

NOTE

Cumulative loads are typically more restrictive than combined linear loads.


1-60-001 Page 3 of 6 Jul 9/2007 D043U544-GPR1

747-400BCF


CARGO COMPARTMENT LOAD LIMITS (Continued) MAIN DECK UNSYMMETRICAL PAYLOAD - LINEAR LOAD LIMITS Unit load devices located side by side on the main deck must not exceed the unsymmetrical linear load limits shown below. 300 23.4

LEFT SIDE AIRPLANE - LB/IN.

266.6

[1]

244.4 45.6

200

145.0 108.0 85.0

100 95.0

85.0 55.0

244.4 55.0

45.6

108.0

[1]

145.0

95.0

266.6 23.4

B.A. 525 to 1000

0 0

100

200

300

RIGHT SIDE AIRPLANE - LB/IN.

B.A. 1800 to 2040

150 10.6

LEFT SIDE AIRPLANE - KG/IN.

B.A. 1480 to 1800 B.A. 2040 to 2218

B.A. 1000 to 1480 120.9

[1] 100

110.8

[1] Limit for 88 inch wide unit load devices to assure area load limit is not exceeded

20.7

65.7 48.9 50 43.0

38.5 38.5 24.0

110.8 24.0

48.9 65.7

43.0

120.9

20.7

[1]

10.6

0 0

50

100

150

RIGHT SIDE AIRPLANE - KG/IN.

1-60-001 Page 4 of 6 Jul 9/2007 D043U544-GPR1


747-400BCF


CARGO COMPARTMENT LOAD LIMITS (Continued) MAIN DECK CENTERLINE LOAD LIMITS Cargo loaded on unit load devices located along the main deck centerline of the airplane between B.A. 525.0 to B.A. 1000.0 (Note that the floor loading rate in this region is 150 LB/IN (68KG/IN)) and B.A. 1480.0 to B.A. 2218.0 (Note that the floor loading rate in this region is 170 LB/IN (77.1KG/IN)) must meet the minimum cargo width requirements shown in the figure below. Between B.A. 1000.0 to B.A. 1480.0 the limitation is 290 LB/IN. (131.5 KG/IN.), provided the area load limit of 400 LB/SQ. FT. (181.4 KG/SQ. FT.) is not exceeded.

AIRPLANE CL MINIMUM CARGO WIDTH

PALLET WIDTH

MIN. CARGO WIDTH - IN.

160

170.0 120

117.0

80

DO NOT OPERATE IN THIS AREA

40.0

40

110.0 0 0

40

80

120 160 LINEAR LOAD - LB/IN.

200

240

MIN. CARGO WIDTH - IN.

160

77.1 120

117.0

80

40

40.0

DO NOT OPERATE IN THIS AREA

49.8 0 0

20

40

60 80 LINEAR LOAD - KG/IN.


100

120

1-60-001 Page 5 of 6 Jul 9/2007 D043U544-GPR1

747-400BCF


CARGO COMPARTMENT LOAD LIMITS (Continued) ALLOWABLE MAIN DECK RUNNING LOAD VERSUS CENTER WING TANK FUEL When the center wing tank contains more than 16700 LB (7574 KG), then the following reduction in allowable main deck running load from B.A. 1000 to 1265 is required. 320 2 9 0 .0

280 38000

ALLOWABLE RUNNING LOAD - LB/IN

16700 240

ZF

ZF W

200

>

56

160

50

W

00

=

25

60

62

W

79

=