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FUELING AND SERVICING MANUAL

(FSM)

Revision: A
01-Apr-2021

CONFIDENTIAL/SECURITY SENSITIVE

Use of this document is restricted to conveyance of information to government agencies as well as employees,
customers, and/or vendors of Avatar Airlines. The information shall not be released, disclosed, or used for any purpose
without express written consent of Avatar Airlines.

Avatar Airlines | Technical Publications

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SAFETY COMMITMENT LETTER Safety Commitment Letter

To: The Employees of Avatar Airlines

We regularly review our commitment to Safety and Security in order to keep it front and center in our
business. As Avatar leaders we commit to maintaining the highest level of safety and security for our
customers and providing a safe work environment for all Avatar employees, We are committed to continuous
improvement in the Avatar operation by evaluating, investigating, analyzing, assessing and mitigating
hazards on a continuous basis. Safety and Security of the Avatar operation are priority #1.

To ensure this happens, we recognize that an effective Safety Management System (SMS) is vital to the
success of Avatar Airlines. We are committed to providing the necessary resources for the continual
implementation of our SMS; 14 CFR 5.21(a)(3). This will allow us to continue to improve the level of safety
and security throughout Avatar Airlines. The Avatar Director of Safety has authority to facilitate and manage
the Avatar Safety Management System.

Safety objectives will be established, published and made available to all Avatar employees. The safety
objectives will be posted on the Avatar Intranet, accessible to all employees. Safety objectives will be a
continuous focus as they are monitored, measured, and tracked to ensure that we meet these objectives.

We believe responding to an emergency is the highest priority of management and employees. The
Emergency Response Plan (ERP) serves as an overall policy and set of procedures to ensure that the
airline's response to a catastrophic event is expeditious, intelligent and compassionate. We periodically
exercise the plan to ensure the plan continues to provide a safe transition from normal to emergency
operations, 14 CFR 5.21(a)(6).

We will not tolerate intentional at-risk actions or behaviors at Avatar Airlines. All employees are personally
responsible and accountable for performing their duties safely and in compliance with laws, regulations and
company policy. Activities involving disregard of these items will be subject to disciplinary action. We believe
this is a necessary element of a Just Culture, 14 CFR 5.21(a)(5).

Every employee must continuously be aware of hazards that have the potential to degrade the level of
safety and security for our employees and our passengers. It is the duty of all employees to report hazards
either directly to management or through reporting tools available to Avatar employees, 14 CFR 5.21(a)(4).

At Avatar, no one will allow any operation to proceed unless he or she is certain it can be carried out
with Safety and Security. To support every Avatar employee in making the hard personal decisions
that this may require, no penalty or disciplinary action will be imposed on any employee who stops
an operation and brings what he or she genuinely views to be a safety or security concern to
management or a fellow employee.

Barry Michaels Dan Eikleberry

CEO, Avatar Airlines COO, Avatar Airlines
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MASTER TABLE OF CONTENTS
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TABLE OF CONTENTS
Master TOC MASTER TABLE OF CONTENTS

SAFETY COMMITMENT LETTER........................................................................................................................................ SCL

MASTER TABLE OF CONTENTS .....................................................................................................................................MTOC
LIST OF EFFECTIVE PAGES ...............................................................................................................................................LEP
RECORD OF REVISIONS ................................................................................................................................................... ROR

CHAPTER 1 - THE ROLE OF AIRCRAFT FUELING ........................................................................................... 1

CHAPTER 2 - GENERAL FUELING POLICY....................................................................................................... 2

CHAPTER 3 - FUELING SAFETY PRECAUTIONS ............................................................................................. 3

CHAPTER 4 - GENERAL FUELING PROCEDURES........................................................................................... 4

CHAPTER 5 - PRESSURE FUELING................................................................................................................... 5

CHAPTER 6 - FUEL TANK SUMP DRAINAGE ................................................................................................... 6

CHAPTER 7 - FUELING RECORD ....................................................................................................................... 7

CHAPTER 8 - FUEL SYSTEM DESCRIPTION..................................................................................................... 8

CHAPTER 9 - FUEL STANDARDS ...................................................................................................................... 9

CHAPTER 10 - DEFUELING PROCEDURES .................................................................................................... 10

CHAPTER 11 - HANDLING FUEL SPILLS ........................................................................................................ 11

APPENDIX A - FUEL DISTRIBUTION TABLES 747-400.......................................................................................................... A
INDEX OF REFERENCES..................................................................................................................................................... IOR

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LIST OF EFFECTIVE PAGES List of Effective Pages

* Asterisk shows pages revised, deleted, or added by current revision.

Page Rev Date Page Rev Date Page Rev Date

Safety Commitment Letter Chapter 4 TOC 5.16 A ....... 01-Apr-2021

5.17 A ....... 01-Apr-2021
SCL.1 A ....... 01-Apr-2021 4.1 A ....... 01-Apr-2021 5.18 A ....... 01-Apr-2021
SCL.2 A ....... 01-Apr-2021 4.2 A ....... 01-Apr-2021 5.19 A ....... 01-Apr-2021
Master TOC Chapter 4 5.20 A ....... 01-Apr-2021
MTOC.1 A ....... 01-Apr-2021 4.1 A ....... 01-Apr-2021 5.21 A ....... 01-Apr-2021
MTOC.2 A ....... 01-Apr-2021 4.2 A ....... 01-Apr-2021 5.22 A ....... 01-Apr-2021
4.3 A ....... 01-Apr-2021 5.23 A ....... 01-Apr-2021
List of Effective Pages 5.24 A ....... 01-Apr-2021
4.4 A ....... 01-Apr-2021
LEP.1 A ....... 01-Apr-2021 4.5 A ....... 01-Apr-2021 5.25 A ....... 01-Apr-2021
LEP.2 A ....... 01-Apr-2021 4.6 A ....... 01-Apr-2021 5.26 A ....... 01-Apr-2021
Record of Revisions 4.7 A ....... 01-Apr-2021 5.27 A ....... 01-Apr-2021
4.8 A ....... 01-Apr-2021 5.28 A ....... 01-Apr-2021
ROR.1 A ....... 01-Apr-2021 5.29 A ....... 01-Apr-2021
ROR.2 A ....... 01-Apr-2021 Chapter 5 TOC 5.30 A ....... 01-Apr-2021
Preface 5.1 A ....... 01-Apr-2021 5.31 A ....... 01-Apr-2021
PR.1 A ....... 01-Apr-2021 5.2 A ....... 01-Apr-2021 5.32 A ....... 01-Apr-2021
PR.2 A ....... 01-Apr-2021 Chapter 5 Chapter 6 TOC
Chapter 1 TOC 5.1 A ....... 01-Apr-2021 6.1 A ....... 01-Apr-2021
1.1 A ....... 01-Apr-2021 5.2 A ....... 01-Apr-2021 6.2 A ....... 01-Apr-2021
1.2 A ....... 01-Apr-2021 5.3 A ....... 01-Apr-2021 Chapter 6
5.4 A ....... 01-Apr-2021
Chapter 1 5.5 A ....... 01-Apr-2021 6.1 A ....... 01-Apr-2021
1.1 A ....... 01-Apr-2021 5.6 A ....... 01-Apr-2021 6.2 A ....... 01-Apr-2021
1.2 A ....... 01-Apr-2021 5.7 A ....... 01-Apr-2021 6.3 A ....... 01-Apr-2021
5.8 A ....... 01-Apr-2021 6.4 A ....... 01-Apr-2021
Chapter 2 TOC
5.9 A ....... 01-Apr-2021 Chapter 7 TOC
2.1 A ....... 01-Apr-2021 5.10 A ....... 01-Apr-2021
2.2 A ....... 01-Apr-2021 7.1 A ....... 01-Apr-2021
5.11 A ....... 01-Apr-2021 7.2 A ....... 01-Apr-2021
Chapter 2 5.12 A ....... 01-Apr-2021
5.13 A ....... 01-Apr-2021 Chapter 7
2.1 A ....... 01-Apr-2021
2.2 A ....... 01-Apr-2021 5.14 A ....... 01-Apr-2021 7.1 A ....... 01-Apr-2021
5.15 A ....... 01-Apr-2021 7.2 A ....... 01-Apr-2021
Chapter 3 TOC
3.1 A ....... 01-Apr-2021
3.2 A ....... 01-Apr-2021
Chapter 3
3.1 A ....... 01-Apr-2021
3.2 A ....... 01-Apr-2021
3.3 A ....... 01-Apr-2021
3.4 A ....... 01-Apr-2021
3.5 A ....... 01-Apr-2021
3.6 A ....... 01-Apr-2021

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LIST OF EFFECTIVE PAGES (CONT)

* Asterisk shows pages revised, deleted, or added by current revision.

Page Rev Date Page Rev Date Page Rev Date

7.3 A....... 01-Apr-2021 10.11 A ....... 01-Apr-2021 A.17 A ....... 01-Apr-2021
7.4 A....... 01-Apr-2021 10.12 A ....... 01-Apr-2021 A.18 A ....... 01-Apr-2021
Chapter 8 TOC 10.13 A ....... 01-Apr-2021 A.19 A ....... 01-Apr-2021
10.14 A ....... 01-Apr-2021 A.20 A ....... 01-Apr-2021
08.1 A....... 01-Apr-2021 10.15 A ....... 01-Apr-2021 A.21 A ....... 01-Apr-2021
08.2 A....... 01-Apr-2021 10.16 A ....... 01-Apr-2021 A.22 A ....... 01-Apr-2021
Chapter 8 10.17 A ....... 01-Apr-2021 A.23 A ....... 01-Apr-2021
8.1 A....... 01-Apr-2021 10.18 A ....... 01-Apr-2021 A.24 A ....... 01-Apr-2021
8.2 A....... 01-Apr-2021 Chapter 11 TOC A.25 A ....... 01-Apr-2021
8.3 A....... 01-Apr-2021 A.26 A ....... 01-Apr-2021
011.1 A ....... 01-Apr-2021 A.27 A ....... 01-Apr-2021
8.4 A....... 01-Apr-2021 011.2 A ....... 01-Apr-2021
8.5 A....... 01-Apr-2021 A.28 A ....... 01-Apr-2021
8.6 A....... 01-Apr-2021 Chapter 11 A.29 A ....... 01-Apr-2021
8.7 A....... 01-Apr-2021 11.1 A ....... 01-Apr-2021 A.30 A ....... 01-Apr-2021
8.8 A....... 01-Apr-2021 11.2 A ....... 01-Apr-2021 A.31 A ....... 01-Apr-2021
11.3 A ....... 01-Apr-2021 A.32 A ....... 01-Apr-2021
Chapter 9 TOC A.33 A ....... 01-Apr-2021
11.4 A ....... 01-Apr-2021
09.1 A....... 01-Apr-2021 A.34 A ....... 01-Apr-2021
09.2 A....... 01-Apr-2021 Appendix A A.35 A ....... 01-Apr-2021
Chapter 9 A.1 A ....... 01-Apr-2021 A.36 A ....... 01-Apr-2021
A.2 A ....... 01-Apr-2021 A.37 A ....... 01-Apr-2021
9.1 A....... 01-Apr-2021 A.3 A ....... 01-Apr-2021 A.38 A ....... 01-Apr-2021
9.2 A....... 01-Apr-2021 A.4 A ....... 01-Apr-2021 A.39 A ....... 01-Apr-2021
9.3 A....... 01-Apr-2021 A.5 A ....... 01-Apr-2021 A.40 A ....... 01-Apr-2021
9.4 A....... 01-Apr-2021 A.6 A ....... 01-Apr-2021 A.41 A ....... 01-Apr-2021
9.5 A....... 01-Apr-2021 A.7 A ....... 01-Apr-2021 A.42 A ....... 01-Apr-2021
9.6 A....... 01-Apr-2021 A.8 A ....... 01-Apr-2021 A.43 A ....... 01-Apr-2021
9.7 A....... 01-Apr-2021 A.9 A ....... 01-Apr-2021 A.44 A ....... 01-Apr-2021
9.8 A....... 01-Apr-2021 A.10 A ....... 01-Apr-2021 A.45 A ....... 01-Apr-2021
Chapter 10 TOC A.11 A ....... 01-Apr-2021 A.46 A ....... 01-Apr-2021
010.1 A....... 01-Apr-2021 A.12 A ....... 01-Apr-2021 Index of References
010.2 A....... 01-Apr-2021 A.14 A ....... 01-Apr-2021
A.15 A ....... 01-Apr-2021 IOR.1 A ...... 01-Apr-2021
Chapter 10 A.16 A ....... 01-Apr-2021 IOR.2 A ....... 01-Apr-2021
10.1 A....... 01-Apr-2021
10.2 A....... 01-Apr-2021
10.3 A....... 01-Apr-2021
10.4 A....... 01-Apr-2021
10.5 A....... 01-Apr-2021
10.6 A....... 01-Apr-2021
10.7 A....... 01-Apr-2021
10.8 A....... 01-Apr-2021
10.9 A....... 01-Apr-2021
10.10 A....... 01-Apr-2021

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RECORD OF REVISIONS
Record of Revisions

As revisions are received and inserted into this manual, complete the boxes below. Specify the date the revision is
inserted in the manual, and enter the name of the person updating the manual.
Manual holders can confirm revision status against the electronic version of this manual by logging into the Company
Website (cms.avatarairlines.com), or by contacting the Manager of Technical Publications
techpubs@avatarairlines.com.

REV DATE INSERTED BY REV DATE INSERTED BY

NBR INSERTED (PRINT NAME) NBR INSERTED (PRINT NAME)

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PREFACE Preface

1 MANUAL COMPLIANCE
14 CFR 119.43(b)(1), 119.43(c), 119.49(a), 121.133(a), 121.135(a)(1), 121.135(a)(2), 121.135(a)(3), 121.135(a)(4),
121.135(b)(1), 121.135(b)(2), 121.135(b)(3), 121.135(b)(4), 121.135(b)(6), 121.135(b)(25)(i), 121.135(b)(26),
121.135(c).
Avatar Airlines, (the “Company”, “Company’s”,”Avatar”) Fueling and Servicing Manual (FSM) has been prepared in
accordance with, and in reference to, 14 CFR 121.133(a), 121.133(b), 121.135(a)(1), 121.135(a)(2), 121.135(a)(3),
21.135(a)(4), 121.135(b)(1), 121.135(b)(2), 121.135(b)(3), 121.135(b)(15), 121.135(b)(17), 121.135(b)(19), 121.135
(b)(26), 121.135(c) and will include other information or instructions as necessary relating to Aircraft Fueling.
It should be noted that additional CFRs are referenced throughout this manual to satisfy the primary regulatory
requirements, including applicable interfacing with Company policies and procedures. Although the goal of the
Company is to define specific policies and procedures within a certain Chapter or Section of our Manual, it should be
understood that there may be other Chapters, Sections and/or manuals that interface with a specific policy or
procedure that need to be referenced to ensure the regulatory requirements are satisfied.
The Company’s Principal Base of Operations is: Avatar Airlines, Inc. 20283 State Road 7, Suite 400, Boca Raton, FL
33498. 14 CFR 119.47, OpSpec A001
The Company will conduct all operations as a direct carrier, only in common carriage per 14 CFR 119.5(g), 119.5(h).
The FSM has been prepared for the use of Company personnel in the performance of their duties. 14 CFR 121.133(a),
121.135(a)(1)
Revisions to the FSM will be issued in a timely manner to ensure all information therein is current and correct.
The Company will maintain at least one complete copy of this manual at its principle base of operations.
Communication with respect to this Fueling and Servicing Manual should be addressed to:

Chief of Operations flightops@avatarairlines.com

2 ORGANIZATION

2.1 Organizational Structure

14 CFR 121.365(a), 121.365(b), 121.369(a)
Position titles are assigned to divisions, which are the departments where their primary duties and responsibilities are
performed. Coordination and cooperation between all departments is required in order for the organization to operate in
an effective and efficient manner. Actual duties and responsibilities can sometime cross these departmental
boundaries.
For further detail refer to COM Chapter 1 Organization

2.2 Position Descriptions

14 CFR 119.65, 119.67, 121.133(a), 121.135(b)(2)
The Position Descriptions are intended to define the qualifications, duties and responsibilities for each job title providing an
understanding for the individual as well as for others. They will not cover every specific duty but generally outline the
objective of the individual and their place within the organization. Individuals are responsible to perform all duties as defined
throughout the Company Manual System as they apply to their particular position.

For further detail refer to COM Chapter 3 - Position Descriptions

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3 DOCUMENTATION
In accordance with regulation, the Company maintains a Technical Documentation management system that controls
both Company generated publications, and other controlled documents such as manufacturer manuals, government
publications, drawings, etc. The system controls the approval, publication, distribution, revision and any associated
processes to assure current and accurate information availability to the persons who need it. The system is detailed
in the Company Manual System (CMS). The Company manuals as a collective group define an interrelated system
of policies and procedures. So information required by any one individual may be found in various individual
manuals.

3.1 Document Revisions

Manual revisions may be required due to regulatory changes, self-disclosures, technology changes, operational
changes, organizational changes, or any of a multitude of factors. It is important that during the revision process all of
the requirements of the Publication Procedures Manual (PPM) are followed to assure a coordinated outcome
compliant with regulation and the Operations Specifications, that there are no unintended consequences, and that
any interfaces are addressed.

For further detail refer to PPM Chapter 7 - Document Revision

3.2 Document Distribution

14 CFR 121.133(a), 121.133(b)
The Technical Publications department maintains a master copy of all company, aircraft, engine, manufacturer, and
other manuals necessary to support the airline operation. All manuals are published in the English language. The
system that controls the distribution, of controlled documentation is referred to as the Company Manual System
(CMS). It includes a database and tracking system to know the current approved manual holders; those provided
sign-on and password electronic access; copies of the current manuals and all previously approved versions; the
documentation supporting revisions to the manuals; a system to track revision distribution; and the Technical
Publications web page. The Company Web page is the preferred source of current publications as update is easily
accomplished and there is no delay as In the case of hard copy distribution.

For further detail refer to PPM Chapter 8 – Document Distribution

For access to Company Manual website go to: cms.avatarairlines.com

4 FORMS
Forms are effective in controlling a process, gathering information, documenting a record, or providing instruction.
The Company maintains forms on a company website with both active (fill in on line) and inactive copy's.
Forms are accessed by department and are separated by active and inactive. A master list will show all of the forms
available.

For access to Forms go to: cms.avatarairlines.com

5 DEFINITIONS & ACRONYMS
14 CFR 1.1, 1.2
A comprehensive list of the most widely used Definitions and Acronyms used in the Company Manual System is
located at:

For access go to PPM Definitions & Acronyms

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CHAPTER 1 TOC Chapter 1 TOC

CHAPTER 1 - THE ROLE OF AIRCRAFT FUELING........................................................................................ 1.1

1. SAFE, RELIABLE AND EFFICIENT FUELING OF AIRCRAFT ....................................................................................... 1.1
2. CONTRACT FUELING .................................................................................................................................................... 1.1

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CHAPTER 1 - THE ROLE OF AIRCRAFT FUELING

Chapter 1

1 SAFE, RELIABLE AND EFFICIENT FUELING OF AIRCRAFT

14 CFR 121.105, 121.123, 121.135(b)(19), FAA Order 8900.1, Volume 2, Chapter 2, Section 5
In accordance with the Federal Aviation Regulation 14 CFR. The Company is primarily responsible for establishing
adequate facilities, procedures for refueling aircraft, eliminating fuel contamination, protection from fire (including
electrostatic protection) and supervising and protecting passengers during refueling. This manual is used in
accordance with Code of Federal Regulations. Director of Maintenance Operations has overall responsibility for the
quality of the Aircraft Fueling Process. Director of Maintenance Operations has delegated the authority to establish and
make changes to the policies, procedures and information for the Aircraft Fueling Process to the Director of Ground
Operations.

2 CONTRACT FUELING
14 CFR 121.105, AC 20-125, AC 00-34A, AC 150/5230-4A, ATA Spec 103
Avatar Airlines does not maintain aircraft fueling equipment at any of its stations. Fueling is accomplished by
contractual agreement with fueling agencies. The contractor is tasked with providing clean, uncontaminated fuel and
competent personnel, adequate facilities and equipment for the proper fueling of Company aircraft.
This manual shall be used by outside agencies performing fueling operations on Company aircraft. The outside
agencies assigned to servicing Company aircraft will have their servicing personnel trained according to procedures as
outlined in the this manual for each type of aircraft in Avatar Airlines inventory. All fueling will be accomplished in
accordance with this manual, Part 139 Airport Certification (see Fuel Handling), AC 20-125 (Water in Aviation Fuels),
NFPA 407 Aircraft Fuel Servicing, AC 00-34A (Aircraft Ground Handling and Servicing), AC 150/5230-4A (Aircraft Fuel
Storage, Handling and Dispensing on Airports) and ATA Spec 103 Jet Fuel Quality Control Standards.
The Fueling Vendor has the responsibility for the following:
• If not trained by Avatar Airlines, training of their personnel to comply with all Company fueling procedures.
• Assign a designated trainer of Avatar Airlines fueling policies and procedures.
• Maintain training records of personnel assigned to Avatar Airlines fueling operations.
• Ensure that all personnel assigned to fueling aircraft are adequately trained in Avatar Airlines fueling procedures
and practices.
• Assignment of prescribed number of personnel to fueling operation.
• Surveillance and enforcement of all safety regulations and fueling precautions.
• Daily surveillance and inspection of all fueling equipment for a safe and efficient operation as per the fueling
equipment inspection procedures of this publication.
• Notify Avatar Airlines Operations Manager or authorized individual whenever fueling equipment and other
elements necessary to comply with Company fueling procedures are removed from service or other wise not
available.
• Ensure that the prescribed quantity and grade of fuel is loaded.
• Ensure that aircraft are fueled/defueled in accordance with this manual.
• Completion of the Fuel Distribution Request Form (Form OFS-100).
• Maintains published procedures for quality and handling, covering all aspects of their operation which as a
minimum meet the requirements of this manual. Avatar Airlines accepts vendor procedures and frequency of
checks and replacements provided they do not exceed standard industry practice as set forth in this manual.
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CHAPTER 2 TOC Chapter 2 TOC

CHAPTER 2 - GENERAL FUELING POLICY.................................................................................................... 2.1

1. GENERAL ........................................................................................................................................................................ 2.1
2. OBJECTIVE ..................................................................................................................................................................... 2.1
3. AUTHORITY AND CONTROL ......................................................................................................................................... 2.1

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CHAPTER 2 - GENERAL FUELING POLICY

Chapter 2

1 GENERAL
The Company Fueling and Servicing Manual (FSM) will interface with other manuals to clarify training, personal
qualification etc. The FSM procedures outline basic precautions and standard practices related to fuel, storage and
fueling operations and is used as the primary aid in aircraft fueling training.

Caution
THIS SUPPLEMENTAL PUBLICATION IS NOT REPRESENTED AS COVERING
EVERY POLICY, DETAIL, VARIATION, OR POSSIBLE CONTINGENCY IN
CONNECTION WITH THE OVERALL SERVICING AND FUELING OF COMPANY
AIRCRAFT. THE GMM, AND APPROPRIATE MAINTENANCE/FLIGHT MANUALS
MUST BE USED IN CONJUNCTION WITH THESE PROCEDURES, AND UNLESS
INDICATED OTHERWISE, TAKES PRECEDENCE.

2 OBJECTIVE
The objective of this Manual is to establish procedures, guidelines, and standards for Company fueling and fuel quality.
These procedures are established in order to help assure the safe and dependable delivery of uncontaminated quality
jet fuel into aircraft utilized in Company operation.

3 AUTHORITY AND CONTROL

This manual was developed to comply with regulations and advisory material outlined in chapter 1 and is part of Avatar
Airlines Manual System (CMS).
The contents of this manual is to be considered the minimum requirements of Avatar Airlines.
Procedures for refueling aircraft, eliminating fuel contamination, protection from fire (including electrostatic protection)
and protecting passengers during refueling and de-fueling operations are of critical importance to the safe and efficient
flight operations. To ensure these procedures are followed the following controls are in place:
• The Director of Maintenance Operations is responsible for the overall quality of the procedures associated with
the procedures in the Fueling and Servicing Manual (FSPM).
• The Director of Maintenance Operations has delegated the authority to establish and make changes to the
policies, procedures and information for the Aircraft Fueling Process to the Director of Ground Operations.
• Before a fueling contractor is added to the approved vendor list, a pre-operation inspection and audit will be
conducted under the direction of the Chief Maintenance Inspector and thereafter as required by the Internal
Audit Program.
• The Chief Maintenance Inspector or his designee will perform periodic audits of the fueling agency's training
records to ensure that an adequate number of personnel are being trained on the Company's policies and
procedures
• Surveillance of fueling procedures and equipment is accomplished continuously by the Operations Manager, or
an authorized individual.
A waiver to the policies and procedures in this manual that will not compromise fuel quality, safety, or security may be
granted due to extenuating circumstances. A request for a waiver should be in writing to the Chief Maintenance
Inspector (CMI) copying the Director of Ground Operations (DGO) and contain the pertinent details and reasons why a
waiver is required. The Grant of Waiver will specify an expiration date and any related stipulations. The Fueling
Contractor will maintain the Grant of Waiver as long as it is effective.
Additionally, Avatar Airlines can accept fuel from vendors who have not been audited by Quality Assurance provided a
fuel quality test is accomplished prior to accepting each load of fuel. This procedure will be used when the Company is
operating to an off-line station due to a diversion, ad-hoc charter or where the vendor has not yet been reviewed and
approved by the Quality department. The Company must request a fuel test to be accomplished at the fuel truck prior to
delivering fuel into the aircraft to ensure the fuel is free of contaminants.
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CHAPTER 3 - FUELING SAFETY PRECAUTIONS .......................................................................................... 3.1

1. GENERAL FUELING SAFETY PRECAUTIONS ............................................................................................................. 3.1
2. CONTACT WITH FUEL ................................................................................................................................................... 3.2
3. STATIC ELECTRICITY .................................................................................................................................................... 3.2
3.1 Common Generators of Static Electricity ......................................................................................................... 3.2
3.2 Grounding (Static Grounding) .......................................................................................................................... 3.2
3.3 Bonding ............................................................................................................................................................ 3.2
3.4 Static Ground and Bonding Procedure ............................................................................................................ 3.3
4. OPERATING EQUIPMENT LIMITATIONS ...................................................................................................................... 3.3
4.1 Fueling Equipment ........................................................................................................................................... 3.3
4.2 Heat Sources ................................................................................................................................................... 3.3
4.3 Electrical Equipment ........................................................................................................................................ 3.3
4.4 Equipment Repair Limitations .......................................................................................................................... 3.3
4.5 Permissible Equipment .................................................................................................................................... 3.4
5. FUEL VAPOR .................................................................................................................................................................. 3.4
6. OXYGEN SERVICING ..................................................................................................................................................... 3.4
7. ADVERSE WEATHER CONDITIONS ............................................................................................................................. 3.5
7.1 Adverse Weather Conditions Precautions ....................................................................................................... 3.5
8. FLASH PHOTOGRAPHY ................................................................................................................................................ 3.5
9. EMERGENCY PROCEDURES ....................................................................................................................................... 3.5

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Chapter 3 CHAPTER 3 - FUELING SAFETY PRECAUTIONS

1 GENERAL FUELING SAFETY PRECAUTIONS

This section describes safety procedures and considerations that must be observed when fueling all Company
airplanes. Safety of personnel, equipment, and facilities is of primary concern and the procedures described in this
section are binding on all personnel who perform fueling operations on Company aircraft.
The procedures in this manual are standard and must be complied with. The only exception will be when there is a
conflict with local airport or Port Authority regulations, in which case the local regulations will take precedence.
All fueling and defueling operations must be under direct supervision of an Operations Manager or other authorized
individual.
Personnel should not depend entirely on mechanical safeguards built into the equipment.
Thorough training, extreme care, and good judgment are essential for personnel safety. Knowledge of the line shutoff
valve locations, the pump motor controls and the tank overflow controls can prevent a costly mishap.
Smoking or open flames are strictly forbidden in fuel storage areas, in or around fuel trucks, and within 50 feet of
fueling operations. Use only electrical equipment and lights which are acceptable under provisions of Article 500 of the
National Electric Code.
Fueling must be done in open air. Defueling or sump draining should be done outside, but may be done in a hangar
when necessary if proper safety precautions are observed. Drained fuel must be taken outside immediately. Fuel will
never be drained directly onto the ramp.

WAR NI NG
DO NOT OPERATE THE AIRCRAFT HF SYSTEM OR THE WEATHER RADAR
WHILE AIRCRAFT IS BEING FUELED. AN EXPLOSION MAY RESULT.

Caution
IF A FOREIGN OBJECT IS INADVERTENTLY DROPPED INTO A FUEL TANK, THE
PERSON IN CHARGE MUST BE NOTIFIED IMMEDIATELY SO THAT STEPS CAN
BE TAKEN TO REMOVE THE OBJECT AND RETURN THE UNIT TO SERVICE AS
QUICKLY AS POSSIBLE.
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2 CONTACT WITH FUEL

• All fueling personnel must take care to prevent fuel from coming into contact with the skin, particularly open
cuts, mouth and eyes.
• If fuel comes in contact with skin, wash thoroughly with soap and water.
• If fuel gets into open cuts, mouth or eyes, immediately wash or rinse the affected parts freely with clear water
and obtain medical attention as soon as possible.
• If fuel is swallowed, a qualified person should give standard first aid at once. Obtain medical attention as
quickly as possible.
• If clothing is saturated with fuel, remove clothing as soon as possible and wash the affected skin with soap
and water.
• Turbine fuel is equally flammable and just as hazardous as gasoline.
• Do not wear clothing that has been saturated or badly wetted by fuel.
• Avoid unnecessarily bodily contact with fuel.
• If fuel gets into eyes, flush with slow low pressure stream of water for several minutes.
• Do not use fuels for cleaning or washing.

3 STATIC ELECTRICITY
14 CFR 121.135(b)(19)

3.1 Common Generators of Static Electricity

a) Hydrocarbon fuels generate electrostatic charge when passing through pumps, filters, valves, and
piping of fuel transfer systems. The primary electrostatic generator is the filter/separator. Because the
fuel is passed under pressure through a one (1) micron filter media, this component increases the level
of static charge on a fuel by a factor of one hundred (100) or more as compared with pipe flow.
Splashing, spraying, or free falling of fuel will further enhance the charge. The amount of water that
may be entrained in the fuel will increase the static generation hazard in the fuel.
b) Static electricity buildup in clothing is a dangerous hazard, inadvertent contamination of clothing with
fuel during fuel handling operation is common AND VERY HAZARDOUS. (Refer to Safety and Security
Manual (SSM) for more detailed information on your individual safety).

NOTE
It is important to remove all sources of ignition in the vicinity of any fuel
handling operation. Sources of ignition such as open flames, engines,
ground/airborne radar signals, etc. are obvious. Less obvious is the
ignition source hazard offered by static electricity.

3.2 Grounding (Static Grounding)

Grounding (Static Grounding) is the process of connecting one or more metal objects and ground conductors to
ground electrodes (an electrical path to earth).

During normal pressure refueling an electrical bond is necessary between the airplane and the refueling vehicle.
Static grounding of the airplane is required when fueling the aircraft.

3.3 Bonding

Bonding is the process of connecting two or more metal objects together with a conductor. The act of bonding is
when you attach a bonding cable from the fueling vehicle to the aircraft at a proper grounding point. For
designated ground points on landing gear or aircraft structure, see Chapter 4.
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3.4 Static Ground and Bonding Procedure

1) Attach grounding cable to a static ground and to the airplane in the following sequence:
a) Connect the grounding cable to an approved, identified static ground point. These points may be located
in the parking surface or in another fixed location.
b) Connect the grounding cable to approved grounding attach point on the airplane.
2) Before the airplane is moved, remove the ground cables from the approved grounding attach point on the
airplane.

Caution
ATTACH GROUNDING AND BONDING CABLES ONLY TO SPECIFIED POINTS ON
THE AIRPLANE. INCORRECTLY ATTACHED GROUNDING AND BONDING
CABLES CAN CAUSE SCRATCHES WHICH CAN CAUSE CORROSION AND
CRACKS ON STRESSED PARTS. GROUNDING AND BONDING WIRES
ATTACHED TO DOORS OR FAIRINGS MADE FROM COMPOSITE MATERIALS DO
NOT PROVIDE A GROUND OR A BOND.

4 OPERATING EQUIPMENT LIMITATIONS

4.1 Fueling Equipment

The following precautions relating to airplane fueling equipment must be observed during the refueling operation:
• Airplane fueling equipment of any type will not be used to fuel ground equipment while the fueling
equipment is connected to the airplane.
• Fuel trucks will not be left unattended while the trucks are connected to the airplane.
• Fuel from one fuel truck will not be transferred to another while either is connected to the airplane.

4.2 Heat Sources

The following is a list of units and systems which must not be operated during the refueling operation:
• Heat guns and similar devices.
• Integral heaters on glycol spray units, except the Trump Model D-40-D and the FMC 1000 equipped with
the Trump JB-GPM Proportioning System/Heater Installation. These are the only units with integral heaters
which may be operated during refueling.

4.3 Electrical Equipment

During the fueling operation, the ground power unit or airplane batteries will not be connected or disconnected.

NOTE
If possible always have power equipment positions up wind from the
fuel truck.

4.4 Equipment Repair Limitations

During fueling operations, if it becomes necessary to perform service or maintenance work on automotive or
electrical equipment, such equipment will be moved a safe distance from the airplane to preclude the possibility of
fire or damage to the airplane.
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4.5 Permissible Equipment

The following units may be operated during fueling operations provided that all safety precautions listed here and
for the operation of each unit are complied with:
• It will be permissible to operate ground air conditioning units for the purpose of air conditioning the
airplane during fueling or defueling.
• It will be permissible for the start truck to continue operation during fueling or defueling provided it is
already in operation.

WAR NI NG
THE STARTING OF THE START TRUCK DURING FUELING OR DEFUELING IS
NOT PERMITTED.

• The ground power unit may be left running and connected.

• Aircraft deicer fluid spray units may be operated, but their integral heaters must not be used except the
Trump Model D-40-D and the FMC 1000 equipped with the Trump JBGPM Proportioning System/ Heater
installation. These are the only units with integral heaters which may be operated during refueling.
• Cargo handling equipment necessary for loading and unloading the airplane may be operated during the
fueling procedure unless an obvious hazard is created.

5 FUEL VAPOR
14CFR 121.135(b)(19)
Fuel vapor is extremely hazardous. Maintain constant vigilance against leakage of fuel, either liquid or vapor, in
buildings, pump houses, enclosed sumps, and refueling pits. Whenever leakage is discovered, stop it promptly and
provide ample ventilation.
Prolonged breathing of fuel vapor, even in non-explosive concentrations, produces an exhilaration followed by
dizziness and nausea. In heavier concentrations, prolonged inhalation produces unconsciousness and even death.
Fuel vapors can be extremely dangerous even in the open air. They are heavier than air, spread out along the ground
and are easily carried along by air movement. They can be ignited by automotive exhaust, automotive ignition
systems, or by any open flame, at a considerable distance from the source of the vapor. This may result in a flash-
back to the source of the vapor, causing a serious fire. Often the vapor cloud can be seen. Maintain constant
vigilance.
Whenever fuel is being handled, adequate grounding procedures must be performed.

6 OXYGEN SERVICING
Fueling is not permitted when oxygen system servicing is taking place.
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7 ADVERSE WEATHER CONDITIONS

14 CFR 121.135(b)(15)

7.1 Adverse Weather Conditions Precautions

1) When thunderstorms or lightning are in the area, approximately a 10-mile (16-kilometer) radius, do these steps

WAR NI NG
STOP THE REFUEL OPERATION DURING ATMOSPHERIC ELECTRICAL
ACTIVITY. DO NOT CONNECT A HEADSET AND DO NOT TOUCH ELECTRICAL
CONNECTIONS TO THE AIRPLANE. LIGHTNING STRIKES CAN CAUSE
INJURIES TO PERSONNEL, AND A FIRE OR EXPLOSION DURING A REFUEL
OPERATION.

a) Contact the airport authority, air traffic control, or Flight Deck crew for guidance on the decision to
continue or suspend fueling operations.
b) Stop the refuel operation when fueling operations are suspended.
c) Disconnect and remove any external headsets.
d) (Do not touch any electrical connections.
2) Refueling operations must stop if strong wind conditions are present. Strong wind conditions can cause a build-
up of static electricity. Large charges of static electricity can develop on support equipment while parked as a
result of the movement of dust particles and air currents during strong wind conditions. Strong wind conditions
can also cause the unwanted movement of items or equipment which can cause injury to persons or strike the
airplane.

8 FLASH PHOTOGRAPHY
Electronic strobe light flash photography may be allowed in the vicinity of the aircraft providing approval from
management. At no time will flash photography take place during any fueling activity within 50 feet of the aircraft unless
the light source is contained behind a barrier such as inside the terminal building or from within an enclosed vehicle.
At no time will “Flash Bulbs” or “electronic strobe lights” contained or uncontained be authorized for taking photographs
of Avatar Airlines aircraft or operations within 50 feet of the aircraft.

9 EMERGENCY PROCEDURES
Prior to fueling the airplane all personnel involved must be familiar with the following in case of an emergency situation:
• Location of the emergency fuel shutoff
• Airport Fire Department phone numbers
• Evacuation of airplane passengers
• Fuel spill containment and ignition source reduction
• Location and use of fire extinguishers
• Responsibilities of fuel servicing and airplane servicing personnel
Anyone taking note of an emergency in progress on or around a Company aircraft is responsible for notifying the
Operations Manager or an authorized individual. The Operations Manager or authorized individual is responsible for
contacting the OCC.
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CHAPTER 4 TOC Chapter 4 TOC

CHAPTER 4 - GENERAL FUELING PROCEDURES........................................................................................ 4.1

1. AIRCRAFT FUELING METHODS ................................................................................................................................... 4.1
2. FUEL SERVICING VEHICLE OPERATION .................................................................................................................... 4.2
3. STATIC GROUNDING/BONDING ................................................................................................................................... 4.2
4. FUELING PREPARATIONS ............................................................................................................................................ 4.3
5. USE OF ELECTRICAL POWER ...................................................................................................................................... 4.4
6. REFUELING WITH PASSENGERS ONBOARD ............................................................................................................. 4.5
6.1 Passengers Deplaned or Boarded ................................................................................................................... 4.5
7. FUELING WITH APU OPERATING ................................................................................................................................ 4.5
8. FUELING WITH ONE ENGINE OPERATING ................................................................................................................. 4.7
9. OVERWING FUELING .................................................................................................................................................... 4.7

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CHAPTER 4 - GENERAL FUELING PROCEDURES

Chapter 4

1 AIRCRAFT FUELING METHODS

14 CFR 121.135(b)(19)
The procedures in this manual contain instructions to fill the airplanes that are equipped with the Goodrich
Replacement Fuel Quantity Indicating System with fuel. The presence of the Goodrich Replacement FQIS can be
determined by examining the fuel quantity indicators installed on P4 or P42 panels. The presence of digital only
indicators with orange/amber light emitting diode (LED) displays, indicate the installation of the Goodrich Replacement
FQIS.
There are two fundamentally different procedures used to fill the airplane with fuel. They are by Pressure Refuel at the
fuel stations, controlled from either P42 underwing refuel panel or from the M5 fueling control module on the cockpit, or
by Overwing (gravity) Refueling. The airplane is normally refueled by the Pressure Refuel Procedure.
The different Pressure Refuel procedures are:
1) Preselect Pressure Refuel - Normal Procedure - To be used when a given quantity of fuel is to be filled. The
Preselect Mode is used only for total fuel loads of 50,000 lbs or greater. If the fuel load will be less than that,
use the manual pressure refueling procedure.

NOTE
Preselect Refueling can be accomplished only from the P42 panel .

2) Manual Pressure Refuel - To be used when specified tanks are to be refueled or when preselect refuel does
not operate.

NOTE
Manual Refueling is the only refueling mode available from the M5
module.

3) Inoperative Refuel Valve Pressure Fueling - To be used when a refuel valve will not open electrically.
4) Inoperative Fuel Quantity Indication Pressure Fueling - To be used when the fuel quantity indication for a
fuel tank does not operate. There are two procedures for when there is an inoperative fuel quantity indicator.
One procedure uses the manual override screw to open the applicable refuel valves. The other procedure uses
the VTO override switch to electrically open the applicable refuel valve. Both procedures are satisfactory but
the manual override screw procedure is preferred because of safety. The VTO override switch can cause a spill
if the surge tank float switches do not operate. For both of these two procedures, the fuel measuring sticks are
to be used to monitor the fuel quantity.
A pressure refuel station, with two fuel hose receptacles, is found in the leading edge of each wing
between the engine nacelles. The refuel station, P42, in the left wing, contains the refuel control panel
to control and monitor the pressure refuel operation.
If the pressure refuel station is not available, the plane can be refueled by the overwing refuel
receptacles. The overwing fill ports are found on the top of each Main Tank, in the top wing skin.
The center wing tank and Reserve Tanks are filled by the transferring of fuel from the Main Tanks.
The 28 volts DC electrical power is supplied from the 28V DC BATT BUS when the power switch on the
P42 panel, or the fueling Power Switch on the M5 module is in the BATT position. The 28V DC GRND
HNDLG BUS is the normal electrical source, when both power switches (on the P42 panel and on the
M5 module) are in the NORM position. If there is no electrical power available, the refuel valves can be
operated manually. The fuel measuring sticks can be used to measure the fuel when there is no
electrical power.
Refuel the airplane at pressures more than 35 psig, but not more than 55 psig.
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A surge tank system is supplied to prevent overfill fuel leakage. If a failure in the overfill system
causes a fuel leakage, you must stop the refuel of the airplane to prevent a fire. The operation of the
refuel valves can be tested during a pressure refuel operation from either the underwing refuel
control panel, P42, or the cockpit fueling control module, M5. When you push the P42 TEST SYS
switch, or the cockpit FQ Test button, the open refuel valves are commanded closed momentarily and
then opened again to check the valves. It is not necessary to do this test each time you refuel the
airplane, but it does provide useful information about the operational status of the refuel valves.

2 FUEL SERVICING VEHICLE OPERATION

All fuel servicing vehicles approaching the aircraft shall STOP 25 feet from aircraft and ensure that there is sufficient
clearance, then proceed cautiously to position the vehicle safely under the wing before starting fueling procedures. If
the servicing vehicle must be backed into position, the use of a guide man is required. The unit must be prepared for
immediate shut-off of fuel supply and withdrawal of unit from under the aircraft in event of an emergency.

WAR NI NG
GROUND EQUIPMENT SHALL NOT BE POSITIONED UNDER WINGTIPS
DURING FUELING OPERATION.THE WINGS ARE DEFLECTED DOWNWARD
UNDER THE FUEL LOAD WITH THE WINGTIPS BEING DEFLECTED MOST.
FUEL TANKS ARE VENTED THROUGH THE WINGTIPS AND MAY PRODUCE A
DANGEROUS AND EXPLOSIVE MIXTURE AROUND THE WINGTIP.

3 STATIC GROUNDING/BONDING
1) Connect a bonding cable to a recognized bonding or grounding point on the airplane and a recognized
grounding or bonding point on the support equipment in use.

Caution
GROUND EQUIPMENT SHALL NOT BE POSITIONED UNDER WINGTIPS
DURING FUELING OPERATION.THE WINGS ARE DEFLECTED DOWNWARD
UNDER THE FUEL LOAD WITH THE WINGTIPS BEING DEFLECTED MOST.
FUEL TANKS ARE VENTED THROUGH THE WINGTIPS AND MAY PRODUCE A
DANGEROUS AND EXPLOSIVE MIXTURE AROUND THE WINGTIP.

WAR NI NG
DO NOT CONNECT A HEADSET AND DO NOT TOUCH ELECTRICAL
CONNECTIONS TO THE AIRPLANE DURING ATMOSPHERIC ELECTRICAL
ACTIVITY. LIGHTNING STRIKES CAN CAUSE INJURIES TO PERSONNEL, A
FIRE OR EXPLOSION DURING AN REFUEL OPERATION.

WAR NI NG
ALWAYS ATTACH THE GROUNDING CABLE TO THE GROUND CONNECTION
FIRST. NEVER ATTACH THE CABLE TO THE AIRPLANE AND THEN TO THE
GROUND CONNECTION.
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2) Attach grounding cable to a static ground and to the airplane in the following sequence:
a) Connect the grounding cable to an approved, identified static ground point. These points may be located
in the parking surface or in another fixed location.
b) Connect the grounding cable to approved grounding attach point on the airplane.
3) Before the airplane is moved, remove the ground cables from the approved grounding attach point on the
airplane.
4) When overwing fueling, connect a bonding cable from the fuel nozzle to the aircraft.

WAR NI NG
FUEL NOZZLE BONDING PLUG SHALL BE COMPLETLY INSERTED INTO
AIRCRAFT JACK BEFORE FUEL TANK FILLER CAP IS OPENED AND UNTIL
FILLER CAP IS CLOSED.

5) Ground aircraft to fuel transfer equipment before starting any fuel transfer operation.

4 FUELING PREPARATIONS
Do not fuel when thunderstorms or lightning within a ten (10) mile radius.
In the event of rain during over wing fueling operations, take precautions to prevent possibility of water entering tank
compartments.
Whenever an aircraft is being fueled, ramp personnel should know the locations of fire fighting equipment, fire alarms
and telephone numbers, which can be used in the event of an emergency.
When ramp extinguishers are used as part of the local plan, there should be unrestricted access to them, and to the
aircraft. One extinguisher can be used between two aircraft.
If fueling nozzles are utilized, do not block or wedge nozzle lever open. Check that ratchet stops on fuel nozzles have
been removed to prevent latching nozzle opening. Check that the deadman valve(s) are spring-loaded to off (closed)
position.
Moving of equipment that may cause a spark is prohibited in fueling areas.
Remove fueling equipment from service for any of the following conditions:
• Fuel leakage which may create a hazard.
• Deadman switch not operating properly.
• Electrical conditions which may create a hazard.
• Coupler driveway interlock system not operating.
• Pressure exceeds 70 psig (± 5 psig) on "no flow" check.

Caution
IF "NO FLOW" PRESSURE EXCEEDS 70 PSIG (± 5 PSIG) FUELING EQUIPMENT
SHOULD NOT BE USED.

Caution
IF NO OTHER EQUIPMENT IS AVAILABLE, EQUIPMENT MAY BE USED ON AN
EMERGENCY BASIS HAVING RESPONSIBLE PERSONNEL, OR AUTHORIZED
DESIGNEE, MONITOR FUELING UNIT GAUGE TO ASSURE THAT 50 PSIG (± 5
PSIG) "FLOW" PRESSURE IS NOT EXCEEDED DURING FUELING OPERATION.
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Caution
NO LIMITS FOR MOMENTARY PRESSURE SURGES (SPIKES) WHICH CAN
OCCUR AS VALVES SHUT OFF IN FUEL TANKS.

Prior to each underwing fueling operation:

• Check the "No Flow" pressure of pumping unit, maximum 70 psig (±5 psig).
• Check the "Flow" pressure maximum 50 psig (±5 psig).
When fueling aircraft, a properly trained and qualified employee must:
• Assure that the truck meter reading is zero and note totalizer reading before fueling operation begins.
• Confirm truck meter reading and note totalizer reading before fueling operation is completed.
Sign vendor delivery ticket for quantity of fuel delivered after checking accuracy of all entries.

NOTE
Ensure that all pressure fueling adapter caps at the aircraft fu-
eling station are installed after the fueling operation stops. Report any
missing and /or defective pressure fueling adapter caps and inoper-
ative fuel quantity gauges to the Captain or First Officer and if avail-
able, the Chief Maintenance Inspector.

5 USE OF ELECTRICAL POWER

• Do not disconnect or connect ground power source during fueling operation.
• Battery, ground, or APU power may be left on.

Caution
THE STEPS THAT FOLLOW ARE IMPORTANT!

• Aircraft ignition switches must be off.

• Checking and use of electrical switches in cabin or cockpit is permissible.
• Do not connect or disconnect electrical circuit connections in area of wing, pylon, or engine pod being fueled.
• Do not operate aircraft radar.
• Do not operate HF radio.
• Do not operate fuel jettison system components
• Cabin and cockpit lights may be left on.

6 REFUELING WITH PASSENGERS ONBOARD

14 CFR 121.135(b)(19)
Passengers may remain on or be allowed to move onto and off the aircraft during normal underwing fueling/defueling
operations. Fuel trucks must be positioned so as to not block emergency exits or next to open exits.

NOTE
Smoking is not permitted during refueling (passengers, Flight Deck
crew, Cabin crew and Ground crew) .
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During refueling where passengers remain onboard the aircraft, the engines will be shut down and a floor level exit will
remain open with a ramp/jetbridge positioned at the door. One Steward must remain at the boarding door. The minimum
crew complement will be uniformly distributed throughout the cabin to provide the most effective assistance for
evacuation in case of an emergency. The Purser will make an announcement reminding passengers that smoking is not
permitted on the ground, along with a request to keep the aisles clear and for passengers to remain in seats with seat
belts unfastened. The announcement will also state that the “No Smoking” sign is illuminated and that compliance with
this regulation is mandatory.
Stewards will be on board to enforce the no smoking rule and to inform the fueling crew if fuel vapors are detectable in
the cabin. The Captain is responsible to ensure that no passengers are onboard without the required crewmembers or
designees. Should such fumes be reported to the Flight Deck or Cabin crew, they will inform the fueling crew and the
fueling operation will stop at once and will continue only after the condition is investigated and it has been determined
safe to continue.
If only employees are aboard, a stand or ladder must be provided at either the crew entrance or the main cabin door.

6.1 Passengers Deplaned or Boarded

Refueling during the period in which passengers are being deplaned or boarded may be performed under the following
circumstances:
• Refueling of right or left wing may be accomplished during the boarding or deplaning of passengers when
underwing fueling method is being used.
Fueling Personnel and cabin crew are alerted to direct all persons away from areas of possible fuel spillage (for
example: fueling equipment and wing fuel tank vents). A hazardous area must be identified for boarding or unloading
passengers during a refuel operation. Barriers must be in position to stop passengers from entering this hazardous
area.

7 FUELING WITH APU OPERATING

During operation of the APU, a qualified individual will be assisting the ground crew to assure a safe refueling
operation. Qualification in this instance shall mean demonstrated knowledge and capability to operate the APU using
both normal and emergency procedures.
Minimum fuel in tank(s) and other APU operating limits are to be observed per 747 AMM Chapter 49, Maintenance
Practices.
1) Comply with the limits for APU operation (AMM 49-11-00/201).

WAR NI NG
COMPLY WITH THE SUBSEQUENT LIMITS AND PRECAUTIONS FOR APU
OPERATION DURING REFUELING. IF YOU DO NOT COMPLY WITH THESE
PRECAUTIONS, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN
OCCUR

2) You can start the APU during a refueling operation if the start is an initial start or a restart after normal
shutdown.
3) (You can shutdown the APU (manual or automatic) during a refueling operation.
4) If the low pressure indication light comes on during APU DC fuel pump operation, immediately shut down the
APU (AMM 49-11-00/201) so the pump will shut off. The switch for the APU DC fuel pump will not shut off the
pump if the APU is operating.
5) If there is a protective automatic shutdown or failure to start condition on the APU, stop the refueling operation
and disconnect the fuel hose(s) from the airplane fueling adapter(s) before you start the APU again.
6) If an APU fire occurs, do these steps in this sequence:
a) Stop the refueling operation.
b) The APU should shutdown automatically.
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c) If the APU does not shutdown automatically, do the APU Emergency Shutdown Procedure (AMM 49-
11-00/201).
d) Discharge the APU fire bottles (AMM 49-11-00/201).
e) Comply with all airport and operator provided fire protection, emergency procedures.
7) If a fuel spill occurs, do these steps:
a) Unload and shutdown the APU (AMM 49-11-00/201).
b) Do not start the APU again until the fire department or the person(s) in charge have given approval.
8) Comply with this APU exhaust precaution during refueling operations:
a) Ensure the fueling vehicles are in a position that avoids any risk of coming in the path of the APU
exhaust stream.
Do not re-start an APU if that APU experienced an automatic shutdown or a failed start attempt during its previous
operation, unless refueling is suspended.
If a fuel spillage occurs during refueling with the APU operating, quick evaluation of the size of the spill and
evaluation is very important by ground personnel involved in the refueling and handling of the aircraft. The following
procedures must be quickly evaluated by the ground personnel but not necessarily in this order.
• Shut down the APU
• Discontinue fueling
• Notify fire department
• Transfer fuel from tank with spillage
• Shutdown support equipment and evacuate non-essential personnel
• Move portable firefighting equipment into position
• Attempt to contain fuel spill, see Chapter 12 - Handling Fuel Spills
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8 FUELING WITH ONE ENGINE OPERATING

14 CFR 121.135(b)(19) & B747 AMM Chapter 12
This alternate procedure is to be used only when it is known that an engine cannot be re-started because of
inoperative ground equipment and/or aircraft APU, and provided that the airport regulations permit.

WAR NI NG
ALL PERSONNEL NOT DIRECTLY INVOLVED WITH THE FUELING
OPERATION MUST VACATE THE AIRCRAFT AND REMAIN AT A DISTANCE OF
FIFTY FEET OR MORE. KEEP ALL PERSONS CLEAR OF RUNNING ENGINE.
PERSONNEL NOT DIRECTLY NEEDED FOR THE FUELING OPERATION
SHALL MAINTAIN A SAFE DISTANCE FROM THE AIRCRAFT.

Due to non-routine nature of this operation, personnel involved must be briefed before fueling operation is started.
Aircraft must be positioned at a distance of fifty feet or more away from any buildings or other aircraft.
Aircraft will be generally headed into the wind.
In the event an airplane with an inoperative APU requires refueling at an enroute stop that is not equipped with an air
supply for starting, refueling may be accomplished with No. 4 engine operating to furnish electrical power and air,
provided the following precautions are observed
• One pilot's station and FE station must be occupied by a qualified Flight Deck crewmember or authorized
mechanic.
• Wheels chocked and parking brake set.
• Hydraulic system pressurized and hydraulic brake pressure normal.
• Communication established and maintained between the Flight Deck and Ground personnel via the service
interphone system.
• All non-essential personnel and equipment must remain clear of aircraft.
• Local airport manager and fire department authorities must be notified prior to fueling.
• All passengers must be deplaned.

9 OVERWING FUELING
Overwing fueling is a seldom used procedure and maintenance personnel must be involved as it requires extending
the leading edge flaps of the wing and installing the safety locks. All procedures in the Aircraft Maintenance Manual
(AMM), Chapter 12, Servicing, must be followed. Avatar has the following policies if the overwing fueling method is
used:
• At least two persons will be assigned to the fuel nozzle during overwing fueling.
• Persons directly engaged in handling overwing fuel nozzles at the tank filler will wear only cotton outer
garments.
• Passengers may not be aboard the aircraft or boarded, until the overwing fueling operation is complete.
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CHAPTER 5 TOC Chapter 5 TOC

CHAPTER 5 - PRESSURE FUELING................................................................................................................ 5.1

1. PREPARATION FOR PRESSURE FUELING ................................................................................................................. 5.1
2. AUTOMATIC PRESSURE REFUELING - SERVICING .................................................................................................. 5.5
2.1 General ............................................................................................................................................................ 5.5
2.2 Automatic Pressure Refuel .............................................................................................................................. 5.5
3. MANUAL PRESSURE REFUELING ............................................................................................................................... 5.13
3.1 General ............................................................................................................................................................ 5.13
3.2 References ....................................................................................................................................................... 5.13
3.3 Access ............................................................................................................................................................. 5.13
3.4 Prepare the Airplane for a Manual Refuel Operation ....................................................................................... 5.14
3.5 Connect the Fueling Equipment ....................................................................................................................... 5.14
3.6 Prepare the Refuel Control Panel, P42 ............................................................................................................ 5.15
3.7 Prepare the Fuel Sheet .................................................................................................................................... 5.15
3.8 Begin the Refuel Operation .............................................................................................................................. 5.15
3.9 Stop the Refuel Operation ............................................................................................................................... 5.16
3.10 Put the Airplane Back to the Usual Condition .................................................................................................. 5.16
4. ALTERNATE REFUELING PROCEDURES .................................................................................................................... 5.17
4.1 General ............................................................................................................................................................ 5.17
4.2 Refuel Operation - Inoperative Refuel Valve ................................................................................................... 5.17
4.3 Refuel Operation - Inoperative Fueling Quantity Indicator ............................................................................... 5.20
4.4 Airplanes With Goodrich Digital FQIS .............................................................................................................. 5.25
5. OVERWING FUELING .................................................................................................................................................... 5.28
5.1 General ............................................................................................................................................................ 5.28
5.2 Overwing Refueling (Fig. 5.5) .......................................................................................................................... 5.28
5.3 Connect the Fueling Equipment ....................................................................................................................... 5.30
5.4 Overwing Refuel Operation .............................................................................................................................. 5.31
5.5 Stop the Overwing Refuel Operation ............................................................................................................... 5.32
5.6 Put the Airplane Back to the Usual Condition .................................................................................................. 5.32

00
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Chapter 5 CHAPTER 5 - PRESSURE FUELING

1 PREPARATION FOR PRESSURE FUELING

14 CFR 121.135(b)(17), 121.135(b)(19)

WAR NI NG
STOP THE REFUEL OPERATION DURING ATMOSPHERIC ELECTRICAL
ACTIVITY. DO NOT CONNECT A HEADSET AND DO NOT TOUCH ELECTRICAL
CONNECTIONS TO THE AIRPLANE. LIGHTNING STRIKES CAN CAUSE
INJURIES TO PERSONNEL, AND A FIRE OR EXPLOSION DURING A REFUEL
OPERATION.

1) Position the fuel servicing vehicle at the airplane, ensure that the equipment:
a) Has a clear exit path at all times
b) Does not interfere with access to the aircraft for rescue or fire protection
c) Does not obstruct the passenger evacuation routes
d) Does not obstruct the chute deployment areas.

Caution
ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THE AIRPLANE.
BONDING CABLES ATTACHED TO COMPOSITE DOORS OR FAIRINGS DO NOT
GIVE AN ELECTRICAL BOND. INCORRECTLY ATTACHED BONDING CABLES
CAN CAUSE SCRATCHES. THESE SCRATCHES CAN CAUSE CORROSION AND
CRACKS ON STRESSED PARTS.

2) Connect a bonding cable from the fueling source to an approved electrical grounding or bonding connection on
the airplane.Supply the electrical power, if it is not available

NOTE
If the fueling source has a permanently attached grounding/bonding
cable, you can use it here.

Caution
EXCEPT IN EMERGENCY CASES, APU OPERATION SHOULD NOT BE STOPPED
IF A LEAKAGE OF FUEL OCCURS WHILE REFUELING. A SUDDEN STOP OF THE
APU WITH A LOAD CAN PUSH GASES THAT BURN BACK THROUGH THE
COMPRESSOR.

WAR NI NG
DO NOT PUT GROUND EQUIPMENT BELOW THE WING TIPS DURING THE
REFUELING OPERATION. THE FUEL TANKS ARE VENTED THROUGH THE
WINGTIP VENTS.AN EXPLOSIVE MIXTURE OF FUEL VAPOR CAN EXIST AT
THESE LOCATIONS.
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WAR NI NG
THE WINGS MOVE DOWN WITH THE FUEL LOAD. THE WINGTIPS MOVE THE
MOST. THE FUEL TANKS ARE OPEN TO THE AIR THROUGH THE WINGTIPS.
A CONCENTRATION OF DANGEROUS AND EXPLOSIVE GASES CAN BE IN
THESE AREAS.

WAR NI NG
DO NOT OPERATE THE HF OR THE WEATHER RADAR DURING THE REFUEL
OPERATION. IF OPERATED, IT COULD CAUSE INJURY TO PERSONS AND
CAUSE DAMAGE TO THE AIRPLANE.

3) Ensure the landing gear doors and the overwing entry doors are closed.
4) Ensure that the FUEL CONTROL switches are in the CUTOFF position.
5) Wing pressure relief valves (4 locations) closed.

WAR NI NG
ENSURE THE FUEL CONTROL SWITCHES ARE IN THE CUTOFF POSITION.
FAILURE TO SET THE FUEL CONTROL SWITCHES TO THE CUTOFF
POSITION CAN CAUSE AN AUTOMATIC FIRING OF THE IGNITER PLUGS. THE
IGNITER PLUGS WILL FIRE WHEN THE FLAPS ARE OUT OF ZERO DETENT,
THE NACELLE ANTI-ICE IS ON, THE FLIGHT START SWITCH IS SET TO "ON",
OR THE ENGINE START SWITCH IS PULLED TO "ON". WITH FUEL LOCATED
IN THE COMBUSTION CHAMBER, AN INTERNAL ENGINE OR TAILPIPE FIRE
CAN CAUSE INJURY TO PERSONS OR CAUSE ENGINE DAMAGE.

WAR NI NG
ENSURE THE CIRCUIT BREAKERS FOR THE FUEL CONTROL VALVES ARE
CLOSED. FAILURE TO OPEN THE APPLICABLE ENGINE IGNITION CIRCUIT
BREAKERS BEFORE YOU OPEN THE ENGINE FUEL CONT VALVE CIRCUIT
BREAKERS CAUSES AN AUTOMATIC FIRING OF THE IGNITER PLUGS IF/
WHEN FLAPS ARE FLIGHT START OUT OF ZERO DETENT, THE NACELLE
ANTI-ICE IS ON, THE CONIGNITION SWITCH IS SET TO "ON". WITH THE FUEL
IN THE COMBUSTION CHAMBER, INTERNAL ENGINE OR TAILPIPE FIRE CAN
CAUSE INJURY TO PERSONS OR CAN CAUSE ENGINE DAMAGE

6) Ensure that these circuit breakers are closed:

a) On the P 12 distribution panel:
• C9600, FUEL QTY 1
• C9601, FUEL QTY 2
b) On the main power panel, P6:
• C9602, FUELING POWER BATTERY
• C86, FUELING VALVES (BATTERY)
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c) On the P 14 panel:
• C9603, FUELING POWER
• C90, FUELING VALVES
7) Open the P42 access doors to get access to the refuel station.
8) Remove the refuel receptacle caps and connect the bonding cable attached to the refuel nozzle to an approved
airplane electrical ground.
9) Visually check fueling receptacle and clean any foreign material before connecting the refueling nozzle.
10) Ensure there are no fuel leaks at the refuel receptacle and the receptacle adapter is in the correct position

Caution
ENSURE THE DEFUEL LEVER IS CORRECTLY POSITIONED IN THE RECESS ON
THE REFUEL RECEPTACLE ADAPTER. IF THE DEFUEL LEVER IS NOT IN THE
CORRECT POSITION, IT IS POSSIBLE TO DAMAGE THE REFUEL RECEPTACLE
ASSEMBLY. IF THE REFUEL RECEPTACLE ASSEMBLY IS DAMAGED, A FUEL
LEAK CAN OCCUR.

Caution
DO NOT HAVE MORE THAN 55 PSI OF FUEL PRESSURE AT THE REFUEL
NOZZLE. THIS IS TO PREVENT DAMAGE TO THE REFUEL SYSTEM
COMPONENTS.

11) Connect the refuel nozzles to the refuel receptacles.

12) Open the manual shutoff valves at the refuel receptacles.
13) If the refuel is to be controlled from the P42 panel:
a) Open the access door fully to get access to the P42 refuel control panel, and get power to the panel.
b) Ensure that panel floodlights come on and the indicators give a fuel quantity indication.

NOTE
As opening of the refuel panel door causes a shift in FQIS power
sources, there may be a delay of several seconds before fuel quantity
information is displayed.

c) Put the POWER switch on the refuel control panel in the NORM or BATT position.
d) Push the TEST GAUGES switch on the refuel control panel for a minimum of one second.
e) Ensure that all the indicator displays read 888.8 for one second and then go off for one second.
f) Release the TEST GAUGES switch and ensure the indicators go to the usual indication.

NOTE
If you continue to hold the TEST GAUGES switch, the display will con-
tinue to show 888.8 for one second and then go off for one second un-
til you release the switch.

NOTE
If the indicator does not operate, the fuel quantity in the tank can be
monitored by the fuel measuring sticks.
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g) Do a push to test all the valve position lights on the P42 refuel control panel. Ensure each light comes
on when pushed.
14) If the refuel is to be controlled from the M5 module in P4 panel on the cockpit:
a) Switch the FUELING OVERRIDE switch to the ON position.
b) Ensure the fuel quantity indicators continue to give fuel quantity indication.

NOTE
As switching the Fueling Override Switch ON causes a shift in FQIS
power sources, there may be a delay of several seconds before fuel
quantity information is displayed.

c) Put the POWER switch on the M5 fueling panel in the NORM or BATT position.
d) Push the FQ TEST switch on the P4 panel for a minimum of one second.
e) Ensure that all of the indicator displays show 888.8 for one second and then go off for one second.
f) Release the FQ TEST switch and ensure the indicators go to the usual indication.

NOTE
If you continue to hold the FQ TEST switch, the displays will continue
to show 888.8 for one second and then go off for one second until you
release the switch.

NOTE
If the indicator does not operate, the fuel quantity in the tank can be
monitored by the fuel measuring sticks.

g) Do a push to test all the valve position lights on the P4 panel. Ensure each light comes on when
pushed.
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2 AUTOMATIC PRESSURE REFUELING - SERVICING

2.1 General
1) This procedure contains this task:
a) Automatic Pressure Refuel
2) Automatic pressure refueling uses the Fuel Quantity Processor Unit (FQPU) to control the fuel distribution and
fuel shutoff.

2.2 Automatic Pressure Refuel

2.2.1 General

1) This task uses the automatic pressure refuel system to refuel the airplane.
2) 747-400 ;
If the total fuel load will be 50,000 pounds or less, use the manual pressure refueling procedure to refuel the
airplane (AMM 12-11-03/301).

2.2.2 References

1) AMM 12-11-01/301, Fuel Servicing

2) AMM 20-41-01/201, Static Grounding
3) AMM 24-29-00/001, Standby 115-Volt AC Power Generation
4) AMM 27-81-00/201, Leading Edge Flap System
5) AMM 28-26-00/201, Defueling

2.2.3 Access

1) Location Zones
221 Control Cabin, Left
222 Control Cabin, Right
521 Leading Edge to Front Spar, Left
621 Leading Edge to Front Spar, Right
2) Access Panels
521BB Fueling Station Access Door
521CB Fueling Control Panel Access Door
621BB Fueling Station Access Door

2.2.4 Prepare the Airplane for a Refuel Operation

1) Read and comply with the precautions in this task: Precautions and Limits for Fuel Servicing
(AMM 12-11-01/301).

WAR NI NG
COMPLY WITH ALL THE REFUEL OPERATIONS PRECAUTIONS IN AMM 12-11-
01/301. FAILURE TO COMPLY WITH THE REFUEL PRECAUTIONS CAN CAUSE
SERIOUS INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

2) Do this task: Prepare the Airplane for a Refuel Operation (AMM 12-11-01/301).
3) Connect the Fueling Equipment (Fig. 5.1
a) Do the operator supplied procedures to position the fuel servicing vehicle.
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Figure 5.1 Fueling Station and Refuel Control Panel

NO. 2 MAIN
TANK

REFUELING
CONTROL
PANEL
LEFT WING
FUELING STATION SEE B
(RIGHT WING OPPOSITE)
SEE A

LEFT WING

FUELING
RECEPTACLE FUELING
RECEPTACLE FUEL STATION DOOR,
521BB OR 621BB

CAP

MANUAL HANDLE
FOR THE FUELING
GROUNDING SHUTOFF VALVE
MANUAL JACKS (NOT SHOWN)
MANUAL HANDLE DEFUELING
FOR THE FUELING VALVE
SHUTOFF VALVE

FUELING STATION
A
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Figure 5.2 Fueling Locations

PRESSURE FUELING OVERFILL REFUEL VALVE

OVERFILL REFUEL VALVE
SYSTEM TEST SWITCH INDICATOR POSITION
RESET CONTROL SWITCH
LIGHT INDICATOR
SWITCH LIGHT
INDICATOR TEST POWER
TEST SWITCH VALVE POSITION/CONTROL (MANUAL)
GAGES SYS OVERFILL
BATT
OPEN REFUEL POWER
NORM
CLOSED SELECT SWITCH
R L 1 0

RESET
CENTER MAIN 2 MAIN 1 RESERVE 1 RESERVE 2 1
TOTAL FUEL

ACTUAL
X 1000 X 1000 X 1000 X 1000 X 1000 X 1000
PRESELECT
TOTAL FUELING QUANTITY
PRESELECT SWITCH SET QTY INDICATOR
SELECT QTY MAIN 3 MAIN 4 RESERVE 4 RESERVE 3 1
OPEN
VALVE PRESELECT
CLOSED 1 6 3 2 1 0
CONTROL SWITCH ALL VALVES OPEN
PRESELECT
CONTROL QTY X 1000 CLOSED

THUMBWHEEL
REFUEL CONTROL PANEL, P42
(7 OR 9 TANK CONFIGURATION)
B
REFUEL VALVE
OVERFILL REFUEL VALVE POSITION
INDICATOR VALVE PRESELECT CONTROL SWITCH INDICATOR
LIGHT CONTROL SWITCH (EXAMPLE) LIGHT (EXAMPLE)

INDICATOR
POWER
TEST SWITCH TEST ALL
OVERFILL VALVE POSITION/CONTROL (MANUAL)
VALVES
BATT
PRESSURE OPEN OPEN REFUEL
NORM
FUELING CLOSED R
POWER
GAUGES R L R L
SYSTEM TEST SELECT
CLOSED
SWITCH SWITCH
SYSTEM RESET
CENTER CENTER CENTER RESERVE 1 RESERVE 2

OVERFILL
ACTUAL
RESET SWITCH X 1000 X 1000 X 1000 X 1000 X 1000 X 1000

PRESELECT FUELING
ENTER
QUANTITY
PRESELECT TOTAL CENTER MAIN 3 MAIN 4 RESERVE 4 RESERVE 3 INDICATOR
PRESLECT CONTROLM
AUX
SWITCH (EXAMPLE
SELECT QTY

0 0 0 0 OPEN
CLOSED
ISOLATION FUELING
QTY X 1000 VALVE VALVE

THUMBWHEEL
(EXAMPLE)
REFUEL CONTROL PANEL, P42
(AIRPLANES WITH BODY FUEL TANK(S))
B
1 AIRPLANES WITH NO. 2 OR NO. 3
RESERVE TANKS
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Figure 5.3 Flight Compartment Fueling Components

DC METERS MODULE
SEE A

FLIGHT COMPARTMENT

40 100
DC 50 150
30 VOLTS + DC

20
0
-
0
50
AMPS

10 100 150

DC METERS
BATTERY BATTERY
SWITCH ON ON ON
ON
APU ESS
BATT
BATT TR
ON ON ON

OFF TR 1 TR 2 TR 3

DC METERS MODULE
A
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4) Connect a bonding cable from the fueling source to an approved electrical grounding or bonding connection on
the airplane (AMM 20-41-01/201).

WAR NI NG
COMPLY WITH THE PRECAUTIONS IN AMM 20-41-01/201 FOR ATTACHMENT OF
BONDING CABLES. AN ADEQUATE ELECTRICAL BOND MAY NOT EXIST IF THE
BONDING CABLES ARE NOT INSTALLED AT APPROVED AIRPLANE GROUND
CONNECTIONS. IF THE FUEL SERVICE EQUIPMENT AND AIRPLANE ARE NOT
CORRECTLY BONDED, A FIRE OR EXPLOSION CAN OCCUR.

Caution
COMPLY WITH THE PRECAUTIONS IN AMM 20-41-01/201 FOR ATTACHMENT OF
BONDING CABLES. AN ADEQUATE ELECTRICAL BOND MAY NOT EXIST IF THE
BONDING CABLES ARE NOT INSTALLED AT APPROVED AIRPLANE GROUND
CONNECTIONS. IF THE FUEL SERVICE EQUIPMENT AND AIRPLANE ARE NOT
CORRECTLY BONDED, A FIRE OR EXPLOSION CAN OCCUR.

5) Open the access doors, 521BB and 621BB, to get access to the fueling station.
6) Connect the bonding cable attached to the refuel nozzle to an approved airplane electrical ground (AMM 20-
41-01/201).

NOTE
The bonding cable is not necessary if there is electrical continuity be-
tween the fueling source and the fueling nozzle.

7) Connect the fuel hose to the fueling receptacle adapter (View A, Fig. 5.2)

WAR NI NG
ENSURE THERE IS NO TENSION ON THE HOSE DURING THE REFUELING
OPERATION. THE HOSE MUST HANG FREELY FROM THE REFUEL ADAPTER
WITH NO TENSION (PRELOAD) IN ANY DIRECTION. TENSION ON THE HOSE
CAN DAMAGE THE FUEL RECEPTACLE AND CAUSE THE HOSE TO
DISCONNECT. INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN
OCCUR.

a) Remove the cap for the fueling receptacles.

b) Ensure there are no fuel leaks.
c) Ensure the fueling receptacle adapter is clean and not damaged.
1) Look for screws that attach to the adapter that are loose, damaged or missing.
2) Look for lugs on the adapter are bent, cracked or missing.
d) Connect the refuel nozzle to the fueling receptacle.
e) Repeat these steps for each fuel hose.
8) Put the manual handle for the FUELING SHUTOFF VALVE to the OPEN position (left wing and right wing, if
necessary).
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2.2.5 Prepare the Refuel Control Panel, P42

1) Fully open access door 521CB (Fig. 5.1).

2) Ensure the panel floodlights come on.
3) If the floodlights do not come on (no ground power), then do these steps:
a) Put the main battery (BATTERY) switch, P4, in the flight compartment to the ON position (Fig. 5.3).
b) Ensure the STANDBY POWER switch is in the OFF position.
c) Put the POWER switch on the P42 panel to the BATT position (Fig. 5.3).
4) Test the indicator lights:
a) Push the PRESS TO TEST indicators lights.
b) Ensure each light comes on when pushed.
5) Test the fueling quantity indicators:
a) Push and hold the TEST GAGES switch for a minimum of 1 second.
b) Ensure all the indicator displays show 888.8 for one second and then go off for 1 second.

NOTE
The test display will continue to cycle until you release the switch.

c) Release the TEST GAGES switch.

d) Ensure all fuel quantity displays go back to the usual indication.

2.2.6 Prepare the Fuel Sheet

1) Use the operator supplied fuel sheet to record the pre-uplift fuel quantity for each tank.
2) Calculate the fuel to be uplifted converted to volume (if necessary).
3) Record the uplift quantity on the fuel sheet (if necessary).

2.2.7 Total Preselect Pressure Refuel

NOTE
To refuel and distribute the fuel load to a set fuel quantity, do the total
preselect refuel operation.

1) Ensure the onboard fuel load is in a valid fuel distribution configuration (equivalent to after a flight operation).
2) Do these steps to input the total preselect fuel quantity, on the P42 panel:
a) Set the SELECT QTY thumbwheels to the total fuel quantity necessary.
b) Move the preselect (SET QTY or TOTAL) switch to the TOTAL or ENTER position and release.
c) Ensure the TOTAL FUEL PRESELECT indicator value is the same as the SELECT QTY thumbwheel
value.
d) If the TOTAL FUEL PRESELECT indicator is blank, move the preselect (SET QTY or TOTAL) switch to
the TOTAL or ENTER position again.

NOTE
A fuel quantity value will be set into the indicator.

e) Makes sure the P42 panel is set for the refuel operation:
f) VALVE POSITION CONTROL switches - CLOSED
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g) ALL VALVES switch - CLOSED

h) AIRPLANES WITH BODY FUEL TANK(S); }
ISOLATION VALVE - OPEN (if body fuel tank is to be refueled)
i) SELECT QTY thumbwheel - set to total preselect value
j) TOTAL PRESELECT indicator - same as SELECT QTY thumbwheel value

2.2.8 Begin the Refuel Operation

1) Put the ALL VALVES switch to the OPEN position.

2) Activate the fuel shutoff control switch (deadman switch) to start the fuel flow.

Caution
DO NOT USE THE MANUAL HANDLE FOR THE FUELING SHUTOFF VALVES TO
REDUCE OR STOP THE REFUEL OPERATION. IF THE MANUAL HANDLE IS
CLOSED DURING THE REFUEL OPERATION, A PRESSURE SURGE AND
SUBSEQUENT DAMAGE COULD OCCUR.

3) Ensure the refuel pressure is between 35 and 55 psi.

Caution
DO NOT USE MORE THAN 55 PSI FUEL PRESSURE AT THE NOZZLE. DAMAGE
TO THE REFUEL SYSTEM CAN OCCUR.

4) Ensure the refuel valve indication lights come on (valves open).

5) Ensure the left and right wing fuel tanks refuel at approximately the same rate.

NOTE
The FQPU will automatically control the distribution of the fuel load.

6) Push the TEST SYS switch for a minimum of 2 seconds and then release the switch.

NOTE
When you press the TEST SYS switch, the FQPU momentarily closes
the refuel valves to check for FQPU valve shutoff control

a) The refuel valve lights will go out and then come on again.
b) The refuel operation will continue.
7) Ensure the fuel flow to the CWT begins again.
8) Monitor the fueling quantity indicators and refuel valve indication lights.
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2.2.9 Stop the Refuel Operation

1) Release the deadman switch to stop the fuel flow when all of the refuel valve position lights are off.

NOTE
The FQPU will automatically close the tank refuel valve(s) when the
tank fuel quantity is at VTO or the preselect value.

2) Put the ALL VALVES switch to the CLOSED position.

3) AIRPLANES WITH BODY FUEL TANKS;
Put the CENTER AUX ISOLATION VALVE to the CLOSED position, if opened.
4) Ensure the onboard fuel load is in a valid pre-flight fuel distribution.
5) Transfer fuel to balance the fuel load if necessary (AMM 28-26-00/201).
6) Wait 1 minute to let the FQIS system stabilize.
7) Record the actual fuel quantities from the fueling quantity indicators.
8) Record the actual fuel quantity from the fuel vehicle flow meter.
9) Do the discrepancy check and ensure it is within limits.

NOTE
Per operator's requirement.

10) Complete the Fuel Sheet.

11) Complete the Delivery Receipt if necessary.
12) Give a copy of the forms to the airline representative or flight crew.

2.2.10 Put the Airplane Back to the Usual Condition

1) Put the manual handle for the FUELING SHUTOFF VALVE to the CLOSED position (left and right wing).
2) Ensure all the P42 panel valve switches are in the CLOSED position.
3) Put the POWER switch to the NORM position (if necessary).
4) If the airplane battery power was used, set the main battery (BATTERY) switch, P4, in the flight compartment
to the OFF position (Fig. 5.3).
5) Disconnect the refuel nozzle from the airplane (Fig. 5.1).
6) Remove the refuel nozzle bonding cable (if installed).
7) Ensure the fueling receptacle adapter is not damaged.
8) Install the cap for the fueling receptacles.
9) Repeat the steps for each fuel hose.
10) Close and security latch these doors:
a) Fueling station access door, 521BB and 621BB
b) Fueling control panel access door, 521CB.
11) Disconnect the bonding/grounding cables (AMM 20-41-01/201).
12) Do the operator supplied procedures to remove the fuel servicing vehicle.
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13) Do this task for extended leading edge flaps: Safety Locks Removal and Extended Leading Edge Activation
(AMM 27-81-00/201).

WAR NI NG
DO THE PROCEDURE IN AMM 27-81-00/201 TO REACTIVATE THE EXTENDED
LEADING EDGE FLAPS. THE FLAPS MOVE QUICKLY AND CAN CAUSE INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT.

3 MANUAL PRESSURE REFUELING

3.1 General
1) This task uses the pressure refuel system to refuel an individual tank or all of the fuel tanks.
2) The electrical refuel valve switches are opened one at a time (manually) for each fuel tank that is to be
refueled.
3) Manual pressure refueling lets the operator control the quantity of fuel in each tank. The fuel quantity processor
unit (FQPU) does not control the fuel distribution. Volumetric top off (VTO) is controlled by the FQPU.
4) You must monitor the fuel distribution to prevent an out of limits center of gravity (CG) or lateral imbalance
condition. To keep the CG and lateral imbalance in the correct limits, it is recommended that all the refuel
valves be opened at the same time.
5) The selected tanks will continue to fill until the refuel valve switch is put in the CLOSED position, or the VTO
level is reached.

3.2 References
1) AMM 12-11-01/301, Fuel Servicing
2) AMM 20-41-01/201, Static Grounding
3) AMM 24-29-00/001, Standby 115-Volt AC Power Generation
4) AMM 27-81-00/201, Leading Edge Flap System
5) AMM 28-26-00/201, Defueling

3.3 Access
1) Location Zones
221 Control Cabin, Left
222 Control Cabin, Right
521 Leading Edge to Front Spar, Left
621 Leading Edge to Front Spar, Right
2) Access Panels
521BB Fueling Station Access Door
521CB Fueling Control Panel Access Door
621BB Fueling Station Access Door
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3.4 Prepare the Airplane for a Manual Refuel Operation

1) Read and comply with the precautions in this task: Precautions and Limits for Fuel Servicing
(AMM 12-11-01/301).

WAR NI NG
COMPLY WITH ALL THE FUEL SERVICING PRECAUTIONS. FAILURE TO
COMPLY WITH THE PRECAUTIONS CAN CAUSE SERIOUS INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.

2) Do this task: Prepare the Airplane for a Refuel Operation (AMM 12-11-01/301).

3.5 Connect the Fueling Equipment

1) Do the operator supplied procedures to position the fuel servicing vehicle.
2) Connect a bonding cable from the fueling source to an approved electrical grounding or bonding connection
on the airplane (AMM 20-41-01/201)

Caution
COMPLY WITH THE PRECAUTIONS IN AMM 20-41-01/201 FOR ATTACHMENT
OF BONDING CABLES. AN ADEQUATE ELECTRICAL BOND MAY NOT EXIST IF
THE BONDING CABLES ARE NOT INSTALLED AT APPROVED AIRPLANE
GROUND CONNECTIONS. IF THE FUEL SERVICE EQUIPMENT AND
AIRPLANE ARE NOT CORRECTLY BONDED, A FIRE OR EXPLOSION CAN
OCCUR.

3) Open the access doors, 521BB and 621BB, to get access to the fueling station.
4) Connect the bonding cable attached to the refuel nozzle to an approved airplane electrical ground
(AMM 20-41-01/201) See Fig 5.1.
5) Connect the fuel hose to the fueling receptacle adapter (View A, Fig. 5.3):

WAR NI NG
ENSURE THERE IS NO TENSION ON THE HOSE DURING THE REFUELING
OPERATION. THE HOSE MUST HANG FREELY FROM THE REFUEL ADAPTER
WITH NO TENSION (PRELOAD) IN ANY DIRECTION. TENSION ON THE HOSE
CAN DAMAGE THE FUEL RECEPTACLE AND CAUSE THE HOSE TO
DISCONNECT. INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN
OCCUR.

6) Remove the cap for the fueling receptacles.

7) Ensure there are no fuel leaks.
8) Ensure the fueling receptacle adapter is clean and not damaged.
a) Look for screws that attach to the adapter that are loose, damaged or missing.
b) Look for lugs on the adapter are bent, cracked or missing.
9) Connect the refuel nozzle to the fueling receptacle.
10) Repeat these steps for each fuel hose.
11) Put the manual handle for the FUELING SHUTOFF VALVE to the OPEN position (left wing and right wing, if
necessary).
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3.6 Prepare the Refuel Control Panel, P42

1) Fully open access door 521CB (Fig. 5.1).
2) Ensure the panel floodlights come on.
3) If the floodlights do not come on (no ground power), then do these steps:
a) Put the main battery (BATTERY) switch, P4, in the flight compartment to the ON position (Fig. 5.3).
b) Ensure the STANDBY POWER switch is in the OFF position.
c) Put the POWER switch on the P42 panel to the BATT position (Fig. 5.3).
4) Test the indicator lights:
a) Push the PRESS TO TEST indicators lights.
b) Ensure each light comes on when pushed.
5) Test the fueling quantity indicators:
a) Push and hold the TEST GAGES switch for a minimum of 1 second.
b) Ensure all the indicator displays show 888.8 for one second and then go off for 1 second.

NOTE
The test display will continue to cycle until you release the switch.

c) Release the TEST GAGES switch.

d) Ensure all fuel quantity displays go back to the usual indication.

3.7 Prepare the Fuel Sheet

1) Use the operator supplied fuel sheet to record the pre-uplift fuel quantity for each tank.
2) Calculate the fuel to be uplifted converted to volume (if necessary).
3) Record the uplift quantity on the fuel sheet (if necessary).

3.8 Begin the Refuel Operation

1) Decide which fuel tanks to refuel.
2) Put the VALVE POSITION CONTROL (MANUAL) switches to the OPEN position for all fuel tanks that are to be
refueled.
3) Activate the fuel shutoff control switch (deadman switch) to start the fuel flow.

Caution
DO NOT USE THE MANUAL HANDLE FOR THE FUELING SHUTOFF VALVES TO
REDUCE OR STOP THE REFUEL OPERATION. IF THE MANUAL HANDLE IS
CLOSED DURING THE REFUEL OPERATION, A PRESSURE SURGE AND
SUBSEQUENT DAMAGE COULD OCCUR.

4) Ensure the refuel pressure is between 35 and 55 psi.

Caution
DO NOT USE MORE THAN 55 PSI FUEL PRESSURE AT THE NOZZLE. DAMAGE
TO THE REFUEL SYSTEM CAN OCCUR.
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5) Ensure the refuel valve indication lights come on (valves open).

6) Ensure the left and right wing fuel tanks refuel at approximately the same rate.
7) Monitor the fuel quantity in each tank.

NOTE
The FQPU will automatically control the distribution of the fuel load.

8) Do these steps to test the FQPU refuel valve shutoff control:

NOTE
When you press the TEST SYS switch, the FQPU momentarily closes
the refuel valves to check for FQPU valve shutoff control

a) Push the TEST SYS switch for a minimum of two seconds and then release the switch.
b) The refuel valve lights will go out and then come on again.
c) The refuel operation will continue.
9) Monitor the fueling quantity indicators and refuel valve indication lights.

3.9 Stop the Refuel Operation

1) Put the individual refuel valve switches to the CLOSED position at the required fuel quantity.
2) If opened, put the ALL VALVES switch to the CLOSED position when all of the refuel valve position lights are
off.

NOTE
The FQPU will automatically close the tank refuel valve(s) when the
tank fuel quantity is at VTO.

3) Release the deadman switch to stop the fuel flow.

4) Ensure the onboard fuel load is in a valid pre-flight fuel distribution.
5) Transfer fuel to balance the fuel load if necessary (AMM 28-26-00/201).
6) Wait 1 minute to let the FQIS system stabilize.
7) Record the actual fuel quantities from the fueling quantity indicators.
8) Record the actual fuel quantity from the fuel vehicle flow meter.
9) Do the discrepancy check and ensure it is within limits.

NOTE
Per operator's requirement.

10) Complete the Fuel Sheet.

11) Complete the Delivery Receipt if necessary.
12) Give a copy of the forms to the airline representative or flight crew.

3.10 Put the Airplane Back to the Usual Condition

1) Put the manual handle for the FUELING SHUTOFF VALVE to the CLOSED position (left and right wing).
2) Ensure all the P42 panel valve switches are in the CLOSED position.
3) Put the POWER switch to the NORM position (if necessary).
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4) If the airplane battery power was used, set the main battery (BATTERY) switch, P4, in the flight compartment to
the OFF position (Fig. 5.3).
5) Disconnect the refuel nozzle from the airplane (Fig. 5.1).
6) Ensure the fueling receptacle adapter is not damaged.
7) Install the cap for the fueling receptacles.
8) Repeat the steps for each fuel hose.
9) Close and security latch these doors:
a) Fueling station access door, 521BB and 621BB
b) Fueling control panel access door, 521CB.
10) Disconnect the bonding/grounding cables (AMM 20-41-01/201).
11) Do the operator supplied procedures to remove the fuel servicing vehicle.
12) Do this task for extended leading edge flaps: Safety Locks Removal and Extended Leading Edge Activation
(AMM 27-81-00/201).

WAR NI NG
DO THE PROCEDURE IN AMM 27-81-00/201 TO REACTIVATE THE EXTENDED
LEADING EDGE FLAPS. THE FLAPS MOVE QUICKLY AND CAN CAUSE INJURY
TO PERSONS OR DAMAGE TO EQUIPMENT.

4 ALTERNATE REFUELING PROCEDURES

4.1 General
This procedure contains these tasks:
1) Refuel Operation - Inoperative Refuel Valve
2) Refuel Operation - Inoperative Fueling Quantity Indicator
3) Refuel Operation - Overfill Condition

4.2 Refuel Operation - Inoperative Refuel Valve

4.2.1 General

1) This task refuels a fuel tank when a refuel valve does not open electrically.
2) There is no automatic refuel valve shutoff or overfill protection when a refuel valve is opened manually. If you
put too much fuel into the tank, fuel will overfill the tank and go into the surge tank(s). If the fuel flow is not
stopped, the surge tank will overfill and an overboard fuel spill will occur.
3) You must monitor the fuel distribution to prevent an out of limits center of gravity (CG) or lateral imbalance
condition.

4.2.2 References

1) AMM 12-11-01/301, Fuel Servicing

2) AMM 20-41-01/201, Static Grounding
3) AMM 24-29-00/001, Standby 115-Volt AC Power Generation
4) AMM 27-81-00/201, Leading Edge Flap System
5) AMM 28-26-00/201, Defueling
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4.2.3 Prepare the Airplane

1) Read and comply with the precautions in this task: Precautions and Limits for Fuel Servicing
(AMM 12-11-01/301)

WAR NI NG
COMPLY WITH ALL THE FUEL SERVICING AND PRESSURE REFUELING
PRECAUTIONS. FAILURE TO COMPLY WITH THE PRECAUTIONS CAN
CAUSE SERIOUS INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

2) Ensure the inoperative refuel valve is in the closed position

WAR NI NG
BEFORE YOU REFUEL THE AIRPLANE, ENSURE THE INOPERATIVE REFUEL
VALVE IS IN THE CLOSED POSITION. A FUEL SPILL CAN OCCUR, AND A
FUEL SPILL CAN CAUSE A FIRE OR AN EXPLOSION.

3) Ensure the fueling manifold does not have pressure.

4.2.4 Refuel the Fuel Tanks

Do a manual pressure refuel operation (AMM 12-11-03/301).

NOTE
Refuel all the fuel tanks except the tank with an inoperative refuel
valve.

4.2.5 Refuel the Fuel Tank - Tank With An Inoperative Refuel Valve

1) Remove or open the applicable access door or panel to get access to the refuel valve control unit.
a) If installed, for the No. 2 or No. 3 reserve tank refuel valve control unit, open the outboard aileron
access panel, 591FB or 691FB.
b) For the No. 1 reserve tank refuel valve control unit, open the outboard aileron access panel, 591AB.
c) If installed, for body tank refuel valve control unit, remove the applicable body tank fuel cell dry bay
access door (AMM 28-11-13/401).
d) For No. 1 main tank refuel valve control unit, open the flap drive access panel, 581EB.
e) For No. 2 main tank refuel valve control unit, open the trailing edge lower access panel, 572GB and/or
571AB.
f) For No. 3 main tank refuel control unit, open the trailing edge lower access panel, 672GB and/or
671AB.
g) For No. 4 main tank refuel valve control unit, open the flap drive access panel, 681EB.
h) For No. 4 reserve tank refuel valve control unit, open the outboard aileron access panel, 691AB.
2) Remove the lockwire from the knurled knob of the valve override screw.

NOTE
Do not remove the retainer plate lockwire, the screw, or the retainer
plate.
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3) Turn the valve override screw (knurled knob) 10-13 turns in the counterclockwise direction (full open).

NOTE
Use pliers, if necessary, to turn the valve override screw.

4) Ensure the refuel control panel, P42, is set for the refuel operation:
a) All the VALVE POSITION CONTROL (refuel valve) switches are in the CLOSED position.
b) ALL VALVES switch is in the CLOSED position.
5) Activate the fuel equipment switch (deadman switch) to start the fuel flow.
6) Ensure the refuel pressure is between 35 and 55 psi.
7) Monitor the fuel quantity.

WAR NI NG
THERE IS NO AUTOMATIC REFUEL SHUTOFF OR OVERFILL PROTECTION
WHEN THE REFUEL VALVES ARE MANUALLY OPENED. WITHOUT AUTO
SHUTOFF OR OVERFILL PROTECTION, A FUEL SPILL CAN OCCUR, AND A
FUEL SPILL CAN CAUSE A FIRE OR EXPLOSION.

NOTE
You can monitor the fuel quantity with the fueling quantity indicators
or the fuel measuring sticks.

8) Release the deadman switch to stop the fuel flow when you have the necessary quantity of fuel.
9) Do the steps to complete the manual refuel operation (AMM 12-11-03/301).

4.2.6 Put the Airplane Back to the Usual Condition

1) Ensure the fueling manifold does not have pressure.

2) Ensure the applicable refuel valve indicator light is on.
3) Turn the valve override screw (knurled knob) 10 to 13 full turns (until you cannot turn it) in the clockwise
direction.

NOTE
You can use a set of pliers to turn the valve override screw.

4) Ensure the applicable refuel valve indicator light goes off.

5) Install lockwire on the knurled knob of the valve override screw.
6) Install or close the applicable access door or panel that you removed or opened to get access to the refuel
valve control unit.
a) If installed for the No. 2 or 3 reserve tank refuel valve control unit, close the outboard aileron access
panel, 591FB or 691FB.
b) For No. 1 reserve tank refuel valve control unit, close the outboard aileron access panel, 591AB.
c) For No. 1 main tank refuel valve control unit, close the flap drive access panel, 581EB.
d) For No. 2 main tank refuel valve control unit, close the trailing edge lower access panel, 572GB and/or
571AB.
e) For No. 3 main tank refuel valve control unit, close the trailing edge lower access panel, 672GB and/or
671AB.
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f) For No. 4 main tank refuel valve control unit, close the flap drive access panel, 681EB.
g) For No. 4 reserve tank refuel valve control unit, close the outboard aileron access panel, 691AB.
7) Make a logbook entry of the inoperative refuel valve.
8) Schedule a maintenance task to troubleshoot and repair the refuel system (AMM 28-21-00/101).

4.3 Refuel Operation - Inoperative Fueling Quantity Indicator

4.3.1 General

This task refuels a fuel tank with an inoperative fueling quantity indicator.

4.3.2 Prepare the Airplane

1) Read and comply with the precautions in this task: Precautions and Limits for Fuel Servicing
(AMM 12-11-01/301).

WAR NI NG
COMPLY WITH ALL THE FUEL SERVICING AND PRESSURE REFUEL
PRECAUTIONS IN AMM 12-11-01/301. FAILURE TO COMPLY WITH THE
PRECAUTIONS CAN CAUSE SERIOUS INJURY TO PERSONS AND DAMAGE
TO EQUIPMENT.

2) Do this task: Prepare the Airplane for a Refuel Operation (AMM 12-11-01/301).
3) Do one of these procedures to refuel the airplane with an inoperative fueling quantity indicator:
a) Fuel Transfer Method
b) Fuel Truck Flow Meter Method
c) Fuel Measuring Sticks Method

4.3.3 Fuel Transfer Method

1) Transfer fuel from the tank with an inoperative fueling quantity indicator:
a) Ensure the refuel valve(s) for the tank with the inoperative fueling quantity indicator are closed.
b) Ensure the receiving tank(s) have enough fuel capacity to accept all of the fuel from the tank with the
inoperative fueling quantity indicator.
c) Transfer all of the fuel from the tank with an inoperative fueling quantity indicator
(AMM 28-26-00/201).
i.Continue the fuel transfer until the fuel pump low pressure lights come on.
2) Calculate the supply tank fuel to remain (Table 5.1).
a) Make a decision about which fuel tank will supply the transfer fuel.
b) Record the INITIAL supply tank fuel quantity, BLOCK A.
c) Use the fuel sheet to find the fuel requirement for the tank with an inoperative fueling quantity indicator.

NOTE
This is the fuel quantity that will be transferred from the supply tank.

d) (Record the TRANSFER fuel quantity, BLOCK B.

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e) Calculate the fuel quantity that will remain in the supply tank after the fuel transfer operation.

NOTE
Subtract the transfer fuel quantity (B) from the initial supply tank fuel
quantity (A) to get the final supply tank fuel quantity (C). Block C is the
fuel quantity that will remain in the supply tank after the fuel transfer
is complete. When the supply tank fuel quantity decreases to this val-
ue, stop the fuel transfer operation.

f) Record the FINAL fuel quantity for the supply tank, BLOCK C.

Table 5.1. Supply Tank Transfer

SUPPLY TANK TRANSFER (FUEL TO REMAIN) LBS

Initial Supply Tank Fuel Quantity INITIAL A
- Transfer Fuel Quantity *[1] - TRANSFER B
= Final Supply Tank Fuel Quantity *[2] = FINAL C

*[1] Fuel quantity required for the tank with an inoperative indicator (per the fuel sheet).
*[2] Fuel quantity to remain in the supply tank after fuel transfer.
3) Prepare the tank with an inoperative fueling quantity indicator:
a) Manually open the tank refuel valve (AMM 28-21-00/001).
4) Transfer a known quantity of fuel into the tank with an inoperative fueling quantity indicator:
a) Transfer fuel from the supply tank into the tank with an inoperative indicator (AMM 28-26-00/201).
b) Monitor the fuel quantity decrease from the supply tank.

WAR NI NG
THERE IS NO AUTOMATIC SHUTOFF OR OVERFILL PROTECTION DURING A
REFUEL OPERATION WHEN THE REFUEL VALVES ARE MANUALLY OPENED.
WITHOUT AUTO SHUTOFF OR OVERFILL PROTECTION A FUEL SPILL CAN
OCCUR. A FUEL SPILL CAN CAUSE A FIRE OR AN EXPLOSION.

c) Stop the transfer at the final fuel quantity, BLOCK C.

d) Put the refuel valve in the CLOSED position (if opened).
e) Use the measuring sticks to verify the actual fuel quantity in the tank with the inoperative indicator.
f) Record the fuel quantity on the fuel sheet.
5) Manually close the applicable refuel valve (AMM 28-21-00/001).

4.3.4 Fuel Truck Flow Meter Method

1) Transfer fuel from the tank with an inoperative fueling quantity indicator.
a) Ensure the refuel valve(s) in the tank with an inoperative indicator are closed.
b) Ensure the receiving tank(s) have enough fuel capacity to accept all of the fuel from the tank with an
inoperative indicator.
c) Transfer all of the fuel from the tank with an inoperative indicator (AMM 28-26-00/201).
d) Continue the fuel transfer until the fuel pump low pressure lights come on.
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2) Calculate the upload fuel quantity for the tank with an inoperative indicator (Table 303).
a) Record the fuel sheet upload fuel quantity in LBS, BLOCK A.
b) Record the current station DENSITY, BLOCK B.
c) Convert the fuel sheet upload fuel quantity in lbs into gallons by dividing lbs by the current station
density.
d) Record the target upload fuel quantity in GALLONS, BLOCK C.

Table 5.2. Upload Fuel Quantity

UPLOAD FUEL QUANITY

Upload Fuel Quantity lbs *[1] LBS A
Current Station Density / DENSITY B
= Target Quantity, gallons = GALLONS C

*[1] Fuel quantity required for the tank with an inoperative fueling quantity indicator (per the fuel
sheet).
3) Prepare the tank with an inoperative fueling quantity indicator:
a) Manually open the tank refuel valve (AMM 28-21-00/001).
b) Upload a known quantity of fuel into the tank with an inoperative fueling quantity indicator:
c) Do the manual refuel operation (AMM 12-11-03/301).
d) Monitor the fuel flowmeter.

WAR NI NG
THERE IS NO AUTOMATIC SHUTOFF OR OVERFILL PROTECTION DURING A
REFUEL OPERATION WHEN THE REFUEL VALVES ARE MANUALLY OPENED.
WITHOUT AUTO SHUTOFF OR OVERFILL PROTECTION A FUEL SPILL CAN
OCCUR. A FUEL SPILL CAN CAUSE A FIRE OR AN EXPLOSION.

e) Stop the upload at the BLOCK C fuel quantity.

f) Put the refuel valve switch in the CLOSED position (if opened).
g) Use the measuring sticks to verify the actual fuel quantity in the tank with the inoperative indicator.
h) Record the upload fuel quantity on the fuel sheet.
4) Manually close the refuel valve (AMM 28-21-00/001).
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4.3.5 Fuel Measuring Sticks Method

1) Calculate the upload fuel quantity for the tank with the inoperative fueling quantity indicator:
Figure 5.4 Fuel Measuring Stick

TAPER PIN

UPPER FLOAT STOP

STICK BEARING

RING MAGNET
FLOAT

CALIBRATED STICK

STICK HOUSING

PACKINGS

BASE

MEASURING STICK
READING PLANE

SOCKET

MEASURING
STICK HEAD
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a) Use the fuel measuring sticks to get stick readings for the tank with the inoperative fueling quantity
indicator.

NOTE
If the fuel quantity is below the minimum stick reading, do the fuel
transfer or fuel truck flow meter method to refuel the tank. You can
also transfer enough fuel into the tank with the inoperative indicator to
get a stick reading (AMM 28-26-00/201).

b) Use the dripstick conversion chart in the fuel measuring stick manual to convert the stick units to
pounds to calculate how much fuel remains in the tank.
c) Record the quantity of fuel in the tank, pounds.
d) Use the fuel sheet to find the total fuel required in the tank.
e) Subtract the quantity of fuel currently in the tank from the total fuel requirement.

NOTE
This is the fuel quantity that needs to be uploaded into the tank

f) Record the upload fuel quantity, pounds.

g) Convert the necessary upload fuel quantity in pounds (kilograms) into gallons by dividing pounds by
the current station density.
h) Record the target upload fuel quantity in gallons.
i) Prepare the tank with an inoperative fueling quantity indicator:
j) Manually open the tank refuel valve (AMM 28-21-00/001).
2) Upload a known quantity of fuel into the tank with the inoperative fueling quantity indicator.
a) Upload fuel from the fuel service equipment into the tank with the inoperative fueling quantity indicator
(AMM 12-11-03/301).
b) Monitor the fuel flowmeter.

WAR NI NG
THERE IS NO AUTOMATIC SHUTOFF OR OVERFILL PROTECTION DURING A
REFUEL OPERATION WHEN THE REFUEL VALVES ARE MANUALLY OPENED.
WITHOUT AUTOMATIC SHUTOFF OR OVERFILL PROTECTION, A FUEL SPILL
CAN OCCUR. A FUEL SPILL CAN CAUSE A FIRE OR EXPLOSION.

c) Stop the upload at the target fuel quantity.

d) Put the refuel valve switch to the CLOSED position (if opened).
e) Use the fuel measuring sticks to verify the actual fuel quantity in the tank with the inoperative fueling
quantity indicator.
f) Record the upload fuel quantity on the fuel sheet.
3) Manually close the inoperative refuel valve (AMM 28-21-00/001).
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4.3.6 Put the Airplane Back to the Usual Condition

1) Do the manual refuel operation (AMM 12-11-03/301).

NOTE
Refuel the remaining fuel tanks per fuel sheet requirements. Ensure
the refuel valve(s) for the tank with an inoperable fueling quantity in-
dicator stays closed.

2) Make a logbook entry for the inoperative fueling quantity indicator.

3) Schedule a maintenance task to trouble shoot and repair the fueling system (AMM 28-21-00/101).

4.4 Airplanes With Goodrich Digital FQIS

Refuel Operation - Early Fuel Quantity Shutoff

4.4.1 General

1) This task refuels a fuel tank when the desired fuel quantity is less than expected (early shutoff).
2) The fuel quantity indication system is a fault tolerant system. When the system detects an error that exceeds
the maximum allowable fuel quantity measurement error, the system will blank the fuel quantity for that tank.
Other less severe FQIS fault conditions can cause the refuel valves to close before the fuel tank reaches the
volumetric top-off (VTO) fuel quantity. This early shutoff is necessary to prevent an overfill condition in the tank
due to possible fuel quantity gaging errors. There are two early shutoff set values:
a) 95% VTO Shutoff
b) 87% VTO Shutoff
3) The early shutoff set value depends on which FQIS components are inoperative.

4.4.2 Airplane Precautions

1) Read and comply with the precautions in this task: Precautions and Limits for Fuel Servicing
(AMM 12-11-01/301).

WAR NI NG
COMPLY WITH ALL THE FUEL SERVICING AND PRESSURE REFUELING
PRECAUTIONS. FAILURE TO COMPLY WITH THE PRECAUTIONS CAN CAUSE
SERIOUS INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

4.4.3 Refuel Operation When an Early Fuel Shutoff Occurs

1) Complete the automatic or manual refuel operation.

2) Wait for one minute to let the FQIS system stabilize.
3) Find out which tank shutoff prior to the VTO.
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4) Do not put the VTO switch to the override position to add more fuel into the fuel tank.

WAR NI NG
IF A REFUEL VALVE CLOSES EARLY, DO NOT CONTINUE TO REFUEL THE
TANK WITH THE VTO SWITCH IN THE OVERRIDE POSITION. AN OVERFILL
CONDITION AND POSSIBLE OVERBOARD FUEL SPILL CAN OCCUR. A FUEL
SPILL CAN CAUSE A FIRE OR EXPLOSION.

5) Do not use the fuel quantity indication value for that tank.
6) Use the fuel quantity measuring sticks to continue to fill the tank (AMM 28-44-00/001).
a) Use the fuel measuring sticks to obtain stick readings for the tank with the blank gage.
b) Use the dripstick conversion chart in the fuel measuring stick manual to convert the stick units to lbs to
calculate how much fuel remains in the tank.
c) Record the quantity of fuel in the tank lbs.
d) Use the fuel sheet to find the total fuel required in the tank.
e) Subtract the quantity of fuel currently in the tank from the total fuel requirement.

NOTE
This is the fuel quantity that needs to be uploaded into the tank.

f) Record the upload fuel quantity in lbs.

g) Convert the necessary upload fuel quantity in lbs into gallons by dividing lbs by the current station
density.
h) Record the target upload fuel quantity in gallons.
i) Manually open the tank refuel valve.
j) Upload fuel from the fuel service equipment into the tank with a blank gage.
k) Monitor the fuel flow meter.
l) Stop the upload at the target fuel quantity.
m) Use the measuring sticks to verify the actual fuel quantity in the tank with the blank gage.
n) Record the upload fuel quantity on the fuel sheet.
7) Manually close the refuel valve.
8) Refuel the remaining fuel tanks per the fuel sheet requirements (AMM 28-26-00/201).
9) Make a logbook entry of the early shutoff condition.
Airplanes Post-SB 28-2018 or Post-SB 28-2026 or with PRR 74517 or PRR 74517-1
Refuel Operation - Overfill Condition

4.4.4 General

1) This task lets the refuel operation continue when all the refuel valves close because fuel goes into the surge
tank and the float switches in the surge tank close.
2) Ensure the refuel valve(s) for the tank with an overfill stay closed when you start the refuel operation again.
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4.4.5 Stop the Refuel Operation After an Overfill Condition

1) Release the deadman switch to stop the fuel flow.

2) Put all the refuel valve switches to the CLOSED or CLOSE position.
3) Find the tank with the overfill condition.

NOTE
Use the fueling quantity indicators, fuel quantity indicators or fuel
measuring sticks.

4) Wait for fuel to drain from the surge tank.

a) If you can not wait, do one of these steps:
1) Use the sump drain valve in the surge tank to drain the fuel.
2) Open this circuit breaker on the right main power center, P15, and attach a DO-NOT-CLOSE tag:

WAR NI NG
THERE IS NO OVERFILL PROTECTION IF YOU OPEN THE FUEL OVERFILL
CONTROL CIRCUIT BREAKER. WITHOUT OVERFILL PROTECTION, A FUEL
SPILL CAN OCCUR.

i.FUEL OVERFILL CONTROL

4.4.6 Begin the Refuel Operation Again

1) Push the OVERFILL RESET OR RESET switch.

2) Ensure the refuel valve(s) for the overfilled tank stay closed.
3) For all the fuel tanks except the tank with the overfill condition, put the applicable refuel valve switches to the
OPEN position as applicable.
4) Do the steps to continue the manual pressure refuel operation (AMM 12-11-03/301).
5) Monitor the fuel flow meter.
6) Stop the upload at the fuel sheet requirements.
1) Do the steps to complete the manual refuel operation (AMM 12-11-03/301).

4.4.7 Put the Airplane Back to Its Usual Condition

1) If opened, remove the DO-NOT-CLOSE tag and close this circuit breaker on the right main power center, P15.
2) ENSURE YOU CLOSE THIS CIRCUIT BREAKER. FAILURE TO CLOSE THE FUEL OVERFILL CONTROL
CIRCUIT BREAKER CAN CAUSE A FUEL SPILL.
a) FUEL OVERFILL CONTROL
3) Make a logbook entry of the overfill condition.
4) Schedule a maintenance task to troubleshoot and repair the pressure fueling system
(AMM 28-21-00/101).
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5 OVERWING FUELING

5.1 General
1) A. This procedure contains a task for overwing refueling.
a) Overwing refueling lets the operator add fuel to the main fuel tanks. Fuel is added through the fill ports
found on the top of the wings. Fuel is transferred to the reserve (auxiliary) tanks, center wing tank
(CWT) and body tanks (if installed).
b) The overwing refuel of the main tanks can be done if the pressure refuel equipment, or electrical power
is not available. With electrical power available, the fuel quantity can be monitored from the flight
compartment or the P42 refuel control panel. With no electrical power available, the fuel quantity can
be monitored with the fuel measuring sticks.
c) You must stop the overwing refuel operation before the tank overfills.
d) You must monitor the fuel distribution to prevent an out of limits center of gravity (CG) or lateral
imbalance condition.

5.2 Overwing Refueling (Fig. 5.5)

5.2.1 References

1) AMM 12-11-01/301, Fuel

2) AMM 20-11-32/201, Flight Control Surfaces Safety Harness Receptacle
3) AMM 20-41-01/201, Static Grounding
4) AMM 27-81-00/201, Leading Edge Flap System
5) AMM 28-26-00/201, Defueling

5.2.2 Prepare the Airplane for an Overwing Refueling Operation

1) Read and comply with the precautions in this task: Precautions and Limits for Fuel Servicing
(AMM 12-11-01/301).

WAR NI NG
COMPLY WITH ALL THE FUEL SERVICING PRECAUTIONS IN AMM 12-11-01/
301. FAILURE TO COMPLY WITH THE PRECAUTIONS CAN CAUSE SERIOUS
INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

2) Supply electrical power (AMM 24-22-00/201).

3) Do not operate the APU during an overwing refuel operation.
4) Ensure the airplane is in a 0.5 degree nose down and a 0.0 degree roll attitude (|2.0 degree pitch and roll).
5) Sump the water from the fuel tanks before you refuel the airplane (AMM 12-11-10/301).
6) Ensure these components are in the closed position:
a) Wing pressure relief valves (4 locations)
b) Landing gear doors
c) Overwing entry doors (passenger and combi airplanes only).
7) Extend the leading edge flaps and install the safety locks.
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WAR NI NG
INSTALL THE LOCKS ON ALL EXTENDED LEADING EDGE FLAPS. THIS WILL
PREVENT INJURY FROM AN ACCIDENTAL OPERATION OF THE FLAPS.

Figure 5.5 Overwing Refueling

NO. 2 MAIN TANK

CENTER
WING
TANK OVERWING
FUELING FILLER PORT
OVERWING GROUNDING
STATION SEE A
FILLER PORT JACK
CONTROL
SEE A PANEL

1 AIRPLANES PRE-SB 28-2044

2 AIRPLANES POST-SB 28-2044 OR
WITH PRR 78025 OR PRR 76304
FILLER CAP

SEAL

LANYARD

FILLER
PORT

UPPER WING FILLER CAP

SKIN ADAPTER 1
SEE B

FILLER CAP
NUT ADAPTER
2
O-RING SEAL RING

OVERWING FILLER PORT FILLER CAP ADAPTER

A B
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5.3 Connect the Fueling Equipment

1) Use the operator supplied procedures to position the fuel vehicle

WAR NI NG
DO NOT POSITION FUEL SERVICING EQUIPMENT OR AIRPLANE SERVICING
EQUIPMENT UNDER THE WING DURING AN OVERWING REFUEL
OPERATION. AN OVERWING FUEL SPILL CAN CAUSE FUEL TO FLOW FROM
THE WING SURFACE ONTO EQUIPMENT UNDER THE WING. A FUEL SPILL
CAN CAUSE A FIRE OR EXPLOSION.

2) Connect a grounding cable from an approved earth ground to an approved electrical ground point on the
airplane (static ground) (AMM 20-41-01/201).

WAR NI NG
YOU MUST GROUND THE AIRPLANE TO AN APPROVED EARTH GROUND
AND BOND THE REFUEL SOURCE BEFORE THE OVERWING REFUEL
OPERATION. IF YOU DO NOT FOLLOW THIS PROCEDURE, A STATIC SPARK
CAN CAUSE FUEL VAPOR TO IGNITE.

3)
4) Connect one grounding cable from the fueling source to an approved earth ground (AMM 20-41-01/201).
5) Connect a bonding cable from the fueling source to an approved airplane electrical ground point (
AMM 20-41-01/201).
6) Put on a safety harness and connect the harness to the supplied harness receptacle (AMM 20-11-32/201).

WAR NI NG
YOU MUST WEAR A SAFETY HARNESS WHEN YOU DO AN OVERWING
REFUEL OPERATION. A SERIOUS INJURY CAN OCCUR IF YOU FALL FROM
THE WING SURFACE.

7) Put pads on the wing surface to prevent damage from the fuel nozzle and fuel hose.
8) Connect the fuel hose to the overwing fill port:

Caution
DO NOT DRAG THE FUEL NOZZLE AND HOSE ACROSS THE WING SURFACE.
DAMAGE TO THE WING SURFACE CAN OCCUR.

a) Open the overwing fill port.

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WAR NI NG
ENSURE THE FUEL LEVEL FOR THE APPLICABLE TANK IS BELOW THE LEVEL
OF THE FILL PORT BEFORE YOU OPEN THE FILL CAP OR A FUEL SPILL CAN
OCCUR. A FUEL SPILL CAN CAUSE A FIRE OR AN EXPLOSION.

Caution
KEEP ALL LOOSE OBJECTS AWAY FROM THE FILL PORT. REMOVE ANY
OBJECTS FROM YOUR SHIRT POCKET (PENS, CIGARETTES, LIGHTERS, ETC.)
BEFORE YOU OPEN THE FILL CAP. IF AN OBJECT DOES FALL INTO THE FUEL
TANK, CONTACT AN AIRLINE REPRESENTATIVE. FIND AND REMOVE THE
OBJECT IMMEDIATELY. UNWANTED OBJECTS IN THE FUEL TANK CAN CAUSE
DAMAGE TO IN-TANK EQUIPMENT AND ELECTRICAL WIRING.

b) Connect the overwing nozzle to the fill port.

c) Use a nozzle extension or spout to ensure the fuel does not splash into the fuel tank.
d) Ensure the nozzle extension is below the level of the fuel.
e) Ensure the overwing nozzle remains in contact with the fill port during the refuel operation.
f) Repeat these steps for each fuel hose.

5.4 Overwing Refuel Operation

1) Record these values on the fuel sheet:
a) Pre-uplift fuel quantity for each tank.

NOTE
If there is no electrical power or the FQIS system is inoperative, use
the fuel measuring sticks to calculate the pre-uplift fuel quantity in
each tank.

b) Final fuel quantity necessary in each tank.

c) Fuel to be uplifted converted to volume.
2) Use the fueling quantity indicators (P42 panel), fuel quantity indicators (flight compartment), or measuring
sticks to monitor the fuel quantity.
3) Activate the fuel equipment switch (deadman switch) to start the fuel flow.
4) Ensure the refuel rate for each tank is a maximum of 155 U.S. gallons per minute.

WAR NI NG
DO NOT REFUEL MORE THAN THE MAXIMUM PERMITTED RATE OF 155 U.S.
GALLONS PER MINUTE FOR EACH TANK. THIS WILL REDUCE STATIC CHARGE
IN THE FUEL TANK.

5) Monitor the fuel quantity.

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WAR NI NG
DO NOT OVERFILL THE TANK. THERE IS NO AUTOMATIC SHUTOFF
CONTROL FOR OVERWING REFUELING.

5.5 Stop the Overwing Refuel Operation

1) When you have the necessary fuel quantity, stop the refuel operation.
2) Release the deadman switch to stop the fuel flow.
3) Disconnect the refuel nozzle from the airplane.
4) Install the overwing fill cap.
5) Remove all equipment used for the overwing refuel operation (pads on the wing surface, safety harness,
etc.).
6) Repeat the steps for each fuel hose.
7) Transfer fuel to the reserve (auxiliary), center wing and body (if installed) tanks as necessary
(AMM 28-26-00/201).
8) Ensure the onboard fuel load is in a valid pre-flight fuel distribution.
9) Record the actual fuel quantities from the fueling quantity indicators.
10) If the fueling quantity indicators are not available, record the actual fuel quantities from the fuel measuring
sticks.
11) Do the discrepancy check and ensure it is within limits.
12) Complete the Fuel Sheet.
13) Complete the Delivery Receipt.
14) Give a copy of the forms to the airline representative or flight crew.
15) Ensure all the refueling control panel switches are in the CLOSED position (if necessary).
16) Put the REFUEL POWER switch to the NORMAL position (if necessary).

5.6 Put the Airplane Back to the Usual Condition

1) Close and latch these door (if opened):
a) Fueling station access door, 521BB and 621BB
b) Fueling control panel access door, 521CB.
2) Do these steps in this sequence to remove the bonding/grounding cables (AMM 20-41-01/201):
a) Disconnect the bonding cable from the airplane to the fuel source.
b) Disconnect the grounding cable from the earth ground to the fuel source.
c) Disconnect the grounding cable from the airplane to the earth ground.
3) Do the operator supplied procedures to remove the fuel vehicle.
4) (Remove the safety locks and activate the extended leading edge flaps (AMM 27-81-00/201).

WAR NI NG
DO THE PROCEDURE IN AMM 27-81-00/201 TO REACTIVATE THE EXTENDED
LEADING EDGE FLAPS. THE FLAPS MOVE QUICKLY AND CAN CAUSE
INJURY TO PERSONS OR DAMAGE TO EQUIPMENT
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CHAPTER 6 TOC Chapter 6 TOC

CHAPTER 6 - FUEL TANK SUMP DRAINAGE ................................................................................................ 6.1

1. GENERAL ........................................................................................................................................................................ 6.1
1.1 Fuel System Drainage ..................................................................................................................................... 6.1
1.2 Water in the Fuel Tank ..................................................................................................................................... 6.1
1.3 Fuel Contamination .......................................................................................................................................... 6.2
1.4 Cold Weather Operations ................................................................................................................................ 6.2
1.5 Sump Drain Valves Installed in the Surge Tank .............................................................................................. 6.2
2. DRAIN THE FUEL TANK SUMPS ................................................................................................................................... 6.2
2.1 References ....................................................................................................................................................... 6.2
2.2 Equipment ........................................................................................................................................................ 6.2
2.3 Prepare for the Procedure ............................................................................................................................... 6.4
2.4 Sump the Tanks ............................................................................................................................................... 6.4

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Chapter 6 CHAPTER 6 - FUEL TANK SUMP DRAINAGE

1 GENERAL
This procedure contains a task to drain the fuel tank sumps.

1.1 Fuel System Drainage

1) There is one sump drain valve installed in each of the fuel tanks including the surge tanks. The sump inlet is at
the lowest area of the fuel tank where water and sediment will collect.
2) You can use the sump drain to do these actions:
a) Remove water from the fuel tank
b) Do a check for fuel contamination
c) Do a check for ice accumulation
d) Collect a fuel sample for microbial growth detection (AMM 28-10-00/201)
e) Do a check of the water scavenge system (if installed)
f) Drain fuel to defuel the tank (AMM 28-26-00/201)
g) Drain fuel from the surge tanks to reset the overfill protection system
3) All fuel tank sumps are drained at the "A" Check.

1.2 Water in the Fuel Tank

1) Water in the fuel tank comes from condensation or from fuel that is uploaded during a refuel operation.
Removal of water will help minimize microbial growth that exists at the fuel/water interface. Microbial growth
can cause fuel system degradation including clogged engine filters, fuel quantity indication problems, and
eventually structural corrosion.
2) During refueling or airplane operations, water mixes in the fuel. Schedule the task to drain the fuel tank after
sufficient time has elapsed to let the water settle to the bottom of the tanks. Water sinks in fuel at the rate of
approximately one foot (30 cm) per hour.
3) Drain the tanks sufficiently to ensure you remove all of the water.
4) AIRPLANES WITH A WATER SCAVENGE EJECTOR PUMP (PRR 74442, PRR 74617-1, PRR 74617-2 OR
POST-SB 28-2025);
A large quantity of water drained from one fuel tank before refueling can show a blocked water scavenge
system, refer to AMM 28-22-08/401.
5) Water in a fuel sample usually shows as layer below the fuel, or as small bubbles in the fuel. Ice crystals
usually appear as cloudiness or haziness and makes the fuel less transparent.
6) To help you see the water in the fuel you can add one or two drops of food coloring (water soluble) into the
container of fuel. Any water in the fuel will be shown by a color. You can put the food coloring into the container
before you drain the fuel sump.
7) If a total of 8 ounces or more of water is drained from any sump, notify Maintenance Control. Maintenance
Control must wire next station to check sumps before refueling and advise findings and also advise previous
station of departure to check fueling equipment for water.

Caution
IF WATER DRAINED FROM SUMP AREA APPEARS SCUMLIKE OR RUSTY,
ADVISE MAINTENANCE CONTROL TO NOTIFY ENGINEERING OF CONDITION
WHICH REQUIRES FURTHER EVALUATION. THE SUMP DRAINAGE SAMPLE
SHOULD BE PLACED IN A CLEAN CONTAINER AND LABELED WITH AIRCRAFT,
DATE, TANK NUMBER, AND FORWARDED TO MAINTENANCE CONTROL FOR
ANALYSIS.
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1.3 Fuel Contamination

1) You can visually inspect the fuel collected from the sump drain for contamination.
2) Fuel with no water, ice, or contamination, is clear and bright and very transparent. The words "clear and
bright" mean that you cannot see undissolved water, sediment, or suspended material when you examine
the fuel in a clear glass or plastic container. If the fuel is free of these types of contamination, it is clear and
bright.
3) Jet-A fuel can have a range of colors from yellow (straw) color to no color. The words "clear and bright" are
not a reference to the color of the fuel. Yellow fuel or fuel that has no color can be "clear and bright" as
specified in the previous step.
4) If the water in the fuel has a foul odor or a brown color, then it is possible there is microbial contamination.
Refer to the check for microbial contamination (AMM 28-10-00/201).
5) If the fuel has a pink or a red color, do the task for fuel tanks contaminated with red dye (AMM 28-11-00/701).
6) If contamination is confirmed, notify Maintenance Control immediately.

1.4 Cold Weather Operations

1) In cold weather the water can freeze on the inside and outside of the fuel tanks. The frozen water can
prevent the sump drain valve from opening. If the ambient temperature is less than 0 degrees Celsius (32
degrees Fahrenheit), then you may have to supply heat before you can drain the sumps.
2) Cold weather can also cause the drain valve to stay open or damage the O-ring when you push the poppet
valve open. Cold weather can also prevent the correct re-seating of the primary or secondary poppet valve
after you drain the sump.
3) You can also use an approved anti-ice additive if the fuel specification permits it. For example, you can add
Phillips PFA 56MB in a maximum concentration of 0.1% by volume.
4) For cold weather maintenance, refer to AMM 12-33-01/301.

1.5 Sump Drain Valves Installed in the Surge Tank

1) The sump drain valves in the surge tanks are installed to do a check for fuel in the surge tank before you
remove the access door for entry.
2) Fuel in the surge tank will drain into the main fuel tanks through the drain check valve in each surge tank.

2 DRAIN THE FUEL TANK SUMPS

2.1 References
1) AMM 12-09-03/201, Body Section 44 Access Doors and Panels
2) AMM 12-33-01/301, Cold Weather Maintenance
3) AMM 28-10-00/201, Microbial Growth
4) AMM 28-11-00/701, Fuel Tanks

2.2 Equipment
1) MIT65B00772 - Receptacle Assembly, Fuel Sump Drain, or Beaker Assembly A12001 (Recommended), or
equivalent.
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Figure 6.1 Fuel Sump Drainage

NO. 1 RESERVE SURGE TANK

CENTER WING NO. 1 MAIN TANK TANK SUMP DRAIN NO. 2 RESERVE SUMP DRAIN
TANK SUMP SUMP DRAIN TANK SUMP DRAIN
DRAINS
1

NO. 2 MAIN TANK

SUMP DRAIN

BODY TANK SUMP DRAIN LOCATIONS

SUMP DRAIN
2
FUEL SUMP
DRAIN VALVE
(EXAMPLE)

WING SKIN
POPPET SEAT PRIMARY
POPPET

FUEL SAMPLING
RECEPTACLE
ASSEMBLY

FUEL

WATER

1 AIRPLANES WITH NO. 2 AND NO. 3

RESERVE TANKS
2 AIRPLANES WITH BODY FUEL TANK
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2.3 Prepare for the Procedure

1) If the ambient temperature is less than 0°C (32°F), do this task: Cold Weather Maintenance
(AMM 12-33-01/301).
2) Let the water go to the bottom of the tank before you open the sump drain valve.
3) If it is necessary to get a fuel sample from the center wing tank sump, open the access doors 191G and
192G (AMM 12-09-03/201).

2.4 Sump the Tanks

NOTE
The optimum airplane attitude to drain the fuel tank sumps is 0.5 de-
gree nose down pitch and zero degree roll.

1) Put the top end of the receptacle assembly against the sump drain poppet.
2) Put the container below the sump drain valve.
3) Push up until the fluid flows into the container.

NOTE
If you cannot open the sump drain valve or fluid does not drain from
the valve, water around the valve or in the valve can be frozen. Do the
applicable cold weather maintenance (AMM 12-33-01/301).

4) Drain each sump until the container is full.

5) Remove the sample container from the sump and let the valve close.
6) Look at the fluid in the container.
7) If the fuel in the container has visible water (free water), do these steps:
a) Empty the fluid from the container.
b) Use the correct procedures to dispose of the fuel.
c) Continue to drain fuel from the sump drain until all of the free water is removed.
8) If the water in the fuel sample container has a foul odor or a brown color, do this task: Detection Test for
Microbial Contamination (AMM 28-10-00/201).
9) If you see red dye in the fuel, do this task: Fuel Tanks Contaminated with Red Dye (AMM 28-11-00/701).
10) Ensure the final sample of fuel from the sump drain is clear and bright.
11) Use the correct procedure to dispose of the fuel.
12) If open, close the center wing tank access access doors 191G and 192G (AMM 12-09-03/201).
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CHAPTER 7 TOC Chapter 7 TOC

CHAPTER 7 - FUELING RECORD .................................................................................................................... 7.1

1. FUELING FORM COMPLETION INSTRUCTIONS ......................................................................................................... 7.1
1.1 Key to Form Completion .................................................................................................................................. 7.1
1.2 Form distribution .............................................................................................................................................. 7.1

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CHAPTER 7 - FUELING RECORD

Chapter 7

1 FUELING FORM COMPLETION INSTRUCTIONS

Completion of the Aircraft Fueling Form (Form OFS-101) is the responsibility of Avatar Airlines Representative as
defined below. Information concerning fuel load will be obtained from the respective flight release and the appropriate
information entered on the form. The fuel density will be obtained from the fuel supplier. All fuel loading instructions
must be in writing using this form.
Avatar Airlines Representative is defined as:
• Authorized A&P Mechanic.
• Operations Manager.
• First Officer and/or Pilot in Command.

1.1 Key to Form Completion

1) Enter aircraft "N" number, flight number, Z-date and IATA 4 letter airport coding.
2) Enter total fuel required from flight release.
3) Enter type of fuel serviced (obtained from fuel supplier, along with fuel density) and additive used.
4) Enter total fuel on board from cockpit gauges, prior to starting fueling.
5) Enter total fuel added (x) fuel density (Ref chart) (=) Added Fuel (+), fuel on board before fueling, item 4 (=)
Total Fuel Calculated.
6) Use this section when conversion to gallons is required. If not required leave blank.
7) Use this section when stick readings are required by alternate fueling method. If not required leave blank.
8) This section used by the Pilot in Command for inclinometer indications.
9) Signature of Pilot in Command after completion of procedure.
10) Signature of individual accepting the fuel load.

1.2 Form distribution

White (Top) copy: This copy retained by Flight Deck Crew and included in trip envelope.

Yellow (2nd) copy: Retained by maintenance (When onboard or at airport).

Pink (3rd) copy: Remains at departure station.

 AVATAR AIRLINES AIRCRAFT FUELING
(UNDER NO CIRCUMSTANCES SHOULD FUELERS PULL ANY CIRCUIT BREAKERS OR REMOTE FUSES)
avatar airlines

VERIFICATION FUEL DENSITY

AIRCRAFT
TAIL NO. N LB / KG / KG / LB /
TOTAL FUEL ADDED DENSITY (See Chart) ADDED UPLIFT FUEL GAL GAL LTR IMP GAL
FLIGHT NO.
GAL X LB/GAL = LBS 6.30 2.858 0.755 7.57
Z-DATE:
6.35 2.880 0.761 7.63
+ STATION:
TANK GAUGE READING 6.40 2.903 0.767 7.68
FUEL ON BOARD
FUEL TYPE: BEFORE FUELING STICK READING LBS 6.45 2.926 0.773 7.75
TANK
2R NUMBER IN INCHES (From Table)
WAS ADDITIVE USED? Y N
LBS
6.50 2.948 0.779 7.81
(CIRCLE ONE)
2R
1R
1R 6.55 2.971 0.785 7.87
REMARKS: =
1M CALCULATED 1M 6.60 2.994 0.791 7.93
TOTAL RAMP FUEL
2M 6.65 3.016 0.797 7.99
2M
LBS CTR 6.70 3.039 0.803 8.05
CTR
3M 6.75 3.062 0.809 8.11
3M CONVERSIONS 4M
6.80 3.084 0.815 8.17
VOLUME FACTOR VOLUME 4R
4M 6.85 3.107 0.821 8.23
(X 0.2642 =) US 3R
LTR
4R (X 3.785 =) GAL TOTAL 6.90 3.130 0.827 8.29
CHAPTER 7 - FUELING RECORD

6.95 3.152 0.833 8.35

3R IMP (X 1.2 =) US
GAL (X 0.833 =) GAL INCLINOMETER INDICATION 7.00 3.175 0.839 8.41
FUELING AND SERVICING MANUAL

TOTAL WING
DENSITY FACTOR DENSITY NOSE UP / ON 7.05 3.198 0.845 8.47
FUEL LEFT RIGHT
LBS
(X 8.345 =) 7.10 3.221 0.851 8.53
HIGH
(X 0.12 =)
KG/LITER LBS/US GAL - o o o 7.15 3.243 0.857 8.59
Form 7.1 Aircraft Fueling Form (Form OFS-101)(Page 1 of 2))

(X 0.833 =)
7.20 3.268 0.863 8.65
(X 1.2 =) LOW
LBs/IMP GAL LBS/US GAL
FUEL LOAD ACCEPTED BY: (PRINT NAME) + 7.25 3.289 0.869 8.71
o o o
(X 2.2046 =)
7.30 3.311 0.875 8.77
KG/GAL (X 0.4536 =) LBS/US GAL

FUELED BY: (PRINT NAME) WHITE - FLIGHT CREW (Trip Envelope)

YELLOW - MAINTENANCE OFS-101 MAR.25.21
PINK - STATION
A

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Form 7.1 Aircraft Fueling Form (Form OFS-101)(Page 2 of 2)

MEASURING STICK INSTRUCTIONS

1. Confirm that the fuel load is for the correct airplane and flight.

2. Confirm that the required fuel load is on board as follows:

ƒ The sum of all the quantity gauges should be at least equal to, but should not exceed by more than
3,000 lbs, the total requested fuel load (ultimately the take-off fuel value entered on the weight and
balance plus taxi fuel).

ƒ Individual gauge values should be within 1,000 lbs of the value found on the fuel distribution chart. See
the Fueling and Servicing Manual (FSM) for further details. Re-check fuel density if all gauges are
reading high or low for a measured amount of fuel added.

ƒ Add the number of pounds of metered fuel delivered to the gauge readings taken. This total should be
no more than 1,000 lbs less than, or 3,000 lbs more than, the total fuel value listed on the weight and
balance plus taxi fuel. Use the fuel gauges totalizer only if proved accurate. Be sure to factor in APU
fuel burn into total required fuel. Typical APU fuel burn is 900 lbs/hr.

ƒ If errors cannot be resolved, recheck by measuring stick. With a quantity gauge inoperative, the
measuring stick MUST be used to confirm fuel load in the associated tank. After a fuel quantity gauge
system has been serviced / repaired, use measuring stick for the first subsequent departure. Fuel
distribution and stick measurement charts can be found in the FSM.

3. Obtain fuel density from fuel supplier in determining pounds of fuel to be added.

MEASURING STICK PROCEDURE

1. Check aircraft inclinometers to determine incline of aircraft in degrees; e.g., nose up or nose down,
left wing high, right wing low, etc.

2. Check measuring stick conversion chart located in the FSM to determine proper stick to be pulled
for the tank fuel required. The stick selected should be the stick giving the largest stick reading in
inches for the tank required.

3. Determine tank fuel required in pounds using fuel distribution chart located in the FSM. Calculate
tank fuel required in pounds. Consult inclinometer chart for tank stick readings. Inclinometer
Charts are located in the FSM and are listed by stick for applicable tanks.

OFS-101 (2) MAR.25.21

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Form 7.2 Fuel Distribution Form (Form OFS-100)(Page 2 of 2)

AVATAR AIR LINES

FLIGHT OPERATIONS
B747-400
FUEL DISTRIBUTION REQUEST FORM
Aircraft
Tail # N____________ FLT No. ____________ Z-DATE: ____________

TANK DESIRED
STATION: ________
No. FUEL DISTRIBUTION
2R lbs

1R lbs

1M lbs
DENSITY: ________
2M lbs (Fuel Density will be obtained
from the Fuel Supplier)

CTR lbs

3M lbs

4M lbs TYPE FUEL

4R lbs JET A Ƒ
3R lbs JET A1 Ƒ
OTHER: _________
TOTAL lbs

AFTER FUELING INFORMATION:

TOTAL US GALLONS ADDED: ________________________
OR
TOTAL LITERS ADDED: _____________________________

** RETURN FORM TO FLIGHT ENGINEER AFTER FUELING **

OFS-100 MAR.25.21
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CHAPTER 8 TOC Chapter 8 TOC

CHAPTER 8 - FUEL SYSTEM DESCRIPTION.................................................................................................. 8.1

1. FUELING SYSTEM DESCRIPTION ................................................................................................................................ 8.1
1.1 General ............................................................................................................................................................ 8.1
1.2 Fueling ............................................................................................................................................................. 8.1
1.3 Fuel Quantity Indicating ................................................................................................................................... 8.1
1.4 Fuel Tank Measuring Sticks ............................................................................................................................. 8.1
1.5 Engine Fuel Valve ............................................................................................................................................ 8.2
1.6 Fuel Boost Pumps ............................................................................................................................................ 8.2
1.7 Center Tank Scavenge Pump .......................................................................................................................... 8.2
1.8 Crossfeed Manifold .......................................................................................................................................... 8.2
1.9 Reserve Tanks No. 1 and No. 4 ....................................................................................................................... 8.2
1.10 Fuel Tank Vent System .................................................................................................................................... 8.2
1.11 Surge Tanks ..................................................................................................................................................... 8.3
2. FUEL TANK ARRANGEMENTS AND CAPACITIES ....................................................................................................... 8.3
3. B747-400 FUEL LOAD DISTRIBUTION .......................................................................................................................... 8.4
3.1 Fuel Load Distribution Procedure ..................................................................................................................... 8.4
3.2 Fuel Distribution Tables ................................................................................................................................... 8.5
4. BALLAST FUEL ............................................................................................................................................................... 8.8

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Chapter 8 CHAPTER 8 - FUEL SYSTEM DESCRIPTION

1 FUELING SYSTEM DESCRIPTION

1.1 General
The fuel system consists of, tanks, a crossfeed manifold, crossfeed valves, two fueling stations, a fuel jettison system,
a vent system, and a surge tank in each wing tip.
All tanks are formed by sealing the internal wing structure. The fuel tanks on the B747-400 have two basic
configurations, nine tanks or seven tanks. The difference between the configurations is the addition of two reserve
tanks for main tanks 2 and 3.The seven tank configuration consists of four main tanks, two reserve tanks and one
center wing tank. The nine tank configuration consists of four main tanks, four reserve tanks and one center wing tank.
Sump drains are provided for draining the low point of each tank.
The aircraft fuel system contains the following valves controlled at the engineer's panel: engine fuel shutoff valves (as
installed), crossfeed valves, reserve tank transfer valves, main tank 1 and 4 jettison transfer valves, center wing jettison
valves, fuel jettison nozzle valves, and an APU fuel valve.
When any of these valves are actuated, an associated in-transit light comes on and remains on until the valve actuator
motor completes its cycle. The light operates in conjunction with the valve motor and not the valve position.

1.2 Fueling
Fueling is normally accomplished using the underwing pressure fueling method. Fuel is delivered under pressure from
external fueling stations (one in each wing) through the fueling manifold and then through fueling valves into each tank.
A fueling control panel is located in the lower leading edge of the left wing, outboard of the fueling station. All controls
required for operation of the fueling system are located in the fuel control panel. When a full tank of fuel is sensed, a
volumetric shutoff automatically closes the tank fueling valve.
Fuel quantity indicators are located at the left wing fueling station. Servicing personnel will normally monitor the
indicators and close the refueling valve when the desired quantity of fuel is loaded.
Overwing fill ports are provided for the four main tanks only.

1.3 Fuel Quantity Indicating

Fuel quantity is indicated in pounds by the use of a capacitance type indicating system. Each fuel tank contains several
densiometer units that compensate for fuel density. The fuel quantity measurement is displayed as a four digit number
on the engineer's fuel panel quantity gages. The gages are displayed in pounds x 1000.
The fuel tank indicator display blanks when indicator power is lost or a fueling gauging fault causes an error greater
than 5.0% of the tank full-scale fuel quantity. A blank indicator display or a reading of 0 pounds indicates that any
remaining fuel cannot be used for flight decisions.
The summation of all tank quantity indicators is displayed by the total fuel indicator and indicates total fuel on board.
Since the total indicator depends on the summation of all tank quantity indicators, a failure or fault of any one indicator
causes the gross weight indicator to go blank.

1.4 Fuel Tank Measuring Sticks

A dripless measuring stick in each tank permits a manual reading of tank quantity. The system consists of a float ring
with magnets encircling a stick with a metal tip. The measuring sticks are unlocked by depressing, rotating 90 degrees
in either direction, and then releasing. Locking is accomplished in the same manner. Fuel quantity is determined by
pulling the stick all the way down then raising it until it magnetically couples with the float. Quantity is read from the
exposed stick calibration at the point where the stick enters the housing. If fuel is added, the stick and float, which are
magnetically coupled together, will rise as the fuel level rises. Main tanks Nos. 1, 2, 3, and 4 have three sticks each.
Reserve tanks Nos. 1 and 4 have one stick each. Reserve tanks Nos. 2 and 3 have two sticks each and the center
tank has one stick.
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1.5 Engine Fuel Valve

The engine fuel valve permits shutting off fuel to the engine at the main tank, downstream from the crossfeed
manifold. The valve body is inside the fuel tank near the pylon and the drive motor is in the forward bulkhead of the
fuel tank. The motor is powered from the Hot Battery bus through the engine fuel valve switch, the engine fire control
handle, and the start lever.

1.6 Fuel Boost Pumps

The electrically driven centrifugal boost pumps in the main tanks receive power from the normal AC busses. DC
power is used for pump control. Boost pump switches are on the engineer's fuel panel. Pump output pressure is
rated at 17 psi. Each pump incorporates an amber low pressure warning light that comes on whenever the pump
discharge pressure drops below limits. The pump pressure lights are powered through the engineer's warning light
circuits.
Both boost pump low pressure lights for any main tank will flash as a warning that the boost pump switches and/or
crossfeed valves are not in the proper configuration for fuel feed to the associated engine. This will occur when:
1) Both boost pump switches are off and the associated crossfeed valve is closed or,
2) Both boost pump switches are off, the associated crossfeed valve is open but the crossfeed manifold is
unpressurized.

1.7 Center Tank Scavenge Pump

The center tank is provided with a scavenge pump to remove residual fuel that cannot be pumped from the tank by
the override/jettison pumps.
The scavenge pump is powered from AC bus 1 through a control switch on the engineer's fuel panel. A low pressure
light comes on whenever pump discharge pressure drops below limits. The scavenge pump transfers fuel into the
No. 2 main tank.
The pump is rated at 1,499 lbs to 1,698 lbs per hour fuel flow.

1.8 Crossfeed Manifold

The crossfeed manifold provides a means of distributing the fuel from the center wing or any main tank to any
engine. The crossfeed manifold can also be interconnected with the jettison manifold through the center wing tank
jettison valves allowing the No. 2 and No. 3 main tank jettison pumps to crossfeed fuel to any engine.
Rotary switches on the fuel panel control crossfeed valve position.
These switches are marked with lines and align with the flow lines on the fuel panel when the crossfeed valves are
open.
Located in the crossfeed manifold is the flow equalization valve. This valve acts as an automatic crossfeed
separation valve. As long as there is approximately equal boost pump pressure on each side of the valve it will
remain closed, preventing fuel imbalance. When the pressure drops below a preset value on one side of the valve it
will open allowing positive fuel feed to be provide to the lower pressure side.

1.9 Reserve Tanks No. 1 and No. 4

The reserve tanks No. 1 and No. 4 fuel is gravity fed into the adjacent outboard main tank through the reserve tank
valve. Aligning the reserve tank valve switch flow line with the flow lines on the fuel panel opens the reserve valve. It
takes approximately twenty minutes to transfer a full reserve tank into its adjacent main.

1.10 Fuel Tank Vent System

The fuel vent system provides positive venting of the fuel tanks to atmosphere during all flight attitudes. Fuel tank
vent ports are positioned so that at least one port is open to the expansion area at all times. Fuel vent float valves
located near the top of the fuel tanks prevent fuel from entering the vent system during airplane attitude changes.
Vent outlets are located near the wingtips in the surge tank vent line.
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1.11 Surge Tanks

A surge tank in each wingtip provides an expansion chamber for excess fuel due to overfilling or thermal expansion. If
the overfill exceeds approximately 30 US gallons an overfill float switch will cause all fueling valves to close. Surge tank
fuel is drained back into the inboard main fuel tanks. If more than 125 US gallons of fuel is collected the fuel will be
vented overboard.

2 FUEL TANK ARRANGEMENTS AND CAPACITIES

Figure 8.1 B747-400 Fuel Tank Capacities at 6.7 Lbs/Gal

FULL TANKS FULL WINGS

358,324 LBS 243,324 LBS
(162,530 KGS) (110,370 KGS)

Table 8.1. B747-400 Fuel Tank Capabilities at 6.7 Lbs/Gal

TANKS GALLONS POUNDS

1 or 4 Reserve 510 3,417

2 or 3 Reserve 785 5,259
1 or 4 Main 4,319 28,935
2 or 3 Main 12,546 84,051
Center 17,164 115,000

TOTAL 62,560 358,317

NOTE
Avatar does not operate the B747 with a body fuel tank or with #2 and
#3 reserve tanks as Dry Bays.
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3 B747-400 FUEL LOAD DISTRIBUTION

3.1 Fuel Load Distribution Procedure

For the purposes of this manual, Fuel Distribution is defined as the allocation of specific portions of the Total Fuel
Load to various aircraft fuel tanks.
Fuel tanks are numbered in the same manner as aircraft engines, i.e. from left to right looking from the tail of the
aircraft.
Takeoff Fuel (TOF) is the fuel required at the start of takeoff roll. Block Fuel is the TOF plus Taxi Fuel. When
distributing the fuel load, the Total Fuel at Block must be accounted for.
Fuel may be loaded simultaneously or in any sequence. For normal operation, load the tanks so that the resulting
fuel distribution is symmetrical about the airplane centerline. Use the Fuel Distribution Request Form (Form OFS-
100), to set the thumb wheels on the refueling station to the total fuel quantity desired.

WAR NI NG
FUEL DISTRIBUTION TABLES ARE AIRCRAFT SPECIFIC. BE SURE TO USE
THE CORRECT DISTRIBUTION TABLE AND/OR PROCEDURE. SEE APPENDIX
B FOR THE TABLES.
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3.2 Fuel Distribution Tables

Table 8.2. B747-400 Fuel Distribution - 30,000 to 228,000 Lbs (Pg 1 of 2)

NEED TABLES
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Table 8.3. B747-400 Fuel Distribution - 230,000 to 345,000 Lbs (Pg 2 of 2)

If B747-400 with 2 & 3 Reserves, use table 6.13 for 230,000 to 354,000 lbs fuel distribution.
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Table 8.4. Fuel Distribution with 2 and 3 Reserves (233,000 to 355,400 Lbs)

If B747-400 with 2 & 3 Reserves, use table 6.12 for 230,000 to 3554,000 lbs fuel distribution.

Table 8.5. B747-400 Fuel Density / Pounds

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4 BALLAST FUEL
On some flights, such as Ferry Flights, it may be necessary to load Ballast Fuel for CG purposes. Ballast Fuel is
loaded in the Center Tank. Normal policy is to load 10,000 lbs as Ballast Fuel, but less may be carried if desired. It is
considered as non-usable fuel, carried as Payload. The procedure for loading Ballast Fuel is set out below.
The 10,000 lbs Ballast Fuel will be entered in the BALLAST box on the Weight and Balance. Use the appropriate
index from the Center Tank Ballast Fuel Index table on the W/B Form. The remainder of the Total Fuel is distributed
normally, as shown above, and the index is taken from the Normal Fuel Distribution Table on the Weight and Balance
Form.

NOTE
When operating a Ferry or other flights with light or zero loads, BAL-
LAST FUEL may be required to bring the ZFW %MAC into limits. Bal-
last Fuel will be specified as such on the Flight Release. Ballast Fuel
is always carried as Payload in the Center Tank and is considered as
UNUSABLE fuel.
Determine the index for Ballast Fuel from the Ballast Fuel Table on the
Weight and Balance form. Enter the Ballast Fuel weight and index in
the BALLAST box on the Weight and Balance. On the Flight Release,
Ballast Fuel is shown as Payload, and the Ballast Fuel Table includes
the fuel necessary to carry the Ballast Fuel. The Flight Plan line item
labeled "REQD" is the required fuel and does not include the Ballast
Fuel.

NOTE
It is important to understand that Ballast Fuel as Payload with its in-
dex, and the rest of the fuel with normal distribution and its index ac-
count for the proper weight distribution on the aircraft.

WAR NI NG
IT IS REQUIRED THAT THE CG FOR THE ZFW BE WITHIN LIMITS ON THE CG
CHART
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CHAPTER 9 TOC Chapter 9 TOC

CHAPTER 9 - FUEL STANDARDS ................................................................................................................... 9.1

1. FUEL STANDARDS ........................................................................................................................................................ 9.1
2. FUEL CONDITION CHECKS .......................................................................................................................................... 9.1
2.1 General ............................................................................................................................................................ 9.1
2.2 Procedure ......................................................................................................................................................... 9.2
2.3 Appearance Test - Also Known as the "White Bucket Test" ............................................................................ 9.2
2.4 Rating of White Bucket Sample ...................................................................................................................... 9.3
2.5 Action Required if Red Dye is Detected ........................................................................................................... 9.4
2.6 Clear and Bright Test ....................................................................................................................................... 9.4
3. FUEL STORAGE FACILITIES INSPECTION .................................................................................................................. 9.5
4. FUELING EQUIPMENT INSPECTION ............................................................................................................................ 9.6
5. TESTING FOR WATER IN FUEL STORAGE FACILITIES ............................................................................................. 9.7
5.1 Fuel in Tank Trucks .......................................................................................................................................... 9.7
5.2 Storage Tank Tests .......................................................................................................................................... 9.8
5.3 Tank Truck Tests ............................................................................................................................................. 9.8
6. TESTING DURING FREEZING CONDITIONS ............................................................................................................... 9.8
7. CONTAMINATED FUEL .................................................................................................................................................. 9.8

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Chapter 9 CHAPTER 9 - FUEL STANDARDS

1 FUEL STANDARDS
14 CFR 121.135(b)(19)
1) This Chapter is intended for use at commercial airports within the 48 contiguous United States.
a) At locations other than those, Alternate Procedures may need to be developed due to local country or
other regulatory requirements.
b) At locations within the 48 contiguous United States, Alternate Procedures to the policies and procedures
in this manual which will not compromise fuel quality, safety or security may be developed.
2) The requirements in this Chapter specify product standards for the facilities and equipment of those
organizations receiving, storing and dispensing fuel for use in Company aircraft:
a) It contains inspections to be performed at specified frequencies for:
1) Fuel Storage Facility
2) Fueling Vehicle
3) Hydrant System Check
b) The inspections specify further testing and checks as follows:
1) Clear and Bright Test
2) White Bucket Test
3) Membrane Filtration Test
4) Free Water Test
5) API Gravity Test
6) Filter Vessel Differential Pressure
7) Bonding Cable Continuity Check
8) Water Defense System (Automatic Water Slug and Dump Systems)
9) Fuel Storage Tank Inspection and Cleaning
10) Water Separator Test (Microsep)
11) Filter Element Replacement Criteria

NOTE
1) In all phases of handling, the fuel shall be visually free from water,
sediment, haze or emulsion.
2) Fuel quantity is measured in Pounds.

2 FUEL CONDITION CHECKS

2.1 General
This section describes the policy and procedures that ensure the quality of fuel meets Company standards when
situations such as Avatar Airlines operating to an off-line station due to a diversion, ad-hoc charter, etc arise which
require that Avatar Airlines accepts fuel from vendors that have not been audited by the Quality Assurance department
and are therefore not on the Approved Vendor List.
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2.2 Procedure
1) Dispatch will notify Maintenance Control.
2) Maintenance Control will verify that the fuel vendor is on the Approved Vendor List and if not will call the
Flight Deck crew and notify them that a "White Bucket" test is required.
3) Prior to the fuel truck delivering fuel to the aircraft, the flight engineer will request a "White Bucket" test to be
accomplished.
4) The fueling company will comply with the request and ensure the fuel is contaminant free as witnessed by
the flight engineer.
5) The Captain will enter a discrepancy into the Aircraft Log using ATA 12-00: “Fuel quality test required prior to
fueling for off line station.”
6) Once the test is completed and confirmed free of contaminates, the flight engineer will sign the item off in the
Aircraft Logbook as follows: “Fuel quality test completed, no contamination found.”
7) The Captain will call MCC to advise that a fuel quality test was accomplished successfully and provide the
following information:
a) Aircraft Number
b) Flight number and UTC Date
c) Station
d) Name of the flight engineer
8) Maintenance Control will review the logbook entry in accordance with procedures in the GPM.
a) Name of the Fueling Vendor (Company)

The following procedures are derived from ATA Spec 103.

These procedures provide a quick method for detecting free water, solids, and other traces of possible
contamination. The two most common sampling methods used for evaluating the visual appearance of aviation
fuel samples are; the White Bucket Test and the Clear and Bright Test.

Therefore, only the white porcelain bucket is to be used for the optimum detection of red dye contaminated fuel.

2.3 Appearance Test - Also Known as the "White Bucket Test"

A White Bucket test may be performed anytime there is doubt as to the purity of the fuel before it is transferred into
the aircraft.
1) Fill a suitable container (preferably a white porcelain bucket) with approximately 1 gallon of fuel.
2) Let the sample settle for 1 minute to remove air bubbles.
3) Place the clean bucket on a level surface and inspect the bottom for water droplets, solid contaminants,
hazy/cloudy condition, brown slime, and observe the color of the fuel.

Caution
TO DETERMINE THE DIFFERENCE BETWEEN A HAZE CAUSED BY
ENTRAINED WATER OR AIR BUBBLES, IT MAY BE NECESSARY TO PERFORM
A WATER DETECTION TEST (REF ATA SPEC 103).
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4) Examine the sample for solids and/or sediment on the bottom of the bucket. Sample clarity can be checked by
placing a small, shiny object with definition on the bucket's bottom. If the fuel is dry, the definition can be easily
distinguished. The amount of sediment observed can be described by a letter category using the ' Color and
Particle Assessment Rating Guide', SGTP-3940, available from Gammon Technical Products, Manasquan, NJ.

NOTE
The presence of contamination is much more evident when the
sample is taken from a pressurized system.Samples removed from a
static system may indicate little contamination when significant
contamination actually can be found under flow or pressurized
conditions. Ensure the fuel sampling tap is free of loose
contaminants.

WAR NI NG
IF A PINK OR REDDISH DISCOLORATION IS OBSERVED, PERFORM A
REFEREE WHITE BUCKET TEST FOR POSSIBLE DYE CONTAMINATION.

2.4 Rating of White Bucket Sample

Table 9.1. Solids Contaminant and Moisture Indicators

Solids Contaminant Indicators Moisture Content Indicators

1.Clean A. Bright

2.Slight Particulate Matter B. Hazy

3.Particulate Mattel C. Cloudy

4. Dirty D. Wet (Free Water)

E. Surfactants

Table 9.2. Rating Definitions

Rating Rating Guide

Clean Refers to lack of particles, silt or sediment,

flakes, dye, rust or solids

Slight Particulate Matter Contains several fine to moderate sized parti-

cles

Particulate Matter A sample in which many small particles may be

seen floating or settled on the bottom

Dirty Discoloration or many particles dispersed in the

fuel or settled on the bottom
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Table 9.3. Moisture Content Indicators

Rating Rating Guide

Bright Brightness is a quality independent of the color

of the sample and refers to the lack of sus-
pended or free water in the sample. Bright fuel
tends to sparkle.

Hazy A condition resulting from fine droplets of mois-

ture dispersed throughout the sample produc-
ing a dull hazy appearance. This can be a
temporary condition brought about by a drop in
temperature. During the first minute, the fuel
can appear hazy due to air bubbles.

Cloudy The result of extremely fine droplets of water

dispersed throughout the sample giving it a
milky appearance

Wet Any form of free water appearing as droplets or

bulk water on the bottom of the bucket or cling-
ing to the sides

Surfactants Slime in the bottom of the bucket or at the fuel/

water interface appearing as a dark brown/
black layer, scum or lacy material floating in or
on the sample

2.5 Action Required if Red Dye is Detected

1) The white bucket test shall be used to inspect for red dye contamination. The referee white bucket shall be
the white porcelain bucket obtained from Gammon Technical Products, GTP-1746B or GTP-1746C. This test
requires collecting approximately a two (2) gallon sample with a fuel depth of 6 inches, +1- 1.0 inch. The
inspector (with normal vision or wearing corrective non-tinted lenses) performs a visual examination of the
fuel for color under normal daylight conditions, or in any well-lighted room such as an office with fluorescent
lighting. If the inspector is not sure of the fuel color, a consensus of the color should be obtained from several
individuals.
• Jet fuel with no visible red tint should be judged acceptable for use in aircraft.
• A red tint resulting from refinery processing will usually disappear when exposed to light. Jet fuel is
acceptable for use if the red tint disappears in less than 30 minutes after being exposed to light.
2) Jet fuel produced by blending a red dyed fuel with a non-dyed fuel may be acceptable, providing the resulting
fuel has no visible red tint, and fuel satisfies [ASTM D1655] specifications. Blending is not to be performed at
an airport fuel storage facility without prior authorization by affected airline(s).

2.6 Clear and Bright Test

NOTE
The White Bucket test may be used in lieu of the Clear and Bright test
where the Clear and Bright test is specified; however, the Clear and
Bright test may NOT be used in lieu of the White Bucket test, when
specified.

The clear and bright test is performed by filling a 32 oz. Mason jar full and then visually examining it for clarity, water,
solids and/or sediment. The jar is then closed, swirled and examined for traces of water at the vortex bottom. There
should be no suspended or visible free water, and sample should be clear and bright (slight sparkle). Air bubbles may
cause hazy appearance immediately after the sample is drawn, but haze clears from the bottom up.
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Therefore, while small water droplets and air bubbles may appear similar, air bubbles will rise while water droplets will
settle upon standing. Finely dispersed droplets in the fuel sample may be caused by temperature change due to cooling
and may show up as a cloudy white appearance.

3 FUEL STORAGE FACILITIES INSPECTION

Storage facilities used to store aviation fuel will be audited in accordance with routine auditing procedures as detailed in
QAM Chapter 7.
Storage facilities must also be inspected by qualified personnel employed by the vendor. Additionally, the vendor must
have a program in place and maintain records to show compliance with the following:
1) A DAILY inspection must be made, with all the findings recorded. The following items are included in the daily
inspections:
a) Check bottom of all storage tanks for water or other contaminants with water draw-off or water-finding
paste.
b) Take a white bucket sample of filter/separator sumps under pressure. Drain off any water.
c) Check and record pressure differential across all filters (under normal flow conditions).
d) Inspect above-ground piping, meters and pumps for leaks (under pressure).
e) Check floating suction for proper operation (if equipped).
f) Check ground cables and clamps.
g) Inspect security locks.
h) Inspect unloading hose, hose cap, and stowage.
2) A WEEKLY inspection must be made with all findings recorded. The weekly inspection will include the following
items, in addition to the daily inspection items:
a) Inspect all fire extinguishers (seals and tags) inspection date.
b) Inspect bottom loading nozzle screens.
c) Inspect bottom loading hose (general condition, cap and stowage).
d) Inspect product identification.
3) A MONTHLY inspection must be made, with all findings recorded. The monthly inspection will include the
following items, in addition to the daily and weekly inspection items:
a) Millipore test (downstream of filter/separator); 3-gallon sample rated dry or 3 liter.
b) Inspect in-line fuel strainers.
c) Continuity check of ground cables and clamps (10 Ohms max).
4) An ANNUAL inspection must be made, with all findings recorded. The annual inspection will include the
followings items, in addition to the daily, weekly, and monthly inspection items:
a) Empty and inspect tank interiors. If more than 15% of tank has contaminants, the tank must be cleaned.
b) Calibrate meters unless a shorter frequency is required by local or state laws.
c) Change filter/separator elements.

NOTE
Filter/separator element life may be extended if a verifiable single el-
ement test is made after twelve months and after eighteen months.
Filter element change is required after two years service.

d) Filter/separator elements must be changed at any time the differential pressure exceeds 15 psi at rated
flow or if there is an unacceptable single element test result.
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e) Trucks/Hydrants using monitor type filters are to be changed in accordance with the manufacturer's
recommendations. Depending on the manufacturer, differential pressure change recommendations
may vary from 15 to 22 psi.
f) Check water slug valve shut-off operation.

4 FUELING EQUIPMENT INSPECTION

Fueling equipment will be audited in accordance with routine auditing procedures as detailed in QAM Chapter 7.
At airports staffed with a Operations Manager, surveillance of fueling procedures and equipment is accomplished
continuously by the Operations Manager, or qualified designee.
Fueling equipment must also be inspected by qualified personnel employed by the vendor. Additionally, the vendor
must have a program in place and maintain records to show compliance with the following:
1) A DAILY inspection must be made, with all findings recorded. A 12-month period of records must be
maintained with all inspections signed. The daily inspection includes the following items:
a) Inspect equipment to see that it is clearly marked as to the type of fuel it contains, flammable/no
smoking decals and emergency shutoffs marked.
b) Inspect the interior of the tanks for water, surfactants, and dirt.
c) Inspect the coating of all epoxy coated tanks.
d) Inspect fire extinguishers (seals, tags, inspection date).
e) Inspect sample from tank sumps.
f) Inspect samples from filter/separator sump drains.
g) Inspect the deadman control valve for proper operation.
h) Check differential pressure, under high-flow conditions.
i) Put system under pressure and check for leaks (record nozzle pressure).
j) Inspect ground wires and clamps.
k) Inspect lift deck for proper operation and emergency shut-off if applicable.
l) Check emergency shut-off operation.
m) Inspect nozzle dust covers (if applicable).
n) Check exhaust system.
o) Inspect all glass mirrors.
p) Check brake interlock.
q) Inspect all lights and lenses. Check tires.
r) Cleanliness of equipment.
s) Air tank drains.
2) A WEEKLY inspection must be made, with all findings recorded. A 12-month period of records must be
maintained with all inspections signed. The weekly inspection includes the following items in addition to the
daily inspections:
a) Inspect delivery hoses (under pressure) for leaks, cuts, and abrasions.
b) Check primary control valve pressure at 35±3 psi.
c) Check secondary pressure control (cannot exceed 50 psi).
d) Inspect dome cover gasket.
e) Inspect manhole gasket.
f) Inspect exhaust system.
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3) A MONTHLY inspection must be made, with all findings recorded. A 12-month period of records must be
maintained with all inspections signed. The monthly inspection includes the following items in addition to the
daily and weekly inspection items.
a) Inspect nozzle screens.
b) Millipore inspection. Downstream of filter/separator, 3-gallon sample rated dry or 3 liter sample rated
dry.
c) Check continuity of ground cables (10 Ohm max).
d) Test water slug valve operation.
4) A YEARLY inspection must be made, with all findings recorded. A 12-month period of records must be
maintained with all inspections signed. The yearly inspection includes the following items in addition to the
daily, weekly and monthly inspection items.
a) Check tank interiors. Drain if necessary.
b) Change filter/separator elements.

NOTE
Filter/separator element life may be extended if a verifiable single el-
ement test is made after twelvemonths and after eighteen months. Fil-
ter element change is required after two years service. Filter/
separator elements must be changed at any time the differential pres-
sure exceed 15 psi at rated flow or if there is an unacceptable single
element test result.

Trucks/Hydrants using monitor type filters are to be changed in accordance with the manufacturer's
recommendations. Depending on the manufacturer, differential pressure change recommendations may vary from 15
to 22 psi.

5 TESTING FOR WATER IN FUEL STORAGE FACILITIES

14 CFR 121.135(b)(19)
Avatar Airlines is responsible to assure that fuels used in Company aircraft are not contaminated. The vendor is
responsible for assuring that water checks are conducted in accordance with the specifications outlined herein and
that the required inspections and records are maintained.

5.1 Fuel in Tank Trucks

Check separator and sump of each truck daily. Check at a definite time, preferably early in the morning.
Check after each refueling.
Make tests per section titled “Tank Truck Tests”. If temperature of fuel is below freezing, refer to following section
titled Contaminated Fuel.
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5.2 Storage Tank Tests

Check with water-indicating paste on a clean pole. Pole must reach to the bottom of the tank.

OR
Check by draining from tank drain into a clean glass container and use water-indicating pastes, or equivalent, to
show water.
All water must be removed by suction pump or through tank drains.
If a tank has a float suction, check that it is floating. Check that slip joints work freely.

5.3 Tank Truck Tests

Drain fuel from separators and sumps into a clean glass container and use water-indicating paste, or equivalent, to
show water.
All water must be removed.

6 TESTING DURING FREEZING CONDITIONS

Where the temperature of fuel is below freezing point of water, no indication of water will be shown. Conduct test for
water during periods of thaw. During thaw, if it suspected that water in the form of ice crystals is present, the
procedure used for removal of liquid water should be used.
A much larger quantity of fuel will have to be removed than when removing liquid water.

7 CONTAMINATED FUEL
14 CFR 121.135(b)(19)
If fuel contamination is discovered during aircraft fuel servicing, the following procedures should be followed:
1) Vendor
• Cease product delivery
• Notify Operations Manager, Pilot In Command or authorized individual as applicable
2) Operations Manager, Pilot In Command or authorized individual
• Notify Operations Control Immediately
3) Operations Control
• Notify Director of Maintenance Operations, Chief Maintenance Inspector and Director of Ground
Operations
4) The Chief Maintenance Inspector will determine the course of action.
If fuel contamination is discovered by maintenance during fuel tank sumping, notify Maintenance Control.
Maintenance Control is to notify Director of Maintenance Operations, Chief Maintenance Inspector, Director of
Ground Operations and Operations Control.
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CHAPTER 10 TOC Chapter 10 TOC

CHAPTER 10 - DEFUELING PROCEDURES ................................................................................................. 10.1

1. DEFUELING MAINTENANCE PRACTICES ................................................................................................................. 10.1
1.1 General .......................................................................................................................................................... 10.1
2. FUEL TANK DEFUELING ............................................................................................................................................. 10.3
2.1 General .......................................................................................................................................................... 10.3
2.2 Equipment and Materials ............................................................................................................................... 10.3
2.3 Fuel Pump Limitations .................................................................................................................................... 10.3
2.4 Pressure Defueling ......................................................................................................................................... 10.4
3. DEFUELING USING AUXILIARY DEFUELING EXTERNAL POWER CONTROL UNIT .............................................. 10.9
3.1 General .......................................................................................................................................................... 10.9
3.2 Equipment and Materials ............................................................................................................................... 10.9
3.3 Prepare for Defueling ..................................................................................................................................... 10.11
3.4 Defuel Center Wing Tank ............................................................................................................................... 10.11
3.5 Defuel Main and Reserve Tanks .................................................................................................................... 10.12
3.6 Restore Airplane to Normal. ........................................................................................................................... 10.13
4. TANK-TO-TANK FUEL TRANSFER .............................................................................................................................. 10.13
4.1 General .......................................................................................................................................................... 10.13
5. LATERAL FUEL IMBALANCE ....................................................................................................................................... 10.14
5.1 General .......................................................................................................................................................... 10.14
5.2 Access ............................................................................................................................................................ 10.14
5.3 Procedure ....................................................................................................................................................... 10.15

00
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Chapter 10 CHAPTER 10 - DEFUELING PROCEDURES

1 DEFUELING MAINTENANCE PRACTICES

FAA AD 2002-19-52, AD 2002-24-51

1.1 General
1) Defueling maintenance practice procedures provide instructions for fuel tank defueling, defueling through
pressure fueling receptacles using auxiliary defueling external power control unit, and tank-to-tank transfer.
Standard precautions in effect at the airport, or as required by the airline must be observed during all defueling
operations.

WAR NI NG
DO NOT OPERATE WEATHER RADAR WHILE THE AIRPLANE IS BEING
REFUELED OR DEFUELED. DO NOT OPERATE IN ANY RADIATING MODE
WHILE A FUELING OPERATION IS BEING CONDUCTED WITHIN 200 FEET OF
THE ANTENNA; AN EXPLOSION MAY OCCUR.

2) When thunderstorms or lightning are within a 10 mile radius of the immediate area, the defueling procedure
should stop.
3) Strong wind conditions can cause a build-up of static electricity. Large charges of static electricity can develop
on support equipment while parked as a result of the movement of dust particles and air currents during strong
wind conditions. Strong wind conditions also cause the unwanted movement of items or equipment which can
hit the airplane or injure persons. Defueling procedures should stop if strong wind conditions are present.
4) If the airplane is to be completely defueled, fuel must be pumped off by jettison pumps to below jettisonable
level and by engine boost pumps to sump level. Then unusable fuel is drained through sump drain valves into
portable containers. If one or more tanks must be entered for maintenance purposes, fuel can be transferred to
other tanks, provided space is available. Remaining fuel can be drained through sump drain valves.
(a) Pump operation during defueling and fuel transfer has the potential for fuel vapors to come in contact
with an ignition source inside a fuel tank. Dry pump operation could cause a fire or an explosion (refer to
MT 28-015). To address the issue of dry pump operation, several limitations have been added to the
defuel and fuel transfer procedures.
(b) To prevent pump operation when the fuel level is below the pump inlet, you must follow these defueling
and fuel transfer procedures:

NOTE
Reference FAA AD 2002-19-52, AD 2002-24-51 and the applicable
AMOC letter.

(1)DEFUELING AND FUEL TRANSFER OPERATIONS;

You must monitor the low pressure indication light in the fuel pump switch (amber PRESS light) and
put the pump switch to the OFF position at the first indication of fuel pump low pressure.
(2)DEFUELING AND FUEL TRANSFER OPERATIONS WITH PASSENGERS ON-BOARD;
You must monitor the applicable tank fuel quantity and put the pump switch(es) to the off position at
or above these fuel quantities (approximate values):
• Center wing tank - 7000 pounds
• Main tanks - 3000 pounds
(3)Very high flow conditions can occur during defueling, fuel transfer and fuel jettison operations. The
high flow conditions can decrease the back pressure in the fueling/jettison manifold. The lack of back
pressure can reduce the output pressure of the fuel pumps to a level where the low PRESS light in
the pump switch comes on. During these high flow conditions the amber low PRESS light does not
indicate that a pump is running dry or that the pump has failed.
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• To monitor pump performance during high flow conditions, it is necessary to monitor the pump low pressure
indication and the fuel quantity indication. If the pump PRESS light comes on and stays on and the fuel
quantity does not decrease, it is possible that the pump is running dry or the pump has failed. The pump
switch must be selected off and stay off until you can evaluate and repair the cause of the no-transfer
condition.
5) Power required during defueling is 28 volts dc and 115 volts ac as supplied from P14 left main power center
and P6 circuit breaker panel, respectively. If APU or external power source is not available, power for
defueling can be obtained from the airplane battery by positioning battery switch to ON, standby power
switch to OFF, and refuel power switch to BATTERY. The following precaution must be observed if the APU
is used during defueling operations.
(a) Main tank no. 2 must contain sufficient fuel to allow continuous operation of the APU during defueling
(AMM 49-11-00/201).
6) Whenever personnel are working in the area of the wing leading edge, safety locks should be installed on all
extended leading edge flaps

WAR NI NG
REFER TO 27-81-00 MP FOR LOCK INSTALLATION PROCEDURE. FLAPS
WILL RETRACT IN 7 SECONDS. INSTALL LOCKS TO PREVENT INJURY FROM
INADVERTENT OPERATION OF FLAPS.

7) When you defuel or transfer fuel, Ensure all unnecessary support equipment and stands are away from the
airplane. During the defuel or transfer operation the change in fuel load causes the pitch and roll attitude to
change. This condition can cause the wing or fuselage to move up or down. During windy or slippery
conditions on the ramp, an aft CG condition can cause the airplane to weathervane and the nose of the
airplane to move sideways. This movement can cause the airplane to contact support equipment.
8) If it necessary to defuel within a hangar prior approval from the maintenance representative in charge of the
aircraft and from local station authorities must be obtained. Additionally, local fire department and/or vendor
requirements must be adhered to.
9) 9) If the removed fuel is intended to be reinstalled in the same aircraft or another aircraft, the following
procedures must be followed.
(a) Maintenance Control must be advised and the Maintenance Controller is responsible for authorizing
and logging in the defueling process.
(b) A dedicated truck and/or tank must be used to ensure that there is no mixing of the removed fuel with
fuel from another aircraft or the vendor's stored fuel.
(c) The truck and/or tank that are going to receive the removed fuel must be emptied of all other fuel and
have all filters replaced prior to beginning the defueling process and filling the truck/tank.
(d) Before the fuel may be supplied to the same aircraft or another aircraft, the filters on the truck or tank
must be replaced and a "white bucket" test must be accomplished as per the applicable fueling
vendor's procedures.
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2 FUEL TANK DEFUELING

2.1 General

The most rapid method of defueling is to connect defueling hoses to all four fueling receptacles and operate truck
and airplane pumps simultaneously. This procedure can be used for total defueling or partial defueling operation as
necessary.

2.2 Equipment and Materials

1) Drain Adapters
(a) Hose Adapter, Sump Drain Valve - 3MIT65B00772 (preferred)
(b) Adapter, Sump Fuel Drain Hose - SE28-1108 (optional)
2) Properly marked and approved container for fuel drained from sumps
(a) Reserve tanks - 5 gallons
(b) Outboard mains - 35 gallons
(c) Inboard mains - 25 gallons
(d) Center wing tank - 125 gallons

2.3 Fuel Pump Limitations

1) Comply with these fuel pump limitations during the defueling and fuel transfer operation:
(a) To operate any of the fuel pumps, you must be in the flight compartment to continuously monitor the low
pressure indication and the fuel quantity in the fuel tank.
(b) Immediately set the applicable fuel pump switch(es) to the off position if the amber PRESS light comes on
and stays on.

WAR NI NG
DO NOT OPERATE ANY FUEL PUMPS IF THE LOW PRESSURE LIGHT COMES
ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A
FIRE OR EXPLOSION.

(c) If the amber PRESS light in the pump switch comes on due to a reduced back-pressure condition, do
these steps:
(1)Monitor the fuel quantity for the applicable tank.
(2)Immediately set the fuel pump switch(es) to the off position if the fuel quantity for the fuel tank does not
decrease.
(d) To defuel an airplane with passengers on-board, do these steps:
(1)Use only the boost pumps to defuel the No. 2 and 3 main tanks. Do not use the main tank jettison
pumps. The fuel inlets for the main tank jettison pumps are above the 3000 pounds fuel level.
(2)Monitor the applicable tank fuel quantity.
(3)Put the pump switch(es) to the off position at or above these fuel quantities (approximate values):
a)Center wing tank - 7000 pounds
b)Main tanks - 3000 pounds
(c) To defuel main tank on airplanes without passengers on-board, do these steps:
(1)If on, set jettison pump switches to the off position when the fuel quantity in the No. 2 or 3 main tanks is
at or above 14,000 pounds.
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(2)Continue to defuel the No. 2 and 3 main tanks below the 14,000 pounds fuel level with the main 2
and 3 boost pumps.

2.4 Pressure Defueling

1) Move all unnecessary support equipment and stands away from the airplane.

Caution
MOVE ALL UNNECESSARY SUPPORT EQUIPMENT AWAY FROM THE
AIRPLANE. POSSIBLE AIRPLANE CONTACT WITH SUPPORT EQUIPMENT
CAN OCCUR. DURING THE DEFUEL OPERATION, THE CHANGE IN FUEL
LOAD CAUSES THE AIRPLANE PITCH AND ROLL ATTITUDE TO CHANGE.
THIS CONDITION CAN CAUSE THE WINGS AND FUSELAGE TO MOVE UP OR
DOWN. DURING WINDY OR SLIPPERY CONDITIONS ON THE RAMP, AN AFT
CG CONDITION CAN CAUSE THE AIRPLANE TO MOVE SIDEWAYS. THIS
MOVEMENT CAN CAUSE THE AIRPLANE TO CONTACT SUPPORT
EQUIPMENT.

2) Bond the fuel truck to the airplane.

3) Supply electrical power (AMM 24-22-00/201).

NOTE
During the defuel procedure, the APU can be started or stopped.
Comply with the APU operations during refueling and defueling pre-
cautions when starting or stopping the APU (AMM 12-11-01/301).

4) Open fueling station access doors in each wing. Open fueling control panel access door on left wing.
5) Remove fueling receptacle caps.
6) On NW ALL EXCEPT 601, lift lever in each receptacle adapter.
7) Do these steps to connect the fuel nozzles to the fueling receptacles:

WAR NI NG
ENSURE THERE IS NO TENSION ON THE HOSE DURING THE FUELING
OPERATION. THE HOSE MUST HANG FREELY FROM THE FUEL ADAPTER
WITH NO TENSION (PRELOAD) IN ANY DIRECTION. TENSION ON THE HOSE
CAN CAUSE THE HOSE TO DISCONNECT. INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT CAN OCCUR.

Caution
BEFORE DEFUEL OPERATIONS, ENSURE THE HOSE NOZZLE AND HOSE-
END CONTROL VALVE (IF USED) ARE CONFIGURED PER THE SUPPLIER'S
MAINTENANCE MANUAL. FAILURE TO DO SO COULD CAUSE DAMAGE TO
THE AIRPLANE.

(a) Ensure that the fueling receptacle is clean, not damaged and there are no fuel leaks.
(1)Ensure that the screws and lugs are not loose or damaged.
(b) Connect the fuel nozzle to the fueling receptacle.
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8) Check that manual defueling valves are closed.

9) Open fueling receptacle manual shutoff valves.
10) Press TEST GAGES switch on fueling control panel and check that fueling quantity indicators are operating
properly.
11) Monitor fueling quantity indicators to determine fuel level in each tank during entire defueling operation.
12) Check that engine fuel shutoff valves are closed.
13) Rotate reserve tank transfer valve switches to open position.
14) Position main tank transfer valve switches to OPEN.
15) Position center wing tank jettison transfer valve switches to OPEN.

WAR NI NG
DO NOT OPEN JETTISON NOZZLE VALVE DURING DEFUELING OPERATION.
FUEL SPILLAGE WILL OCCUR CAUSING A HAZARDOUS CONDITION.

16) To operate any of the fuel pumps, you must be in the flight compartment to continuously monitor the fuel
quantity and the low pressure indication in the fuel tank.

WAR NI NG
DO NOT OPERATE ANY FUEL PUMPS IF THE LOW PRESSURE LIGHT COMES
ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A
FIRE OR EXPLOSION.

WAR NI NG
COMPLY WITH FUEL PUMP LIMITATIONS DURING DEFUEL AND FUEL
TRANSFER OPERATIONS TO ENSURE THE FUEL PUMPS DO NOT RUN DRY.
FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.

(a) Immediately set the applicable fuel pump switch(es) to OFF if the low PRESS light comes on and stays
on.

NOTE
When defueling fuel with minimum back pressure to the pumps, it is
possible for the low pressure light(s) to be on. In this case, monitor the
tank quantity and put the pump switch(es) to OFF if the fuel quantity
for the tank does not decrease.

(1)If the amber low PRESS light in the pump switch comes on due to a reduced back pressure condition,
do these steps:
a)Monitor the fuel quantity for the applicable tank.
b)Immediately set the applicable fuel pump switch(es) to OFF if the fuel quantity for the fuel tank does not
decrease.
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17) To defuel an airplane with passengers on-board, do these steps:

(a) Put the center wing tank override/jettison pump switches to ON.
(b) Start the fuel truck defueling pumps.
(c) Continue to defuel until the desired quantity remains.

WAR NI NG
COMPLY WITH FUEL PUMP LIMITATIONS DURING DEFUEL AND FUEL
TRANSFER OPERATIONS TO ENSURE THE FUEL PUMPS DO NOT RUN DRY.
FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR
EXPLOSION.

(d) Monitor the center wing tank fuel quantity.

(e) Put the center wing tank override/jettison pump switches to the off position at or above a center wing
tank fuel quantity of 7000 pounds.
18) To defuel an airplane without passengers on-board, do these steps:
(a) Put the center wing tank override/jettison pump switches and main jettison pump switches to ON.
(b) Start fuel truck defueling pumps.
(c) Continue defueling until desired quantity remains.

WAR NI NG
COMPLY WITH FUEL PUMP LIMITATIONS DURING DEFUEL AND FUEL
TRANSFER OPERATIONS TO ENSURE THE FUEL PUMPS DO NOT RUN DRY.
FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR
EXPLOSION.

(d) Monitor the applicable fuel tank quantity.

(e) Put the main tank jettison pump switches to the off position when the fuel quantity in the No. 2 and 3
main tanks are at or above 14,000 pounds.
(f) Put the center wing tank override/jettison pump switches to off when the applicable warning lights
come on.
19) Position center wing tank jettison transfer valve switches to CLOSE.
20) Close main tank transfer valves.
21) Stop fuel truck defueling pumps.
22) Close fueling receptacle manual shutoff valves.
23) Open manual defueling valves.
24) Position engine crossfeed valve switches to open.
25) To operate any of the fuel pumps, you must be in the flight compartment to continuously monitor the fuel
quantity and the low pressure indication in the fuel tank.

WAR NI NG
DO NOT OPERATE ANY FUEL PUMPS IF THE LOW PRESSURE LIGHT COMES
ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A
FIRE OR EXPLOSION.
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WAR NI NG
COMPLY WITH FUEL PUMP LIMITATIONS DURING DEFUEL AND FUEL
TRANSFER OPERATIONS TO ENSURE THE FUEL PUMPS DO NOT RUN DRY.
FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.

(a) Immediately set the applicable fuel pump switch(es) to OFF if the low PRESS light comes on and stays
on.

NOTE
When defueling fuel with minimum back pressure to the pumps, it is
possible for the low pressure light(s) to be on. In this case, monitor the
tank quantity and put the pump switch(es) to OFF if the fuel quantity
for the tank does not decrease.

(1)If the amber low PRESS light in the pump switch comes on due to a reduced back pressure condition,
do these steps:
a)Monitor the fuel quantity for the applicable tank.
b)Immediately set the applicable fuel pump switch(es) to OFF if the fuel quantity for the fuel tank does not
decrease.
26) To defuel an airplane with passengers on-board, do these steps:
(a) Position all boost pump switches to ON.
(b) Position center wing tank scavenge pump switch to ON.
(c) Start fuel truck defueling pumps.
(d) Continue defueling until desired quantity remains.

WAR NI NG
COMPLY WITH FUEL PUMP LIMITATIONS DURING DEFUEL AND FUEL
TRANSFER OPERATIONS TO ENSURE THE FUEL PUMPS DO NOT RUN DRY.
FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.

(e) Monitor the main tank fuel quantities.

(f) Put the boost pump switches to off at or above a main tank fuel quantity of 3000 pounds.
(g) Put the center wing tank scavenge pump switch to OFF when the warning light comes on.
27) To defuel an airplane without passengers on-board, do these steps:
(a) Put all the boost pump switches to ON.
(b) Put the center wing tank scavenge pump switch to ON.
(c) Start the fuel truck defueling pumps.
(d) Continue defueling until desired quantity remains.
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WAR NI NG
COMPLY WITH FUEL PUMP LIMITATIONS DURING DEFUEL AND FUEL
TRANSFER OPERATIONS TO ENSURE THE FUEL PUMPS DO NOT RUN DRY.
FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR
EXPLOSION.

(e) Put each pump switch to OFF as its applicable warning light comes on.
28) Position reserve tank transfer valve switches to close.
29) Position engine crossfeed valve switches to close.
30) Stop fuel truck defueling pump(s).
31) Close manual defueling valves.
32) On ALL EXCEPT NW 601, stow lever in each receptacle adapter.

Caution
IF LEVER IS NOT STOWED AND RECEPTACLE CAP IS INSTALLED, FUEL
LEAKAGE CAN RESULT.

33) Install fueling receptacle caps and close fuel station access doors.
34) Disconnect the bonding cable between the fueling vehicle and the approved electrical grounding or bonding
connection on the airplane.
35) Drain remaining fuel from the fuel tanks.

NOTE 1
Optimum airplane attitude for draining of fuel tank sumps is 1/2 de-
gree nose down pitch and zero degree roll.

NOTE 2
The approximate quantity of fuel remaining in each sump is:
5 gallons in each reserve tank, 35 gallons in each outboard main, 25
gallons in each inboard main and 125 gallons in the center wing tank.

(a) Electrically ground all containers or any associated equipment to basic airplane structure, but not in
immediate vicinity of drainage (AMM 20-41-01/201).
(b) If not using drain tool assembly (see par. B, Equipment and Materials for effectivity), remove primary
poppet from sump drain valve (AMM 28-11-04).
(c) Place drain tool assembly hose or drain adapter hose in container and insert drain tool or screw drain
adapter into sump drain fitting as applicable.
(d) When draining is complete, remove drain tool assembly or drain adapter.
(e) If primary poppet was removed, install primary poppet in sump drain valve using new O-ring
(AMM 28-11-04).
36) Remove electrical power if no longer required (AMM 24-22-00/201).
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3 DEFUELING USING AUXILIARY DEFUELING EXTERNAL POWER CONTROL UNIT

3.1 General
1) This method of defueling is intended to be used where it is not possible to power the boost pump(s) through the
airplane electrical system.

WAR NI NG
IF PUMP INSTALLATION HAS BEEN DAMAGED, DO NOT USE PUMP TO
DEFUEL AIRPLANE.

2) Move all unnecessary support equipment and stands away from the airplane.

Caution
MOVE ALL UNNECESSARY SUPPORT EQUIPMENT AWAY FROM THE AIRPLANE
POSSIBLE AIRPLANE CONTACT WITH SUPPORT EQUIPMENT CAN OCCUR.
DURING THE DEFUEL OPERATION, THE CHANGE IN FUEL LOAD CAUSES THE
AIRPLANE PITCH AND ROLL ATTITUDE TO CHANGE. THIS CONDITION CAN
CAUSE THE WINGS AND FUSELAGE TO MOVE UP OR DOWN. DURING WINDY
OR SLIPPERY CONDITIONS ON THE RAMP. AN AFT CG CONDITION CAN CAUSE
THE AIRPLANE TO WEATHERVANE AND THE NOSE OF THE AIRPLANE TO
MOVE SIDEWAYS. THIS MOVEMENT CAN CAUSE THE AIRPLANE TO CONTACT
SUPPORT EQUIPMENT.

3.2 Equipment and Materials

Auxiliary Defueling External Power Control Unit (PCU), F70316-140. See Figure 10.1 and 10.2
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Figure 10.1 Auxiliary Defueling External Power Control Unit Setup

CENTER TANK
CONNECTIONS

DEFUELING
TRUCK AFT NO. 2
BOOST PUMP JUMPER
WIRE SYSTEM (TYPICAL)

BOOST PUMP
(TYPICAL)

DEFUELING POWER
CONTROL UNIT
F70316

POWER CART DEFUELING

TRUCK

DEFUELING POWER
CONTROL UNIT F70316

Figure 10.2 Defueling Power Control Unit Control Panel

DEFUELING POWER CONTROL UNIT

PHASE
SEQUENCE
INDICATOR
28VDC 115VAC
AVAIL AVAIL

J1 L1
MASTER POWER
CAUTION L3 L2
MAINTAIN 5 FT MASTER POWER
28VDC 115VAC ON
CLEARANCE OF S1
ENGINES AND
FUELING AREAS L4
CB2 CB1
S2

707 CENTER TANKS OVERRIDE PUMPS

707 FUEL BOOST PUMPS 727/737/747 FUEL BOOST PUMPS

A B A B

CB6 CB5 CB4 CB3

747 JETTISON
OVERRIDE PUMP
ON ON ON ON

CONTROL ON
OFF OFF OFF OFF
S6 S5 S4 S3
LOW PRESSURE WARNING LOW PRESSURE WARNING CB7
OFF
S7
LOW
PRESSURE WARNING
A B A B

L9
L8 L7 L6 L5

J3 J2
J4
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3.3 Prepare for Defueling

1) Bond the fuel truck to the airplane.
2) Check that fuel system circuit breakers on P6, P12, P14, and P15 panels are open.
3) Check that refuel valves are closed.
4) Check that engine fuel shutoff valves are closed.
5) Check that fuel jettison valves are closed.
6) Open fueling station access doors in each wing.
7) Open control panel access door in left wing.
8) Remove fueling receptacle caps.
9) Do these steps to connect the fuel nozzle to the fueling receptacle:

WAR NI NG
ENSURE THERE IS NO TENSION ON THE HOSE DURING THE FUELING
OPERATION. THE HOSE MUST HANG FREELY FROM THE FUEL ADATPER
WITH NO TENSION (PRELOAD) IN ANY DIRECTION. TENSION ON THE HOSE
CAN DAMAGE THE FUEL RECEPTACLE AND CAUSE THE HOSE TO
DISCONNECT. INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN
OCCUR.

Caution
BEFORE DEFUEL OPERATIONS, ENSURE THE HOSE NOZZLE AND HOSE-END
CONTROL VALVE (IF USED) ARE CONFIGURED PER THE SUPPLIER'S
MAINTENANCE MANUAL. FAILURE TO DO SO COULD CAUSE DAMAGE TO THE
AIRPLANE.

(a) Ensure that the fueling receptacle is clean, not damaged and there are no fuel leaks.
(1)Ensure that the screws and lugs are not loose or damaged.
(b) Connect the fuel nozzle to the fueling receptacle.
10) Prepare auxiliary defueling external power control unit (PCU).
(a) Remove cable assemblies from stowage box and place PCU on top of box so that PCU control panel is a
minimum of 30 inches above ground level. Locate within cable reach of desired boost pump.
(b) Check that all PCU circuit breakers are open and PCU pump switches are OFF.
11) Connect P1 of -4 cable assembly to J1 of PCU.
12) Connect terminal end of -4 cable assembly to ground power cart(s) AC and DC connections.

3.4 Defuel Center Wing Tank

1) Open fueling receptacle manual shutoff valves.
2) Close manual defueling valves.
3) Manually open center wing tank jettison valves.
4) Disconnect jettison override pump (M224 or M225) and pressure switches (S66 or S68) electrical connectors.
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5) Install -7 cable assembly.

(a) Connect P2 to jettison override pump (M224 or M225).
(b) Connect P3 to pressure switch (S66 or S68).
(c) Connect P2 and P3 grounds to airplane grounds.
(d) Connect P1 to J4 of PCU.
6) Close CB 1 (115 V AC) and CB 2 (28 V DC) circuit breakers on PCU.
7) Check that 28 V DC AVAIL, 115 V AC AVAIL and PH SEQ lights illuminate.
8) Depress MSTR PWR ON switch, release and check that MASTER POWER ON light illuminates.
9) Close CONTROL (CB 7) circuit breaker (PCU).
10) Position switch S7 to ON and observe that low pressure light (L9) illuminates momentarily until pump
pressure builds up.

NOTE
Fuel truck suction pump may be used to assist defueling operation.

11) Continue defueling until low pressure light (L9) illuminates. Place switch S7 to OFF and open CONTROL
(CB 7) circuit breaker.
12) ( Disconnect -7 cable assembly.
13) Close fueling receptacle manual shutoff valves.

3.5 Defuel Main and Reserve Tanks

1) Open applicable crossfeed valves.
2) Manually open reserve and main tank transfer valves.
3) Open manual defueling valve(s).
4) Disconnect applicable fuel boost pump(s) (M22, M23, M26, M27, M28, M29, M31 or M32) and pressure
switches (S62, S63, S64, S65, S69, S70, S71, or S72) electrical connectors.
5) Install -10 cable assembly.
(a) Connect P2 to applicable pressure switch.
(b) Connect P2 ground to airplane ground.
6) Install -15 cable assembly.
(a) Connect P2 to applicable boost pump.
(b) Connect P2 ground to airplane ground.
7) Install -5 cable assembly.
(a) Connect P4 and P5 connectors to P1 connector of -10 cable assembly.
(b) Connect P2 and P3 connectors to P1 connector of -15 cable assembly.
(c) Connect P1 to J2 of PCU.
8) Close CB 1 (115 V AC) and CB 2 (28 V DC) circuit breakers on PCU.
9) Check that 28 V DC AVAIL, 115 V AC AVAIL and PH SEQ lights illuminate.
10) Depress MSTR PWR ON switch, release and check that MASTER POWER ON light illuminates.
11) Close A (CB 4) and B (CB 3) circuit breakers.
12) Position switches S4 and S3 to ON and observe that low pressure lights (L5 and L6) illuminate momentarily
until pump pressure builds up.
13) Continue defueling until low pressure light (L5 or L6) illuminates. Place applicable switch (S4 or S3) to OFF
and open applicable A or B circuit breaker.
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14) Close crossfeed valves and manual defueling valves.

15) Disconnect -5, -10 and -15 cable assemblies.

3.6 Restore Airplane to Normal.

1) Depress MSTR PWR OFF switch.
2) Open CB 1 and CB 2.
3) Disconnect -4 cable assembly from ground power cart and PCU.
4) Stow cable assemblies and PCU in box.
5) Install fueling receptacle caps and close fuel station access doors.
6) Disconnect the bonding cable between the fueling vehicle and the approved electrical grounding or bonding
connection on the airplane.

4 TANK-TO-TANK FUEL TRANSFER

4.1 General
1) Tank-to-tank transfer is accomplished by following the basic procedure used for defueling and using the
components used for pressure fueling. Instead of connecting a defueling truck, the fueling receptacle caps are
left installed. The refueling manifold is pressurized by the jettison pumps and refuel valve(s) in the tank(s)
selected to receive the fuel is opened. When the jettison pumps have pumped down to the reserve level the
remaining fuel can be pumped out with boost pumps. By opening the manual defueling valves at the fueling
stations and opening the outboard fueling receptacle manual shutoff valves, fuel from the boost pumps will flow
back into the refuel manifold. Remaining fuel in the center wing tank can be removed by operating the
scavenge pump to transfer fuel into the No. 2 main tank. After all usable fuel has been pumped off, the
remaining fuel is drained through the sumps.
2) When transferring fuel from one tank to another, observe the fuel quantity limits for each tank to prevent
overfilling and spillage through the vent system.
3) When you transfer fuel from tank-to-tank, to operate any of the fuel pumps, you must be in the flight
compartment to continuously monitor the fuel quantity and the low pressure indication in the fuel tank.

WAR NI NG
DO NOT OPERATE ANY FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON
AND STAYS ON. FUEL VAPORS IN THE FUEL TANK MAY IGNITE AND CAUSE A
FIRE OR EXPLOSION.

(a) Immediately set the applicable fuel pump switch(es) to off if the low PRESS light comes on and stays on.

NOTE
When transferring fuel with minimum back pressure to the pumps, it
is possible for the low pressure light(s) to be on. In this case, monitor
the tank quantity and put the pump switch(es) to off if the fuel quantity
for the tank does not decrease.
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(1)If the amber low PRESS light in the pump switch comes on due to a reduced back pressure
condition, do these steps:
a)Monitor the fuel quantity for the applicable tank.
b)Immediately set the applicable fuel pump switch(es) to off if the fuel quantity for the fuel tank does not
decrease.
c)To do the fuel transfer on airplanes with passengers on-board, comply with these limitations:
d)Use only the boost pumps to transfer fuel from the No. 2 and 3 main tanks. Do not use the main tank
jettison pumps. The fuel inlets for the main tank jettison pumps are above the 3000 pounds fuel level.
e)Monitor the applicable tank fuel quantity.
f)Put the pump switch(es) to the off position at or above these fuel quantities (approximate values):
1.Center wing tank - 7000 pounds
2.Main tanks - 3000 pounds
g)To do the fuel transfer from the main tank on airplanes without passengers on-board, comply with these
limitations:
1.If on, set jettison pump switches to the off position when the fuel quantity in the No. 2 or 3 main tanks is
at or above 14,000 pounds.
2.Continue to defuel the No. 2 and 3 main tanks below the 14,000 pounds fuel level with the main 2 and
3 boost pumps.
4) Move all unnecessary support equipment and stands away from the airplane.

Caution
MOVE ALL UNNECESSARY SUPPORT EQUIPMENT AWAY FROM THE
AIRPLANE. POSSIBLE AIRPLANE CONTACT WITH SUPPORT EQUIPMENT
CAN OCCUR. DURING THE DEFUEL OPERATION, THE CHANGE IN FUEL
LOAD CAUSES THE AIRPLANE PITCH AND ROLL ATTITUDE TO CHANGE.
THIS CONDITION CAN CAUSE THE WINGS AND FUSELAGE TO MOVE UP OR
DOWN. DURING WINDY OR SLIPPERY CONDITIONS ON THE RAMP. AN AFT
CG CONDITION CAN CAUSE THE AIRPLANE TO WEATHERVANE AND THE
NOSE OF THE AIRPLANE TO MOVE SIDEWAYS. THIS MOVEMENT CAN
CAUSE THE AIRPLANE TO CONTACT SUPPORT EQUIPMENT.

5 LATERAL FUEL IMBALANCE

5.1 General
1) When you defuel the airplane, if all the tanks are not defueled for maintenance operations, a lateral fuel
imbalance will occur. Use the limits in this procedure to control the lateral fuel imbalance.
2) The graphs in this task are for static maintenance operations only. To taxi or tow the airplane for ground
operations, use the lateral balance limits found in the applicable weight and balance manual.

5.2 Access

Location Zones

500 Left Wing

600 Right Wing

5.3 Procedure
1) Use this procedure only for lateral imbalances caused by unsymmetrical fuel loading which can occur during
fuel system maintenance operations.
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2) You must also calculate all other lateral imbalances that occur at the same time when you calculate the lateral
balance limits for maintenance operations.
3) To find the lateral imbalance moment for a given weight of fuel in one of the tanks refer to Figure 10.3.
4) To defuel one fuel tank only, use one of these procedures:
(a) Option 1
(1)Find the gross weight of the airplane before you remove the fuel from the tank.
(2)Subtract, from the airplane gross weight, the weight of the fuel to be removed.
(3)The applicable fuel tank can be defueled if the airplane gross weight after defueling (the result from
step 2) is less than or equal to the gross weight limit shown in Table 10.1.

Table 10.1. To Defuel a Single Tank

@ MTW = lbs 613,000 713,000 738,000 753,000 778,000 803,000 808,000 816,000 823,000 836,000
TANK LIMIT A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW
TO BE lbs-in LIMIT LIMIT LIMIT LIMIT LIMIT LIMIT LIMIT LIMIT LIMIT LIMIT
DEFUELED lbs lbs lbs lbs lbs lbs lbs lbs lbs lbs
R1 OR R4 3,174,480 NONE NONE NONE NONE NONE NONE NONE NONE NONE NONE
R2 OR R3 5,516,480 NONE NONE NONE NONE NONE NONE NONE NONE NONE NONE
M1 OR M4 19,761,609 564,200 621,000 635,200 643,700 658,000 672,200 675,000 679,500 683,500 690,900
M2 OR M3 23,249,020 537,000 569,800 578,000 582,900 591,100 599,300) 600,900 603,500 605,800 610,100

Table 10.2. To Defuel all of the Tanks in One Wing

@ MTW =lbs 613,000 713,000 738,000 753,000 778,000 803,000 808,000 816,000 823,000 836,000
A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW A/P GW
LIMIT lbs LIMIT lbs LIMIT lbs LIMIT lbs LIMIT lbs LIMIT lbs LIMIT lbs LIMIT lbs LIMIT lbs LIMIT lbs
537,000 569,800 578,000 582,900 591,100 599,300 600,900 603,500 605,800 610,100

(b) Option 2
(1)Find the maximum taxi weight (MTW) of the airplane from the weight and balance manual.
(2)Find the lateral imbalance moment (LIM) from Figure 10.3.
(3)With the LIM from the step before use this equation to calculate the maximum gross weight (GW) in lbs
after defueling:

+ (LIM-13,500,000 LB-IN) x (500,000 LB - MTW)

(14,500,000 LB-IN)
(4)The applicable tank can be defueled if the airplanes gross weight after defueling is less than or equal to
the calculated maximum gross weight (GW).
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5) To defuel all the fuel tanks in one wing, use one of these procedures:
(a) Option 1:
(1)Find the maximum taxi weight of the airplane from the weight and balance manual.
(2)Find the gross weight of the airplane with no fuel.
(3)Add 97,859 pounds to the gross weight found in the previous step.
(4)If the weight you calculated in the previous step is less than or equal to the gross weight limit shown
in Table 10.2, do the subsequent steps to defuel the airplane.

NOTE
For intermediate maximum taxi weights, use the lower limit values.

(5)Defuel the reserve tank(s).

(6)Defuel the inboard and outboard main tanks on the applicable side until they are empty, while you
defuel the opposite outboard main tank until it contains only 8,782 pounds .
(b) Option 2
(1)Use Figure 10.3 to find the total lateral imbalance moment (LIM) of all the fuel remaining in the
opposite wing.

NOTE
The total LIM must be less than 28,000,000 lb-in (3163552 Nm).

(2)From the TOTAL LIM, calculate the limit gross weight in lbs (GW) with this equation:

T W + (TOTAL LIM-13,500,000 LB-IN) x (500,000 LB - MTW)

(14,500,000 LB-IN)
(3)The applicable wing can be defueled if the airplane gross weight after defueling is less than or equal
to the limit gross weight (GW).
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Figure 10.3 Lateral Imbalance

25

89077
23.2

20 31822
19.7
IMBALANCE X 1000000 IN-LB

4
15 3

10 1 Reserves 1 or 4
2 Reserves 2 or 3
3 Mains 1 or 4
4 Mains 2 or 3

5595
5.5
5
2
3791
3.3
1

0
0 10000 20000 30000 40000 50000 60000 70000 80000 90000

FUEL IN TANK IN POUNDS 1

1 THIS GRAPH GIVES GENERAL LATERAL IMBALANCE LIMITS FOR

STATIC MAINTENANCE OPERATIONS ONLY. FOR FLIGHT OPERATIONS
AND MORE DATA ON GROUND MAINTENANCE OPERATIONS, REFER TO
THE WEIGHT AND BALANCE MANUAL.
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CHAPTER 11 TOC Chapter 11 TOC

CHAPTER 11 - HANDLING FUEL SPILLS ..................................................................................................... 11.1

1. FUEL SPILLAGE SAFETY PRECAUTIONS ................................................................................................................. 11.1
2. FUEL SPILL DEFINITIONS ........................................................................................................................................... 11.1
3. FUELS SPILLS WHILE FUELING AIRCRAFT .............................................................................................................. 11.2
3.1 Notification of Authorities - General ............................................................................................................... 11.2
3.2 Fueler Fuel Spill Procedures .......................................................................................................................... 11.2
3.3 Ramp Employees Fuel Spill Procedures ........................................................................................................ 11.2
4. FUEL SPILLS IN HANGAR ........................................................................................................................................... 11.3
4.1 Small Spills ..................................................................................................................................................... 11.3
4.2 Intermediate Spills .......................................................................................................................................... 11.3
4.3 Flood Spills ..................................................................................................................................................... 11.4
5. CLEAN-UP, DISPOSAL, FOLLOW UP - GENERAL ..................................................................................................... 11.4

00
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Chapter 11 CHAPTER 11 - HANDLING FUEL SPILLS

The purpose of this standard is to establish minimum safety, health, fire protection and environmental requirements in
the event of a fuel or chemical spill. Each station must be prepared to respond to more stringent local rules and
regulations. Ensure compliance with current codes when taking clean up or disposal actions. Stations should make
prior arrangements with airport authorities, fire department, and/or their local fuel vendor to handle spill response/
cleanup and disposal.

1 FUEL SPILLAGE SAFETY PRECAUTIONS

Many dangers exist when fuel is spilled or allowed to drip without adequate safety measures taken. Some of the more
dangerous properties of raw fuel and fuel vapors are as follows:
1) Fuel vapor is three to four times heavier than air, and will settle in the lowest areas. Equipment dragged across
a cement floor can easily give off enough of a spark to ignite a low lying vapor, even though the air above it
may seem relatively clear.
2) It takes about 1% of fuel vapor in the air to make conditions right for explosion or fire.
3) Fuel will, under certain conditions, burn with such rapidity as to constitute an explosion.
Fuel vapors can be ignited by heat, fire, electrically or mechanically produced sparks, friction, or static electricity.
Fuel vapor has a tendency to drift; therefore, the same precautions apply in the areas where vapors drift as do in the
immediate spillage area.
It is the responsibility of the authorized Supervisor in the area, or on the aircraft involved, to proceed with the safety
precautions outlined in this publication. The Supervisor will apply all precautions possible until spillage is cleared, or
until the Airport Fire Department relieves the supervisor of this responsibility.

2 FUEL SPILL DEFINITIONS

• Absorbed compound - Speedi-dri or approved equivalent. If not available, sand may be used.
• SMALL spill - an amount easily and quickly covered with absorbent compound.
• INTERMEDIATE spill - a continuous dripping for a short period of time (such as a loose fuel line in the fuselage
or wings, with the fuel dripping onto the ground).
• FLOOD spill - a large quantity spread over the ground to the extent that it could not be covered or controlled
with absorbent compound.
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3 FUELS SPILLS WHILE FUELING AIRCRAFT

3.1 Notification of Authorities - General

Fuel spills and/or chemical spills require notification of various governmental authorities. Various types of liquids
have different (RQ) reportable quantities which trip the reporting requirements. It is Avatar Airlines's responsibility to
ensure that the following calls are made by the Operations Manager, PIC or authorized individual or its contractor
handling the incident. Personnel should follow the following Spill Notification Guidelines:
1) Airport Fire Department - Call the Airport Fire Department immediately for:
• Spills: which present a fire hazard
• Spills: over 10 feet in any direction
• Spills: over 50 square feet in area
• A continuous spill
• A spill into a sewer, water body or soil

NOTE
The Local Airport Fire Department will evaluate the need to mobilize
Fire Equipment .

2) Avatar Airlines Operations Control Center (OCC) - Immediate notification to the OCC and Director of Ground
Operations are required for all fuel spills.
a) Written reports are required to be reported to the Director of Ground Operations for any spill that
reaches a sewer, water body or soil. The Director of Ground Operations will forward copies of all
reports to the Director of Operational Safety (DOS).
b) State and Federal Spill Reporting - will be conducted by the Director of Operational Safety (DOS).
c) Emergency Response Contractors - the Director of Ground Operations will assist local Station
d) Managers coordinating the services of spill response contractors.
e) Company Maintenance Control - Notify Maintenance Control of the fuel spill.

3.2 Fueler Fuel Spill Procedures

• Immediately cut off the spill source.
• Cease fueling, let go of deadman switch.
• Activate any emergency fuel shut off equipment to stop the flow.
• Notify the Operations Manager, PIC or authorized individual as required if they are present.
• Contain the spill by covering with speedy-dry or building dams. Every attempt must be made to prevent
the fuel from getting into a drain or on the soil.

3.3 Ramp Employees Fuel Spill Procedures

• Assist in directing traffic away from spill.
• Assist in contacting local or airport fire department and supervisor.
• Check vehicles in the immediate area to see that they are not running.
• Assist by rerouting any non-essential traffic.
• Assist by spreading speedy-dry, etc. to prevent spill from entering drain or soil.

4 FUEL SPILLS IN HANGAR

• Check that no electric equipment, lights, or flashlights are switched ON or OFF in the area of spill or in the
possible path of a vapor drift.
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WAR NI NG
ELECTRICAL SWITCHES BEING TURNED ON OR OFF PRODUCE SPARKS.

• Do not drag equipment across the floor that might cause a spark.
• Position qualified personnel with fire equipment on standby, at a distance from spillage, equal to the maximum
effective range of fire equipment.
• Limit the number of personnel in the vicinity of the spill to the minimum required to handle the emergency. Keep
all personnel on upwind (wind to back) side of spill.
• Do not start any automotive equipment in the vicinity of the spill, or in the possible path of a vapor drift.
• Whenever possible, turn off floor power before a possible vapor drift reaches switches.
• Stop all automotive equipment from entering the hangar area.
• Set up additional fire fighting equipment. Position a Foamite and/or dry chemical cylinder within effective range.
• Whenever possible, dam off drain openings, using sand bags or absorbent compound.

4.1 Small Spills

• Apply absorbent compound over the entire spill as quickly as possible.
• After complete absorption of the fuel by the absorbent compound, sweep up and remove.

WAR NI NG
DO NOT FLUSH FUEL OR ABSORBENT COMPOUND DOWN SEWER DRAIN.

• Place used absorbent compound in a container and place outside of the hangar.

4.2 Intermediate Spills

• Notify Maintenance Representative or the Representative's designee.
• Accomplish SPILLAGE IN HANGAR procedure as detailed previously.
• Set up safety containers to catch fuel dripping from aircraft. Do not drag containers.

WAR NI NG
DO NOT FLUSH FUEL OR ABSORBENT COMPOUND INTO SEWER DRAIN
OPENINGS.

Cover any spillage on hangar floor with absorbent compound.

• Extend full cooperation to Airport Fire Department. On their arrival they will assume full command.
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4.3 Flood Spills

• Accomplish intermediate spill precautions as detailed above.
• Clear the entire area of personnel not needed to aid in the emergency.
When it appears that Airport Fire Department will not arrive within a period of 15 to 20 minutes, the Individual in
charge will evaluate the situation and, if necessary, proceed as follows:
1) With Foamite or dry chemical fire fighting equipment (wheeled) at least 75 feet away from the edge of the
spill, build up agent around the outer edges of spill, then gradually roll agent over the spill until it is entirely
covered.
2) Do not attempt to clean up agent until Airport Fire Department arrives. Then clean up only as directed.

WAR NI NG
DO NOT EXPOSE PERSONNEL TO HAZARDOUS CONDITIONS.

5 CLEAN-UP, DISPOSAL, FOLLOW UP - GENERAL

• Advance consideration should be given to recovery of as much free liquid as possible, rather than generating
a volume of solid waste from speedy-dry. Solid wastes generally translate into increased disposal costs and
liability.
• Place recovered spoils in an appropriately labeled container and store in a specially authorized storage area
for final disposal off-site. Dispose of material in accordance with state and federal guidelines. Avatar Airlines
fuel contractors should be able to assist or handle this procedure. Local airport authorities may have specific
procedures.
• Inspect impacted aircraft to assure no fuel or fuel vapors have accumulated in any interior areas.
Decontaminate any impacted items and/or areas.
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APPENDIX A - FUEL DISTRIBUTION TABLES 747-400 Appendix A

1. MEASURING STICK SLOPE ADJUSTMENTS

The measuring stick values published in this appendix are based on the airplane being parked with the wings level
(0.0° Roll) with a typical -0.5° (nose down) pitch attitude. The published values are only accurate for those conditions
and not valid for other airplane conditions.

Due to variances in ramp conditions and airplane loading, it may be difficult to attain those exact conditions. The
following correction charts are provided to allow use of the measuring sticks under various airplane parking conditions.

Correction charts are only available for the Main tanks and the Center Wing tank.

NOTE
A certain degree of error is introduced when using the correction
charts provided below. A secondary method of verification should be
used when determining fuel tank levels when outside of the baseline
parameters (0.0° Roll/-0.50 Pitch). A comparison of the affected
tank's corrected stick value with the indicated quantities and the cor-
rected stick values of the other main tanks can be used to validate the
corrected stick value.

MAIN TANKS 2 and 3

MAIN TANKS 1 and 4
STICK 17 Low Wing Level High Wing
STICK 21 Low Wing Level High Wing -2.0° -1.0° 0.0° +1.0° +2.0°
-2.0° -1.0° 0.0° +1.0° +2.0° +1.5° -2.0“ -1.0“ 0 +0.8“ +1.6“
Nose
Nose +1.5° -0.7“ -0.6“ 0 +0.4“ +0.7“
UP +0.5° -1.8“ -0.9“ 0 +0.7“ +1.5“
UP +0.5° -0.8“ -0.4“ 0 +0.4“ -0.2“
Nose -0.5° 0 0 0 0 0
Nose -0.5° 0 0 0 0 0
DOWN -1.5° -1.6“ -0.8“ 0 +0.7“ +1.7“
DOWN -1.5° -0.3“ -0.1“ 0 -0.6“ -1.3“

STICK 18 Low Wing Level High Wing

STICK 22 Low Wing Level High Wing -2.0° -1.0° 0.0° +1.0° +2.0°
-2.0° -1.0° 0.0° +1.0° +2.0° +1.5° +1.5“ +0.6“ 0 -0.7“ -1.4“
Nose
Nose +1.5° +2.8“ +1.4“ 0 -1.3“ -2.3“
UP +0.5° +1.1“ +0.6“ 0 -0.8“ -1.7“
UP +0.5° +2.6“ +0.9“ 0 -1.0“ -2.0“
Nose -0.5° 0 0 0 0 0
Nose -0.5° 0 0 0 0 0
DOWN -1.5° +1.6“ +0.9“ 0 -1.0“ -1.9“
DOWN -1.5° +2.4“ +1.0“ 0 -0.9“ -1.2“

STICK 19 Low Wing Level High Wing

-2.0° -1.0° 0.0° +1.0° +2.0°
Nose +1.5° +4.7“ +2.3“ 0 -2.0“ -3.6“
UP +0.5° +4.3“ +2.0“ 0 -1.7“ -2.9“
Nose -0.5° 0 0 0 0 0
DOWN -1.5° +2.9“ +1.4“ 0 -1.1“ -1.9“

CENTER WING TANK

STICK 24 Low Wing Level High Wing
-2.0° -1.0° 0.0° +1.0° +2.0°
Nose +1.5° +4.0“ +2.0“ 0 -2.0“ -2.0“
UP +0.5° +4.0“ +2.0“ 0 -2.0“ -3.8“
Nose -0.5° 0 0 0 0 0
DOWN -1.5° +4.0“ +2.0“ 0 -1.9“ +4.0“
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6.1 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.3
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6.1 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.4
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6.1 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.5
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6.1 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.6
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6.2 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.7
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01-Apr-2021

6.2 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.8
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A

01-Apr-2021

6.2 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.9
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6.2 lb / gal (pg 4 of 4)

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6.3 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.11
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01-Apr-2021

6.3 lb / gal (pg 2 of 4)

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01-Apr-2021

6.3 lb / gal (pg 3 of 4)

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APPENDIX A - FUEL DISTRIBUTION TABLES 747-400
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6.3 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.14
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01-Apr-2021

6.4 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.15
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01-Apr-2021

6.4 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.16
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01-Apr-2021

6.4 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.17
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01-Apr-2021

6.4 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.18
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6.5 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.19
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01-Apr-2021

6.5 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.20
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6.5 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.21
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01-Apr-2021

6.5 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.22
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01-Apr-2021

6.6 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.23
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A

01-Apr-2021

6.6 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.24
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A

01-Apr-2021

6.6 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.25
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01-Apr-2021

6.6 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.26
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6.7 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.27
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A

01-Apr-2021

6.7 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.28
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01-Apr-2021

6.7 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.29
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01-Apr-2021

6.7 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.30
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01-Apr-2021

6.8 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.31
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A

01-Apr-2021

6.8 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.32
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A

01-Apr-2021

6.8 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.33
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A

01-Apr-2021

6.8 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.34
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01-Apr-2021

6.9 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.35
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01-Apr-2021

6.9 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.36
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6.9 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.37
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01-Apr-2021

6.9 lb / gal (pg 4 of 4)

 FUELING AND SERVICING MANUAL A.38
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01-Apr-2021

7.0 lb / gal (pg 1 of 4)

 FUELING AND SERVICING MANUAL A.39
APPENDIX A - FUEL DISTRIBUTION TABLES 747-400 Revision: A
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A

01-Apr-2021

7.0 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.40
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01-Apr-2021

7.0 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.41
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01-Apr-2021

7.0 lb / gal (pg 4 of 4)

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01-Apr-2021

7.1 lb / gal (pg 1 of 4)

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01-Apr-2021

7.1 lb / gal (pg 2 of 4)

 FUELING AND SERVICING MANUAL A.44
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01-Apr-2021

7.1 lb / gal (pg 3 of 4)

 FUELING AND SERVICING MANUAL A.45
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7.1 lb / gal (pg 4 of 4)

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INDEX OF REFERENCES Revision: A
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INDEX OF REFERENCES INDEX OF REFERENCES

CFR- Title Chapter/Section

121.105 - Contract Fueling .....................................................................................................................Chap 1 - Sec 2
121.105 - Safe, Reliable and Efficient Fueling of Aircraft .......................................................................Chap 1 - Sec 1
121.123 - Safe, Reliable and Efficient Fueling of Aircraft .......................................................................Chap 1 - Sec 1
121.135(b)(15) - Adverse Weather Conditions .......................................................................................Chap 3 - Sec 7
121.135(b)(17) - Preparation for Pressure Fueling .................................................................................Chap 5 - Sec 1
121.135(b)(19) - Aircraft Fueling Methods ..............................................................................................Chap 4 - Sec 1
121.135(b)(19) - Contaminated Fuel ......................................................................................................Chap 9 - Sec 7
121.135(b)(19) - Fuel Standards ............................................................................................................Chap 9 - Sec 1
121.135(b)(19) - Fuel Vapor ...................................................................................................................Chap 3 - Sec 5
121.135(b)(19) - Fueling With One Engine Operating ............................................................................Chap 4 - Sec 8
121.135(b)(19) - Preparation for Pressure Fueling .................................................................................Chap 5 - Sec 1
121.135(b)(19) - Safe, Reliable and Efficient Fueling of Aircraft ............................................................Chap 1 - Sec 1
121.135(b)(19) - Static Electricity ...........................................................................................................Chap 3 - Sec 3
121.135(b)(19) - Testing for Water in Fuel Storage Facilities .................................................................Chap 9 - Sec 5
AC 00-34A - Contract Fueling .................................................................................................................Chap 1 - Sec 2
AC 150/5230-4A - Contract Fueling ........................................................................................................Chap 1 - Sec 2
AC 20-125 - Contract Fueling .................................................................................................................Chap 1 - Sec 2
AD 2002-19-52 - Defueling Maintenance Practices ..............................................................................Chap 10 - Sec 1
AD 2002-24-51 - Defueling Maintenance Practices ..............................................................................Chap 10 - Sec 1
ATA Spec 103 - Contract Fueling ...........................................................................................................Chap 1 - Sec 2
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