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Fueling Manual

Manual Number: ME0018AC

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Table of contents

00.00A TITLE PAGE

00.00B REVISION HIGHLIGHTS

TOCFront Matter

Uncontrolled copy when not viewed via http://me.aa.com/manuals. Check revision date. Make sure data is current before use.

Rev.

Fueling Manual09/01/2015

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Section 00.00A - Title Page

Fueling Manual

Manual Number: ME0018AC

Maintenance Operations SupportDFW International Airport - Hangar 1

1631 W. 20th St.MD 1129

DFW Airport, Texas 75261

Copyright © (2015) All Rights Reserved

Section 00.00ATitle Page


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Section 00.00B - Revision HighlightsRevision Highlights

05/15/2018Issue Date:Rev. 33Revision Number:

Changes inserted with this revision are listed in the table below.

DescriptionSection TitleSection

Revise sub-section 15.01.1.J to clarify whenthe electronic fuel dispatch and upliftreporting system can be utilized and whetherForm 10012 or Form E117 is required. Addnew sub-section 15.01.4 to list proceduresto be followed when utilizing QTTechnologies electronic fuel dispatch anduplift reporting system.

Jet Fuel Service Forms15.01

Section 00.00BRevision Highlights


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Table of contents

01.01 MANUAL OVERVIEWGENERAL..........................................................................................................................1MANUAL OVERVIEW........................................................................................................1ELECTRONIC MANUAL DISTRIBUTION.........................................................................1ELECTRONIC MANUAL REVISION STATUS...................................................................2REVISIONS.......................................................................................................................2INTERPRETATION............................................................................................................2ORGANIZATION................................................................................................................2RESPONSIBILITY AND AUTHORITY...............................................................................3

TOCManual Overview


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Section 01.01 - Manual Overview01.01.1 General

A. The American Airlines Electronic Fueling Manual is part of the Technical Operations Manual System.It is comprised of fueling policies, procedures and regulations to ensure the safe and effectiveperformance of American Airlines aircraft. Information contained in the electronic Fueling Manualencompasses numerous industry standards to maintain compliance with local, state and federalregulations, as applicable. Industry standards referenced are the American Society for Testing andMaterials (ASTM), Energy Institute (EI), National Fire Protection Association (NFPA), Airlines forAmerica (A4A), Air Transport Association (ATA 103), International Air Transport Association (IATA)and Joint Inspection Group (JIG). Federal Regulations compliance is directed towards CFR 14, Parts121.105, 121.131, 121.133, 121.135(b)(19), 121.137 and 121.373.

01.01.2 Manual Overview

A. The Fuel Manual is divided into the following general sections and subsections.1. Manual Overview2. Safety3. Personnel Qualifications4. Fuel Quality Control Standards5. Fuel Quality Assurance Program6. Variance/Alternate Procedures7. Product Standards for Jet Fuel8. Fuel Specifications, Authorization and Procedures9. Shipment of Jet Fuel Samples10. Fueling Instructions11. Fueling and Vehicle Ramp Operations12. Fueling With Crew or Passengers Onboard13. Special Fueling Procedures14. Reporting Fuel Density15. Jet Fuel Forms16. General Fuel Storage Facility (Storage Threat Checklist)17. Aircraft Fueling Procedures Manuals18. Terms and Definitions

01.01.3 Electronic Manual Distribution

A. The Fueling Manual is available system-wide to all AA personnel and distributed electronically on theAmerican Airlines website https://aaemanuals.aviationzone.net and via PDF at https://manuals.aa.com.The Fueling Manual is also available to outside fueling contractors, and regulatory agencies, with AAapproval at https://aaemanuals.aviationzone.net and via PDF at https://manuals-ext.aa.com.NOTE : In the event internet access is compromised and access to the AA Fueling Manual is not

allowed, information can be provided via phone, by contacting Fuel Engineering or contactIOC at 817-956-8000.

B. AA approved fuel contractors must have access to the Electronic Fueling Manual to meet therequirements of CFR 14 Part 121.137. Fuel contractors shall have sufficient personnel on staff that

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possesses the knowledge, skill and capability to access the electronic manual and retrieve informationnecessary to perform assigned duties.NOTE : At International stations that do not have Electronic Fueling Manual access (for example,

computer compatibility, internet problems, etc.), it is the responsibility of the AA local stationmanagement to provide the fueling vendor(s) access to the AA Electronic Fueling Manual.

C. It is the responsibility of local station management, with the assistance of the manager of aircraftmaintenance for that region, to notify fueling vendors in person, by e-mail, or other agreeable method,upon notification of new fueling manual revision.1. AA approved fuel contractors must have access to the Electronic Fueling Manual to meet the

requirements of CFR 14 Part 121.137. Fuel contractors shall have sufficient personnel on staffthat possesses the knowledge, skill and capability to access the electronic manual and retrieveinformation necessary to perform assigned duties.a. The accessibility of all Electronic Fueling Manual at AA stations is the responsibility of local

station management.NOTE : If the fueling vendor cannot access the AA Electronic Fueling Manual, local AA

personnel can assist allowing the fueling vendor access.

b. When there is a fuel vendor change, station management is responsible for assuring thatthe new vendor can access the American Airlines Electronic Fueling Manual prior to beginningfueling operations.

01.01.4 Electronic Manual Revision Status

A. The electronic version of the Fueling Manual is to be considered current at all times.B. The Title Page of the Fueling Manual contains the current revision number and revision date. A list

of sections changed at each revision is contained in the Highlights, immediately following the ManualRevision Checklist. Each manual section (example, Section 02.30, 08.01, etc.) indicates the date itwas last revised. A revision to any information within a section results in a date change to the entiresection, with pink text noting the information changed online and revision bars in printed and PDFversions.

C. If required, manual excerpts may be printed and are considered current as long as the user candemonstrate the content of the printed excerpt matches the online manual.

01.01.5 Revisions

A. Requests for revisions to the content of this manual shall be submitted per the manual revision processin the M&E Administrative Manual (MEAM) Section 03.06.

01.01.6 Interpretation

A. Interpretation of the words shall, must, will, should, and may, as used in this manual, is to be as follows:1. Shall,must, and will are directive in nature and mean that the action described is mandatory and

that there is no flexibility, unless authorized by Fuel Engineering.2. Should and may are guiding in nature and indicate actions that are desirable and permissible,

but are not mandatory. Some flexibility is allowed.

01.01.7 Organization

A. Fuel Engineering, a subdivision of Maintenance Operations Support (MOS), is responsible for thetechnical accuracy, content, and procedural applicability of the Fueling.



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B. The Director, Component, APU & MOS Engineering directs and controls the activities in the FuelEngineering Department through the Senior Manager Maintenance Operations Support and the FuelEngineering specialists under his/her direction.

01.01.8 Responsibility and Authority

A. Managing Director, Corporate Safety, Employee Safety, Fueling and Deicing1. Ensures overall effectiveness of the AA Fuel Program2. Oversees coordination among all interfacing workgroups3. Monitors accountability of all workgroups to the compliance with procedures

B. Director, Component, APU and MOS Engineering1. Responsible for the overall content and quality of the AA Fuel Manual and has the authority to

approve changes2. Ensures the AA Fuel Manual has been developed andmaintained in accordance with appropriate

industry standards and regulationsC. Senior Manager, MOS Engineering or designee

1. Develops and maintains the AA Fuel Manual in accordance with appropriate industry standardsand regulations

D. Senior Manager, Fueling and Deicing or designee1. Coordinates aircraft fuel program procedures among all interfacing workgroups2. Maintains accountability of all workgroups to be in compliance with procedures

E. General Manager or designee1. Completes the quarterly Aircraft Servicing Observation Checklist2. Ensures access to the AA Fuel Manual is made available to the fuel vendor if needed3. Verifies fuel density reports are being received from the fuel vendor4. Ensures fuel vendor provides a monthly roster of personnel qualified to fuel AA aircraft

NOTE : The individuals listed above may delegate their authority in this section per the guidelinesin the AA General Manual (GM) Section 02.06.

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Table of contents

02.01 SAFETYGENERAL..........................................................................................................................1FIRE PREVENTION..........................................................................................................1FIRE EXTINGUISHERS....................................................................................................1BONDING..........................................................................................................................2SPILLS...............................................................................................................................2

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Section 02.01 - Safety02.01.1 General

A. AA accepts the recognized industry fueling standards of the Air Transport Association’s Specification103 (ATA 103) and JIG. Compliance with the requirements of either standard is acceptable. It isacknowledged that Fuel Storage and Into-Plane operators will base their operating procedures onindustry standards, or their own company standards that are based on industry standards for aviationfuel storage, handling, and dispensing.

B. If the vendor program fails to meet at least the minimum of these standards in any part, even whereaccepted by the state of operation, a Variance document may be required.

C. Turbine fuel and oil can be irritating to the eyes and skin and poisonous when taken internally. Everyeffort should be made to avoid contact with the skin or eyes and excessive breathing of vapors. (Referto SDS and Employee Safety and Health Manual (ESHM) Section 04.12 for policy and proceduresfor emergency eyewash and showers when exposed to corrosive chemicals.)

02.01.2 Fire Prevention

A. The following requirements shall apply:1. Observe local fire laws, regulations and published procedures.2. Smoking or open flames of any kind are prohibited in or near fuel storage facilities, fueling

equipment, or aircraft.3. No smoking signs shall be posted in the cabs of all fuel servicing vehicles.4. The use of camera flash or flood lights (except explosion proof types) are not permitted in the

immediate vicinity of fuel servicing operations or flammable liquid spills.5. Bonding operations shall be conducted in accordance with this manual.6. Fuel leaks associated with fueling facilities or equipment must be corrected immediately.7. Fueling or defueling shall be discontinued during severe electrical storms in accordance with

local station procedures.8. Position the fueling vehicle so that it may be rapidly driven or towed away from the aircraft in the

event of an emergency.9. Fueling or defueling should be performed outside of hangars or enclosed buildings.

02.01.3 Fire Extinguishers

A. Fire extinguisher requirements for the protection of fueling equipment and fuel servicing operationsare given below:

B. Aircraft Fuel Servicing Vehicles1. Hydrant Carts: 1, 9kg, (20 lbs.) BC Fire Extinguisher for Aircraft Fuel Servicing vehicles.

NOTE : Hydrant carts outside of United States require 2, 9kg, (20 lbs.) BC fire extinguishers.

2. Tankers: 2, 9kg, (20 lbs.) BC Fire Extinguishers for Aircraft Fuel Servicing vehicles.C. Aircraft Fuel Servicing (Fueling and Defueling) and Storage Facilities

NOTE : Depending on the requirements of the local authority having jurisdiction, where fuelingoperations take place, the local fire marshal/chief will have the final authority to determinethe amount and size of fire extinguishers necessary to be placed on the ramp/apron.

1. Requirements for extinguishing equipment at airports and facilities is in accordance with localrequirements and/or accepted industry standards or practices including:a. Air Transport Association (ATA) 103

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b. Joint Inspection Group (JIG)c. National Fire Protection Association (NFPA)

02.01.4 Bonding

A. During aircraft fuel servicing operations, there may be several possible sources of static electricity.1. The aircraft may be charged, the fuel passing through the hose may generate static electricity,

and/or the fuel servicing truckmay also be charged. The presence of flammable vapors and staticelectricity creates a fire hazard. Similar hazards also exist when draining flammable liquids. Safetyfrom fires caused by static charge ignition is dependent upon maintaining a constant electricalpotential at any point in the system.

NOTE : Aircraft fuel servicing is considered the transfer of fuel into or from an aircraft.

B. Bonding is defined as the electrical circuit connection made between two units of equipment, thepurpose of which is to minimize the electrical potential difference between them.

02.01.4.1 Bonding ProceduresA. Prior to making any fueling connection to the aircraft, the fueling equipment shall be bonded to the

aircraft by use of a bonding cable, thus providing a conductive path to equalize potential between thefueling equipment and aircraft. The bond shall be maintained until fueling connections have beenremoved, thus permitting the reuniting of separated charges that could be generated during the fuelingoperation.NOTE : When a hydrant servicer or cart is used for fueling, the hydrant coupler/hose shall be

connected to the hydrant system prior to bonding the fueling equipment to the aircraft.1.

2. Bonding and fueling equipment shall be disconnected in the reverse order of connection.3. When more than one truck is used in fueling an aircraft, each operator shall be

responsible for his/her own bonding procedure.4. 2015SW210132When using an aircraft fueling stand, AA does not require the aircraft

fueling equipment to be bonded to the fueling stand or require the fueling stand to bebonded to the aircraft.

CAUTION: BONDING CLAMPS MUST NEVER BE ATTACHED TO ANY PARTS OF ANAIRCRAFT, EXCEPT TO THE BONDING POINTS PROVIDED. USING THEBONDING POINTS PREVENTS SCRATCHING OF THE HIGHLY STRESSEDCOMPONENTS OF THE LANDING GEAR (WHICH CAN CAUSE LANDING GEARFAILURE, AND DAMAGE TO OTHER AIRCRAFT PARTS).

B. Refer to each fleet section for the location of the bonding points.

02.01.5 Spills

A. A serious hazard in ground operations is fire from spillage of aircraft fuel.B. Every effort should be given to preventing spills of aircraft fuel.C. Spills from hose breakage, leakage, and other fueling equipment failure, can be reduced by daily

inspections and preventive maintenance as outlined in this manual.D. Each spill must be considered on an individual basis due to such variables as weather, equipment

arrangement, passenger safety, availability of personnel, and equipment. Proper communication isvital when a spill or a fire occurs.

E. Immediate notification is required for any spill of a serious, or potentially hazardous, nature. Refer tothe AA Environmental Management Manual, Chapter 3 - "Spill Response," and the Spill ResponseGuide (Appendix D) for appropriate fuel spill notification and cleanup requirements.

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02.01.5.1 Fuel Spill ProceduresA. Exposure to fuel any part of the aircraft surfaces and/or within structure can be damaging:

1. Based on the extent and nature of the spill, the decision will be made by Local Management toclean the aircraft using the fleet specified wash Job Cards.

2. Fuel softens rubber, therefore, if tires are exposed or standing in fuel refer to General ProceduresManual (GPM) for required checks and procedures.

B. Spillage from Aircraft Fuel Tank Vents1. If a fuel spill occurs during normal fueling operations, it may indicate a failure or malfunction of a

component of the fuel system. STOP FUELING AND NOTIFY AIRCRAFT MAINTENANCE INPERSON IMMEDIATELY.

END

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Table of contents

03.01 PERSONNEL QUALIFICATIONSGENERAL..........................................................................................................................1TRAINING..........................................................................................................................1

TOCPersonnel Qualifications


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Section 03.01 - Personnel Qualifications03.01.1 General

A. Vendor personnel performing into plane fueling/defueling procedures must be fully trained and ableto read, write and speak English, or the station must ensure that there is an American Airlines (AA)or contract representative available for language interpretations.

B. Fueling vehicles servicing American Airlines must be operated in accordance with the requirementsof this manual.

C. Only AA Flight Crew Members or trained and authorized AA/Contract Maintenance personnel shallobserve and perform necessary aircraft cockpit procedures during fueling and defueling operations.

D. All references to Form 802 in this section shall imply "Form 802 or equivalent."

03.01.2 Training

A. The following criteria establish the qualifications which apply to American Airlines Aircraft Maintenanceor Contract Maintenance personnel:1. Aircraft Maintenance Technicians (AMTs) involved in the fueling/defueling process, including

INOP Gauge procedures, for AA must be maintenance qualified for the fleet type being serviced.NOTE : AA Maintenance or Contract Maintenance personnel are exempt from the annual

proficiency requirement.

NOTE : Contract Maintenance is defined as vendor personnel who do regularly scheduledmaintenance, for example, ETOPS/Daily/Service checks, etc. on AA aircraft and arenot under the direct supervision of Maintenance Operations Control (MOC). Othermaintenance entities, for example, On-call Maintenance, that do regular fueling/defuelingprocedures in conjunction with or apart from fueling vendor personnel must meet thetraining criteria outlined below.

NOTE : On-call Maintenance vendors who can be contracted with AA for as needed or ad hocmaintenance duties under the direct supervision of Maintenance Operations Control(MOC) who do not perform regular fueling/defueling procedures in conjunction withfueling vendor personnel can be used to assist the fueling vendor as needed throughcoordination with MOC including INOP gauge procedures and are exempt from thetraining requirements outlined below.

B. The following criteria establish the qualifications which apply to fueling vendor personnel performinginto plane fueling/defueling procedures. The AA Station Manager shall ensure that the vendor conformsto these requirements.1. Vendors performing into plane fueling/defueling procedures must be fully trained by a qualified

and authorized representative of the AA Maintenance Training Department or their appointeddesignee, for example, vendor designated trainer.a. Training courses (initial and proficiency) shall be authorized by AA Maintenance Training,

be fleet specific and have a specific course number assigned. Refer to Table 03.01-1.b. After training, each prospective fueler must be checked by a person designated by American

Airlines Maintenance Training to assure the proficiency of vendor personnel performing intoplane fueling/defueling procedures. This check must be made by an experienced instructoror training designee.NOTE : Vendor personnel annual proficiency requirement may be accomplished on other

airlines aircraft, providing the aircraft used is the same fleet type AA flies.

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c. A monthly roster shall be provided to the AA General Manager or designee by the vendorwho performs normal or alternate fueling procedures identifying all vendor personnel whoare current in fueling procedures for AA. The list will include (refer to Figure 03.01-1):NOTE : Themonthly qualification roster is not applicable at stations where AAMaintenance

or Contract Line Maintenance personnel perform all fuel servicing functions, forexample, fuel panel operation, completion of the fuel slip, inoperative gaugeprocedures, etc., as specific fuel servicing training is not required. If a fuel, groundhandling, or on-call maintenance vendor performs fueling services, in whole or inpart, that require specific training as outlined in this section, the monthly qualificationroster policy applies.

(1) The name and employee number of each qualified vendor employee(2) The aircraft type they are qualified/current on(3) If they are INOP gauge qualified by aircraft type

d. Vendor personnel trained and qualified in Inoperative Fuel Gauges Procedures can performsaid procedures with oversight from Inoperative trained and qualified DesignatedTrainers/Supervisors/Leads. If there is no Designee/Supervisor/Lead available the Inoperativeprocedures must be performed by Maintenance.(1) Training courses given to vendor designated trainers by AA Maintenance Training shall

be documented on Form 802 and copies maintained in the vendor's local training file.Refer to Figure 03.01-1.NOTE : Personnel receiving training prior to January 1, 2004 may not have a Form

802 on record. Record of training may only exist in LMS and is to beconsidered adequate for verification and reference. If no LMS record or Form802 exists, employee must be retrained by an authorized designee.

NOTE : References to the AA Form 802 shall be inclusive of all revisions.

NOTE : Initial and recurrent training records, paper or electronic from US Airways, willsuffice as applicable documentation for training verification and referenceuntil superseded.

a) Only appointed vendor training designees are required to be tracked in LMS.b) AA appointed vendor training designees shall be trained by fleet type, and are then

authorized to train other vendor personnel to fuel/defuel AA aircraft, including newhires, transfers and personnel who may be assigned to service AA aircraft.NOTE : Designees are not authorized to train/qualify another designee.

c) Training courses given to vendor refuel/defuel personnel by vendor designatedtrainers are documented on Form 802 and maintained in the vendor's local trainingfile.

(2) AAMaintenance Training Instructor, upon completion of vendor designee training, shall:a) Retain the original Form 802 for entry into LMS.b) Coordinate with the vendor to update the station roster provided to the AA General

Manager monthly. Refer to Section 03.01.2.c) Provide vendor training designee(s) with a copy of the original AA Form(s) 802 to

be retained in the local training file of the vendor for future verification and reference.(3) Vendor training designee(s), upon completion of training to refueling/defueling personnel

to service AA aircraft, shall:a) Update the station roster provided to the AA General Manager monthly.



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b) Make sure a copy of the initial training Form 802 is completed and retained in thelocal training file of the vendor for future verification and reference.NOTE : Form 802 is legibly completed in its entirety. Each training session is

documented on a new Form 802. Revising or updating a previouslycompleted Form 802, for example, adding a trainee name(s), coursenumber, etc., is not permitted.

(4) Vendor training designee(s)and/or fueling/maintenance management/supervisors willmake sure their respective personnel remain qualified to perform services on AA aircraftincluding recurrent proficiency training. Vendor training designee(s) administer a verifiableproficiency review annually for each fueler. This review consists of observing jobperformance, for example normal/abnormal fueling, defueling, INOP gauge procedures(if applicable), etc., and determining whether it is up to standards. If not consideredproficient, the fueler will be retrained and re-qualified. (An example of a proficiencyreview is located in https://manuals.aa.com or https://manuals-ext.aa.com under FuelingForms. The vendor can use their company proficiency form.) Make sure a copy of theproficiency training Form 802 is retained in the local training file of the vendor for futureverification and reference.NOTE : Vendor training designee(s) are exempt from annual proficiency requirements.

Table 03.01-1: Training Courses

INOP GaugeCourse

INOPGaugeDesigneeCourse

Fuel/DefuelCourse (Initial)

Fuel/DefuelDesignee Course

Fleet

MX01871MX01909MX07307MX07313B-737

MX01872MX01910MX05030MX05031B-757

MX01873MX01911MX06160MX06161B-767

MX01874MX01912MX07708MX07715B-777

MX01875MX01913MX07811MX07812B-787

MX01892MX01916MX09080MX09081MD-80

MX01877MX01915MX08211MX08212A-319/A-320/A-321

MX01879MX01917MX03330MX03331A-330

MX01876MX01914MX04330MX04331E-190



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Figure 03.01-1: Monthly Roster

END



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Table of contents

04.01 FUEL QUALITY CONTROL STANDARDSGENERAL..........................................................................................................................1STANDARDS.....................................................................................................................2FUEL QUALITY (GENERAL GUIDELINES)......................................................................2

TOCFuel Quality Control Standards


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Section 04.01 - Fuel Quality Control Standards04.01.1 General

A. Safety is American Airlines' number one priority when dealing with aircraft fueling operations.B. The concept of safety within the context of aviation is:C. The state in which the possibility of harm to persons or of property damage is reduced to, and

maintained at or below, an acceptable level through a continuing process of hazard identification andsafety risk management.

D. The American Airlines Fuel Manual is compiled, authorized and distributed by the management ofAmerican Airlines. This manual has been prepared by American Airlines. Its intended use is to assistand convey procedural guidelines to fuel servicing personnel for American Airlines aircraft.NOTE : This document incorporates the necessary requirements of the Federal Aviation

Administration (FAA) where required together with industry Standards and best practices.

E. This manual includes instructions and information necessary to allow the personnel concerned toperform their duties and responsibilities with a high degree of safety.

F. Vendors at any station, that does not have Electronic Fueling Manual access (for example, computercompatibility, Internet problems, etc.), it is the responsibility of the AA local station management toprovide the Fueling vendor access to the AA Electronic Fueling Manual when needed

G. This manual is intended to set forth the operational fueling and procedures of American Airlines (alsoreferred to as “the company” or “the carrier”) unless an exception and or variance is documented .This manual provides guidance for company personnel, authorized representatives (also known ascontractors or vendors) in areas associated with the operation of American Airlines with aviationspecific and business standard policies, and designed to provide guidance for effectively protectingthe company, its employees, customers, assets and operations.NOTE : American Airlines will ensure each service agreement with an external ground handling

organization that performs refueling functions for the Operator includes a service levelagreement or equivalent document that specifies measurable safety and quality standardsrequired to be fulfilled by the respective external ground handling organization. At this timeit will confirm that both domestic and international service vendors have competent personnel,adequate facilities and equipment to fulfill American Airlines requirements.

NOTE : The records, equipment, and facilities of fuel storage and delivery organizations (hereinaftervendor or vendors) are available for inspections during normal working hours.

H. This manual contains instructions and information for Maintenance, Flight Operations, Stations andFueling Vendors to conduct operations in accordance with American Airlines policies, procedures,and any regulations as specified by the Administrator.

I. All fuel delivered to American Airlines aircraft must meet current ASTM D-1655 or DEF91-91specifications and must be free from water and contamination that could affect the quality of thefuel.

J. AA accepts the recognized industry fueling standards of the Air Transport Association’s Specification103 (ATA 103) and JIG. Compliance with the requirements of either standard is acceptable. It isacknowledged that Fuel Storage and Into-Plane operators will base their operating procedures onindustry standards, or their own company standards that are based on industry standards for aviationfuel storage, handling, and dispensing.

K. If the vendor program fails to meet at least the minimum of these standards in any part, even whereaccepted by the state of operation, a Variance document may be required.

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04.01.2 Standards

A. Air Transport Association (ATA) 103B. Canadian Standards Association (CSA) B836C. Joint Inspection Group (JIG) GuidelinesD. Aviation Fuel Quality Requirements for Jointly Operated Systems (AFQRJOS)

NOTE : AFQRJOS means shared responsibility of two or more oil companies at one site.

E. Various related information was drawn from various World Standards and provided the framework forthis document, and is where necessary incorporated by reference with the standard.1. European Aviation Safety Agency (EASA/JARs)2. Federal Aviation Administration (FARs)3. Transport Canada (CARs)4. Energy Institute (EI)5. National Fire Protection Association (NFPA)

F. The Standards contained in this publication are primarily intended to:1. Ensure that the safe practices contained herein can be applicable in all areas of the world.2. Include suitable reference to environmental protection controls and facilities that are receiving

increased emphasis and regulation in most regions.

04.01.3 Fuel Quality (General Guidelines)

A. If visible contamination is found, fueling must be discontinued from that source and the airline notified.Fueling shall not be resumed from the system until the source of contamination is found and removed.

B. If for any reason a fueling system becomes inoperable so as to impair the airlines operations, theairline must be notified.

C. All inspections and tests specified in this document shall be performed by qualified personnel employedby the vendor or a qualified independent agency under contract to the vendor.1. Storage facility personnel are considered qualified if they have been trained to perform their duties

and responsibilities, and are proficient in performing these tasks, exhibiting a high degree ofknowledge and safety.

2. The vendor shall be responsible for training fuel storage facility personnel to receive, store, performquality tests and dispense fuel in keeping with the guidelines and procedures contained in thismanual, as well as industry guidelines and practices.

3. The vendor is responsible for assuring that all fuel-handling personnel employed are properlytrained. Written records of all employees’ training shall be maintained on file.

D. Fuel which is removed from an aircraft because of possible contamination shall be held in quarantineuntil laboratory tests have been performed to determine its acceptability.

E. Product defueled from an aircraft for purposes other than contamination should be returned to theairline from which it was removed. Defueled product may not be delivered to another company’saircraft without its approval. Defueling aircraft directly into joint use fueling systems is not authorizedunless all system users have unanimously approved a procedure.

F. Sumped fuel shall not be used for aviation purposes unless the storage facility is equipped with areclaim system in accordance with ATA 103 or JIG 2 standards or equivalent. If the facility does nothave a reclaim system, the vendor shall dispose of sump fuel in accordance with applicable localregulation.

END

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Table of contents

05.01 QUALITY ASSURANCE PROGRAMGENERAL..........................................................................................................................1

TOCQuality Assurance Program


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Section 05.01 - Quality Assurance Program05.01.1 General

A. Fuel vendors’ programs, adherence to those programs and compliance with the AA program will bevalidated through preliminary and risk-based audits as well as periodic observations conducted byAA personnel. The initial and risk-based audits will be conducted by Quality Assurance personnel inaccordance with the Quality Assurance Procedures Manual, Chapter 4 and Chapter 5. Periodicobservations will be managed by the General Manager or the highest ranking AA representative ateach station who is responsible for assuring that the Aircraft Servicing Oversight Checklist is performedat least once each calendar quarter. The checklist can be accessed through a link under the AmericanAirlines Manual Collection - Procedures Manuals website at https://manuals.aa.com orhttps://manuals-ext.aa.com.NOTE : Seasonal, new and/or temporary operation stations are not exempt from the quarterly

observation requirements, and will perform an observation at least once each calendarquarter during the operational season. If operations begin in the last month of a calendarquarter, an observation is not due for that period.

B. American Airlines has joined the IATA IFQP Fuel Quality Pool. The airline will accept other IATA IFQPfuel audit reports conducted by other IATA IFQP qualified fuel auditors.

END

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Table of contents

06.01 VARIANCE/ALTERNATE PROCEDURESGENERAL..........................................................................................................................1VARIANCE REQUEST FORM...........................................................................................2VARIANCE APPROVAL LETTER......................................................................................3

TOCVariance/Alternate Procedures


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Section 06.01 - Variance/Alternate Procedures06.01.1 General

A. A Request for a Variance/Alternate Proceduresmust be submitted to the airline (Fuel Engineering/DFW)in writing.NOTE : Previously issued Fuel Waivers and AMOC’s are valid until expired.

1. The request for a Variance Figure 06.01-1 must include the pertinent details and reason why theVariance is required.

2. A Variance must be approved in writing or written by Fuel Engineering/DFWwhen applicable andshall include an expiration date.

3. If a vendor intends to comply with lesser standards than the requirements outlined in this section,a Variance must be requested from AA Fuel Engineering.

4. For additional information or clarification of current guidelines to be used, contact Fuel Engineeringin person, by e-mail, or other agreeable means.

5. Communications with regard to this document and requests for a Variance to any of its provisionsshall be addressed to or through the airline’s local General Manager. The General Manager isresponsible for internal airline company coordination with the appropriate personnel. Technicalmatters can be addressed directly to Fuel Engineering, MD1129, DFW. Refer to Figure 06.01-1for an example of the Variance Request Form.NOTE : All Variance/approval letters written by Fuel Engineering in regards to the American

Airlines Fuel Manual are considered applicable regardless of the American AirlinesFuel Manual revision. For information concerning the status of a Variance/approvalletter, you may contact Fuel Engineering, MD1129, DFW in person, by e-mail, or otheragreeable method.

B. It is required that all alternate procedures and/or Variance(s) issued to a station, which authorizevariations to the American Airlines’ Fueling Manual, be available at the affected location.

C. A master file for all current Variance(s) is maintained by Fuel Engineering, DFW. For any informationconcerning Variance(s) issued to a particular station, you may contact Fuel Engineering, MD1129,DFW in person, by e-mail, or other agreeable method.

D. Effective Variance(s) are available for electronic viewing at the following hyperlink, Fueling Variance.NOTE : Only stations with Variance(s) in effect will have folders available for viewing. If you do not

see a folder with your airport code, consider there to be no Variance(s) or alternateprocedures in effect for your station.

E. Stations should be pro-active in establishing a follow-up system for ensuring the currency andapplicability of all issued Variance(s).

Section 06.01Variance/Alternate Procedures


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06.01.2 Variance Request Form

Figure 06.01-1: Variance Request Form



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06.01.3 Variance Approval Letter

Figure 06.01-2: Variance Approval Letter

END



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Table of contents

07.01 PRODUCT STANDARDS FOR JET FUELGENERAL..........................................................................................................................1

TOCProduct Standards for Jet Fuel


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Section 07.01 - Product Standards for Jet Fuel07.01.1 General

A. Specification Requirements1. Aviation fuel specifications contain a table (or tables) of fuel property requirements, with their

minimum and/or maximum allowable values. However, in addition to the table of properties,aviation fuel specifications contain numerous requirements related to permitted materials (bothfuel components and additives), quality assurance, management of change, testing anddocumentation (traceability), and cleanliness, which are designed to ensure that fuel deliveredinto aircraft is fit-for-purpose.NOTE : A declaration of “on specification” or “meeting the specification” means meeting the

various maximum/minimum limits for fuel property tests and also satisfying all otheraspects of the specification such as material composition, approved additives, qualityassurance, management of change, cleanliness, traceability, etc.

a. Use of the following industry standards produced by the listed organizations for storage,handling, and dispensing of jet fuel into American Airlines aircraft is acceptable.(1) Air Transport Association (ATA 103)(2) Joint Inspection Group (JIG)

b. The common objective of these industry standards is to provide aviation fuel into aircraft thatis:(1) Controlled from point to point in the distribution path(2) On specification including density, conductivity and color(3) Clean and free of particulate matter(4) Free of water (dry)(5) Free of microbial growth(6) Uncontaminated by FAME (Fatty Acid Methyl Ester) compounds exceeding 50 ppm

NOTE : ASTM Standard Practice D 4306-84 latest edition, entitled "Standard Practice forSampling Aviation Fuel for Test Affected by Trace Contamination"

2. Jet fuel shall conform to ASTMD-1655, latest revision, "Standard Specification for Aviation TurbineFuels", Jet A or Jet A-1 kerosene type.

3. In all phases of fuel handling, the appearance of jet fuel shall be clear and bright (visually free ofundissolved water, sediment and suspended matter). The odor of the fuel shall not be nauseatingor irritating.

4. The color of jet fuel generally ranges from water white to light straw or amber. Other colors maybe an indication that the fuel has been contaminated by other products or unauthorized additives.In such cases, it shall be the facility operator’s responsibility to discontinue fuel transfer and/orquarantine the product until the fuel has been determined acceptable for aircraft use.

B. The following jet fuel purity and specification parameters should apply UPSTREAM of the airportreceiving filtration.

Test MethodMaximum AllowableTest Property

VisualClear and BrightAppearance

ASTM D-129837° to 51° API corrected to 60°F (15°C)API Gravity

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NOTE : It is important that the facility operator properly sample all inbound deliveries upstream of receivingfiltration for potential product (comingling) contamination, excessive water and dirt levels. Inboundjet fuel purity shall permit reasonable receiving filtration system performance and service life.Upstream appearance ratings of less than clear and bright may indicate excessive contaminationlevels which could result in shortened receiving filtration life and may increase operational costs.Unacceptable operational and economic issues based on upstream jet fuel purity levels are tobe resolved between the applicable shipper, facility operator and customer.

NOTE : The White Bucket test may be used in lieu of the Clear and Bright test where the Clear andBright test is specified. However, the Clear and Bright test may not be used in lieu of the WhiteBucket test where specified.

NOTE : If there is a sudden change in API gravity of 1 degree or more from the same source or supplier,immediate investigation is required. The vendor shall stop receipt of fuel from the source untilthe reason for the gravity change is determined.

END

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Table of contents

08.01 FUEL SPECIFICATIONS, AUTHORIZATION AND PROCEDURES (KEROSENE TYPEFUEL)GENERAL..........................................................................................................................1SPECIFICATIONS.............................................................................................................1REQUIREMENTS..............................................................................................................1SPECIAL FUELING PROCEDURES.................................................................................2

TOCFuel Specifications, Authorization and Procedures(Kerosene Type Fuel)


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Section 08.01 - Fuel Specifications, Authorization and Procedures(Kerosene Type Fuel)

08.01.1 General

A. The following specifications, requirements and quality assurance provisions are to be used for theprocurement of aviation turbine fuels (jet fuel) purchased by American Airlines and/or provided by theinto-plane fueling agent contracted by American Airlines to furnish plane side fuel delivery, to AAaircraft.

B. The seller or provider (of jet fuel) and American Airlines shall refer to this specification, or its latestrevision, in all contracts and communications regarding jet fuel specifications.

C. The seller or provider shall follow the requirements of the AA Fueling Manual. If the seller or provideris unable to meet these requirements, a request for a Variance can be requested.

08.01.2 Specifications

A. The fuel will meet or exceed the specification requirements in any one of the following documentsunless otherwise noted:1. ASTM D 1655 Jet A/A-1 Grades

NOTE : Naphthalene content shall not exceed 3.0% by volume as determined by ASTM testmethod D 1840.

2. IATA Guidance Material for Aviation Turbine Fuel Kerosene Type3. Aviation Fuel Quality Standards for Jointly Operated Systems (AFQRJOS) Jet A14. US Military Fuel Specifications, Mil T-5624N (JP-5) and Mil T-T-83133C (JP-8)

NOTE : JP-8+100 contains the "Betz Additive" (injected downstream of the mobile filtrationsystem), which is detrimental to ground and mobile fuel filtration systems and shouldnot be used.

5. DEFENSE STANDARD 91-91 (DERD 2494)6. CAN/CGSB-3.23-2012 Aviation Turbine Fuel, (Grades JET A and JET A-1)

NOTE : Flash point for JetA and JetA1 must be 38°C minimum.

B. The Russian fuel will meet or exceed the specification requirements in the following document.1. GOST10227Commonwealth of Independent Statutes (CIS) Russian Civilian aviation turbine fuel

(jet fuel, TS-1) specificationNOTE : Flash point for TS-1 must be 28°C minimum.

08.01.3 Requirements

A. The fuel will meet the following requirements.1. The fuel will meet all provisions of the latest revisions of the applicable specifications as indicated

under Specifications including, but not limited to, any provisions with respect to material andworkmanship.

2. The fuel will meet the specifications required by the receiving terminal or pipeline, as applicable,if such specifications are more stringent than those indicated under Specifications.

3. The fuel shall be acceptable for use in American Airlines aircraft. Such acceptability shall bedetermined by the airframe and engine manufacturers.

4. The fuel shall be compatible with existing ground handling and filtration systems.

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5. Except as provided under Section 08.01.2, "Specifications," the fuel will contain no additivesexcept those listed in the applicable specifications, unless approved by American Airlines FuelEngineering/DFW in writing. If any additives are approved, the seller will furnish American Airlineswith a list of all such additives.a. Authorized Fuels

(1) Commerciala) Jet Ab) Jet A1c) Jet A50

(2) Militarya) JP-5b) JP-8

(3) Russiana) TS-1

NOTE : Wide Cut Jet Fuel. Special fueling procedures must be followed.

NOTE : Fueling usage must be considered by fleet type.

08.01.4 Special Fueling Procedures

A. Should the use of JP-8+100 be unavoidable, advise MOC to ensure the aircraft is tracked and thefueling ratio is 3 to 1 prior to defueling.

END

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Table of contents

09.01 SHIPMENT OF JET FUEL SAMPLESREFERENCES..................................................................................................................1GENERAL..........................................................................................................................1

TOCShipment of Jet Fuel Samples


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Section 09.01 - Shipment of Jet Fuel Samples09.01.1 References

A. United States Codes of Federal Regulations, 49 CFR, Section 172.11, current revision.B. International Civil Aviation Organization’s Technical Instruction for the Safe Transport of Dangerous

Goods by Air, current revision.C. IATA Dangerous Goods Regulations, current revision.D. ASTM Standard Practice D 4306-84, entitled "Standard Practice for Sampling Aviation Fuel for Test

Affected by Trace Contamination", current revision.E. Refer to American Airlines Hazardous Material Shipping Manual (HSM) Section 05.07, current revision.

09.01.2 General

A. American Airlines personnel shipping Jet Fuel Samples must follow HSM Section 05.07 instructions.Any fuel vendor who is shipping a fuel sample to American Airlines must follow procedures whichcomply with the IATA Dangerous Goods Regulations, current revision.

END

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Table of contents

10.01 FUELING INSTRUCTIONSGENERAL..........................................................................................................................1FUEL HYDRANT CART.....................................................................................................1PROCEDURES..................................................................................................................1

TOCFueling Instructions


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Section 10.01 - Fueling Instructions10.01.1 General

WARNING: DONOTPERFORMTHESEMAINTENANCETASKSDURINGREFUELINGOPERATIONWITH OR WITHOUT PASSENGERS OR CREW ONBOARD: CONNECT ORDISCONNECT THE BATTERY CHARGERS, AIRPLANE GROUND-POWERGENERATORS OR OTHER ELECTRICAL GROUND-POWER COMPONENTS. DONOT TEST THE POWER EQUIPMENT UNTIL AFTER THE REFUELING OPERATIONIS COMPLETE.

A. To the nature of fueling operations, these requirements are to be observed as an aid in preventingfires and accidents. The only exception will be when there is a conflict with local airport or Port Authorityregulations, in which case the local regulations will take precedence in those items where there is aconflict.NOTE : Fuel trucks/tankers are not to be disconnected fromA/Cuntil all fueling discrepancies have

been cleared.

10.01.2 Fuel Hydrant Cart

CAUTION: AIRCRAFT MOVEMENTS, BOTH INGRESS AND EGRESS, MUST BE STOPPEDIMMEDIATELY IF STATIONARY HYDRANT CART IS NOT COMPLETELY PARKEDWITHIN THE DESIGNATED MARKINGS ON THE RAMP.

A. Stationary hydrant carts must be positioned in designated and permanently marked ramp locationsat all times.1. Each permanently designated location must be determined locally based on:

a. Hydrant pit locationb. Aircraft approach to gate relative to taxi/lead-in markings and jetway parkingc. Traffic flow pattern around the aircraft and terminal area that may conflict with safe ground

servicing requirements2. The hydrant cart pit hose is not to be connected to the pit when not in use.3. Person responsible for aircraft fueling operations must monitor the hydrant cart and the fueling

panel at all times.4. Non-motorized hydrant carts are to be inspected and deficiencies reported and repaired prior to

use.

10.01.3 Procedures

A. Prior to any fueling/defueling operation, special note must be made of any temporary placards installedat the fueling panel which would affect the fueling/defueling operation (inop fuel gauges, etc.).NOTE : Prior to fueling any aircraft visually verify the aircraft number against the aircraft number

on the fuel slip. If the aircraft number and number on the fuel slip does not match contactan AA representative immediately. Do not fuel the aircraft until the discrepancy is resolved.

B. If the difference between the right and left wing exceeds the allowable amount on the fuel slip afterrefueling, notify Aircraft Maintenance or station management in person, by radio, telephone or otheragreeable method.WARNING: WHENTHERE ISAN INACCURATE/INOPERATIVEORASUSPICIONOFAGAUGE

NOT INDICATING PROPERLY, OR OTHER MECHANICAL PROBLEM, STOPFUELING AND IMMEDIATELY NOTIFY AIRCRAFT MAINTENANCE OR STATION

Section 10.01Fueling Instructions


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MANAGEMENT IN PERSON, BY RADIO, TELEPHONE OR OTHER AGREEABLEMETHOD.

NOTE : If a fueling gauge is currently on MEL placard as being inoperative, aircraft maintenancedoes not need to be notified, unless specific procedures during fueling operations requirethe attention of aircraft maintenance.

NOTE : Prior to fueling, place safety markers or cones to mark the area of fueling hoses from fuelingunit to aircraft to prevent potential hose damage.

C. Vendor Personnel performing into plane fueling/defueling procedures for AA must be fully trained andable to read, write and speak English. Or, the fueler must be monitored by an individual who is fullytrained on American Airlines fueling/defueling procedures and able to read, write and speak English.1. The individual acting as the fueling monitor (the monitor is not required to remain at the aircraft

fueling panel, but must be readily available should the fueler require any assistance) has theresponsibility to ensure that the fuel slips are properly documented and the correct fuel load isonboard the aircraft.

D. Electrical maintenance to systems which could cause heated wires or arcs shall not be performedduring fueling/defueling operations on any aircraft.

E. Dry chemical fire extinguishers shall be positioned accordingly.F. Fueling or defueling shall be discontinued during severe electrical storms in accordance with local

station procedures.G. Fueling or defueling should be performed outside of hangars or enclosed buildings.H. When fueling/defueling is accomplished:

1. Provide ladders, platforms, etc., as required to functionally, and safely perform all fuelingoperations.

I. Operation of the APU is permitted while aircraft is being fueled.J. Fueling vehicles and facilities must be designed with fail-safe features such as:

1. Overwing fuel nozzle handles with retaining notches removed.2. Loading facility control valves spring-loaded to the off position.3. Hydrant pit valves with self-closing poppets.4. Deadman controls installed on all types of refueler trucks and hydrant carts.

NOTE : Deadman controls on refueler trucks, hydrant carts, and facilities must be held openby hand.

K. Fuel Verification by the use of Fuel Measuring Sticks may be performed by trained and qualifiedvendor personnel or Aircraft Maintenance personnel where applicable. Before using a measuringstick, it must be pulled to its maximum extension to assure that it is not broken or damaged (whichcould result in false indication).Any broken or damaged measuring stick shall immediately be reportedto a maintenance representative for action. Do not insert a broken measuring stick into its housingassembly.

L. Using of Aircraft Drip Sticks1. Fueling procedures using the aircraft drip stick method as the sole alternate means for refueling

risks the possibility of drip sticks being inoperative or inaccurate. Therefore, sticks are used onlyin conjunction with the "Metering of a Known Quantity," as means of verifying that the inoperativetank has been fueled to a value reasonably close to the quantity required. Refer to each aircraftsection for instructions on use of measuring sticks, and for specific requirements regardingalternate procedures allowed.

M. Converting Stick Chart Readings to Actual Pounds



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1. Fuel measuring stick chart values contained in this manual are based on a nominal density of6.70 or 6.76 lbs./gal. Actual fuel density at a station may range, for example, from 6.55 lbs./gal.to 6.85 lbs./gal. or higher. If the actual density deviates in either direction from the nominal chartvalue of 6.70 or 6.76, it may be desirable to correct the nominal chart value based on pounds toactual pounds based on current local fuel density. This may be accomplished by performing thefollowing:a. Obtain an actual fuel density, by performing an API gravity test (refer to Section 02.01).

NOTE : To correctly determine fuel weight at the fueling temperature, measurement mustbe reported as "observed" or uncorrected. Do not correct for temperature @ 60°F.

2. Use the appropriate fuel verification chart based on 6.70 or 6.76 lbs./gal. to convert from inchesto pounds.NOTE : To utilize the fuel verification charts contained in this manual, aircraft should be

determined level.

CAUTION: BE CERTAIN TO VERIFY THE STICK VALUE BEING INTERPRETEDCORRESPONDS TO CORRECT FUEL STICK VERIFICATION CHART FORFLEET TYPE, AIRCRAFT NUMBER, AND FUEL TANK BEING MEASURED.

a. Multiply the pounds obtained in step b. by the ratio of the actual fuel density to 6.70 or 6.76lbs./gal. The following is the "Actual Pound" calculation:

Pounds (from applicable fuel stickverification chart) = Actual Pounds

XActual Fuel Density (lb/gal)

6.70 lbs/gal or 6.76 lbs/gal

b. Example: The actual fuel density is 6.82 lbs/gal. The fuel verification chart is based on adensity of 6.70 lbs/gal. The pound value obtained from the fuel verification chart in Step a.is 9976 pounds.

9976 Pounds = 10155 Actual PoundsX6.82 lbs/gal

6.70 lbs/gal

c. Example: The actual fuel density is 6.82 lbs/gal. The fuel verification chart is based on adensity of 6.76 lbs/gal. The pound value obtained from the fuel verification chart in Step a.is 9976 pounds.

9976 Pounds = 10064 AcutualPounds

X6.82 lbs/gal

6.76 lbs/gal

N. During fuel transfer operations between aircraft tanks, all fueling nozzles must be disconnected fromthe aircraft.

O. After completing fuel servicing operations, make the appropriate entries on the fuel servicing form.P. Do not operate any open flame device in the vicinity of the aircraft being fueled or defueled.Q. Normally, aircraft engines are shut down during fueling operations. However, in the case where loss

of power would result in a stranded aircraft, fuel may be added with an engine running at the discretionof an authorized airline representative. In addition to the precautions and requirements in this manual,a jet engine mounted at the rear of the aircraft or on the wing on the side opposite from the fuelingpoint may be operated.

R. Personnel engaged in overwing fueling operations shall not carry any loose tools in their clothing orother articles, in their breast pockets.



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S. The fueling vehicle operator shall monitor the aircraft fueling panel.T. Ground Support Equipment Operation

1. It is permissible for the turbine starter unit to operate during fueling or defueling.2. The ground power units may be left running and connected.3. Ground Power Units (GPU) shall be positioned at least 20 feet (6 meters) away from the fueling

vehicle and wing tank vents.CAUTION: 1. GPU SHALL NOT BE DISCONNECTED OR SWITCHES OPERATED

DURING FUELING.2. IN THE EVENT OF A FUEL SPILL, THE ENGINES ON THE GPU SHALL

BE STOPPED UNTIL SPILLAGE IS REMOVED AND THERE IS NODANGER FROM FLAMMABLE VAPORS.

U. All personnel involved in aircraft fueling operations must be completely familiar with all emergencyprocedures relative to the fueling operation. This includes familiarization with:1. Emergency procedures to stop the flow of all fuel from the fueling facility.2. Procedures to follow when fuel spillage occurs.3. Location of emergency and firefighting equipment and its proper use.

V. Keep fueling nozzles clean at all times; do not drag nozzles over the ground.W. Fueling aircraft with vehicles containing two separate types of fuel is not permissible, for example, Jet

A and Avgas.X. Always keep areas beneath the aircraft fuel tank vents clear of all motorized and electrical Equipment.

During winter operations, if the fuel tank vents are plugged with ice and/or snow, contact AircraftMaintenance for appropriate action.

Y. Air Conditioning units may be started but must be stopped in the event of a fuel spill.

END



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Table of contents

11.01 FUELING AND VEHICLE RAMP OPERATIONSGENERAL..........................................................................................................................1OPERATION OF FUELING VEHICLES ON THE RAMP...................................................1AIRCRAFT ARRIVAL.........................................................................................................2APPROACHING AIRCRAFT.............................................................................................2POSITIONING VEHICLES.................................................................................................2PARKING POSITIONS.......................................................................................................3

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Section 11.01 - Fueling and Vehicle Ramp Operations11.01.1 General

CAUTION: AIRCRAFT MOVEMENTS, BOTH INGRESS AND EGRESS, MUST BE STOPPEDIMMEDIATELY IF STATIONARY HYDRANT CART IS NOT COMPLETELY PARKEDWITHIN THE DESIGNATED MARKINGS ON THE RAMP.

A. Stationary hydrant carts must be positioned in designated and or permanently marked ramp locationsat all times.

B. Do not approach an arriving aircraft until it has come to a complete stop, properly chocked and itsengines shut down.

C. At stations where hydrant system fueling is performed, an indicating marker should be placed in closeproximity to the hydrant fueling pit to indicate that the pit cover is open for fueling operations.

D. All hydrant vehicle/carts hose couplers shall be disconnected from hydrant pits after servicing fuel toaircraft. Leaving unattended hydrant couplers connected to hydrant pit is prohibited.

E. Do not connect two trucks to the same fueling manifold on the same wing. A slight difference in truckoperating pressure may cause fuel to flow from one truck to the other and overflow the truck with thelower operating pressure.

F. Fueling with trucks arranged and connected one behind the other (piggy-back) is prohibited.G. If an interruption occurs during a fueling or defueling operation and the fueling vehicle cannot be

constantly attended, the aircraft fueling nozzle(s) shall be disconnected.H. Do not service ground equipment from fueling vehicle while fueling the aircraft.I. During overwing fueling operations, minimize "whipping" or "backlash" tendencies in the fueling hose.J. Inspection hatches on aircraft fueling trucks shall not be opened in terminal areas near aircraft. These

hatches are for inspection and cleaning and should only be opened by contractor/airlinemaintenancepersonnel.

K. Hydrant pit covers shall be kept closed when not in use.L. Stationary hydrant carts shall have the tow vehicle disconnected and the brake set during fueling

operations.NOTE : Hydrant carts not equipped with or having an inoperative mechanical brake/interlock system

will be chocked on a minimum of two wheels, with a chock both forward and aft of eachwheel.

M. Fueling or defueling shall be discontinued during severe electrical storms in accordance with localstation procedures.

N. Fueling or defueling should be performed outside of hangars or enclosed buildings.

11.01.2 Operation of Fueling Vehicles on the Ramp

A. Vendor personnel must be qualified in the operation of each type vehicle that they will operate, ateach station, regardless of previous experience.1. Drivers must observe airport traffic rules, speed limits and regulations and adjust speed in

accordance with existing conditions.2. Aircraft always have the total right-of-way.3. Drivers should accelerate slowly and stop slowly. Always come to a full stop when required.

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11.01.3 Aircraft Arrival

A. During gate arrival of American Airlines aircraft via taxi, all ground equipment must remain outsidethe safety clearance lines, including approach from the aft, until the aircraft LOWER red beacon lighthas been turned off by the captain. This action signifies the engines have been shut down and theaircraft is parked. The standard ground handling process should then begin.

B. Should the lower beacon light be inoperative, the UPPER red beacon will be used for reference.

11.01.4 Approaching Aircraft

A. Fueling vehicles will normally approach aircraft from the rear, but may approach from the front whenramp congestion requires. During the approach to the aircraft it is required that:1. Two (2) safety stops must be performed by bringing fueling vehicles to a full stop approximately

fifty (50) feet from the aircraft and a second full stop made approximately eight (8) feet from thefinal parking position.

2. When approaching a parked aircraft with a fueling truck, do not exceed a speed at which a stopcan be safely made with the hand (parking) brake.NOTE : When the vehicle is positioned at the aircraft, shift to NEUTRAL or PARK immediately.

Set the parking brake before leaving the driver’s position.

11.01.5 Positioning Vehicles

CAUTION: FUELING VEHICLES MUST BE OPERATED WITH EXTREME CAUTION AND SAFEDISTANCES MAINTAINED BETWEEN THE FUELING VEHICLE, AIRCRAFT ANDOTHER GROUND SERVICE EQUIPMENT.

A. Ensure proper clearance between mobile fueling equipment and the aircraft at all times. Positioninga fueling vehicle under the aircraft wing on A319/A320/A321, B757 and widebody aircraft fleet typesmay be required for some fueling operations. When positioning a fueling vehicle under the aircraftwing for fueling operations, ensure that the potential for the aircraft to settle is taken into consideration.The possibility of the aircraft settling due to added fuel load, payload, etc., and contacting the fuelingvehicle must be avoided. Positioning a fueling vehicle under the aircraft wing on aircraft fleet typesother than A319/A320/A321, B757 and widebody aircraft is prohibited.

B. Equipment performing aircraft servicing functions shall not be positioned within a 3 m (10 ft) radiusof aircraft fuel system vent openings.

C. Position refueler so that it may be rapidly driven or towed away from the aircraft in the event of anemergency. It is prohibited to position fueling equipment next to open exits with or without passengerson board. Ramp equipment should not be positioned where it will obstruct the movement of a fuelingvehicle.

D. When there is a doubt about clearance, use a guide person. The guide person must be positionedwhere he/she can judge clearances and be in full view of the driver. If the view of the guide personbecomes obscured, he/she must give the STOP signal and reposition him/herself. The driver shouldonly proceed while receiving a continuous signal. The driver must stop if he/she loses visual contactwith the guide person, should the guide person stop signaling, or if there is any question as to thesafety of the operation. When a guide person is used, the driver is still responsible for the safe operationof the fueling vehicle.NOTE : A guide person must be used when backing and when driving in congested areas. For

vehicles equipped with an operating back up video camera and monitor, the use of a guideperson is not required.

E. Drivers must notify their Supervisor immediately when any accident occurs in which they are involved,regardless of injury or damage.



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F. Equipment must never be parked in a manner which could result in damage to an aircraft or otherequipment.

11.01.6 Parking Positions

A. Parking positions of fueling vehicles shall be accomplished as follows:1. Wide Body Aircraft

a. Position fueling vehicle parallel to the aircraft fuselage and clear of engines.b. Position lift deck under aircraft fueling panel to allow ample work space during the fueling

operation.c. Fueling equipment positioning will vary depending on the type of fueling equipment used. In

most cases, the fueling platform of the fueling vehicle may be positioned beneath the aircraftunderwing fuel panel.

d. Equipment performing aircraft servicing functions shall not be positioned within a 3 m (10 ft)radius of aircraft fuel system vent openings.

2. Narrow Bodied Aircrafta. Position fueling vehicle parallel to the aircraft fuselage adjacent to the wing tip.b. Or, position fueling vehicle parallel to the leading edge of the right wing.c. Or, due to unusual circumstances, fueling vehicle may be positioned parallel to the trailing

edge of the right wing.d. Fueling equipment positioning will vary depending on the type of fueling equipment used. In

most cases, the fueling platform of the fueling vehicle may be positioned beneath the aircraftunderwing fuel panel.

e. Equipment performing aircraft servicing functions shall not be positioned within a 3 m (10 ft)radius of aircraft fuel system vent openings.

END



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Table of contents

12.01 FUELING WITH PASSENGERS OR CREW ON BOARDGENERAL..........................................................................................................................1

TOCFueling with Passengers or Crew on Board


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Section 12.01 - Fueling with Passengers or Crew on Board12.01.1 General

A. The written procedures in this section are based on IOSA current standards.1. All aircraft ground time with or without passengers on board is considered a fueling/defueling

period. Crewmembers are not required to be present during fueling if there are no passengerson board.NOTE : The fueler is responsible for the fueling operations. The fueler’s employer will be the

responsible organization. It is important that the fueling company ensures that all fueler’swho fuel American Airlines aircraft have been properly trained and have a clearunderstanding of how and when such fueling communication takes place and are ableto execute procedures in an expeditious manner. Communication to the qualifiedperson(s) onboard the aircraft may also involve:

a. Aircraft inter-communication systemb. Direct person-to-person contact

2. Emergency Communications are enacted in the event of a fuel spill, hazardous condition or fire.a. The fueler will contact fueling supervisor or manager-on-duty by radio, and who in turn will

notify AA local, operations or manager-on-duty.b. The fueler will also inform any local AA ground personnel that are in the immediate gate

area.c. AA operations will notify local fire department as required.d. The flight crew/ flight attendants will be notified in the most expedient manner by use of

Aircraft communication system, direct person-to-person contact or other methods that ensuredirect and timely communication through station operations management, maintenance, orother local forms of gate operations control.NOTE : Defueling or transferring of fuel from any tank on the B737 and B757 using the

integral tank fuel boost pumps with passengers on board is permitted providedthe tank quantity from which fuel is being taken is maintained at 2000 pounds ormore.

e. If a fuel spill, hazardous condition oremergency should occur during fueling STOP FUELING,notify qualified station personnel or Flight Crew/Flight Attendants immediately, and aircraftmaintenance as required.

3. Station personnel will coordinate with the Flight Crew about the decision to deplane.4. Flight Attendants will be stationed in the aircraft cabin as outlined in the American Airlines Flight

Attendants In-Flight Manual.5. When fueling with passengers on board, the Jet Bridge or passenger loading stairs must be

positioned at an entry door of the airplane and the door will remain open. On the MD-80, the aftstairs may be used in lieu of a jet bridge or passenger loading stairs.NOTE : When fueling an MD-80 away from the gate, if the passenger loading stairs are

positioned at the entry door of the aircraft, the aft stairs can remain stowed (up) andentry door may be open. If no passenger loading stairs are positioned, aft stairs mustbe lowered, however, aft entry door may be closed.

6. During boarding, or if the cockpit crew is not onboard, one Flight Attendant is permitted to stepoff the aircraft to use a Jet bridge phone in order to contact the agent and advise of any safetyrelated or hazardous condition that may exist.

Section 12.01Fueling with Passengers or Crew on Board


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NOTE : However, at stations where no jet bridge or loading stairs are available, refueling withpassengers aboard is permitted, provided all usable exit doors are armed and a FlightAttendant is stationed at each armed door.

Depending on the requirements of the local authority having jurisdiction, where fuelingoperations take place with passengers onboard away from the terminal building andstairways are not provided, such as during inclement weather (diversions), all slidesshall be armed and the ARFF (Airport Rescue Fire Fighting) services shall be notifiedto respond in stand-by position in the vicinity of the fueling activity, with at least onevehicle.

7. Pilots are not required to be present during fueling with or without passengers on-board, however,if present ensure communication is maintained by any suitable means between the fueler andqualified on-board personnel.NOTE : However, at stations where no jet bridge or loading stairs are available, refueling with

passengers aboard is permitted, provided all usable exit doors are armed and a FlightAttendant is stationed at each armed door.

Depending on the requirements of the local authority having jurisdiction, where fuelingoperations take place with passengers onboard away from the terminal building andstairways are not provided, such as during inclement weather (diversions), all slidesshall be armed and the ARFF (Airport Rescue Fire Fighting) services shall be notifiedto respond in stand-by position in the vicinity of the fueling activity, with at least onevehicle.

8. Fueling equipment shall not be position to obstruct aircraft emergency exit routes, with or withoutpassengers on board including evacuation chutes.

9. Smoking is not permitted in the airplane or on the ramp.

END

Section 12.01Fueling with Passengers or Crew on Board


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Table of contents

13.01 SPECIAL FUELING PROCEDURESDIVERSIONS, CHARTERS AND POLAR OPERATIONS.................................................1POLAR ROUTE OPERATIONS.........................................................................................2

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Section 13.01 - Special Fueling Procedures13.01.1 Diversions, Charters and Polar Operations

A. Diversion Flights1. In the event of a flight diversion into a station that does not have normally scheduled operations

for the subject aircraft type and fuel service is required, coordination between the local AA stationrepresentative (if available), the flight crew and the MOC MOD is essential. The MOC MOD shallensure every effort is taken to verify fuel is received from an AA-qualified fuel vendor and theperson performing the fueling operation is currently qualified to fuel the aircraft type for AA.

2. If an AA-qualified fuel supply vendor is not available and it becomes necessary to fuel at anydomestic or international diversion location using an unapproved vendor, the MOC MOD willcoordinate accomplishment of the following between the Flight Crew or other AA representativeand the local fuel vendor:a. The Captain or his/her representative shall request a sample of fuel from the fuel servicing

vehicle, to be used for his/her visual examination.(1) The Captain or designee shall observe a fuel sample drawn from the fuel servicing

vehicle sump drain.NOTE : The visual examination is preferably taken in a clean glass container with a

diameter of no less than 3 inches (32 oz. Mason jar is suitable).

(2) Ensure the sample is free from undissolved water, sediment and suspended matter.The color of the fuel should range from water white to slight amber color.NOTE : There should be no cloudiness or particulate observed. If the sample is suspect

and does not meet the assessment criteria, additional samples may be takenuntil an acceptable assessment result is achieved.

(3) Upon completion of the fuel servicing, the Captain or designee will sign his or her namein the remarks section of the Fuel Service Record confirming completion of the aboveassessment steps.NOTE : If an AA Computer Generated Jet Fuel Service form is not available, the MOC

MOD will provide by e-mail or fax a Form E117, "Fuel Service Record" (referto Section 15.01.2), to the vendor/station.

3. If fueling is to be performed by an individual that is not qualified in the AA program for the aircrafttype, the MOC MOD will provide a one-time authorization after:a. Verifying the individual is currently qualified in another carrier’s program to fuel the aircraft

type (training records to be verified), ORb. Coordinating with an appropriate Maintenance Control Technician (MCT) on duty to provide

the fueler with the relevant procedures for fueling the aircraft type and assist the fueler throughthe process, as needed.

4. The Captain will verify the correct fuel load was delivered and that a fuel slip was properlycompleted by the fueler for the operation. All fuel slips/delivery tickets must show the Ops Ordernumber, type of fuel delivered, gallons provided, and vehicle number.

5. The MOC MOD or Captain will ensure a copy of the fuel slip is sent to Fuel Engineering via fax,e-mail or mail.

B. Charter Flights1. When operating a charter flight into an airport not serviced by AA or not having a fuel vendor

currently approved the following procedures must be accomplished:

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http://partners.aa.com/techops/TEQ/RegEngSupport/TechOpsForms/Form%20E117.pdf






a. Vendors performing fueling on AA aircraft must be approved by QA prior to charter(non-scheduled) operations.

b. Charter Planning provides a monthly schedule of all charter flight activity to FuelAdministration.NOTE : The schedule will contain the charter station contact information, the date, time of

operation, line of flight (airport to airport), and flight frequency.

13.01.2 Polar Route Operations

A. When flying the Polar Routes, a fuel temperature analysis shall be used. The Jet A fuel specificationlimits the freezing point to a maximum of -40°C, the Jet A-1 limit is -47°C maximum. Because fuelspecifications may vary by country, the appropriate fuel procurement specification for the fuel beingdispensed shall be used. The actual freezing point of delivered fuel at the time of dispatch must bemeasured.1. Requirements for Polar Route Fueling Approval

a. Station must have the equipment as specified in ASTMD2386, D5972 and D7153 StandardTest Method for Freezing Point of Aviation Fuels.

b. A qualified trained person must perform or observe the fuel freeze point analysis.c. Have a written process specific to the location for responsibilities, sampling, testing and

reporting.d. Demonstrate the ability to perform the responsibilities, procedures and reporting to DFWFE

or their delegated representative.e. Obtain written approval from DFWFE. DFWFE will then add the location to the approved

station list in this manual.B. Approved Stations

1. ORD and DFW. As more stations are approved to fly the Polar route, the procedures for thesestations will be implemented.

2. The following is a list of responsibilities, procedures, and reporting that must be accomplishedprior to flight departure.a. Responsibilities

(1) AA Flight Dispatch, Airport Fuel Facility Operator, into plane fueler’s and AA FuelEngineers (DFW) will coordinate all aspects of the testing procedure to ensure data isrequested, obtained and relayed to flight crews in a timely manner.

(2) It is important for all above parties, to coordinate and share responsibility for the programas follows:a) FLIGHT - Dispatch will be responsible for determining when planeside sampling is

required and for notifying Fueling Supervisor. Dispatch will also relay test resultreported by fueling vendor to flight crews prior to flight.

b) FS - Fueling supervisor will be responsible for ensuring jet fuel freeze samples aretaken during aircraft refueling and sample delivered to testing facility. Fuelingsupervisor will also be responsible for notifying testing facility when analysis will berequired.

c) Testing Facility -Will be responsible for performing freezing point analysis andreporting results to AA dispatch. DFWFE - Fuel Engineering will be responsible forproviding technical support and monitoring jet fuel freeze testing procedure.

(3) Notification



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a) It is necessary that all involved parties be notified as soon as possible that planesidefuel sampling will be required. It is recommended that required personnel be notifiedat least four hours prior to flight departure. The following procedure shall be used:(1) FLIGHT - Dispatch will notify appropriate Fueling supervisor in person or other

agreeable method when planeside sampling is required. Notification shallinclude flight number and a contact phone number.

(2) FS - Upon notification from dispatch, fueling supervisor will notify the appropriatetesting fuel facility supervisor on duty in person or other agreeable method thatan analysis will be required and provide an approximate time the fuel sampleswill be delivered.

(4) Planeside Sample Procedurea) Sample Equipment - The following equipment will be supplied by FS for taking the

planeside fuel samples:(1) 1 liter HDPE plastic bottle with caps for fuel samples (CPN 4166405) or

equivalent(2) Adequate size container for holding flushed jet fuel(3) Sampling device equipped with male actuator nipple, on/off valve and flex

tubingb) Sampling Procedure - Samples for the Polar flight freeze testing shall be taken as

follows:(1) Attach sampling device to sample connection located downstream of fueling

equipment filter or at nozzle.NOTE : Draw four fuel samples into one liter plastic bottle or equivalent.

These samples shall be drawn into the same bottle at equally spacedintervals, approximately one fourth of fuel drawn at a time.

(2) Fuel approximately a minimum of 500 gallons into aircraft before taking thefirst sample.

(3) Flush ample amount of fuel to displace sample connection (3-4 ounces shouldbe sufficient).

(4) The first fuel sample taken shall be drawn when the gallons meter counter readapproximately 600 gallons.

(5) Fill the fuel sample bottle with approximately one fourth of fuel, while continuingfueling the aircraft.

(6) Take two more fuel samples equally spaced during aircraft refueling.(7) Take fourth and final fuel sample near the end of refueling operation.(8) A total of four fuel samples shall be in one sample bottle when complete.(9) Mark sample bottle with date, flight number, fueling unit, time of sample and

final fuel meter reading.(10) Deliver fuel samples to testing facility immediately.

END



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Table of contents

14.01 REPORTING FUEL DENSITYGENERAL..........................................................................................................................1PROCEDURES..................................................................................................................1APPENDIX 1......................................................................................................................1

TOCReporting Fuel Density


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Section 14.01 - Reporting Fuel Density14.01.1 General

A. Each station is responsible for reporting an accurately determined fuel density at least one time perday, which is essential to ensuring proper aircraft performance and weight and balance calculationsfor each flight.

14.01.2 Procedures

A. These procedures are effective immediately upon receipt, and will continue until amended by FuelEngineering.1. Each station will designate a person and/or work group at your station responsible for receiving,

recording and reporting the fuel density at least once a day.NOTE : Fuel Density is provided by the local fuel facility, ensure your station is on their

notification list to be informed.

2. The first fuel density report is transmitted as early as possible prior to the first departure of theday, usually in conjunction with the daily "Field Conditions" report, but all efforts should be madeto report the fuel density at least 90 minutes prior to the first departure of the day.

3. The person responsible for reporting the fuel density will maintain a log for auditing purposes,which will include:a. The date of each reportb. The time of each reportc. The density reportedd. The name of the person reportinge. The fuel density log must be retained for one year.

4. Stations with operations throughout the day will report fuel density at the following intervals:a. First report (as noted above), thereafterb. Second report should be reported approximately mid-day.c. Third report may be necessary based on the station flight schedule and should be reported

early evening.5. A standardized form in DECS/FOS be used to report the fuel density. Refer to Appendix 1.6. To ensure proper controls and tracking, stations with direct controls and tracking, stations with

direct access to the fuel density update entries should no longer update FOS directly, and shouldfollow the reporting procedures contained herein.

7. For any problems with the automated message, contact FOS Control8. Questions regarding the fuel density determination or procedures associated with it should be

directed to Fuel Engineering.

14.01.3 Appendix 1

A. To access the standardized FOS Fuel Density Message in the DECS, enter RF 5000 FUEL.B. Refer to FOS Control for more information regarding the complete process of determining the fuel

density.1. Response:

RF 5000 FUEL

***HOME THEN RESET/ESC DOWN TO SEND LINE. THEN TAB TO STOPS*** SEND TULDBHDQML FCG5 FCG6 FC67 ¥

Section 14.01Reporting Fuel Density


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ATTN FOS CONTROL

FUEL DENSITY

<ENTER HEREa. To update this data:

(1) Press the ‘Home’ key.(2) Press the ‘Reset’ or ‘Esc’ key until the cursor is on the letter ‘S’ in SEND.(3) Use the tab key and enter the complete fuel density a. Eg - 6.64.(4) Use the tab key and enter the three character airport code.(5) Use the tab key to put the cursor on the ‘E’ at Enter Here.(6) Press the ‘Enter’ key.

A successfully sent message will provide a response that says ‘OK’.

END

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Table of contents

15.01 JET FUEL SERVICE FORMSGENERAL..........................................................................................................................1FORM E117 JET FUEL SERVICE RECORD (FUEL SLIP)...............................................2COMPUTER GENERATED JET FUEL SERVICE RECORD (FUEL SLIP), FORM 10012.3QT TECHNOLOGIES - ELECTRONIC FUEL DISPATCH AND UPLIFT REPORTINGSYSTEMS..........................................................................................................................4ACCEPTANCE...................................................................................................................5JET FUEL SERVICE RECORD- ALTERNATE FUELING PROCEDURE.........................5FUEL ONBOARD (FOB)....................................................................................................7METRIC CONVERSIONS..................................................................................................7FUEL LOAD ALLOWABLE VARIANCE (OVERFUEL TRACKING & REPORTING).........7

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Section 15.01 - Jet Fuel Service Forms15.01.1 General

A. The flight crewmembers are not provided a copy of the Jet Fuel Service Record (fuel slip) when allfuel quantity gauges or indicators are operative (domestic non overwater flights only).

B. A fuel slip will normally be provided to flight crewmembers on international flights. However, it is notrequired and flights may depart without it unless required by a placard Minimum Equipment List (MEL)item.

C. The flight crewmembers must receive a copy of the fuel slip when there is an inoperative/inaccuratecockpit gauge/indicator even when the effective tank is supposed to be empty.

D. The aircraft Captain must be advised of any top-off or MEL related fuel added, and there must be afuel release showing additional fuel. Vendor personnel are never to add fuel to an aircraft without afuel release.

E. During the closeout the cockpit crew will ensure that the fuel-on-board quantity and the flight releasetotal quantity essentially agrees. If they do not agree, the cockpit crew will resolve the matter with theLoad Agent and/or fuel servicemen prior to departure.

F. Since the cockpit crew will not ordinarily receive a fuel slip, close attention by the fueler must be givento the fuel slip calculations. Arithmetic should be checked for accuracy. Turbine fuel conversion chartsmay be used, but when using a density other than 6.70 lb/gal, use of a calculator is preferred.

G. If a gauge/indicator is identified as inoperative, before the printout of the fuel slip, an automatic messagewill be in REMARKS portion of the fuel slip, stating the inoperative gauge/indicator and the requirementto deliver a copy of the fuel slip to the cockpit.NOTE : The computer will print out two consecutive copies of the fuel slip. No carbon sheet will be

provided. Therefore, two identical fuel slips must be completed.

H. In the event a cockpit gauge/indicator problem surfaces after the printout of the fuel slip, no automaticmessage will be in REMARKS section and the computer will print out only one copy of the fuel slip.(The original can be reproduced in this situation, and the original shall be the fuel slip that goes to thecockpit.) The fueler must retrieve an Inoperative Fuel Quantity Indicator Service Record, Form 10014,to record the manual stick readings.

I. There are two types of jet fuel service forms (fuel slips):1. Form 10012, Computer-generated Jet Fuel Service Record (fuel slip) in gallons.2. Form E117, Jet Fuel Service Record (fuel slip) in gallons.

NOTE : The Form E117 fuel slip can be duplicated by copy machine.

3. The preferred and standard form is the computer-generated form. This fuel slip is generated bythe load agent or other authorized airline representative. When the fuel slip is received by thefueler, all identification information at the top of the form will be completed with the exception ofFuel Grade, which is to be completed by the fueler. TheGATERELEASEQUANTITYREQUIRED- LBS. for each tank, with the TOTAL, will also be provideda. Only minor text corrections are permitted on the Jet Fuel Service Record (fuel slip), Form

10012, and Inoperative Fuel Quantity Indicator Service Record, Form 10014. If a single entryerror is made, strike through the incorrect entry and enter the correct text/number(s) adjacentto the error followed by the initials of the fueler. All Jet Fuel Service Record (fuel slip) andFuel Quantity Indicator Service Record numerical entries including corrections must belegible. If the text size of the enter error(s) does not allow a correction in the adjacent spaceor the amount of errors and corrections create an overall non legible appearance, a newform will be issued and used.

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b. Complete Jet Fuel Service Record (fuel slip) and Inoperative Fuel Quantity Indicator ServiceRecords will be retained on file for a minimum of 90 days (3 months) by the station AmericanAirlines (AA) General Manager or other authorized airline representative.

J. Departure stations utilizing an electronic fuel dispatch and uplift reporting system such as QT, VarecFuels Manager, TotalFBO and Logicraft are not required to complete the computer-generated JetFuel Service Record, Form 10012, or Jet Fuel Service Record, Form E117, as long as the fuel onboardand uplift data is recallable for a minimum of six months post fueling, the data is capable of beingprinted as the Jet Fuel Service Record, and there is not an inoperative/inaccurate cockpitgauge/indicator. The approved use of an electronic fuel dispatch and uplift reporting system to reportfuel quantity constitutes the completion of the Jet Fuel Service Record. Stations using electronic fueldispatch and uplift reporting systems are still required to complete the Inoperative Fuel QuantityIndicator Service Record, Form 10014, when necessary. In the event that there is aninoperative/inaccurate cockpit gauge/indicator, either Form 10012 or Form E117 must be completedin order to provide fuel uplift quantities to the flight crew, per Section 15.01.1.C. Should the electronicfuel dispatch and uplift reporting system become inoperative, the fuel service provider is required todefer to the computer-generated Jet Fuel Service Record. Form E117may also be used if the computerprinter is inoperative.

15.01.2 Form E117 Jet Fuel Service Record (Fuel Slip)

A. Form E117 may be used under the following conditions:1. When the computer is not available or not operating2. For charter operations at cities not served by American Airlines3. When a computerized slip becomes damaged or obliterated due to weather, torn, overall non

legible appearance and cannot be replaced due to time constraints4. When the aircraft Captain requests a special review of the fuel load5. Whenever an aircraft is topped off6. When a trip is fueled through a station and an aircraft fuel quantity gauge/indicator is MEL

placarded and there is a flight crew change7. When prefueling overnight aircraft for tow and taxi ballast fuel or to expedite morning departures8. When determined as essential by local station management

B. Completing the Form E1171. The Load agent or airline representative will generate and complete the Fuel Density, Aircraft

No., Aircraft Type, Flight number/date, Station, gate release quantities for each aircraft fuel tank,and gate release quantity total fields on Form E117. The fueler will then complete the remainingrequired information on Form E117 including:a. The actual fuel grade loaded, for example:

(1) Jet A(2) Jet A-1(3) Jet A-50(4) TS-1(5) JP-5(6) JP-8

b. Record the GAUGE READING BEFORE FUELING in pounds on the fuel slip in the spacesrepresenting each aircraft fuel tank. Record them as they appear. Do not round off values.

c. Summarize and record the GAUGE READINGS BEFORE FUELING TOTAL in pounds fromeach aircraft fuel tank.



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d. Perform the fuel servicing and record the GAUGE READINGS AFTER FUELING in poundsin the spaces representing each aircraft fuel tank.

e. Summarize and record the GAUGE READINGS AFTER FUELING TOTAL in pounds fromeach aircraft fuel tank.

f. Calculate and record the fuel added in pounds by subtracting the BEFORE FUELING TOTALpounds from the AFTER FUELING TOTAL pounds.

g. Divide the pounds added by the actual density listed at the top of the form and record thegallons delivered. If the actual density is unavailable, use 6.7 for gallons.

h. Record the gallons delivered from the equipment meter.i. Record the actual difference of gallons delivered based on density versus the equipment

meter. Make sure the actual difference is within the allowable difference specified in thetolerance chart on the form.NOTE : Should the allowable difference between GALLONS delivered and METER

GALLONS ADDED be exceeded (+/-), a fuel quantity error could exist. Notify theMaintenance Operations Control (MOC) or local station A/CMaintenance in personfor corrective action guidance. Do not disconnect from aircraft until issue has beenresolved.

NOTE : The allowable difference (aircraft fuel quantity gauge/indicator check) on the fuelslip is not to be interpreted as an allowable difference you may make to the fuelload. The allowable difference is there solely to adjust for any slight error in thefuel gauge/indicator on the aircraft, truck meter and possible difference in fueldensity, and to alert the fueler to a possible inaccurate/inoperative fuelgauge/indicator on the aircraft.

j. Fueler Initials, Signature and Employee number - The person responsible for reinstalling thefuel cap (on applicable fleets, otherwise N/A) and closing the fuel panel door will apply theirinitials in ink in the applicable spaces. The person responsible for fueling the aircraft will signtheir name and enter their employee number in ink on the designated line (Initials are notacceptable). In addition, the fueler shall enter the number of the refueling equipment usedin the space provided.NOTE : Initials are not acceptable, except where noted. Ensure the completed fuel slip is

correctly filled out in ink.

15.01.3 Computer Generated Jet Fuel Service Record (Fuel Slip), Form 10012

A. Completing the Form10012 computer-generated Jet Fuel Service Record (fuel slip):1. On top of form, fill in the actual fuel grade loaded, for example, Jet A, Jet A-1, Jet A-50, TS-1,

JP-5, JP-8.2. Record the GAUGE READING BEFORE FUELING in pounds on the fuel slip in the spaces

representing each aircraft fuel tank. Record them as they appear. Do not round off values.3. Summarize and record the GAUGE READINGS AFTER FUELING TOTAL in pounds from each

aircraft fuel tank.4. Perform the fuel servicing and record the GAUGE READINGS AFTER FUELING in pounds in

the spaces representing each aircraft fuel tank.5. Summarize and record the GAUGE READINGS AFTER FUELING TOTAL in pounds from each

aircraft fuel tank.6. Calculate and record the fuel added in pounds by subtracting BEFORE FUELING TOTAL pounds

from the AFTER FUELING TOTAL pounds.



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7. Divide the pounds added by the actual density listed at the top of the form and record the gallonsdelivered.

8. Record the gallons delivered from the equipment meter.9. Record the actual difference of gallons delivered based on density versus the equipment meter.

Make sure the allowable difference is within the specified limit.NOTE : Should the allowable difference between GALLONS delivered and METER GALLONS

ADDED be EXCEEDED (+/-), a fuel quantity error could exist. Notify MOC or localstation A/C Maintenance in person for corrective action guidance. Do not disconnectfrom aircraft until issue has been resolved.

NOTE : The allowable difference (aircraft fuel quantity gauge/indicator check) on the fuel slipis not to be interpreted as an allowable difference you may make to the fuel load. Theallowable difference is there solely to adjust for any slight error in the fuel gauge/indicatoron the aircraft, truck meter and possible difference in fuel density, and to alert the fuelerto a possible inaccurate/inoperative fuel gauge/indicator on the aircraft.

10. Fueler Initials, Signature and Employee number - The person responsible for reinstalling the fuelcap (on applicable fleets, otherwise N/A) and closing the fuel panel door will apply their initials inink in the applicable spaces. The person responsible for fueling the aircraft will sign their nameand enter their employee number in ink on the designated line. (Initials are not acceptable.) Inaddition, the fueler shall enter the number of the refueling equipment used in the space provided.NOTE : Initials are not acceptable, except where noted. Make sure that the completed fuel slip

is correctly filled out in ink.

15.01.4 QT Technologies - Electronic Fuel Dispatch and Uplift Reporting Systems

A. Completing the fuel service record via the QT Technologies electronic fuel dispatch and uplift system:NOTE : Training on the use of the electronic fuel system handheld device is completed by QT

Technologies.

1. After selecting the flight to be serviced using the electronic fuel system handheld device, verifythat gate, aircraft type and tail information coincide and input the corresponding tail number intothe handheld device.

2. Verify required fuel uplift quantity and select the correct fuel servicing equipment on the handhelddevice using the barcode located on the servicing equipment.

3. Record the GAUGE READINGS BEFORE FUELING in pounds in the fields representing eachaircraft fuel tank. Record them as they appear. Do not round off values.

4. Perform the fuel servicing and record the GAUGE READINGS AFTER FUELING in pounds inthe fields representing each aircraft fuel tank.

5. Confirm that the start and end totalizer values on the handheld device coincide with the valuesprinted on the physical meter ticket. If they do not match, change the values on the handhelddevice to match the meter ticket by entering the correct values in the fields provided.NOTE : Should the allowable difference between GALLONS delivered and METER GALLONS

ADDED be EXCEEDED (+/-), a fuel quantity error could exist. The handheld devicewill prompt the fueler to check how much fuel was pumped when this situation arises.Notify MOC or local station A/C Maintenance in person for corrective action guidance.Do not disconnect from aircraft until issue has been resolved.

6. Fueler Signature and Employee Number - QT Technologies is required to maintain a log of fuelername and employee number for each flight that is serviced using the reporting system's handhelddevices. When the fuel onboard and uplift data is printed as the Jet Fuel Service Record, per



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Section 15.01.1.J., the fueler name and employee number will be printed in place of the requiredinitials and signature indicated by Section 15.01.3.A.10.

15.01.5 Acceptance

A. In the event of over-fueling, or an aircraft swap resulting in too much fuel onboard, the Flightcrew canreject the actual fuel-on-board, if the quantity is greater than the GATE RELEASE QTY. REQUIRED- LBS. quantity shown on the Fuel Service Record. Therefore, if overage exceeds the ALLOWABLEFLEET VARIANCE, the Fuel Service Person is required to notify the Load Agent/Dispatch in personto determine if this overage is acceptable.1. If the overage is acceptable, Dispatch will issue a new Fuel Service Record showing the approved

quantities. Adjustments can be made by tank-to-tank transfer or by defuel/refuel, if necessary.2. If the overage is unacceptable, it may be necessary to defuel the excess fuel down to the original

release.B. In the event the allowable difference between GALLONS delivered and METER GALLONS ADDED

(+/-) is exceeded, the following procedures will be accomplished.1. Make sure the fuel density as reported on the fuel slip is the same as the aircraft indication or

draw a sample of fuel from the aircraft to measure the current fuel density. If the aircraft indicatedor measured fuel density is the same as reported on the fuel slip, proceed with steps below. Ifthe aircraft indicated or measured fuel density differs from the fuel slip, use the indicated ormeasured density to determine actual gallons delivered. If the allowable difference is still exceeded,proceed with steps below.NOTE : Not all aircraft have a fuel density indicator/display. Assistance from aircraft maintenance

will be required to obtain a clean sump sample for density measuring.

2. The fuel vendor will contact and coordinate with aircraft maintenance in person to have a manualquantity indication reading (fuel measuring stick) procedure accomplished on all tanks if equipped.Fuel vendor personnel, if trained and qualified or AA/Contract aircraft maintenance personnelmay perform this procedure. If the aircraft tank manual quantity indication readings compared tothe tank quantity gauge readings differ by more than 3%, the normal quantity system for thattank/indicator may be faulty. Aircraft maintenance personnel will follow standard procedures torepair or defer the discrepancy, for example, Aircraft Maintenance Manual (AMM), MinimumEquipment List (MEL), etc., according to company procedures.NOTE : Aircraft tank(s) not equipped with a manual indicator(s), for example, measuring stick(s),

will have a known quantity transferred from another aircraft tank with an operativenormal quantity indicator. This will provide a method to validate the normal quantityindicator in the tank without a manual indicator is functioning properly.

3. If the manual & aircraft tank quantity indications do not differ by more than 3%, the equipmentmeter may be faulty. The vendor will contact local station management in person who will notifyFuel Administration in person to coordinate with the vendor on monitoring the meter performanceon subsequent refueling and or make sure corrective action, for example, replacement,re-calibration, etc. is accomplished.NOTE : Suspected faulty equipment meters will be excluded from fueling operations where a

known quantity is required to be delivered.

15.01.6 Jet Fuel Service Record- Alternate Fueling Procedure

A. In addition to the information above, when performing alternate fueling procedures the following mustbe completed on the jet fuel service record:1. Record on bottom of fuel slip the fuel tank indicator that is inoperative if not already preprinted.



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2. When fuel is transferred to empty a tank with an inoperative gauge, enter 0 in the appropriate"before fueling" portion of fuel slip, also enter actual indicator readings from other operative tankgauges.

B. When an aircraft fuel tank quantity indicator gauge is inoperative, the following procedures must befollowed:WARNING: ONLY VENDOR DESIGNATED TRAINERS/SUPERVISORS/LEADS WHO ARE

TRAINED AND QUALIFIED WILL PERFORM IN OP GAUGE PROCEDURES. IFTRAINED AND QUALIFIED FUEL PERSONNEL ARE UNAVAILABLE, QUALIFIEDAA MAINTENANCE OR CONTRACTED MAINTENANCE PERSONNEL WILL BEUSED.

NOTE : Refer to the Inoperative Quantity Indication procedures for each fleet type for specificInstructions on performing inoperative gauge tank quantity reading procedures.

1. When utilizing Method 1 as outlined in the applicable fleet section of this manual for InoperativeQuantity Indication procedures of obtaining individual tank quantities by the respective operativecockpit display for the inoperative under wing panel quantity indicator, indicate method 1 in theremarks section of the fuel slip as the procedure used.

2. When utilizing Method 2 or Method 3 as outlined in the applicable fleet section of the manual forInoperative Quantity Indication procedures of obtaining individual tank quantities by delivering aknown quantity and or reading measuring stick values, completed the Inoperative Fuel QuantityIndicator service record.NOTE : Regardless of how pre-service fuel for the affected tank is derived, the majority of fleet

types will require "Metering a Known Quantity" and then "Verifying the Fuel Load byMeasuring Stick" for an inoperative fuel gauge.

NOTE : Should the transfer of fuel or other procedures requiring cockpit access becomenecessary, Flight Crew or Maintenance personnel must perform these functions. Foradditional assistance, such as malfunctioning fuel valve operation, opening and closingof gear doors, etc. contact Aircraft Maintenance personnel in person or, if not on duty,contact MOC in person.

C. Form 10014 , Inoperative Fuel Quantity Indicator Service Record.NOTE : Form 10014 can be ordered from Tulsa Stationery, MD 128, or 918-292-3106 or can be

duplicated by copy machine or printed from the figure below and used if neither of the aboveforms are available for whatever reason.

1. Form 10014 must be completed in ink when utilizing Method 2 or 3 to determine fuel quantity bymeasuring stick.

2. Completing Form 10014:a. The Load agent or other airline representative will generate & complete the Flight No., Aircraft

No., Station, & Date.b. The individual performing the inoperative gauge readings shall:

(1) Check the box for Method 2 or Method 3 for the procedure being used.(2) Record the tank with the inoperative fuel quantity indicator, for example, L, LI, C, ACT,

Trim.(3) Record the Aircraft/Air Data Inertial Reference Unit (ADIRU) readings (Pitch & Roll)

before and after fueling as applicable.(4) Circle the stick(s) used in the applicable tank to perform the quantity measurement

before and after fueling as applicable.



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(5) Record the units or inches read from the stick(s) utilized, the actual pounds from theMLI stick charts and total pounds before and after fueling as applicable.

(6) Initial in the space validating the stick(s) have been properly secured.(7) Print your name, job title, and company.(8) Provide your signature and distribute accordingly.

15.01.7 Fuel Onboard (FOB)

A. In the event a fueler arrives at an aircraft having sufficient fuel on board for the flight1. If necessary, contact station management or Aircraft Maintenance in person to transfer/redistribute

fuel, and if the Fuel on Board exceeds the Allowable Variance for overfueling, LoadPlanning/Weight and Balance must be contacted in person for a new fuel release. THEN:

2. The Fuel Grade entry may be left blank or N/A when no fuel has been delivered.3. Record the GAUGE READING BEFORE FUELING in pounds on the fuel slip in the spaces

representing each aircraft fuel tank. Record them as they appear. Do not round off values.4. Summarize and record the GAUGEREADINGS BEFORE FUELING TOTAL in pounds from each

aircraft fuel tank.5. Record Fuel on Board (FOB) in the CALCULATED FUEL ADDED space provided.6. Fueler Initials, Signature and Employee number -The person responsible for closing the fuel panel

door will apply their initials in ink in the applicable spaces. The fuel cap installed space (onapplicable fleets) may be left blank or N/A unless the cap was removed during servicing. Theperson responsible for determining and recording sufficient fuel onboard the aircraft will sign theirname and enter their employee number in ink on the designated line (Initials are not acceptable).In addition, the fueler may leave blank or N/A the Equipment No. space.NOTE : Initials are not acceptable, except where noted. Make sure that the completed fuel slip

is correctly filled out in ink.

15.01.8 Metric Conversions

A. At stations outside of the United States where it is required to convert liters and/or decaliters to U.S.Gallons to ensure the actual difference is within the allowable difference, the following minimumstandard conversion factors shall be used:1. Liters to U.S. Gallons: Liters multiplied (x) by 0.264 equals U.S. gallons added. Or2. Liters divided by 3.785 equals U.S. gallons added.

(Liters) (3,785) = U.S. gallons added3. Decaliters to U.S. Gallons: Decaliters multiplied (x) by 2.64 equals U.S. gallons added.

15.01.9 Fuel Load Allowable Variance (Overfuel Tracking & Reporting)

A. In order to prevent possible overfueling delays, the final fuel load should not exceed the variance byfleet as indicated below. Every effort should be made to fuel the aircraft as close as possible to thefuel load requirements, as indicated on the jet fuel service record. Additional fuel should not be boardedto compensate for APU burn.

Table 15.01-1: Fleet Variance400 lbs.=B777-200200 lbs.=B737200 lbs.=E190

400 lbs.=B777-300 ER400 lbs.=B757200 lbs.=MD80

400 lbs.=B787450 lbs.=B767400 lbs.=A330

1000 lbs.=B767/AC 301-317



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200 lbs.=A319/A320

200 lbs.=A321

Table 15.01-2: Allowable Difference (Aircraft Fuel Quantity Gauge/Indicator Check)750 gal.=B777-200150 gal.=B737150 gal.=E190

750 gal.=B777-300 ER290 gal.=B757150 gal.=MD80

750 gal.=B787525 gal.=B767150 gal.=A319/A320

750 gal.=A330290 gal.=A321

gal. = gallons

END



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Table of contents

16.01 GENERAL FUEL STORAGE FACILITY SABOTAGE "THREAT" CHECKLISTGENERAL..........................................................................................................................1

TOCGeneral Fuel Storage Facility Sabotage "Threat"Checklist


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Section 16.01 - General Fuel Storage Facility Sabotage "Threat"Checklist

16.01.1 General

A. The continued operation of fuel storage facilities is imperative to the successful operation of an airline.Any threat to these facilities must immediately be reported to the local airport security authority andAmerican Airlines System Operations Control (SOC) at 817-967-8000.

B. Should the threat to the operation of a fuel storage facility be communicated via telephone, an importantconsideration is the personal "profile" of the caller.

C. The following check list is included as an essential guideline to assist the appropriate authorities inestablishing a personal "profile" of the caller or perpetrator.

D. Refer to the AA Safety, Security and Environmental Policy & Procedures Manual (located on Jetnet)for more information.

Figure 16.01-1: Sabotage Threat Checklist

END

Section 16.01General Fuel Storage Facility Sabotage "Threat"Checklist


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Table of contents

17.01 FUELING MANUAL A319/A320GENERAL..........................................................................................................................1UNDERWING PRESSURE FUELING (AUTOMATIC OPERATION).................................3UNDERWING PRESSURE FUELING (MANUAL OPERATION).......................................8UNDERWING PRESSURE FUELING (WITHOUT ELECTRICAL POWER).....................9TANK-TO-TANK GROUND TRANSFER OF FUEL.........................................................11PROCEDURE TO USE THE ADIRU TO FIND THE PITCH AND ROLL DATA...............12PROCEDURE TO USE THE FQIC INPUT PARAMETERS TO FIND THE PITCH ANDROLL DATA......................................................................................................................13REFUELING WITH INOPERATIVE FUELING QUANTITY INDICATORS......................13USE OF MAGNETIC LEVEL INDICATORS (MLI)...........................................................15DEFUELING....................................................................................................................20

17.02 FUEL QUANTITY - MAGNETIC LEVEL INDICATORS (MLI)GENERAL..........................................................................................................................1

TOCFueling Manual - A319/A320


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Section 17.01 - Fueling Manual A319/A32017.01.1 General

A. The fuel system has two main tanks and one center tank. There is also a vent surge tank located ineach wing, outboard of the wing tank.1. For aircraft 001-100:

a. Center tank has an approximate volume of 2,179 US gal.b. Main (wing) tanks each have an approximate volume of 2,103 US gal.

2. For aircraft 125-128:a. Center tank has an approximate volume of 2,180 US gal.b. Main (wing) tanks each have an approximate volume of 2,108 US gal.

3. For aircraft 102-105, 107-114, 117-119, 121-124, 601-601, 604-604, 640-640, 647-647, 649-665,667-669, 673-705, 708-717, 721-725, 730-730, 732-733, 737-738, 740-742, 744-758, 760-760,762-799, 801-810, 812-899:a. Center tank has an approximate volume of 2,180 US gal.b. Main (wing) tanks each have an approximate volume of 2,062 US gal.

NOTE : Maximum fuel weight capacity will vary depending on fuel density.

NOTE : The use of JP-4 or Jet B is prohibited on all A319/A320 aircraft.

NOTE : Fuel trucks/tankers are not to be disconnected from the aircraft until all fuelingdiscrepancies have been cleared.

B. Pressure Fueling1. The airplane is equipped with one pressure fueling receptacle, which is located in the right-midwing

leading edge, approximately 11 feet from ramp level. Refer to Figure 17.01-5.2. The airplane is equipped with one fueling control panel, which is located in the lower fuselage,

inboard of the right wing root or in the right-mid-wing leading edge (depending on aircraftconfiguration). Access to the control panel is through a hinged access door, approximately 6 feetfrom ramp level. The control panel is used for controlling and monitoring the pressure fuelingoperation and contains fuel quantity indicators and switches. Refer to Figure 17.01-3 andFigure 17.01-4.

3. For normal refueling operations, the airplanemust be refueled in the automatic pre-selectedmode. The automatic mode allows all tanks to receive fuel simultaneously and beautomatically filled in the proper order.

4. External or APU electrical power should be used for pressure fueling operations. If external orAPU power sources are not available, the airplane battery may be used as a power source.

C. Gravity FuelingNOTE : Not all A319/320 aircraft are equipped with overwing fill ports.

1. Overwing fueling of the A319/320 aircraft can be performed at stations which are properly equippedto safely perform gravity overwing fueling.

2. The A319/320 has overwing fill ports located on the LEFT and RIGHT wing tanks only. Refer toFigure 17.01-1.

3. Fuel is sent directly into the outer cell of each wing tank from which the inner cell is filled byopening the inter-cell transfer valves.

4. The center tank is not equipped with an overwing port and must be fueled directly by the pressurefueling method or indirectly by fuel transfer from the wing tank(s) .

Section 17.01Fueling Manual A319/A320


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NOTE : The operation of the inter-cell transfer valves must be performed by Maintenancepersonnel.

5. When overwing fueling, the fuel nozzle must extend long enough to reach the bottom of the fueltank. This is essential to reducing the static-producing characteristics of the fuel to the lowestpossible level.

6. It is imperative that, when overwing fueling is performed, precautions are taken that will not allowfuel to ‘waterfall’ into the fuel tank.CAUTION: NO PERSON SERVICING OR CHECKING ANY FUEL TANK WILL HAVE

LOOSE OBJECTS SUCH AS TOOLS, PENCILS, MATCHES, STEEL CLEATSHOES, ETC. ON THEIR PERSON THAT CAN FALL INTO A FUEL TANK ORSCRATCH THE WING SURFACE DURING THE FUELING OPERATION.

CAUTION: IF ANY OBJECT IS DROPPED INTO THE FUEL TANK, NOTIFY AIRCRAFTMAINTENANCE IN PERSON IMMEDIATELY.

7. Aircraft fueling requirements and limitations:a. Wing tanks must have equal amounts of fuel in each wing after the completion of fueling.b. Fuel tanks may be fueled individually or simultaneously.

Figure 17.01-1: Overwing Fuel Port and Ground Location

D. Fuel Quantity Measuring1. The primary measuring devices used in determining fuel quantity are the cockpit and lower

fuselage or wing (depending on aircraft configuration) fuel quantity indicators. The lower fuselagefuel or wing quantity indicators, located on the control panel, are used during normal fuelingoperations. Refer to Figure 17.01-3 and Figure 17.01-4.



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2. An alternate means of determining and/or verifying fuel quantity may be obtained by the use ofmagnetic level indicators (fuel measuring sticks) located on the bottom of each inner/outer wingtank and center tank. Refer to Figure 17.01-9.

E. If the Fuel Quantity Indication (FQI) system is in degraded mode (any quantity gauge indication isdisplayed with two dashes across the last two digits on the EWD), contact Aircraft Maintenance inperson for handling per Minimum Equipment List (MEL) Chapter 28.WARNING: 1. DONOTOPERATE THE FUEL TANKER/PUMPUNIT UNTIL THEOPERATION

OF THE WEATHER RADAR IS STOPPED.2. GROUND EQUIPMENT SHALL NOT BE POSITIONED UNDER WING TIPS

DURING FUELING OPERATION.3. FUELING VEHICLEMUST BE PROPERLY BONDED TO AIRCRAFT BEFORE

ANY FUELING OR DEFUELING OPERATION.4. WHENTHERE ISAN INACCURATE/INOPERATIVEGAUGE,ORASUSPICION

OF A GAUGE NOT INDICATING PROPERLY, STOP FUELING AND NOTIFYAIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON.NOTE : IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARD

AS BEING INOPERATIVE, AIRCRAFT MAINTENANCE DOES NOTNEED TO BE NOTIFIED UNLESS SPECIFIC PROCEDURESDURING FUELING OPERATIONS REQUIRE THE ATTENTION OFAIRCRAFT MAINTENANCE.

5. IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION,NOTIFYAIRCRAFTMAINTENANCE IMMEDIATELY INPERSON.DO NOT START OR RESUME FUELING OPERATIONS UNTIL CORRECTIVEACTION HAS BEEN TAKEN.

6. MUST COMPLETE A NORMAL APU SHUTDOWN IF A FUEL SPILL HASOCCURRED DURING THE REFUEL/DEFUEL PROCEDURE.

7. DEFUELING OR TRANSFERRING FUEL WITH PASSENGERS ONBOARDTHE AIRCRAFT IS PROHIBITED EXCEPT UNDER CERTAIN CONDITIONS.REFER TO SECTION 12.01.

17.01.2 Underwing Pressure Fueling (Automatic Operation)

A. The following method (automatic pre-select) must be used for all normal refueling operations. Makesure all refuel/defuel valve switches are in the NORM position prior to, and during, refueling.NOTE : During automatic fueling, the outer tanks receive fuel first. If the selected fuel quantity

exceeds the wing tank capacity, the center tank is refueled simultaneously.

B. Obtain the jet fuel service record. Refer to Section 15.01.C. Position the fuel vehicle.D. Bond the fueling vehicle to the aircraft. Refer to Figure 17.01-2.

NOTE : The bonding points are located on each main landing gear shock strut.



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Figure 17.01-2: MLG Bonding Point Location



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Figure 17.01-3: Fueling Control Panel



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E. Remove the refuel coupling cap. Refer to Figure 17.01-5.F. Connect the coupling of the fuel supply hose to the aircraft refuel/defuel coupling.G. Open the access door 192MB or 622KB. Refer to Figure 17.01-3 and Figure 17.01-4.

1. Electrical power is supplied to the refuel control panel when the access door is opened.NOTE : After the refuel control panel access door has opened, if you use refuel battery power

only, it is not possible to start the refuel sequence until after approximately 35 - 40seconds. This is because the Fuel Quantity Indication Computer (FQIC) and FLSSBITE sequences operate first. Do not keep the door open longer than necessary,because the battery can discharge.

H. Access the refuel/defuel control panel 800VU/801VU.I. Perform the test of the refuel panel 800VU/801VU.

1. Place TEST switch to the LTS position and hold. Verify the following:



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a. HI LVL lights and the DEFUELER/XFR OPEN lights are on and the CKPT and END lightscome on.

b. FUEL QTY, PRESELECTED and ACTUALLY displays show all (8s).c. Release the TEST switch and verify the following:

(1) Lights go back to their initial condition.(2) FUEL QTY, PRESELECTED and ACTUAL displays go back to their initial condition.

2. Place TEST switch in HIGH position and hold.a. Make sure that HI LVL lights change condition. (If they were on, they will go off. If they were

off, they will come on.)b. Release the TEST switch.

(1) Make sure that HI LVL lights go back to their initial condition.J. On the refuel/defuel control panel 800VU/801VU:

1. Make sure that the REFUEL VALVES switches are in the NORM position.a. Place the PRESELECTED rocker switch to the INC position and hold.b. Make sure that the number on the PRESELECTED display increases.c. When the PRESELECTED display shows the required fuel load, release the switch.

K. Set the MODE SELECT switch to the REFUEL position. Refer to Figure 17.01-3 and Figure 17.01-4.L. Record FUEL QUANTITY in each tank in the GAUGE READING BEFORE FUELING LBS. spaces

on the fuel slip. Refer to Section 15.01.CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM SAFE

PRESSURE OF 50 PSI (3.45 BAR).

M. Start the pump on the fuel tanker/pump unit.N. Make sure that the numbers on the FUELQTY indicator and the ACTUAL preselector display increases.

NOTE : Aircraft will have a final recomputation prior to the END light illuminating. During this time,fuel will stop and then resume.

O. When the refuel operation is complete (refer to Figure 17.01-3 and Figure 17.01-4), make sure that:1. The END light comes on.2. The numbers on the ACTUAL and the PRESELECTED displays are stable and the same +/-

100kg (220.5 lb).3. The FUEL QTY display for each tank shows the fuel is divided correctly between the tanks.4. If the tanks are full, the HI LVL lights come on.

P. Stop the pump on the fuel tanker/pump-unit.Q. Put the MODE SELECT switch to the OFF-and guarded position.R. Legibly complete all applicable fields on the Jet Fuel service record (fuel slip). Refer to Section 15.01.S. Disconnect the coupling from the fuel supply from the aircraft refuel/defuel coupling.T. Install the refuel coupling cap 41QM.

CAUTION: MAKESURETHEHANDLEOFTHEREFUELCOUPLINGCAPPOINTSAFTWHENTHE CAP IS CLOSED AND LOCKED.

U. Close the access door 192MB or 622KB. Refer to Figure 17.01-3 and Figure 17.01-4.V. Disconnect aircraft and fueling vehicle bonding cable.



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17.01.3 Underwing Pressure Fueling (Manual Operation)

A. This procedure does not set the fuel quantity to be put on the airplane. The automatic fuel shutoffcontrol will close each refuel valve when the fuel tanks are full. To stop refueling at a specific fuelquantity shown on the FUEL QTY display, put the REFUEL VALVE CONTROL to the CLOSE position.The LOAD SEL display will be off.

B. Obtain the jet fuel service record. Refer to Section 15.01.C. Position the fuel vehicle.D. Bond the fueling vehicle to the aircraft. Refer to Figure 17.01-2.E. Remove the refuel coupling cap 41QM. Refer to Figure 17.01-5.F. Connect the coupling of the fuel supply hose to the aircraft refuel/defuel coupling.G. Open the access door 192MB ro 622KB. Refer to Figure 17.01-3 and Figure 17.01-4.H. Perform the test of the refuel panel 800VU/801VU.

1. Place TEST switch to the LTS position and hold. Verify the following:a. High (HI) LVL lights and the DEFUEL/XFROPEN lights are on and the CKPT and END lights

come on.b. FUEL QTY, PRESELECTED and ACTUAL displays show all (8s).c. Release the TEST switch and verify the following:


2. Place TEST switch to the HIGH position and hold.a. Make sure that HI LVL lights change their condition. (If they were on, they will go off. If they

were off, they will come on.)b. Release the TEST switch.

(1) Make sure that the HI LVL lights go back to their initial condition.I. On the refuel/defuel control panel 800VU:

1. Place the MODE SELECT switch to the REFUEL position.2. Place the REFUEL VALVES switch(es) for the applicable fuel tank(s) to the OPEN position.3. Place the REFUEL VALVES switch(es) for the tank(s) which will not be refueled to the SHUT

position.NOTE : If REFUEL VALVE switches secured in NORM position using safety wire, Maintenance

to cut safety wire to select OPEN/SHUT position for refuel valve switches.

J. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS" spaceson the fuel slip. Refer to Section 15.01.

K. Start the pump on the fuel tanker/pump unit.CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM SAFE

PRESSURE OF 50PSI (3.45 BAR).

L. On the refuel/defuel control panel 800VU:1. Make sure the numbers on the FUEL QTY indicator and ACTUAL preselector displays increase.2. Monitor the FUEL QTY displays.3. When each tank has the correct fuel quantity, place the REFUEL VALVE switch to the SHUT

position.M. When the fuel tank quantities are correct, stop the pump on the fuel tanker/pump unit.N. On the refuel/defuel control panel 800VU:



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1. Put the MODE SELECT switch to the OFF position and close the guard on the switch.2. Put the applicable REFUEL VALVES switch(es) to the NORM position and close the guard(s) on

the switch(es).NOTE : Maintenance to re-install safety wire MS20995C20 on the refuel valve switches.

O. Disconnect the coupling of the fuel supply hose from the aircraft refuel/defuel coupling.P. Install the coupling cap 41QM. Refer to Figure 17.01-5.


Q. Legibly complete all applicable fields on the Jet Fuel service record (fuel slip). Refer to Section 15.01.R. Close the access door 192MB or 622KB. Refer to Figure 17.01-3 and Figure 17.01-4.S. Disconnect aircraft and fueling vehicle bonding cables.

17.01.4 Underwing Pressure Fueling (Without Electrical Power)

NOTE : Contact Aircraft Maintenance in person.

CAUTION: WITH FUELING VALVE(S) MANUALLY OPENED, THERE IS NO ELECTRICALPROTECTION TO PREVENT OVERFILL FUEL SPILLS.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft. Refer to Figure 17.01-2.D. Remove the refuel coupling cap and open the access panel.

1. Remove the refuel coupling cap 41QM. Refer to Figure 17.01-5.2. Open the applicable access panel 522JB (622JB).

E. Connect the coupling of the fuel supply hose to the aircraft refuel/defuel coupling.F. Release the Magnetic Level Indicators (MLI) of the tanks to be refueled. Refer to Section 17.01.8.G. If the intercell transfer valves (if installed) are open:

1. The inner and outer cells of the wing tanks fill together.2. The full capacity of the wing tank is less than normal.

WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEARTHE ENDOF THEREFUEL. BECAUSE THERE IS NO ELECTRICAL POWER,THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT OPERATE.

CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUMSAFE PRESSURE OF 50 PSI (3.45BAR).

H. Start the pump on the fuel tanker/pump unit.I. Push and hold in the manual plunger(s) on the refuel valve(s) of the applicable fuel tank(s).J. Use the MLIs to monitor the quantity of fuel in each tank.

NOTE : Refer to the fuel tables for the maximum capacity of each fuel tank and for the total fuelcapacity. If the intercell transfer valves are open, the full capacity of a wing tank is less thannormal.

NOTE : Make sure the outer wing fuel tanks are full. This will prevent the risk of structural damage.

K. When the quantity of fuel in a tank is correct, release the manual plunger on the related refuel valve.L. When all the fuel quantities are correct, stop the pump on the fuel tanker/pump unit.



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M. Make an entry in the Aircraft Maintenance Logbook (AML) logbook to check the fuel configurationbefore the subsequent flight.

N. Retract and lock the MLIs.O. Disconnect the coupling of the fuel supply hose from the aircraft refuel coupling.P. Install the coupling cap and close the access panel.


1. Install the refuel coupling cap 41QM. Refer to Figure 17.01-5.2. Close the applicable access panel 522JB (622JB).

Q. Legibly complete all applicable fields on the Jet Fuel service record (fuel slip). Refer to Section 15.01.R. Disconnect aircraft and fueling vehicle bonding cable.



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Figure 17.01-5: Pressure Fueling Receptacle

17.01.5 Tank-to-Tank Ground Transfer of Fuel

NOTE : Contact the Flight Crew or Aircraft Maintenance in person. Refer to AMM Section28-25-00-869-001-A, "Aircraft Fuel Transfer Procedure."



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Figure 17.01-6: Cockpit Fueling Controls

17.01.6 Procedure to Use the ADIRU to Find the Pitch and Roll Data

NOTE : Contact Flight Crew or Aircraft Maintenance in person. (Refer to AMMTask 12-11-28-860-001-A).

1. In Table 17.01-1, use the PITCH data to find the equivalent number.2. In Table 17.01-1, use the ROLL data to find the equivalent letter.3. Put together the number and the letter to identify the square to use in the MLI procedure.

Table 17.01-1: Table 1

RefRollRefPitch



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Aminus 1.51minus 1.5

Bminus 1.02minus 1.0

Cminus 0.53minus 0.5

D0.040.0

Eplus 0.55plus 0.5

Fplus 1.06plus 1.0

Gplus 1.57plus 1.5

17.01.7 Procedure to Use the FQIC Input Parameters to Find the Pitch and Roll Data

NOTE : Contact Flight Crew or Aircraft Maintenance in person. Refer to AMM Task 12-11-28-860-002-A.

A. In Table 17.01-1, use the PITCH data to find the equivalent number.B. In Table 17.01-1, use the ROLL data to find the equivalent letter.C. Put together the number and the letter to identify the square to use in the Magnetic Level Indicator

(MLI) procedure. Refer to AMM Task 12-11-28-650-007.D. Put the aircraft back to its initial configuration.

17.01.8 Refueling with Inoperative Fueling Quantity Indicators

A. Method 1 - For use when the flight deck fuel quantity display is operational and one or more of theunderwing panel fuel quantity displays are inoperative. Refer to Section 15.01.5.1. Individual fuel tank quantity may be determined by the respective cockpit display for the inoperative

lower fuselage/underwing panel fuel indicator, provided respective cockpit display is verifiedoperational. Verification of fuel quantity, by measuring stick, is not required with Method 1. Useof Method 1 will be noted on the Jet Fuel service record (fuel slip), with a copy of the fuel slipprovided to the Flight Crew as early as practicable after fueling.

B. Method 2 - For use on main tanks (wings) and center tanks when the flight deck fuel quantity displayis inoperative, one or more of the underwing panel fuel quantity displays are inoperative and fuel onboard can be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.5.1. Determine the aircraft attitude. Refer to Section 17.01.6 or Section 17.01.7.2. Before fueling, determine existing fuel tank quantity with the measuring stick(s) of the affected

tank. Refer to Section 17.01.9. Subtract this from the tank quantity required and convert to gallons.Fuel the tank to desired level, using the equipment meter. Use measuring(s) to verify tank quantity.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons. Refer

to Section 15.01.7 to deliver the desired known quantity.

3. Provide Flight Crew with completed copy of the Jet Fuel service record (fuel slip) and an InoperativeFuel Quantity Indicator service record making sure that all required entries and signatures arelegible and in place as early as practicable, before departure.

C. Method 3 - For use on main tanks (wings) and center tanks when the flight deck fuel quantity displayis inoperative, one or two of the underwing panel fuel quantity displays are inoperative and fuel onboard cannot be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.5. To fuel the aircraft with inoperative fueling control panel quantity indicators,refer to Section 17.01.9.



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1. Completely defuel tank with inoperative indicator by transferring fuel to other tank(s) or defueling.Refer to Section 17.01.5.

2. Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged by the fuelequipment meter reading. Alternately, transfer fuel from tanks(s) with operative indicator. Referto Section 17.01.5.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons. To

deliver the desired known quantity, refer to Section 15.01.7.

3. Fill tanks(s) with operative indicator to quantity of fuel required.4. Determine the aircraft attitude. Refer to Section 17.01.6 or Section 17.01.7.5. Use measuring sticks(s) to verify tank quantity with the inoperative quantity indicator.6. Provide Flight Crew with completed copy of the Jet Fuel service record (fuel slip) and an Inoperative

Fuel Quantity Indicator service record that makes sure that all required entries and signaturesare legible and in place as early as practicable, before departure.

D. Anytime fuel quantity is determined by measuring stick, the following procedure must be used:1. Determine the method, 2 or 3, (refer to Section 17.01.8) to be used to fuel the aircraft and check

the applicable box on the Inoperative Fuel Quantity Indicator Service Record.a. When using method 2, perform the following:

(1) Determine:a) The aircraft attitude before fueling.b) Tank stick(s) needed to measure the fuel quantity and associated charts to determine

the pounds in the affected tank.(2) Record the before fueling information where applicable on the fuel slip and Inoperative

Fuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (for example L,

LI, C, ACT1, Trim, etc.) in the space provided below "TANK."b) Record the before fueling aircraft attitude (pitch and roll).c) Circle the stick(s) utilized before fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only).d) Record the units/inches read from the applicable stick(s) in the before fueling spaces.e) Record the before fueling quantity from the applicable stick chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.(3) Fuel the tank to the desired amount by delivering a known quantity.(4) Determine:

a) The aircraft attitude after fueling.b) Tank stick(s) needed to measure the fuel quantity and associated charts to determine

the after fueling pounds in the affected tank.(5) Record the after fueling information where applicable on the fuel slip and Inoperative

Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only).c) Record the units/inches read from the applicable stick(s) in the after fueling spaces.d) Record the after fueling quantity from the applicable stick chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.



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e) Make sure all sticks are secured and initial where applicable; print your name,present title and company name followed by your complete signature (no initials).

f) Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.(6) The stick reading in inches and conversion to pounds must be verified by a cockpit crew

member by reviewing the completed fuel slip and Inoperative Fuel Quantity Indicatorservice record.

b. When using method 3, perform the following:(1) Empty the affected tank by defueling or transferring all remaining fuel to other tanks.

Refer to Section 17.01.10 or Section 17.01.5.(2) Record the before fueling information where applicable on the fuel slip and Inoperative

Fuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (for example, L,

LI, C, ACT1, Trim, etc.) in the space provided below "TANK."b) Leave the before fueling aircraft attitude (pitch and roll) spaces blank and do not

circle any stick(s) used before fueling & applicable inner/outer cell tanks.c) Record the before fueling quantity of zero pounds on the fuel slip and the Inoperative

Fuel Quantity Indicator Service Record.(3) Fuel the tank to the desired amount by delivering a known quantity.(4) Determine:



Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) & applicable inner/outer cell


fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Make sure all sticks are secured and initial where applicable; print your name,

present title and company name followed by your complete signature (no initials).f) Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.

(6) The stick reading in inches and conversion to pounds must be verified by a cockpit crewmember by reviewing the completed fuel slip and Inoperative Fuel Quantity Indicatorservice record.

17.01.9 Use of Magnetic Level Indicators (MLI)

NOTE : For MLI, refer to Figure 17.01-9.

A. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), aVendor Supervisor, Lead or Supervisor/Lead, or Designated Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

B. Open the access door 192MB or 622KB. Refer to Figure 17.01-3 and Figure 17.01-4.NOTE : If operating in battery power, do not keep the door open longer than necessary because

the battery can discharge.



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C. Obtain from Aircraft Maintenance or the Flight Crew and write down the aircraft attitude figure.D. Use of the Magnetic Level Indicators (MLI)

1. Use the flow chart and do these steps: (Refer to Figure 17.01-7, "How to Read a Wing Tank MLISHEET 1".) (Refer to Figure 17.01-8, "How to Read the CTR MLI SHEET 1".)NOTE : Depending on aircraft configuration, there are either four or five MLI in each wing tank

and one in the center tank. Refer to Figure 17.01-9.

NOTE : The MLI Stick number attitude charts outlined in Section 17.02 are applicable to both4 (sticks 2 - 5) and 5 (sticks 1 - 5) MLI per wing aircraft.

a. Use a screwdriver to push the applicable MLI and turn it through 90 degrees.b. Hold and carefully lower the MLI fully. Then carefully lift the MLI until you feel the magnets

engage.c. Read the units mark nearest to the bottom-skin of the wing and write down the number.



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Figure 17.01-7: How to Read a Wing Tank MLI



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Figure 17.01-8: How to Read the CTR MLI

2. Retract the MLI and use a screwdriver to turn it through 90 degrees to lock it.3. Find the volume of fuel in each tank as follows:

a. Use the applicable MLI stick number and the applicable aircraft attitude grid-square letter tofind the correct fuel quantity table.



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NOTE : For a grid reading of C3:1. Use the attitude monitor reading CLEFT WING column 3 for the LH wing.2. Use the attitude monitor reading CRIGHT WING column 3 for the RH wing.

b. Find the applicable MLI unit number row and the applicable aircraft attitude (grid-squareletter and number) row in the table. Find the intersection of the applicable rows to give thecorrect volume of fuel in the tank.NOTE : Only even number MLI units are listed in the tables. To calculate the volume of

fuel for uneven numbers, interpolate between the nearest even numbers in thetable.

MLI stick No. 2 (LH Wing)Example:

18:UNIT reading

C3 on (attitude monitor):Pitch and Roll attitude

1000 US gal:Fuel Quantity table reading (volume)

6.75 lb/US gal:Actual Density of fuel sample

1000 x 6.75 = 6750 lb=Actual fuel mass at 6.75 lb/US gal

NOTE : The above example is for one MLI only.

4. Add together the values for each tank to find the total volume of fuel.NOTE : The MLI are accurate to +/- 5% of their indication. This is not sufficiently accurate to

use them as data for the Fuel Quantity Indication (FQI).

5. Multiply the total volume of the fuel by the Specific Gravity of the fuel. The result is the total massof the fuel.NOTE : When the outer cell is full, it is not possible to get an accurate reading above 220 liters

(58.1174 US gallons). This is because of the MLI No. 5 position and the shape of thecell.

NOTE : At some attitudes, MLI No. 5 can only record a maximum fuel reading of 850 liters(224.5444 US gallons). The maximum capacity of the outer wing cell is 880 liters(232.4695 US gallons).

NOTE : When the aircraft is fully refueled, the maximum capacity of the inner wing cell is 6924liters (1829.1124 US gallons).

E. Complete the Fuel Slip and Inoperative Fuel Quantity Indicator service record. Refer to Section 17.01.8and Section 15.01.

F. Close the access door 192MB or 622 KB. Refer to Figure 17.01-3 and Figure 17.01-4.



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Figure 17.01-9: Magnetic Level Indicators (MLI)

17.01.10 Defueling

NOTE : AA Flight Crew or Maintenance personnel must be present and operate applicable cockpitswitches or levers. In the event that a fuel system or components there of (excluding inoperativegauge) is malfunctioning, inoperable or when assistance is required to safely perform fuelingoperations, contact AA Maintenance personnel or Station Operations through coordination withMOC when AA Maintenance personnel are not on duty for assistance. Examples of inoperativeor malfunctioning fuel system components or assistance situations include inoperativerefuel/defuel valves, inoperative transfer valves, transferring fuel, opening and closing the aircraftlanding gear doors, etc.

NOTE : Product defueled from an aircraft for purposes other than contamination should be returned tothe airline from which it was removed. Defueled product may not be delivered to anothercompany’s aircraft without its approval. Defueling aircraft directly into joint use fueling systemsis not authorized unless a procedure has been unanimously approved by all system users.

NOTE : For maintenance procedures, it is not necessary to defuel both of the wing tanks. It is possibleto have one wing tank empty and the other wing tank full.



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A. Bond the fueling vehicle to the aircraft. Refer to Figure 17.01-2.B. Open the access door 192MB or 622KB. Refer to Figure 17.01-3 and Figure 17.01-4.C. Do not spill fuel on the engines or the brakes. If you spill fuel on engines or brakes that are hot, it can

cause fires.D. Remove the refuel coupling cap 41QM. Refer to Figure 17.01-5.E. Connect the hose-coupling of the fuel tanker/pump unit to the aircraft refuel/defuel coupling.F. Make sure the fuel tanker(s) has (have) sufficient space for the fuel quantity to be defueled.G. Energize the aircraft electrical circuits. Refer to AMM Task 24-41-00-861-002.H. Energize the Electronic Centralized Aircraft Monitor (ECAM) system. Refer to AMM Task

31-60-00-860-001.I. On the ECAM Control Panel:

1. Push (in) the FUEL system page button.J. On the refuel/defuel control panel 800VU:

1. Make sure that the refuel valve switches are in the NORM and guarded position.2. Put the MODE SELECT switch to the DEFUEL XFR position and make sure the OPEN light

comes on.K. On the panel 40VU (refer to Figure 17.01-6), push (in) the X FEED P/BSW. Make sure the ON and

OPEN lights come on.L. Make sure that on the SD FUEL page, the crossfeed valve indication is shown green in-line (valve

open).WARNING: WHEN YOU OPERATE THE FUEL PUMPS DURING A MAINTENANCE

PROCEDURE, FLIGHT CREW OR A MAINTENANCE PERSON MUST BE IN THECOCKPIT. THIS PERSONMUSTSTOPTHEPUMPSWHENTHE LOWPRESSUREFAULT LIGHT(S) (ON PANEL 40VU) COME ON, TO PREVENT OPERATION OFTHE PUMP(S) WITHOUT FUEL (DRY RUNNING). OPERATION OF THE PUMPSWITHOUT FUEL CAN CAUSE A FIRE.

CAUTION: DONOT LET THE FUEL PUMPSOPERATE FORMORETHAN 15MINUTESWITHTHE FAULT LIGHT ON. THIS CAN CAUSE DAMAGE TO THE FUEL PUMPS.

M. On the panel 40VU:1. Push (in) the MODE SEL P/BSW. Make sure the MAN light of the MODE SEL P/BSW goes off

(center tank pumps now in automatic control).NOTE : You can defuel the center tank with the center tank pumps in manual control.

2. Push (in) the applicable TK PUMPS P/BSWs. Make sure the applicable P/BSW OFF lights gooff.

N. On the SD Fuel page, monitor the fuel quantity indications. Make sure the applicable fuel quantityindications and the Fuel on Board (FOB) figures decrease.NOTE : When you defuel the left wing tank only, a small quantity of fuel will go in to the right wing

tank. Because the crossfeed valve is open, fuel can go through the grooves in the suctionbypass valve.

O. When the fuel quantity has decreased to the necessary level:1. On the panel 40VU:

a. Release (out) the applicable TK PUMPS P/BSWs. Make sure the related TK PUMPS P/BSWOFF lights come on.



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b. Release (out) the MODE SEL P/BSW. Make sure the MAN light of the MODE SEL P/BSWcomes on (center tank pumps now in manual control).

2. On the SD Fuel page, make sure the tank contents become stable.P. To defuel the wing tanks until empty:

1. On the panel 40VU:a. Make sure the MODE SEL P/BSW is released (out) and the MAN light is on (center tank

pumps are in manual control).b. Push (in) the L TK PUMPS 1 and 2 (R TK PUMPS 1 and 2) P/BSWs. Make sure the applicable

P/BSW OFF I lights go off.c. Operate the L TK PUMPS 1 and 2 (R TK PUMPS 1 and 2) P/BSWs until the applicable

P/BSW FAULT light comes on.d. Release (out) the L TK PUMPS 1 and 2 (R TK PUMPS 1 and 2) P/BSWs. Make sure the

applicable P/BSW OFF lights come on and the applicable P/BSW FAULT lights go off.2. Drain the remaining fuel from the tank(s). Refer to AMM TASK 28-25-00-650-003.

Q. To defuel the center tank until empty:CAUTION: MAKE SURE A PERSON IS IN THE COCKPIT DURING A MANUAL FUEL

TRANSFER FROM THE CENTER TANK TO THE WING TANKS. THIS PERSONMUSTMONITORTHEOVERFLOWWARNINGLIGHTBECAUSETHEAUTOMATICSHUTOFFATHIGHFUELLEVEL ISOVERRIDDENDURINGMANUALTRANSFER.

1. On the panel 40VU:a. Push (in) the MODE SEL P/BSW. Make sure the MAN light of the MODE SEL P/BSW goes

off (center tank pumps now in automatic control).b. Push (in) the CTR TK PUMPS 1 and 2 P/BSWs. Make sure the OFF lights of the CTR TK

PUMPS 1 and 2 P/BSWs go off.c. Let the CTR TK PUMPS 1 and 2 operate until the FAULT lights of the CTR TK PUMPS 1

and 2 P/BSWs come on.d. On the ECAM lower DU, make sure:

(1) The CTR in-line green symbol goes off.(2) The CTR cross-line amber symbol comes on.

e. Release (out) the CTR TK PUMPS 1 and 2 P/BSWs. Make sure the applicable OFF lightscome on and the applicable FAULT lights go off.

f. Release (out) the MODE SEL P/BSW. Make sure the MAN light of the MODE SEL P/BSWcomes on (center tank pumps now in manual control).

2. Drain the remaining fuel from the center tank. Refer to AMM TASK 28-25-00-650-003.CAUTION: BEFORE YOU CLOSE THE CROSSFEED VALVE, MAKE SURE:

- THE FUEL PUMP(S) IS (ARE) OFF.

- THE REFUEL VALVE(S) IS (ARE) IN THE CLOSED POSITION.

THIS WILL PREVENT DAMAGE TO THE CROSSFEED VALVE.

R. On the panel 40VU, release (out) the X FEED P/BSW. Make sure the ON and OPEN lights go off.S. On the SD FUEL page, make sure the crossfeed valve indication shows green gross-line (valve

closed).T. On the refuel/defuel panel 800VU:



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1. Put the MODE SELECT switch to the OFF and guarded position. Make sure the OPEN light goesoff.

U. Close the access door 192MB or 622KB. Refer to Figure 17.01-3 and Figure 17.01-4.V. De-energize the electrical circuits. Refer to AMM TASK 24-41-00-862-002.W. Disconnect the hose coupling of the fuel tanker from the aircraft.X. Install the refuel coupling cap 41QM. Refer to Figure 17.01-5.Y. Disconnect the bonding cable.

END



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Section 17.02 - Fuel Quantity - Magnetic Level Indicators (MLI)17.02.1 General

A. Refer to A319/A320 Magnetic Level Indicating (MLI) Charts as follows:1. Access the Stick Charts at http://me.aa.com/manuals/fw/FuelingStickCharts/#z.

END

Section 17.02Fuel Quantity - Magnetic Level Indicators (MLI)


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http://me.aa.com/manuals/fw/FuelingStickCharts/#z





Table of contents

18.01 FUELING MANUAL - A321GENERAL..........................................................................................................................1UNDERWING PRESSURE FUELING (AUTOMATIC OPERATION).................................3UNDERWING PRESSURE FUELING (MANUAL OPERATION).......................................7UNDERWING PRESSURE FUELING (WITHOUT ELECTRICAL POWER).....................9GRAVITY OVERWING FUELING....................................................................................11TANK-TO-TANK GROUND TRANSFER OF FUEL.........................................................12PROCEDURE TO USE THE ADIRU TO FIND THE PITCH AND ROLL DATA...............13PROCEDURE TO USE THE FQIC INPUT PARAMETERS TO FIND THE PITCH ANDROLL DATA......................................................................................................................13REFUELING WITH INOPERATIVE FUELING QUANTITY INDICATORS......................13USE OF MAGNETIC LEVEL INDICATORS (MLI)...........................................................17DEFUELING....................................................................................................................22

18.02 FUEL QUANTITY - MAGNETIC LEVEL INDICATORS

TOCFueling Manual - A321


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Section 18.01 - Fueling Manual - A32118.01.1 General

A. The fuel system has two main tanks, one center tank, and if equipped, one or two Additional CenterTanks (ACTs). There is also a vent surge tank located in each wing, outboard of the wing tank.1. For aircraft 161-163, 165, 167, 169-174, 176-193, 507-510, 519-521, 523-524, 534-573, 575-576,

578-599, 783-800, 850-910, 911-950 and 986-999:a. Center tank has an approximate volume of 2,166 US gal.b. Main (wing) tanks each have an approximate volume of 2,047 US gal.c. If equipped, each ACT has an approximate volume of 790 US gal.

2. For aircraft 150-159 and 194-300:a. Center tank has an approximate volume of 2,166 US gal.b. Main (wing) tanks each have an approximate volume of 2,094 US gal.c. If equipped, each ACT has an approximate volume of 790 US gal.


NOTE : The use of JP-4 or Jet B is prohibited on all A321 aircraft.

NOTE : Fuel trucks/tankers are not to be disconnected from the aircraft until all fuelingdiscrepancies have been cleared.

B. Pressure Fueling1. The airplane is equipped with one pressure fueling receptacle, which is located in the right-midwing

leading edge, approximately 11 feet from ramp level. Refer to Figure 18.01-6.2. The airplane is equipped with one fueling control panel, which is located in the lower fuselage,

inboard of the right wing root or in the right-midwing leading edge (depending on aircraftconfiguration). Access to the control panel is through a hinged access door, approximately 6 feetfrom ramp level respectively. The control panel is used for controlling and monitoring the pressurefueling operation and contains fuel quantity indicators and switches. Refer to Figure 18.01-4 andFigure 18.01-5.

3. For normal refueling operations, the airplanemust be refueled in the automatic pre-selectedmode. The automatic mode allows all tanks to receive fuel simultaneously and beautomatically filled in the proper order.


C. Gravity FuelingNOTE : Not all A321 aircraft are equipped with overwing fill ports.

1. Overwing fueling of the A321 aircraft can be performed at stations which are properly equippedto safely perform gravity overwing fueling.

2. The A321 has overwing fill ports located on the LEFT and RIGHT wing tank only. Refer toFigure 18.01-2.

3. Fuel is sent directly into the outer cell of each wing tank from which the inner cell is filled byopening the inter-cell transfer valves.

4. The center tank is not equipped with an overwing port and must be fueled directly by the pressurefueling method or indirectly by fuel transfer from the wing tank(s).NOTE : The operation of the inter-cell transfer valves must be performed by Maintenance

personnel.

Section 18.01Fueling Manual - A321


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5. When overwing fueling, the fuel nozzle must be extended long enough to reach the bottom ofthe fuel tank. This is essential to reducing the static-producing characteristics of the fuel to thelowest possible level.

6. It is imperative that, when overwing fueling is performed, precautions are taken that will not allowfuel to "waterfall" into the fuel tank.CAUTION: NO PERSON SERVICING OR CHECKING ANY FUEL TANK WILL HAVE

LOOSE OBJECTS SUCH AS TOOLS, PENCILS, MATCHES, STEEL CLEATSHOES, ETC. ON THEIR PERSON THAT CAN FALL INTO A FUEL TANK ORSCRATCH THE WING SURFACE DURING THE FUELING OPERATION.

CAUTION: IF ANY OBJECT IS DROPPED INTO THE FUEL TANK, NOTIFY AIRCRAFTMAINTENANCE IN PERSON IMMEDIATELY.

7. Aircraft fueling requirements and limitations:a. Wing tanks must have equal amount of fuel in each wing after the completion of fueling.b. Fuel tanks may be fueled individually or simultaneously.

D. Fuel Quantity Measuring1. The primary measuring devices used in determining fuel quantity are the cockpit and lower

fuselage or wing (depending on aircraft configuration) fuel quantity indicators. The lower fuselageor wing fuel quantity indicators, located on the control panel, are used during normal fuelingoperations. Refer to Figure 18.01-4 and Figure 18.01-5.

2. An alternate means of determining and/or verifying fuel quantity may be obtained by the use ofmagnetic level indicators (fuel measuring sticks) located on the bottom of each inner/outer wingtank and center tank. Refer to Figure 18.01-11.

E. If the Fuel Quantity Indication (FQI) system is in degraded mode (any quantity gauge indication isdisplayed with two dashes across the last two digits on the EWD), contact Aircraft Maintenance forhandling per Minimum Equipment List (MEL) Chapter 28.WARNING: 1. DONOTOPERATE THE FUEL TANKER/PUMPUNIT UNTIL THEOPERATION

OF THE WEATHER RADAR IS STOPPED.2. GROUND EQUIPMENT SHALL NOT BE POSITIONED UNDER WING TIPS

DURING FUELING OPERATION.3. FUELING VEHICLEMUST BE PROPERLY BONDED TO AIRCRAFT BEFORE

ANY FUELING OR DEFUELING OPERATION.4. WHENTHERE ISAN INACCURATE/INOPERATIVEGAUGE,ORASUSPICION

OF A GAUGE NOT INDICATING PROPERLY, STOP FUELING AND NOTIFYAIRCRAFT MAINTENANCE IMMEDIATELY.NOTE : IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARD

AS BEING INOPERATIVE, AIRCRAFT MAINTENANCE DOES NOTNEED TO BE NOTIFIED UNLESS SPECIFIC PROCEDURESDURING FUELING OPERATIONS REQUIRE THE ATTENTION OFAIRCRAFT MAINTENANCE.

5. IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION, NOTIFY AIRCRAFT MAINTENANCE IMMEDIATELY. DO NOTSTART OR RESUME FUELING OPERATIONS UNTIL CORRECTIVE ACTIONHAS BEEN TAKEN.

6. MUST COMPLETE A NORMAL APU SHUTDOWN IF A FUEL SPILL HASOCCURRED DURING THE REFUEL/DEFUEL PROCEDURE.



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7. DEFUELING OR TRANSFERRING FUEL WITH PASSENGERS ONBOARDTHE AIRCRAFT IS PROHIBITED EXCEPT UNDER CERTAIN CONDITIONS.REFER TO SECTION 12.01.

Figure 18.01-1: Usable Fuel Tank Capacities


A. The following method (automatic pre-select) must be used for all normal refueling operations. Makesure all refuel/defuel valve switches are in the NORM position prior to, and during, refueling.NOTE : During automatic fueling, the outer tanks receive fuel first. If the selected fuel quantity

exceeds the wing tank capacity, the center tank is refueled simultaneously.

B. Obtain the jet fuel service record. Refer to Section 15.01.

Figure 18.01-2: Gravity Refuel Cap

C. Position the fuel vehicle.D. Bond the fueling vehicle to the aircraft. Refer to Figure 18.01-3.



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NOTE : The bonding points are located on each main landing gear shock strut.



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Figure 18.01-3: MLG Bonding Point Location




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E. Remove the refuel coupling cap. Refer to Figure 18.01-6.F. Connect the coupling of the fuel supply hose to the aircraft refuel/defuel coupling.G. Open the access door 192MB or 622KB. Refer to Figure 18.01-4 and Figure 18.01-5.

1. Electrical power is supplied to the refuel control panel when the access door is opened.NOTE : After the refuel control panel access door has opened, if you use refuel battery power

only, it is not possible to start the refuel sequence until after approximately 35 - 40seconds. This is because the Fuel Quantity Indication Computer (FQIC) and FLSSBITE sequences operate first. Do not keep the door open longer than necessary,because the battery can discharge.

H. Access the refuel/defuel control panel 800VU/801VU.I. Perform the test of the Refuel Panel 800VU/801VU.

1. Place TEST switch to the LTS position and hold. Verify the following:a. HI LVL lights and the DEFUELER/XFR OPEN lights are on and the CKPT and END lights

come on.



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b. FUEL QTY, PRESELECTED and ACTUALLY displays show all (8s).c. Release the TEST switch and verify the following:


2. Place TEST switch in HIGH position and hold.a. Make sure that HI LVL lights change condition. (If they were on, they will go off. If they were

off, they will come on.)b. Release the TEST switch.

(1) Make sure that HI LVL lights go back to their initial condition.J. On the refuel/defuel control panel 800VU/801VU:

1. Make sure that the REFUEL VALVES switches are in the NORM position.a. Place the PRESELECTED rocker switch to the INC position and hold.b. Make sure that the number on the PRESELECTED display increases.c. When the PRESELECTED display shows the required fuel load, release the switch.

K. Set the MODE SELECT switch to the REFUEL position. Refer to Figure 18.01-4 and Figure 18.01-5.L. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS" spaces

on the fuel slip. Refer to Section 15.01.CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM SAFE

PRESSURE OF 50 PSI (3.45 BAR).

M. Start the pump on the fuel tanker/pump unit.N. Make sure that the numbers on the FUELQTY indicator and the ACTUAL preselector display increases.

NOTE : Aircraft will have a final recomputation prior to the END light illuminating. During this time,fuel will stop and then resume.

O. When the refuel operation is complete (refer to Figure 18.01-4 and Figure 18.01-5), make sure that:1. The END light comes on.2. The numbers on the ACTUAL and the PRESELECTED displays are stable and the same +/-

100kg (220.5 lb).3. The FUEL QTY display for each tank shows the fuel is divided correctly between the tanks.4. If the tanks are full, the HI LVL lights come on.

P. Stop the pump on the fuel tanker/pump-unit.Q. Put the MODE SELECT switch to the OFF-and guarded position.R. Legibly complete all applicable fields on the Jet Fuel service record (fuel slip). Refer to Section 15.01.S. Disconnect the coupling from the fuel supply from the aircraft refuel/defuel coupling.T. Install the refuel coupling cap 41QM.


U. Close the access door 192MB or 622KB . Refer to Figure 18.01-4 and Figure 18.01-5.V. Disconnect aircraft and fueling vehicle bonding cable.


A. This procedure does not set the fuel quantity to be put on the airplane. The automatic fuel shutoffcontrol will close each refuel valve when the fuel tanks are full. To stop refueling at a specific fuel



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quantity shown on the FUEL QTY display, put the REFUEL VALVE CONTROL to the CLOSE position.The LOAD SEL display will be off.

B. Obtain the jet fuel service record. Refer to Section 15.01.C. Position the fuel vehicle.D. Bond the fueling vehicle to the aircraft. Refer to Figure 18.01-3.E. Remove the refuel coupling cap 41QM. Refer to Figure 18.01-6.F. Connect the coupling of the fuel supply hose to the aircraft refuel/defuel coupling.G. Open the access door 192MB or 622KB . Refer to Figure 18.01-4 and Figure 18.01-5.H. Perform the test of the refuel panel 800VU/801VU.

1. Place TEST switch to the LTS position and hold. Verify the following:a. High (HI) LVL lights and the DEFUEL/XFROPEN lights are on and the CKPT and END lights

come on.b. FUEL QTY, PRESELECTED and ACTUAL displays show all (8s).c. Release the TEST switch and verify the following:


2. Place TEST switch to the HIGH position and hold.a. Make sure that HI LVL lights change their condition. (If they were on, they will go off. If they

were off, they will come on.)b. Release the TEST switch.

(1) Make sure that the HI LVL lights go back to their initial condition.I. On the refuel/defuel control panel 800VU:

NOTE : If refuel valve switches secured in NORM position using safety wire, Maintenance to cutsafety wire to select OPEN/SHUT position for refuel valve switches.

1. Place the MODE SELECT switch to the REFUEL position.2. Place the REFUEL VALVES switch(es) for the applicable fuel tank(s) to the OPEN position.3. Place the REFUEL VALVES switch(es) for the tank(s) which will not be refueled to the SHUT

position.J. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS" spaces

on the fuel slip. Refer to Section 15.01.K. Start the pump on the fuel tanker/pump unit.

CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUM SAFEPRESSURE OF 50PSI (3.45 BAR).

L. On the refuel/defuel control panel 800VU/801VU:1. Make sure the numbers on the FUEL QTY indicator and ACTUAL preselector displays increase.2. Monitor the FUEL QTY displays.

NOTE : Refer to the fuel table Figure 18.01-1 for the maximum capacity of each fuel tank andfor the total fuel capacity. (Refer to AMM TASK 12-11-28-650-007.)

a. To monitor the fuel quantity of the center tank, put the FQI SELECT CTR/ACT switch onpanel 801 VU to the CTR position:(1) On panel 800 VU, read the fuel quantity on the CTR FUEL QTY display.

a) To monitor the total fuel quantity of the center tank and the ACT(s), put the FQISELECT CTR/ACT switch on panel 801 VU to the CTR + ACT position:



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b) On panel 800 VU, read the fuel quantity on the CTR FUEL QTY display.b. To monitor the fuel quantity of the ACT(S), put the FQI SELECT CTR/ACT switch on panel

801 VU to each ACT position in turn.(1) On panel 800 VU, read the fuel quantity of the applicable ACT on the CTR FUEL QTY

display.3. When each tank has the correct fuel quantity, place the REFUEL VALVE switch to the SHUT

position.M. When the fuel tank quantities are correct, stop the pump on the fuel tanker/pump unit.N. On the refuel/defuel control panel 800VU/801VU:

1. Put the MODE SELECT switch to the OFF position and close the guard on the switch.2. Put the applicable REFUEL VALVES switch(es) to the NORM position and close the guard(s) on

the switch(es).NOTE : Maintenance to re-install safety wire MS20995C20 on the refuel valve switches.

O. Disconnect the coupling of the fuel supply hose from the aircraft refuel/defuel coupling.P. Install the coupling cap 41QM. Refer to Figure 18.01-6.


Q. Legibly complete all applicable fields on the Jet Fuel service record (fuel slip). Refer to Section 15.01.R. Close the access door 192MB or 622KB . Refer to Figure 18.01-4 and Figure 18.01-5.S. Disconnect aircraft and fueling vehicle bonding cables.

18.01.4 Underwing Pressure Fueling (Without Electrical Power)

NOTE : Contact Aircraft Maintenance.

CAUTION: WITH FUELING VALVE(S) MANUALLY OPENED, THERE IS NO ELECTRICALPROTECTION TO PREVENT OVERFILL FUEL SPILLS.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft. Refer to Figure 18.01-3..D. Remove the refuel coupling cap and open the access panel.

1. Remove the refuel coupling cap 41 QM. Refer to Figure 18.01-6.2. Open the applicable access panel 522 JB (622 JB).

E. Connect the coupling of the fuel supply hose to the aircraft refuel/defuel coupling.F. To find pitch and roll data, request the information from the Flight Crew. If the Flight Crew cannot

provide this information, call Aircraft Maintenance and have them find it by:1. Using Air Data Inertial Reference Unit (ADIRU) (Refer to Section 18.01.7.)2. Using FQIC (Refer to Section 18.01.8.)

G. Release the Magnetic Level Indicators (MLI) of the tanks to be refueled. Refer to Section 18.01.9.H. If the intercell transfer valves are open:

1. The inner and outer cells of the wing tanks fill together.2. The full capacity of the wing tank is less than normal.

WARNING: BE CAREFUL NOT TO FILL THE TANKS MORE THAN NECESSARY NEARTHE ENDOF THEREFUEL. BECAUSE THERE IS NO ELECTRICAL POWER,THE HIGH-LEVEL PROTECTION SYSTEM WILL NOT OPERATE.



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CAUTION: DO NOT LET THE REFUEL PRESSURE BE MORE THAN THE MAXIMUMSAFE PRESSURE OF 50 PSI (3.45 BAR).

I. Start the pump on the fuel tanker/pump unit.J. Push and hold in the manual plunger(s) on the refuel valve(s) of the applicable fuel tank(s).K. Use the MLIs to monitor the quantity of fuel in each tank.

NOTE : Refer to the fuel table Figure 18.01-1 for the maximum capacity of each fuel tank and forthe total fuel capacity. If the intercell transfer valves are open, the full capacity of a wingtank is less than normal.

NOTE : Make sure the outer wing fuel tanks are full. This will prevent the risk of structural damage.

L. When the quantity of fuel in a tank is correct, release the manual plunger on the related refuel valve.M. When all the fuel quantities are correct, stop the pump on the fuel tanker/pump unit.N. Make an entry in the Aircraft Maintenance Logbook (AML) to check the fuel configuration before the

subsequent flight.O. Retract and lock the MLIs.P. Disconnect the coupling of the fuel supply hose from the aircraft refuel coupling.Q. Install the coupling cap and close the access panel.


1. Install the refuel coupling cap 41QM. Refer to Figure 18.01-6.2. Close the applicable access panel 522JB (622JB).

R. Legibly complete all applicable fields on the Jet Fuel service record (fuel slip). Refer to Section 15.01.S. Disconnect aircraft and fueling vehicle bonding cable.



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Figure 18.01-6: Pressure Fueling Receptacle

18.01.5 Gravity Overwing Fueling

NOTE : Not all A321 aircraft are equipped with overwing fill ports.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fuel vehicle to the aircraft. Refer to Figure 18.01-3.D. On the cockpit panel 11VU, push the FUEL pushbutton switch (in) and monitor the aircraft fuel

configuration on the ECAM Fuel System Page. Refer to Figure 18.01-7.1. Refer to the applicable Aircraft Maintenance Manual section to correctly configure the aircraft (for

example, circuit breaker collaring, valve positioning, etc.).



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CAUTION: BEFORE CLOSING THE CROSSFEED VALVE, ENSURE THAT THE FUELPUMP(S) IS (ARE) OFF AND THE REFUEL VALVE(S) IS (ARE) IN THECLOSED POSITION. THIS WILL PREVENT DAMAGE TO THE CROSSFEEDVALVE.

E. On the panel 40VU, make sure that the X FEED P/BSQ 4QE is not pushed (in) (the ON and OPENlegends of the P/BSW are off).NOTE : It is recommended that all of the fuel pumps are switched to off to do this procedure. This

decreases the risk of possible fuel spills. it is permitted for the wing-tank pumps to beswitched to on, if there is a minimum of 1653 lbs. of fuel in the applicable wing-tank.

F. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS" spacedon the fuel slip. Refer to Section 15.01.

G. Connect the ground (earthing) cable of the refuel nozzle to the wing ground (earth) connection. Referto Figure 18.01-2.

H. Remove the applicable overing refuel cap 44 QM (45 QM). Refer to Figure 18.01-2.CAUTION: KEEP THE RATE OF REFUEL THE SAME AS, OR LESS THAN, THE RATE OF

FLOW THROUGH THE TRANSFER VALVES.

I. Put the fuel nozzle in the overwing refuel point.J. Start the pump on the fuel tank/pump unit.K. Use the fuel pumps in the wing tanks to move the fuel to the center tank from the wing tanks.L. Monitor the fuel quantities continuously on the ECAM lower Display Unit.

NOTE : The overwing refuel point is not at the highest point on the wing. Thus you cannot refuelthe wing tanks to full.

M. When a fuel quantities are correct, stop the pump on the fuel tanker/pump unit.N. Remove the fuel nozzle from the overwing refuel point.O. Install the overwing refuel cap 44 QM (45 QM).P. Disconnect the grounding (earthing) cable of the refuel nozzle from the wing ground (earth) connection.Q. Correct the fuel configuration, move the fuel from the inner cells of the wing tanks to fill the outer cells

of the wing tank (for example, transfer procedure, as outlined in the applicable Aircraft MaintenanceManual section).NOTE : Make sure that the outer wing fuel tanks are full. This will prevent the risk of structural

damage.

R. Refer to the applicable Aircraft Maintenance Manual section to correctly re-configure the aircraft (forexample, circuit breaker closing, valve positioning, etc.).

S. Legibly complete all applicable fields on the Jet Fuel service record (fuel slip). Refer to Section 15.01.


NOTE : Contact the Flight Crew or Aircraft Maintenance. Refer to AMM Section 28-25-00-869-001-A,"Aircraft Fuel Transfer Procedure."



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Figure 18.01-7: Cockpit and Lower Fuselage Fueling Controls

18.01.6 Procedure to Use the ADIRU to Find the Pitch and Roll Data

NOTE : Contact Flight Crew or Aircraft Maintenance. (Refer to AMM Task 12-11-28-860-001-A.)

1. In Table 18.01-1, use the PITCH data to find the equivalent number.2. In Table 18.01-1, use the ROLL data to find the equivalent letter.3. Put together the number and the letter to identify the square to use in the MLI procedure.

Table 18.01-1: Table 1

RefRollRefPitch

Aminus 1.51minus 1.5

Bminus 1.02minus 1.0

Cminus 0.53minus 0.5

D0.040.0

Eplus 0.55plus 0.5

Fplus 1.06plus 1.0

Gplus 1.57plus 1.5

18.01.7 Procedure to Use the FQIC Input Parameters to Find the Pitch and Roll Data

NOTE : Contact Flight Crew or Aircraft Maintenance.

A. In Table 18.01-1, use the PITCH data to find the equivalent number.B. In Table 18.01-1, use the ROLL data to find the equivalent letter.C. Put together the number and the letter to identify the square to use in the Magnetic Level Indicator

(MLI) procedure. Refer to AMM Task 12-11-28-650-007.D. Put the aircraft back to its initial configuration.

18.01.8 Refueling with Inoperative Fueling Quantity Indicators


lower fuselage/underwing panel fuel quantity indicator, provided respective cockpit display isverified operational. Verification of fuel quantity, by measuring stick, is not required with Method1. Use of Method 1 must be noted on the Jet Fuel service record (fuel slip), with a copy of thefuel slip provided to the Flight Crew as early as practicable after fueling.

B. Method 2 - For use on main tanks (wings) and center tank when the flight deck fuel quantity displayis inoperative, one or more of the underwing panel fuel quantity displays are inoperative and fuel onboard can be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.5.1. Determine the aircraft attitude. Refer to Section 18.01.7 and Section 18.01.8.2. Before fueling, determine existing fuel tank quantity with the measuring stick(s) of the affected

tank. Refer to Section 18.01.10. Subtract this quantity from the tank quantity required and convertto gallons. Fuel the tank to desired level, using the equipment meter. Use measuring stick(s) toverify tank quantity.



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NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons. Referto Section 15.01.7 to deliver the desired known quantity.

3. Provide the Flight Crew with the completed copy of the Jet Fuel service record (fuel slip) and anInoperative Fuel Quantity Indicator service record ensuring all required entries and signaturesare legible and in place as early as practicable, before departure.

C. Method 3 - For use on main tanks (wings) and center tank when the flight deck fuel quantity displayis inoperative, one or two of the underwing panel fuel quantity displays are inoperative and fuel onboard cannot be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.5. To fuel the aircraft with inoperative fueling control panel quantity indicators,refer to Section 18.01.10.1. Completely defuel tank with the inoperative indicator by transferring fuel to other tank(s). Refer

to Section 18.01.6.2. Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged by the fuel

equipment meter reading. Alternately, transfer required fuel from tank(s) with operative indicator.Refer to Section 18.01.6.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons. To

deliver the desired known quantity, refer to Section 15.01.7.

3. Fill tank(s) with operative indicator to quantity of fuel required.4. Determine the aircraft attitude. Refer to Section 18.01.7 or Section 18.01.8.5. Use measuring stick(s) to verify tank quantity with the inoperative quantity indicator.6. Provide the Flight Crew with the completed copy of the Jet Fuel service record (fuel slip) and an

Inoperative Fuel Quantity Indicator service record ensuring all required entries and signaturesare legible and in place as early as practicable, before departure.

D. Anytime fuel quantity is determined by measuring stick, the following procedure must be used:1. Determine the method, (refer to Method 2 or Method 3 above) to be utilized to fuel the aircraft

and check the applicable box on the Inoperative Fuel Quantity Indicator Service Record.a. When using Method 2, perform the following:

(1) Determine:a) The aircraft attitude before fueling.b) Tank stick(s) needed to measure the fuel quantity, and associated charts to

determine the pounds in the affected tank.(2) Record the before fueling information where applicable on the fuel slip and Inoperative


LI, C, ACT1, Trim, etc.) in the space provided below TANK.b) Record the before fueling aircraft attitude (pitch and roll).c) Circle the stick(s) utilized before fueling (all aircraft) and applicable inner/outer cell



a) The aircraft attitude after fueling.



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b) Tank stick(s) needed to measure the fuel quantity, and associated charts todetermine the after fueling pounds in the affected tank.

(5) Record the after fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner/outer cell



present title, and company name followed by your complete signature (no initials).f) Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.


b. When using Method 3, perform the following:(1) Empty the affected tank by defueling or transferring all remaining fuel to other tanks.



LI, C, ACT1, Trim, etc.) in the space provided below "TANK".b) Leave the before fueling aircraft attitude (pitch and roll) spaces blank and do not

circle any stick(s) utilized before fueling and applicable inner/outer cell tanks.c) Record the before fueling quantity of zero pounds on the fuel slip and the Inoperative


a) The aircraft attitude after fueling.b) Tank stick(s) needed to measure the fuel quantity, and associated charts to

determine the after fueling pounds in the affected tank.(5) Record the after fueling information where applicable on the fuel slip and Inoperative

Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner/outer cell






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E. Inaccurate Or Inoperative ACT Tank Quantity IndicatorsNOTE : ACT tanks do not contain magnetic level indicators.

1. Method 1 - For use when the flight deck fuel quantity display is operational and one or more ofthe underwing panel fuel quantity displays are inoperative.a. ACT fuel tank quantity may be determined by the respective cockpit display for the inoperative

lower fuselage/underwing panel fuel quantity indicator, provided respective cockpit displayis verified operational. Verification of fuel quantity, by measuring stick, is not required withMethod 1. Use of Method 1 must be noted on the Jet Fuel service record (fuel slip), with acopy of the fuel slip provided to the Flight Crew as early as practicable after fueling.

2. Method 2 - N/A on A321 Series aircraft3. Method 3 - For use on ACT tanks when the flight deck quantity display is inoperative and one or

more of the underwing panel fuel quantity displays are inoperative.NOTE : Completely defuel tank with the inoperative indicator by transferring fuel to the center

tank.

NOTE : ACT tank(s) fuel transfer is limited to the center tank only. Center tank must have theavailable capacity to accept fuel transfer.

NOTE : All WARNINGS, CAUTIONS and NOTEs under Section 18.01.1 General, must beobserved.

a. Obtain the jet fuel service record. Refer to Section 15.01.b. Position the fuel vehicle.c. Bond the fueling vehicle to the aircraft.d. Open fueling control panel access door.e. Completely defuel tank with the inoperative indicator by transferring fuel to center tank. Refer

to Section 18.01.5 for transfer procedures.f. Enter 0 (zero) pounds of pre-service fuel on the fuel slip, for the affected tank.g. Ensure the fueling receptacle is clean.h. Connect fueling nozzle to aircraft pressure fueling receptacle.

CAUTION: PRIOR TO APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLESTO THE LOCKED POSITION AND OPEN POPPET ACTUATING LEVER.ATTEMPT TO REMOVE NOZZLE. IF NOZZLE CAN BE REMOVED, IT ISDEFECTIVE AND MUST BE REMOVED FROM SERVICE.

i. Refer to manual refueling procedures Section 18.01.3 in order to refuel affected ACTindividually.

j. Record FUEL QUANTITY for each operational tank in the "GAUGE READING BEFOREFUELING LBS" spaces on the fuel slip. Refer to Section 15.01.

k. Note the affected tank's required pounds after fueling and divide by the density shown onthe fuel slip. This provides the number of gallons to be metered into the affected tank.

l. Ensure all other refuel valve switches are in the shut position, with the exception of theaffected tank being fueled. Fuel the tank to the desired level using the truck meter. Shut theaffected tank refuel valve switch. Record actual gallons metered into affected tank on thefuel slip after converting to pounds.



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m. Open refuel valve switches for remaining tanks and finish fueling aircraft to the amountindicated on the fuel slip, using the operative fuel panel gauges. After completion, ensure allrefuel valves and switches are placed in the shut position and then to the normal positionwith the switch guard down. De power the refuel panel (refer to manual refueling proceduresin Section 18.01.3).

n. Record the total "gallons/liters added" from equipment meter on the fuel slip. Refer to Section15.01.NOTE : Ensure the fuel slip is correctly filled out and legible.

o. Close fueling nozzle valve; remove fueling nozzle.p. Ensure the fueling receptacle is not leaking after fueling is complete and install fuel cap.q. Disconnect fueling vehicle bonding cable from aircraft.r. Provide flight crew with completed copy of fuel slip, ensuring all required entries and signatures

are legible and in place, as early as practicable before departure. Ensure use of ACTMethod3, is noted on the fuel slip in the remarks section.

18.01.9 Use of Magnetic Level Indicators (MLI)

A. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), aVendor Supervisor, Lead or Supervisor/Lead, Designee Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

B. Open the access door 192MB or 622KB. Refer to Figure 18.01-4 and Figure 18.01-5.NOTE : If operating in battery power, do not keep the door open longer than necessary because

the battery can discharge.

C. Obtain from Aircraft Maintenance or the Flight Crew and write down the aircraft attitude figure (PITCHand ROLL data).

D. Use of the Magnetic Level Indicators (MLI)1. Use the flow chart and do these steps. Refer to Figure 18.01-8 and Figure 18.01-9 .

NOTE : Depending on the aircraft configuration, there are either three or seven MLIs in eachwing tank and one in the center tank. Refer to Figure 18.01-11 and Figure 18.01-12.

NOTE : All MLI Stick number attitude charts outlined in Section 18.02 are applicable to both 3(sticks 2 - 4) and 7 (sticks 1 - 7) MLI per wing aircraft.



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Figure 18.01-8: How to Read a Wing Tank MLI 3 per wing



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Figure 18.01-9: How to Read a Wing Tank MLI - 7 per Wing



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Figure 18.01-10: How to Read the CTR MLI

a. Use a screwdriver to push the applicable MLI and turn it through 90 degrees.b. Hold and carefully lower the MLI fully. Then carefully lift the MLI until you feel the magnets

engage.c. Read the units mark nearest to the bottom-skin of the wing, and write down the number.

2. Retract the MLI and use a screwdriver to turn it through 90 degrees to lock it.3. Find the volume of fuel in each tank as follows:

a. Use the applicable MLI stick number and the applicable aircraft attitude grid-square letter tofind the correct fuel quantity table.NOTE : For a grid reading of C3:

1. Use the attitude monitor reading CLEFT WING column 3 for the LH wing.2. Use the attitude monitor reading CRIGHT WING column 3 for the RH wing.

b. Find the applicable MLI unit number row and the applicable aircraft attitude (grid-squareletter and number) row in the table. Find the intersection of the applicable rows to give thecorrect volume of fuel in the tank.NOTE : Only even number MLI units are listed in the tables. To calculate the volume of

fuel for uneven numbers, interpolate between the nearest even numbers in thetable.

MLI stick No. 2 (LH Wing)Example:

20:UNIT reading

C3 on (attitude monitor):Pitch and Roll attitude

1050 US gal:Fuel Quantity table reading (volume)

6.75 lb/US gal:Actual density of fuel sample

1050 x 6.75 = 7087.5 lb=Actual fuel mass at 6.75 lb/US gal

NOTE : The above example is for one MLI only.

4. Add together the values for each tank to find the total volume of fuel.NOTE : The MLI are accurate to +/- 5% of their indication. This is not sufficiently accurate to

use them as data for the Fuel Quantity Indication (FQI).

NOTE : When the aircraft is fully refueled, the maximum capacity of the inner wing cell is 77501(2047.3167 gallons).

5. Multiply the total volume of the fuel by the Specific Gravity of the fuel. The result is the total massof the fuel.

E. When the stick reading is taken, enter the applicable aircraft attitude, tank, sticker number, readingand conversion to pounds on the Inoperative Fuel Tank Indicator service record.

F. Proceed normally to determine the number of gallons added on the Jet Fuel service record. Refer toSection 15.01.

G. Close the access door 192MB or 622KB. Refer to Figure 18.01-4 and Figure 18.01-5.



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Figure 18.01-11: Magnetic Level Indicators (MLI) - 3 per wing



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Figure 18.01-12: Magnetic Level Indicators (MLI) - 7 per Wing

18.01.10 Defueling

NOTE : AA Flight Crew or Maintenance personnel must be present and operate applicable cockpitswitches or levers. In the event that a fuel system or components there of (excluding inoperativegauge) is malfunctioning, inoperable or when assistance is required to safely perform fuelingoperations, contact AA Maintenance personnel or Station Operations through coordination withAA MOC in person, by e-mail or other agreeable method when AA Maintenance personnel arenot on duty for assistance. Examples of inoperative or malfunctioning fuel system componentsor assistance situations include, inoperative refuel/defuel valves, inoperative transfer valves,transferring fuel, opening and closing aircraft landing gear doors, etc.

NOTE : Product defueled from an aircraft for purposes other than contamination should be returned tothe airline from which it was removed. Defueled product may not be delivered to anothercompany's aircraft without its approval. Defueling aircraft directly into joint use fueling systemsis not authorized unless a procedure has been unanimously approved by all system users.



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WARNING: MAKE SURE THE FUEL SUPPLY HOSE IS CORRECTLY CONNECTED TO THECOUPLING BEFORE YOU REFUEL/DEFUEL THE AIRCRAFT. DO NOT CONNECTTHE FUEL SUPPLY HOSE IF THERE ARE SIGNS OF DAMAGE TO THE AIRCRAFTCOUPLING LUGS OR SLOTS.

CAUTION: IF YOU OPERATE THE APU DURING A DEFUEL PROCEDURE, MAKE SURE THEFUEL LEVEL IN THE TANKS IS SUFFICIENT. IF THE FUEL IS BELOW THE LOWLEVEL, AIR CAN GO INTO THE FEED LINE. THIS WILL CAUSE THE APU TO STOP.

NOTE : You must prime the ACT transfer pump before you can move fuel from the ACT into the centertank.

NOTE : For maintenance procedures, it is not necessary to defuel both of the wing tanks. It is possibleto have one wing tank empty and the other wing tank full.

A. Bond the fueling vehicle to the aircraft. Refer to Figure 18.01-3.B. Open the access door 192MB or 622KB. Refer to Figure 18.01-4 and Figure 18.01-5.C. Do not spill fuel on the engines or the brakes. If you spill fuel on engines or brakes that are hot, it can

cause fires.D. Remove the refuel coupling cap 41QM. Refer to Figure 18.01-6.E. Connect the hose-coupling of the fuel tanker/pump unit to the aircraft refuel/defuel coupling.F. Make sure the fuel tanker(s) has (have) sufficient space for the fuel quantity to be defueled.G. On the ECAM Control Panel:

1. Push (in) the FUEL system page button.H. On the refuel/defuel control panel 800VU and 801 VU:

1. Make sure that the refuel valve switches are in the NORM and guarded position.2. Put the MODE SELECT switch to the DEFUEL XFR position and make sure the OPEN light

comes on.I. On the panel 40VU (refer to Figure 18.01-7), push (in) the X FEED P/BSW. Make sure the ON and

OPEN lights come on.J. Make sure that on the SD FUEL page, the crossfeed valve indication is shown green in-line (valve

open).WARNING: WHEN YOU OPERATE THE FUEL PUMPS DURING A MAINTENANCE

PROCEDURE, FLIGHT CREW OR A MAINTENANCE PERSON MUST BE IN THECOCKPIT. THIS PERSONMUSTSTOPTHEPUMPSWHENTHE LOWPRESSUREFAULT LIGHT(S) (ON PANEL 40VU) COME ON, TO PREVENT OPERATION OFTHE PUMP(S) WITHOUT FUEL (DRY RUNNING). OPERATION OF THE PUMPSWITHOUT FUEL CAN CAUSE A FIRE.

CAUTION: DONOT LET THE FUEL PUMPSOPERATE FORMORETHAN 15MINUTESWITHTHE FAULT LIGHT ON. THIS CAN CAUSE DAMAGE TO THE FUEL PUMPS.

K. On the panel 40VU:1. Push (in) the MODE SEL P/BSW. Make sure the MAN light of the MODE SEL P/BSW goes off.2. Push (in) the L TK PUMPS 1 and 2 ® TK PUMPS 1 and 2) P/BSWs and the related CTR TK XFR

P/BSW.3. Push (in) the ACT AUTO P/BSW to set it to FWD.4. Make sure the applicable P/BSW OFF lights go off.

L. On the SD Fuel page, monitor the fuel quantity indications. Make sure the applicable fuel quantityindications and the Fuel on Board (FOB) figures decrease.



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NOTE : When you defuel the left wing tank only, a small quantity of fuel will go into the right wingtank. Because the crossfeed valve is open, fuel can go through the grooves in the suctionvalves of the pump.

NOTE : When you defuel the wing tanks only, gravity will move the center (transfer) tank fuel intothe wing tanks.

M. When the fuel quantity has decreased to the necessary level:1. On the panel 40VU:

a. Release (out) the L TK PUMPS 1 and 2 (R TK PUMPS 1 and 2) P/BSWs, the related CTRTK XFR P/BSW and the ACT AUTO P/BSW (set to AUTO). Make sure the applicable P/BSWOFF lights come on.

b. On the SD Fuel page:(1) Make sure the fuel quantity indications become stable.(2) Make sure that the fuel quantity indication for the center tank stops decreasing.

N. To defuel the installed ACT(s) until empty:NOTE : Before this procedure, you must make sure that the center tank has sufficient space for the

fuel from the ACT(s).

1. On the panel 40VU:a. Set the ACT AUTO P/BSW to FWD. On the ECAM lower DU, make sure the applicable ACT

fuel quantity decreases and the CTR fuel quantity increases.b. On the ECAM lower DU, when the applicable ACT fuel quantity indicates zero for 2 minutes:

(1) On the panel 40 VU, set the ACT AUTO P/BSW to auto.c. If necessary, drain the remaining fuel from the ACT(s).

O. To defuel the center (transfer) tank until empty:WARNING: MOVE ALL THE FUEL OUT OF THE CENTER TANK BEFORE YOUGET ACCESS

TO A WING TANK. FUEL IN THE CENTER TANK WILL MOVE INTO AN EMPTYWING TANK BY GRAVITY.

1. On the panel 40VU:a. Push (in) the CTR TK L XFR ( CTR TK R XFR) P/BSW(s) and the related TK PUMPS 1 and

2 P/BSWs. Make sure the applicable P/BSW OFF lights go off.b. On the ECAM lower DU, monitor the center (transfer) tank fuel quantity.c. When the center (transfer) tank fuel quantity indicated zero for 2 minutes, on the panel 40

VU:(1) Release (out) the CTR TK L XFR (CTR TK R XFR) P/BSW(s).(2) Release (out) the related TK PUMPS 1 and 2 P/BSWs.(3) Make sure the applicable P/BSW OFF lights come on.

2. If necessary, drain the remaining fuel from the tank.CAUTION: BEFORE YOU CLOSE THE CROSSFEED VALVE, MAKE SURE:

- THE FUEL PUMP(S) IS (ARE) OFF.

- THE REFUEL VALVE(S) IS (ARE) IN THE CLOSED POSITION.

THIS WILL PREVENT DAMAGE TO THE CROSSFEED VALVE.

P. On the panel 40VU, release (out) the X FEED P/BSW. Make sure the ON and OPEN lights go off.



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Q. On the SD FUEL page, make sure the crossfeed valve indication shows green cross-line (valveclosed).

R. On the refuel/defuel panel 800VU:1. Put the MODE SELECT switch to the OFF and guarded position. Make sure the OPEN light goes

off.S. Close the access door 192MB or 622KB. Refer to Figure 18.01-4 and Figure 18.01-5.T. Disconnect the hose coupling of the fuel tanker from the aircraft.


U. Install the refuel coupling cap 41QM. Refer to Figure 18.01-6.V. Disconnect the bonding cable.

END



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Section 18.02 - Fuel Quantity - Magnetic Level IndicatorsA. Refer to A321 Magnetic Level Indicators (MLI) Charts as follows:

1. Access the Stick Charts at http://me.aa.com/manuals/fw/FuelingStickCharts/#z.

END

Section 18.02Fuel Quantity - Magnetic Level Indicators


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Table of contents

19.01 FUELING MANUAL - A330-200GENERAL..........................................................................................................................1

19.02 FUEL SYSTEM INFORMATIONGENERAL..........................................................................................................................1SYSTEM DETAILS.............................................................................................................1

19.03 FUEL PANELGENERAL..........................................................................................................................1FUELING PANEL (990VU)................................................................................................1

19.04 SAFETY PRECAUTIONSGENERAL..........................................................................................................................1

19.05 GENERAL FUELINGFUEL TANK SUMP CHECK..............................................................................................1

19.06 FUEL SYSTEM TESTGENERAL..........................................................................................................................1TEST PROCEDURE..........................................................................................................1

19.07 PRESSURE FUELING WITH AUTOMATIC CONTROLPRESSURE REFUEL WITH AUTOMATIC CONTROL FROM PANEL 990VU.................1

19.08 PRESSURE FUELING WITH AUTOMATIC CONTROL - LOAD PRESELECTORINOPERATIVEPROCEDURES - PRESSURE FUELING WITH MANUAL CONTROL - LOADPRESELECTOR INOPERATIVE.......................................................................................1

19.09 OVERWING FUELINGOVERWING FUELING PROCEDURES............................................................................1

19.10 ALTERNATE FUELINGGENERAL..........................................................................................................................1INOPERATIVE WING/CENTER/TRIM TANK QUANTITY INDICATION............................1DETERMINING FUEL QUANTITY BY MAGNETIC LEVEL INDICATORS (MLI)..............2

TOCFueling Manual - A330-200


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19.11 FUEL TRANSFERGENERAL..........................................................................................................................1INNER TANK GROUND FUEL TRANSFER......................................................................1

19.12 DEFUELINGGENERAL..........................................................................................................................1DEFUEL OF THE CENTER TANK....................................................................................1DEFUEL OF THE TRIM TANK..........................................................................................2DEFUELING WING TANKS - LOWER QUANTITY...........................................................2DEFUELING WING TANKS - EMPTY...............................................................................3SUCTION DEFUELING.....................................................................................................3CLOSE UP.........................................................................................................................4

19.13 MAGNETIC LEVEL INDICATORS (MLI)GENERAL..........................................................................................................................1ACCESS............................................................................................................................1SPECIFIC GRAVITY (SG)/DENSITY.................................................................................1MLI SYSTEM AND STICK NUMBER ATTITUDE CHARTS..............................................1MAGNETIC LEVEL INDICATORS MLI CHARTS..............................................................4



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Section 19.01 - Fueling Manual - A330-20019.01.1 General

WARNING: DO NOT OPERATE THE HF COMMUNICATION SYSTEM WHILE FUELING THEAIRPLANE. A FIRE OR AN EXPLOSION CAN OCCUR.

WARNING: GROUND EQUIPMENT MUST NOT BE POSITIONED UNDER WING TIPS DURINGFUELING OPERATION.

WARNING: FUELING VEHICLE MUST BE PROPERLY BONDED TO AIRCRAFT BEFORE ANYFUELING/DEFUELING OPERATION.

WARNING: WHEN THERE IS AN INACCURATE/INOPERATIVE OR A SUSPICION OF A GAUGENOT INDICATING PROPERLY, STOP FUELING AND NOTIFY AIRCRAFTMAINTENANCE IMMEDIATELY IN PERSON OR OTHER AGREEABLE METHOD.

NOTE : IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARD AS BEING INOPERATIVE,AIRCRAFT MAINTENANCE DOES NOT NEED TO BE NOTIFIED, UNLESS SPECIFICPROCEDURESDURINGFUELINGOPERATIONSREQUIRETHEATTENTIONOFAIRCRAFTMAINTENANCE.

WARNING: IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION, NOTIFY AIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON OROTHERAGREEABLEMETHOD.DONOTSTARTORRESUMEFUELINGOPERATIONSUNTIL CORRECTIVE ACTION HAS BEEN TAKEN.

WARNING: DO NOT START OR SHUT DOWN APU SHOULD FUEL SPILL.

WARNING: DEFUELING OR TRANSFERRING FUEL WITH PASSENGERS ONBOARD THEAIRCRAFT IS PROHIBITED, EXCEPT UNDER CERTAIN CONDITIONS.

A. The fuel system has two main tanks, one center tank and one trim tank. There is also a vent surgetank located in each wing, outboard of the wing tank and in each Trimmable Horizontal Stabilizer(THS), outboard of the trim tank.1. For all A330-200 aircraft:

a. Center tank has an approximate volume of 10,979 US gal.b. Trim tank has an approximate volume of 1,646 US gal.c. Main (wing) tanks each have an approximate volume of 12,059 US gal.


NOTE : This aircraft also contains collector cells. Each collector cell is maintained full offuel for the main booster pumps. The approximate fuel quantity in each collectorcell is 2,512 lbs, provided that the fuel density is 6.70 lb/gal. Actual fuel weightcapacity will vary depending on fuel density.

Table 19.01-1: Refuel/Defuel Limitations

40 PSIMaximum Refuel Pressure (Primary)

50 PSIMaximum Refuel Pressure (Secondary)

350 GPMMaximum Refuel Rate - Wing Tanks

450 GPMMaximum Refuel Rate - Simultaneous

Section 19.01Fueling Manual - A330-200


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11 PSIMaximum Defuel Pressure

Right Wing FairingFuel Panel Location (Primary)

Left WingFuel Panel Location (Secondary)

NOTE : Fuel pressure should not exceed a constant 50 psi at any time during the fueling operation.

Table 19.01-2: A330-200 Fuel Distribution - (assuming a fuel density of 6.70 lb/gal)FUEL DISTRIBUTION CHART

Trim Tank (lbs)Rt Tank Outer (lbs)Rt Tank Inner (lbs)Ctr Tank (lbs)Lt Tank Inner (lbs)Lt Tank Outer (lbs)Total Fuel (lbs)

0000000

002,00002,00004,000

004,00004,00008,000

006,00006,000012,000

008,00008,000016,000

0010,000010,000020,000

0010,150010,150020,300

01,85010,150010,1501,85024,000

03,85010,150010,1503,85028,000

05,85010,150010,1505,85032,000

06,45010,150010,1506,45033,200

06,45011,550011,5506,45036,000

06,45013,550013,5506,45040,000

06,45015,550015,5506,45044,000

06,45017,550017,5506,45048,000

06,45019,550019,5506,45052,000

06,45021,550021,5506,45056,000

06,45023,550023,5506,45060,000

06,45025,550025,5506,45064,000

06,45027,550027,5506,45068,000

06,45029,550029,5506,45072,000

06,45031,550031,5506,45076,000

06,45033,550033,5506,45080,000

06,45034,700034,7006,45082,300

1,7006,45034,700034,7006,45084,000

5,4006,45034,700034,7006,45087,700

5,4006,45034,850034,8506,45088,000

5,4006,45036,850036,8506,45092,000

5,4006,45038,850038,8506,45096,000

5,4006,45040,850040,8506,450100,000

5,4006,45042,850042,8506,450104,000

5,4006,45044,850044,8506,450108,000

5,4006,45046,850046,8506,450112,000

5,4006,45048,850048,8506,450116,000

5,4006,45050,850050,8506,450120,000

5,4006,45052,850052,8506,450124,000

5,4006,45054,850054,8506,450128,000

5,4006,45056,850056,8506,450132,000



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FUEL DISTRIBUTION CHART

Trim Tank (lbs)Rt Tank Outer (lbs)Rt Tank Inner (lbs)Ctr Tank (lbs)Lt Tank Inner (lbs)Lt Tank Outer (lbs)Total Fuel (lbs)

5,4006,45058,850058,8506,450136,000

5,4006,45060,850060,8506,450140,000

5,4006,45062,850062,8506,450144,000

5,4006,45064,850064,8506,450148,000

5,4006,45066,850066,8506,450152,000

5,4006,45068,850068,8506,450156,000

5,4006,45070,850070,8506,450160,000

5,4006,45072,850072,8506,450164,000

5,4006,45074,350074,3506,450167,000

5,5006,45074,35090074,3506,450168,000

5,9006,45074,3504,50074,3506,450172,000

6,3006,45074,3508,10074,3506,450176,000

6,7006,45074,35011,70074,3506,450180,000

7,1006,45074,35015,30074,3506,450184,000

7,5006,45074,35018,90074,3506,450188,000

7,9006,45074,35022,50074,3506,450192,000

8,3006,45074,35026,10074,3506,450196,000

8,7006,45074,35029,70074,3506,450200,000

9,1006,45074,35033,30074,3506,450204,000

9,5006,45074,35036,90074,3506,450208,000

9,9006,45074,35040,50074,3506,450212,000

10,3006,45074,35044,10074,3506,450216,000

10,7006,45074,35047,70074,3506,450220,000

11,0006,45074,35051,40074,3506,450224,000

11,0006,45074,35055,40074,3506,450228,000

11,0006,45074,35059,40074,3506,450232,000

11,0006,45074,35063,40074,3506,450236,000

11,0006,45074,35067,40074,3506,450240,000

11,0006,45074,35073,60074,3506,450246,200



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Figure 19.01-1: Tanks Location

END



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Section 19.02 - Fuel System Information19.02.1 General

A. Fueling is accomplished in the following manner:1. A pressure refuel through couplings in the lower surface of each wing (auto/manual).2. A gravity over wing refuel through over wing ports in the upper surface of each wing.

NOTE : The tankers should be positioned as outlined in Figure 19.02-1.

B. The system may be powered electrically from:1. On-board auxiliary power unit (APU).2. Ground Power Unit (GPU).3. On-board battery.

C. Refueling may be controlled from:1. A refuel panel in the right lower belly fairing.2. A secondary refuel panel next to the left wing receptacles.

19.02.2 System Details

A. The fuel system stores fuel in the main fuel tanks, the center tank, and the trim tank, six tanks total(refer to Figure 19.02-2). The fuel system controls and supplies fuel in the correct quantities to thefuel tanks during refueling. It supplies fuel to the engines and APU, while transferring fuel to and fromthe trim tank to keep the Center of Gravity (CG) within limits.

B. A set of pipes connects the refuel couplings to the fuel inlet valve of each tank. Refueling is normallyautomatic, the required fuel load being set on the preselector. All tanks that require refueling start tobe refueled simultaneously. Refuel valves close automatically when the tanks contain the preselectedload or when sensors detect a high fuel level. Manual control is available. Transfer is possible fromeither inner tank to any other tank except the trim tank, provided the Fuel Control and MonitoringComputer (FCMC) is powered.

C. Each inner tank contains a collector cell. This makes a fuel reservoir for two main engine-feed fuelpumps. Each pair of fuel pumps has one standby fuel pump. Vent surge tanks are installed outboardof each outer tank and on the right hand (RH) side of the trim tank in the Trimable Horizontal Stabilizer(THS). Each vent surge tank has a minimum capacity (before leakage can occur) which is five timeslarger than the volume of its vent pipes. This makes sure that there is no fuel spillage during aircraftmovement on the ground and takeoff. All fuel tanks have water drain valves at their lowest point.

D. After a refuel operation to the maximum tank capacity, the fuel can expand 2% (68°F; 20°C temperatureincrease), without spillage at the refuel attitude and during subsequent:1. Towing2. Aircraft movement3. Take-off and rejected take-off

Section 19.02Fuel System Information


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Figure 19.02-1: Tanker Positions

NOTE : Tanker positions are subject to change according to local or airport requirements.



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Figure 19.02-2: Fuel System Schematic

E. The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. It is controlled from therefuel/defuel control panel 990VU in the RH lower belly fairing or (left wing) (refer to Figure 19.02-3).Two refuel/defuel fuel hose couplings are installed in the leading edge of the left hand (LH) and RHwings (refer to Figure 19.02-4). These are the interface between the refuel/defuel system and theexternal fuel supply. Each refuel/defuel coupling can have two refuel hoses connected to it.1. There are two different procedures to refuel the aircraft:

a. Pressure refuel (automatic/manual)b. Over wing refuel (gravity/manual)

2. To fill the fuel tanks to their maximum capacity, the aircraft must be on the level ground and theTHS set at 0 degrees. It is possible to refuel the aircraft on a ground slope of up to 2 degreesand still get the maximum capacity. But, on ground slopes of more than 2 degrees, it is not possibleto get the maximum capacity.

3. When the refuel supply is from four fuel hoses, the time to refuel the aircraft (from the usualreserves to the maximum capacity) is limited by pump pressure. The fuel distribution after refueldepends on the quantity of fuel in the aircraft.WARNING: DURING REFUEL OPERATION, IT IS NECESSARY TO KEEP A SAFE

LONGITUDINAL BALANCE IN THE AIRCRAFT. IT IS IMPERATIVE TO KEEPFUEL LOAD PER THE REFUEL DISTRIBUTION TABLE. THUS, THE INLETVALVE TO THE TRIM TANK CANNOT OPEN UNLESS ONE OF THESE TWOCONDITIONS OCCUR:

THE FUEL CONTENTS IN THE TWO INNER TANKS ARE AT HI-LEVEL.

THE TWO INLET VALVES OF THE INNER TANKS ARE OPEN.



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4. When the quick-release door to the refuel/defuel panel opens, it activates a microswitch whichsends a signal to the Fuel Control Monitoring System (FCMS). In addition, power is supplied toall fueling panel functions. The load switch sets the preselected fuel quantity. This is shown inthe PRESELECTED window of the Fuel Quantity Indicating (FQI) indicator. To do a refuel, thisquantity must be set to a larger value than the ACTUAL indication. The MODE SELECT switchis set to REFUEL, which sends a signal to the FCMS and supplies electrical power to the fuelsystem components. At the start of refuel, the hi-level test push button switch is pushed in, sendinga continuity test signal to the hi-level and overflow sensors, along with their circuits.

5. At the end of the refuel, the END light comes on to show that the refuel is completed. The MODESELECT switch is set to OFF and the isolation valve closes. If the fuel distribution at the end ofthe refuel is incorrect, it can be corrected through a ground transfer. If the difference in the wingsis greater than 6614 lbs. (3000 kg):a. The END light on the refuel/defuel control panel flashesb. A WING TK FUEL IMBALANCE warning is given on the ECAM

6. If the difference between the ACTUAL fuel load and the PRESELECTED fuel load is more than440 lbs. (200 kg) 10 seconds after the refuel is completed, one more refuel can be made. If thefuel quantity is still out of this limit, the END light on the refuel/defuel panel flashes.



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Figure 19.02-3: Refuel/Defuel Control Panels



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Figure 19.02-4: Refuel/Defuel Couplings

F. There are two procedures to defuel the aircraft:1. Pressure (aircraft fuel pumps supply the fuel to the defueler).2. Suction (defueler supplies the suction to remove the fuel).

NOTE : It is possible to suction defuel all of the fuel tanks. But, when the trim tank containsfuel, it is not possible to suction defuel the wing tanks. On the ground, it is possible tomove fuel from tank to tank through the fuel ground transfer procedure.

G. The Fuel Indicating Systems are:1. FQI system, which gives separate and total fuel quantity indications.2. The Magnetic Level Indicators (MLI), a secondary system used to estimate fuel quantity when

the aircraft is on the ground.3. The tank level sensing, which gives indications and warnings when the fuel is at given levels.4. The fuel temperature measurement, which gives continuous temperature indications and warnings

when the fuel temperature is at specified levels.



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H. Fuel Quantity Indicating System (FQI) - Measures the total quantity of fuel in the range unusable tooverflow. It gives fuel indications for each of the fuel tank areas (LH/RH outer/inner/collector/center/trimtanks). The FQI has fuel probes with a capacitance that is in proportion to the amount to fuel thattouches the probes. The FCMS continuously measures the capacitances in each area.

I. MLI - A secondary direct-reading system used (only on the ground) to calculate the fuel quantity inthe inner, outer and center tanks. It is not necessary to have electrical power to use the indicators.NOTE : Since there are no Magnetic Level Indicators in the trim tank, the MLI procedure does not

include trim tank (refer to Figure 19.02-5).

NOTE : If the trim tank quantity indication is inoperative at the refuel panel(s) and the flight deck,then the trim tank must be verified to be full or empty.



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Figure 19.02-5: Magnetic Level Indicators - Inner, Outer and Center Tanks

J. Tank Level Sensing - The fuel system has level sensors which send fuel level signals to the FCMS.The FCMS uses the fuel level data to control the operation of the tank inlet valves during a refuel orfuel transfer.

END



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Section 19.03 - Fuel Panel19.03.1 General

A. The primary component of the Fueling system is the External Fueling Panels (990VU). There is anexternal panel mounted in the right side belly fairing, behind access panel 198DB, along with anotherpanel in the left wing. These panels are used to control the refuel operation, either in automatic modeunder the control of the Fuel Control and Monitoring Computer (FCMC) or in manual mode from theREFUEL-DEFUEL-VALVES switches (refer to Figure 19.03-1).

19.03.2 Fueling Panel (990VU)

A. Fuel Quantity Indicator (FQI) Panel (refer to Figure 19.03-1) - Shows the quantity of fuel in each fueltank, the total fuel quantity (ACTUAL) in the aircraft and the required fuel quantity (PRESELECTED).

B. Load Switch - Used to set the required fuel quantity on the PRESELECTED display.C. Mode Select Switch - When set to REFUEL, the fuel-tank inlet valves can be opened and shut either

automatically by the FCMC or manually by the applicable REFUEL-DEFUELVALVES switch. Whenset to DEFUEL, the inlet-valves can be opened and shut manually as required.

D. Refuel-Defuel-Valves Switches - Open or shut the applicable fuel-tank inlet valve and override anyautomatic command. When set to NORM, the FCMC controls the operation of the inlet valves. If aninlet valve actuator fails and the related valves switch has no effect, valves may be opened or closedby Maintenance personnel only.NOTE : The FCMC gives priority to a valve switch command over that of a software command.

Therefore, an Auto-Refuel, with the correct fuel distribution, can only be achieved when allthe REFUEL-DEFUEL-VALVES switches are set to NORM.

E. High Level Lights - Illuminate when the related fuel-tank high level sensors are wet, indicating a fueltank is full. The trim tank high level light may be used for full tank verification if the FQI for this tankis operative at the Refuel Panel(s) and Flight Deck.

F. Lights - Illuminate when the related surge tank level sensors are wet.

Section 19.03Fuel Panel


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Figure 19.03-1: Fueling Control Panel (990VU)

G. High Level Test - Before the start of a refuel, a test of the high Level Protection system is required.To start the test, the HI LVL TEST Push Button Switch (P/BSW) is pushed in and held, for approximately10 seconds. If the applicable circuits and level sensors are serviceable, the six HIGH LEVEL lightsand the three OVERFLOW lights come on. If a fuel-tank is full or a surge-tank has overflowed, suchthat the high-level light is already on, the test will turn the light off. Therefore, if a light does not changefrom its initial state, during the test, there is a fault with the applicable circuit.NOTE : A sensor circuit may fail such that the high-level light, or overflow light, comes on when a

tank is not full. This condition is described in this manual as "failed wet."

H. Transfer Valve Switch - Controls the operation of the Aft Transfer. This enables a post-refuelground-transfer of fuel, from one aircraft fuel-tank to another, to be controlled from the external fuelingpanel.NOTE : The TRANSFER VALVE must be set to CLOSED during an auto-refuel operation.

I. Power Supply Switch - When the PWR SUPPLY switch is set to NORM, the refuel power source canbe from either the APU, or a GPU. When the switch is set to BAT, the power source is from the aircraftbatteries.

J. Emergency Shutdown - This switch is used to shut down the APU if a fuel spillage or overflow occurs.



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K. End Indicator Light - A steady light indicates that the refuel is complete. A flashing light indicates thatthe refuel isolation valves have shut, if one of the following conditions occurs:1. Surge tank overflow sensor is wet2. Jettison valve is open3. Fuel tank high level sensor circuit has failed4. T TANK FWD, transfer push button switch (P/BSW) is pushed (in)5. There is a difference between the flight deck fuel control panel set up and the external refuel/defuel

panel set up.L. Flight Deck Indicator - Not usedM. Refuel/Defuel Couplings - There is a refuel/defuel coupling in each wing. Each coupling has two valve

heads allowing up to four refuel hoses to be connected at the same time. An isolation valve is installedin a circular housing at the center of each coupling.

N. Refuel/Defuel Isolation Valve - There is an electrically controlled and fuel pressure operated isolationvalve, incorporated in each coupling. The refuel isolation valve controls the fuel supply from the refuelsource to the refuel gallery. In case of an electrical failure, the isolation valves may be opened manuallyby means of an override switch mounted on the valve housing. Fuel passes through the isolation valveinto a refuel gallery from where fuel flows to the inlet valves out of the various aircraft fuel tanks (inner,outer, center and trim).NOTE : The refuel pressure at the isolation valve must not exceed (40 psi).

O. Fuel Probes - The FQI system has fuel probes with a capacitance that is in proportion to the amountof fuel that touches the probes. The Fuel Control Monitoring System (FCMS) continuously measuresthis capacitance and uses the fuel quantity data to control the operation of the fuel system and displaythe fuel tank quantities.

P. High Level/Overflow Sensors - Two high level sensors are installed in each main fuel tank and thecenter tank and one overflow sensor is installed in each wing surge tank and the trim surge tank. Thehigh level sensors in the wing, center and trim tanks are set at the same level and when they becomewet the FCMC closes the applicable inlet valve. When an overflow sensor in a surge tank becomeswet, the FCMC closes the refuel isolation valves.

Q. Inlet Valves - The primary function of the inlet valves is to control the flow of fuel from the refuel galleryinto the related tank.NOTE : Manual override of the inlet valve actuators is a maintenance function only.

R. FCMC - There are two FCMCs in the FCMS which control the automatic refuel process.1. Each FCMC receives input data from fuel:

a. Temperature sensorsb. Densitometersc. Quantity probes and level sensors

2. These data are reused by the two FCMCs to continuously calculate the fuel distribution and centerof gravity, and give protection against aircraft overbalance and fuel spillage. However, only theFCMC in control (normally FCMC1) sends discrete command signals to the refuel isolation valvesand the applicable inlet valves, used in the refuel process. Each FCMC has hardware and softwarethat provides the FCMC with Built-In-Test Equipment (BITE). The BITE continuously monitorsthe FCMC and fuel system components for failures and can do a BITE (self) Test.

END



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Section 19.04 - Safety Precautions19.04.1 General

A. The following material will outline the minimal procedures for fueling A330 aircraft. The proceduresare intended to sequentially outline the necessary steps to make sure a safe and efficient fuelingoperation.1. Obtain a Jet Fuel Service Record (Fuel Slip). Refer to Section 15.01.

a. Before positioning fueling equipment around aircraft, aircraft engines must be shut down andwheel chocks must be in place.

2. Properly position refueling equipment.a. Maintain 5 feet separation between aircraft and fueling equipment.

(1) Because fueling equipment may vary in model, type and size, it may be necessary touse fuel equipment parking positions other than those shown (refer to Figure 19.04-1for recommended fuel equipment parking positions) in this manual due to local stationregulations and passenger boarding bridge/aircraft gate positioning.

(2) Unless these conditions exist, a 5 foot clearance must be maintained at all times whenfuel equipment is positioned at the gate.a) Exceptions:

(1) Only fuel equipment that is designed to fuel aircraft by positioning under thewing can be used to service the aircraft. This equipment must maintain a 12inch clearance from the underside of the wing to the highest part of theequipment when positioned under the aircraft wing. This clearance must bemaintained the entire time the aircraft is being fueled.

b) Examples:(1) Hydrant Truck with Lift Deck(2) Low Profile Tank Truck(3) Stationary Hydrant Cart

NOTE : Stationary Hydrant Carts must be parked in the designated ramparea at all times.

Section 19.04Safety Precautions


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Figure 19.04-1: Fueling Equipment Positioning

b. Never back a refueler (tank truck) towards or away from the aircraft without a guide person.NOTE : For vehicles equipped with an operating back up video camera and monitor, the

use of a guide person is not required.

3. Bond refueler to aircraft bonding lug as outlined in Figure 19.04-2 on right or left main landinggear.

4. Stop fuel tanker 200 ft. (60 m) from aircraft while the weather radar is in operation.5. Do not begin refuel/defuel operations until weather radar is turned off.6. Do not refuel/defuel within 100 ft. (30 m) of operating radar of HF radar equipment.7. Make sure fuel tanker/hydrant contains correct fuel.8. If auxiliary power unit (APU) must be operating during refuel/defuel, the following is mandatory:

a. APU must be started before start of refuel/defuel (except in an emergency, for example, fuelspill).

b. Do not stop APU during refuel/defuel (except in an emergency, for example, fuel spill).c. If APU stops during refuel/defuel, do not start the APU again until there is no danger of fuel

vapor ignition.



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9. Make sure all electrical equipment used does not cause sparks.10. If passengers remain on board during refueling, a flight attendant must be in the cabin near the

main entry door. The passenger loading bridge must be attached to the aircraft with the mainentry door open at all times.

Figure 19.04-2: Location of the Grounding Points on the Nose Landing Gear (NLG) and MainLanding Gear (MLG)

END



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Section 19.05 - General Fueling19.05.1 Fuel Tank Sump Check

A. Fuel Tank Sump Locations1. There are six sump valves on each wing, two sump valves in the center tank and three sump

valves for the trim tank. Refer to Figure 19.05-1.B. Fuel Tank Sump Check

1. Aircraft fuel sumping is the responsibility of Maintenance personnel and will be in accordancewith scheduled maintenance checks.

Figure 19.05-1: Water Drain Valves - Location

END

Section 19.05General Fueling


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Section 19.06 - Fuel System Test19.06.1 General

A. This test must be performed before any refueling operation. Refer to Section 19.06.2.B. The High Level Detection System may be inoperative (for example, on Minimum Equipment List

(MEL)). If so, continuously monitor the fuel quantity during refueling.1. If the Inner Tanks High Level Detection System is inoperative:

a. The Inner Tank fuel quantity indications in the cockpit must be operative.b. Center Tank pumps must be selected OFF.

2. If the Outer Tank quantity indicators are inoperative, and the Outer Tank High Level DetectionSystem is inoperative, continuously monitor the Outer Tank fuel quantity via the Magnetic LevelIndicators (MLI).

3. If the Center Tank quantity indicators are inoperative, and the Center Tank High Level DetectionSystem is inoperative, continuously monitor the Center Tank fuel quantity using the MLI.

19.06.2 Test Procedure

A. Open fuel panel door (refer to Section 19.03.2).NOTE : If the fuel panel does not energize, put the PWR SUPPLY switch to BAT.

NOTE : Ignore the indications during the first 30 seconds after power-up.

B. Lift guard, push (in) the refuel/defuel control panel and hold the HI LEVEL TEST switch.1. The HI LEVEL lights and the OVERFLOW lights go to the opposite condition.2. The CKPT and END lights will come on.3. The PRESELECTED and ACTUAL fuel quantity displays will show all 8s.

C. Release HI-LEVEL TEST switch.1. Wait 10 seconds.2. The lights will go back to their initial condition.3. The PRESELECTED and ACTUAL fuel quantity displays will go back to their initial condition.

END

Section 19.06Fuel System Test


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Section 19.07 - Pressure Fueling With Automatic Control19.07.1 Pressure Refuel with Automatic Control from Panel 990VU

CAUTION: DO NOT LET THE REFUEL PRESSURE GET TO MORE THAN 50 POUNDS PERSQUARE INCH (PSI). THIS WILL PREVENT DAMAGE TO THE AIRCRAFT FUELSYSTEM.

A. On the refuel/defuel control panel 990VU (refer to Section 19.03.2):1. Put the LOAD switch to the INC position and hold it there.2. Make sure that the numbers on the PRESELECTED display increase.3. When the PRESELECTED display shows the necessary fuel load, release the LOAD switch.

NOTE : To do a refuel, the figure set must be a minimum of 440 lbs. (200 kg) more than theFuel on Board (FOB) figure.

4. Make sure that the REFUEL VALVES switches are in the NORM position and guarded.NOTE : If a switch is moved to SHUT during the automatic refuel, the applicable valve closes.

If a switch is moved to OPEN during the automatic refuel, the Fuel Control MonitoringSystem (FCMS) ignores the command until the automatic refuel is complete. Then,after approximately 15 seconds the refuel will continue (in manual mode) into theapplicable tank.

a. Start the pump on the fuel tanker/pump unit.b. At the refuel/defuel control panel 990VU:

(1) Put the MODE SELECT switch to the REFUEL position.NOTE : If the following switches are not in the correct configuration, the END light will

flash:

a) One or more of the inlet valve switches is in the OPEN or SHUT position.b) On the FUEL panel 245VU, the T TK FEED switch is set to OPEN or ISOL.c) On cockpit FUEL panel 245VU, the T TANK MODE switch is set to FWD.d) On cockpit FUEL panel 245VU, the OUTER TK XFR switch is set to MAN.

(2) Make sure that the numbers on the fuel quantity and the ACTUAL displays increase.(3) When the refuel stops, make sure that:

a) The END light comes on and does not flash.b) The numbers on the ACTUAL and the PRESELECTED displays are stable and are

the same (-440 lbs. (-200 kg) +440 lbs. (200 kg)).(4) Set the MODE SELECT switch to OFF.(5) If the power supply is from the battery, put the PWR SUPPLY switch to NORM.

a) Stop the pump on the fuel tanker/pump unit.b) Close up.

B. Close Access.1. Disconnect the coupling of the four fuel supply hoses from the aircraft refuel/defuel couplings.2. Install the refuel/defuel coupling caps.3. Refuel panel closure.

CAUTION: DO NOT APPLY TOOMUCH FORCE TO THE OPERATING RODWHEN YOUCLOSE THE PANEL. THIS PREVENTS DAMAGE TO THE MECHANISM.

Section 19.07Pressure Fueling With Automatic Control


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a. Close the access panels.b. Close the fuel control panel.

END

Section 19.07Pressure Fueling With Automatic Control


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Section 19.08 - Pressure Fueling With Automatic Control - LoadPreselector Inoperative

19.08.1 Procedures - Pressure Fueling With Manual Control - Load Preselector Inoperative

CAUTION: DO NOT LET THE REFUEL PRESSURE GET TO MORE THAN 3.4 BAR (50 POUNDSPER SQUARE INCH (PSI)). THISWILL PREVENT DAMAGE TO THE AIRCRAFT FUELSYSTEM.

A. On the refuel/defuel control panel, set the switches as follows (refer to Section 19.03.2):1. Put the REFUEL/DEFUEL VALVE switch(es) for the fuel tank(s) you want to refuel to the OPEN

position.NOTE : If refuel valves secured in NORM position, Maintenance to cut wire to manually

open/shut valves.

NOTE : To refuel the trim-tank, you must have one of these conditions:

a. The two inner-tank inlet valves are openb. The center-tank inlet valve is open.c. The two inner tanks fuel quantities are above 30865 lbs. (14000 kg)d. One inner tank fuel quantity is above 30865 lbs. (14000 kg) and the other inner-tank inlet

valve is open.B. Put the REFUEL/DEFUEL VALVE switch(es) for the tank(s) you do not want to refuel to the SHUT

position.WARNING: EXTREMECAUTIONMUST BE EXERCISEDWHENADDING FUEL TO THE TRIM

TANK MANUALLY. FOLLOW THE FUEL DISTRIBUTION TABLE (REFER TOSECTION 19.01.1 ) CAREFULLY OR AIRCRAFT COULD TIP ON ITS TAIL.

NOTE : If the trim tank is to be fueled, it must be done in two steps:

(1) When the trim tank fuel quantity reaches 2200 lbs. below that shown on the FuelDistribution Table (refer to Section 19.01.1), shut the trim tank inlet valve.

(2) When the two inner tanks are at the target value (refer to Section 19.01.1), open thetrim tank inlet valve.

C. Start the pump on the fuel tanker/pump unit.D. On the refuel/defuel control panel:

1. Put the MODE SELECT switch to the REFUEL position.2. If the refuel isolation valve does not open, do the next step.3. On the refuel isolation valve, push in and hold the override push button switch.4. Monitor the fuel quantity displays.5. Make sure that the numbers on the FUEL QUANTITY and ACTUAL displays increase.6. When each tank has the correct fuel quantity, put its REFUEL/DEFUEL VALVE switch to the

SHUT position.NOTE : Each tank quantity can increase 220 lbs. (100 kg) to 440 lbs. (200 kg) after the

REFUEL/DEFUEL VALVE switch is set to SHUT.

NOTE : If necessary, refer toTable 19.01.1 to make sure the fuel distribution is correct for flight.

7. When the fuel tank quantities are correct, put the MODE SELECT switch to the OFF position.

Section 19.08Pressure Fueling With Automatic Control - LoadPreselector Inoperative


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8. If it was necessary to operate the override push button switch, do the next step. On the refuelisolation valve, release the override push button switch.a. Put the applicable REFUEL VALVES switch(es) to the NORM position.b. If the power supply is from the battery, put the PWR SUPPLY switch to NORM.

NOTE : Maintenance to reinstall Safety Wire MPN MS20995C20 on all REFUEL/DEFUEL VALVEswitches into NORM positions.

E. Stop the pump on the fuel tanker/pump unit.

END

Section 19.08Pressure Fueling With Automatic Control - LoadPreselector Inoperative


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Section 19.09 - Overwing Fueling19.09.1 Overwing Fueling Procedures

NOTE : This procedure is not authorized for refueling the trim tank. Contact American Airlines (AA)Maintenance.

A. Connect the ground cables of the refuel nozzles to the wing ground connections.B. Remove the overwing refuel caps (Figure 19.09-1).

NOTE : The overwing refuel caps are located on the inner tanks.

C. Put the fuel nozzles in the overwing refuel points.D. Start the pump on the fuel tanker/pump units.

CAUTION: KEEPTHERATEOFFUELGROUNDTRANSFERTHESAMEAS (OR LESSTHAN)THE RATE OF FLOW INTO THE INNER TANK.

E. Start a ground fuel transfer from the inner tanks to the other fuel tank(s).F. Fill the inner tanks with the necessary amount of fuel.

NOTE : Be careful not to overfill the tanks. There is no automatic cut-out.

G. When the fuel quantities are correct, stop the pump on the fuel tanker/pump unit.H. Stop the ground fuel transfer.

Section 19.09Overwing Fueling


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Figure 19.09-1: Overwing Refuel - Adaptor Cap

END



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Section 19.10 - Alternate Fueling19.10.1 General

A. Alternate fueling procedures can be used to fuel a tank with inoperative fuel quantity indicators.Degraded Electronic Centralized Aircraft Monitoring (ECAM) indications (last two digits dashed "--")are considered operational and do not require alternate fueling procedures or verification by ManualMagnetic Level Indicators (MLI).

B. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), aVendor Supervisor, Lead or Supervisor/Lead, or Designated Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

C. If transferring fuel or other flight deck procedures becomes necessary, American Airlines (AA) FlightCrew or Maintenance personnel must be contacted in person to do these functions. For additionalassistance, such as malfunctioning fuel valve operation, opening and closing gear doors, transferringfuel, etc., contact AA Maintenance personnel in person or, if not on duty, contact MaintenanceOperations Center (MOC) in person.

D. Inoperative ECAM FUEL page indications for outer tank, inner tank or center tank require verificationof fuel quantity by MLIs.

19.10.2 Inoperative Wing/Center/Trim Tank Quantity Indication

A. The following outlines allowable inoperative gauge procedures.NOTE : Degraded ECAM Indications (last two digits dashed "--"), are considered operative and do

not require alternate fueling procedures or verification by MLIs.

NOTE : Refer to Section 15.01.5 for applicable method and recording requirements.

1. Method 1 - Flight deck display is operative and fuel panel display is inoperative.a. Fueling that tank can be accomplished using the flight deck ECAM display as the reference

display.b. One or more indicators can be inoperative at the fuel panel provided they are available in

the flight deck and either one member of the Flight Crew or aircraft Maintenance personnelremains in the flight deck to monitor the fueling operationNOTE : Communications between the fueler stationed at the fuel panel and the flight deck

must be established and maintained throughout the fueling operation.

c. Use of Method 1 will be noted on the fuel slip in the remarks field, with a copy of the fuel slipprovided to the Flight Crew as early as practicable after fueling.

2. Method 2A - Flight deck and fuel panel displays for the wing or the center tank are inoperative.CAUTION: DO NOT ATTEMPT TO FUEL THE AIRCRAFT USING THE AUTOMATIC

REFUEL METHOD. MULTIPLE PROBE FAILURE OR COMPUTER FAILUREHAS OCCURRED.

a. If the flight deck ECAM display and the fuel panel display are blank or display XXs, separaterefueling of the affected tank must be accomplished using the alternate refuel method.

b. Before fueling make sure the high level shutoffs are operational using the test switch at thefuel panel.

c. Before fueling, determine existing fuel tank quantity with the MLIs of the affected tank. Referto Figure 19.02-5. Subtract this quantity from the tank quantity required and convert to gallons.Fuel the tank to desired level, using the fueling equipment meter. Use MLIs to verify tankquantity. Refer to Section 19.10.3.

Section 19.10Alternate Fueling


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NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons,(refer to Section 15.01.7) to deliver the desired known quantity.

d. Provide Flight Crew with completed copy of fuel slip and an Inoperative Fuel Quantity IndicatorService Record making sure all required entries and signatures are legible and in place asearly as practicable, before departure.

3. Method 2B - Flight deck display is inoperative and fuel panel display is operative.a. Fueling that tank can be accomplished by using the operative fuel panel display as a reference.b. Fuel quantity in associated tank must be checked by manual MLIs.c. Before fueling, determine existing fuel tank quantity with the MLIs of the affected tank. Refer

to Figure 19.02-5. Subtract this quantity from the tank quantity required and convert to gallons.Fuel the tank to desired level, using the fueling equipment meter. Use MLIs to verify tankquantity. Refer to Section 19.10.3.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons,

(refer to Section 15.01.7) to deliver the desired known quantity.

d. Provide Flight Crew with completed copy of fuel slip and an Inoperative Fuel Quantity IndicatorService Record making sure all required entries and signatures are legible and in place asearly as practicable, before departure.

4. Method 3 - Flight deck and fuel panel displays for the wing or the center tank are inoperative.a. Completely defuel tank with the inoperative indicator by defueling or transferring fuel to other

tank(s). Refer to Section 19.11.WARNING: WHEN YOU OPERATE THE FUEL PUMPS DURING A MAINTENANCE

PROCEDURE, FLIGHT CREW OR A MAINTENANCE PERSON MUSTBE IN THE FLIGHT DECK. THIS PERSON MUST STOP THE PUMPSWHENTHE LOWPRESSUREFAULT LIGHT(S) (ONPANEL 40VU) COMEON, TOPREVENTOPERATIONOFTHEPUMP(S)WITHOUTFUEL (DRYRUNNING). OPERATION OF THE PUMPSWITHOUT FUEL CAN CAUSEA FIRE.

CAUTION: DO NOT LET THE FUEL PUMPS OPERATE FOR MORE THAN 15MINUTESWITH THE FAULT LIGHT ON. THIS CAN CAUSE DAMAGE TOTHE FUEL PUMPS.

b. Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged by thefuel equipment meter reading. Alternately, transfer required fuel from tank(s) with operativeindicator.

c. Fill tank(s) with operative indicator to quantity of fuel required.NOTE : Use of Method 3 requires final verification by MLIs. Refer to Section 19.10.3.

5. Flight deck and fuel panel displays for the trim tank are inoperative.a. The trim tank indication can be inoperative provided it is determined to be EMPTY.b. Empty trim tank can be verified by the automatic closure of the trim tank isolation valve during

manual forward transfer provided the tank mode Push Button Switch (P/B SW) is in the AUTOposition. This is a flight deck function. Refer to Section 19.12.3.

19.10.3 Determining Fuel Quantity By Magnetic Level Indicators (MLI)

A. Anytime fuel quantity is determined by MLIs, the following procedure must be used:1. Determine the Method, 2 or 3 (refer to Section 19.10.2), to be used to fuel the aircraft and check

the applicable box on the Inoperative Fuel Quantity Indicator Service Record.



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a. When using Method 2, do the following:(1) Determine:

a) The aircraft attitude before fueling.b) Tank MLIs needed to measure the fuel quantity, and associated charts to determine

the pounds in the affected tank.(2) Record the BEFORE FUELING information where applicable on the fuel slip and

Inoperative Fuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (for example, L,

LI, C, ACT1, Trim, etc.) in the space provided below "TANK."b) Record the BEFORE FUELING aircraft attitude (pitch and roll).c) Circle the MLIs utilized before fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only).d) Record the units/inches read from the applicable MLIs in the BEFORE FUELING

spaces.e) Record the BEFORE FUELING quantity from the applicable MLIs in pounds on the


a) The aircraft attitude after fueling.b) Tank MLIs needed to measure the fuel quantity, and associated charts to determine

the AFTER FUELING pounds in the affected tank.(5) Record the AFTERFUELING information where applicable on the fuel slip and Inoperative

Fuel Quantity Indicator Service Record:a) Record the AFTER FUELING aircraft attitude (pitch and roll).b) Circle the MLIs utilized after fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only).c) Record the units/inches read from the applicable MLIs in the AFTER FUELING

spaces.d) Record the AFTER FUELING quantity from the applicable MLIs in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Make sure all MLIs are secured and initial where applicable. Print your name, present

title, and company name followed by your complete signature (no initials).f) Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.

(6) The MLIs reading in inches and conversion to pounds must be verified by a FlightCrewmember by reviewing the completed fuel slip and Inoperative Fuel Quantity IndicatorService Record.

b. When using Method 3, do the following:(1) Empty the affected tank by defueling or transferring all remaining fuel to other tanks.

Refer to Section 19.11.(2) Record the BEFORE FUELING information where applicable on the fuel slip and

Inoperative Fuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (ex. L, LI, C,

ACT1, Trim, etc.) in the space provided below "TANK."b) Leave the BEFORE FUELING aircraft attitude (pitch and roll) spaces blank and do

not circle any MLIs utilized before fueling and applicable inner/outer cell tanks.



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c) Record the BEFORE FUELING quantity of 0 lbs. on the fuel slip and the InoperativeFuel Quantity Indicator Service Record.

(3) Fuel the tank to the desired amount by delivering a known quantity.(4) Determine:


the AFTER FUELING pounds in the affected tank.(5) Record the AFTERFUELING information where applicable on the fuel slip and Inoperative

Fuel Quantity Indicator Service Record:a) Record the AFTER FUELING aircraft attitude (pitch and roll).b) Circle the MLIs utilized after fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only).c) Record the units/inches read from the applicable MLIs in the AFTER FUELING

spaces.d) Record the AFTER FUELING quantity from the applicable MLIs in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Make sure all MLIs are secured and initial where applicable. Print your name, present


(6) The MLIs reading in inches and conversion to pounds must be verified by a FlightCrewmember by reviewing the completed fuel slip and Inoperative Fuel Quantity IndicatorService Record.

END



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Section 19.11 - Fuel Transfer19.11.1 General

NOTE : The Fuel Control Monitoring System (FCMS) must be energized for fuel ground transfer.

NOTE : Only Flight/Maintenance personnel can perform tasks in the flight deck.

19.11.2 Inner Tank Ground Fuel Transfer

NOTE : When fuel quantity in the Inner Tank decreases to 7716 lbs., the two intertank transfer valveswill open, automatically draining the outer tanks into the inner tanks.

A. Refuel Panel (Refer to Section 19.03.2.)1. MODE SELECT switch set to REFUEL.2. TRANSF valve switch set to OPEN.

NOTE : The TRANSF valve switch opens the left hand (LH) aft transfer valve (only if a relatedSTBY or main pump is on) and opens the right hand (RH) transfer valve (only if arelated STBY or main pump is on). This function prevents a loss of fuel pressure to theauxiliary power unit (APU).

3. Applicable REFUEL/DEFUEL valves are set to OPEN.B. Flight Deck Overhead Panel

1. STBY (or main) fuel pumps set to ON (Maintenance Personnel Only).2. Crossfeed valve pushbutton switch set to OPEN.3. When the required quantity is reached, release out the fuel pump switch(s) and crossfeed valve

switch.4. STBY (or main) fuel pumps set to OFF (Maintenance Personnel Only).5. Crossfeed valve pushbutton switch set to CLOSED.

C. Refuel Panel1. MODE SELECT switch set to OFF.2. TRANSF VALVE switch set to CLOSED.3. Applicable REFUEL/DEFUEL valves set to SHUT.4. Applicable REFUEL/DEFUEL valves set to NORM (switch guard down).

END

Section 19.11Fuel Transfer


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Section 19.12 - Defueling19.12.1 General

WARNING: MAKE SURE THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR.MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/ORDAMAGE TO EQUIPMENT.

A. Refuel/Defuel Panel (Refer to Section 19.03.2.)NOTE : If trim tank is to be fully defueled, Maintenance or Flight Crew must set the Trimmable

Horizontal Stabilizer (THS) to 0 degrees.

1. Put two access platforms in position.2. Open the access panels.3. Remove the refuel/defuel coupling caps.4. Connect couplings.

NOTE : If one hose is to be connected, it must be connected to the coupling identified "UseThis Adapter To Defuel."

5. Open fuel panel access door.6. Make sure the REFUEL-DEFUEL-VALVES switches are in the NORM (guarded) position.7. Set the MODE SELECT switch to the DEFUEL position.8. Set the TRANSF valve switch to open.

19.12.2 Defuel of the Center Tank

A. Defuel of the center tank to a lower quantity:1. Push (in) the L and R CTR TANK Pushbutton Switches (P/B SWs). Make sure that:

a. The OFF lights go off.b. On the Electronic Centralized Aircraft Monitoring (ECAM), the FUEL page shows the L and

R CTR TANK fuel pump symbols are in-line (pumps in operation).2. Monitor the fuel contents on the FUEL page. Make sure that the center tank and the total contents

figures decrease.3. When the fuel contents have decreased to the necessary level:

a. Release (out) the L and R CTR TANK P/B SWs. Make sure that:(1) The OFF lights come on.(2) The FUEL page shows the L and R CTR TANK fuel pump symbols are crossline (pumps

not in operation).4. Monitor the fuel contents indications on the FUEL page. Make sure that the indications become

stable. Read and make a record of the fuel quantities.CAUTION: DO NOT LET THE FUEL PUMPS OPERATE FOR MORE THAN 15 MINUTES

WITH THE FAULT LIGHT ON. THIS PREVENTS DAMAGE TO THE FUELPUMPS.

B. Defuel of the center tank until empty.1. Push (in) the L and R CTR TANK P/B SWs (3QL1 and 3QL2). Make sure that:

a. The OFF lights go off.b. The FUEL page shows the L and R CTR TANK fuel-pump symbols are in-line (pumps in

operation).

Section 19.12Defueling


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2. Operate the L and R CTR TANK pumps until a pump FAULT light comes on.3. Release (out) the related CTR TANK P/B SW. Make sure that:

a. The OFF light comes on.b. The FAULT light goes off.c. The FUEL page shows the related CTR TANK fuel pump symbol is cross-line (pump not in

operation).d. Do this operation for the other pump.

NOTE : Only Flight/Maintenance personnel can perform tasks in the flight deck.

19.12.3 Defuel of the Trim Tank

A. Defuel the Trim Tank by manual forward transfer.1. Push in the T TANK MODE P/B SW on flight deck overhead fuel panel.

a. Make sure the FWD light comes on.b. Make sure the fuel page show the trim-tank isolation valve symbol is in-line (valve open) and

the forward-transfer triangular symbol (fuel-transfer in operation).2. Monitor the fuel contents, making sure the trim tank figure decreases.

NOTE : If trim tank quantity indication is inoperative on ECAM, the trim tank may be verifiedempty by automatic closure of the trim tank isolation valve during manual forwardtransfer provided the tank mode P/B SW is in auto position. The automatic closure ofthe isolation valve can be viewed on the ECAM panel page.

NOTE : During defueling, the fuel from the trim tank goes in to the two inner tanks. Make surethat there is enough space in the inner tanks. If the inner tanks are full, use the suctiondefuel procedure to defuel the trim tank.

3. When the fuel contents have decreased to the necessary level, release the T TANK MODE P/BSW.a. Make sure the FWD light goes off.b. Make sure the fuel pages shows the trim-tank isolation valve symbol is cross-line (valve

closed) and the forward-transfer triangular symbol is not in view (fuel-transfer is not inoperation).

4. Monitor the fuel content on the FUEL page. Make sure the trim tank indications become stable.Read and make a record of the fuel quantities.

19.12.4 Defueling Wing Tanks - Lower Quantity

NOTE : The Fuel Control Monitoring System (FCMS) prevents a defuel of the wing tanks until the trimtank is empty.

A. Refuel/Defuel Panel (Refer to Section 19.02.2)1. REFUEL-DEFUEL-VALVES switches in the NORM (guarded) position.2. Mode select switch DEFUEL position.

B. Flight Deck1. Push (in) the L STBY and the R STBY P/B SWs to start the pumps. Make sure that:

a. The OFF lights go off.b. The FUEL page shows the related fuel pump symbol is IN-LINE (pumps in operation).

2. Monitor the fuel contents indications on the FUEL page. Make sure that the inner tank contentsand the total fuel contents figures decrease.



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NOTE : When the fuel quantity in one of the inner tanks decreases to 8820 lbs. (4000 kg), thetwo intertank transfer valves open. Fuel from the outer tanks then flows in to the innertanks.

3. When the fuel contents have decreased to the necessary levels, release (out) the L STBY andthe R STBY P/B SWs. Make sure:a. The related pump P/B SW OFF light comes on.b. The FUEL page show the related fuel pump symbol is cross-line (pumps not in operation).

4. Monitor the fuel contents indications on the FUEL page. Make sure that the indications becomestable. Read and make a record of the fuel quantities.

19.12.5 Defueling Wing Tanks - Empty

CAUTION: DO NOT LET THE FUEL PUMPS OPERATE FOR MORE THAN 15 MINUTES WITHTHE FAULT LIGHT ON. THIS PREVENTS DAMAGE TO THE FUEL PUMPS.

A. Flight Deck1. Push (in) the L1, R1, L STBY and the R STBY P/B SWs to start the pumps. Make sure:

a. The OFF lights go off.b. The FUEL page shows that the related fuel pump symbol is in-line (pumps in operation).

2. Monitor the fuel quantity in the collector cells.3. When the fuel level in the collector cell is approximately 1100 lbs. (500 kg), put the TRANSF

VALVE switch to CLOSED.NOTE : During a defuel, the fuel pump can empty the collector cell faster than the collector cell

can fill. Thus, you must let the collector cell fill again BEFORE the defuel can continue.

4. When the collector cell is full again, put the TRANSF VALVE switch to OPEN.5. Do these steps again until the inner tank indication is zero.6. Operate the pump until a pump FAULT light comes on.7. Release (out) the related pump P/B SW. Make sure:

a. The relate FAULT light goes off.b. The related pump P/B SW OFF light comes on.c. The FUEL page shows the related fuel pump symbol is cross-line (pump not in operation).d. Do this for EACH pump.

8. On the ECAM make sure that the fuel page shows:a. The trim tank isolation valve symbol is cross-line (valve closed).b. The forward fuel transfer symbol is not in view (fuel-transfer not in operation).c. The fuel pump symbols are cross-line (pumps not in operation).

19.12.6 Suction Defueling

A. Refuel/Defuel Panel (Refer to Section 19.03.2.)1. MODE SELECT switch is set to DEFUEL.2. The necessary fuel-tank refuel/defuel valves switches are set to OPEN.3. The fuel is then removed from the set fuel tanks by suction from the tanker.

NOTE : If the trim tank contains fuel, then fuel-system interlocks prevent a suction defuel ofthe inner tanks.

4. When finished defueling, set refuel/defuel valves switches to SHUT.



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19.12.7 CLOSE UP

A. Refuel/Defuel Panel (Refer to Section 19.03.2.)1. Make sure the refuel/defuel valves switches are set to NORM (guarded) position.2. Set the MODE SELECT switch to the OFF position.3. Close the access panel.4. Disconnect the defuel couplings.5. Install the caps.6. Close the access panels.

END



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Section 19.13 - Magnetic Level Indicators (MLI)19.13.1 General

CAUTION: IT IS IMPORTANT TO MAKE THE CORRECT CALCULATIONS.

CAUTION: VERIFY ANY MINIMUM EQUIPMENT LIST (MEL) PLACARD THAT IS POSTEDON/NEAR THE INOPERATIVE INDICATOR. THE SUPERVISOR FUELING OR LEADFUELER MUST BE PRESENT TO OVERSEE THE ENTIRE ALTERNATE FUELINGPROCEDURE.

NOTE : For applicable Method and Recording requirements, refer to Section 15.01.

19.13.2 Access

A. Open the fuel control panel access panel.

19.13.3 Specific Gravity (SG)/Density

A. Get a fuel sample from the aircraft and find its density.B. Alternate procedure:

1. The SG is also available on the Fuel Control Monitoring System (FCMS) Input Parameters Page3. Use the SG to find the density (multiply SG x 8.34 to find density in lbs./gal).

2. Use density of 6.7 lbs./gal (per fuel standard).

19.13.4 MLI System and Stick Number Attitude Charts

A. Put an adjustable access platform below the applicable Magnetic Level Indicators (MLI) (refer toFigure 19.13-1).CAUTION: DO NOT LET THE MAGNETIC LEVEL INDICATORS FALL FREELY. THE

MAGNETIC LEVEL INDICATORS ARE FRAGILE.

CAUTION: RETRACT THE MAGNETIC LEVEL INDICATORS AS SOON AS POSSIBLE.DAMAGE TO AN EXTENDED MLI CAN BE EASILY CAUSED.

NOTE : To do the MLI procedure on the inner tanks, the main fuel pumps must not be in operation.If themain pumps have been in operation, wait tenminutes before starting theMLI procedure.This allows the fuel to settle down making sure a level reading is taken during the MLIoperation. Afterwards, use the time curve shown on the Collector-Cell Correction FactorChart to get a correct reading. Refer to Table 19.13-1.

NOTE : The MLIs in the center and inner tanks are accurate to ± 5% of their indication. The MLIsin the outer tank are accurate to ± 7.5% of their indication. MLI values are not as accurateas the values given by the Fuel Control and Monitoring Computer (FCMC) and you mustnot use them for comparison.

NOTE : Start the procedure with each of the outboard MLIs in the outer and inner tank. If they haveno reading, move to the next MLI inboard. Continue moving inboard until an MLI shows areading. When a MLI shows a reading, use that MLI for the procedure.

B. Use a screwdriver to push (in) the applicable MLI and turn it through 90 degrees(°).C. Hold and carefully lower the MLI fully. Then carefully lift the MLI until the magnets engage.D. Read the units mark nearest to the bottom skin of the wing and write down the number.


Section 19.13Magnetic Level Indicators (MLI)


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E. Retract the MLI and use a screwdriver to turn it through 90° to lock it.F. Do this procedure for each applicable MLI.

NOTE : Only use one MLI reading from each applicable tank.

G. Calculation Procedure1. Read and write down the aircraft attitude. Obtain the pitch and roll from Air Data/Inertial Reference

Unit (ADIRU).NOTE : For applicable Method and Recording requirements, refer to Section 15.01.

NOTE : Maintenance personnel can obtain the pitch and roll from the ADIRU.

2. Use the applicable MLI Stick # Attitude Charts. Refer to Section 19.13.5. Based on pitch/roll dataand MLI stick height to find the volume of fuel in the tank. Refer to Figure 19.13-2 and Section19.13.5.

3. For an inner tank, there could be additional fuel in the collector-cells. To find the additional fuelquantity in one inner tank, refer to Table 19.13-1. This is to be added to the corrected quantity ofthe inner tank, to give at total quantity of the inner tank.

4. Add the additional GALLONS to the indicated tank volume to get actual volume1.NOTE : This procedure is not applicable (N/A) for any inner tank quantity above 3,000 gallons

as the collectors will be full.

NOTE : The fuel quantity in the collector cell will decrease with time. Use the applicable columnthat specifies the time since the main fuel pumps have been switched off. The datataken from this table gives a more accurate fuel quantity. To verify time since pumpsOFF contact operations in person or other agreeable method for the most current blocktime. Refer Table 19.13-1.

Table 19.13-1: Correction for Collection Tank Quantity (One Inner Tank)

ADDITIONAL FUEL QUANTITY (GALLONS)1INDICATED TANK

TIME SINCE PUMPS SHUT-OFF (MIN)

90+60+40+30+20+10+VOLUME (US GALLONS)

3396

3170

122867

232641

12382339

26522113

1449671811

3864901585

2460841101282

50811101401056

1277109137172792

42106136172198528

1294159185224254226

271191802142512770

5. Use the applicable Attitude charts based on pitch/roll data and MLI stick height to find the volumeof fuel in the tank. Refer to Figure 19.13-2 and Section Section 19.13.5.NOTE : The trim-tank can also contain fuel quantity of between 0 and 10,582 lbs. (4,800 kg).



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Figure 19.13-1: MLI - Locations



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Figure 19.13-2: Air Data/Inertial Reference System (ADIRS) Roll Indications for Left and Right Wing

19.13.5 Magnetic Level Indicators MLI Charts

A. Refer to A330-200 Magnetic Level Indicators MLI Charts as follows:1. Access the Stick Charts at http://me.aa.com/manuals/fw/FuelingStickCharts/#z

END



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Table of contents

20.01 FUELING MANUAL - A330-300GENERAL..........................................................................................................................1FUEL DISTRIBUTION.......................................................................................................1

20.02 FUEL SYSTEM INFORMATIONGENERAL..........................................................................................................................1SYSTEM DETAILS.............................................................................................................1

20.03 FUEL PANEL DESCRIPTIONGENERAL..........................................................................................................................1FUELING PANEL (990VU)................................................................................................1

20.04 SAFETY PRECAUTIONSGENERAL..........................................................................................................................1

20.05 GENERAL FUELINGFUEL TANK SUMP CHECK..............................................................................................1

20.06 FUEL SYSTEM TESTGENERAL..........................................................................................................................1TEST PROCEDURE..........................................................................................................1

20.07 PRESSURE FUELING WITH AUTOMATIC CONTROLPRESSURE REFUEL WITH AUTOMATIC CONTROL FROM PANEL 990VU.................1

20.08 PRESSURE FUELING WITH MANUAL CONTROL - LOAD PRESELECTOR INOPPROCEDURES..................................................................................................................1

20.09 OVERWING FUELINGPROCEDURES - OVERWING FUELING..........................................................................1

20.10 ALTERNATE FUELINGGENERAL..........................................................................................................................1PROCEDURES - INOPERATIVE WING/TRIM-TANK QUANTITY INDICATION..............1DETERMINING FUEL QUANTITY BY MLIS.....................................................................2

20.11 FUEL TRANSFER



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GENERAL..........................................................................................................................1PROCEDURES - INNER TANK GROUND LEVEL TRANSFER.......................................1

20.12 DEFUELINGGENERAL..........................................................................................................................1PROCEDURES - DEFUELING WING TANKS (LOWER QUANTITY)..............................2PROCEDURES - DEFUELING WING TANKS (EMPTY)..................................................2PROCEDURES - SUCTION DEFUELING.........................................................................3PROCEDURES - CLOSE UP............................................................................................3

20.13 MAGNETIC LEVEL INDICATORS (MIL)GENERAL..........................................................................................................................1PROCEDURES - ACCESS................................................................................................1PROCEDURES - SPECIFIC GRAVITY/DENSITY.............................................................1PROCEDURES - MLI SYSTEM AND STICK NUMBER ATTITUDE CHARTS..................1MAGNETIC LEVEL INDICATORS MLI CHARTS..............................................................4



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Section 20.01 - Fueling Manual - A330-30020.01.1 General

A. The fuel system has two main tanks and one trim tank. There is also a vent surge tank located in eachwing, outboard of the wing tank and in each Trimable Horizontal Stabilizer (THS), outboard of the trimtank.1. For all A330-300 aircraft:

a. Trim tank has an approximate volume of 1,644 US gal.b. Main (wing) tanks each have an approximate volume of 12,051 US gal.


NOTE : This aircraft also contains collector cells. Each collector cell is maintained full offuel for the main booster pumps. The approximate fuel quantity in each collectorcell is 2,512 lbs, provided that the fuel density is 6.70 lb/gal. Actual fuel weightcapacity will vary depending on fuel density.

Table 20.01-1: Refuel Pressure

40 pounds per square inch (PSI)Maximum Refuel Pressure (Primary)

50 PSIMaximum Refuel Pressure (Secondary)

350 gallons per minute (General Procedures Manual (GPM))Maximum Refuel Rate - Wing Tanks

450 GPMMaximum Refuel Rate - Simultaneous

11 PSIMaximum Defuel Pressure

Right Wing FairingFuel Panel Location (Primary)

Left WingFuel Panel Location (Secondary)

NOTE : Fuel pressure should not exceed a constant 50 pounds per square inch, gauge (psig) at anytime during the fueling operation.

20.01.2 Fuel Distribution

WARNING: DO NOT OPERATE THE HIGH FREQUENCY COMMUNICATION SYSTEM WHILEFUELING THE AIRPLANE. A FIRE OR AN EXPLOSION CAN OCCUR.

GROUND EQUIPMENT MUST NOT BE POSITIONED UNDER WING TIPS DURINGFUELING OPERATION.

FUELING VEHICLE MUST BE PROPERLY BONDED TO AIRCRAFT BEFORE ANYFUELING/DEFUELING OPERATION.

WHEN THERE IS AN INACCURATE/INOPERATIVE OR SUSPICION OF A GAUGENOT INDICATING PROPERLY, STOP FUELING AND NOTIFY AIRCRAFTMAINTENANCE IMMEDIATELY IN PERSON.

NOTE : If a fuel component(s) is currently on MEL placard as being inoperative, Aircraft Maintenancedoes not need to be notified, unless specific procedures during fueling operations require theattention of Aircraft Maintenance.

If a circuit breaker is tripped, trips or opens during fueling operation, notify Aircraft Maintenanceimmediately in person. Do not start or resume fueling operations until corrective action has beentaken. Do not start or shut down APU should fuel spill occur.



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Defueling or transferring fuel with passengers onboard the aircraft is prohibited, except undercertain conditions.

Table 20.01-2: A330-300 Fuel Distribution (assuming a fuel density of 6.70 lb/gal)

Trim Tank(lbs.)

Right Tank Inner(lbs.)

Right TankOuter (lbs.)

Left Tank Inner(lbs.)

Left TankOuter(lbs.)

Total Fuel (lbs.)

000000

02,00202,00204,000

04,00104,00108,000

06,00106,001012,000

06,6141,3876,6141,38716,000

06,6143,3866,6143,38620,000

06,6145,3886,6145,38824,000

07,5646,4377,5646,43728,000

09,5646,4379,5646,43732,000

011,5636,43711,5636,43736,000

013,5636,43713,5636,43740,000

015,5656,43715,5656,43744,000

017,5646,43717,5646,43748,000

019,5646,43719,5646,43752,000

021,5636,43721,5636,43756,000

025,5636,43725,5636,43760,000

025,5636,43725,5636,43764,000

027,5646,43727,5646,43768,000

029,5646,43729,5646,43772,000

031,5646,43731,5646,43776,000

033,5636,43733,5636,43780,000

3,53233,7976,43733,7976,43784,000

5,29134,9196,43734,9196,43788,000

5,29136,9196,43736,9196,43792,000

5,29138,9186,43738,9186,43796,000

5,29140,9186,43740,9186,437100,000

5,29142,9176,43742,9176,437104,000

5,29144,9176,43744,9176,437108,000

5,29146,9196,43746,9196,437112,000



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Trim Tank(lbs.)

Right Tank Inner(lbs.)

Right TankOuter (lbs.)

Left Tank Inner(lbs.)

Left TankOuter(lbs.)

Total Fuel (lbs.)

5,29148,9186,43748,9186,437116,000

5,29150,9186,43750,9186,437120,000

5,29152,9186,43752,9186,437124,000

5,29154,9176,43754,9176,437128,000

5,29156,9196,43756,9196,437132,000

5,29158,9196,43758,9196,437136,000

5,29160,9186,43760,9186,437140,000

5,29162,9186,43762,9186,437144,000

5,29164,9176,43764,9176,437148,000

5,29166,9196,43766,9196,437152,000

5,29168,9196,43768,9196,437156,000

5,29170,9186,43770,9186,437160,000

5,29172,9186,43772,9186,437164,000

6,97574,0756,43774,0756,437168,000

10,97574,0756,43774,0756,437172,000

10,98874,0756,43774,0756,437174,000



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Figure 20.01-1: Tanks - Location

END



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Section 20.02 - Fuel System Information20.02.1 General

A. Fueling is done in the following manner:1. A pressure refuel through couplings in the lower surface of each wing (auto/manual).2. A gravity over wing refuel through over wing ports in the upper surface of each wing.

NOTE : The tankers should be positioned as outlined in Figure 20.02-1.

B. The system can be powered electrically from:1. On-board auxiliary power unit (APU)2. Ground Power Unit (GPU)3. On-board battery

C. Refueling can be controlled from:1. A refuel panel in the right lower belly fairing.2. A secondary refuel panel next to the left wing receptacles.

20.02.2 System Details

A. The fuel system stores fuel in the main fuel tanks and the trim tank, 5 tanks total. Refer toFigure 20.02-2.The fuel system controls and supplies fuel in the correct quantities to the fuel tanks during refueling.It supplies fuel to the engines and APU, while transferring fuel to and from the trim tank to keep theCenter of Gravity (CG) within limits.

B. A set of pipes connects the refuel couplings to the fuel inlet valve of each tank. Refueling is normallyautomatic, the required fuel load being set on the preselector. All tanks that require refueling start tobe refueled simultaneously. Refuel valves close automatically when the tanks contain the preselectedload or when sensors detect a high fuel level. Manual control is available. Transfer is possible fromeither inner tank to any other tank except the trim tank, provided the Fuel Control and MonitoringComputer (FCMC) is powered.

C. Each inner tank contains a collector cell. This makes a fuel reservoir for two main engine-feed fuelpumps. Each pair of fuel pumps has one standby fuel pump. Vent surge tanks are installed outboardof each outer tank and on the right hand (RH) side of the trim tank in the Trimable Horizontal Stabilizer(THS). Each vent surge tank has a minimum capacity (before leakage can occur) which is five timeslarger than the volume of its vent pipes. This makes sure that there is no fuel spillage during aircraftmovement on the ground and take-off. All fuel tanks have water drain valves at their lowest point.

D. After a refuel operation to the maximum tank capacity, the fuel can expand 2% (68 degrees Fahrenheit(°F); 20 degrees Celsius (°C) temperature increase), without spillage at the refuel attitude and duringsubsequent:1. Towing2. Aircraft movement3. Take-off and rejected take-off.



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Figure 20.02-1: Tanker Positions

NOTE : Tanker positions are subject to change according to local or airport requirements.



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Figure 20.02-2: Identification of Fuel System Valves

E. The Refuel/Defuel system controls the flow of fuel into or out of the aircraft. It is controlled from therefuel/defuel control panel 990VU in the RH lower belly fairing or (left wing). Refer to Figure 20.02-3.Tworefuel/defuel fuel hose couplings are installed in the leading edge of the left hand (LH) and RH wings.Refer to Figure 20.02-4. These are the interface between the refuel/defuel system and the externalfuel supply. Each refuel/defuel coupling can have two refuel hoses connected to it.1. There are two different procedures to refuel the aircraft:

a. Pressure refuel (automatic/manual)b. Over wing refuel (gravity/manual)

2. To fill the fuel tanks to their maximum capacity, the aircraft must be on the level ground and theTHS set at 0 degrees. It is possible to refuel the aircraft on a ground slope of up to 2 degreesand still get the maximum capacity. But, on ground slopes of more than 2 degrees, it is not possibleto get the maximum capacity.



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3. When the refuel supply is from four fuel hoses, the time to refuel the aircraft (from the usualreserves to the maximum capacity) is limited by pump pressure. The fuel distribution after refueldepends on the quantity of fuel in the aircraft.WARNING: DURING REFUEL OPERATION, IT IS NECESSARY TO KEEP A SAFE

LONGITUDINAL BALANCE IN THE AIRCRAFT. IT IS IMPERATIVE TO KEEPFUEL LOAD IN ACCORDANCE WITH THE REFUEL DISTRIBUTION TABLE.THUS, THE INLET VALVE TO THE TRIM TANK CANNOT OPEN UNLESSONE OF THESE TWO CONDITIONS OCCUR:

THE FUEL CONTENTS IN THE TWO INNER TANKS ARE AT HI-LEVEL.

THE TWO INLET VALVES OF THE INNER TANKS ARE OPEN.

4. When the quick-release door to the refuel/defuel panel opens, it activates a microswitch whichsends a signal to the FCMS. In addition, power is supplied to all fueling panel functions. The loadswitch sets the preselected fuel quantity. This is shown in the PRESELECTED window of theFuel Quantity Indicating (FQI) system. To do a refuel, this quantity must be set to a larger valuethan the ACTUAL indication. The MODE SELECT switch is set to REFUEL, which sends a signalto the FCMS and supplies electrical power to the fuel system components. At the start of refuel,the hi-level test push button switch is pushed in, sending a continuity test signal to the hi-leveland overflow sensors, along with their circuits.

5. At the end of the refuel, the END light comes on to show that the refuel is completed. The MODESELECT switch is set to OFF and the isolation valve closes. If the fuel distribution at the end ofthe refuel is incorrect, it can be corrected through a ground transfer. If the difference in the wingsis greater than 6614 lbs. (3000 kilogram (kg)):a. The END light on the refuel/defuel control panel flashes.b. A WING TK FUEL IMBALANCE warning is given on the ECAM.

6. If the difference between the ACTUAL fuel load and the PRESELECTED fuel load is more than440 lbs. (200 kg) 10 seconds after the refuel is completed, one more refuel can be made. If thefuel quantity is still out of this limit, the END light on the refuel/defuel panel flashes.



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Figure 20.02-3: Refuel/Defuel Control Panels



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Figure 20.02-4: Refuel/Defuel Control Couplings

F. There are two procedures to defuel the aircraft:1. Pressure (aircraft fuel pumps supply the fuel to the defueler).2. Suction (defueler supplies the suction to remove the fuel).

a. It is possible to suction defuel all of the fuel tanks. But, when the trim tank contains fuel, it isnot possible to suction defuel the wing tanks. On the ground, it is possible to move fuel fromtank to tank through the fuel ground transfer procedure.

G. The Fuel Indicating Systems are:1. FQI system, which gives separate and total fuel quantity indications.2. The Magnetic Level Indicators (MLI), a secondary system used to estimate fuel quantity when

the aircraft is on the ground.3. The tank level sensing which gives indications and warnings when the fuel is at given levels.



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4. The fuel temperature measurement, which gives continuous temperature indications and warningswhen the fuel temperature is at specified levels.

H. FQI1. Measures the total quantity of fuel in the range unusable to overflow. It gives fuel indications for

each of the fuel tank areas (LH/RH outer/inner/collector/trim tanks). The FQI has fuel probes witha capacitance that is in proportion to the amount to fuel that touches the probes. The Fuel Controland Monitoring System (FCMS) continuously measures the capacitances in each area.

I. MLI1. A secondary direct-reading system used (only on the ground) to calculate the fuel quantity in the

inner and outer tanks. It is not necessary to have electrical power to use the indicators.NOTE : Since there are no Magnetic Level Indicators in the trim tank, the MLI procedure does

not include trim tank. Refer to Figure 20.02-5.

NOTE : If the trim tank quantity indication is inoperative at the refuel panel(s) and the flightdeck, then the trim tank must be verified to be full or empty.

J. Tank Level Sensing1. The fuel system has level sensors which send fuel level signals to the FCMS. The FCMS uses

the fuel level data to control the operation of the tank inlet valves during a refuel or fuel transfer.



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Figure 20.02-5: Magnetic Level Indicators - Inner and Outer Tanks

END



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Section 20.03 - Fuel Panel Description20.03.1 General

A. The primary components of the Fueling system are the External Fueling Panels (990vu). There is anexternal panel mounted in the right side belly fairing, behind access panel 198DB, along with anotherpanel in the left wing. These panels are used to control the refuel operation, either in automatic modeunder the control of the Fuel Control and Monitoring Computer (FCMC) or in manual mode from theRefuel-Defuel-Valves switches. Refer to Figure 20.03-1.

20.03.2 Fueling Panel (990vu)

A. Fuel Quantity Indicator (FQI) Panel1. Shows the quantity of fuel in each fuel tank, the total fuel quantity (ACTUAL) in the aircraft and

the required fuel quantity (PRESELECTED). Refer to Figure 20.03-1.B. Load Switch

1. Used to set the required fuel quantity on the PRESELECTED display.C. Mode Select Switch

1. When set to REFUEL, the fuel-tank inlet valves can be opened and shut either automatically bythe FCMC ormanually by the applicable REFUEL/DEFUELVALVES switch.When set to DEFUEL,the inlet-valves can be opened and shut manually as required.

D. Refuel/Defuel Valves Switches1. Opens or shuts the applicable fuel-tank inlet valve and overrides any automatic command. When

set to NORM, the FCMC controls the operation of the inlet valves. If an inlet valve actuator fails,valves may be opened or closed by Maintenance personnel only.NOTE : The FCMC gives priority to a valve switch command over that of a software command.

Therefore, an Auto-Refuel, with the correct fuel distribution, can only be achieved whenall the REFUEL/DEFUEL VALVES switches are set to NORM.

E. High Level Lights1. Illuminate when the related fuel-tank high level sensors are wet, indicating a fuel tank is full. The

trim tank high level light can be used for full tank verification if the FQI for this tank is operativeat the Refuel Panel(s) and Flight Deck.

F. Overflow Lights1. Illuminate when the related surge tank level sensors are wet.

Section 20.03Fuel Panel Description


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Figure 20.03-1: Fueling Panel (990vu)

G. High Level Test1. Before the start of a refuel, a test of the High Level Protection system is required. To start the

test, the HI LVL TEST Push Button Switch (P/BSW) is pushed in and held, for approximately 10seconds. If the applicable circuits and level sensors are serviceable, the six HIGH LEVEL lightsand the three OVERFLOW lights come on. If a fuel-tank is full or a surge-tank has overflowed,such that the high-level light is already on, the test turns the light off. Therefore, if a light doesnot change from its initial state during the test, there is a fault with the applicable circuit.NOTE : A sensor circuit can fail such that the high-level light, or overflow light comes on when

a tank is not full. This condition is described in this handbook as "failed wet."

H. Transfer Valve Switch1. Controls the operation of the Aft Transfer. This enables a post-refuel ground-transfer of fuel, from

one aircraft fuel-tank to another, to be controlled from the external fueling panel.NOTE : The TRANSFER VALVE must be set to CLOSED during an auto-refuel operation.

I. Power Supply Switch1. When the PWR SUPPLY switch is set to NORM, the refuel power source can be from either the

auxiliary power unit (APU), or a ground power unit (GPU). When the switch is set to BAT, thepower source is from the aircraft batteries.



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J. Emergency Shutdown1. This switch is used to shut down the APU if a fuel spillage or overflow occurs.

K. End Indicator Light1. A steady light indicates that the refuel is complete. A flashing light indicates that the refuel isolation

valves have shut, if one of the following conditions occurs:a. Surge tank overflow sensor is wet.b. Jettison valve is open.c. Fuel tank high level sensor circuit has failed.d. T TANK FWD, transfer push button switch (P/BSW) is pushed (in).e. There is a difference between the flight deck fuel control panel set up and the external

refuel/defuel panel set up.L. Flight Deck Indicator

1. Not usedM. Refuel/Defuel Couplings

1. There is a refuel/defuel coupling in each wing. Each coupling has two valve heads allowing upto four refuel hoses to be connected at the same time. An isolation valve is installed in a circularhousing at the center of each coupling.

N. Refuel/Defuel Isolation Valve1. There is an electrically controlled and fuel pressure operated isolation valve, incorporated in each

coupling. The refuel isolation valve controls the fuel supply from the refuel source to the refuelgallery. In case of an electrical failure, the isolation valves may be opened manually by meansof an override switch mounted on the valve housing. Fuel passes through the isolation valve intoa refuel gallery from where fuel flows to the inlet valves out of the various aircraft fuel tanks (inner,outer and trim).NOTE : The refuel pressure at the isolation valve must not exceed (40 pounds per square inch

(psi)).

O. Fuel Probes1. The FQI system has fuel probes with a capacitance that is in proportion to the amount of fuel that

touches the probes. The Fuel Control Monitoring System (FCMS) continuously measures thiscapacitance and uses the fuel quantity data to control the operation of the fuel system and displaythe fuel tank quantities.

P. High Level/Overflow Sensors1. Two high level sensors are installed in each main fuel tank and one overflow sensor is installed

in each wing surge tank and the trim surge tank. The high level sensors in the wing and trim tanksare set at the same level and when they become wet the FCMC closes the applicable inlet valve.When an overflow sensor in a surge tank becomes wet, the FCMC closes the refuel isolationvalves.

Q. Inlet Valves1. The primary function of the inlet valves is to control the flow of fuel from the refuel gallery into the

related tank.NOTE : Manual override of the inlet valve actuators is a maintenance function only.

R. FCMC1. There are two FCMCs in the FCMS which control the automatic refuel process. Each FCMC

receives input data from fuel: Temperature sensors; densitometers; quantity probes and levelsensors. These data are reused by the two FCMCs to continuously calculate the fuel distribution



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and center of gravity, and give protection against aircraft overbalance and fuel spillage. However,only the FCMC in control (normally FCMC1) sends discrete command signals to the refuel isolationvalves and the applicable inlet valves, used in the refuel process. Each FCMC has hardware andsoftware that provides the FCMC with Built-In-Test Equipment (BITE). The BITE continuouslymonitors the FCMC and fuel system components for failures and can do a BITE (self) Test.

END



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Section 20.04 - Safety Precautions20.04.1 General

A. The following material outlines the minimal procedures for fueling American Airlines (AA) A330 aircraft.The procedures are intended to sequentially outline the necessary steps to make sure of safe andefficient fueling operation.1. Obtain a Jet Fuel Service Record (Fuel Slip). Refer to Section 15.01.

a. Before positioning fueling equipment around aircraft, aircraft engines must be shut down andwheel chocks must be in place.

2. Properly position refueling equipment.a. Maintain 5-foot separation between aircraft and fueling equipment.

(1) Since fueling equipment can vary in model, type and size, it can be necessary to usefuel equipment parking positions other than those shown in this manual due to localstation regulations and passenger boarding bridge/aircraft gate positioning. Refer toFigure 20.04-1.

(2) Unless these conditions exist, a five foot clearance must be maintained at all times whenfuel equipment is positioned at the gate.

Only fuel equipment that is designed to fuel aircraft by positioningunder the wing can be used to service the aircraft. This equipmentMUST maintain a 12-inch clearance from the underside of the wing tothe highest part of the equipment when positioned under the aircraftwing. This clearance must be maintained the entire time the aircraft isbeing fueled.

EXCEPTIONS:

Hydrant Truck with Lift Deck

Low Profile Tank Truck

Stationary Hydrant Cart

Examples:

NOTE : Stationary Hydrant Carts must be parked in the designated ramp area at alltimes.



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Figure 20.04-1: Fueling Equipment Positioning

b. Never back refueler (tank truck) towards or away from the aircraft without a guide person.NOTE : For vehicles equipped with an operating backup video camera and monitor, the

use of a guide person is not required.

B. Bond refueler to aircraft bonding lug below on right or left main landing gear (MLG). Refer toFigure 20.04-2.

C. Stop fuel tanker 200 feet (60 m) from aircraft while the weather radar is in operation. Do not beginrefuel/defuel operations until weather radar is turned off.

D. Do not refuel/defuel within 100 feet (30 m) of operating radar of High Frequency (HF) radar equipment.E. Make sure fuel tanker/hydrant contains correct fuel.F. If an auxiliary power unit (APU) must be operating during refuel/defuel, the following is mandatory:

1. APUmust be started before start of refuel/defuel except in an emergency (for example, fuel spill).2. Do NOT stop APU during refuel/defuel except in an emergency (for example, fuel spill.)3. If APU stops during refuel/defuel, do not start the APU again until there is no danger of fuel vapor

ignition.G. Make sure all electrical equipment used does NOT cause sparks.H. If passengers remain on board during refueling, a flight attendant must be in the cabin near the main

entry door. The passenger loading bridge must be attached to the aircraft with the main entry dooropen at all times.



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Figure 20.04-2: Location of the Grounding Points on the NLG and MLG

END



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Section 20.05 - General Fueling20.05.1 Fuel Tank Sump Check

A. Fuel Tank Sump Locations1. There are seven sump valves on each wing, outboard vent surge tank, outboard wing outer and

inboard wing inner tank and two sump valves for the trim tank. Refer to Figure 20.05-1.B. Fuel Tank Sump Check

1. Aircraft fuel sumping is the responsibility of Maintenance personnel and is to be in accordancewith scheduled maintenance checks.



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Figure 20.05-1: Water Drain Valves - Location

END



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Section 20.06 - Fuel System Test20.06.1 General

A. This test must be performed before any refueling operation. Refer to Section 20.06.2.B. The High Level Detection System can be inoperative (for example, on MEL). If so, you must

continuously monitor the fuel quantity during refueling.1. If the Inner Tanks High Level Detection System is inoperative, the Inner Tank fuel quantity

indications in the cockpit must be operative.2. If the Outer Tank quantity indicators are inoperative, and the Outer Tank High Level Detection

System is inoperative, you must continuously monitor the Outer Tank fuel quantity through theMagnetic Level Indicators (MLI).

20.06.2 Test Procedure

A. Open fuel panel door. Refer to Section 20.03.2.NOTE : If the fuel panel does not energize, put the PWR SUPPLY switch to BAT.

NOTE : Ignore the indications during the first 30 seconds after power-up.

B. On the refuel/defuel control panel HI LEVEL TEST switch lift guard, push (in) and hold.1. The HI LEVEL lights and the OVERFLOW lights go to the opposite condition.2. The CKPT and END lights come on.3. The PRESELECTED and ACTUAL fuel quantity displays show all 8’s.

C. Release HI-LEVEL TEST switch.1. Wait 10 seconds.2. The lights go back to their initial condition.3. The PRESELECTED and ACTUAL fuel quantity displays go back to their initial condition.

END

Section 20.06Fuel System Test


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Section 20.07 - Pressure Fueling with Automatic Control20.07.1 Pressure Refuel with Automatic Control from Panel 990vu

CAUTION: DO NOT LET THE REFUEL PRESSURE GET TO MORE THAN 50 POUNDS PERSQUARE INCH (PSI). THIS WILL PREVENT DAMAGE TO THE AIRCRAFT FUELSYSTEM.

A. On the refuel/defuel control panel 990vu (Refer to Section 20.03.02):1. Put the LOAD switch to the INC position and hold it there.2. Make sure that the numbers on the PRESELECTED display increase.3. When the PRESELECTED display show the necessary fuel load, release the LOAD switch.

NOTE : To do a refuel, the figure set must be a minimum of 440 pounds (lbs.) (200 kilogram(kg)) more than the Fuel on Board (FOB) figure.

4. Make sure that the REFUEL VALVES switches are in the NORM position and guarded.NOTE : If a switch is moved to SHUT during the automatic refuel, the applicable valve closes.

If a switch is moved to OPEN during the automatic refuel, the Fuel Control andMonitoring System (FCMS) ignores the command until the automatic refuel is complete.After approximately 15 seconds the refuel continues (in manual mode) into the applicabletank.

a. Start the pump on the fuel tanker/pump unit.b. At the refuel/defuel control panel 990vu:

(1) Put the MODE SELECT switch to the REFUEL position.NOTE : If the following switches are not in the correct configuration, the END light will

flash:

One or more of the inlet valve switches is in the OPEN or SHUT position.

On cockpit FUEL panel 245vu, the T TANK MODE switch is set to FWD.

On cockpit FUEL panel 245vu, the OUTER TK XFR switch is set to MAN.

(2) Make sure that the numbers on the fuel quantity and the ACTUAL displays increase.(3) When the refuel stops, make sure:

a) The END light comes on and does not flash.b) The numbers on the ACTUAL and the PRESELECTED displays are stable and are

the same -440 lbs. (-200 kg) +440 lbs. (200 kg).(4) Set the MODE SELECT switch to OFF.(5) If the power supply is from the battery, put the PWR SUPPLY switch to NORM.

a) Stop the pump on the fuel tanker/pump unit.b) Close-up.

B. Close Access1. Disconnect the coupling of the four fuel supply hoses from the aircraft refuel/defuel couplings.2. Install the refuel/defuel coupling caps.3. Refuel panel closure.

CAUTION: DO NOT APPLY TOOMUCH FORCE TO THE OPERATING RODWHEN YOUCLOSE THE PANEL. THIS PREVENTS DAMAGE TO THE MECHANISM.

a. Close the access panels.

Section 20.07Pressure Fueling with Automatic Control


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b. Close the fuel control panel.

END

Section 20.07Pressure Fueling with Automatic Control


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Section 20.08 - Pressure Fueling with Manual Control - LoadPreselector INOP

20.08.1 Procedures

CAUTION: DO NOT LET THE REFUEL PRESSURE GET TO MORE THAN 3.4 BAR (50 POUNDSPER SQUARE INCH (PSI)). THISWILL PREVENT DAMAGE TO THE AIRCRAFT FUELSYSTEM.

A. On the refuel/defuel control panel set the switches as follows (Refer to Section 20.03):1. Put the REFUEL/DEFUEL VALVE switch(es) for the fuel tank(s) to refuel to the OPEN position.

NOTE : If REFUEL VALVES secured in NORM position, maintenance to cut wire to manuallyopen/shut valves.

NOTE : To refuel the trim-tank, one of these conditions must apply:

The two inner-tank inlet valves are open.

The two inner tanks fuel quantities are above 30,865 pounds (lbs.) (14,000 kilogram(kg)).

One inner tank fuel quantity is above 30,865 lbs. (14,000 kg) and the other innertankinlet valve is open.

2. Put the REFUEL/DEFUEL VALVE switch(es) for the tank(s) you do not want to refuel, to theSHUT position.WARNING: EXTREME CAUTION MUST BE TAKEN WHEN ADDING FUEL TO THE

TRIM-TANK MANUALLY. FOLLOW THE FUEL DISTRIBUTION TABLECAREFULLY OR AIRCRAFT COULD TIP ON ITS TAIL. REFER TO SECTION20.01.

NOTE : If the trim-tank is to be fueled, it must be done in two steps:

When the trim tank fuel quantity reaches 2,200 lbs. below that shown on the FuelDistribution Table, shut the trim-tank inlet valve. Refer to Section 20.01.

When the two inner tanks are at the target value, open the trim-tank inlet valve. Referto Section 20.01.

B. Start the pump on the fuel tanker/pump unit.C. On the refuel/defuel control panel:

1. Put the MODE SELECT switch to the REFUEL position.2. If the refuel isolation valve does not open, do the next step.3. On the refuel isolation valve, push in and hold the OVERRIDE push button switch.4. Monitor the fuel quantity displays.5. Make sure that the numbers on the fuel quantity and ACTUAL displays increase.6. When each tank has the correct fuel quantity, put its REFUEL/DEFUEL VALVE switch to the

SHUT position.NOTE : Each tank quantity can increase 220 lbs. (100 kg) to 440 lbs. (200 kg) after the

REFUEL/DEFUEL VALVE switch is set to SHUT.

NOTE : If necessary, to make sure the fuel distribution is correct for flight, refer to Section20.01.

Section 20.08Pressure Fueling with Manual Control - LoadPreselector INOP


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7. When the fuel tank quantities are correct, put the MODE SELECT switch to the OFF position.8. If it was necessary to operate the OVERRIDE push button switch, do the next step.

a. On the refuel isolation valve, release the override push button switch.(1) Put the applicable REFUEL VALVES switch(es) to the NORM position.(2) If the power supply is from the battery, put the PWR SUPPLY switch to NORM.

NOTE : Maintenance to reinstall safety wire MPN MS20995C20 on all REFUEL/DEFUEL VALVEswitches into NORM positions.

D. Stop the pump on the fuel tanker/pump unit.

END

Section 20.08Pressure Fueling with Manual Control - LoadPreselector INOP


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Section 20.09 - Overwing Fueling20.09.1 Procedures - Overwing Fueling

NOTE : This procedure is not authorized for refueling the trim-tank. Contact American Airlines (AA)Maintenance in person.

NOTE : The overwing refuel caps are located on the inner tanks.

A. Connect the ground cables of the refuel nozzles to the wing ground connections.B. Remove the overwing refuel caps. Refer to Figure 20.09-1.C. Put the fuel nozzles in the overwing refuel points.D. Start the pump on the fuel tanker/pump units.

CAUTION: KEEPTHERATEOFFUELGROUNDTRANSFERTHESAMEAS (OR LESSTHAN)THE RATE OF FLOW INTO THE INNER TANK.

E. Start a ground fuel transfer from the inner tanks to the other fuel tank(s).F. Fill the inner tanks with the necessary amount of fuel.

NOTE : Be careful not to overfill the tanks. There is no automatic cut-out.

G. When the fuel quantities are correct, stop the pump on the fuel tanker/pump unit.H. Stop the ground fuel transfer.



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Figure 20.09-1: Overwing Refuel - Adaptor Cap

END



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Section 20.10 - Alternate Fueling20.10.1 General

A. Alternate fueling procedures can be used to fuel a tank with inoperative fuel quantity indicators.Degraded Electronic Centralized Aircraft Monitoring (ECAM) Indications (last 2 digits dashed "--") areconsidered operational and do not require alternate fueling procedures or verification by MagneticLevel Indicators (MLI).

B. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), avendor Supervisor, Lead or Supervisor/Lead, or Designated Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

C. If the transfer of fuel or other flight deck procedures become necessary, American Airlines (AA) flightcrew or Maintenance personnel must be contacted in person to perform these functions. For additionalassistance, such as malfunctioning fuel valve operation, opening and closing of gear doors, transferringfuel, etc., contact AAMaintenance personnel or, if not on duty, contact Maintenance Operations Center(MOC) in person.

D. Inoperative ECAM FUEL Page Indications for Outer Tank or Inner Tank require verification of fuelquantity by MLI.

20.10.2 Procedures - Inoperative Wing/Trim-Tank Quantity Indication

A. The following alternate fueling procedures outline allowable inoperative gauge procedures.NOTE : Degraded ECAM indicators (last 2 digits dashed "--") are considered operative and do not

require alternate fueling procedures or verification by MLI.


1. Method 1 - Flight deck display is operativ. Fuel panel display is inoperative.a. Fueling of that tank can be done using the flight deck ECAM display as the reference display.b. One or more indicators can be inoperative at the fuel panel provided they are available in

the flight deck. Either one member of the flight crew or AA Maintenance personnel remainsin the flight deck to monitor the fueling operation.NOTE : Communications between the fueler stationed at the fuel panel and the flight deck

must be established and maintained throughout the fueling operation.

2. Method 2A - Flight deck display is inoperative. Fuel panel display is operative.a. Fueling of that tank can be done using the operative fuel panel display as a reference.b. Fuel quantity in associated tank must be checked by Manual.c. Before fueling, determine existing fuel tank quantity with MLIs of the affected tank. Refer to

Figure 20.02-5. Subtract this quantity from the quantity required and convert to gallons. Fuelthe tank to desired level, using the fueling equipment meter. Use MLIs to verify tank quantity.Refer to Section 20.10.3.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons

(reference Section 15.01.7) to deliver the desired known quantity.

3. Method 2B - Flight deck and fuel panel displays for the wing are inoperative.CAUTION: DO NOT ATTEMPT TO FUEL THE AIRCRAFT USING THE AUTOMATIC

REFUEL METHOD. MULTIPLE PROBE FAILURE OR COMPUTER FAILUREHAS OCCURRED.

a. If the flight deck ECAM display and the fuel panel display are blank or display XXs, separaterefueling of the affected tank must be done using the alternate refuel method.



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b. Before fueling make sure the high level shutoffs are operational by use of the test switch atthe fuel panel.

c. Before fueling, determine existing fuel tank quantity with the MLIs of the affected tank. Referto Figure 20.02-5. Subtract this quantity from the tank quantity required and convert to gallons.Fuel the tank to desired level, using the fueling equipment meter. Use MLIs to verify tankquantity. Refer to Section 20.10.3.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons

(refer to Section 15.01.7) to deliver the desired known quantity.

d. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity Indicatorservice record. Make sure all required entries and signatures are legible and in place asearly as practicable, before departure.

4. Method 3 - Flight deck and fuel panel displays for the wing are inoperative.a. Completely defuel tank with the inoperative indicator by defueling or transferring fuel to other

tank(s). Refer to Section 20.11.WARNING: WHEN YOU OPERATE THE FUEL PUMPS DURING A MAINTENANCE

PROCEDURE, FLIGHT CREW OR A MAINTENANCE PERSON MUSTBE IN THE COCKPIT. THIS PERSON MUST STOP THE PUMPS WHENTHE LOW PRESSURE FAULT LIGHT(S) (ON PANEL 40VU) COME ON,TO PREVENT OPERATION OF THE PUMP(S) WITHOUT FUEL (DRYRUNNING). OPERATION OF THE PUMPSWITHOUT FUEL CAN CAUSEA FIRE.

CAUTION: DO NOT LET THE FUEL PUMPS OPERATE FOR MORE THAN 15MINUTESWITH THE FAULT LIGHT ON. THIS CAN CAUSE DAMAGE TOTHE FUEL PUMPS.

b. Fuel the tank with the inoperative indicator separately, quantity of fuel required, as gaugedby the fuel equipment meter reading. Alternately, transfer required fuel from tank(s) withoperative indicator.

c. Fill tank(s) with using the operative indicator to the quantity of fuel required.NOTE : Use of Method 3 requires final verification. Refer to Section 20.10.3.

5. Flight deck and fuel panel displays for the trim-tank are inoperative.a. The trim-tank indication can be inoperative provided it is determined to be EMPTY.b. Empty trim-tank can be verified by the automatic closure of the trim-tank isolation valve during

manual forward transfer, provided the tank mode Push Button Switch (P/B SW) is in theAUTO position. This is a flight deck function. Refer to Section 20.12.1.

20.10.3 Determining Fuel Quantity by MLIs

A. Anytime fuel quantity is determined by MLIs, the following procedure must be used:1. Determine the method, 2 or 3, (refer to Section 20.10.2) to be used to fuel the aircraft and check



determine the pounds in the affected tank.



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(2) Record the before fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (for example L,

LI, C, ACT1, Trim, etc.) in the space provided below "TANK".b) Record the before fueling aircraft attitude (pitch and roll).c) Circle the stick(s) utilized before fueling (all aircraft) and applicable inner/outer cell





Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the MLIs utilized after fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only).c) Record the units/inches read from the applicable MLIs in the after fueling spaces.d) Record the after fueling quantity from the applicable MLIs chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Make sure all MLIs are secured and initial where applicable; print your name, present


(6) The MLIs reading in inches and conversion to pounds must be verified by a cockpit crewmember by reviewing the completed fuel slip and Inoperative Fuel Quantity Indicatorservice record.


Refer to Section 20.11.(2) Record the before fueling information where applicable on the fuel slip and Inoperative


LI, C, ACT1, Trim, etc.) in the space provided below "TANK".b) Leave the before fueling aircraft attitude (pitch and roll) spaces blank and do not

circle any MLIs used before fueling & applicable inner/outer cell tanks.c) Record the before fueling quantity of zero pounds on the fuel slip and the Inoperative


a) The aircraft attitude after fueling.b) Tank MLIs needed to measure the fuel quantity and associated charts to determine

the after fueling pounds in the affected tank.



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(5) Record the after fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the MLIs utilized after fueling (all aircraft) & applicable inner/outer cell (Airbus

319/320 aircraft only).c) Record the units/inches read from the applicable MLIs in the after fueling spaces.d) Record the after fueling quantity from the applicable MLI chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Make sure all MLIs are secured and initial where applicable; print your name, present

title and company name followed by your complete signature (no initials).f) Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.

(6) The MLI reading in inches and conversion to pounds must be verified by a cockpit crewmember by reviewing the completed fuel slip and Inoperative Fuel Quantity Indicatorservice record.

END



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Section 20.11 - Fuel Transfer20.11.1 General

NOTE : The Fuel Control Monitoring System (FCMS) must be energized for fuel ground transfer.

NOTE : Only Flight/Maintenance personnel can do tasks in the flight deck.

20.11.2 Procedures - Inner Tank Ground Level Transfer

NOTE : When fuel quantity in the Inner Tank decreases to 7716 lbs., the two intertank transfer valveswill open, automatically draining the outer tanks into the inner tanks.

NOTE : If REFUEL VALVES secured in NORM position, maintenance to cut wire to manually open/shutvalves.

A. Refuel Panel (refer to Section 20.03.)1. MODE SELECT switch set to REFUEL.2. TRANSF valve switch set to OPEN.

NOTE : The TRANSF valve switch opens the left hand (LH) aft transfer valve (only if a relatedstandby (stby) or main pump is on) and opens the right hand (RH) transfer valve (onlyif a related stby or main pump is on). This function prevents a loss of fuel pressure tothe auxiliary power unit (APU).

3. Applicable REFUEL/DEFUEL valves are set to OPEN.B. Flight Deck Overhead Panel.

1. STBY (or main) fuel pumps set to ON (Maintenance personnel only.)2. Crossfeed valve pushbutton switch set to OPEN.3. When the required quantity is reached, release out the fuel pump switch(s) and crossfeed valve

switch.4. STBY (or main) fuel pumps set to OFF (Maintenance personnel only.)5. Crossfeed valve pushbutton switch set to CLOSED.

C. Refuel Panel1. MODE SELECT switch set to OFF.2. TRANSF VALVE switch set to CLOSED.3. Applicable REFUEL/DEFUEL valves set to SHUT.4. Applicable Refuel/Defuel valves set to NORM (switch guard down.)

NOTE : Maintenance to reinstall safety wire MPN MS20995C20 on the REFUEL/DEFUEL VALVEswitches into NORM positions.

END



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Section 20.12 - Defueling20.12.1 General

WARNING: MAKE SURE THE TRAVEL RANGES OF THE FLIGHT CONTROLS ARE CLEAR.MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/ORDAMAGE TO EQUIPMENT.

A. Refuel/Defuel Panel (Refer to Section 20.03.)NOTE : If trim-tank is to be fully defueled, Maintenance personnel or flight crew must set the

Trimmable Horizontal Stabilizer to 0 degrees.

1. Put two access platforms in position.2. Open the access panels.3. Remove the refuel/defuel coupling caps.4. Connect couplings.

NOTE : If one hose is to be connected, it must be connected to the coupling identified "UseThis Adapter to Defuel."

5. Open fuel panel access door.6. Make sure the REFUEL-DEFUEL-VALVES switches are in the NORM (guarded) position.7. Set the MODE SELECT switch to the DEFUEL position.

B. Flight DeckNOTE : Only Flight Crew/Maintenance personnel can do tasks in the flight deck.

1. Defuel the Trim-tank by manual forward transfer.a. Push in the T TANK MODE push button switch (P/B SW) on flight deck overhead fuel panel.

(1) Make sure the FWD light comes on.(2) Make sure the fuel page show the trim-tank isolation valve symbol is in-line (valve open)

and the forward-transfer triangular symbol (fuel-transfer in operation).2. Monitor the fuel contents, making sure the trim-tank figure decreases.

NOTE : If trim-tank quantity indication is inoperative on Electronic Centralized Aircraft Monitoring(ECAM), the trim-tank can be verified empty by automatic closure of the trim-tankisolation valve during manual forward transfer provided the tank mode P/B SW is inauto position. The automatic closure of the isolation valve can be viewed on the ECAMpanel page.

NOTE : During defueling, the fuel from the trim-tank goes in to the two inner tanks. Make surethat there is enough space in the inner tanks. If the inner tanks are full, use the suctiondefuel procedure to defuel the trim-tank.

3. When the fuel contents have decreased to the necessary level, release the T TANK MODE P/BSW.a. Make sure the FWD light goes off.b. Make sure the fuel pages shows the trim-tank isolation valve symbol is cross-line (valve

closed) and the forward-transfer triangular symbol is not in view (fuel-transfer is not inoperation).

4. Monitor the fuel content on the FUEL page. Make sure the trim-tank indications become stable.Read and make a record of the fuel quantities.



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20.12.2 Procedures - Defueling Wing Tanks (Lower Quantity)

NOTE : The Fuel Control Monitoring System (FCMS) prevents a defuel of the wing tanks until the trim-tankis empty.

A. Refuel/Defuel Panel (Refer to Section 20.03.)1. Refuel/Defuel valve switches in the NORM (guarded) position.2. Mode select switch DEFUEL position.

B. Flight Deck1. Push (in) the L STBY and the R STBY Push Button Switches (P/B SWs) to start the pumps. Make

sure that:a. The OFF lights go off.b. The FUEL page shows the related fuel pump symbol is IN-LINE (pumps in operation).

2. Monitor the fuel contents indications on the FUEL page. Make sure that the inner tank contentsand the total fuel contents figures decrease.NOTE : When the fuel quantity in one of the inner tanks decreases to 8,820 lbs. (4,000 kg), the

two intertank transfer valves open. Fuel from the outer tanks then flows in to the innertanks.

C. When the fuel contents have decreased to the necessary levels, release (out) the L STBY AND THER STBY P/B SWs. Make sure:

D. The related pump P/B SW OFF light comes on.E. The FUEL page show the related fuel pump symbol is cross-line (pumps not in operation).F. Monitor the fuel contents indications on the FUEL page. Make sure that the indications become stable.

Read and make a record of the fuel quantities.

20.12.3 Procedures - Defueling Wing Tanks (Empty)

CAUTION: DO NOT LET THE FUEL PUMPS OPERATE FOR MORE THAN 15 MINUTES WITHTHE FAULT LIGHT ON. THIS PREVENTS DAMAGE TO THE FUEL PUMPS.

A. Flight Deck1. Push (in) the L1, R1, L STBY and the R STBY Push Button Switches (P/B SWs) to start the

pumps. Make sure:a. The OFF lights go off.b. The FUEL page shows that the related fuel pump symbol is in-line (pumps in operation).

2. Monitor the fuel quantity in the collector cells.3. When the fuel level in the collector cell is approximately 1100 lbs. (500 kg), put the TRANSF

VALVE switch to CLOSED.NOTE : During a defuel, the fuel pump can empty the collector cell faster than the collector cell

can fill. Thus, the collector cell must fill again before the defuel can continue.

4. When the collector cell is full again, put the TRANSF VALVE switch to OPEN.5. Do these steps again until the inner tank indication is zero.6. Operate the pump until a pump FAULT light comes on.7. Release (out) the related pump P/B SW. Make sure:

a. The relate FAULT light goes off.b. The related pump P/B SW OFF light comes on.c. The FUEL page shows the related fuel pump symbol is cross-line (pump not in operation).



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d. Do this for each pump.8. On the ECAM make sure that the fuel page shows:

a. The trim-tank isolation valve symbol is cross-line (valve closed).b. The forward fuel transfer symbol is not in view (fuel-transfer not in operation).c. The fuel pump symbols are cross-line (pumps not in operation).

20.12.4 Procedures - Suction Defueling

A. Refuel/Defuel Panel (Refer to Section 20.03.)NOTE : If REFUEL VALVES secured in NORM position, maintenance to cut wire to manually

open/shut valves.

1. MODE SELECT switch is set to DEFUEL.2. The necessary fuel-tank refuel/defuel valves switches are set to OPEN.3. The fuel is then removed from the set fuel tanks by suction from the tanker.

NOTE : If the trim-tank contains fuel, then fuel-system interlocks prevent a suction defuel ofthe inner tanks.

4. When finished defueling, set refuel/defuel valves switches to SHUT.

20.12.5 Procedures - Close Up

A. Refuel/Defuel Panel (Refer to Section 20.03.)1. Make sure the refuel/defuel valves switches are set to NORM (guarded) position.2. Set the MODE SELECT switch to the OFF position.3. Close the access panel.4. Disconnect the defuel couplings.5. Install the caps.6. Close the access panels.

NOTE : Maintenance to reinstall safety wire MPN MS20995C20 on the REFUEL/DEFUEL VALVEswitches into NORM positions.

END



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Section 20.13 - Magnetic Level Indicators (MIL)20.13.1 General

CAUTION: IT IS IMPORTANT TO MAKE SURE OF CORRECT CALCULATIONS.

CAUTION: VERIFY ANY MINIMUM EQUIPMENT LIST (MEL) PLACARD THAT IS POSTEDON/NEAR THE INOPERATIVE INDICATOR. THE SUPERVISOR FUELING OR LEADFUELER MUST BE PRESENT TO OVERSEE THE ENTIRE ALTERNATE FUELINGPROCEDURE.


20.13.2 Procedures - Access

A. Open the fuel control panel access panel. Refer to Section 20.03.

20.13.3 Procedures - Specific Gravity/Density

A. Get a fuel sample from the aircraft and find its density.B. Alternate procedure

1. The specific gravity (SG) is also available on the Fuel Control Monitoring System (FCMS) InputParameters, Aircraft Maintenance Manual (AMM). Use the SG to find the density (multiply SG x8.34 to find density in pounds (lbs.)/gallon (gal)).

2. Use density of 6.7 (lbs./gal (per fuel standard).

20.13.4 Procedures - MLI System and Stick Number Attitude Charts

A. Put an adjustable access platform below the applicable Magnetic Level Indicator (MLI) Refer toFigure 20.13-1.CAUTION: DO NOT LET THE MLIS FALL FREELY. THE MLIS ARE FRAGILE.

CAUTION: RETRACT THE MLIS AS SOON AS POSSIBLE. DAMAGE TO AN EXTENDEDMLICAN BE EASILY CAUSED.

NOTE : To do the MLI procedure on the inner tanks, the main fuel pumps must not be in operation.If themain pumps have been in operation, wait tenminutes before starting theMLI procedure.This allows the fuel to settle down and make sure a level reading is taken during the MLIoperation. Afterwards, use the time curve shown on the Collector-Cell Correction FactorChart for correct reading. Refer to Table 20.13-1.

NOTE : The MLIs in the inner tanks are accurate to ± 5% of their indication. The MLIs in the outertank are accurate to ± 7.5% of their indication. MLI values are not as accurate as the valuesgiven by the Fuel Control and Monitoring Computer (FCMC). Do not use them forcomparison.

NOTE : Start the procedure with each of the outboard MLI in the outer and inner tank. If they haveno reading, move to the next MLI inboard. Continue moving inboard until an MLI shows areading. When a MLI shows a reading, use that MLI for the procedure.

B. Use a screwdriver to push (in) the applicable MLI and turn it through 90 degrees (°).C. Hold and carefully lower the MLI fully. Carefully lift the MLI until the magnets engage.D. Read the units mark nearest to the bottom skin of the wing and write down the number.


Section 20.13Magnetic Level Indicators (MIL)


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E. Retract the MLI and use a screwdriver to turn it through 90° to lock it.F. Do this procedure for each applicable MLI.

NOTE : Only use one MLI reading from each applicable tank.

G. Calculation Procedure1. Read and write down the aircraft attitude. Obtain the pitch and roll from Air Data/Inertial Reference

Unit (ADIRU).NOTE : For applicable Method and Recording requirements, refer to Section 15.01.

NOTE : Maintenance personnel can obtain the pitch and roll from the ADIRU.

H. Use the applicable MLI Stick # Attitude charts. Refer to Section 20.13.5 based on pitch/roll data andMLI stick height to find the volume of fuel in the tank. Refer to Figure 20.13-2 and Section 20.13.5.

I. For an inner tank, there could be additional fuel in the collector-cells. To find the additional fuel quantityin one inner tank, refer to Table 20.13-1. This is to be added to the corrected quantity of the innertank, to give at total quantity of the inner tank.

J. Add the additional GALLONS to the indicated tank volume to get actual volume.NOTE : This procedure is not applicable (N/A) for any inner tank quantity above 3,000 gal as the

collectors will be full.

NOTE : The fuel quantity in the collector cell will decrease with time. Use the applicable columnthat specifies the time since the main fuel pumps have been switched OFF. The data takenfrom the table gives a more accurate fuel quantity. To verify time since pumps OFF contactMaintenance Operations Control (MOC) in person for most current block time. Refer toTable 20.13-1.

Table 20.13-1: Correction for Collection Tank Quantity (One Inner Tank)Addition Fuel Quantity (gal) 1Indicated Tank

Time Since Pumps Shut-off (min)

90+60+40+30+20+10+Volume (US gal)

3,396

3,170

122,867

232,641

12382,339

26522,113

1449671,811

3864901,585

2460841101,282

50811101401,056

1277109137172792

42106136172198528

1294159185224254226

271191802142512770

K. Use the applicable MLI Stick # Attitude charts in Section 20.13.5 based on pitch/roll data and MLIstick height to find the volume of fuel in the tank. Refer to Figure 20.13-2 and Section 20.13.5.NOTE : The trim-tank can also contain fuel quantity of between 0 and 10,582 lbs. (4,800 kg).




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Figure 20.13-1: MLI Locations



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Figure 20.13-2: Air Data/Inertial Reference System (ADIRS) Roll Indications for Left and Right Wing

20.13.5 Magnetic Level Indicators MLI Charts

A. Refer to A330-300 Magnetic Level Indicators MLI Charts as follows:1. Access the Stick Charts at http://me.aa.com/manuals/fw/FuelingStickCharts/#z

END



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Table of contents

21.01 FUELING MANUAL - B737GENERAL..........................................................................................................................1UNDERWING PRESSURE FUELING...............................................................................4UNDERWING PRESSURE FUELING WITHOUT ELECTRICAL POWER.......................6TANK-TO-TANK GROUND TRANSFER OF FUEL...........................................................7INACCURATE OR INOPERATIVE FUELING QUANTITY INDICATORS........................13OPERATION OF FUEL QUANTITY MEASURING STICKS............................................15DETERMINING FUEL QUANTITY BY MEASURING STICK..........................................16DEFUELING....................................................................................................................20B737 FUEL DISTRIBUTION GUIDE................................................................................22

TOCFueling Manual - B737


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Section 21.01 - Fueling Manual - B73721.01.1 General

A. The fuel system has two main tanks and one center tank. There is also a vent surge tank located ineach wing, outboard of the wing tank. Refer to Figure 21.01-1.1. For all B737 aircraft:

a. Center tank has an approximate volume of 4,299 US gal.b. Main (wing) tanks each have a approximate volume of 1,288 US gal.


NOTE : The use of Jet B is prohibited on all B737 aircraft.

NOTE : Ensure the wing PRESSURE RELIEF valves are in the closed position and FUELTANK VENTS are not blocked before starting the refuel operation.

B. Pressure Fueling1. Pressure fueling is accomplished through a single point fueling station, with or without electrical

power. The fueling station consists of a single pressure fueling receptacle and control panel. Thecontrol panel is used for controlling and monitoring the pressure fueling operation and containsfuel quantity indicators and switches. Refer to Figure 21.01-2.

2. Fuel flow through the pressure fueling receptacle (manifold) is directed to any or all fuel tanksdesired through electrically or manually operated fuel tank fill valves, which are located on thefront spar at the right wing fueling station.

3. Access to the fueling station and control panel is through a hinged access door located on thelower surface of the right midwing leading edge, approximately 9 ½ feet from ramp level. Referto Figure 21.01-2.

4. External or APU electrical power should be used for pressure fueling operations. If external orAPU power sources are not available, the airplane battery may be used as a power source.NOTE : Fuel truck/tankers are not to be disconnected from a/c until all fueling discrepancies

have been cleared.

WARNING: (1) DONOTOPERATETHEHFCOMMUNICATIONSYSTEMWHILEFUELINGTHE AIRPLANE. A FIRE OR AN EXPLOSION CAN OCCUR.

(2) GROUNDEQUIPMENTMUSTNOTBEPOSITIONEDUNDERWINGTIPSDURING FUELING OPERATION.

(3) GROUND CLEARANCE FOR ADVANCED TECHNOLOGY WINGLETSON B737-MAX8 IS APPROXIMATELY 10 FEET 2 INCHES (3.1 M).POTENTIAL FOR AIRCRAFT DAMAGE IF GROUND VEHICLES AREDRIVEN UNDER AIRCRAFT WING.

(4) FUELING VEHICLE MUST BE PROPERLY BONDED TO AIRCRAFTBEFORE ANY FUELING/DEFUELING OPERATION.

(5) WHEN THERE IS AN INACCURATE/INOPERATIVE OR A SUSPICIONOF A GAUGE NOT INDICATING PROPERLY, STOP FUELING ANDNOTIFY AIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON.

(6) NOTE: IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARDASBEING INOPERATIVE, AIRCRAFTMAINTENANCEDOESNOTNEEDTOBENOTIFIED, UNLESSSPECIFICPROCEDURESDURINGFUELINGOPERATIONS REQUIRE THE ATTENTION OF AIRCRAFTMAINTENANCE.

Section 21.01Fueling Manual - B737


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(7) IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURINGFUELING OPERATION, NOTIFY AIRCRAFT MAINTENANCEIMMEDIATELY IN PERSON. DO NOT START OR RESUME FUELINGOPERATIONS UNTIL CORRECTIVE ACTION HAS BEEN TAKEN.

(8) DO NOT START OR SHUT DOWN APU SHOULD FUEL SPILL OCCUR.(9) DEFUELINGORTRANSFERRINGFUELWITHPASSENGERSONBOARD

THE AIRCRAFT IS PROHIBITED, EXCEPT UNDER CERTAINCONDITIONS. (REFER TO SECTION 21.01.4 AND SECTION 21.01.8.).

Figure 21.01-1: Fuel Tanks and Vent System



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Figure 21.01-2: Pressure Refueling System

C. Gravity fueling - There is no overwing gravity - fill provisions.D. Fuel Quantity Indicating System (FQIS) - the FQIS uses a variable capacitance principle and an

advanced microprocessor to measure fuel quantity.1. The primary indicating devices used in determining fuel quantity are the cockpit and underwing

fuel quantity indicators. The underwing fuel quantity indicators, located on the control panel areused during normal fueling operations. Refer to Figure 21.01-2.

2. An alternate means of determining fuel quantity may be obtained by the use of the mechanicalmagnetic measuring sticks located on the bottom of the main wing tanks and center tank. Referto Figure 21.01-9.

E. Fuel Jettison - There is no fuel jettison system provided, because the maximum take-off weight is notsubstantially higher than the maximum landing weight.

F. Automatic water scavenge system.1. An automatic water scavenge system decreases water accumulation in the center and main

tanks.G. Automatic center tank fuel scavenge system

1. When the fuel in the center tank is sufficiently low, the main tanks automatically supply fuel tothe engines. The remaining fuel in the center tank automatically transfers to the No. 1 tank.



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Figure 21.01-3: Fuel Quantity Indicating System

21.01.2 Underwing Pressure Fueling

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Correctly position the fuel vehicle.C. Connect a bonding cable from the fueling source to an approved electrical ground or bonding connection

on the airplane. Refer to Figure 21.01-4.CAUTION: ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THE AIRPLANE.

INCORRECTLY ATTACHED BONDING CABLES CAN CAUSE SCRATCHES.THESE SCRATCHES CAN CAUSE CORROSION AND CRACKS ON STRESSEDPARTS. BONDING CABLES ATTACHED TO COMPOSITE DOORS OR FAIRINGSDO NOT GIVE AN ELECTRICAL BOND.



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D. Open fueling control station access door. If the external or APU power is applied, the electrical powerfor the fueling will be automatically supplied when the fueling control station access door is in the fullyextended position. If external or APU power is not applied, the aircraft may be fueled with batterypower. Inform the Flight Crew or Aircraft Maintenance to place the battery switch in the cockpit to theON position. Upon fueling completion and closure of the fueling control access door, inform the FlightCrew or Aircraft Maintenance to place the battery switch to the OFF position. Refer to Figure 21.01-5.NOTE : If the fueling station door is open and the fueling station does not have power, move the

fueling indication test switch to the FUEL DOOR SWITCH BYPASS position. This actionsupplies hot battery bus power to the fueling station. Refer to Figure 21.01-8.

Figure 21.01-4: Bonding Point Location

E. Connect fueling nozzle to aircraft pressure fueling receptacle. Refer to Figure 21.01-5.CAUTION: PRIOR TO APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLES TO THE

LOCKED POSITION AND OPEN POPPET ACTUATING LEVER. ATTEMPT TOREMOVENOZZLE. IF NOZZLECANBEREMOVED, IT IS DEFECTIVEANDMUSTBE REMOVED FROM SERVICE.

F. Select and hold the FUELING INDICATION TEST SWITCH on the refuel control panel in the TESTGAUGES position. Refer to Figure 21.01-8.1. Make sure all of the fueling quantity indicators operate correctly.

NOTE : The test blanks the fueling quantity indicators display for two seconds, then all LEDsegments go on for two seconds. This sequence continues as long as you hold theTEST SWITCH. If you hold the TEST SWITCH for more than 20 seconds, the testmode will time out and the indicator will go back to its usual operating mode. If aninternal fault is found during the test, the indicator will show Ind FAIL.

2. Release the FUELING INDICATION TEST SWITCH.G. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS." spaces

on the fuel slip. Refer to Section 15.01.H. Determine fuel load per tank from fuel slip. "GATE RELEASE QUANTITY REQUIRED - LBS." Refer

to Section 15.01.



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1. When power is first applied to the fueling station, it will be in the MANUAL mode. Refer toFigure 21.01-8. The MANUAL mode will be indicated with a "1" for tank #1, a "2" for tank #2 anda "C" for the center tank, on the lower scale of each level indicator. If the manual mode is desiredduring fueling, you do not have to rotate the round knob below the lower scale of each indicator.

2. The AUTOMATIC mode is selected by rotating the knob of the indicators to the desired tankvolume to match "GATE RELEASE QUANTITY REQUIRED - LBS." calculations. Refer toFigure 21.01-8. Rotating the knob clockwise will increase the number on the lower scale andcounter-clockwise will decrease the number.

I. Press to test each FUELING VALVE POSITION LIGHT. Verify each light illuminates when pressed.Refer to Figure 21.01-8.

J. Place applicable FUELING VALVE POSITION switches to the FUEL position. The blue "valve open"indicator lights will illuminate when the fueling shutoff valve solenoids have power and there is fuelpressure at the fueling valve. Refer to Figure 21.01-8.

K. Start fueling operation by activating deadman control.1. During the refueling, observe that the valve position light illuminates/extinguishes normally when

opening/closing the associated fueling shutoff valve.L. Monitor applicable fuel quantity indicators. Refer to Figure 21.01-8.M. When fueling valves close automatically, place applicable FUELING VALVE control switches to OFF

position. Refer to Figure 21.01-8.N. When operation is complete, stop fueling source by releasing deadman control.O. Remove fueling nozzle. Refer to Figure 21.01-5.

1. After the refueling nozzle is disconnected, visually check for fuel leakage.P. Check that all FUELING VALVE control switches are in the OFF position, then close the fueling control

station access door. Refer to Figure 21.01-5.Q. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.R. Disconnect aircraft and fueling vehicle bonding cable.

21.01.3 Underwing Pressure Fueling Without Electrical Power

CAUTION: 1. NO AUTOMATIC SHUTDOWN OR OVERFILL PROTECTION EXISTS WITHOUTELECTRICAL POWER.

2. DO NOT USE FUELING VALVES MANUALLY TO REDUCE OR STOP FUELING.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Correctly position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control station access door. Refer to Figure 21.01-5.E. Connect fueling nozzle to aircraft pressure fueling receptacle. Refer to Figure 21.01-5.

CAUTION: PRIOR TO APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLES TO THELOCKED POSITION AND OPEN POPPET ACTUATING LEVER. ATTEMPT TOREMOVENOZZLE. IF NOZZLECANBEREMOVED, IT IS DEFECTIVEANDMUSTBE REMOVED FROM SERVICE.

F. Use magnetic measuring sticks to determine fuel quantity in each tank before fueling. Refer to Section15.01 and Figure 21.01-9.

G. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS." slotson the fuel slip. Refer to Section 15.01.



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H. Determine fuel load per tank from fuel slip "GATE RELEASE QUANTITY REQUIRED - LBS." Referto Section 15.01.

I. Manually open applicable fueling valve(s). Refer to Figure 21.01-5.J. Start fueling operation by activating deadman control.K. Monitor magnetic measuring sticks carefully during the fueling process. Refer to Figure 21.01-9.

Figure 21.01-5: Fueling Shutoff Valves

L. Stop the fueling source when desired amount of fuel is obtained in each respective fuel tank byreleasing deadman control.

M. Verify fuel tank quantity by use of magnetic measuring sticks.N. Manually close applicable fueling valve(s). Refer to Figure 21.01-5.O. Remove fueling nozzle.P. Close fueling station control access door. Refer to Figure 21.01-5.Q. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.R. Disconnect aircraft and fueling vehicle bonding cable.


WARNING: DEPLANE ALL PASSENGERS AND NON-ESSENTIAL CREW WHEN DEFUELING AMAIN TANKOR TRANSFERRING FUEL FROMAMAIN TANK THAT HAS AQUANTITYBELOW 2,000 POUNDS (900 KILOGRAMS) UNTIL THE PROCESS HAS BEENCOMPLETED AND THE RESPECTIVE FUEL BOOST PUMPS ARE TURNED OFF.

WARNING: WHEN TRANSFERRING OR DEFUELING CENTER OR MAIN WING TANKS, THEFUEL PUMP LOW PRESSURE INDICATION LIGHTS MUST BE MONITORED ANDTHE FUEL PUMPSPOSITIONEDTOOFFAT THE FIRST INDICATIONOF FUEL PUMP



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LOW PRESSURE. TRANSFERRING FUEL OR DEFUELING WITH PASSENGERS ONBOARD IS PROHIBITED EXCEPT UNDER CERTAIN CONDITIONS:

ALTERNATIVE PROCEDURE (CONDITIONAL):

FUEL MAY BE TRANSFERRED FROM THE CENTER TANK OR THE AIRCRAFTCENTER TANK MAY BE DEFUELED WITH PASSENGERS ON BOARD, PROVIDEDTHE AUTOMATIC SHUTOFF SYSTEM FOR THE CENTER TANK BOOST PUMP ISOPERATING.

NOTE : American Airlines (AA) Flight Crew or maintenance personnel must be present and operateapplicable cockpit switches or levers when fuel is required to be transferred or to verify the fueltank is empty. In the event that a fuel system or components there of (excluding inoperativegauge) is malfunctioning, inoperable or when assistance is required to safely perform fuelingoperations, contact AA Maintenance personnel or Station Operations through coordination withMaintenance Operations Control (MOC) when AA maintenance personnel are not on duty forassistance. Examples of inoperative or malfunctioning fuel system components or assistancesituations includes:1. Inoperative refuel/defuel valves2. Inoperative transfer valves3. Transferring fuel, opening4. Closing the aircraft landing gear doors, etc.

A. To transfer fuel between tanks, you use the defuel system, fueling system and the engine fuel feedsystem. This is a summary of the fuel transfer procedure. Refer to Figure 21.01-6, Figure 21.01-7 andFigure 21.01-8:1. Move the defuel valve to the open position. Refer to Figure 21.01-6.2. Turn on the boost pumps in the tank you want to defuel. Refer to Figure 21.01-8.3. Open the crossfeed valve. Refer to Figure 21.01-7.4. Move the refuel valve switch to the open position in the tank you want to put fuel into. Refer to

Figure 21.01-8.5. After fuel transfer, turn the boost pumps off. Refer to Figure 21.01-7.6. Close the crossfeed valve. Refer to Figure 21.01-7.7. Move the defuel valve to the closed position. Refer to Figure 21.01-6.

B. To transfer fuel from the right main wing tank to the left main wing tank (refer to Figure 21.01-6,Figure 21.01-7 and Figure 21.01-8):1. Move the DEFUEL VALVE handle to the OPEN position. Refer to Figure 21.01-6.2. Place right main tank boost pump switch(es) in the (cockpit) to the ON position. Refer to

Figure 21.01-7.3. Place CROSSFEED VALVE (cockpit) to the OPEN position. Refer to Figure 21.01-7.4. Place left main tank FUELING VALVE switch to the FUEL Position. Refer to Figure 21.01-8.5. Monitor applicable fuel quantity indicators and place right main tank boost pump switch(es) to

OFF when desired fuel quantity is obtained. Refer to Figure 21.01-7.6. Place the DEFUEL VALVE handle to the CLOSED position. Place left main tank FUELINGVALVE

switch to the OFF position. Refer to Figure 21.01-6.C. To transfer fuel from the left main wing tank to the right main wing tank. Refer to Figure 21.01-6,

Figure 21.01-7 and Figure 21.01-8):1. Move the DEFUEL VALVE handle to the OPEN position. Refer to Figure 21.01-6.



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2. Place left main tank boost pump switch(es) in the (cockpit) to the ON position. Refer toFigure 21.01-7.

3. Place CROSSFEED VALVE (cockpit) to the OPEN position. Refer to Figure 21.01-7.4. Place right main tank FUELING VALVE switch to the FUEL position. Refer to Figure 21.01-8.5. Monitor applicable fuel quantity indicators and place left main tank boost pump switch(es) to OFF

when desired fuel quantity is obtained. Refer to Figure 21.01-7.6. Place the DEFUEL VALVE handle to the CLOSED position. Place right main tank FUELING

VALVE switch to the OFF position. Refer to Figure 21.01-6.D. To transfer fuel from the right and/or left main wing tank(s) to the center tank (refer to Figure 21.01-6,

Figure 21.01-7 and Figure 21.01-8):1. Move the DEFUEL VALVE handle to the OPEN position. Refer to Figure 21.01-6.2. Place right and/or left main tank(s) boost pump switch(es) in (cockpit) to the ON position. Refer

to Figure 21.01-7.3. Place center tank FUELING VALVE switch to the FUEL position. Refer to Figure 21.01-8.4. Monitor applicable fuel quantity indicators and place right and/or left main tank boost pump

switch(es) to OFF when desired fuel quantity is obtained. Refer to Figure 21.01-7.5. Move the DEFUEL VALVE handle to the CLOSED position. Place center tank FUELING VALVE

switch to the OFF position. Refer to Figure 21.01-6.E. To transfer fuel from the center tank to the right and/or left main wing tank(s) (refer to Figure 21.01-6,

Figure 21.01-7 and Figure 21.01-8):WARNING: DEPLANEALL PASSENGERSANDNON-ESSENTIALCREWWHENDEFUELING

A MAIN TANK OR TRANSFERRING FUEL FROM A MAIN TANK THAT HAS AQUANTITY BELOW 2,000 POUNDS (900 KILOGRAMS) UNTIL THE PROCESSHAS BEEN COMPLETED AND THE RESPECTIVE FUEL BOOST PUMPS ARETURNED OFF.

WARNING: WHEN TRANSFERRING OR DEFUELING CENTER ORMAINWING TANKS, THEFUELPUMPLOWPRESSURE INDICATION LIGHTSMUSTBEMONITOREDANDTHE FUEL PUMPS POSITIONED TO OFF AT THE FIRST INDICATION OF FUELPUMP LOW PRESSURE. TRANSFERRING FUEL OR DEFUELING WITHPASSENGERS ON BOARD IS PROHIBITED EXCEPT UNDER CERTAINCONDITIONS:


FUEL MAY BE TRANSFERRED FROM THE CENTER TANK OR THE AIRCRAFTCENTERTANKMAYBEDEFUELEDWITHPASSENGERSONBOARD, PROVIDEDTHE AUTOMATIC SHUTOFF SYSTEM FOR THE CENTER TANK BOOST PUMPIS OPERATING.

1. Move the DEFUEL VALVE handle to the OPEN position. Refer to Figure 21.01-6.2. Place center tank boost pump switch(es) in (cockpit) to the ON position. Refer to Figure 21.01-7.3. Place right and/or left main tank(s) FUELING VALVE switch(es) to the FUEL position. Refer to

Figure 21.01-8.4. Monitor applicable fuel quantity indicators and place center tank boost pump switch(es) to OFF

when desired fuel quantity is obtained. Refer to Figure 21.01-7.5. Move the DEFUEL VALVE handle to the CLOSED position. Place FUELING VALVE switch(es)

to the OFF position. Refer to Figure 21.01-6.



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F. On completion of fuel transfer, check that all tank boost pumps are OFF in the cockpit. Refer toFigure 21.01-7.

G. Ensure that all FUELING VALVE switches are OFF and the DEFUELING VALVE handle is in theCLOSED position. Close fueling control station access door. Refer to Figure 21.01-6 and Figure 21.01-8.

Figure 21.01-6: Defuel Valve Handle



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Figure 21.01-7: Fuel System Panel (P5-2) Cockpit



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Figure 21.01-8: Underwing Fueling Panel

21.01.5 Inaccurate or Inoperative Fueling Quantity Indicators


underwing panel fuel quantity indicator, provided respective cockpit display is verified operational.Verification of fuel quantity, by measuring stick, is not required with Method 1. Use of Method 1should be noted on the fuel slip in the remarks field, with a copy of the fuel slip provided to theflight crew as early as practicable after fueling.

B. Method 2 - For use on main tanks (wings) and center tank when the flight deck fuel quantity displayis inoperative, one or more of the underwing panel fuel quantity displays are inoperative and fuel onboard can be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.5.1. Before fueling, determine existing fuel tank quantity with the measuring stick(s) of the affected

tank. Refer to Figure 21.01-9. Subtract this quantity from the tank quantity required and convertto gallons. Fuel the tank to desired level, using the fueling equipment meter. Use measuringstick(s) to verify tank quantity. Refer to Section 21.01.7.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons, refer

to Section 15.01.7, to deliver the desired known quantity.

2. Determine the aircraft attitude, (pitch and roll) using the inclinometers located in the left wheelwell. Assistance from Aircraft Maintenance personnel can be requested in making thisdetermination. Refer to B737 AMM for procedures.NOTE : The pitch inclinometer is graduated in letters A thru U. The roll inclinometer is graduated

in numbers 0 thru 20. The inclinometers are installed in the left wheel well for the mainlanding gear. Verification Charts, included in this section, are based on a density of6.76 lb/gal.

3. Ensure that the airplane attitude is within the usable pitch and roll limits of the stick conversiontables, B737-NG Pitch: inclinometer reading E to M (-3.00 to +1.00 degrees) Roll: inclinometerreading 6 to 14 (-2.00 to +2.00 degrees). B737-MAX8 Pitch: inclinometer reading G to O (-2.00to +2.00 degrees) Roll: inclinometer reading 6 to 14 (-2.00 to + 2.00 degrees).a. If the approximate fuel quantity in the fuel tank is known, refer to the tables below to find

which fuel stick to use (Table 21.01-1 or Table 21.01-2).NOTE : Each fuel stick has a range of a minimum and a maximum fuel quantity that you

can measure.

Table 21.01-1: Fuel Measuring Stick Range (B737-NG)

Fuel load at the nominal airplane attitude of: Pitch = I (-1.0 degree); Wing Roll = 10 (0degrees) roll

MAXIMUMMEASURABLEFUEL LOAD(POUNDS)

MAXIMUMSTICK UNIT

MINIMUMMEASURABLEFUEL LOAD(POUNDS)

MINIMUMSTICK UNIT

TANKSTICK

16,76021.61,7782.2CENTER1

29,84821.613,0722.0CENTER2



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Fuel load at the nominal airplane attitude of: Pitch = I (-1.0 degree); Wing Roll = 10 (0degrees) roll

4,39813.01,3742.0MAIN3

6,02210.83,7042.0MAIN4

7,1568.05,8941.8MAIN5

7,7837.06,9051.8MAIN6

8,3967.07,6971.8MAIN7

8,7926.08,3561.8MAIN8

Table 21.01-2: Fuel Measuring Stick Range (B737-MAX8)

Fuel load at the nominal airplane attitude of: Pitch = K (0.0 degrees); Wing Roll = 10(0 degrees) roll

MAXIMUMMEASURABLEFUEL LOAD(POUNDS)

MAXIMUMSTICK UNIT

MINIMUMMEASURABLEFUEL LOAD(POUNDS)

MINIMUMSTICK UNIT

TANKSTICK

17,54122.41,7352.0CENTER1

29,05821.612,3412.0CENTER2

4,59413.61,2061.6MAIN3

6,06410.83,4171.6MAIN4

7,1028.65,7151.6MAIN5

7,7457.66,6801.6MAIN6

8,3297.67,5241.6MAIN7

8,6506.67,9931.6MAIN8

b. If the approximate fuel quantity in the fuel tank is not known, start at the most outboard fuelstick for the applicable fuel tank and pull down the fuel sticks until you find the correct fuelstick (within its range).

4. Carefully, lower the fuel stick to its fully extended length. Use a fingertip (or the flat palm of yourhand) to slowly lift the fuel stick until the magnet catches the float.a. If the fuel level is not in the correct range for the fuel stick, go to the next inboard fuel stick

until you find one with the fuel level that is in range.5. Read the fuel level at the lower edge of the retainer and record on the Inoperative Fuel Quantity

Indicator Service Record.6. Stow the stick as soon as you are done recording the reading. An extended stick is easily damaged.7. Go to the correct fuel stick conversion table, for the applicable fuel stick number. Refer to Section

21.01.9.a. Find the correct column for the wing roll attitude and for the side of the airplane where you

are making the measurement.b. Find the fuel stick unit in the conversion table that agrees with actual (measured) fuel stick

value.



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c. Find the fuel stick unit in the conversion table that agrees with actual (measured) fuel stickvalue. Read across from the fuel stick unit in the conversion table to find the airplane rollattitude for the applicable side of the airplane; then read down from the correct wing rollattitude to find the fuel quantity in pounds.

8. Use the reported density of the loaded fuel to correct the fuel quantity in the conversion table fordensity variation Refer to Section 10.01.

9. Complete the fuel slip and the Inoperative Fuel Quantity Indicator Service Record ensuring allrequired entries and signatures are legible and in place as early as practicable, and provide copiesto the flight crew before departure.

C. Method 3 - For use on Center Tank and on main tanks (wings) when the flight deck fuel quantitydisplay is inoperative, one or two of the underwing panel fuel quantity displays are inoperative andfuel on board cannot be determined using fuel measuring sticks both before and after the refuelingoperation. Refer to Section 15.01.5.1. Completely defuel tank with the inoperative indicator by transferring fuel to other tank(s) Refer

to Section 21.01.4.WARNING: DEPLANE ALL PASSENGERS AND NON-ESSENTIAL CREW WHEN

DEFUELING A MAIN TANK OR TRANSFERRING FUEL FROM A MAIN TANKTHAT HAS A QUANTITY BELOW 2,000 POUNDS (900 KILOGRAMS) UNTILTHE PROCESS HAS BEEN COMPLETED AND THE RESPECTIVE FUELBOOST PUMPS ARE TURNED OFF.

WARNING: WHEN TRANSFERRING OR DEFUELING CENTER OR MAIN WING TANKS,THE FUEL PUMP LOW PRESSURE INDICATION LIGHTS MUST BEMONITORED AND THE FUEL PUMPS POSITIONED TO OFF AT THE FIRSTINDICATION OF FUEL PUMP LOW PRESSURE. TRANSFERRING FUEL ORDEFUELING WITH PASSENGERS ON BOARD IS PROHIBITED EXCEPTUNDER CERTAIN CONDITIONS:


FUEL MAY BE TRANSFERRED FROM THE CENTER TANK OR THEAIRCRAFT CENTER TANK MAY BE DEFUELED WITH PASSENGERS ONBOARD,PROVIDEDTHEAUTOMATICSHUTOFFSYSTEMFORTHECENTERTANK BOOST PUMP IS OPERATING.

2. Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged by the fuelequipment meter reading. Alternately, transfer required fuel from tank(s) with operative indicator.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to gallons, (refer

to Section 15.01), to deliver the desired known quantity.

3. Fill tank(s) with operative indicator to quantity of fuel required.NOTE : Use of Method 3 requires final verification by measuring stick. Refer to Section 21.01.7.

4. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity Indicatorservice record ensuring all required entries and signatures are legible and in place as early aspracticable, before departure. Refer to Section 15.01.

21.01.6 Operation of Fuel Quantity Measuring Sticks

A. In general, the magnetic measuring sticks are less accurate than the fuel quantity indicating system.The sticks should only be used as an alternate means of measuring fuel quantity, or to verify actualpresence of fuel in the tank.



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B. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), aVendor Supervisor, Lead or Supervisor/Lead, Designated Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

C. Each main wing tank contains 6 fuel measuring sticks located on the lower wing surface, numbered3 through 8 inboard to outboard. The center tank contains a total of 4 fuel measuring sticks, 2 perwing, numbered 1 and 2 inboard to outboard. Refer to Figure 21.01-9.

D. The measuring sticks are the magnetic dripless-type, consisting of a mounting, a tube housing, aninner tube (indicator stick) graduated in inches for determining fuel tank quantity and a circular float.The float is installed on the tube housing and is free to move up and down with the fuel level in thetank. Refer to Figure 21.01-9. When the fuel level stick tip is magnetically coupled to the circular float,the stick is positioned relative to the fuel level in the tank.

E. Fuel quantities quoted in the fuel quantity charts are based on fuel with a density of 6.7 pounds perU.S. gallon. Use the verification charts immediately at the end of this section to convert from inchesto pounds.NOTE : When actual fuel density deviates greatly from the nominal chart value of 6.70 pounds per

gallon, it may be desirable to convert the chart derived pound value to "actual pound" valuebased on local station density. Refer to Section 10.01.

F. The stick is unlocked (released) or locked (stowed) by depressing the stick latch and turning the latch90 degrees in either direction. A flat-bit screwdriver can be used to depress and turn the latch. Theoperating procedures for all sticks are identical.

G. During fueling, the measuring stick(s) may remain extended as the float rises with the fuel in the tank,the graduated stick in inches can be read as the float carries the stick up into the tank.

21.01.7 Determining Fuel Quantity by Measuring Stick

A. Anytime fuel quantity is determined by measuring stick, the following procedure must be used:1. Determine the method, 2 or 3, (refer to Section 21.01.5) to be utilized to fuel the aircraft and check


(1) Determine:a) The aircraft attitude before fueling.b) Tank stick(s) needed to measure the fuel quantity and associated charts to determine

the pounds in the affected tank.(2) Record the before fueling information where applicable on the fuel slip and Inoperative

Fuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (ex. L, LI, C,

ACT1, Trim, etc.) in the space provided below "TANK."b) Record the before fueling aircraft attitude (pitch and roll).c) Circle the stick(s) used before fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only).d) Record the units / inches read from the applicable stick(s) in the before fueling

spaces.e) Record the before fueling quantity from the applicable stick chart in pounds on the


a) The aircraft attitude after fueling.



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b) Tank stick(s) needed to measure the fuel quantity and associated charts to determinethe after fueling pounds in the affected tank.

(5) Record the after fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner / outer cell

(Airbus 319/320 aircraft only)c) Record the units/inches read from the applicable stick(s) in the after fueling spaces.d) Record the after fueling quantity from the applicable stick chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Ensure all sticks are secured and initial where applicable. Print your name, present





Fuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (ex. L, LI, C,

ACT1, Trim, etc.) in the space provided below "TANK."b) Leave the before fueling aircraft attitude (pitch and roll) spaces blank and do not

circle any stick(s) utilized before fueling and applicable inner/outer cell tanks.c) Record the before fueling quantity of zero pounds on the fuel slip and the Inoperative




Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) used after fueling (all aircraft) and applicable inner/outer cell

(Airbus 319/320 aircraft only)c) Record the units/inches read from the applicable stick(s) in the after fueling spaces.d) Record the after fueling quantity from the applicable stick chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Ensure all sticks are secured and initial where applicable. Print your name, present




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Figure 21.01-9: Magnetic Measuring Stick



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21.01.8 Defueling

WARNING: DEPLANE ALL PASSENGERS AND NON-ESSENTIAL CREW WHEN DEFUELING AMAIN TANKOR TRANSFERRING FUEL FROMAMAIN TANK THAT HAS AQUANTITYBELOW 2,000 POUNDS (900 KILOGRAMS) UNTIL THE PROCESS HAS BEENCOMPLETED AND THE RESPECTIVE FUEL BOOST PUMPS ARE TURNED OFF.

WARNING: WHEN TRANSFERRING OR DEFUELING CENTER OR MAIN WING TANKS, THEFUEL PUMP LOW PRESSURE INDICATION LIGHTS MUST BE MONITORED ANDTHE FUEL PUMPSPOSITIONEDTOOFFAT THE FIRST INDICATIONOF FUEL PUMPLOW PRESSURE. TRANSFERRING FUEL OR DEFUELING WITH PASSENGERS ONBOARD IS PROHIBITED EXCEPT UNDER CERTAIN CONDITIONS:


FUEL MAY BE TRANSFERRED FROM THE CENTER TANK OR THE AIRCRAFTCENTER TANK MAY BE DEFUELED WITH PASSENGERS ON BOARD, PROVIDEDTHE AUTOMATIC SHUTOFF SYSTEM FOR THE CENTER TANK BOOST PUMP ISOPERATING.


A. The aircraft fuel system is designed to permit partial or complete defueling of any or all tanks. Portionsof the pressure fueling and engine fuel feed systems are used for defueling operations.CAUTION: DURING DEFUELING OPERATIONS, PROBLEMS MAY ARISE WHILE

TRANSFERRINGFUELANDDEFUELINGSIMULTANEOUSLY.WHENDEFUELINGAIRCRAFT, YOU SHOULD ONLY PERFORM ONE PROCEDURE AT A TIME,EITHER TRANSFER FUEL OR DEFUEL.

B. Defueling can be accomplished by the suction method, boost pump pressure method, or by acombination of both.1. Defueling by the suction method is used primarily to remove minimum quantities of fuel from the

tanks when adjusting fuel loads. This method is accomplished using the fuel truck suction pumpto withdraw fuel from the tanks through the tank fill lines and fueling valves. Only partial defuelingcan be accomplished by this method.NOTE : The center tank cannot be defueled by the suction method.

2. Defueling by the boost pump pressure method can be used for partial or complete defueling ofany or all tanks. This method is faster than suction defueling, and is accomplished by using therespective center and/or wing tank fuel boost pumps to pump fuel from the tanks and into thedefueling line. Fuel truck suction can be used during the method to increase the defueling flowrate. Any residual fuel remaining in the tanks after completely defueling can be drained throughthe tanks sump drain valves.

C. Suction Method (Partial Defueling)NOTE : External or APU electrical power should be used for defueling operations. If external or

APU power sources are not available, the airplane battery may be used as a power source.

1. Correctly position the defueling vehicle.2. Bond the defueling vehicle to the aircraft.

NOTE : Place a monitor by the dome cover access to ensure tanker does not overfill.



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3. Open fueling control station access door. If the external, or APU power is applied, the electricalpower for the fueling will be automatically supplied when the fueling control station access dooris in the fully extended position. If external, or APU power is not applied, the aircraft may be fueledwith battery power. Place the Battery switch in the cockpit to the ON position and open the fuelingcontrol station access door. Refer to Figure 21.01-5.

4. Connect hose nozzle to fueling receptacle. Open nozzle valve. Refer to Figure 21.01-5.5. Move DEFUEL VALVE handle to the open position. Refer to Figure 21.01-6.6. Start defueling truck suction pump.7. Monitor applicable fuel quantity indicators. Refer to Figure 21.01-8.8. Position FUELING VALVE switch(es) to CLOSE when the desired amount of fuel is obtained in

each respective tank. Verify corresponding FUELINGVALVE position indicator light extinguishes.Refer to Figure 21.01-8.

9. Move DEFUEL VALVE handle to the closed position. Refer to Figure 21.01-6.10. Stop defueling truck suction pump immediately.11. Remove hose nozzle from fueling receptacle. Refer to Figure 21.01-5.12. Close fueling control station access door. Refer to Figure 21.01-5.

NOTE : Close the tanker unit dome cover.

13. Disconnect aircraft and fueling vehicle bonding cable.D. Pressure Defueling (Partial or Complete Defueling)

WARNING: DEPLANEALL PASSENGERSANDNON-ESSENTIALCREWWHENDEFUELINGA MAIN TANK OR TRANSFERRING FUEL FROM A MAIN TANK THAT HAS AQUANTITY BELOW 2,000 POUNDS (900 KILOGRAMS) UNTIL THE PROCESSHAS BEEN COMPLETED AND THE RESPECTIVE FUEL BOOST PUMPS ARETURNED OFF.



FUEL MAY BE TRANSFERRED FROM THE CENTER TANK OR THE AIRCRAFTCENTERTANKMAYBEDEFUELEDWITHPASSENGERSONBOARD, PROVIDEDTHE AUTOMATIC SHUTOFF SYSTEM FOR THE CENTER TANK BOOST PUMPIS OPERATING.

NOTE : External or APU electrical power should be used for defueling operations. If external orAPU power sources are not available, the airplane battery may be used as a power source.

1. Correctly Position the defueling vehicle.2. Bond the defueling truck to the aircraft.

NOTE : Place a monitor by the dome cover access to ensure tanker does not overfill.

3. Open fueling control station access door. If the external, or APU power is applied, the electricalpower for the fueling will be automatically supplied when the fueling control station access dooris in the fully extended position. If external, or APU power is not applied, the aircraft may be fueled



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with battery power. Place the Battery switch in the cockpit to the ON position and open the fuelingcontrol station access door. Refer to Figure 21.01-5.

4. Connect hose nozzle to fueling receptacle. Open nozzle valve. Refer to Figure 21.01-5.5. Move DEFUEL VALVE handle to the open position. Refer to Figure 21.01-6.6. Set FUELING VALVE position switch(es) to open. Refer to Figure 21.01-8.7. For tanks to be defueled, place respective fuel boost pump switches (in cockpit) to ON position.

Refer to Figure 21.01-7.NOTE : All fuel tanks can be defueled individually or simultaneously as required.

8. To expedite the defueling process, start fuel vehicle defueling pump.9. Monitor applicable fuel quantity indicators and continue defueling until desired fuel quantity

remains. Refer to Figure 21.01-8.10. Stop fuel truck defueling pump just prior to desired fuel tank(s) quantity.11. Place applicable fuel boost pump switches in cockpit to OFF position, when desired defueling of

each tank is accomplished. Refer to Figure 21.01-7.12. Position FUELING VALVE position switch(es) to CLOSE. Refer to Figure 21.01-8.13. Move DEFUEL VALVE handle to closed. Refer to Figure 21.01-6.14. Close fueling control station access door. Refer to Figure 21.01-5.

NOTE : Close and lock the tanker unit dome cover.

15. If required, drain applicable fuel tank sumps.16. Disconnect aircraft and fueling vehicle bonding cable.

21.01.9 B737 Fuel Distribution Guide

A. Refer to B737 Fuel Quantity Measuring Stick Charts as follows:1. Access the Stick Charts at http://me.aa.com/manuals/fw/FuelingStickCharts/#z.

END



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Table of contents

22.01 FUELING MANUAL - B757GENERAL..........................................................................................................................1UNDERWING PRESSURE FUELING (AUTOMATIC OPERATION).................................4UNDERWING PRESSURE FUELING (MANUAL OPERATION).......................................6UNDERWING PRESSURE FUELING WITHOUT ELECTRICAL POWER.......................7OVERWING (GRAVITY) FUELING....................................................................................9TANK-TO-TANK GROUND TRANSFER OF FUEL.........................................................11INACCURATE OR INOPERATIVE FUELING QUANTITY INDICATORS........................14OPERATION OF FUEL QUANTITY MEASURING STICKS............................................16DETERMINING FUEL QUANTITY BY MEASURING STICK..........................................17DEFUELING....................................................................................................................19GENERAL........................................................................................................................22

22.02 B757 FUEL DISTRIBUTION GUIDEGENERAL..........................................................................................................................1



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A. Fueling can be accomplished by the pressure or gravity method, with or without power, utilizingconventional ground support equipment. The airplane is normally fueled by the pressure method.Overwing gravity fueling should be considered as an emergency procedure.

B. The fuel system has two main tanks and one center tank. There is also a vent surge tank located ineach wing, outboard of the wing tank.1. For B757 aircraft (5BS – 5CY and 5DM – 5EP):

a. Center tank has approximate volume of 6924 USgal.b. Main (wing) tanks each have an approximate volume of 2,176 USgal.

2. For B757 aircraft (5DJ, 5DK and 5ER – 5FT):a. Center tank has approximate volume of 7017 USgal.b. Main (wing) tanks each have an approximate volume of 2,236 USgal.

3. For B757 aircraft (200 - 207, 935 – 939 and 941, 942):a. Center tank has approximate volume of 7000 USgal.b. Main (wing) tanks each have an approximate volume of 2,239 USgal.


NOTE : Fuel truck/tankers are not to be disconnected from a/c until all fueling discrepancies havebeen cleared.

NOTE : The use of Jet B is prohibited on all B-757 aircraft.

WARNING: A) DO NOT OPERATE THE HF COMMUNICATION SYSTEM DURINGREFUELING OPERATIONS. A FIRE OR EXPLOSION CAN OCCUR.

B) GROUND EQUIPMENT MUST NOT BE POSITIONED UNDER WING TIPSDURING FUELING OPERATION.

C) FUELING VEHICLEMUST BE PROPERLY BONDED TO AIRCRAFT BEFOREANY FUELING/DEFUELING OPERATION.

D) WHEN THERE IS AN INACCURATE/INOPERATIVE OR A SUSPICION OF AGAUGE NOT INDICATING PROPERLY, STOP FUELING AND NOTIFYAIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON, BY RADIO,TELEPHONE OR OTHER AGREEABLE METHOD.

E) NOTE: IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARD ASBEING INOPERATIVE, AIRCRAFT MAINTENANCE DOES NOT NEED TO BENOTIFIED, UNLESS SPECIFIC PROCEDURES DURING FUELINGOPERATIONS REQUIRE THE ATTENTION OF AIRCRAFT MAINTENANCE.

F) IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION,NOTIFYAIRCRAFTMAINTENANCE IMMEDIATELY INPERSON,BYRADIO, TELEPHONEOROTHERAGREEABLEMETHOD.DONOTSTARTOR RESUME FUELING OPERATIONS UNTIL CORRECTIVE ACTION HASBEEN TAKEN.

G) DO NOT START OR SHUTDOWN APU SHOULD FUEL SPILL OCCUR.H) DEFUELING OR TRANSFERRING FUEL WITH PASSENGERS ONBOARD

THE AIRCRAFT IS PROHIBITED, EXCEPT UNDER CERTAIN CONDITIONS.



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REFER TO SECTION 22.01.06 TANK-TO-TANK GROUND TRANSFER OFFUEL OR SECTION 22.01.10 DEFUELING.

C. Pressure Fueling1. Pressure fueling is accomplished through a single point fueling station. The fueling station consists

of 2 pressure fueling receptacles and control panel. The control panel is used for controlling andmonitoring the pressure fueling operation and contains fuel quantity indicators and switches.Refer to Figure 22.01-2.

2. Fuel flow through the pressure fueling receptacles (manifold) is directed to any or all fuel tanksdesired through electrically or manually operated fuel tank fill valves which are located on therear spar of each main wing tank and main gear wheel well area.

3. Access to the fueling station and control panel is through a hinged access door located on thelower surface of the right midwing leading edge, approximately 13-1/2 feet from ramp level. Referto Figure 22.01-2.


D. Gravity Fueling1. Overwing gravity fueling of the aircraft fuel tanks becomes necessary only when pressure fueling

facilities are not available. Overwing fill ports are located on top of the right and left main wingtanks. Refer to Figure 22.01-1. The center tank can be filled by fuel transfer from the main wingtanks.

E. Fuel Quantity Measuring1. The primary measuring devices used in determining fuel quantity are the cockpit and underwing


2. An alternate means of determining fuel quantity may be obtained by the use of the mechanicalmagnetic measuring sticks located on the bottom of the main wing tanks and center tank. Referto Figure 22.01-7.



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Figure 22.01-1: Overview and Fuel Tank Capacities



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Figure 22.01-2: Fueling Station and Control Panel


A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft. Refer to Figure 22.01-3 for location of aircraft bonding point.

NOTE : The B757 has bonding points on eachmain landing gear truck assembly shield. Fuel nozzlegrounding receptacles are provided at the gravity fueling points.



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Figure 22.01-3: Bonding Point Location

D. Open fueling control station access door. Electrical power for fueling will be automatically suppliedwhen the access door is in the fully extended position.NOTE : If electrical power is not available when the fueling control station access door is opened,

battery power may be obtained by positioning the POWER switch to the BAT position. Referto Figure 22.01-2.

1. Position fueling receptacle(s) to FUEL mode. Refer to Figure 22.01-2.E. Connect fueling nozzle(s) to aircraft pressure fueling receptacle(s).


F. Test LOAD SELECT INDICATORS by pressing IND TEST switch; 88.8 should appear on the upperand lower LCD displays. Refer to Figure 22.01-2.

G. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING LBS." spaceson the fuel slip. Refer to Section 15.01.

H. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.

I. Press to test each FUELING VALVE INDICATOR LIGHT. Verify each light illuminates when pressed.Refer to Figure 22.01-2.

J. At the LOAD SELECTOR control, position thumbwheel switches to desired amount of fuel. Pressselected TANK LOAD SET switch, and hold for one second minimum. Repeat process for each tank.Refer to Figure 22.01-2.



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NOTE : a) The thumbwheel has only 3 numbers to preselect desired amount of fuel per tank. Asper Section 15.01, the amount of fuel required for tanks 1 and 3 is 14,575. The numberson the thumbwheel should then be 14.6 x 1,000 = 14,600 pounds.

b) If error is made during selection process, press applicable TANK LOAD SET switchand repeat procedure.

c) It is desirable to fuel all tank simultaneous.

K. Place applicable FUELING VALVE switches to the FUEL position. The blue valve open indicator lightswill illuminate only when fueling pressure is applied. Refer to Figure 22.01-2.NOTE : If one or more fuel valves are electrically inoperable, refer to Section 22.01.4.

L. Start fueling operation by activating deadman control.M. Monitor applicable fuel quantity indicators.N. Press SYSTEM TEST button. Fueling valves will close sequentially. Fueling valves will reopen and

fueling operation continues. Refer to Figure 22.01-2.O. Fueling valves will close automatically when the required pre-selected amount of fuel is obtained in

each tank.NOTE : Fueling valves will also close should a malfunction occur.

P. When fueling valves close automatically, place applicable FUELING VALVE switches toOFF position.Q. When operation is complete, stop fueling source by releasing deadman control.R. Remove fueling nozzle(s).

1. Position fueling receptacle(s) to FUEL mode. Refer to Figure 22.01-2.S. Check that all FUELING VALVE switches are in theOFF position, then close the fueling control station

access door.T. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.U. Disconnect aircraft and fueling vehicle bonding cables.


A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fuel control station access door. Electrical power for fueling will be automatically supplied when

the access door is in the fully extended position.NOTE : If electrical power is not available when the fueling control station access door is opened,




F. Test LOAD SELECT INDICATORS by pressing IND TEST switch. 88.8 should appear on the upperand lower LCD displays. Refer to Figure 22.01-2.

G. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS." spaceson the fuel slip. Refer to Section 15.01.



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H. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.

I. Press to test each FUELING VALVE INDICATOR LIGHT. Verify each light illuminates when pressed.Refer to Figure 22.01-2.

J. If the LOAD SELECT INDICATORS are not blank, press applicable TANK LOAD SET switches toblank the displays and to select the manual mode.

K. Place applicable FUELING VALVE switches to the FUEL position. The blue "valve open" indicatorlights will illuminate only when fueling pressure is applied. Refer to Figure 22.01-2.

L. Start fueling operation by activating deadman control.NOTE : If one or more fueling valves are electrically inoperable, refer to Section 22.01.4.

M. Monitor applicable fuel quantity indicators.NOTE : Use caution when reaching maximum capacity of each respective tank to avoid overfilling

the tank resulting in a fuel spill.

N. Place applicable FUELING VALVE switch to theOFF position when desired amount of fuel is obtainedin each respective tank. Verify that the blue FUELING VALVE indicator lights extinguish.

O. When operation is complete, stop fueling source by releasing deadman control.1. Position fueling receptacle(s) to FUEL mode. Refer to Figure 22.01-2.

P. Remove fueling nozzle(s).Q. Check that all FUELING VALVE switches are in theOFF position, then close the fueling control station

access door.R. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.S. Disconnect aircraft and fueling vehicle bonding cables.


CAUTION: NO AUTOMATIC SHUTDOWN OR OVERFILL PROTECTION EXISTS WITHOUTELECTRICAL POWER.

1.

2. DO NOT USE FUELING VALVES MANUALLY TO REDUCE OR STOP FUELING.

A. Obtain the jet fuel service record.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control station access door.



F. Use magnetic measuring sticks to determine fuel quantity in each tank before fueling. Refer to Section22.01.7, Section 22.01.8 and Section 22.01.9.NOTE : Aircraft must be level (wings 0 degrees and nose -0.3 degrees) to obtain accurate fuel tank

quantities when using measuring sticks.

G. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS." spaceson the fuel slip. Refer to Section 15.01.



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H. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.CAUTION: PRIOR TO GAINING ACCESS TO THE CENTER TANK FUELING VALVES,

ENSURE THAT APPLICABLE LANDING GEAR DOOR LOCKS ARE INSTALLED.RAPID ACTION OF DOORS MAY CAUSE INJURY OR DAMAGE IF LOCKS ARENOT INSTALLED. FOR AA AIRCRAFT, REFER TO SECTION 32-00-15 OF THEAA MAINTENANCE MANUAL.

I. Manually open applicable fueling valve(s). Refer to Figure 22.01-4.1. Verify fueling manifold is not pressurized.

NOTE : Fueling manifold will depressurize automatically when fueling pressure is not appliedand the center tank contains less than 22,000 lbs. of fuel.

2. Remove lockwire from knurled knob of fuel valve override screw.3. Rotate override screw 10-13 complete revolutions in counterclockwise direction.

NOTE : Pliers may be required to initially loosen override screw.

CAUTION: DO NOT REMOVE RETAINER PLATE LOCKWIRE, SCREWS, OR RETAINERPLATE. FUEL LEAKAGE MAY DEVELOP.

J. Start fueling operation by activating deadman control.K. Monitor magnetic measuring sticks carefully during the fueling process.

CAUTION: WITHOUT ELECTRICAL POWER DURING FUELING PROCESS AND FUELINGVALVE(S) MANUALLY OPENED, THERE IS NO ELECTRICAL PROTECTION TOPREVENT OVERFILL FUEL SPILLS.

L. Stop the fueling source when desired amount of fuel is obtained in each respective fuel tank byreleasing deadman control.

M. Verify fuel tank quantity by use of magnetic measuring sticks.NOTE : Aircraft must be level (wings 0 degrees and nose -0.3 degrees) to obtain accurate fuel tank


WARNING: PRIOR TO GAINING ACCESS TO THE CENTER TANK FUELING VALVES,ENSURE THAT APPLICABLE LANDING GEAR DOOR LOCKS ARE INSTALLED.RAPID ACTION OF DOORS MAY CAUSE INJURY OR DAMAGE IF LOCKS ARENOT INSTALLED. (FOR AA AIRCRAFT, REFERENCE SECTION 32-00-15 OF THEAA MAINTENANCE MANUAL.

N. Manually close applicable fueling valve(s). Refer to Figure 22.01-4.1. Verify fueling manifold is not pressurized.

NOTE : Fueling manifold will depressurize automatically when fueling pressure is not appliedand the center tank contains less than 22,000 lbs. of fuel.

2. Rotate override screw 10-13 complete revolutions in clockwise direction.3. Ensure knurled knob of fuel valve(s) override screw is lockwired in place.

O. Remove fueling nozzle(s).1. Position fueling receptacle(s) to FUEL mode (refer to Figure 22.01-2).

P. Close fueling station control access panel.Q. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.R. Disconnect aircraft and fueling vehicle bonding cables.



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S. Install applicable fueling valve access panels. Refer to Figure 22.01-4.T. Remove applicable landing gear door locks.

Figure 22.01-4: Fueling Valve Manual Operation

22.01.5 Overwing (Gravity) Fueling

NOTE : Overwing fueling is considered an emergency fueling method and shall be used only when thefollowing conditions exist:(1) No underwing (pressure) fueling vehicles available.(2) Aircraft underwing (pressure fuel system) components are malfunctioning.(3) Other emergencies, as recognized by station management.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.



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D. Open fueling control station access door. Electrical power for fueling will be automatically suppliedwhen the access door is in the fully extended position.NOTE : If electrical power is not available when the fueling control station access door is opened,


E. Test LOAD SELECT INDICATORS by pressing IND TEST switch. 88.8 should appear on the upperand lower LCD displays. Refer to Figure 22.01-2.

F. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS." spaceson the fuel slip. Refer to Section 15.01.

G. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.NOTE : Main wing tanks may be fueled by the overwing gravity method only. The center tank can

be filled by fuel transfer from the main wing tanks. Refer to Section 22.01.6 for fuel transferprocedures and warnings.

H. Use suitable lift device or ladder to gain access to main wing tank overwing fill port(s). Refer toFigure 22.01-5.

I. Place maintenance mats on the wing where service personnel must walk.J. Connect fueling nozzle grounding plug to overwing fill grounding receptacle.K. Remove overwing filler cap for tank to be fueled and insert fueling nozzle. Slowly open fueling nozzle

valve, start fueling. Refer to Figure 22.01-5.NOTE : Load main wing tanks with equal amounts of fuel.

CAUTION: DO NOT EXCEED MAXIMUM ALLOWABLE FUELING RATE OF 100 GPM.

L. If the center tank requires fuel, transfer fuel from main wing tank(s) that is being overwing (gravity)fueled. Refer to Section 22.01.5 for fuel transfer procedures and warnings.

M. Monitor applicable fuel quantity indicators.N. After fuel transfer is complete, top-off main wing tank(s) to desired fuel quantity.

CAUTION: USE EXTREME CAUTION WHEN REACHING MAXIMUM CAPACITY FOR MAINWINGTANKS TOAVOIDOVERFILLING THE TANKRESULTING IN A FUEL SPILL.

O. When fueling is complete, stop fueling source by releasing deadman control.P. Remove fueling nozzle. Disconnect nozzle grounding plug.Q. Install and lock fill adapter cap(s).R. Remove maintenance mats.S. If fuel transfer was accomplished, ensure the center tank FUELING VALVE switch is in the OFF

position. Close fueling control station access door.T. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.U. Disconnect aircraft and fueling vehicle bonding cables.



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Figure 22.01-5: Overwing (Gravity) Fueling

22.01.6 Tank-To-Tank Ground Transfer of Fuel

WARNING: THECENTERTANKFUELPUMPSWITCHESMUSTNOTBEPOSITIONEDONUNLESSTHE CENTER TANK CONTAINS USABLE FUEL. FOR GROUND AND FLIGHTOPERATIONS, THE CENTER TANK FUEL PUMP SWITCH MUST BE SELECTEDOFFWHEN THE RESPECTIVE CTR L FUEL PUMP OR CTR R FUEL PUMP MESSAGEDISPLAYS. BOTH CENTER FUEL PUMP SWITCHES MUST BE SELECTED TO OFF



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WHEN EITHER CTR L FUEL PUMP OR CTR R FUEL PUMP MESSAGE DISPLAYS IFTHE CENTER TANK IS EMPTY.

WARNING: WHEN TRANSFERRING FUEL OR DEFUELING CENTER OR MAIN WING TANKS,THE CENTER FUEL PUMP LOWPRESSUREMUST BEMONITORED AND THE FUELPUMP SWITCHES POSITIONED TO OFF AT THE FIRST INDICATION OF LOWPRESSURE. PRIOR TO TRANSFERRING FUEL OR DEFUELING, CONDUCT A LAMPTEST OF THE RESPECTIVE FUEL PUMP PRESS LIGHTS.

WARNING: DEFUELING MAIN TANKS WITH PASSENGERS ONBOARD IS PROHIBITED IF MAINTANK FUEL PUMPS ARE POWERED. FUEL MAY BE TRANSFERRED FROM TANKTO TANK, OR THE AIRCRAFT MAY BE DEFUELEDWITH PASSENGERS ONBOARD,PROVIDED FUEL QUANTITY IN THE MAIN TANK FROM WHICH FUEL IS BEINGTRANSFERRED FROM IS MAINTAINED ABOVE 2,000 LBS (900 KILOGRAMS).

NOTE : The center tank pumps each have the UFI installed for automatic shutoff and are exempt frommaintaining 2,000 lbs. or any level of fuel except usable fuel when transferring or defueling (notapplicable to Legacy US Aircraft).

A. Ground transfer of fuel is accomplished by following the basic procedure used for defueling (refer toSection 22.01.10) and using the components used for pressure fueling. The fueling manifold ispressurized by fuel tank boost pumps and the fueling valve(s) in the tank(s) selected to receive fuelis opened.CAUTION: DURING DEFUELING OPERATIONS, PROBLEMS MAY ARISE WHILE


NOTE : The following operational procedures may be used when required, during the overwing(gravity) fueling method. Tank-to-tank fuel load adjustments may also be accomplished bythe following procedures.

WARNING: DO NOT OPERATE HYDRAULIC SYSTEM IF FUEL IN EITHERMAINWING TANKIS LESS THAN 4,020 LBS. (600 GAL).

B. To transfer fuel from the right main wing tank to the left main wing tank (refer to Figure 22.01-6):1. Place left main tank FUELING VALVE switch to the FUEL Position.2. Place right main tank DEFUEL VALVE switch to the OPEN position.3. Place CROSSFEED VALVE (cockpit) to the OPEN position.4. Place right main tank boost pump switch(es) (cockpit) to the ON position.5. Monitor applicable fuel quantity indicators and place right main tank boost pump switch(es) to

OFF when desired fuel quantity is obtained.6. Place right main tank DEFUEL VALVE switch to the CLOSED position. Place left main tank

FUELING VALVE switch to the OFF position.7. Top-off right main wing tank if required.

C. To transfer fuel from the left main wing tank to the right main wing tank (refer to Figure 22.01-6):1. Place right main tank FUELING VALVE switch to the FUEL position.2. Place left main tank DEFUEL VALVE switch to the OPEN position.3. Place CROSSFEED VALVE (cockpit) to the OPEN position.4. Place left main tank boost pump switch(es) (cockpit) to the ON position.



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5. Monitor applicable fuel quantity indicators and place left main tank boost pump switch(es) toOFFwhen desired fuel quantity is obtained.

6. Place left main tank DEFUEL VALVE switch to the CLOSED position. Place right main tankFUELING VALVE switch to the OFF position.

7. Top-off left main wing tank if required.D. To transfer fuel from the right and/or left main wing tank(s) to the center tank (refer to Figure 22.01-6):

1. Place center tank FUELING VALVE switch to the FUEL position.2. Place right and/or left main tank(s) DEFUEL VALVE switch(es) to the OPEN position.3. Place right and/or left main tank(s) boost pump switch(es) (cockpit) to the ON position.4. Monitor applicable fuel quantity indicators and place right and/or left main tank boost pump

switch(es) to OFF when desired fuel quantity is obtained.5. Place right and/or left main tank DEFUEL VALVE switch(es) to the CLOSED position. Place

center tank FUELING VALVE switch to the OFF position.6. Top-off right and/or left main wing tanks, if required.

E. To transfer fuel from the center tank to the right and/or left main wing tank(s) (refer to Figure 22.01-6):WARNING: DEPLANEALL PASSENGERSANDNON-ESSENTIALCREWWHENDEFUELING

A TANK OR TRANSFERRING FUEL FROM A TANK THAT HAS A QUANTITYBELOW 2,000 POUNDS (900 KILOGRAMS) UNTIL THE PROCESS HAS BEENCOMPLETED AND THE RESPECTIVE FUEL BOOST PUMPS ARE TURNEDOFF.



FUEL MAY BE TRANSFERRED FROM TANK TO TANK OR THE AIRCRAFT MAYBE DEFUELED WITH PASSENGERS ON BOARD, PROVIDED THE FUELQUANTITY IN THE TANK FROMWHICH FUEL IS BEING TAKEN IS MAINTAINEDAT NOT LESS THAN 2,000 POUNDS (900 KILOGRAMS).

1. Place right and/or left main tank(s) FUELING VALVE switch(es) to the FUEL position.2. Place right and/or left main tank(s) DEFUEL VALVE switch(es) to the OPEN position.3. Place center tank boost pump switch(es) (cockpit) to the ON position.4. Monitor applicable fuel quantity indicators and place center tank boost pump switch(s) to OFF

when desired fuel quantity is obtained.5. Place right and/or left main tank(s) DEFUEL VALVE switch(es) to the CLOSED position. Place

FUELING VALVE switch(es) to the OFF position.6. Top-off center tank, if required.

F. On completion of fuel transfer, check that all tank boost pumps are OFF in the cockpit.G. Ensure that all FUELINGVALVE switches areOFF and the DEFUELINGVALVE switches areCLOSED.

Close fueling control station access door.



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Figure 22.01-6: Cockpit and Underwing Fueling Controls


NOTE : When the flight deck fuel quantity display is inoperative, its respective underwing panelquantity indicator may be used to determine fuel tank quantity, provided respective underwing

1.

display is verified operational. Additionally, after refueling, the total fuel quantity in all tankscontaining fuel must be verified by using measuring sticks. A copy of the fuel slip must beprovided to the flight crew for departure.

2. When an inoperative fuel tank quantity indication channel exists, the total fuel quantity inthe affected tank must be verified by using measuring sticks after refueling. A copy of thefuel slip must be provided to the flight crew for departure.

A. Method 1 - For use when the flight deck fuel quantity display is operational and one or more of theunderwing panel fuel quantity displays are inoperative. Refer to Section 15.01.5.



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Individual fuel tank quantity may be determined by the respective cockpit display for the inoperativeunderwing panel quantity indicator, provided respective cockpit display is verified operational.

1.

Verification of fuel quantity, by measuring stick, is not required with Method 1. Use of Method 1will be noted on the fuel slip, with a copy of the fuel slip provided to the flight crew as early aspracticable after fueling.

B. Method 2 - For use on main tanks (wings) and center tank when the flight deck fuel quantity displayis inoperative, one or more of the underwing panel fuel quantity displays are inoperative and fuel onboard can be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.5.1. Determine if aircraft is within the limits of -2.30° to +1.70° pitch and -2.00° to 2.00° roll. The aircraft

must be within these limits of pitch and roll in order to use the fuel measuring sticks. Assistancefrom Aircraft Maintenance personnel must be requested in making this determination. Refer toB757 AMM for procedures.a. Each airplane has a leveling scale and a plumb bob that can hang in the right main wheel

well. The airplane attitude is found by the position of the plumb bob above the leveling scale.The fore and aft scale is used for pitch and the side to side scale is for roll. Refer to Figure22.01-7.

Figure 22.01-7: Plumb Bob and Leveling Scale



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2. Before fueling, determine existing fuel tank quantity with the measuring stick of the affected tank.Subtract this quantity from the tank quantity required and convert to gallons. Fuel the tank todesired level using the truck meter. Use measuring stick(s) to verify tank quantity. Refer to Section22.01.9 for verification procedure.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons to

deliver the desired known quantity. Refer to Section 15.01.7.

3. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity IndicatorService Record ensuring all required entries and signatures are legible and in place as early aspracticable, before departure.

C. Method 3 - For use on main tanks (wings) and center tank when the flight deck fuel quantity displayis inoperative, one or two of the underwing panel fuel quantity displays are inoperative and fuel onboard cannot be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.5.1. Completely defuel tank with the inoperative indicator by transferring fuel to other tank(s) or by

defueling. Refer to Section 22.01.6 or Section 22.01.10.WARNING: DEPLANE ALL PASSENGERS AND NON-ESSENTIAL CREW WHEN

DEFUELING A TANK OR TRANSFERRING FUEL FROM A TANK THAT HASA QUANTITY BELOW 2,000 POUNDS (900 KILOGRAMS) UNTIL THEPROCESS HAS BEEN COMPLETED AND THE RESPECTIVE FUEL BOOSTPUMPS ARE TURNED OFF.

WARNING: WHEN TRANSFERRING OR DEFUELING CENTER OR MAIN WING TANKS,THE FUEL PUMP LOW PRESSURE INDICATION LIGHTS MUST BEMONITORED AND THE FUEL PUMPS POSITIONED TO OFF AT THE FIRSTINDICATION OF FUEL PUMP LOW PRESSURE. TRANSFERRING FUEL ORDEFUELING WITH PASSENGERS ON BOARD IS PROHIBITED EXCEPTUNDER CERTAIN CONDITIONS:

ALTERNATIVE PROCEDURE (CONDITIONAL);

FUEL MAY BE TRANSFERRED FROM TANK TO TANK OR THE AIRCRAFTMAYBEDEFUELEDWITHPASSENGERSONBOARD, PROVIDEDTHEFUELQUANTITY IN THE TANK FROM WHICH FUEL IS BEING TAKEN ISMAINTAINED AT NOT LESS THAN 2,000 POUNDS (900 KILOGRAMS).

2. Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged by the fuelequipment meter reading. Alternately, transfer required fuel from tank(s) with operative indicator.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to gallons, refer


3. Fill tank(s) with operative indicator to quantity of fuel required.NOTE : Use of Method 3 requires final verification by measuring stick.

4. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity IndicatorService Record ensuring all required entries and signatures are legible and in place as early aspracticable, before departure. Refer to Section 15.01.





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B. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), aVendor Supervisor, Lead or Supervisor/Lead, Designated Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

C. Each main wing tank contains 5 fuel measuring sticks located on the lower wing surface. The centertank contains 4 fuel measuring sticks. Refer to Figure 22.01-8)

D. The measuring sticks are the magnetic dripless-type, consisting of a mounting, a tube housing, aninner tube (indicator stick) graduated in inches for determining fuel tank quantity, and a circular float.The float is installed on the tube housing and is free to move up and down with the fuel level in thetank. Refer to Figure 22.01-8. When the fuel level stick tip is magnetically coupled to the circular float,the stick is positioned relative to the fuel level in the tank.

E. Fuel quantities quoted in the fuel quantity charts are based on fuel with a density of 6.7 pounds perU.S. Gallon. Use the Verification Charts to convert from inches to pounds.NOTE : When actual fuel density deviates greatly from the nominal chart value of 6.70 pounds per


F. The stick is unlocked (released) or locked (stowed) by depressing the stick latch and turning the latch90 degrees in either direction. A flat-bit screwdriver can be used to depress and turn the latch. Theoperating procedures for all sticks are identical.

G. During fueling, the measuring stick(s) may remain extended as the float rises with the fuel in the tank,the graduated stick in inches can be read as the float carries the stick up into the tank.


A. Anytime fuel quantity is determined by measuring stick, the following procedure must be used:1. Determine the method, 2 or 3, (refer to Section 22.01.7) to be used to fuel the aircraft and check









determine the after fueling pounds in the affected tank.



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(5) Record the after fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner/outer cell




(6) The stick reading in inches and conversion to pounds must be verified by a cockpit crewmember by reviewing the completed fuel slip and Inoperative Fuel Quantity IndicatorService Record.
















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22.01.10 Defueling

WARNING: THECENTERTANKFUELPUMPSWITCHESMUSTNOTBEPOSITIONEDONUNLESSTHE CENTER TANK CONTAINS USABLE FUEL. FOR GROUND AND FLIGHTOPERATIONS, THE CENTER TANK FUEL PUMP SWITCH MUST BE SELECTEDOFFWHEN THE RESPECTIVE CTR L FUEL PUMP OR CTR R FUEL PUMP MESSAGEDISPLAYS. BOTH CENTER FUEL PUMP SWITCHES MUST BE SELECTED TO OFFWHEN EITHER CTR L FUEL PUMP OR CTR R FUEL PUMP MESSAGE DISPLAYS IFTHE CENTER TANK IS EMPTY.



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WARNING: WHEN TRANSFERRING FUEL OR DEFUELING CENTER OR MAIN WING TANKS,THE CENTER FUEL PUMP LOWPRESSUREMUST BEMONITORED AND THE FUELPUMP SWITCHES POSITIONED TO OFF AT THE FIRST INDICATION OF LOWPRESSURE. PRIOR TO TRANSFERRING FUEL OR DEUELING, CONDUCT A LAMPTEST OF THE RESPECTIVE FUEL PUMP PRESS LIGHTS.

WARNING: DEFUELING MAIN TANKS WITH PASSENGERS ONBOARD IS PROHIBITED IF MAINTANK FUEL PUMPS ARE POWERED. FUEL MAY BE TRANSFERRED FROM TANKTO TANK, OR THE AIRCRAFT MAY BE DEFUELEDWITH PASSENGERS ONBOARD,PROVIDED FUEL QUANTITY IN THE MAIN TANK FROM WHICH FUEL IS BEINGTRANSFERRED FROM IS MAINTAINED ABOVE 2,000 LBS (900 KILOGRAMS).

NOTE : The center tank pumps each have the UFI installed for automatic shutoff and are exempt frommaintaining 2,000 lbs. or any level of fuel except usable fuel when transferring or defueling.

NOTE : Center tank may be defueled until UFI shuts off the center pump(s) or lower pressure light comeson and stays on. Refer to TDG AFM for UFI equipped aircraft.


A. The aircraft fuel system is designed to permit partial or complete defueling of any or all tanks. Portionsof the pressure fueling and engine fuel feed systems are used for defueling operations.CAUTION: DURING DEFUELING OPERATIONS, PROBLEMS MAY ARISE WHILE



tanks when adjusting fuel loads. This method is accomplished using the fuel truck suction pumpto withdraw fuel from the tanks through the tank fill lines and fueling valves. Only partial defuelingcan be accomplished by this method.NOTE : The center tank cannot be defueled by the suction method.

2. Defueling by the boost pump pressure method can be used for partial or complete defueling ofany or all tanks. This method is faster than suction defueling, and is accomplished by using therespective center and/or wing tank fuel boost pumps to pump fuel from the tanks and into thedefueling line. Fuel truck suction can be used during the method to increase the defueling flowrate. Any residual fuel remaining in the tanks after completely defueling can be drained throughthe tanks sump drain valves.

C. Suction method (partial defueling)CAUTION: DO NOT OPERATE HYDRAULIC SYSTEM IF FUEL IN EITHER MAIN TANK IS

LESS THAN 4,020 LBS (600 GAL.).


1. Position the defueling vehicle.2. Bond the defueling truck to the aircraft.



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NOTE : Place a monitor by the dome cover access to ensure tanker DOES NOT overfill.

3. Open fueling control station access door. Electrical power for defueling will be automaticallysupplied when the access door is in the fully extended position.

4. Position fueling receptacle(s) to DEFUEL mode.5. Connect hose nozzle(s) to fueling receptacle(s). Open nozzle valve.6. Test "LOAD SELECT INDICATORS" by pressing TEST IND switch. 88.8 shall appear on upper

and lower LCD displays.7. Test DEFUELING VALVE indicator lights by press-to-test.8. Set DEFUELING VALVE switch(es) to OPEN. The blue "valve open" indicator light should

illuminate.NOTE : The center tank is not equipped with a defuel valve switch. Refer to Figure 22.01-6.

9. Start defueling truck suction pump.10. Monitor applicable fuel quantity indicators.11. Position DEFUEL VALVE switch(es) to CLOSE when the desired amount of fuel is obtained in

each respective tank. Verify corresponding DEFUEL VALVE position indicator light extinguishes.12. Stop defueling truck suction pump immediately.13. Close defueling nozzle valve. Remove nozzle.

NOTE : Position fueling receptacle(s) to FUEL mode. Refer to Figure 22.01-2.

a. Position fueling receptacle(s) to FUEL mode.14. Close fueling control station access door.


15. Disconnect aircraft and fueling vehicle bonding cable.D. Pressure defueling (partial or complete defueling)

WARNING: IN ORDER TO COMPLY WITH AN AIRWORTHINESS DIRECTIVE ISSUED BYTHE FAA, AA/TWA WILL BEGIN ISSUING NON-STANDARD FUEL LOADS FORTHE 757. AMINIMUMLOADOF 1,000 LBSWILL BEMAINTAINED IN THECENTERTANK. CAREFUL ATTENTION SHOULD BE GIVEN TO ALL 757 FUEL SLIPS TOENSURE A PROPER DISTRIBUTION. ANY DEVIATION FROM THE FUEL SLIPDISTRIBUTION SHOULD BE COMMUNICATED TO THE FLIGHT CREW ORBALANCE PLANNING AS SOON AS FUELING IS COMPLETED.

WARNING: DEPLANEALL PASSENGERSANDNON-ESSENTIALCREWWHENDEFUELINGA TANK OR TRANSFERRING FUEL FROM A TANK THAT HAS A QUANTITYBELOW 2,000 POUNDS (900 KILOGRAMS) UNTIL THE PROCESS HAS BEENCOMPLETED AND THE RESPECTIVE FUEL BOOST PUMPS ARE TURNEDOFF.



FUEL MAY BE TRANSFERRED FROM TANK TO TANK OR THE AIRCRAFT MAYBE DEFUELED WITH PASSENGERS ON BOARD, PROVIDED THE FUEL



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QUANTITY IN THE TANK FROMWHICH FUEL IS BEING TAKEN IS MAINTAINEDAT NOT LESS THAN 2,000 POUNDS (900 KILOGRAMS).

CAUTION: DO NOT OPERATE HYDRAULIC SYSTEM IF FUEL IN EITHER TANK IS LESSTHAN 4,020 LBS (600 GAL.).


1. Position the defueling vehicle.2. Bond the defueling truck to the aircraft.

NOTE : Place a monitor by the dome cover access to ensure tanker DOES NOT overfill.

3. Open fueling control access door. Electrical power for defueling will be automatically suppliedwhen the access door is in the fully extended position.

4. Position fueling receptacle(s); to DEFUEL mode.5. Connect hose nozzle(s) to fueling receptacle(s); open nozzle valve.6. Test "LOAD SELECT INDICATOR" by pressing TEST IND switch. 88.8 shall appear on upper

and lower LCD displays.7. Test DEFUELING VALVE indicator lights by press-to-test.8. Set DEFUELING VALVE switch(es) to OPEN. The blue "valve open" indicator light should

illuminate.NOTE : The center tank is not equipped with a defuel valve switch. Refer to Figure 22.01-6.

9. For tanks to be defueled, place respective fuel boost pump switches (cockpit) to ON position.Refer to Figure 22.01-6)NOTE : All fuel tanks can be defueled individually or simultaneously, as required.

10. To expedite the defueling process, start fuel truck defueling pump.11. Monitor applicable fuel quantity indicators and continue defueling until desired fuel quantity

remains.12. Stop fuel truck defueling pump just prior to desired fuel tank(s) quantity.13. Place applicable fuel boost pump switches to OFF position, when desired defueling of each tank

is accomplished.14. Position DEFUEL VALVE switch(es) to CLOSE. Verify corresponding DEFUEL VALVE position

indicator light extinguishes.15. Close defueling nozzle valve(s). Remove nozzle(s).

a. Position fueling receptacle(s) to FUEL mode. Refer to Figure 22.01-2.16. Close fueling control station access door.


17. If required, drain applicable fuel tank sumps.18. Disconnect aircraft and fueling vehicle bonding cable.

22.01.11 General

A. Simmonds Precision Fuel Quantity Indicating System (FQIS)1. AA B757 aircraft numbered 5BV and subsequent have the Simmonds FQIS installed when

received from the factory.



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2. The Simmonds system is similar to the Honeywell FQIS, but with major differences in the wingpanel control fuel tank indication system.

B. Automatic Operation1. Prior to fueling, or while fueling, a failure may occur which will cause a tank accuracy to exceed

plus or minus 5 percent. The affected fuel tank indicator will then display PUSH SET. The presetfuel load cannot be set and the automatic system will not function accurately. Refer toFigure 22.01-9.CAUTION: DURING THE PUSH SET MODE, THERE IS NO VOLUMETRIC SHUTOFF

(VSO).

2. When this occurs, stop fueling immediately and notify Aircraft Maintenance or station managementin person, by radio, telephone or other agreeable method.

3. Press the set button of the affected tank to place the system in the manual mode. The fuel quantityand load select windows will appear blank. Fuel the affected tank using alternate fuelingprocedures.

4. When a FAIL is displayed in the load select window, the aircraft can be fueled in the manualmode using the fuel quantity indicator since the accuracy is not affected by this failure. Refer toFigure 22.01-8.

5. When this occurs, notify Aircraft Maintenance or stationmanagement in person, by radio, telephoneor other agreeable method.

6. When a fuel quantity indicator is blinking, the accuracy of the indicator is doubtful. Stop fuelingimmediately and notify Aircraft Maintenance or station management in person, by radio, telephoneor other agreeable method.



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Figure 22.01-9: Auto Mode Fails

END



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Section 22.02 - B757 Fuel Distribution Guide22.02.1 General


END

Section 22.02B757 Fuel Distribution Guide


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Table of contents

23.01 FUELING MANUAL - B767GENERAL..........................................................................................................................1UNDERWING PRESSURE FUELING (AUTOMATIC OPERATION).................................4UNDERWING PRESSURE FUELING (MANUAL OPERATION).......................................6UNDERWING PRESSURE FUELING WITHOUT ELECTRICAL POWER.......................7OVERWING (GRAVITY) FUELING....................................................................................9TANK-TO-TANK GROUND TRANSFER OF FUEL.........................................................12INACCURATE OR INOPERATIVE FUELING QUANTITY INDICATORS........................14OPERATION OF FUEL QUANTITY MEASURING STICKS............................................18DETERMINING FUEL QUANTITY BY MEASURING STICK..........................................19DEFUELING....................................................................................................................21

23.02 B767 FUEL DISTRIBUTION GUIDES (FDG) AND QUANTITY VERIFICATION CHARTS(QVG)GENERAL..........................................................................................................................1



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A. Fueling can be accomplished by the pressure or gravity method, with or without power, utilizingconventional ground support equipment. The airplane is normally fueled by the pressure method.Overwing gravity method should be considered as an emergency procedure.

B. The fuel system has two main tanks and one center auxiliary tank. There is also a vent surge tanklocated in each wing, outboard of the wing tank.1. For B767 aircraft (N351 - N370):

a. Center auxiliary tank has approximate volume of 12,000 US gal.b. Main (wing) tanks each have an approximate volume of 6,070 US gal.

2. For B767 aircraft (N371 - N399):a. Center auxiliary tank has approximate volume of 11,900 US gal.b. Main (wing) tanks each have an approximate volume of 5,993 US gal.

C. Maximum fuel weight capacity will vary depending on fuel densityNOTE :

NOTE : Fuel trucks/tankers are not to be disconnected from a/c until all fueling discrepancies havebeen cleared.


WARNING: A. DO NOT OPERATE THE HF COMMUNICATION SYSTEM WHILE FUELINGTHE AIRPLANE. A FIRE OR AN EXPLOSION CAN OCCUR.

B. GROUND EQUIPMENT MUST NOT BE POSITIONED UNDER WING TIPSDURING FUELING OPERATION.

C. FUELING VEHICLEMUST BE PROPERLY BONDED TO AIRCRAFT BEFOREANY FUELING/DEFUELING OPERATION.

D. WHEN THERE IS AN INACCURATE/INOPERATIVE OR A SUSPICION OF AGAUGE NOT INDICATING PROPERLY, STOP FUELING AND NOTIFYAIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON.

E. NOTE: IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARD ASBEING INOPERATIVE, AIRCRAFT MAINTENANCE DOES NOT NEED TO BENOTIFIED UNLESS SPECIFIC PROCEDURES DURING FUELINGOPERATIONS REQUIRE THE ATTENTION OF AIRCRAFT MAINTENANCE.

F. IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION,NOTIFYAIRCRAFTMAINTENANCE IMMEDIATELY INPERSON.DO NOT START OR RESUME FUELING OPERATIONS UNTIL CORRECTIVEACTION HAS BEEN TAKEN.

G. DO NOT START OR SHUT DOWN APU SHOULD FUEL SPILL OCCUR.

D. Pressure Fueling1. Pressure fueling is accomplished through a single point fueling station. The fueling station consists

of 2 pressure fueling receptacles and control panel. The control panel is used for controlling andmonitoring the pressure fueling operation and contains fuel quantity indicators and switches.Refer to Figure 23.01-2.

2. Fuel flow through the pressure fueling receptacles (manifold) is directed to any or all fuel tanksdesired through electrically or manually operated fuel tank fill valves which are located on therear spar of each main wing tank.



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3. Access to the fueling station and control panel is through a hinged access door located on thelower surface of the left midwing leading edge, approximately 14-1/2 feet from ramp level. Referto Figure 23.01-2.


E. Gravity Fueling1. Overwing gravity fueling of the aircraft fuel tanks becomes necessary only when pressure fueling

facilities are not available. Overwing fill ports are located on top of the right and left main wingtanks. Refer to Figure 23.01-1. The center auxiliary tank can be filled by fuel transfer from themain wing tanks.

F. Fuel Quantity Measuring1. The primary measuring devices used in determining fuel quantity are the cockpit and underwing


2. An alternate means of determining fuel quantity may be obtained by the use of mechanicalmagnetic measuring sticks located on the bottom of the main wing and center auxiliary fuel tanks.Refer to Figure 23.01-7.



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Figure 23.01-1: Fuel Tank



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Figure 23.01-2: Left Wing Fueling Station Fueling Station and Control Panel


A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft (refer to Figure 23.01-3) for location of aircraft bonding point.



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Figure 23.01-3: Bonding Lug Location

NOTE : The bonding points are located on the nose landing gear and main landing gear bogieshield.

D. Open fueling control station access door. Electrical power for fueling will be automatically suppliedwhen fueling control station access door is in the fully extended position.NOTE : If electrical power is not available when the fueling control station access door is opened,

battery power may be obtained by positioning the POWER switch to the BATT position.Refer to Figure 23.01-2.

E. Remove pressure fueling receptacle cap.NOTE : Pressure fueling caps are required on all A/C N342 thru 350, and A/C N366 thru 399. If cap

is missing or inoperative, fueling receptacle must be placarded: "Fueler, if fuel cap ismissing, ensure receptacle is free of contamination before fueling, and no leaks areobserved after fueling."If fuel cap is missing and not placarded, or leakage is observedbefore and after fueling, notify Aircraft Maintenance in person or other agreeable method.

1. Position fueling receptacle to FUEL position. Refer to Figure 23.01-2.F. Connect fueling nozzle(s) to aircraft pressure fueling receptacle(s).

1. CAUTION: PRIOR TO APPLYING FUEL PRESSURE; ROTATE NOZZLE HANDLES TOTHELOCKEDPOSITIONANDOPENPOPPETACTIVATINGLEVER.ATTEMPTTO REMOVE NOZZLE. IF NOZZLE CAN BE REMOVED, IT IS DEFECTIVEAND MUST BE REMOVED FROM SERVICE.

G. Test LOAD SELECT INDICATORS by pressing IND TEST switch. "88.8" should appear on the upperand lower LCD displays. Refer to Figure 23.01-2.

H. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS." spaceson the fuel slip. Refer to Section 15.01.

I. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.

J. Press to test FUELING VALVE INDICATOR LIGHT. Verify each light illuminates when pressed. Referto Figure 23.01-2.

K. At the LOAD SELECTOR control, position thumbwheel switches to desired amount of fuel. Pressselected TANK LOAD SET switch, and hold for one second minimum. Repeat process for each tank.Refer to Figure 23.01-2.



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NOTE : a) The thumbwheel has only three (3) numbers to preselect desired amount of fuel per tank.As per Figure 23.01-4, the amount of fuel required for tanks 1 and 3 is 40,668. The numberson the thumbwheel should then be 40.7; x 1000 = 40,700 pounds.

b) If error is made during selection process, press applicable TANK LOAD SET switch andrepeat procedure.

L. Place applicable FUELING VALVE switches to the FUEL POSITION. The blue "valve open" indicatorlights will illuminate, indicating fueling valves will open when fuel pressure is applied. Refer toFigure 23.01-2.NOTE : a) It is desirable to fuel all tanks simultaneously.

b) If one or more fuel valves are electrically inoperable, refer to Section 23.01.4.

M. Start fueling operation by activating deadman control.N. Monitor applicable fuel quantity indicators.O. Press SYSTEM TEST button; fueling valves will close sequentially. Fueling valves will reopen and

fueling operation continues. Refer to Figure 23.01-2.P. Fueling valves will close automatically when the required pre-selected amount of fuel is obtained in

each tank.NOTE : Fueling valve will also close should a malfunction occur.

Q. When fueling valves close automatically, place applicable FUELING VALVE SWITCHES to OFFposition.

R. When operation is complete, stop fueling source by releasing deadman.S. Remove fueling nozzle(s).

1. Ensure fueling receptacle(s) are in FUEL position. Refer to Figure 23.01-2.T. Install pressure fueling receptacle cap.

NOTE : Pressure fueling caps are required on all A/C N342 thru 350, and A/C N366 thru 399. If capis missing or inoperative, fueling receptacle must be placarded: "Fueler, if fuel cap ismissing, ensure receptacle is free of contamination before fueling, and no leaks areobserved after fueling." If fuel cap is missing and not placarded, or leakage is observedbefore and after fueling, notify Aircraft Maintenance in person or other agreeable method.

U. Check that all FUELING VALVE switches are in THE OFF position, then close the fueling controlstation access door.

V. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.W. Disconnect aircraft and fueling vehicle bonding cable.


A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control station access door. Electrical power for fueling will be automatically supplied

when fueling control station access door is in the fully extended position.NOTE : If electrical power is not available when the fueling control station access door is opened,


E. Remove pressure fueling receptacle cap.



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F. Connect fueling nozzle(s) to aircraft pressure fueling receptacle(s).1. Prior to applying fuel pressure; rotate nozzle handles to the locked position and open poppet

activating lever. Attempt to remove nozzle. If nozzle can be removed, it is defective and must beremoved from service.

G. Test LOAD SELECT INDICATORS by pressing IND TEST switch. "88.8" should appear on the upperand lower LCD displays. Refer to Figure 23.01-2.


I. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.

J. Press to test FUELING VALVE INDICATOR LIGHT. Verify each light illuminates when pressed. Referto Figure 23.01-2.

K. Place applicable FUELING VALVE switches to the FUEL position. The blue "valve open" indicatorlights will illuminate, indicating fueling valves will open when fuel pressure is applied. Refer toFigure 23.01-2.

L. Start fueling operation by activating deadman control.NOTE : If one or more fueling valves are electrically inoperable, refer to Section 23.01.4.

M. Monitor applicable fuel quantity indicators.NOTE : Use caution when reaching maximum capacity of each respective tank to avoid overfilling

the tank resulting in a fuel spill.

N. Place applicable FUELING VALVE switch to the OFF position when desired amount of fuel is obtainedin each respective tank. Verify that the blue FUELING VALVE indicator lights extinguish.

O. When operation is complete, stop fueling source by releasing deadman.P. Remove fueling nozzle(s).Q. Install pressure fueling receptacle cap.

NOTE : Pressure fueling caps are required all A/C N342 thru 350, and A/C N366 thru 399. If cap ismissing or inoperative, fueling receptacle must be placarded: "Fueler, if fuel cap ismissing,ensure receptacle is free of contamination before fueling, and no leaks are observedafter fueling." If fuel cap is missing and not placarded, or leakage is observed before andafter fueling, notify Aircraft Maintenance in person or other agreeable method.

R. Check that all FUELING VALVE switches are in the OFF position, then close the fueling control stationaccess door.

S. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.T. Disconnect aircraft and fueling vehicle bonding cable.


CAUTION: NO AUTOMATIC SHUTDOWN OR OVERFILL PROTECTION EXISTS WITHOUTELECTRICAL POWER.

DO NOT USE FUELING VALVES MANUALLY TO REDUCE OR STOP FUELING.



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A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control station access door.E. Remove pressure fueling receptacle cap.


1. Place fueling receptacle to FUEL position. Refer to Figure 23.01-2.F. Connect fueling nozzle(s) to aircraft pressure-fueling receptacle(s).

1. Prior to apply fuel pressure; rotate nozzle handles to the lock position and open poppet actuatinglever. Attempt to remove nozzle. If nozzle can be removed, it is defective and must be removedfrom service.

G. Use magnetic measuring sticks to determine fuel quantity in each tank before fueling. Refer to Section15.01.NOTE : Aircraft must be level (wings 0 degrees and nose 0 degrees) to obtain accurate fuel tank



I. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.WARNING: PRIORTOGAININGACCESSTOFUELINGVALVES, ENSURETHATAPPLICABLE

LANDING ANDWINGGEAR DOOR LOCKS ARE INSTALLED. RAPID ACTION OFDOORS MAY CAUSE INJURY OR DAMAGE IF LOCKS ARE NOT INSTALLED.(FORAAAIRCRAFT, REFERENCESECTION32-00-15OFTHEAAMAINTENANCEMANUAL.

J. Manually open applicable fueling valve(s). Refer to Figure 23.01-4.1. Verify fueling manifold is not pressurized.2. Remove lockwire from knurled knob of fuel valve override screw.3. Rotate override screw 10-13 complete revolutions in counterclockwise direction.

NOTE : Pliers may be required to initially loosen override screw.

K. Start fueling operation by activating deadman control.L. Monitor magnetic measuring sticks carefully during the fueling process. Refer to Figure 23.01-7.

CAUTION: WITHOUT ELECTRICAL POWER DURING FUELING PROCESS AND FUELINGVALVE(S) MANUALLY OPENED, THERE IS NO ELECTRICAL PROTECTION TOPREVENT OVERFILL FUEL SPILLS.

M. Stop fueling operation, through manually opened fuel valve(s), when desired amount of fuel is obtainedin each respective fuel tank by releasing deadman.

N. Verify fuel tank quantity by use of magnetic measuring sticks. Refer to Section 23.01.8 and Section23.01.9.NOTE : Aircraft must be level (wings 0 degrees and nose 0 degrees) to obtain accurate fuel tank




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WARNING: PRIORTOGAININGACCESSTOFUELINGVALVES, ENSURETHATAPPLICABLELANDING ANDWINGGEAR DOOR LOCKS ARE INSTALLED. RAPID ACTION OFDOORS MAY CAUSE INJURY OR DAMAGE IF LOCKS ARE NOT INSTALLED.(FORAAAIRCRAFT, REFERENCESECTION32-00-15OFTHEAAMAINTENANCEMANUAL.

O. Manually close applicable fueling valve(s). Refer to Figure 23.01-4.1. Verify fueling manifold is not pressurized.2. Rotate override screw 10-13 complete revolutions in clockwise direction.3. Ensure knurled knob of fuel valve(s) override screw is lockwired in place.

P. Remove fueling nozzle(s).Q. Install pressure fueling receptacle cap.


R. Close fueling station control access panel.S. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.

NOTE : Ensure the completed fuel slip is correctly filled out and legible.

T. Disconnect aircraft and fueling vehicle bonding cables.U. Install applicable fueling valve access panels. Refer to Figure 23.01-4.V. Remove applicable landing and wing gear door locks.

23.01.5 Overwing (Gravity) Fueling

NOTE : Overwing fueling is considered an emergency fueling method, and shall be used only when thefollowing conditions exist:1. No underwing (pressure) fueling vehicles available2. Aircraft underwing (pressure fuel system) components malfunctioning3. Other emergencies, as recognized by station management

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control station access door. Electrical power for fueling will be automatically supplied

when fueling control station access door is in the fully extended position.NOTE : If electrical power is not available when the fueling control station access door is opened,


E. Test LOAD SELECT INDICATORS by pressing IND TEST switch. "88.8" should appear on the upperand lower LCD displays. Refer to Figure 23.01-2.

F. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS." spaceson the fuel slip. Section 15.01.

G. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.



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NOTE : Main wing tanks may be fueled by the overwing (gravity method only). The center auxiliarytank can be filled by fuel transfer from the main wing tanks. Refer to Section 23.01.5 forfuel transfer procedures.

H. Use suitable lift device or ladder to gain access to main wing tank overwing fill port(s). Refer toFigure 23.01-5.

I. Place maintenance mats on the wing where service personnel must walk.J. Connect fueling nozzle grounding plug to overwing fill grounding receptacle.K. Remove overwing filler cap for tank to be fueled and insert fueling nozzle. Slowly open fueling nozzle

valve. Start fueling.CAUTION: DO NOT EXCEED MAXIMUM ALLOWABLE FUELING RATE OF 155 GPM.

L. If the center auxiliary tank requires fuel, transfer fuel from main wing tank(s) that is being overwing(gravity) fueled. Refer to Section 23.01.5 for fuel transfer procedures.

M. Monitor applicable fuel quantity indicators.N. After fuel transfer is complete, top-off main wing tank(s) to desired fuel quantity.

CAUTION: USE EXTREME CAUTION WHEN REACHING MAXIMUM CAPACITY FOR MAINWINGTANKS TOAVOIDOVERFILLING THE TANKRESULTING IN A FUEL SPILL.

O. When fueling is complete, stop fueling source.P. Remove fueling nozzle. Disconnect nozzle grounding plug.Q. Install and lock fill adapter cap(s).R. Remove maintenance mats.S. If fuel transfer was accomplished, ensure the center auxiliary tank FUELING VALVE switch is in the

OFF position. Close fueling control station access door.T. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.U. Disconnect aircraft and fueling vehicle bonding cable.



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Figure 23.01-4: Fueling Valve - Manual Operation



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Figure 23.01-5: Overwing (Gravity) Fueling


A. Ground transfer of fuel is accomplished by following the basic procedure used for defueling (refer toSection 23.01.10), and using the components used for pressure fueling. The fueling manifold ispressurized by fuel tank boost pumps and fueling valve(s) in the tank(s) selected to receive fuel isopened.NOTE : The following operational procedures may be used when required, during the overwing

(gravity) fueling method. Tank-to-tank fuel load adjustments may also be accomplished bythe following procedures.



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NOTE : A/C N335 thru N399, are not equipped with a center aux tank defuel valve switch. Refer toFigure 23.01-6.

B. To transfer fuel from the right main wing tank to the left main wing tank. Refer to Figure 23.01-6:1. Place left main tank FUELING VALVE switch to the FUEL position.2. Place right main tank DEFUEL VALVE switch to the OPEN position.3. Place right main tank boost pump switch(es) (cockpit) to the ON position.4. Monitor applicable fuel quantity indicators and place right main tank boost pump switch(s) to OFF

when desired fuel quantity is obtained.5. Place right main tank DEFUEL VALVE switch to the CLOSED position. Place left main tank

FUELING VALVE switch to the OFF position.6. Top-off right main wing tank if required.

C. To transfer fuel from the left main wing tank to the right main wing tank. Refer to Figure 23.01-6:1. Place right main tank FUELING VALVE switch to the FUEL position.2. Place left main tank DEFUEL VALVE switch to the OPEN position.3. Place left main tank boost pump switch(es) (cockpit) to the ON position.4. Monitor applicable fuel quantity indicators and place left main tank boost pump switch(es) to OFF

when desired fuel quantity is obtained.5. Place left main tank DEFUEL VALVE switch to the CLOSED position. Place right main tank

FUELING VALVE switch to the OFF position.6. Top-off left main wing tank if required.

D. To transfer fuel from the right and/or left wing tank(s) to the center auxiliary tank. Refer toFigure 23.01-6):1. Place center auxiliary tank FUELING VALVE switch to the FUEL position.2. Place right and/or left main tank(s) DEFUEL VALVE switch(es) to the OPEN position.3. Place right and/or left main tank(s) boost pump switch(es) cockpit) to the ON position.4. Monitor applicable fuel quantity indicators and place right and/or left main tank boost pump

switch(es) to OFF when desired fuel quantity is obtained.5. Place right and/or left main tank DEFUEL VALVE switch(es) to the CLOSED position. Place

center auxiliary tank FUELING VALVE switch to the OFF position.6. Top-off right and/or left main wing tanks if required.

E. To transfer fuel from the center auxiliary tank to the right and/or left main wing tank(s). Refer toFigure 23.01-6):1. Place right and/or left main tank(s) FUELING VALVE switch(es) to the FUEL position.2. Place right and/or left main tank(s) DEFUEL VALVE switch(es) to the OPEN position.3. Place center auxiliary tank boost pump switch(es) (cockpit) to the ON position.4. Monitor applicable fuel quantity indicators and place center auxiliary tank boost pump switch(es)

to OFF when desired fuel quantity is obtained.5. Place right and/or left wing tank(s) DEFUEL VALVE switch(es) to the CLOSED position; place

FUELING VALVE switch(es) to the OFF position.6. Top-off center auxiliary tank if required.

F. On completion of fuel transfer, check that all tank boost pumps are OFF in the cockpit.G. Ensure that all FUELINGVALVE switches are OFF and the DEFUELINGVALVE switches are CLOSED;

close fueling control station access door.



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Figure 23.01-6: Cockpit and Underwing Fueling Controls



underwing panel quantity indicator. Refer to Section 15.01.NOTE : (1) Should the flight deck fuel quantity display be inoperative, its respective underwing

panel quantity indicator may be used to determine fuel tank quantity. Verificationof fuel quantity, by measuring stick, is not required with Method 1. Use of Method



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1 will be noted on the fuel slip in the remarks field, with a copy of the fuel slipprovided to the Flight Crew as early as practicable after fueling.

(2) When an inoperative fuel tank quantity indication channel exists, the total fuelquantity in all tanks containing fuel must be verified by using measuring sticksafter refueling. The stick readings must also agree with the fuel tank quantityindicators. Method 3 shall be used in these instances with the actual before quantitytank gauge readings recorded in lieu of zero (0) for each respective tank on aseparate Inoperative Fuel Quantity Indicator service record.

B. Method 2 - For use on main tanks (wings) and center tank when the flight deck fuel quantity displayis inoperative, one or more of the underwing panel fuel quantity displays are inoperative, and fuel onboard can be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.1. Determine if aircraft is within the limits of -2.00° to +2.00° pitch and roll. The aircraft must be

within these limits of pitch and roll in order to use the fuel measuring sticks.. Assistance fromAircraft Maintenance personnel must be requested to make this determination.a. Each airplane has a leveling scale and a plumb bob that can hang in the left main wheel

well. The airplane attitude is found by the position of the plumb bob above the leveling scale.The fore and aft scale is used for pitch and the side to side scale is for roll. Refer toFigure 23.01-7.

b. Also in the left main wheel well are bubble type inclinometers. The longitudinal inclinometermeasures the airplane pitch. The lateral inclinometer measures the airplane roll for the leftwing. The airplane roll for the right wing will be the opposite of the quantity measured for theleft wing. Refer to Figure 23.01-8.



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Figure 23.01-7: Leveling Scale

2. Before fueling, determine existing fuel tank quantity with the measuring stick of the affected tank.Subtract this quantity from the tank quantity required and convert to gallons. Fuel the tank todesired level, using the truck meter. Use measuring stick(s) to verify tank quantity. Refer to Section23.01.9.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to gallons,

Reference Section 15.01.7, to deliver the desired known quantity.

3. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity Indicatorservice record ensuring all required entries and signatures are legible and in place as early aspracticable, before departure.



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Figure 23.01-8: Inclinometer

C. Method 3 - For use on main tanks (wings) and center tank when the flight deck fuel quantity displayis inoperative, one or two of the underwing panel fuel quantity displays are inoperative, and fuel onboard cannot be determined using fuel measuring sticks both before and after the refueling operation.Refer to Section 15.01.1. Completely defuel tank with the inoperative indicator by transferring fuel to other tank(s). Refer

to Section 23.01.6.2. Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged by the fuel

vehicle meter reading. Alternately, transfer required fuel from tank(s) with operative indicator.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to gallons, Refer


3. Fill tank(s) with operative indicator to quantity of fuel required.NOTE : Use of Method 3 requires final verification by measuring stick. Refer to Section 23.01.9.



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4. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity Indicatorservice record. Make sure all required entries and signatures are legible and in place as early aspracticable, before departure. Refer to Section 15.01.



B. Each main wing tank contains 7 fuel measuring sticks located on the lower wing surface. The centeraux tank contains 2 fuel measuring sticks, 1 stick located in each aux tank half. Refer to Figure 23.01-7.

C. The measuring sticks are the magnetic dripless-type, consisting of a mounting, a tube housing, aninner tube (indicator stick) graduated in inches for determining fuel tank quantity, and a circular float.The float is installed on the tube housing and is free to move up and down with the fuel level in thetank. Refer to Figure 23.01-7. Then the fuel level stick tip is magnetically coupled to the circular float,the stick is positioned relative to the fuel level in the tank.

D. Fuel quantities quoted in the fuel quantity charts are based on fuel with a density of 6.7 pounds perU.S. Gallon. Use the Verification Charts to convert from inches to pounds.NOTE : When actual fuel density deviates greatly from the nominal chart value of 6.70 pounds per


E. The stick is unlocked (released) or locked (stowed) by depressing the stick latch and turning the latch90 degrees in either direction. A flat-bit screwdriver can be used to depress and turn the latch. Theoperating procedures for all sticks are identical.

F. During fueling, the measuring stick(s) may remain extended as the float rises with the fuel in the tank,the graduated stick in inches can be read as the float carries the stick up into the tank.



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A. Any time fuel quantity is determined by measuring stick, this procedure must be used:1. Determine the method, 2 or 3, (Refer to Section 23.01.7) to be used to fuel the aircraft and check



determine the pounds in the affected tank.



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(2) Record the before fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (for example L,






Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner/ outer cell















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(5) Record the after fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) & applicable inner/outer cell





23.01.10 Defueling


A. The aircraft fuel system is designed to permit partial or complete defueling of any or all tanks. Portionsof the pressure fueling and engine fuel feed systems are used for defueling operations.


tanks when adjusting fuel loads. This method is accomplished using the fuel truck suction pumpto withdraw fuel from the tanks through the tank fill lines and fueling valves. Only partial defuelingcan be accomplished by this method.

2. Defueling by the boost pump pressure method can be used for partial or complete defueling ofany or all tanks. This method is faster than suction defueling, and is accomplished by using therespective center aux and/or wing tank fuel boost pumps to pump fuel from the tanks and intothe defueling line. Fuel truck suction can be used during the method to increase the defuelingflow rate. Any residual fuel remaining in the tanks after completely defueling can be drainedthrough the tanks sump drain valves.

C. Suction Method (Partial Defueling)WARNING: DO NOT OPERATE RADIO, RADAR OR ANY OTHER

ELECTRICAL/ELECTRONICS EQUIPMENT ON AIRCRAFT EXCEPT ASSPECIFIED.

A)

B) DEFUELING VEHICLESMUST BE PROPERLY BONDED TO THE AIRCRAFTBEFORE ANY DEFUELING OPERATION.

CAUTION: DO NOT OPERATE HYDRAULIC SYSTEM IF FUEL IN EITHER MAIN TANK ISLESS THAN 600 US GALLONS.

NOTE : For A/C N335 thru N399 only: The center aux tank cannot be defueled by the suctionmethod.

a)



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b) External or APU electrical power should be used for defueling operations. If externalor APU power sources are not available, the airplane battery may be used as a powersource.

1. Position the defueling vehicle.2. Bond the defueling vehicle to the aircraft.3. Open fueling control station access door. Electrical power for defueling will be automatically

supplied when fueling control station access door is in the fully extended position.4. Position fueling receptacle(s) to DEFUEL mode.5. Remove pressure fueling receptacle cap.

NOTE : Pressure fueling cap required for departure on all aircraft A/C N342 thru 350, and A/CN366 thru 399.

6. Connect hose nozzle(s) to fueling receptacle(s); open nozzle valve.NOTE : Place a monitor by the dome cover access to ensure tanker DOES NOT overfill.

7. Test "LOAD SELECT INDICATORS" by pressing TEST IND switch; 88.8 shall appear on upperand lower LCD displays.

8. Test DEFUELING VALVE indicator lights by press-to-test.9. Set DEFUELINGVALVE switch(es) to open. The blue "valve open " indicator light should illuminate.

NOTE : A/C N335 thru N399 are not equipped with a center aux tank defuel valve switch. Referto Figure 23.01-6.

10. Start defueling truck suction pump.11. Monitor applicable fuel quantity indicators.12. Position DEFUEL VALVE switch(es) to CLOSE when the desired amount of fuel is obtained in

each respective tank. Verify corresponding DEFUEL VALVE position indicator light extinguishes.13. Stop defueling truck suction pump immediately.14. Close defueling nozzle valve; remove nozzle.

a. Ensure fueling receptacle is in FUEL position. Refer to Figure 23.01-2.15. Install pressure fueling receptacle cap.

NOTE : Pressure fueling cap required for departure on all A/C N342 thru 350, and A/C N366thru 399.

16. Close fueling control station access door.NOTE : Close and lock the tanker unit dome cover.

17. Disconnect defueling vehicle and aircraft bonding cable.D. Pressure Defueling (Partial or Complete Defueling)

WARNING: DO NOT OPERATE RADIO, RADAR, OR ANY OTHERELECTRICAL/ELECTRONICS EQUIPMENT ON AIRCRAFT EXCEPT ASSPECIFIED.

A)

B) DEFUELING UNIT MUST BE PROPERLY GROUNDED AND AIRCRAFTPROPERLY BONDED BEFORE ANY DEFUELING OPERATION.

CAUTION: DO NOT OPERATE HYDRAULIC SYSTEM IF FUEL IN EITHER TANK IS LESSTHAN 600 U.S. GALLONS.




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1. Position the defueling vehicle.2. Bond the defueling vehicle to the aircraft.3. Open fueling control access door. Electrical power for defueling will be automatically supplied

when fueling control station access door is in fully extended position.4. Position fueling receptacle(s); to DEFUEL mode.5. Remove pressure fueling receptacle cap.


6. Connect hose nozzle(s) to fueling receptacle(s); open nozzle valve.NOTE : Place a monitor by the dome cover access to ensure tanker DOES NOT overfill.

7. Test "LOAD SELECT INDICATOR" by pressing TEST IND switch. "88.8" shall appear on upperand lower LCD displays.

8. Test DEFUELING VALVE indicator lights by press-to-test.9. Set DEFUELINGVALVE switch(es) to open. The blue "valve open" indicator light should illuminate.

NOTE : A/C N335 thru N399 are not equipped with a center aux tank defuel valve switch. Referto Figure 23.01-6.

10. For tanks to be defueled, place respective fuel boost pump switches (cockpit) to ON position.Refer to Figure 23.01-6.NOTE : All fuel tanks can be defueled individually or simultaneously as required.

11. To expedite the defueling process, start fuel truck defueling pump.12. Monitor applicable fuel quantity indicators and continue defueling until desired fuel quantity

remains.13. Stop fuel truck defueling pump just prior to desired fuel tank(s) quantity.14. Place applicable fuel boost pump switches to OFF position, when desired defueling of each tank

is accomplished.15. Position DEFUEL VALVE switch(s) to CLOSE. Verify corresponding DEFUEL VALVE position

indicator light extinguishes.16. Close defueling nozzle valve(s); remove nozzle(s).

a. Place fueling adapter back to FUEL position. Refer to Figure 23.01-2.17. Install pressure fueling receptacle cap.


18. Close fueling control station access door.NOTE : Close and lock the tanker unit dome cover.

19. If complete defueling was accomplished, drain applicable fuel tank sumps.20. Disconnect aircraft and fueling vehicle bonding cable.

END



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Section 23.02 - B767 Fuel Distribution Guides (FDG) and QuantityVerification Charts (QVG)

23.02.1 General


END

Section 23.02B767 Fuel Distribution Guides (FDG) and QuantityVerification Charts (QVG)


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Table of contents

24.01 FUELING MANUAL - B777-200GENERAL..........................................................................................................................1PRESSURE REFUELING - WITH A SET FUEL QUANTITY (AUTOMATIC) (REFER TOFIGURE 24.01-1 AND FIGURE 24.01-2)...........................................................................2PRESSURE REFUELING - WITH NO SET FUEL QUANTITY.......................................10PRESSURE REFUELING - WITH INOPERATIVE REFUEL VALVES............................12PRESSUREREFUELING -WITH AN INOPERATIVE FUELQUANTITYDISPLAY (REFERTO FIGURE 24.01-2).......................................................................................................17DEFUELING....................................................................................................................20

24.02 FUEL SUMP - OPERATIONGENERAL..........................................................................................................................1

24.03 FUEL QUANTITY MEASURING STICK - SERVICINGGENERAL..........................................................................................................................1FIND THE FUEL QUANTITY (REFER TO FIGURE 24.01-1)............................................2DETERMINING FUEL QUANTITY BY MEASURING STICK..........................................10FUEL MEASURING STICK CHARTS..............................................................................12

TOCFueling Manual - B777-200


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Section 24.01 - Fueling Manual - B777-20024.01.1 General


WARNING: DO NOT OPERATE THE HF COMMUNICATION SYSTEM DURING REFUELINGOPERATIONS. A FIRE OR EXPLOSION CAN OCCUR.

1.

2. GROUNDEQUIPMENTMUSTNOTBEPOSITIONEDUNDERWINGTIPSDURINGFUELING OPERATION.

3. FUELINGVEHICLEMUSTBEPROPERLYBONDEDTOAIRCRAFTBEFOREANYFUELING/DEFUELING OPERATION.

4. WHENTHERE ISAN INACCURATE/INOPERATIVEORASUSPICIONOFAGAUGENOT INDICATING PROPERLY, STOP FUELING AND NOTIFY AIRCRAFTMAINTENANCE IMMEDIATELY.

NOTE: IF A FUEL COMPONENT(S) IS CURRENTLY ON MINIMUM EQUIPMENTLIST (MEL) PLACARD AS BEING INOPERATIVE, AIRCRAFT MAINTENANCEDOESNOTNEEDTOBENOTIFIED, UNLESSSPECIFICPROCEDURESDURINGFUELING OPERATIONS REQUIRE THE ATTENTION OF AIRCRAFTMAINTENANCE IMMEDIATELY IN PERSON.

5. IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION, NOTIFY AIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON.DO NOT START OR RESUME FUELING OPERATIONS UNTIL CORRECTIVEACTION HAS BEEN TAKEN.

6. DO NOT START OR SHUT DOWN APU SHOULD A FUEL SPILL OCCUR.

CAUTION: DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUEL NOZZLE. IFYOU USE MORE THAN 50 PSI FUEL PRESSURE, YOU CAN CAUSE DAMAGE TOTHE REFUELING SYSTEM COMPONENTS.

DO NOT REMOVE ELECTRICAL POWER WHILE REFUELING. IF YOU REMOVEELECTRICAL POWER WHILE REFUELING, THE REFUELING VALVES WILL CLOSEAND CAN DAMAGE EQUIPMENT.

A. Refueling Station:1. The refueling stations are installed in the leading edge, just outboard of each engine.2. The left refueling station contains refuel adapters, bonding points, lights, an interphone jack, and

an integrated refuel panel (IRP).3. The right refueling station contains refuel adapter, bonding points, lights, and an interphone jack.4. Aluminum foil placards installed on the refueling station door have refueling information and

cautions.B. Surge tank overfill system:

1. There is a surge tank overfill system to catch fuel from the fuel tanks that are more than full andprevent fuel spills onto the ground. If the surge tank overfill system does not operate correctlyand there is a fuel spill at the wing tip, stop the pressure refueling source immediately to keepthe fire hazard to a minimum.

C. Fuel loading limits:1. The fuel system has two main tanks and one center tank. There is also a vent surge tank located

in each wing, outboard of the wing tank.a. For all B777-200 aircraft:

Section 24.01Fueling Manual - B777-200


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(1) Center tank has an approximate volume of 26,100 US gal.(2) Main (wing) tanks each have an approximate volume of 9,560 US gal.


NOTE : A STOP indication can show in a LOAD SELECT window on the IRP for agiven tank This means that the Volumetric Shutoff (VSO) has been exceededby 100 gallons or more. The refueler should stop refueling. The STOPindication will remain until the quantity in the tank is reduced to the VSO levelor below the VSO level for that tank.

NOTE : The FQPU can command the refuel valves to the closed position if there is aconfirming or confirmed tank unit failure. The fuel quantity processor unit(FQPU) software will reduce the shutoff level to 3.2% below VSO. If the FQPUcommands early shutoff in one main tank, then there will be a fuel imbalanceof approximately 2000 to 2200 LB (1000 to 1100 KG) between the left andright main fuel tanks.

2. You can refuel all the tanks at the same time or in sequence.NOTE : The usual procedure for refueling the center tank is to put fuel in the center tank if the

left and right main tanks will be filled to capacity.

3. Refuel the left and right main tanks with equal quantities of fuel.

24.01.2 Pressure Refueling - With A Set Fuel Quantity (Automatic) (Refer to Figure 24.01-1 andFigure 24.01-2)

A. General1. The fuel quantity to be loaded is entered in the LOAD SELECT QTY control and will show on the

LOAD SEL display when you push the LOAD SELECT SET switch. During pressure refuelingwith a SET fuel quantity in the LOAD SEL display, the FQIS operates with the pressure refuelingsystem. The FQPU closes the refuel valves when the SET fuel quantity is the same as the FQISfuel quantity.NOTE : (1) The refueling operator can operate the refuel valve control switches at the

integrated refuel panel (IRP) to stop the refuel operation.(2) With a LOADSELECTQTY entered for each main tank, the FQIS will automatically

keep the main tank fuel level balanced during the refuel operation. If the quantityof one main tank becomes 1000 LB more than the other main tank, one refuelvalve for the tank with the higher quantity will be closed. When the main tankquantities become equal, the valve will open.

2. The total fuel quantity is the sum of all the fuel tanks. If the total quantity selected is more thanthe main fuel tanks capacity, the main tanks will fill to full and the center fuel tank will fill with theremaining fuel. All fuel tanks are filled with fuel at the same time. If the center tank fills to its LOADSELECT value before the main tanks reach VSO, the center tank refuel valves will close. At thispoint the LOAD SELECT values for the three tanks will be updated and the center tank refuelvalves will reopen and fueling will continue to the updated LOAD SELECT value.

3. The examples below will show the final tank values for TOTAL LOAD SELECT quantities of12,600 LB, 15,000 LB, 90,100 LB and 132,500 LB.a. TOTAL LOAD SELECT = 12,600 LB)

NOTE : Left main tank load selects = 6,300 LB

Right main tank load selects = 6,300 LB



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Center load select = 0.0

b. TOTAL LOAD SELECT = 15,000 LBNOTE : Left main tank load selects = 7,500 LB



c. TOTAL LOAD SELECT = 90,100 LBNOTE : Left main tank load selects = 45,100 LB



Notice that the odd 100 LB of fuel was put in the left tank.

d. TOTAL LOAD SELECT = 132,500 LBNOTE : Left main tank load selects = 66,300 LB



e. For the first three totals, the load select values are never recalculated since 95% of maintank VSO is never reached. For the last total, at 95% of main tank VSO, assuming the averagedensity is 6.78 lb/gal, the load select values are recalculated. The left and right main loadselects will change to 63,000 LB, and the center load select will change to 6,500 LB. Duringrecalculation at 95% VSO the refueling valves will close then reopen. Also, the aboveexamples assume that the center tank quantity starts at zero. If there is fuel in the centertank before you do the TOTAL LOAD SELECT the center tank quantity of fuel will be usedto determine the final main tank quantities. For example:

MAIN TANK LOAD SELECT = (TOTAL LOAD SELECT - CENTER QUANTITY) / 2B. Procedure

WARNING: DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TOTHE AIRPLANE DURING ATMOSPHERIC ELECTRICAL ACTIVITY OR

A)

STRONGRADIOACTIVEFIELDS. LIGHTINGSTRIKEANDHIGHDISCHARGECURRENTS CAN CAUSE SEVERE INJURY.

B) DONOTOPERATE THEHFCOMMUNICATION SYSTEMOR THEWEATHERRADAR DURING REFUELING OPERATIONS. A FIRE OR EXPLOSION CANOCCUR.

C) DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION THE FUEL TANKS ARE VENTED THROUGH THEWINGTIPS, A DANGEROUS AND EXPLOSIVE MIXTURE AROUND THEWINGTIP CAN OCCUR.

D) DO NOT START OR SHUT DOWN APU SHOULD A FUEL SPILL OCCUR.E) DO NOT OPERATE THE LEADING EDGE SLATS. ACCIDENTAL SLAT

OPERATION COULD CAUSE DAMAGE TO EQUIPMENT AND INJURY TOPERSONS.

F) ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. BONDING CABLES ATTACHED TO COMPOSITE DOORS OFFAIRINGS DO NOT GIVE AN ELECTRICAL BOND.



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CAUTION: DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUEL NOZZLE.IF YOU USEMORE THAN 50 PSI FUEL PRESSURE, YOU CAN CAUSE DAMAGETO THE REFUELING SYSTEM COMPONENTS.

DO NOT REMOVE ELECTRICAL POWERWHILE REFUELING. IF YOU REMOVEELECTRICAL POWER WHILE REFUELING, THE REFUELING VALVES WILLCLOSE AND CAN DAMAGE EQUIPMENT.


Figure 24.01-1: Left Wing Pressure Refueling Panel



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Figure 24.01-2: Left Wing Pressure Refueling Panel - Detail



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Figure 24.01-3: Right Wing Pressure Refueling Station



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Figure 24.01-4: Bonding Point Locations

2. Connect a bonding cable from the fueling source to an approved electrical grounding or bondingconnection on the airplane. Refer to Figure 24.01-4.

3. Open the Refueling Station Door, (refer to Figure 24.01-1), installed on the left wing.4. Open the Refueling station Door, (refer to Figure 24.01-3), installed on the right wing, if it is

necessary.



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WARNING: YOU MUST BOND THE AIRPLANE TO THE REFUELING SOURCECORRECTLY BEFORE YOU REFUEL THE AIRPLANE. THE RELEASE OFSTATIC ELECTRICITY CAN CAUSE A FIRE OR EXPLOSION.

5. Connect the refuel nozzles to one or more of the refuel adapters.a. Place the REFUEL/DEFUEL handle of the fueling adapter to the "REFUEL" position.


6. Make sure the fuel quantity displays are on.a. The FUEL QTY displays will come on within 60 seconds after you open the refueling station

door. Refer to Figure 24.01-2.b. If the FUEL QTY display(s) does not show the fuel quantity, put the POWER switch on the

IRP to the BATT position.c. Make sure the FUEL QTY display(s) show the fuel quantity.d. If one or more of the FUEL QTY displays continue to be off, do the "Pressure Refueling -

With an Inoperative Fuel Quantity Display Manual" procedure.NOTE : Make sure the total fuel legend TF shows on the TOTAL/BACKUP display. This

shows there is 28V DC at the IRP.

(1) If the total fuel legend "TF" is not on or the refueling station door lights do not come on,do the "Pressure Refueling - With an Inoperative Refuel Valve" procedure to open therefuel valves.

7. Push the TEST IND switch to do a test of the fuel quantity indicators and the blue valve positionlights.

8. During the test, a test pattern shows in the fuel quantity indicators, and the valve position indicationlights come on. If a fuel quantity indicator fails the test, all of its LEDs go off.

9. Make sure each blue valve position light comes on and then goes off.a. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY

REQUIRED - LBS." Refer to Section 15.01.10. To set the fuel quantity for each fuel tank you are to refuel, do the steps that follows:

a. At the LOAD SELECT QTY, set the thumbwheel switches to the necessary quantity of fuel.b. Push the LOAD SELECT SET switch for the applicable fuel tank for 1 second and release.c. Make sure the quantity input into the LOAD SELECT QTY shows on the LOAD SEL display

for the applicable fuel tank.(1) If you make an error during the selection procedure, push the applicable LOADSELECT

SET switch to remove the value from the LOAD SEL display and do the procedure again.11. To set the TOTAL fuel quantity (refer to Figure 24.01-2) that you are to refuel, do the steps that

follow:a. At the LOAD SELECT QTY, set the thumbwheel switches to the necessary quantity of fuel.b. Make sure the TOTAL/BACKUP display on the IRP is set to show the total fuel quantity.c. Push the LOAD SELECT SET switch for the total fuel indicator for 1 second and release.d. Make sure the fuel quantity on the LOAD SELECT QTY shows on the LOAD SEL display

for the TOTAL/BACKUP display.(1) If you make an error during the selection procedure, push the applicable LOAD SELECT

SET switch to remove the value and do the procedure again.



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12. Record FUEL QUANTITY in each tank in the GAUGE READING BEFORE FUELING - LBSspaces on the Jet Fuel Service Record (fuel slip). Refer to Section 15.01.

13. Start the fueling source.14. To open the refuel valves, do the steps that follow:

a. Put the applicable refuel valve switches to the OPEN position (refer to Figure 24.01-2).NOTE : The FQIS processor controls the start of refueling. The refuel valves will close

automatically when:● The fuel quantity equals the set fuel quantity● The fuel tank is full● The fuel spills into a surge tank.● During recalculation at 95% VSO the refuel valves will close and reopen.● If you put a refuel valve control switch to the CLOSE position during automatic

refueling, the pressure refueling operation stops for that fuel tank.

b. Make sure the applicable blue refuel valve lights come on.(1) If the refuel valve lights do not stay on, refer to the Pressure Refueling - With an

Inoperative Refuel Valve procedure.15. Monitor the fuel quantity on the FUEL QTY displays, on the IRP.16. If the message PUSH SET shows on the FUEL QTY display, the refuel operation will stop.

a. Do the "Pressure Refueling - With An Inoperative Fuel Quantity Display Manual" procedureto continue refueling the applicable fuel tank.

b. Do an Overfill Test:(1) Apply fueling pressure.(2) Push the OVERFILL TEST switch on the IRP, P18 (refer to Figure 24.01-2).(3) Make sure the refuel valve lights go off.

NOTE : This shows that the refuel valves are closed.

(4) Set the OVERFILL RESET switch to the RESET position on the IRP, P18.(5) Set the OVERFILL RESET switch to the NORMAL position on the IRP, P18.(6) Make sure the refuel valve lights come on.

NOTE : This shows that the refuel valves are open.

17. Set the refuel valve switches for all the applicable tanks to the CLOSE position when refuelingis complete.NOTE : The FQIS system will automatically close the refuel valve when the fuel quantity in the

tank is the same as the set fuel quantity (or the fuel tank is full).

18. Stop the fueling source.19. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.20. Disconnect the fueling nozzles.21. Disconnect the bonding cable.22. If the power switch is in the BATT position, put the power switch to the NORMAL position.23. Close the left refueling station door.24. Close the right refueling station door, if it is open.



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24.01.3 Pressure Refueling - With No SET Fuel Quantity

A. General1. This procedure does not set the fuel quantity to be put on the airplane. The automatic fuel shutoff

control will close each refuel valve when the fuel tanks are full. To stop refueling at a specific fuelquantity shown on the FUEL QTY display, put the REFUEL VALVE CONTROL to the CLOSEposition. The LOAD SEL display will be off.NOTE : You do not have to open the refuel valves manually on the rear spar for this procedure.

B. ProcedureWARNING: DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TO

THE AIRPLANE DURING ATMOSPHERIC ELECTRICAL ACTIVITY ORA)



C) DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. THE WEIGHT OF THE FUEL WILL CAUSE THEWINGSTOMOVEDOWNANDTHEWINGTIPSMOVETHEMOST. BECAUSETHEFUELTANKSAREVENTEDTHROUGHTHEWINGTIPS, ADANGEROUSAND EXPLOSIVE MIXTURE AROUND THE WINGTIP CAN OCCUR.

D) DO NOT START OR SHUT DOWN APU SHOULD A FUEL SPILL OCCUR.E) DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUEL

NOZZLE. IF YOU USE MORE THAN 50 PSI FUEL PRESSURE, YOU CANCAUSE DAMAGE TO THE REFUELING SYSTEM COMPONENTS.

F) DO NOT OPERATE THE LEADING EDGE SLATS. ACCIDENTAL SLATOPERATION COULD CAUSE DAMAGE TO EQUIPMENT AND INJURY TOPERSONS.

G) ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. BONDING CABLES ATTACHED TO COMPOSITE DOORS ORFAIRINGS DO NOT GIVE AN ELECTRICAL BOND.

CAUTION: DO NOT REMOVE ELECTRICAL POWERWHILE REFUELING. IF YOU REMOVEELECTRICAL POWER WHILE REFUELING, THE REFUELING VALVES WILLCLOSE AND CAN DAMAGE EQUIPMENT.



3. Open the refueling station door, installed on the left wing.4. Open the refueling station door, installed on the right wing, if it is necessary.


5. Connect the refuel nozzles to one or more of the refuel adapters.a. Place the REFUEL/DEFUEL handle of the fueling adapter to the REFUEL position.



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door.b. If the FUEL QTY display(s) does not show the fuel quantity, put the POWER switch on the

IRP to the BATT position.c. Make sure the FUEL QTY display(s) show the fuel quantity.d. If one or more of the FUEL QTY displays continue to be off, do the "Pressure Refueling -

With An Inoperative Fuel Quantity Display" procedure.NOTE : Make sure the total fuel legend TF shows on the TOTAL/BACKUP display. This


(1) If the total fuel legend TF is not on or the refueling station door lights do not come on,do the "Pressure Refueling - With Inoperative Refuel Valves" procedure to open therefuel valves.

7. Push the TEST IND switch to do a test of the fuel quantity indicators and blue valve positionlights.


9. Make sure each blue valve position light comes on and then goes off.a. Record the FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING -

LBS" spaces on the fuel slip. Refer to Section 15.01.b. Determine fuel load per tank from fuel record "GATE RELEASE QUANTITY REQUIRED -

LBS." Refer to Section 15.01.10. Start the fueling source.11. To open the refuel valves, do these steps:

a. Put the applicable refuel valve control switches to the OPEN position.NOTE : If you put a refuel valve control switch to the CLOSE position during refueling, the

pressure refueling operation stops for that fuel tank.

b. Make sure the applicable blue refuel valve lights come on.NOTE : The blue light shows that the refuel valves in the applicable fuel tank are in the

open position.

(1) If the refuel valve lights do not stay on, refer to the "Pressure Refueling With anInoperative Refuel Valve" procedure.

12. Monitor the fuel quantity on the FUEL QTY display, on the IRP.13. If the message PUSH SET shows on the FUEL QTY display, the refuel operation will stop.

a. Do the "Pressure RefuelingWith An Inoperative Fuel Quantity Display" procedure to continuerefueling the applicable fuel tank.

b. Do an overfill test.

To do an overfill test, do these steps:(1) Apply fueling pressure.(2) Push the OVERFILL TEST switch on the IRP.



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(3) Make sure the refuel valve lights go off.NOTE : This shows that the refuel valves are closed.

(4) Set the OVERFILL RESET switch to the RESET position on the IRP.(5) Set the OVERFILL RESET switch to the NORMAL position on the IRP.(6) Make sure the refuel valve lights come on.


14. Put the applicable refuel valve switches to the CLOSE position for the fuel tanks with the correctquantity of fuel.

15. Stop the fueling source.16. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.17. Disconnect the fueling nozzles.18. Disconnect the bonding cable.19. If the battery power switch is in the BATT position, put the battery power switch to the NORMAL

position.20. Close the refueling station door.21. Close the refueling station door, if it is open.

24.01.4 Pressure Refueling - With Inoperative Refuel Valves

A. General1. This procedure lets the operator refuel one or more fuel tanks with inoperative refuel valves. You

can operate the refuel valves manually on the rear spar.2. There is no automatic refuel shutoff protection when the refuel valves are opened manually. If

you put too much fuel into a fuel tank, fuel can spill into the surge tanks and possibly overboard.



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Figure 24.01-5: Refuel Valve Control Unit Location



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Figure 24.01-6: Refuel Valve Control Unit Servicing






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C) DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. THE WEIGHT OF THE FUEL WILL CAUSE THEWINGSTOMOVEDOWNANDTHEWINGTIPSMOVETHEMOST. BECAUSETHEFUELTANKSAREVENTEDTHROUGHTHEWINGTIPS, ADANGEROUSAND EXPLOSIVE MIXTURE AROUND THE WINGTIP CAN OCCUR.




G) ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. BONDING CABLES ATTACHED TO COMPOSITE DOORS OFFAIRINGS DO NOT GIVE AN ELECTRICAL BOND.




3. Open the refueling station door, installed on the left wing.4. Open the refueling station door, installed on the right wing, if it is necessary.5. Connect the refuel nozzles to one or more of the refuel adapters.

a. Place the REFUEL/DEFUEL handle of the fueling adapter to the REFUEL position.CAUTION: PRIOR TO APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLES

TO THE LOCKED POSITION AND OPEN POPPET ACTUATING LEVER.ATTEMPT TO REMOVE NOZZLE. IF NOZZLE CAN BE REMOVED, IT ISDEFECTIVE AND MUST BE REMOVED FROM SERVICE.

6. Make sure the fuel quantity displays are on.a. The FUEL QTY displays will come on within 60 seconds after you open the Refueling Station

Door.b. If the FUEL QTY display(s) does not show the fuel quantity, put the POWER switch on the

IRP to the BATT position.c. Make sure the FUEL QTY display(s) show the fuel quantity.d. If one or more of the FUEL QTY displays continue to be off, call aircraft maintenance.

NOTE : Make sure the total fuel legend TF shows on the TOTAL/BACKUP display. Thisshows there is 28V DC at the IRP.

e. Record the FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING -LBS" spaces on the fuel slip. Refer to Section 15.01.



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f. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITYREQUIRED - LBS." Refer to Section 15.01.

7. Do these steps to get access to the refuel valve control unit(s) (refer to Figure 24.01-5 andFigure 24.01-6), to be performed by Aircraft Maintenance:a. To get access to the refuel valve control units in the left or right main fuel tank, notify Aircraft

Maintenance in person to do these steps:(1) Open the inboard fixed trailing edge panel 18 to get access to the inboard refuel valve

control unit in the left main fuel tank. Refer to Figure 24.01-5.(2) Do one of these steps to access the outboard refuel valve control unit in the left main

fuel tank:a) Remove the midspan fixed trailing edge panel. Refer to Figure 24.01-5.b) Extend the trailing edge flaps to 30 degrees.c) Deactivate the trailing edge flaps. To deactivate them, do Task 27-51-00-040-801.

WARNING: DO NOT REACTIVATE THE FLAP/SLAT SYSTEM UNTILFUELING OPERATION IS COMPLETED AND FUELING ANDDOOR(S) ARE CLOSED.

b. To get access to the refuel valve control units in the center fuel tank, notify AircraftMaintenance in person to do these steps:(1) Make sure the downlock pins are installed on the nose and main landing gear.

WARNING: OBEYTHE INSTALLATIONPROCEDUREFORTHE LANDINGGEARDOOR SAFETY PINS. THE DOORS OPEN AND CLOSE QUICKLYAND CAN CAUSE INJURIES TO PERSONS AND DAMAGE TOEQUIPMENT.

(2) Install landing gear door safety pins.8. Do these steps to open the refuel valve(s) manually. Refer to Figure 24.01-6.

NOTE : The refuel valves will not open if the refuel manifold is pressurized.

a. Make sure the fueling source is off.CAUTION: DO NOT REMOVE THE RETAINER PLATE LOCKWIRE, SCREWS, OR

THE RETAINER PLATE. FUEL LEAKAGE CAN OCCUR AND CAUSEDAMAGE.

b. Have Aircraft Maintenance remove the lockwire from the override screw (knurled knob) only.c. Turn the override screw (knurled knob) 10 to 13 turns in the counterclockwise direction.

CAUTION: THERE IS NO AUTOMATIC REFUEL SHUTOFF OR OVERFILLPROTECTIONWHEN THE REFUEL VALVES ARE OPENEDMANUALLY.

DO NOT MANUALLY USE THE REFUEL VALVES TO SLOW OR STOPTHE REFUELING. IF YOU MANUALLY CLOSE THE REFUEL VALVESDURING FUELING, PRESSURE SURGES AND DAMAGE TO THEEQUIPMENT CAN OCCUR.

9. Start the fueling source.10. Release the deadman switch on the fueling source to stop refueling when you get the correct

quantity of fuel in the fuel tank.a. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.

11. Have Aircraft Maintenance do these steps to close the refuel valves manually:



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CAUTION: TIGHTENTHEKNURLEDKNOBBYHAND. IF YOUTIGHTENTHEKNURLEDKNOB WITH TOOLS YOU CAN DAMAGE THE REFUEL VALVE CONTROLUNIT.

a. Turn the override screw (knurled knob) on the refuel valve control unit 10 to 13 turns in theclockwise direction until the override screw stops.

b. Install lockwire to the override screw (knurled knob).c. For the refuel valves in the left or right main fuel tank, have Aircraft Maintenance do these

steps:(1) Close the inboard fixed trailing edge panel for the inboard refuel valve.(2) Do one of these steps to close access to the outboard refuel valve:

a) Install the midspan fixed trailing edge panel.b) Reactivate the trailing edge flaps. To reactivate the flaps do Task 27-51-00-440-801.

d. For the center fuel tank, have Aircraft Maintenance do this step:WARNING: OBEY THE INSTALLATION PROCEDURE FOR THE LANDING GEAR

DOOR SAFETY PINS. THE DOORS OPEN AND CLOSE QUICKLY ANDCAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

(1) Remove Landing Gear Door Safety Pins.12. Disconnect the fueling nozzles.13. Disconnect the bonding cable.14. Close the refueling station door.15. Close the refueling station door, if it is open.

24.01.5 Pressure Refueling - With an Inoperative Fuel Quantity Display (Refer to Figure 24.01-2)

A. General1. This procedure lets the operator refuel one or more fuel tanks with a FQPU failure. The FUEL

QTY display and the LOAD SEL display will be off for the fuel tanks with the failure. Only onerefuel valve will open for the fuel tank with the failure.CAUTION: THERE IS NO VOLUMETRIC SHUTOFF (VSO) WHEN THE FUEL QUANTITY

DISPLAYS ARE OFF.

2. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display),a Vendor Supervisor, Lead or Supervisor/Lead, or Designated Trainer performing the duties ofaircraft refueling must be present to oversee and coordinate the operation.

3. Three methods can be used to fill the tanks with inoperative fueling panel gauges. Refer to Section24.03.3 and Section 15.01.5. These methods are:a. Method 1 - For use when the flight deck fuel quantity display is operational and one or more

of the underwing panel fuel quantity displays are inoperative:(1) Push the TOTAL/BACKUP DISPLAY TANK SELECT switch on the IRP, P28, until the

tank desired appears. This will be indicated with a legend of RM for right main tank, CTfor center tank, or LM for left main tank, in the lower left corner of the TOTAL/BACKUPdisplay.

(2) Individual tank quantities may be determined by the respective cockpit display for theinoperative underwing panel quantity indicator. Use of Method 1 shall be noted on thefuel slip in the remarks field, with a copy of the fuel slip provided to the flight crew asearly as practicable after fueling.



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b. Method 2 - For use on main tanks (wings) and center tank when the flight deck fuel quantitydisplay is inoperative, one or more of the underwing panel fuel quantity displays are inoperativeand fuel on board can be determined using fuel measuring sticks both before and after therefueling operation:(1) Before fueling, determine existing fuel tank quantity with the measuring stick of the

affected tank. Refer to Section 24.03.NOTE : This method requires that the aircraft attitude be known. It will be required to

coordinate with the Flight Crew or aircraft maintenance to determine the aircraftattitude. This is determined three different ways:(1) FQIS Maintenance Page in the flight deck(2) Plumb bob indicator located in the right main gear well (refer to Section

24.03).(3) Inclinometer in the nose wheel well (refer to Section 24.03).

(2) Top off tank(s) with operative indicator to quantity of fuel required.(3) Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged

by the fuel vehicle meter reading. Alternately, transfer required fuel from tank(s) withoperative indicator. Use measuring stick(s) to verify tank quantity.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to

gallons, Reference Section 15.01.7, to deliver the desired known quantity.

(4) Provide flight crew with completed copy of fuel slip and an Inoperative Fuel QuantityIndicator service record. Make sure all required entries and signatures are legible andin place as early as practicable, before departure.NOTE : (1) If there is a failure during refueling, the message PUSH SET will show on

the FUEL QTY display. Push the load select set switch to continue refueling.The FUEL QTY display and the LOAD SEL display will go off. One refuelvalve will open in the applicable fuel tank.

(2) If the FUELQTY display and the LOADSEL display are off when the refuelpanel door is opened the PUSH SET message will not show.

c. Method 3 - For use on main tanks (wings) and center tank when the flight deck fuel quantitydisplay is inoperative, one or two of the underwing panel quantity displays are inoperativeand fuel on board cannot be determined using fuel measuring sticks both before and afterthe refueling operation:(1) Completely defuel the tank with the inoperative indicator by transferring fuel to other

tank(s). Use the operative tank indicators of the tanks the fuel was transferred into tometer the fuel back into the tank with the inoperative indicator. OR

(2) Fuel the tank with the inoperative indicator separately, to the quantity of fuel required,as gauged by the fueling equipment meter reading. Use measuring stick(s) to verify tankquantity.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to

gallons, Reference Section 15.01.7, to deliver the desired known quantity.

(3) Provide flight crew with completed copy of fuel slip and an Inoperative Fuel QuantityIndicator service record. Make sure all required entries and signatures are legible andin place as early as practicable, before departure.

4. You do not have to open the refuel valves manually on the rear spar for this procedure.B. Procedure



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A)



C) DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. BECAUSE THE FUEL TANKS ARE VENTEDTHROUGH THE WINGTIPS, A DANGEROUS AND EXPLOSIVE MIXTUREAROUND THE WINGTIP CAN OCCUR.




G) ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. THESESCRATCHESCANCAUSECORROSIONANDCRACKSON STRESSED PARTS. BONDING CABLES ATTACHED TO COMPOSITEDOORS OF FAIRINGS DO NOT GIVE AN ELECTRICAL BOND.




3. Open the refueling station door installed on the left wing.4. Open the refueling station door installed on the right wing, if it is necessary.



6. In the event that the FUEL QTY display does not operate, do these steps:a. Wait 60 seconds after you open the Refueling Station door, to see if the FUEL QTY displays

will come on.NOTE : Make sure the total fuel legend TF shows on the TOTAL/ BACKUP display.

b. If the FUEL QTY display does not show the fuel quantity, put the POWER switch on the IRPto the BATT position.

c. Make sure the FUEL QTY display(s) show the fuel quantity.



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d. If one or more of the FUEL QTY displays continue to be off, refer to "Fuel Measuring StickProcedures" in Section 24.03.

24.01.6 Defueling


A. The defuel system moves fuel from the airplane tanks to the refuel station. It also moves fuel fromone airplane tank to another (tank-to-tank transfer). There are three ways to get fuel out of the tanks.1. Pressure defuel

a. The pressure defuel system uses aircraft fuel boost pumps, or fuel override/jettison pumps,to remove fuel from the fuel tanks.

b. At the flight deck, the fuel panel P5 (refer to Figure 24.01-7) has switches that control thefuel boost pumps and the transfer valves.

Figure 24.01-7: Defuel Operation

c. Each boost pump switch on the P5 panel has two lighted indications: An ON light comes onwhen the switch is selected to the ON position and the pump comes on. A PRESS light



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comes on when there is low pump pressure. The PRESS light should go off as soon as theswitch is turned on.

d. During the defueling procedure, the fuel flows through the engine fuel feed manifold, throughthe defuel valve, into the refuel manifold and out of the refuel adapters into the fueling vehicles,or through refueling valves into another fuel tank in the airplane. Refer to Figure 24.01-8.NOTE : When defueling into a tanker truck, the refuel valve switches at the P28 integrated

refuel panel (IRP) at the right wing fueling station (refer to Figure 24.01-7) mustremain closed to prevent fuel from recirculating within the aircraft tanks.

2. Suction defuelinga. Suction defueling may be accomplished without operating the wing tank boost pumps. Fuel

flows from the bypass valves into the engine feedmanifold. It then flows through the crossfeedvalves into the refuel valve and goes into the refuel/jettison manifold. From the refuel/jettisonmanifold, it flows through the refueling station adapters and into the fuel vehicle. Refer toFigure 24.01-8.

3. Tank-to-tank transfera. Tank-to-tank transfer requires the use of the defuel valve, refuel valves, engine fuel spar

valves, engine fuel crossfeed valve and wing boost pumps. This procedure is basically thesame as pressure defueling except that the fuel is not placed into the fueling vehicle. It isplaced into another tank by opening the refuel valve of the tank that the fuel should betransferred into.CAUTION: DURING A TANK-TO-TANK TRANSFER, THE FUELING VEHICLE HOSE

ADAPTER MUST BE DISCONNECTED FROM THE AIRCRAFT PRIORTO THE START OF THE TRANSFER TO PREVENT ACCIDENTALTRANSFER OF FUEL FROM THE WING TO THE FUELING VEHICLE.

B. Pressure defuelingWARNING: DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TO


STRONG RADIOACTIVE FIELDS. LIGHTNING STRIKE AND HIGHDISCHARGE CURRENTS CAN CAUSE SEVERE INJURY.


C) DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. THE WEIGHT OF THE FUEL WILL CAUSE THEWINGSTOMOVEDOWNANDTHEWINGTIPSMOVETHEMOST. BECAUSETHEFUELTANKSAREVENTEDTHROUGHTHEWINGTIPS, ADANGEROUSAND EXPLOSIVE MIXTURE CAN OCCUR IN THAT AREA.

D) DO NOT START OR SHUT DOWN APU SHOULD A FUEL SPILL OCCUR.E) DO NOT OPERATE THE LEADING EDGE SLATS. ACCIDENTAL SLAT


CAUTION: DO NOT REMOVE ELECTRICAL POWER WHILE TRANSFERRINGTANK-TO-TANK. IFYOUREMOVEELECTRICALPOWERWHILETRANSFERRING,THE REFUELING VALVES WILL CLOSE AND MAY DAMAGE EQUIPMENT.



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Figure 24.01-8: Defuel-Functional Description-Fuel Flow

1. External or APU electrical power should be used for pressure defueling operations. If external orAPU power sources are not available, the airplane battery may be used as a power source.

2. Connect a bonding cable to an approved electrical grounding or bonding connection on theairplane. Refer to Figure 24.01-4.

3. Open the refueling station door. Refer to Figure 24.01-7, view A.4. Connect the fuel nozzles to one or more fueling adapters.5. Move the valve on the fueling nozzle hose to the OPEN position.

a. Place the REFUEL/DEFUEL handle of the fueling adapter to theDEFUEL position if defuelinginto a fueling vehicle.


door.b. If the FUEL QTY display(s) does not show the fuel quantity, put the POWER switch of the

IRP to the BATT position.c. Make sure the FUEL QTY displays show the fuel quantity.d. If the IRP FUEL QTY displays continue to be off, you may use the fuel panel (P5) in the

cockpit to defuel/transfer fuel from the airplane.CAUTION: IF THE FUELING PANEL (P5) IN THE COCKPIT IS USED TO DEFUEL

THE AIRCRAFT, A SECOND PERSON IS REQUIRED FORCOMMUNICATION. ONE PERSON IN THE COCKPIT WITHCOMMUNICATION TO THE PERSON AT THE GROUND REFUELINGPANEL.

NOTE : Make sure the total fuel legend TF shows on the TOTAL/BACKUP display. Thisshows there is 28 VDC at the IRP.


8. During the test, a test pattern shows in the fuel quantity indicators and the valve position indicationlights come on. If a fuel quantity indicator fails the test, all of its LEDs go off.

9. Make sure each blue valve position light comes on and then goes off.a. Determine fuel load in each tank. Record FUEL QUANTITY in each tank in the GAUGE

READING BEFORE FUELING - LBS spaces on the fuel slip. Determine the amount of fuelto be removed from the aircraft by calculating the difference between GATE RELEASEQUANTITY REQUIRED - LBS on the fuel slip. The total of that calculation will give the amountof fuel to be removed.

10. Move the DEFUEL VALVE switch on the IRP to OPEN position.11. Open the CROSSFEED valve switch on the P5 cockpit fueling panel. A lighted bar should appear

across the CROSSFEED switch when activated.WARNING: DO NOT OPERATE A FUEL PUMP IF THE AMBER PRESS LIGHT COMES

ON AND STAYS ON. IT CAN CAUSE THE IGNITION OF THE FUEL FUMESIN THE TANK WHICH WILL CAUSE A FIRE OR EXPLOSION. FIRES ANDEXPLOSIONS CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TOEQUIPMENT.



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12. To operate any of the fuel pumps, you must be in the flight compartment to continuously monitorthe fuel quantity and the low pressure indication in the applicable tank. Immediately set theapplicable fuel pump switch-light(s) to OFF if the amber PRESS light comes on and stays on.NOTE : Extended running of the fuel pumps with the PRESS light on may set flight deck alerts

requiring maintenance personnel troubleshooting prior to flight, as well as, flight delays.

13. From (P5) panel, turn on the wing boost pumps in the tanks that are to be defueled. Refer toFigure 24.01-7. The ON light in the switch should come on and the PRESS light should go off.

14. Start defueling the airplane.15. When the desired level of fuel in each tank is reached, turn off the wing boost pump of that tank.16. If defueling with the center tank pumps:

a. Push the L and R CENTER PUMPS switch-lights to the off position when the necessaryquantity of fuel is removed.

b. Keep a minimum of 5500 lb (2495 kg) of fuel in the center tank.NOTE : This fuel quantity is necessary to make sure that the pump INLET is in the fuel.

c. If the center tank fuel is less than 5500 lb (2495 kg), continuously monitor the fuel quantityand the low pressure indication in the center tank.(1) Immediately set the L and R CENTER PUMPS switch-lights to the off position if the

amber PRESS light comes on and stays on.NOTE : To prevent the pumps from dry running, the center tank pumps should be

turned off when the minimum fuel quantity remains in the tank.

(2) Make sure that the applicable Engine Indicating and Crew Alerting System (EICAS)status message does not show on the EICAS display for the applicable pump:a) FUEL PUMP CENTER L.b) FUEL PUMP CENTER R.

17. When all tanks are defueled to the required level, move the defuel valve switch on the IRP panelto the CLOSED position. Make sure the actual fuel load after fueling matches the required loadas indicated on the fueling slip at the GATE RELEASE QUANTITY REQUIRED - LBS column.

18. Move the fueling nozzle valve to the closed position.19. Remove the fueling nozzle from the airplane.

a. Place the REFUEL/DEFUEL handle of the fueling adapter to the REFUEL position.20. Disconnect the bonding cable from the airplane.21. Stow the fueling adapter on the fueling vehicle.22. If the battery power switch is in the BATT position, put the battery power switch to the NORMAL

position.23. Close the refueling station door.

C. Suction defueling1. Suction defueling is the same as the pressure defueling procedure except you do not turn on the

wing boost pumps. It will still require that you turn on the crossfeed valve switches on the cockpit(P5) panel.NOTE : This procedure will be slower than pressure defueling. It may be desirable to use a

combination of both pressure and section at the same time to defuel the airplane faster.

2. Suction defueling stops when one of the bypass valve inlets is uncovered. Thus, if the tanks donot become empty at the same time, there may be fuel remaining in one or more tanks.

D. Tank-to-tank transfer:



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1. Tank-to-tank transfer is the same as pressure defuel, with the following exceptions.a. Do not connect the fueling adapter hose from the fueling vehicle to the airplane.b. You must select which tank to transfer the fuel into by opening the refuel valve on the IRP.

WARNING: DONOTOPERATEAFUELPUMP IF THEAMBERPRESSLIGHTCOMESON AND STAYS ON. IT CAN CAUSE THE IGNITION OF THE FUELFUMES IN THE TANK WHICH WILL CAUSE A FIRE OR EXPLOSION.FIRESANDEXPLOSIONSCANCAUSE INJURIES TOPERSONNELANDDAMAGE TO EQUIPMENT.

c. To operate any of the fuel pumps, you must be in the flight compartment to continuouslymonitor the fuel quantity and the low pressure indication in the applicable tank. Immediatelyset the applicable fuel pump switch-light(s) to OFF if the amber PRESS light comes on andstays on.NOTE : Extended running of the fuel pumps with the PRESS light on may set flight deck

alerts requiring maintenance personnel troubleshooting prior to flight, as well as,flight delays.

d. If defueling with the center tank pumps:(1) Push the L and R CENTER PUMPS switch-lights to the off position when the necessary

quantity of fuel is removed.(2) Keep a minimum of 5500 lb (2495 kg) of fuel in the center tank.

NOTE : This fuel quantity is necessary to make sure that the pump INLET is in thefuel.

(3) If the center tank fuel is less than 5500 lb (2495 kg), continuously monitor the fuel quantityand the low pressure indication in the center tank.a) Immediately set the L and R CENTER PUMPS switch-lights to the off position if the

amber PRESS light comes on and stays on.NOTE : To prevent the pumps from dry running, the center tank pumps should

be turned off when the minimum fuel quantity remains in the tank.

b) Make sure that the applicable EICAS status message does not show on the EICASdisplay for the applicable pump:1. FUEL PUMP CENTER L.2. FUEL PUMP CENTER R.

e. If the tank you are defueling is to be emptied, let the wing boost pump(s) operate until thePRESS light of the cockpit fueling panel for that tank comes on. At that point, turn off thewing boost pump(s) switch(s).

f. If the tank is not to be completely defueled, turn off the IRP refuel valve switch at the desiredlevel.

END



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Section 24.02 - Fuel Sump - Operation24.02.1 General

A. Fuel Tank Sump Locations1. There are two sump drain valves installed in the center fuel tank, one sump drain valve in each

main fuel tank, and one sump drain valve in each surge tank. There are six sump drain valves intotal, installed on the airplane.

B. Fuel Tank Sump Check1. Aircraft fuel sumping is the responsibility of maintenance personnel and is to be in accordance

with the scheduled maintenance checks.

END

Section 24.02Fuel Sump - Operation


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Section 24.03 - Fuel Quantity Measuring Stick - Servicing24.03.1 General

A. Introduction1. The Model B777-200 IGW airplane has magnetic type dripless fuel measuring sticks. Six fuel

measuring sticks are installed in each main fuel tank and two fuel measuring sticks are installedin each side of the center fuel tank. In this procedure the fuel measuring sticks are referred to asfuel sticks 1 and 2 for the center fuel tank and fuel sticks 3 through 8 for the main fuel tanks. Referto Figure 24.03-1 and Figure 24.03-2.

2. This procedure contains the information necessary to find the fuel quantity in each fuel tank withthe use of the fuel measuring sticks. To find the fuel quantity the airplane attitude must be known.When the airplane is at a level attitude (-0.70° nose down and 0.00° wing roll).

B. Airplane Attitude1. The airplane pitch and roll attitude must be known in addition to the fuel height to find the fuel

quantity in each fuel tank. Find the airplane attitude with one of these methods:a. Airplane pitch and roll is displayed on the center tank EICAS maintenance page in the flight

deck. This pitch and roll is determined from the Airplane Data Inertial Reference Unit (ADIRU)acceleration data and is displayed to the nearest tenth of a degree. Have the Flight Crew orMaintenance do the steps that follow if electrical power is available.(1) Make sure the ADIRU is powered and aligned, do this task:

a) Air Data Inertial Reference Unit - Alignment.(2) Look at page 2 of the FUEL QTY maintenance page on EICAS.

a) Make a record of the PITCH and ROLL indications.b. Each airplane has a plumb bob attachment and a leveling scale, which are used to find the

airplane attitude. The scale is graduated in degrees for pitch (TAIL DOWN or NOSE DOWN)and wing roll (LEFTWING DOWN or RIGHTWING DOWN). The plumb bob attachment andthe leveling scale are installed in the right main gear wheel well.

c. Each airplane also has pitch and roll inclinometers which are used to find the airplane attitude.The pitch inclinometer is graduated in degrees of NOSE UP and NOSE DOWN. The rollinclinometer is graduated in degrees of LEFT WING UP and DOWN, RIGHT WING UP andDOWN. The inclinometers are installed in the wheel well for the nose landing gear.

2. It is important to know the sign conversion for pitch and roll in the conversion tables. Positive rollis wing high, for the left or right wing. When the roll is positive for one wing, it is negative for theother wing. Positive pitch is nose high.a. For example, if the airplane attitude is 1.3° nose up and 2.0° left wing down, the fuel load in

the left wing will be found in the table labeled "Pitch = 1.30 Degrees" and in the columnlabeled "2.00" for roll attitude. The fuel load in the right tank will be found on the same pagefor pitch and in the column labeled "2.00" for roll attitude.

C. Fuel Level Measurement1. The fuel stick consists of a float assembly, a stick housing and the measuring stick. The float

assembly contains a magnet and floats on the fuel. The measuring stick contains a steel armatureat its top end that is free to slide up and down in the stick housing. When the steel armature is inthe magnetic field of the magnet in the float, the float will hold the stick from its top end. Thebottom of the stick will extend from the lower wing surface. The stick is graduated in linear unitsand gives a visual indication of the fuel height in the tank. The stick measurement is read wherethe lower wing surface intersects the fuel stick.

Section 24.03Fuel Quantity Measuring Stick - Servicing


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2. The fuel sticks measure the fuel height in the applicable fuel tank, which is then converted topounds in the conversion tables. The range for each fuel stick is shown in Figure 24.03-6. Theminimum reading in Figure 24.03-6 corresponds to the top unit on the fuel stick. The maximumreading corresponds to the bottom unit on the fuel stick.

3. The fuel sticks are installed through the lower wing surface of each fuel tank. Fuel sticks 1 and2 are installed through the bottom wing skin in the left and right center fuel tank. Fuel sticks 3through 8 are installed in fuel tank access doors in each main fuel tank.

4. The fuel sticks are unlocked from their base by pressing lightly and turning the stickcounterclockwise 90 degrees. The stick must then be lowered through the magnet and then raisedslowly on the fingertip or palm until it is captured by the magnet in the float. Once the stick iscaptured by the magnet, read it without touching the stick. The stick measurement is read at thelower edge of the retainer. To replace the stick, push it into the housing and turn it clockwise untilit locks in its place.

D. Description of Tables1. The conversion tables make up the main body of this procedure. The tables contain fuel load in

pounds versus fuel stick readings, corrected for airplane attitude. These tables were generatedby Boeings P187 Fuel Tank Model to simulate the fuel tanks and their contents at various airplaneattitudes. The results are a determination of fuel height at each fuel stick location and thecorresponding fuel volume in the fuel tank, based on 6.70 lb./gal.NOTE : When actual fuel density deviates greatly from the nominal chart value of 6.70 pounds

per gallon, it may be desirable to convert the chart derived pound value to "actualpound" value based on local station density. Refer to Section 10.01.3.

2. The airplane attitude must be in the limits shown above in order to use the conversion tables. Ifthe airplane attitude is not within these limits, the fuel quantity cannot be determined accuratelywith this procedure.a. Pitch = (-2.7° to +1.3°)b. Wing Roll = (-2.0° to +2.0°)

24.03.2 Find the Fuel Quantity (Refer to Figure 24.01-1)

A. General1. To find the fuel level, use a fuel stick that shows best mid-range quantity.

B. Procedure1. Park the airplane on a level surface.2. Have Maintenance do these steps to find the airplane attitude.

NOTE : The airplane attitude will change while fuel is loaded. The airplane attitude and fuelquantity should be checked after the fuel is loaded to get the correct fuel quantity.

3. Have Maintenance do these steps if electrical power is not available:a. Make sure the landing gear downlock pins are installed on the nose and main landing gear,

do this task - Landing Gear Downlock Pins Installation (Reference AMM TASK32-00-30-480-801).WARNING: USETHECORRECTPROCEDURETOOPENTHEDOORS. THEDOORS

OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONSOR DAMAGE TO EQUIPMENT.

b. Open the landing gear doors, do this task: Landing Gear Ground Door Release SystemOperation (Open the Doors) (Reference AMM TASK 32-00-40-860-802).



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WARNING: USE THE CORRECT PROCEDURE TO INSTALL THE DOOR LOCKS.THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURYTO PERSONS OR DAMAGE TO EQUIPMENT.

c. Install the door locks, do this task: Landing Gear Door Safety Pins Installation (ReferenceAMM TASK 32-00-15-480-801).

d. Look at the plumb bob and the leveling scale in the right wheel well to get the pitch and rolldata. Refer to Figure 24.03-4, or

e. Look at the Leveling Inclinometers in Nose Wheel Well. Refer to Figure 24.03-5.4. Make sure the airplane attitude is within these limits:

a. -2.7° to +1.3° pitchb. -2.0° to +2.0° wing roll.



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Figure 24.03-1: Fuel Measuring Sticks - Left Wing



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Figure 24.03-2: Fuel Measuring Sticks - Right Wing



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Figure 24.03-3: Fuel Measuring Sticks - Assembly



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Figure 24.03-4: Airplane Leveling Plumb Bob and Scale



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Figure 24.03-5: Aircraft Leveling Inclinometers

c. If the airplane is not within the above limits, call Aircraft Maintenance.5. If the approximate fuel quantity in the fuel tank is known, refer to Figure 24.03-6 to find which fuel

stick to use.NOTE : Each fuel stick has a range of a minimum and a maximum fuel quantity that you can

measure.



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Figure 24.03-6: Fuel Measuring Stick Range

6. If the approximate fuel quantity in the fuel tank is not known, start at the most outboard fuel stickfor the applicable fuel tank and pull down the fuel sticks until you find the correct fuel stick thatwill give the best mid-range reading.

7. Use a screwdriver and push up lightly on the latch of the fuel stick and turn the screwdriver slot90° counterclockwise to release the stick.

8. Carefully, lower the fuel stick to its fully extended length.9. Use a fingertip (or the flat palm of your hand) to slowly lift the fuel stick until resistance is felt.

NOTE : Resistance occurs when the float magnet catches the steel armature of the fuel stick.The fuel stick is held in this position by the magnet on the float.

10. Release the fuel stick.11. Read the fuel level at the lower edge of the retainer. Refer to Figure 24.03-3.

a. If the fuel level is not in the correct range for the fuel stick, go to the fuel stick with the fuellevel that is in mid-range.

12. Lower and read the fuel stick three times to make sure the fuel level you read is repeatable.NOTE : When fuel quantity is verified by measuring stick, measuring shall be performed by the

fuel servicemen and shall be monitored by cockpit crew member.

13. Push the fuel stick up into the housing.14. Push up lightly on the latch of the fuel stick with a screwdriver and turn the screwdriver slot 90°

clockwise until the fuel stick locks into position.15. Go to the correct fuel stick conversion table for the applicable fuel stick number. (Ref. AMM

12-11-05-650-801.)



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NOTE : The fuel sticks are numbered inboard to outboard as Stick No. 3 through Stick No. 8,on the left and right wings. The fuel sticks for the center tank are numbered 1 and 2.

16. Find the page with the correct fuel stick number and pitch attitude.NOTE : Pitch attitude is shown as NOSEUP (+) and NOSEDOWN (-) for the pitch inclinometer.

NOSE UP (+) is the same as TAIL DOWN on the airplane leveling scale.

17. Find the correct column for the wing roll attitude, measured in degrees.18. Find the fuel stick unit in the conversion table that agrees with actual (measured) fuel stick value.19. Read across from the fuel stick unit in the conversion table to find the airplane roll attitude, then

read down from the correct wing roll attitude to find the fuel quantity in pounds.20. The fuel quantity shown is the quantity of usable fuel in the applicable fuel tank.

C. Put the Airplane Back to Its Usual Condition.WARNING: USETHECORRECTPROCEDURETOREMOVETHEDOORLOCKS. THEDOORS

CAN OPEN AND CLOSE QUICKLY AND CAUSE INJURY TO PERSONS ORDAMAGE TO EQUIPMENT.

1. Remove the door lock, do this task: Landing Gear Door Safety Pins Removal.WARNING: USE THE CORRECT PROCEDURE TO CLOSE THE DOORS. THE DOORS

OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS ORDAMAGE TO EQUIPMENT.

2. Close landing gear doors.














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(5) Record the after fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner/ outer cell





b. When using method 3, perform the following:NOTE : When using Method 3 to verify all tank quantities after fueling for an inoperative

fuel tank quantity indication channel fault, record the actual before quantity tankgauge readings in lieu of zero (0) for each respective tank on a separate InoperativeFuel Quantity Indicator Service Record.

(1) Empty the affected tank by defueling or transferring all remaining fuel to other tanks.Refer to Section 24.01.6.

(2) Record the before fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (for example, L,












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24.03.4 Fuel Measuring Stick Charts

A. Refer to B777-200 Fuel Measuring Stick Charts as follows:1. Access The Stick Charts at http://me.aa.com/manuals/fw/FuelingStickCharts/#z.

END



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Table of contents

25.01 FUELING MANUAL - B777-300ERGENERAL..........................................................................................................................1PRESSURE REFUELING - WITH A SET FUEL QUANTITY (AUTOMATIC) - FIGURE25.01-1 AND FIGURE 25.01-2..........................................................................................2PRESSURE REFUELING - WITH NO SET FUEL QUANTITY.......................................10PRESSURE REFUELING - WITH INOPERATIVE REFUEL VALVES............................12PRESSUREREFUELING -WITHAN INOPERATIVEFUELQUANTITYDISPLAY - FIGURE25.01-2.............................................................................................................................17DEFUELING....................................................................................................................20

25.02 FUEL SUMP - OPERATIONGENERAL..........................................................................................................................1

25.03 FUEL QUANTITY MEASURING STICK - SERVICINGGENERAL..........................................................................................................................1FIND THE FUEL QUANTITY (REFER TO FIGURE 25.01-1)............................................2DETERMINING FUEL QUANTITY BY MEASURING STICK..........................................10FUEL MEASURING STICK CHARTS..............................................................................12

TOCFueling Manual - B777-300ER


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Section 25.01 - Fueling Manual - B777-300ER25.01.1 General

NOTE : The use of Jet B is prohibited on all B-777 aircraft.

WARNING: DO NOT OPERATE THE HF COMMUNICATION SYSTEM DURING REFUELINGOPERATIONS. A FIRE OR EXPLOSION CAN OCCUR.

1.

2. GROUNDEQUIPMENTMUSTNOTBEPOSITIONEDUNDERWINGTIPSDURINGFUELING OPERATION.

3. FUELINGVEHICLEMUSTBEPROPERLYBONDEDTOAIRCRAFTBEFOREANYFUELING/DEFUELING OPERATION.

4. WHENTHERE ISAN INACCURATE/INOPERATIVEORASUSPICIONOFAGAUGENOT INDICATING PROPERLY, STOP FUELING AND NOTIFY AIRCRAFTMAINTENANCE IMMEDIATELY IN PERSON.NOTE : IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARD AS

BEING INOPERATIVE, AIRCRAFT MAINTENANCE DOES NOT NEEDTOBENOTIFIEDUNLESSSPECIFICPROCEDURESDURINGFUELINGOPERATIONS REQUIRE THE ATTENTION OF AIRCRAFTMAINTENANCE.

5. IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION, NOTIFY AIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON.DO NOT START OR RESUME FUELING OPERATIONS UNTIL CORRECTIVEACTION HAS BEEN TAKEN.

6. DO NOT START OR SHUT DOWN APU IF A FUEL SPILL OCCURS.

CAUTION: DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUEL NOZZLE. IFYOU USE MORE THAN 50 PSI FUEL PRESSURE, YOU CAN CAUSE DAMAGE TOTHE REFUELING SYSTEM COMPONENTS.

DO NOT REMOVE ELECTRICAL POWER WHILE REFUELING. IF YOU REMOVEELECTRICAL POWER WHILE REFUELING, THE REFUELING VALVES WILL CLOSEAND CAN DAMAGE EQUIPMENT.

A. Refueling Station1. The refueling stations are installed in the leading edge, just outboard of each engine.2. The left refueling station contains refuel adapters, bonding points, lights, an interphone jack and

an integrated refuel panel (IRP).3. The right refueling station contains refuel adapter, bonding points, lights and an interphone jack.4. Aluminum foil placards installed on the refueling station door have refueling information and

cautions.B. Surge Tank Overfill System

1. There is a surge tank overfill system to catch fuel from the fuel tanks that are more than full, andprevent fuel spills onto the ground. If the surge tank overfill system does not operate correctlyand there is a fuel spill at the wing tip, stop the pressure refueling source immediately to keepthe fire hazard to a minimum.

C. Fuel Loading Limits1. The fuel system has two main tanks and one center tank. There is also a vent surge tank located

in each wing, outboard of the wing tank.a. For all B777-300ER aircraft:

Section 25.01Fueling Manual - B777-300ER


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(1) Center tank has an approximate volume of 27,290 USgal.(2) Main (wing) tanks each have an approximate volume of 10,300 USgal.


NOTE : A STOP indication can show in a LOAD SELECT window on the IRP for agiven tank. This means that the volumetric shutoff (VSO) has been exceededby 100 gallons or more. The refueler should stop refueling. The STOPindication will remain until the quantity in the tank is reduced to the VSO levelor below the VSO level for that tank.

NOTE : The fuel quantity processor unit (FQPU) can command the refuel valves tothe closed position if there is a confirming or confirmed tank unit failure. TheFQPU software will reduce the shutoff level to 3.2% below VSO. If the FQPUcommands early shutoff in one main tank, then there will be a fuel imbalanceof approximately 2,000 to 2,200 lbs. (1,000 to 1,100 kg) between the left andright main fuel tanks.

2. You can refuel all the tanks at the same time or in sequence.NOTE : The usual procedure for refueling the center tank is to put fuel in the center tank if the

left and right main tanks will be filled to capacity.

3. Refuel the left and right main tanks with equal quantifies of fuel.

25.01.2 Pressure Refueling -With a Set Fuel Quantity (Automatic) - Figure 25.01-1 and Figure 25.01-2

A. General1. The fuel quantity to be loaded is entered in the LOAD SELECT QTY control and will show on the

LOAD SEL display when you push the LOAD SELECT SET switch. During pressure refuelingwith a SET fuel quantity in the LOAD SEL display, the fuel quantity indicating system (FQIS)operates with the pressure refueling system. The FQPU closes the refuel valves when the SETfuel quantity is the same as the FQIS fuel quantity.NOTE : 1. The refueling operator can operate the refuel valve control switches at the IRP to

stop the refuel operation.2. With a LOADSELECTQTY entered for each main tank, the FQIS will automatically

keep the main tank fuel level balanced during the refuel operation. If the quantityof one main tank becomes 1,000 lbs. more than the other main tank, one refuelvalve for the tank with the higher quantity will be closed. When the main tankquantities become equal, the valve will open.

2. The total fuel quantity is the sum of all the fuel tanks. If the total quantity selected is more thanthe main fuel tanks’ capacity, the main tanks will fill to full and the center fuel tank will fill with theremaining fuel. All fuel tanks are filled with fuel at the same time. If the center tank fills to its LOADSELECT value before the main tanks reach VSO, the center tank refuel valves will close. At thispoint the LOAD SELECT values for the three tanks will be updated and the center tank refuelvalves will reopen and fueling will continue to the updated LOAD SELECT value.

3. The examples below will show the final tank values for TOTAL LOAD SELECT quantities of12,600 lbs., 15,000 lbs., 90,100 lbs. and 132,500 lbs.1. TOTAL LOAD SELECT = 12,600 lbs.

NOTE : Left main tank load selects = 6,300 lbs.

Right main tank load selects = 6,300 lbs.




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2. TOTAL LOAD SELECT = 15,000 lbs.NOTE : Left main tank load selects = 7,500 lbs.






Notice that the odd 100 lbs. of fuel was put in the left tank.




5. For the first three totals, the load select values are never recalculated, since 95% of maintank VSO is never reached. For the last total, at 95% of main tank VSO, assuming the averagedensity is 6.78 lbs./gallon, the load select values are recalculated. The left and right mainload selects will change to 63,000 lbs., and the center load select will change to 6,500 lbs.During recalculation at 95% VSO, the refueling valves will close, then reopen. Also, the aboveexamples assume that the center tank quantity starts at zero. If there is fuel in the centertank before you do the TOTAL LOAD SELECT, the center tank quantity of fuel will be usedto determine the final main tank quantities. For example:

MAIN TANK LOAD SELECT = (TOTAL LOAD SELECT - CENTER QUANTITY) /2


THE AIRPLANE DURING ATMOSPHERIC ELECTRICAL ACTIVITY OR1.


2. DONOTOPERATE THEHFCOMMUNICATION SYSTEMOR THEWEATHERRADAR DURING REFUELING OPERATIONS. A FIRE OR EXPLOSION CANOCCUR.

3. DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. THE FUEL TANKS ARE VENTED THROUGH THEWINGTIPS. A DANGEROUS AND EXPLOSIVE MIXTURE AROUND THEWINGTIP CAN OCCUR.

4. DO NOT START OR SHUT DOWN APU IF A FUEL SPILL OCCURS.5. DO NOT OPERATE THE LEADING EDGE SLATS. ACCIDENTAL SLAT


6. ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. BONDING CABLES ATTACHED TO COMPOSITE DOORS OFFAIRINGS DO NOT GIVE AN ELECTRICAL BOND.



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CAUTION: DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUELNOZZLE. IF YOU USE MORE THAN 50 PSI FUEL PRESSURE, YOU CANCAUSE DAMAGE TO THE REFUELING SYSTEM COMPONENTS.

1.

2. DO NOT REMOVE ELECTRICAL POWER WHILE REFUELING. IF YOUREMOVE ELECTRICAL POWER WHILE REFUELING, THE REFUELINGVALVES WILL CLOSE AND CAN DAMAGE EQUIPMENT.





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Figure 25.01-2: Left Wing Pressure Refueling Panel - Detail



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Figure 25.01-3: Right Wing Pressure Refueling Station



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Figure 25.01-4: Bonding Point Locations


3. Open the Refueling Station Door (refer to Figure 25.01-1) installed on the left wing.4. Open the Refueling Station Door (refer to Figure 25.01-3) installed on the right wing, if it is

necessary.



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CAUTION: PRIOR TO APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLESTO THE LOCKED POSITION AND OPEN POPPET ACTUATING LEVER.ATTEMPT TO REMOVE NOZZLE. IF NOZZLE CAN BE REMOVED, IT ISDEFECTIVE AND MUST BE REMOVED FROM SERVICE..

6. Make sure the fuel quantity displays are on.a. The FUEL QTY displays will come on within 60 seconds after you open the Refueling Station

Door. Refer to Figure 25.01-2.b. If the FUEL QTY display(s) does not show the fuel quantity, put the POWER switch on the

IRP to the BATT position.c. Make sure the FUEL QTY display(s) shows the fuel quantity.d. If one or more of the FUEL QTY displays continue to be off, do the Pressure Refueling - With

an Inoperative Fuel Quantity Display Manual procedure.NOTE : Make sure the total fuel legend "TF" shows on the TOTAL/BACKUP display. This


(1) If the total fuel legend "TF" is not on, or the refueling station door lights do not come on,do the Pressure Refueling - With an Inoperative Refuel Valve procedure to open therefuel valves.



9. Make sure each blue valve position light comes on and then goes off.a. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY

REQUIRED - LBS." Refer to Section 15.01.10. To set the fuel quantity for each fuel tank you are to refuel, do the steps that follow:

a. At the LOAD SELECT QTY, set the thumbwheel switches to the necessary quantity of fuel.b. Push the LOAD SELECT SET switch for the applicable fuel tank for 1 second and release.c. Make sure the quantity input into the LOAD SELECT QTY shows on the LOAD SEL display

for the applicable fuel tank.(1) If you make an error during the selection procedure, push the applicable LOADSELECT

SET switch to remove the value from the LOAD SEL display and do the procedure again.11. To set the TOTAL fuel quantity (refer to Figure 25.01-2) that you are to refuel, do the steps that

follow:a. At the LOAD SELECT QTY, set the thumbwheel switches to the necessary quantity of fuel.b. Make sure the TOTAL/BACKUP display on the IRP is set to show the total fuel quantity.c. Push the LOAD SELECT SET switch for the total fuel indicator for 1 second and release.d. Make sure the fuel quantity on the LOAD SELECT QTY shows on the LOAD SEL display

for the TOTAL/BACKUP display.(1) If you make an error during the selection procedure, push the applicable LOADSELECT

SET switch to remove the value and do the procedure again.



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12. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING - LBS"spaces on the Jet fuel Service Record (Fuel Slip). Refer to Section 15.01.

13. Start the fueling source.14. To open the refuel valves, do the steps that follow:

a. Put the applicable refuel valve switches to the OPEN position. Refer to Figure 25.01-2.NOTE : The FQIS processor controls the start of refueling. The refuel valves will close

automatically when:1. The fuel quantity equals the set fuel quantity.2. The fuel tank is full.3. The fuel spills into a surge tank.4. During recalculation at 95% VSO, the refuel valves will close and reopen.

If you put a refuel valve control switch to the CLOSE position during automaticrefueling, the pressure refueling operation stops for that fuel tank.

b. Make sure the applicable blue refuel valve lights come on.(1) If the refuel valve lights do not stay on, refer to the Pressure Refueling - With an

Inoperative Refuel Valve procedure.15. Monitor the fuel quantity on the FUEL QTY displays on the IRP.16. If the message PUSH SET shows on the FUEL QTY display, the refuel operation will stop.

a. Do the Pressure Refueling - With an Inoperative Fuel Quantity Display Manual procedure tocontinue refueling the applicable fuel tank.

b. Do an Overfill Test.(1) Apply fueling pressure.(2) Push the OVERFILL TEST switch on the IRP, P18. Refer to Figure 25.01-2.(3) Make sure the refuel valve lights go off.


(4) Set the OVERFILL RESET switch to the RESET position on the IRP, P18.(5) Set the OVERFILL RESET switch to the NORMAL position on the IRP, P18.(6) Make sure the refuel valve lights come on.


17. Set the refuel valve switches for all the applicable tanks to the CLOSE position when refuelingis complete.NOTE : The FQIS system will automatically close the refuel valve when the fuel quantity in the

tank is the same as the set fuel quantity (or the fuel tank is full).

18. Stop the fueling source.19. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.20. Disconnect the fueling nozzles.21. Disconnect the bonding cable.22. If the power switch is in the BATT position, put the power switch to the NORMAL position.23. Close the left Refueling Station Door.24. Close the right Refueling Station Door, if it is open.



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A. General1. This procedure does not set the fuel quantity to be put on the airplane. The automatic fuel shutoff

control will close each refuel valve when the fuel tanks are full. To stop refueling at a specific fuelquantity shown on the FUEL QTY display, put the REFUEL VALVE CONTROL to the CLOSEposition. The LOAD SEL display will be off.NOTE : You do not have to open the refuel valves manually on the rear spar for this procedure.





3. DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. THE WEIGHT OF THE FUEL WILL CAUSE THEWINGSTOMOVEDOWNANDTHEWINGTIPSMOVETHEMOST. BECAUSETHEFUELTANKSAREVENTEDTHROUGHTHEWINGTIPS, ADANGEROUSAND EXPLOSIVE MIXTURE AROUND THE WINGTIP CAN OCCUR.

4. DO NOT START OR SHUT DOWN APU IF A FUEL SPILL OCCURS.5. DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUEL


6. DO NOT OPERATE THE LEADING EDGE SLATS. ACCIDENTAL SLATOPERATION COULD CAUSE DAMAGE TO EQUIPMENT AND INJURY TOPERSONS.

7. ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. BONDING CABLES ATTACHED TO COMPOSITE DOORS ORFAIRINGS DO NOT GIVE AN ELECTRICAL BOND.




3. Open the Refueling Station Door, installed on the left wing.4. Open the Refueling Station Door, installed on the right wing, if it is necessary.


5. Connect the refuel nozzles to one or more of the refuel adapters.a. Place the REFUEL/DEFUEL handle of the fueling adapter to the "REFUEL" position.



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IRP to the BATT position.c. Make sure the FUEL QTY display(s) shows the fuel quantity.d. If one or more of the FUEL QTY displays continue to be off, do the "Pressure Refueling -

With An Inoperative Fuel Quantity Display" procedure.NOTE : Make sure the total fuel legend "TF" shows on the TOTAL/BACKUP display. This


(1) If the total fuel legend "TF" is not on or the refueling station door lights do not come on,do the Pressure Refueling - With Inoperative Refuel Valves procedure to open the refuelvalves.

7. Push the TEST IND switch to do a test of the fuel quantity indicators and blue valve positionlights.

8. During the test, a test pattern shows in the fuel quantity indicators, and the valve position indicationlights come on. If a fuel quantity indicator light fails the test, all of its LEDs go off.

9. Make sure each blue valve position light comes on and then goes off.a. Record the FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING -

LBS" spaces on the fuel slip. Refer to Section 15.01.b. Determine fuel load per tank from fuel record "GATE RELEASE QUANTITY REQUIRED -

LBS." Refer to Section 15.01.10. Start the fueling source.11. To open the refuel valves, do these steps:

a. Put the applicable refuel valve control switches to the OPEN position.NOTE : If you put a refuel valve control switch to the CLOSE position during refueling, the

pressure refueling operation stops for that fuel tank.

b. Make sure the applicable blue refuel valve lights come on.NOTE : The blue light shows that the refuel valves in the applicable fuel tank are in the

open position.

(1) If the refuel valve lights do not stay on, refer to the "Pressure Refueling - With anInoperative Refuel Valve procedure."

12. Monitor the fuel quantity on the FUEL QTY display on the IRP.13. If the message "PUSH SET" shows on the FUEL QTY display, the refuel operation will stop.

a. Do the "Pressure Refueling -With An Inoperative Fuel Quantity Display" procedure to continuerefueling the applicable fuel tank.

b. Do an overfill test. To do an overfill test, do these steps:(1) Apply fueling pressure.(2) Push the OVERFILL TEST switch on the IRP.(3) Make sure the refuel valve lights go off.



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(4) Set the OVERFILL RESET switch to the RESET position on the IRP.(5) Set the OVERFILL RESET switch to the NORMAL position on the IRP.(6) Make sure the refuel valve lights come on.

NOTE : this shows that the refuel valves are open.

14. Put the applicable refuel valve switches to the CLOSE position for the fuel tanks with the correctquantity of fuel.

15. Stop the fueling source.16. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.17. Disconnect the fueling nozzles.18. Disconnect the bonding cable.19. If the battery power switch is in the BATT position, put the battery power switch to the NORMAL

position.20. Close the Refueling Station Door.21. Close the Refueling Station Door, if it is open.

25.01.4 Pressure Refueling - With Inoperative Refuel Valves

A. General1. This procedure lets the operator refuel one or more fuel tanks with inoperative refuel valves. You

can operate the refuel valves manually on the rear spar.2. There is no automatic refuel shutoff protection when the refuel valves are opened manually. If

you put too much fuel into a fuel tank, fuel can spill into the surge tanks and possibly overboard.



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Figure 25.01-5: Refuel Valve Control Unit Location



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Figure 25.01-6: Refuel Valve Control Unit Servicing






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3. DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. THE WEIGHT OF THE FUEL WILL CAUSE THEWINGSTOMOVEDOWNANDTHEWINGTIPSMOVETHEMOST. BECAUSETHEFUELTANKSAREVENTEDTHROUGHTHEWINGTIPS, ADANGEROUSAND EXPLOSIVE MIXTURE AROUND THE WINGTIP CAN OCCUR.




7. ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. BONDING CABLES ATTACHED TO COMPOSITE DOORS ORFAIRINGS DO NOT GIVE AN ELECTRICAL BOND.




3. Open the refueling station door, installed on the left wing.4. Open the refueling station door, installed on the right wing, if it is necessary.5. Connect the refuel nozzles to one or more of the refuel adapters.

a. Place the REFUEL/DEFUEL handle of the fueling adapter to the REFUEL position.CAUTION: PRIOR TO APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLES

TO THE LOCKED POSITION AND OPEN POPPET ACTUATING LEVER.ATTEMPT TO REMOVE NOZZLE. IF NOZZLE CAN BE REMOVED, IT ISDEFECTIVE AND MUST BE REMOVED FROM SERVICE.



IRP to the BATT position.c. Make sure the FUEL QTY display(s) shows the fuel quantity.d. If one or more of the FUEL QTY displays continues to be off, call aircraft maintenance.


e. Record the FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING -LBS" spaces on the fuel slip. Refer to Section 15.01.



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f. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITYREQUIRED - LBS." Refer to Section 15.01.

7. Do these steps to get access to the refuel valve control unit(s). Refer to Figure 25.01-5 andFigure 25.01-6. These steps to be performed by Aircraft Maintenance.a. To get access to the refuel valve control units in the left or right main fuel tank, notify Aircraft

Maintenance in person to do these steps:(1) Open the inboard fixed trailing edge panel 18 to get access to the inboard refuel valve

control unit in the left main fuel tank. Refer to Figure 25.01-5.(2) Do one of these steps to access the outboard refuel valve control unit in the left main

fuel tank:a) Remove the midspan fixed trailing edge panel. Refer to Figure 25.01-5.b) Extend the trailing edge flaps to 30 degrees.c) Deactivate the trailing edge flaps. To deactivate them, do Task 27-51-00-040-801.

WARNING: DO NOT REACTIVATE THE FLAP/SLAT SYSTEM UNTILFUELING OPERATION IS COMPLETED AND FUELING ANDDOOR(S) ARE CLOSED.

b. To get access to the refuel valve control units in the center fuel tank, notify AircraftMaintenance in person to do these steps:(1) Make sure the downlock pins are installed on the nose and main landing gear.

WARNING: OBEYTHE INSTALLATIONPROCEDUREFORTHE LANDINGGEARDOOR SAFETY PINS. THE DOORS OPEN AND CLOSE QUICKLYAND CAN CAUSE INJURIES TO PERSONS AND DAMAGE TOEQUIPMENT.

(2) Install landing gear door safety pins.8. Do these steps to open the refuel valve(s) manually. Refer to Figure 25.01-6.

NOTE : The refuel valves will not open if the refuel manifold is pressurized.

a. Make sure the fueling source is off.CAUTION: DO NOT REMOVE THE RETAINER PLATE LOCKWIRE, SCREWS, OR

THE RETAINER PLATE. FUEL LEAKAGE CAN OCCUR AND CAUSEDAMAGE.

b. Have Aircraft Maintenance remove the lockwire from the override screw (knurled knob) only.c. Turn the override screw (knurled knob) 10 to 13 turns in the counterclockwise direction.

CAUTION: 1. THERE IS NO AUTOMATIC REFUEL SHUTOFF OR OVERFILLPROTECTION WHEN THE REFUEL VALVES ARE OPENEDMANUALLY.

2. DO NOT MANUALLY USE THE REFUEL VALVES TO SLOW ORSTOP THE REFUELING. IF YOU MANUALLY CLOSE THE REFUELVALVES DURING FUELING, PRESSURE SURGES AND DAMAGETO THE EQUIPMENT CAN OCCUR.

9. Start the fueling source.10. Release the deadman switch on the fueling source to stop refueling when you get the correct

quantity of fuel in the fuel tank.a. Legibly complete all applicable fields on the fuel slip. Refer to Section 15.01.

11. Have Aircraft Maintenance do these steps to close the refuel valves manually:



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CAUTION: TIGHTENTHEKNURLEDKNOBBYHAND. IF YOUTIGHTENTHEKNURLEDKNOB WITH TOOLS YOU CAN DAMAGE THE REFUEL VALVE CONTROLUNIT.

a. Turn the override screw (knurled knob) on the refuel valve control unit 10 to 13 turns in theclockwise direction until the override screw stops.

b. Install lockwire to the override screw (knurled knob).c. For the refuel valves in the left or right main fuel tank, have Aircraft Maintenance do these

steps:(1) Close the inboard fixed trailing edge panel for the inboard refuel valve.(2) Do one of these steps to close access to the outboard refuel valve:

a) Install the midspan fixed trailing edge panel.b) Reactivate the trailing edge flaps. To reactivate the flaps, do Task 27-51-00-440-801.c) For the center fuel tank, have Aircraft Maintenance do this step:

WARNING: OBEY THE INSTALLATION PROCEDURE FOR THE LANDINGGEAR DOOR SAFETY PINS. THE DOORS OPEN AND CLOSEQUICKLY AND CAN CAUSE INJURIES TO PERSONS ANDDAMAGE TO EQUIPMENT.

(1) Remove landing gear door safety pins.12. Disconnect the fueling nozzles.13. Disconnect the bonding cable.14. Close the refueling station door.15. Close the refueling station door if it is open.

25.01.5 Pressure Refueling - With an Inoperative Fuel Quantity Display - Figure 25.01-2

A. General1. This procedure lets the operator refuel one or more fuel tanks with a fuel quantity processor unit

(FQPU) failure. The FUEL QTY display and the LOAD SEL display will be off for the fuel tankswith the failure. Only one refuel valve will open for the fuel tank with the failure.CAUTION: THERE IS NO VOLUMETRIC SHUTOFF (VSO) WHEN THE FUEL QUANTITY

DISPLAYS ARE OFF.

2. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display),a Vendor Supervisor, Lead or Supervisor/Lead, or Designated Trainer performing the duties ofaircraft refueling must be present to oversee and coordinate the operation.

3. Three methods can be used to fill the tanks with inoperative fueling panel gauges. Refer to Section25.03.3 and Section 15.01. These methods are:a. Method 1 - For use when the flight deck fuel quantity display is operational and one

or more of the underwing panel fuel quantity displays are inoperative:(1) Push the TOTAL/BACKUP DISPLAY TANK SELECT switch on the IRP, P28, until the

tank desired appears. This will be indicated with a legend of RM for right main tank, CTfor center tank, or LM for left main tank, in the lower left corner of the TOTAL/BACKUPdisplay.

(2) Individual tank quantities may be determined by the respective cockpit display for theinoperative underwing panel quantity indicator. Use of Method 1 shall be noted on thefuel slip in the remarks field, with a copy of the fuel slip provided to the flight crew asearly as practicable after fueling.



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b. Method 2 - For use on main tanks (wings) and center tank when the flight deck fuelquantity display is inoperative, one or more of the underwing panel fuel quantitydisplays are inoperative and fuel on board can be determined using fuel measuringsticks both before and after the refueling operation:(1) Before fueling, determine existing fuel tank quantity with the measuring stick of the

affected tank. Refer to Section 25.03.NOTE : This method requires that the aircraft attitude be known. It will be required to

coordinate with Flight Crew or aircraft maintenance to determine the aircraftattitude. This is determined three different ways:1. FQIS Maintenance Page in the flight deck2. Plumb bob indicator located in the right main gear well (Refer to Section

25.03.)3. Inclinometer in the nose wheel well (Refer to Section 25.03.)

(2) Top off tank(s) with operative indicator to quantity of fuel required.(3) Fuel tank with inoperative indicator separately, to quantity of fuel required, as gauged

by the fuel vehicle meter reading. Alternately, transfer required fuel from tank(s) withoperative indicator. Use measuring stick(s) to verify tank quantity.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to

gallons, refer to Section 15.01.7, to deliver the desired known quantity.

(4) Provide flight crew with completed copy of fuel slip and an Inoperative Fuel QuantityIndicator service record. Make sure all required entries and signatures are legible andin place as early as practicable, before departure.NOTE : 1. If there is a failure during refueling, the message PUSH SET will show

on the FUEL QTY display. Push the load select set switch to continuerefueling. The FUEL QTY display and the LOAD SEL display will go off.One refuel valve will open in the applicable fuel tank.

2. If the FUEL QTY display and the LOAD SEL display are off when therefuel panel door is opened, the PUSH SET message will not show.

c. Method 3 - For use on main tanks (wings) and center tank when the flight deck fuelquantity display is inoperative, one or two of the underwing panel quantity displaysare inoperative and fuel on board cannot be determined using fuel measuring sticksboth before and after the refueling operation:(1) Completely defuel the tank with the inoperative indicator by transferring fuel to other

tank(s). Use the operative tank indicators of the tanks into which the fuel was transferredto meter the fuel back into the tank with the inoperative indicator, OR

(2) Fuel the tank with the inoperative indicator separately, to the quantity of fuel required,as gauged by the fueling equipment meter reading. Use measuring stick(s) to verify tankquantity.NOTE : If the fueling equipment dispenses in Liters, convert the required liters to

gallons, refer to Section 15.01.7, to deliver the desired known quantity.

(3) Provide flight crew with completed copy of fuel slip and an Inoperative Fuel QuantityIndicator service record. Make sure all required entries and signatures are legible andin place as early as practicable, before departure.

4. You do not have to open the refuel valves manually on the rear spar for this procedure.B. Procedure



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1.

STRONG RADIOACTIVE FIELDS. LIGHTNING STRIKES AND HIGHDISCHARGE CURRENTS CAN CAUSE SEVERE INJURY.


3. DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. BECAUSE THE FUEL TANKS ARE VENTEDTHROUGH THE WINGTIPS, A DANGEROUS AND EXPLOSIVE MIXTUREAROUND THE WINGTIP CAN OCCUR.




7. ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THEAIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. THESESCRATCHESCANCAUSECORROSIONANDCRACKSON STRESSED PARTS. BONDING CABLES ATTACHED TO COMPOSITEDOORS OF FAIRINGS DO NOT GIVE AN ELECTRICAL BOND.




3. Open the Refueling Station Door installed on the left wing.4. Open the Refueling Station Door installed on the right wing if it is necessary.



6. In the event that the FUEL QTY display does not operate, do these steps:a. Wait 60 seconds after you open the Refueling Station door, to see if the FUEL QTY displays

will come on.NOTE : Make sure the total fuel legend "TF" shows on the TOTAL/BACKUP display.

b. If the FUEL QTY display does not show the fuel quantity, put the POWER switch on the IRPto the BATT position.

c. Make sure the FUEL QTY display(s) shows the fuel quantity.



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d. If one or more of the FUEL QTY displays continue to be off, refer to "Fuel Measuring StickProcedures" in Section 25.03.

25.01.6 Defueling

NOTE : Product defueled from an aircraft for purposes other than contamination should be returned tothe airline from which it was removed. Defueled product may not be delivered to anothercompany’s aircraft without its approval. Defueling aircraft directly into joint use fueling systemis not authorized unless a procedure has been unanimously approved by all system users.

A. The defuel system moves fuel from the airplane tanks to the refuel station. It also moves fuel fromone airplane tank to another (tank-to-tank transfer). There are three ways to get fuel out of the tanks.1. Pressure defuel

a. The pressure defuel system uses aircraft fuel boost pumps, or fuel override/jettison pumps,to remove fuel from the fuel tanks.

b. At the flight deck, the fuel panel P5 (refer to Figure 25.01-8) has switches that control thefuel boost pumps and the transfer valves.

Figure 25.01-8: Defuel Operation

c. Each boost pump switch on the P5 panel has two lighted indications:(1) An ON light comes on when the switch is selected to the ON position and the pump

comes on.



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(2) A PRESS light comes on when there is low pump pressure. The PRESS light shouldgo off as soon as the switch is turned on.

d. During the defueling procedure, the fuel flows through the engine fuel feed manifold, throughthe defuel valve, into the refuel manifold and out of the refuel adapters into the fueling vehicles,or through refueling valves into another fuel tank in the airplane. Refer to Figure 25.01-9.NOTE : When defueling into a tanker truck, the refuel valve switches at the P28 integrated

Refuel Panel (IRP) at the right wing fueling station (refer to Figure 25.01-8) mustremain closed to prevent fuel from recirculating within the aircraft tanks.

2. Suction defuelinga. Suction defueling may be accomplished without operating the wing tank boost pumps. Fuel

flows from the bypass valves into the engine feedmanifold. It then flows through the crossfeedvalves into the refuel valve and goes into the refuel/jettison manifold. From the refuel/jettisonmanifold, it flows through the refueling station adapters and into the fuel vehicle. Refer toFigure 25.01-9.

3. Tank-to-tank transfera. Tank-to-tank transfer requires the use of the defuel valve, refuel valves, engine fuel spar

valves, engine fuel crossfeed valve and wing boost pumps. This procedure is basically thesame as pressure defueling except that the fuel is not placed into the fueling vehicle. It isplaced into another tank by opening the refuel valve of the tank that the fuel should betransferred into.CAUTION: DURING A TANK-TO-TANK TRANSFER, THE FUELING VEHICLE HOSE

ADAPTER MUST BE DISCONNECTED FROM THE AIRCRAFT PRIORTO THE START OF THE TRANSFER TO PREVENT ACCIDENTALTRANSFER OF FUEL FROM THE WING TO THE FUELING VEHICLE.

B. Pressure defuelingWARNING: DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TO




3. DO NOT PUT GROUND EQUIPMENT BELOW THEWINGTIPS DURING THEREFUELING OPERATION. THE WEIGHT OF THE FUEL WILL CAUSE THEWINGSTOMOVEDOWNANDTHEWINGTIPSMOVETHEMOST. BECAUSETHEFUELTANKSAREVENTEDTHROUGHTHEWINGTIPS, ADANGEROUSAND EXPLOSIVE MIXTURE CAN OCCUR IN THAT AREA.

4. DO NOT START OR SHUT DOWN APU SHOULD A FUEL SPILL OCCUR.5. DO NOT OPERATE THE LEADING EDGE SLATS. ACCIDENTAL SLAT


CAUTION: DO NOT REMOVE ELECTRICAL POWER WHILE TRANSFERRINGTANK-TO-TANK. IFYOUREMOVEELECTRICALPOWERWHILETRANSFERRING,THE REFUELING VALVES WILL CLOSE AND MAY DAMAGE EQUIPMENT.



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Figure 25.01-9: Defuel-Functional Description-Fuel Flow

1. External or APU electrical power should be used for pressure defueling operations. If external orAPU power sources are not available, the airplane battery may be used as a power source.



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2. Connect a bonding cable to an approved electrical grounding or bonding connection on theairplane. Refer to Figure 25.01-4.

3. Open the Refueling Station Door. Refer to Figure 25.01-8, View A.4. Connect the fuel nozzles to one or more fueling adapters.5. Move the valve on the fueling nozzle hose to the OPEN position.

a. Place the REFUEL/DEFUEL handle of the fueling adapter to the DEFUEL position if defuelinginto a fueling vehicle.


door.b. If the FUEL QTY display(s) does not show the fuel quantity, put the POWER switch of the

IRP to the BATT position.c. Make sure the FUEL QTY displays show the fuel quantity.d. If the IRP FUEL QTY displays continue to be off, you may use the fuel panel (P5) in the

cockpit to defuel/transfer fuel from the airplane.CAUTION: IF THE FUELING PANEL (P5) IN THE COCKPIT IS USED TO DEFUEL

THE AIRCRAFT, A SECOND PERSON IS REQUIRED FORCOMMUNICATION. ONE PERSON MUST BE IN THE COCKPIT WITHCOMMUNICATION TO THE PERSON AT THE GROUND REFUELINGPANEL.



8. During the test, a test pattern shows in the fuel quantity indicators and the valve position indicationlights come on. If a fuel quantity indicator fails the test, all of its LEDs go off.

9. Make sure each blue valve position light comes on and then goes off.a. Determine fuel load in each tank. Record FUEL QUANTITY in each tank in the "GAUGE

READING BEFORE FUELING - LBS" spaces on the fuel slip. Determine the amount of fuelto be removed from the aircraft by calculating the difference between "GAUGE READINGBEFORE FUELING - LBS" and "GATE RELEASE QUANTITY REQUIRED - LBS" on thefuel slip. The total of that calculation will give the amount of fuel to be removed.

10. Move the DEFUEL VALVE switch on the IRP to OPEN position.11. Open the CROSSFEED valve switch on the P5 cockpit fueling panel. A lighted bar should appear

across the CROSSFEED switch when activated.WARNING: DO NOT OPERATE A FUEL PUMP IF THE AMBER PRESS LIGHT COMES

ON AND STAYS ON. IT CAN CAUSE THE IGNITION OF THE FUEL FUMESIN THE TANK WHICH WILL CAUSE A FIRE OR EXPLOSION. FIRES ANDEXPLOSIONS CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TOEQUIPMENT.

12. To operate any of the fuel pumps, you must be in the flight compartment to continuously monitorthe fuel quantity and the low pressure indication in the applicable tank. Immediately set theapplicable fuel pump switch-light(s) to OFF if the amber PRESS light comes on and stays on.NOTE : Extended running of the fuel pumps with the PRESS light on may set flight deck alerts

requiring maintenance personnel troubleshooting prior to flight, as well as, flight delays.



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13. From (P5) panel, turn on the wing boost pumps in the tanks that are to be defueled. Refer toFigure 25.01-8. The ON light in the switch should come on and the PRESS light should go off.

14. Start defueling the airplane.15. When the desired level of fuel in each tank is reached, turn off the wing boost pump of that tank.16. If defueling with the center tank pumps:

a. Push the L and R CENTER PUMPS switch-lights to the off position when the necessaryquantity of fuel is removed.

b. Keep a minimum of 5500 lb (2495 kg) of fuel in the center tank.NOTE : This fuel quantity is necessary to make sure that the pump INLET is in the fuel.

c. If the center tank fuel is less than 5500 lb (2495 kg), continuously monitor the fuel quantityand the low pressure indication in the center tank.(1) Immediately set the L and R CENTER PUMPS switch-lights to the off position if the

amber PRESS light comes on and stays on.NOTE : To prevent the pumps from dry running, the center tank pumps should be

turned off when the minimum fuel quantity remains in the tank.

(2) Make sure that the applicable Engine Indicating and Crew Alerting System (EICAS)status message does not show on the EICAS display for the applicable pump:a) FUEL PUMP CENTER L.b) FUEL PUMP CENTER R.

17. When all tanks are defueled to the required level, move the defuel valve switch on the IRP panelto the CLOSED position. Make sure the actual fuel load after fueling matches the required loadas indicated on the fueling slip at the "GATE RELEASE QUANTITY REQUIRED - LBS" column.

18. Move the fueling nozzle valve to the closed position.19. Remove the fueling nozzle from the airplane.

a. Place the REFUEL/DEFUEL handle of the fueling adapter to the REFUEL position.20. Disconnect the bonding cable from the airplane.21. Stow the fueling adapter on the fueling vehicle.22. If the battery power switch is in the BATT position, put the battery power switch to the NORMAL

position.23. Close the Refueling Station Door.

C. Suction defueling1. Suction defueling is the same as the pressure defueling procedure except you do not turn on the

wing boost pumps. It will still require that you turn on the cross feed valve switches on the cockpit(P5) panel.NOTE : This procedure will be slower than pressure defueling. It may be desirable to use a

combination of both pressure and section at the same time to defuel the airplane faster.

2. Suction defueling stops when one of the bypass valve inlets is uncovered. Thus, if the tanks donot become empty at the same time, there may be fuel remaining in one or more tanks.

D. Tank-to-tank transfer1. Tank-to-tank transfer is the same as pressure defuel, with the following exceptions:

a. Do not connect the fueling adapter hose from the fueling vehicle to the airplane.b. You must select which tank to transfer the fuel into by opening the refuel valve on the IRP.



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WARNING: DONOTOPERATEAFUELPUMP IF THEAMBERPRESSLIGHTCOMESON AND STAYS ON. IT CAN CAUSE THE IGNITION OF THE FUELFUMES IN THE TANK WHICH WILL CAUSE A FIRE OR EXPLOSION.FIRESANDEXPLOSIONSCANCAUSE INJURIES TOPERSONNELANDDAMAGE TO EQUIPMENT.

c. To operate any of the fuel pumps, you must be in the flight compartment to continuouslymonitor the fuel quantity and the low pressure indication in the applicable tank. Immediatelyset the applicable fuel pump switch-light(s) to OFF if the amber PRESS light comes on andstays on.NOTE : Extended running of the fuel pumps with the PRESS light on may set flight deck

alerts requiring maintenance personnel troubleshooting prior to flight, as well as,flight delays.

d. If defueling with the center tank pumps:(1) Push the L and R CENTER PUMPS switch-lights to the off position when the necessary

quantity of fuel is removed.(2) Keep a minimum of 5500 lb (2495 kg) of fuel in the center tank.

NOTE : This fuel quantity is necessary to make sure that the pump INLET is in thefuel.

(3) If the center tank fuel is less than 5500 lb (2495 kg), continuously monitor the fuel quantityand the low pressure indication in the center tank.a) Immediately set the L and R CENTER PUMPS switch-lights to the off position if the

amber PRESS light comes on and stays on.NOTE : To prevent the pumps from dry running, the center tank pumps should

be turned off when the minimum fuel quantity remains in the tank.

b) Make sure that the applicable EICAS status message does not show on the EICASdisplay for the applicable pump:(1) FUEL PUMP CENTER L.(2) FUEL PUMP CENTER R.

e. If the tank you are defueling is to be emptied, let the wing boost pump(s) operate until thePRESS light of the cockpit fueling panel for that tank comes on. At that point, turn off thewing boost pump(s) switch(es).

f. If the tank is not to be completely defueled, turn off the IRP refuel valve switch at the desiredlevel.

END



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Section 25.02 - Fuel Sump - Operation25.02.1 General

A. Fuel Tank Sump Locations1. There are two sump drain valves installed in the center fuel tank, one sump drain valve in each

main fuel tank and one sump drain valve in each surge tank. There are six sump drain valves intotal installed on the airplane.

B. Fuel Tank Sump Check1. Aircraft fuel sumping is the responsibility of Maintenance personnel and is to be in accordance

with scheduled maintenance checks.



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Figure 25.02-1: Fuel Sump Drain Valve Servicing



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Figure 25.02-2: Fuel Sump Drain Valve Installation

END



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Section 25.03 - Fuel Quantity Measuring Stick - Servicing25.03.1 General

A. Introduction1. The Model 777-300ER airplane has magnetic type dripless fuel measuring sticks. Eight fuel

measuring sticks are installed in each main fuel tank and 2 fuel measuring sticks are installed ineach side of the center fuel tank. In this procedure, the fuel measuring sticks are referred to asfuel sticks 1 and 2 for the center fuel tank and fuel sticks 3 through 10 for the main fuel tanks.Refer to Figure 25.03-1 and Figure 25.03-2.

2. This procedure contains the information necessary to find the fuel quantity in each fuel tank withthe use of the fuel measuring sticks. To find the fuel quantity, the airplane attitude must be known.When the airplane is at a level attitude (-0.54° "nose down and 0.00°" wing roll.)

B. Airplane Attitude1. The airplane pitch and roll attitude must be known in addition to the fuel height to find the fuel

quantity in each fuel tank. Find the airplane attitude with one of these methods:a. Airplane pitch and roll is displayed on the center tank EICAS maintenance page in the flight

deck. This pitch and roll is determined from the Airplane Data Inertial Reference Unit (ADIRU)acceleration data and is displayed to the nearest tenth of a degree. Have the Flight Crew orMaintenance do the steps that follow if electrical power is available.(1) Make sure the ADIRU is powered and aligned. Do this task:

a) Air Data Inertial Reference Unit - Alignment(2) Look at page 2 of the FUEL QTY maintenance page on EICAS.

a) Make a record of the PITCH and ROLL indications.b. Each airplane has a plumb bob attachment and a leveling scale, which are used to find the

airplane attitude. The scale is graduated in degrees for pitch (TAIL DOWN or NOSE DOWN)and wing roll (LEFTWING DOWN or RIGHTWING DOWN.) The plumb bob attachment andthe leveling scale are installed in the right main gear wheel well.

c. Each airplane also has pitch and roll inclinometers which are used to find the airplane attitude.The pitch inclinometer is graduated in degrees of NOSE UP and NOSE DOWN. The rollinclinometer is graduated in degrees of LEFT WING UP and DOWN, RIGHT WING UP andDOWN. The inclinometers are installed in the wheel well for the nose landing gear.

2. It is important to know the sign conversion for pitch and roll in the conversion tables. Positive rollis wing high for the left or right wing. When the roll is positive for one wing, it is negative for theother wing. Positive pitch is nose high.a. For example, if the airplane attitude is 0.46° nose up and 2.0° left wing down, the fuel load

in the left wing will be found in the table labeled Pitch=0.46 Degrees and in the column labeled2.00 for roll attitude. The fuel load in the right tank will be found on the same page for pitchand in the column labeled 2.00 for roll attitude.

C. Fuel Level Measurement1. The fuel stick consists of a float assembly, a stick housing and the measuring stick. The float

assembly contains a magnet and floats on the fuel. The measuring stick contains a steel armatureat its top end that is free to slide up and sown in the stick housing. When the steel armature is inthe magnetic field of the magnet in the float, the float will hold the stick from its top end. Thebottom of the stick will extend from the lower wing surface. The stick is graduated in linear unitsand gives a visual indication of the fuel height in the tank. The stick measurement is read wherethe lower wing surface intersects the fuel stick.



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2. The fuel stick measures the fuel height in the applicable fuel tank, which is then converted topounds in the conversion tables. The range for each fuel stick is shown in Figure 25.03-6. Theminimum reading in Figure 25.03-6 corresponds to the top unit on the fuel stick. The maximumreading corresponds to the bottom unit on the fuel stick.

3. The fuel sticks are installed through the lower wing surface of each fuel tank. Fuel sticks 1 and2 are installed through the bottom wing skin in the left and right center fuel tank. Fuel sticks 3through 10 are installed in fuel tank access doors in each main fuel tank.

4. The fuel sticks are unlocked from their base by pressing lightly and turning the stickcounterclockwise 90 degrees. The stick must then be lowered through the magnet and then raisedslowly on the fingertip or palm until it is captured by the magnet in the float. Once the stick iscaptured by the magnet, read it without touching the stick. The stick measurement is read at thelower edge of the retainer. To replace the stick, push it into the housing and turn it clockwise untilit locks in its place.

D. Description of Tables1. The conversion tables make up the main body of this procedure. The tables contain fuel load in

pounds versus fuel stick readings, corrected for airplane attitude. These tables were generatedby Boeing’s P187 Fuel Tank Model to simulate the fuel tanks and their contents at various airplaneattitudes. The results are a determination of fuel height at each fuel stick location and thecorresponding fuel volume in the fuel tank, based on 6.76 lbs./gal.NOTE : When actual fuel density deviates greatly from the nominal chart value of 6.76 lbs./gal.,

it may be desirable to convert the chart derived pound value to "actual pound" valuebased on local station density. Refer to Section 10.01.

2. The airplane attitude must be in the limits shown above in order to use the conversion tables. Ifthe airplane attitude is not within these limits, the fuel quantity cannot be determined accuratelywith this procedure.a. Pitch = (-2.54° to +1.46°)b. Wing Roll = (-2.0° to +2.0°)

25.03.2 Find the Fuel Quantity (Refer to Figure 25.01-1)

A. General1. To find the fuel level, use a fuel stick that shows best mid-range quantity.

B. Procedure1. Park the airplane on a level surface.2. Have Maintenance do these steps to find the airplane attitude.

NOTE : The airplane attitude will change while fuel is loaded. The airplane attitude and fuelquantity should be checked after the fuel is loaded to get the correct fuel quantity.

3. Have Maintenance do these steps if electrical power is not available:a. Make sure the landing gear downlock pins are installed on the nose and main landing gear.

Do this task: Landing Gear Downlock Pins Installation (Reference AMM TASK32-00-30-480-801.)WARNING: USETHECORRECTPROCEDURETOOPENTHEDOORS. THEDOORS

OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONSOR DAMAGE TO EQUIPMENT.

b. Open the landing gear doors. Do this task: Landing Gear Ground Door Release SystemOperation (Open the Doors) (Reference AMM TASK 32-00-40-860-802.)



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WARNING: USE THE CORRECT PROCEDURE TO INSTALL THE DOOR LOCKS.THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURYTO PERSONS OR DAMAGE TO EQUIPMENT.

c. Install the door locks. Do this task: Landing Gear Door Safety Pins Installation (ReferenceAMM TASK 32-00-15-480-801.)

d. Look at the plumb bob and the leveling scale in the right wheel well to get the pitch and rolldata. Refer to Figure 25.03-4, or

e. Look at the Leveling Inclinometers in Nose Wheel Well. Refer to Figure 25.03-5.4. Make sure the airplane attitude is within these limits:

a. -2.54° to +1.46° pitchb. -2.0° to +2.0° wing rollc. If the airplane is not within the above limits, call Aircraft Maintenance



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Figure 25.03-1: Fuel Measuring Sticks - Left Wing



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Figure 25.03-2: Fuel Measuring Sticks - Right Wing



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Figure 25.03-3: Fuel Measuring Sticks - Assembly



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Figure 25.03-4: Airplane Leveling Plumb Bob and Scale



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Figure 25.03-5: Aircraft Leveling Inclinometers

5. If the approximate fuel quantity in the fuel tank is known, refer to Figure 25.03-6 to find which fuelstick to use.NOTE : Each fuel stick has a range of a minimum and a maximum fuel quantity that you can

measure.



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Figure 25.03-6: Fuel Measuring Stick Range

6. If the approximate fuel quantity in the fuel tank is not known, start at the most outboard fuel stickfor the applicable fuel tank and pull down the fuel sticks until you find the correct fuel stick thatwill give the best mid-range reading.

7. Use a screwdriver and push up lightly on the latch of the fuel stick and turn the screwdriver slot90° counterclockwise to release the stick.

8. Carefully lower the fuel stick to its fully extended length.9. Use a fingertip (or the flat palm of your hand) to slowly lift the fuel stick until resistance is felt.

NOTE : Resistance occurs when the float magnet catches the steel armature of the fuel stick.The fuel stick is held in this position by the magnet on the float.

10. Release the fuel stick.11. Read the fuel level at the lower edge of the retainer. Refer to Figure 25.03-3.

a. If the fuel level is not in the correct range for the fuel stick, go to the fuel stick with the fuellevel that is in mid-range.

12. Lower and read the fuel stick three times to make sure the fuel level you read is repeatable.NOTE : When fuel quantity is verified by measuring stick, measuring shall be performed by the

fuel servicemen and shall be monitored by cockpit crew member.

13. Push the fuel stick up into the housing.14. Push up lightly on the latch of the fuel stick with a screwdriver and turn the screwdriver slot 90°

clockwise until the fuel stick locks into position.15. Go to the correct fuel stick conversion table for the applicable fuel stick number. (Reference AMM

12-11-07-970-006.)NOTE : The fuel sticks are numbered inboard to outboard as stick no. 3 through stick no. 10,

on the left and right wings. The fuel sticks for the center tank are numbered 1 and 2.

16. Find the page with the correct fuel stick number and pitch attitude.



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NOTE : Pitch attitude is shown as NOSEUP (+) and NOSEDOWN (-) for the pitch inclinometer.NOSE UP (+) is the same as TAIL DOWN on the airplane leveling scale.

17. Find the correct column for the wing roll attitude, measured in degrees.18. Find the fuel stick unit in the conversion table that agrees with actual (measured) fuel stick value.19. Read across from the fuel stick unit in the conversion table to find the airplane roll attitude, then

read down from the correct wing roll attitude to find the fuel quantity in pounds.20. The fuel quantity shown is the quantity of usable fuel in the applicable fuel tank.

C. Put the airplane back to its usual condition.WARNING: USETHECORRECTPROCEDURETOREMOVETHEDOORLOCKS. THEDOORS

CAN OPEN AND CLOSE QUICKLY AND CAUSE INJURY TO PERSONS ORDAMAGE TO EQUIPMENT.

1. Remove the door lock. Do this task: Landing Gear Door Safety Pins Removal.WARNING: USE THE CORRECT PROCEDURE TO CLOSE THE DOORS. THE DOORS

OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS ORDAMAGE TO EQUIPMENT.

2. Close landing gear doors.












Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch and roll).



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b) Circle the stick(s) utilized after fueling (all aircraft) and applicable inner/ outer cell(Airbus 319/320 aircraft only).

c) Record the units/inches read from the applicable stick(s) in the after fueling spaces.d) Record the after fueling quantity from the applicable stick chart in pounds on the




b. When using method 3, perform the following:NOTE : When using Method 3 to verify all tank quantities after fueling for an inoperative

fuel tank quantity indication channel fault, record the actual before quantity tankgauge readings in lieu of zero (0) for each respective tank on a separate InoperativeFuel Quantity Indicator Service Record.

(1) Empty the affected tank by defueling or transferring all remaining fuel to other tanks.Refer to Section 25.01.6.

(2) Record the before fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (for example, L,













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25.03.3 Fuel Measuring Stick Charts

A. Refer to B777-300ER Fuel Measuring Stick Charts as follows:1. Access the Stick Charts at http://me.aa.com/manuals/fw/FuelingStickCharts/#z.

END



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Table of contents

26.01 FUELING MANUAL - B787GENERAL..........................................................................................................................1PRESSURE REFUELING (IN COLD WEATHER).............................................................2PRESSURE REFUELING - WITH A SET FUEL QUANTITY (AUTOMATIC)....................6PRESSURE REFUELING - WITH NO SET FUEL QUANTITY.......................................12REFUELING - (WITH A FUEL QUANTITY INDICATION NOT IN OPERATION)............15PRESSURE REFUELING - (WITH BATTERY POWER).................................................18TANK-TO-TANK FUEL TRANSFER................................................................................20DEFUELING....................................................................................................................23

26.02 FUEL SUMP - OPERATION



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NOTE : The use of JP-4 or Jet B is prohibited on all B787 aircraft.

WARNING: 1. DO NOT OPERATE THE HF COMMUNICATION SYSTEM DURING REFUELINGOPERATIONS. A FIRE OR EXPLOSION CAN OCCUR.

2. THE SATCOM SYSTEMCAN BEOPERATED DURING A REFUELINGOPERATION.

3. GROUND EQUIPMENT MUST NOT BE POSITIONED UNDER WING TIPS DURINGFUELING OPERATION.

4. FUELING VEHICLE MUST BE PROPERLY BONDED TO AIRCRAFT BEFORE ANYFUELING/DEFUELING OPERATION.

5. WHEN THERE IS AN INACCURATE/INOPERATIVE OR A SUSPICIONOF AGAUGENOT INDICATING PROPERLY,STOP FUELING AND NOTIFY AIRCRAFTMAINTENANCE IMMEDIATELY.

NOTE : If a fuel component(s) is currently on MEL placard as being inoperative, aircraft maintenancedoes not need to be notified unless specific procedures during fueling operations require theattention of aircraft maintenance.

WARNING: 1. IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION, NOTIFY AIRCRAFT MAINTENANCE IMMEDIATELY. DO NOT STARTOR RESUME FUELING OPERATIONS UNTIL CORRECTIVE ACTION HAS BEENTAKEN.


3. DO NOT START REFUELING IF A FIRE OR ENGINE OVERHEAT WARNING EICASMESSAGE SHOWS.

4. DONOTSTARTREFUELING IF ANYPARTOF THE LANDINGGEAR ISUNUSUALLYHOT.

5. DO NOT REMOVE ELECTRICAL POWER FROM THE AIRCRAFT.

NOTE : If you remove electrical power, the refueling valves that are open will stay open. The refueloperation will not stop when the fuel tanks are full. This could cause an overfill or a fuel spill.

CAUTION: 1. DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUEL NOZZLE.IF YOU USE MORE THAN 50 PSI FUEL PRESSURE, YOU CAN CAUSE DAMAGE TOTHE REFUELING SYSTEM COMPONENTS.

2. DO NOT OPERATE THE HYDRAULIC SYSTEMS UNLESS THE FUEL LEVEL ISHIGHER THAN THE HEAT EXCHANGERS. WITHOUT SUFFICIENT FUEL, THE HEATEXCHANGER WILL BECOME TOO HOT. DAMAGE TO THE HYDRAULIC SYSTEMWILL OCCUR.

A. Refueling Station1. The refueling stations are installed in the leading edge, just outboard of the left engine.2. The refueling station contains the Refuel Control Panel (RCP), refuel adapters, bonding points,

and lights.3. Markers installed on the refueling station door have refueling information and cautions.

B. Surge Tank Overfill System



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1. There is a surge tank outboard of each main fuel tank. The surge tanks catch fuel when a fueltank fills to more than its full capacity.

C. Fuel Loading Limits1. The fuel system has two main tanks and one center tank. There is also a vent surge tank located

in each wing, outboard of the wing tank.a. For all B787 aircraft:

(1) Center tank has an approximate volume of 22,200 USgal.(2) Main (wing) tanks each have an approximate volume of 5,570 USgal.


2. You can refuel all the tanks at the same time or you can refuel them one tank at a time.NOTE : The usual procedure for refueling is to put no fuel in the center tank unless you fill the

left and right main tanks to their main capacity.

3. Refuel the left and right main tanks with equal quantities of fuel.D. Aircraft Attitude:

1. Make sure that the aircraft has a ground attitude of -0.78° ± 2.0° (nose-down) pitch and 0.0° ±2.0°roll.NOTE : A ground attitude of -0.78° (nose-down) pitch and 0.0° roll will make sure that the fuel

quantity indications are accurate.

E. When thunderstorms or lightning are in the area (approximately a 10 mi (16 km) radius), you muststop the refueling operation.

F. Refuel operations must stop if there are strong wind conditions.NOTE : Strong wind conditions can cause static electricity to collect. Large quantities of static

electricity can collect on support equipment while parked, from the movement of dustparticles and air currents during strong wind conditions.

NOTE : Strong wind conditions can also cause the unwanted movement of items or equipment,which can cause injury to personnel or damage to the aircraft.

26.01.2 Pressure Refueling (In Cold Weather)

A. General1. This procedure is used to refuel the aircraft in cold weather.

a. A small quantity of hydraulic fluid can leak into the fuel tanks at very low temperatures.(1) The procedure will remove the hydraulic fluid from the fuel tank surfaces.

b. These are the two conditions for which the procedure is used:(1) The outside air temperature is less than -45°F (-43°C) before startup of the hydraulic

system, or(2) The aircraft has been stored or parked overnight in an outside air temperature of less

than -55°F (-48°C) for more than 15 days.c. The steps of this task cannot be fully completed from the refuel control panel.

(1) Access to the flight compartment is necessary for some parts of the procedure.d. The procedure assumes that power will be supplied to the hydraulic systems and other

aircraft systems from the APU.B. Prepare for the Refuel Operation

1. Make sure that the three hydraulic systems are pressurized.



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a. If they are not pressurized, do these tasks:(1) Hydraulic System - Left (with an Electric Motor Pump) - Pressurization, AMM

B787-A-29-11-00-18D-210B-A(2) Hydraulic System - Center (with an Electric Motor Pump) - Pressurization, AMM

B787-A-29-11-00-20D-210B-A(3) Hydraulic System - Right (with an Electric Motor Pump) - Pressurization, AMM

B787-A-29-11-00-19D-210B-A2. Do this procedure to move all fuel from the main tanks to the center tank: Tank-to-Tank Fuel

Transfer - Operation. Refer to Section 26.01.7.a. Do these steps to make sure that the APU continues to operate:

(1) Do not let the fuel quantity in the left main tank become less than 700 lb (400 kg) whilethe APU uses fuel from the left main tank.

(2) When there is a minimum of 9,000 lb (4,100 kg) or fuel in the center tank, do these steps:a) Put the L CENTER PUMP switch on the P5 Overhead Panel, to the ON position.b) Continue to move the fuel from the left and right main tanks until they are empty.

3. Connect a bonding cable from the fueling source to an approved electrical ground or bondingconnection on the aircraft.a. Open this access panel: 521FB - Fixed LE Outboard of Nacelle Strut Panel (Refer to Figure

26.01-1.)b. Make sure that the fuel quantity indicators and load select displays come on within 10 seconds

after you open the access panel.(1) Make sure that the fuel quantity indicators show the fuel quantities.(2) Make sure that the lower load select display shows: "0.0 lb" "LOAD SEL."

c. If the Refuel Control Panel (RCP) does not come on, put the POWER switch on the RCP tothe BATTERY position.(1) Make sure that the fuel quantity indicators show the fuel quantities.(2) Make sure that the lower load select display shows: "0.0 lb" "LOAD SEL."

d. If the RCP continues to be off, do this task: Pressure Refueling (with Battery Power) - Fueling.Refer to Section 26.01.6.WARNING: MAKE SURE THAT THERE IS NO TENSION ON THE HOSE. THE HOSE

MUSTHANGFREELYFROMTHEREFUELADAPTER,WITHNOFORCEON IT. TENSION ON THE HOSE CAN CAUSE DAMAGE TO THE FUELRECEPTACLE AND CAUSE THE HOSE TO DISCONNECT. INJURIESTO PERSONNEL AND DAMAGE TO EQUIPMENT CAN OCCUR.

4. Connect the refuel nozzles to the refuel adapters.C. Prepare the Refuel Control Panel (RCP)

1. Push and hold the TEST switch to the PANEL position.NOTE : This does a test of the fuel quantity indicators, load select displays, the overfill indication

light, and the valve position lights.

a. Make sure that these fuel quantities show on the three fuel quantity indicators while you holdthe TEST switch in the PANEL position:(1) RIGHT - 88.8 lbs.(2) CENTER - 88.8 lbs.(3) LEFT - 88.8 lbs.



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b. If one of the displays does not come on, use the applicable load select display to see thefuel quantity for that tank.(1) If the applicable load select display does not show that tank's fuel quantity, then do this

task to refuel the aircraft: Pressure Refueling (with a Fuel Quantity Indication Not inOperation). Refer to Section 26.01.5.

c. Make sure that all of the LEDs on the load select displays come on.NOTE : The load select displays will go back to their usual condition when you release the

TEST switch.

d. Make sure that the six blue refuel valve position lights come on and then go off.e. Make sure that the red OVERFILL indication light comes on and then goes off.f. Release the TEST switch.

D. Pressure Refueling (in Cold Weather) Procedure1. Do this task to make the total fuel quantity in the center tank equal to 115,400 lb (52,400 kg):

Pressure Refueling (with a Set Fuel Quantity). Refer to Section 26.01.3.NOTE : This quantity of fuel is sufficient to flush unwanted hydraulic fluid from the fuel tank

structure.

2. Do this task to move fuel from the center tank to the left main tank, with the subsequent changes:Tank-to-Tank Fuel Transfer - Operation. Refer to Section 26.01.7.CAUTION: BE CAREFUL WHEN YOU ADD FUEL TO A FUEL TANK WITH REFUEL

VALVES THAT DO NOT OPERATE. IF YOU ADD TOO MUCH FUEL OR ADDFUEL TOO QUICKLY, FUEL CAN SPILL FROM THE SURGE TANK VENT.SPILLED FUEL CAN CAUSE INJURY TO PERSONNEL AND DAMAGE TOEQUIPMENT.

a. After you start the fuel transfer operation, do this step:NOTE : This will keep one refuel valve open after the left main tank is full. If you do not do

this before the left main tank fills, the valves will automatically close. If this occurs,you cannot open them again until you remove some fuel from the left main tank.

(1) Action/Condition: Open this circuit breaker:

LocationCBDesignationPanel

CE2821807REFUEL VLVCLOSE-LIB

CB1CCIRCUIT BREAKER INDICATIONAND CONTROL

b. Do these steps after the fuel quantity in the left main tank is 30,000 lb (13,600 kg):(1) Refer to this task to operate the fuel sump drain valve for the left surge tank (AMM

B787-A-12-11-02-01A-228A-A Figure 1): Surge Tank Fuel Check - Defueling, AMMB787-A-12-11-02-02A-221A-A.a) Do not complete the steps to defuel the adjacent main fuel tank.

(2) Continue to hold the sump drain valve open.(3) Stop the fuel transfer operation when fuel drains from the left surge tank sump drain

valve.NOTE : The fuel quantity in the left main tank will be approximately 39,000 lb (17,700

kg).

3. Set the pressure at the fueling cart to less than 20 psi (138 kPa).NOTE : This will help to make sure that fuel does not spill out of the surge tank vent.



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a. Do this task to add approximately 680 lb (300 kg) of fuel to the left main fuel tank: PressureRefueling (with No Set Fuel Quantity) - Fueling. Refer to Section 26.01.4.NOTE : This will let a small quantity of fuel spill into the left surge tank. The necessary

quantity of fuel will be added in approximately 3 minutes at the lowered fuelpressure.

(1) Action/Condition: Close this circuit breaker:


CE2821807REFUEL VLVCLOSE-LIB


4. Do this task to move fuel from the center tank to the right main tank, with the subsequent changes:Tank-to-Tank Fuel Transfer - Operation. Refer to Section 26.01.7.CAUTION: BE CAREFUL WHEN YOU ADD FUEL TO A FUEL TANK WITH REFUEL

VALVES THAT DO NOT OPERATE. IF YOU ADD TOO MUCH FUEL OR ADDFUEL TOO QUICKLY, FUEL CAN SPILL FROM THE SURGE TANK VENT.SPILLED FUEL CAN CAUSE INJURY TO PERSONNEL AND DAMAGE TOEQUIPMENT.

a. After you start the fuel transfer operation, do this step:NOTE : This will keep one refuel valve open after the right main tank is full. If you do not

do this before the right main tank fills, the valves will automatically close. If thisoccurs, you cannot open them again until you remove some fuel from the rightmain tank.

(1) Action/Condition: Open this circuit breaker:


CE2821811REFUEL VLVCLOSE-RIB


b. Do these steps after the fuel quantity in the right main tank is 30,000 lb (13,600 kg):(1) Refer to this task to operate the fuel sump drain valve for the right surge tank (AMM

B787-A-12-11-02-01A-228A-A Figure 1): Surge Tank Fuel Check - Defueling, AMMB787-A-12-11-02-02A-221A-A.a) Do not complete the steps to defuel the adjacent main fuel tank.

(2) Continue to hold the sump drain valve open.(3) Stop the fuel transfer operation when fuel drains from the right surge tank sump drain

valve.NOTE : The fuel quantity in the right main tank will be approximately 39,000 lb (17,700

kg).

5. Set the pressure at the fueling cart to less than 20 psi (138 kPa).NOTE : This will help to make sure that fuel does not spill out of the surge tank vent.

a. Do this task to add approximately 680 lb (300 kg) of fuel to the right main fuel tank: PressureRefueling (with No Set Fuel Quantity) - Fueling. Refer to Section 26.01.4.NOTE : This will let a small quantity of fuel spill into the right surge tank. The necessary

quantity of fuel will be added in approximately 3 minutes at the lowered fuelpressure.



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(1) Action/Condition: Close this circuit breaker:


CE2821811REFUEL VLVCLOSE-RIB


6. Do this task to remove sufficient fuel from the main fuel tanks to let the fuel drain from the surgetanks: Tank-to-Tank Fuel Transfer - Operation. Refer to Section 26.01.7.a. Move fuel from the main tanks to the center tank until the fuel quantity in each main tank is

36,600 lb (16,600 kg).NOTE : This will make the fuel quantity in each main tank less than the Volumetric Shut

Off (VSO) quantity.

7. Do this task to fill the main tanks to the VSO quantity from the center tank again: Tank-to-TankFuel Transfer - Operation. Refer to Section 26.01.7.

8. If it is necessary, continue to add fuel to the center fuel tank.a. Do the applicable task:

(1) Pressure Refueling (with a Set Fuel Quantity) - Fueling. Refer to Section 26.01.3.(2) Pressure Refueling (with No Set Fuel Quantity) - Fueling. Refer to Section 26.01.4.

E. Disconnect the fueling nozzles.F. Close this access panel: 521FB - Fixed LE Outboard of Nacelle Strut Panel. (Refer to Figure 26.01-1.)G. Disconnect the bonding cable that you installed between the fueling source and the aircraft.

26.01.3 Pressure Refueling - With a Set Fuel Quantity (Automatic)

A. General1. This procedure sets the quantity of fuel that you will put on the aircraft. The refueling operation

will stop when the fuel quantity is equal to the set quantity.B. Procedure

WARNING: 1. DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TOTHE AIRCRAFT DURING ATMOSPHERIC ELECTRICAL ACTIVITY OR STRONGRADIOACTIVEFIELDS. LIGHTNINGSTRIKEANDHIGHDISCHARGECURRENTSCAN CAUSE SEVERE INJURY.

2. DO NOT OPERATE THE HF COMMUNICATIONS SYSTEM OR THEWEATHERRADAR DURING REFUELING OPERATIONS. A FIRE OR EXPLOSION CANOCCUR.

3. DO NOT PUT GROUND EQUIPMENT BELOW THE WINGTIPS DURING THEREFUELING OPERATION. THE FUEL TANKS ARE VENTED THROUGH THEWINGTIPS. ADANGEROUSANDEXPLOSIVEMIXTUREAROUNDTHEWINGTIPCAN OCCUR.


5. DO NOT OPERATE THE LEADING EDGE SLATS. ACCIDENTAL SLATOPERATION COULD CAUSE INJURY TO PERSONS AND DAMAGE TOEQUIPMENT.

6. ATTACHBONDINGCABLESONLY TOSPECIFIEDPOINTSONTHEAIRCRAFT.INCORRECTLY ATTACHED BONDING CABLES CAN CAUSE SCRATCHES.



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BONDING CABLES ATTACHED TO COMPOSITE DOORS OF FAIRINGS DO NOTGIVE AN ELECTRICAL BOND.


NOTE : If you remove electrical power, the refueling valves that are open will stay open. The refueloperation will not stop when the fuel tanks are full. This could cause an overfill or a fuelspill.

CAUTION: DO NOT USE MORE THAN 50 PSI FUEL PRESSURE AT THE REFUEL NOZZLE.IF YOU USEMORE THAN 50 PSI FUEL PRESSURE, YOU CAN CAUSE DAMAGETO THE REFUELING SYSTEM COMPONENTS.




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Figure 26.01-2: Bonding Point Locations Fig. 1 of 2



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Figure 26.01-3: Bonding Point Locations Fig. 2 of 2

1. Connect a bonding cable from the fueling source to an approved electrical grounding or bondingconnection on the aircraft. Refer to Figure 26.01-2 and Figure 26.01-3.

2. Open the access panel: 521FB-Fixed LE Outboard of Nacelle Strut Panel. (Refer toFigure 26.01-1.)a. Make sure that the fuel quantity indicators and load select displays come on within 10 sec




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b. If the Refuel Control Panel (RCP) does not come on, put the POWER switch on the RCP tothe BATTERY position.(1) Make sure that the fuel quantity indicators show the fuel quantities.(2) Make sure that the lower load select display shows: "0.0 lb" "LOAD SEL."

c. If the RCP shows BATTERY MANUAL, refer to Section 26.01.6., Pressure Refueling (withBattery Power).WARNING: MAKE SURE THAT THERE IS NO TENSION ON THE HOSE. THE HOSE

MUSTHANGFREELYFROMTHEREFUELADAPTER,WITHNOFORCEON IT. TENSION ON THE HOSE CAN CAUSE DAMAGE TO THE FUELRECEPTACLE AND CAUSE THE HOSE TO DISCONNECT. INJURIESTO PERSONNEL AND DAMAGE TO EQUIPMENT CAN OCCUR.

3. Connect the refuel nozzles to the refuel adapters and prepare the Refuel Control Panel.a. Push and hold the TEST switch to the PANEL position.

NOTE : This does a test of the fuel quantities indicators, load select displays, the overfillindication light, and the valve position lights.

b. Make sure that these fuel quantities show on the three fuel quantity indicators while you holdthe TEST switch in the PANEL position:(1) RIGHT: 88.8 lbs.(2) CENTER: 88.8 lbs.(3) LEFT: 88.8 lbs.

c. If one of the displays does not come on, use the applicable load select display to see thefuel quantity for that tank.(1) If the applicable load select display does not show that tank's fuel quantity, then do this

task to refuel the aircraft: Pressure Refueling (with a Fuel Quantity Indication Not inOperation). Refer to Section 26.01.5.

d. Make sure that all of the LEDs on the load select displays come on.NOTE : The load select displays will go back to their usual condition when you release the

TEST switch.

e. Make sure that the six blue refuel valve position lights come on and then go off.f. Make sure that the red OVERFILL indication light comes on and then goes off.g. Release the TEST switch.h. Record the Gauge Reading Before Fueling for each tank on the Jet Fuel Service Record

(Fuel Slip). Refer to Section 15.01.4. Do these steps to set the LOAD SELECT fuel quantity:

a. Make sure that "LOAD SEL" shows on the second line of the lower load select display.(1) If "LOAD SEL" does not show, push the lower DISPLAY SELECT button until it shows.(2) Push the LOAD SELECT QTY switch to the INCREMENT position to increase the fuel

quantity that shows on the display.NOTE : The quantity will increase more quickly while holding the switch up.

5. Prepare for the Refuel Operationa. Make sure that the REFUEL/DEFUEL handle for each refuel adapter is in the REFUEL

position.b. Put the ALL VALVES switch to the ENABLE position.



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NOTE : The system will open the applicable refuel valves to add the necessary fuel quantityto each of the fuel tanks. Make sure that the applicable blue refuel valve lightscome on.

c. Make sure that the applicable blue refuel valve lights come on.d. Push the TEST switch to the SYSTEM position to do a test of the refuel system.

NOTE : This test makes sure that all of the valves will close correctly when the refuelingoperation is complete. The refuel valves that are open will close and then openagain, one valve at a time. While they close and open, the valve indication lightswill go off and come on again.

e. Make sure that the applicable blue refuel valve lights go off and come on again.NOTE : SYS TEST is removed from the applicable load select display when the test

completes. If the test completes satisfactorily, the load select display will show thedata that it contained before the test started. If the test does not completesatisfactorily, the lower load select display will show FUELING INHIBIT.

6. Start the refuel operation.7. Do these steps to start the refuel operation:

a. Activate the deadman switch to start the fuel flow.b. Make sure that the refuel pressure is between 35 and 50 psi.c. Make sure that the applicable refuel valve indication lights are on.

NOTE : When the lights are on, the valves are open.

d. Make sure that the left and right main fuel tanks refuel at approximately the same rate.8. Monitor the TOTAL fuel quantity on the upper load select display.

a. If the second line of this display does not show "TOTAL," push the top DISPLAY SELECTbutton until it does.

9. Unexpected Shutoff of the Refuel Operation.NOTE : These steps are only applicable if the refuel operation stops automatically, before it is

completed.

10. If the refuel operation stops before it is completed, there is a problem with one or more of the fuelheight sensors.NOTE : If a fuel height sensor is unserviceable, the system will decrease the Volumetric Shut

Off (VSO) quantity for that fuel tank. The system will close the refuel valves for eachof the main tanks when one tank has the decreased VSO quantity.

11. If the red OVERFILL indication light on the RCP comes on, the refuel operation will stop. Do thesesteps:a. Set the ALL VALVES switch to the CLOSE position.b. Do one of these tasks to remove fuel from the overfilled fuel tank, until the applicable maximum

quantity shows:(1) Tank-to-Tank Fuel Transfer - Operation. Refer to Section 26.01.7.(2) aircraft (Pressure Method) - Defueling. Refer to Section 26.01.8.

NOTE : The fuel quantity for the tank that overfilled will flash on the RCP.

12. Stop the refuel operation.NOTE : The system will automatically close the refuel valves when the fuel tanks contain the

fuel quantity that is set.



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13. Do these steps after the system automatically closes all of the refuel valves.a. Release the deadman switch.b. Put the ALL VALVES switch to the CLOSE position.

(1) Make sure that all of the blue refuel valve lights go off.c. If the power switch is in the BATT position, put the power switch to the NORMAL position.d. Legibly complete all applicable fields on the Jet Fuel Service Record (Fuel Slip). Refer to

Section 15.01.e. Disconnect the fueling nozzles.f. Disconnect the bonding cable.g. Close the left Refueling Station Door.


A. General1. This procedure does not set the fuel quantity to be put on the aircraft. There are two ways that

refueling can stop during this procedure:a. The system will automatically close the refuel valve for a fuel tank when that tank is full.b. The refuel valves can be closed manually to stop the fuel flow to the tanks.

NOTE : You can close the valves for one fuel tank at a time.

(1) To stop refueling at a specified quantity, put the MANUAL FUELING switch to the CLOSEposition when the quantity shows on the fuel quantity indicators.

B. ProcedureWARNING: 1. DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TO

THE AIRCRAFT DURING ATMOSPHERIC ELECTRICAL ACTIVITY OR STRONGRADIOACTIVE FIELDS. LIGHTING STRIKE AND HIGH DISCHARGE CURRENTSCAN CAUSE SEVERE INJURY.

2. DO NOT OPERATE THE HF COMMUNICATION SYSTEM OR THE WEATHERRADAR DURING REFUELING OPERATIONS. A FIRE OR EXPLOSION CANOCCUR.

3. DO NOT PUT GROUND EQUIPMENT BELOW THE WINGTIPS DURING THEREFUELINGOPERATION. THEWEIGHTOF THEFUELWILL CAUSETHEWINGSTO MOVE DOWN AND THE WINGTIPS MOVE THE MOST. BECAUSE THE FUELTANKS ARE VENTED THROUGH THE WINGTIPS, A DANGEROUS ANDEXPLOSIVE MIXTURE AROUND THE WINGTIP CAN OCCUR.


5. DONOTUSEMORETHAN 50 PSI FUEL PRESSUREAT THEREFUELNOZZLE.IF YOU USEMORE THAN 50 PSI FUEL PRESSURE, YOU CAN CAUSE DAMAGETO THE REFUELING SYSTEM COMPONENTS.


7. ATTACHBONDINGCABLESONLY TOSPECIFIEDPOINTSONTHEAIRCRAFT.INCORRECTLY ATTACHED BONDING CABLES CAN CAUSE SCRATCHES.BONDING CABLES ATTACHED TO COMPOSITE DOORSOR FAIRINGS DONOTGIVE AN ELECTRICAL BOND.



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NOTE : If electrical power is removed, the refueling valves that are open will stay open. The refueloperation will not stop when the fuel tanks are full. This could cause an overfill or a fuelspill.

1. Connect a bonding cable from the fueling source to an approved electrical grounding or bondingconnection on the aircraft. (Refer to Figure 26.01-2 and Figure 26.01-3.)

2. Open the access panel: 521FB-Fixed LE Outboard of Nacelle Strut Panel. (Refer toFigure 26.01-1.)a. Make sure that the fuel quantity indicators and load select displays come on within 10 sec


b. If the Refuel Control Panel does not come on, put the POWER switch on the RCP to theBATTERY position.(1) Make sure that the fuel quantity indicators show the fuel quantities.(2) Make sure that the lower load select display shows: "0.0 lb" "LOAD SEL."

c. If the RCP continues to be off, refer to Section 26.01.6.3. Connect the refuel nozzles to the refuel adapters and prepare the RCP.

a. Push and hold the TEST switch to the PANEL position.NOTE : This does a test of the fuel quantities indicators, load select displays, the overfill

indication light, and the valve position lights.

b. Make sure that these fuel quantities show on the three fuel quantity indicators while you holdthe TEST switch in the PANEL position:(1) RIGHT: 88.8 lbs.(2) CENTER: 88.8 lbs.(3) LEFT: 88.8 lbs.

c. If one of the displays does not come on, use the applicable load select display to see thefuel quantity for that tank.(1) If the applicable load select display does not show that tanks fuel quantity, then do this

task to refuel the aircraft: Pressure refueling (with a Fuel Quantity Indication Not inOperation). Refer to Section 26.01.5.

d. Make sure that all of the LEDs on the load select displays come on.NOTE : The load select displays will go back to their usual condition when you release the

TEST switch.

e. Make sure that the six blue refuel valve position lights come on and then go off.f. Make sure that the red OVERFILL indication light comes on and then goes off.g. Release the TEST switch.h. Record the Gauge Reading Before Fueling for each tank on the Jet Fuel Service Record

(Fuel Slip). Refer to Section 15.01.4. Prepare for the Refuel Operation

a. Make sure that the REFUEL/DEFUEL handle for each refuel adapter is in the REFUELposition.

b. Put the applicable MANUAL FUELING switches to the OPEN position.



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NOTE : The refuel valves will close automatically when the fuel tank is full. If you put oneof the MANUAL FUELING switches to the CLOSE position during this procedure,refueling stops for that fuel tank.

(1) Make sure that the applicable blue refuel valve lights come on.c. Push the TEST switch to the SYSTEM position to do a test of the refuel system.

NOTE : This test makes sure that all of the valves will close correctly when the refuelingoperation is complete. The refuel valves that are open will close and then openagain, one valve at a time. While they close and open, the valve indication lightswill go off and come one again.

(1) Make sure that the applicable blue refuel valve lights go off and come on again.NOTE : SYS TEST will be removed from the applicable load select display when the

test completes. If the test completes satisfactorily, the load select display willshow the data that it contained before the test started. If the test does notcomplete satisfactorily, the lower load select display will show FUELINGINHIBIT.

5. Start the refuel operation.6. Do these steps to start the refuel operation:

a. Activate the deadman switch to start the fuel flow.b. Make sure that the refuel pressure is between 35 and 50 psi.c. Make sure that the applicable refuel valve indication lights are on.


d. Make sure that the left and right main fuel tanks refuel at approximately the same rate.7. Unexpected Shutoff of the Refuel Operation.

NOTE : These steps are only applicable if the refuel operation stops automatically, before it iscompleted.

a. If the refuel operation stops before it is completed, there is a problem with one or more ofthe fuel height sensors.NOTE : If a fuel height sensor is unserviceable, the system will decrease the Volumetric

Shut Off (VSO) quantity for that fuel tank. The system will close the refuel valvesfor each of the main tanks when one tank has the decreased VSO quantity.

(1) During a subsequent maintenance opportunity, correct the fault that caused the refuelingoperation to stop before it completed.

b. If the red OVERFILL indication light on the RCP comes on, the refuel operation will stop. Dothese steps:(1) Set the three MANUAL FUELING valves switch to the CLOSE position.(2) Do one of the tasks to remove fuel from the overfilled fuel tank, until the applicable

maximum quantity shows.(3) Tank-to-Tank Fuel Transfer - Operation (refer to Section 26.01.7.)(4) Aircraft (Pressure Method) - Defueling (refer to Section 26.01.8).)


(5) Stop the refuel operation.(6) Release the deadman switch.(7) Put the MANUAL FUELING switches to the CLOSE position.



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NOTE : The FQIS will automatically close the refuel valves for a fuel tank when thatfuel tank is full.

a) Make sure that all of the blue refuel valve lights go off.(8) If the power switch is in the BATTERY position, put the power switch to the NORMAL

position.(9) Legibly complete all applicable fields on the Fuel Slip. Refer to Section 15.01.(10) Disconnect the fueling nozzles.(11) Disconnect the bonding cable.(12) Close the left Refueling Station Door.

26.01.5 Refueling - (With a Fuel Quantity Indication Not in Operation)

A. General1. This procedure gives the steps to refuel the aircraft with one or more fuel quantity indicator that

do not operate.a. You can use the fuel quantity that is calculated by the Flight Management Computer (FMC)

to find the unknown fuel quantity.b. After you find the unknown fuel quantity, you can add a known quantity of fuel from a different

fuel tank.B. Procedure

WARNING: 1. DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TOTHE AIRCRAFT DURING ATMOSPHERIC ELECTRICAL ACTIVITY OR STRONGRADIOACTIVEFIELDS. LIGHTNINGSTRIKEANDHIGHDISCHARGECURRENTSCAN CAUSE SEVERE INJURY.


3. DO NOT PUT GROUND EQUIPMENT BELOW THE WINGTIPS DURING THEREFUELINGOPERATION. THEWEIGHTOF THEFUELWILL CAUSETHEWINGSTO MOVE DOWN AND THE WINGTIPS MOVE THE MOST. BECAUSE THE FUELTANKS ARE VENTED THROUGH THE WINGTIPS, A DANGEROUS ANDEXPLOSIVE MIXTURE AROUND THE WINGTIP CAN OCCUR.

4. DO NOT START OR SHUT DOWN APU SHOULD A FUEL SPILL OCCUR.



7. ATTACHBONDINGCABLESONLY TOSPECIFIEDPOINTSONTHEAIRCRAFT.INCORRECTLY ATTACHED BONDING CABLES CAN CAUSE SCRATCHES.BONDING CABLES ATTACHED TO COMPOSITE DOORS OF FAIRINGS DO NOTGIVE AN ELECTRICAL BOND.




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2. Open the access panel: 521FB-Fixed LEOutboard of Nacelle Strut Panel. Refer to Figure 26.01-1.a. Make sure that the fuel quantity indicators and load select displays come on within 10 sec

after you open the access panel.b. If the Refuel Control Panel does not come on, put the POWER switch on the RCP to the

BATTERY position.3. Connect the refuel nozzles to the refuel adapters.

a. Make sure that the REFUEL/DEFUEL handle for each refuel adapter is in the REFUELposition.

4. Find the fuel quantity for the tank with an inoperative display.a. Contact Maintenance to perform the steps in order to find the calculated fuel quantity with

the Flight Management Function (FMF):(1) Press the CDU button on the Multi Function Keyboard (MFK) to show the FMF on the

on Display (MFD).(2) Select PROG on the MFD to show the PROGRESS 1/4 page.(3) Select NEXT PAGE on the MFD to show the PROGRESS 2/4 page.(4) Record the value for CALCULATED FUEL QTY.(5) Do this task to show the FUEL SYNOPTIC PAGE - Primary Display System Show a

System Synoptic Page - Software Operation.a) Record the Gauge Reading Before Fueling (for example, FMF display) for each

tank with operable fuel quantity indications on the Fuel Slip. Refer to Section 15.01.(6) Subtract the sum of the fuel quantities for the operating indications from the

CALCULATED FUEL QTY to find the fuel quantity for the tank with the inoperativeindication. Record the Gauge Reading Before Fueling, (for example, calculated amount)for the tank with inoperative fuel quantity indication on the Jet Fuel Service Record (FuelSlip). Refer to Section 15.01.a) Use the value that you calculated as the pre-uplift fuel quantity for the tank with the

display that does not operate.5. Refueling the tank with the Inoperative display.

a. If there is insufficient fuel in the tanks with displays that are operational perform this task toadd a sufficient quantity of fuel (for transfer purposes) to a fuel tank with a display that isoperational. Refer to Sec 16.01.4 Pressure Refueling - With No Set Fuel Quantity.

b. Use this tank to move the necessary quantity of fuel to the tank with the display that isinoperative: Refer to Section 26.01.7 Tank to Tank Fuel Transfer.

c. Record the GAUGEREADINGAFTER FUELING, for the tank with the inoperative indication,on the Jet Fuel Service Record (fuel slip).

d. In the remarks section of the Jet Fuel Service Record (fuel Slip) record that, Fuel ManualSection 26.01.5 procedure was used to refuel the tank with the inoperative indicator. Example:Right tank was refueled using fuel manual 16.01.5 alternate refueling procedure.

6. Prepare for the refuel operation for the tanks with operations indicators.a. Put the MANUAL FUELING switches, for the applicable fuel tanks with displays that operate,

to the OPEN position.



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NOTE : The refuel valves will close automatically when the fuel tank is full. If you put oneof the MANUAL FUELING switches to the CLOSE position during this procedure,refueling stops for that fuel tank.

(1) Make sure that the applicable blue refuel valve lights come on.NOTE : When the lights are on, the valves are open.

7. Start the refuel operation.a. Do these steps to start the refuel operation:

(1) Activate the deadman switch to start the fuel flow.(2) Make sure that the refuel pressure is between 35 and 50 psi.

b. Push the TEST switch to the SYSTEM position to do a test of the refuel system.NOTE : This test makes sure that all of the valves will close correctly when the refueling

operation is complete. The refuel valves that are open will close and then openagain, one valve at a time. While they close and open, the valve indication lightswill go off and come one again.

(1) Make sure that the applicable blue refuel valve lights go off and come on again.NOTE : SYS TEST will be removed from the applicable load select display when the

test completes. If the test completes satisfactorily, the load select display willshow the data that it contained before the test started. If the test does notcomplete satisfactorily, the lower load select display will show FUELINGINHIBIT.

8. Unexpected Shutoff of the Refuel OperationNOTE : These steps are only applicable if the refuel operation stops automatically, before it is

completed.

a. If the refuel operation stops before it is completed, there is a problem with one or more ofthe fuel height sensors.NOTE : If a fuel height sensor is unserviceable, the system will decrease the volumetric

shutoff (VSO) quantity for that fuel tank. The system will close the refuel valvesfor each of the main tanks when one tank has the decreased VSO quantity.

(1) During a subsequent maintenance opportunity, correct the fault that caused the refuelingoperation to stop before it completed.

b. If the red OVERFILL indication light on the RCP comes on, the refuel operation will stop. Dothese steps:(1) Set the three MANUAL FUELING valve switches to the CLOSE position.(2) Do one of these tasks to remove fuel from the overfilled fuel tank, until the applicable

maximum quantity shows.(3) Tank-to-Tank Fuel Transfer - Operation. Refer to Section 26.01.7.(4) Aircraft (Pressure Method) - Defueling. Refer to Section 26.01.8.2.


a) After you defuel the overfilled fuel tank, the fuel in the surge tank will drain into themain fuel tank.NOTE : The OVERFILL indication will go off and the fuel quantity indicator for

that fuel tank will stop flashing.

(5) During a subsequent maintenance opportunity, correct the fault that caused the overfill.



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9. Stop the refuel operation.10. Release the deadman switch.11. Put the MANUAL FUELING switches to the CLOSE position.

NOTE : The FQIS will automatically close the refuel valves for a fuel tank when that fuel tankis full.

a. Make sure that all of the blue refuel valve lights go off.12. If the power switch is in the BATTERY position, put the power switch to the NORMAL position.13. Legibly complete all applicable fields on the Jet Fuel Service Record (Fuel Slip). Refer to Section

15.01.14. Disconnect the fueling nozzles.15. Disconnect the bonding cable.16. Close the left Refueling Station Door.

26.01.6 Pressure Refueling - (With Battery Power)

A. General1. This procedure lets you add fuel to the left main tank when only battery power is available.

a. You can use battery power to put sufficient fuel in the left main fuel tank to operate the APU.b. After the APU is operating, you can continue to refuel the aircraft. Refer to Section 26.01.3

or Section 26.01.4.B. Procedure

WARNING: 1. DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TOTHE AIRCRAFT DURING ATMOSPHERIC ELECTRICAL ACTIVITY OR STRONGRADIOACTIVEFIELDS. LIGHTNINGSTRIKESANDHIGHDISCHARGECURRENTSCAN CAUSE SEVERE INJURY.


3. DO NOT PUT GROUND EQUIPMENT BELOW THE WINGTIPS DURING THEREFUELINGOPERATION. BECAUSETHEFUELTANKSAREVENTEDTHROUGHTHE WINGTIPS, A DANGEROUS AND EXPLOSIVE MIXTURE AROUND THEWINGTIP CAN OCCUR.




7. ATTACHBONDINGCABLESONLY TOSPECIFIEDPOINTSONTHEAIRCRAFT.INCORRECTLY ATTACHED BONDING CABLES CAN CAUSE SCRATCHES.THESE SCRATCHES CAN CAUSE CORROSION AND CRACKS ON STRESSEDPARTS. BONDING CABLES ATTACHED TO COMPOSITE DOORS OF FAIRINGSDO NOT GIVE AN ELECTRICAL BOND.




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2. Open the access panel: 521FB-Fixed LEOutboard of Nacelle Strut Panel. Refer to Figure 26.01-1.3. Connect the refuel nozzles to one or more of the refuel adapters.4. Prepare the Refuel Operation.

a. Put the POWER switch to the BATTERY position on the RCP.(1) Make sure that the load select displays come on within 10 seconds.

a) The top display will show the fuel quantity for the left main fuel tank.b) The bottom display will show "BATTERY."

b. Push and hold the TEST switch to the PANEL position.NOTE : This does a test of the fuel quantity indicators, load select displays, the overfill

indication light, and the valve position lights.

(1) Make sure that these fuel quantities shows on the three fuel quantity indicators whileyou hold the TEST switch in the PANEL position:a) RIGHT - 88.8 lbs.b) CENTER - 88.8 lbs."c) LEFT - 88.8 lbs.

(2) If one of the displays does not come on, use the applicable load select display to seethe fuel quantity for that tank.

(3) Make sure that all of the LEDs on the load select displays come on.NOTE : The load select displays will go back to their usual condition when you release

the TEST switch.

(4) Make sure that the blue valve position lights for the left main fuel tank come on and thengo off.

(5) Make sure that the red OVERFILL indication light comes on and then goes off.5. Start the Refuel Operation

a. Do these steps to start the refuel operation:(1) Activate the deadman switch to start the fuel flow.(2) Put the LEFT MANUAL FUELING switch to the OPEN position.

NOTE : The refuel valves will close automatically when the fuel tank is full. If you putthe LEFT MANUAL FUELING switch to the CLOSE position during thisprocedure, refueling will stop.

(3) Make sure that the blue refuel valve light for the left main tank comes on.(4) Make sure that the refuel pressure is between 35 psi and 50 psi.(5) Make sure that the refuel valve indication lights for the left main tank are on.


6. Unexpected Shutoff of the Refuel OperationNOTE : These steps are only applicable if the refuel operation stops automatically, before it is

completed.



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a. If the fuel quantity management system senses the low battery signal, refueling will stop.(1) If the left main fuel tank does not contain sufficient fuel to operate the APU, make sure

Electrical Power is activated.a) Do one of these tasks to continue refueling the aircraft:

(1) Pressure Refueling (with a Set Fuel Quantity) - Fueling (refer to Section26.01.3.)

(2) Pressure Refueling (with No Set Fuel Quantity) - Fueling (refer to Section26.01.4.)

(2) If the red OVERFILL indication light on the RCP comes on, refueling will stop. Do thesesteps:a) Set the LEFT MANUAL FUELING valve switch to the CLOSE position.b) Do one of these tasks to remove fuel from the left main fuel tank, until it contains a

maximum of 39,000 lbs. (17,700 kg) of fuel:(1) Tank-to-Tank Fuel Transfer - Operation. Refer to Section 26.01.7.(2) Aircraft (Pressure Method) - Defueling. Refer to Section 26.01.8.2.(3) After defueling the left main fuel tank, the fuel in the surge tank will drain into

the main fuel tank.NOTE : The OVERFILL indication will go off and the fuel quantity indicator

for the left main fuel tank will stop flashing.

c) During a subsequent maintenance opportunity, correct the fault that caused theoverfill.

7. Stop the refuel operation.8. Release the deadman switch.9. Put the MANUAL FUELING switches to the CLOSE position.

NOTE : A minimum of 3,000 lbs. (1,400 kg) of fuel is necessary in the left main tank to startthe APU and operate it for one hour. Approximately 525 lbs. (240 kg) of fuel is necessaryfor each hour of operation after the first.

NOTE : The FQIS will automatically close the refuel valves for the left main fuel tank when itis full.

a. Make sure that all of the blue refuel valve lights go off.10. Put the POWER switch to the NORMAL position.

26.01.7 Tank-to-Tank Fuel Transfer

A. General1. This procedure uses the defuel/isolation valves to connect the fuel feed manifold and the refuel

manifold. The boost pumps move fuel out of the main fuel tanks and the override/jettison pumpsmove fuel out of the center tank. To move the fuel between the fuel tanks, the fuel system mustbe in the configuration that follows:a. The defuel/isolation valves must be open.b. A minimum of one fuel pump must operate in the fuel tank that supplies fuel.c. A minimum of one refuel valve must be open in the fuel tank that gets the fuel.

2. The system lets you monitor the fuel quantity at the RCP or on the EICAS display.3. During ground operations, there are no limits on the permitted difference in the fuel quantities of

the two main tanks. One wing can be full while the other wing is empty.



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4. If a fuel tank must be fully defueled, drain the remaining fuel through the drain valve of the fuelsump and make sure to Fuel Tank Entry Preparation is completed.

B. Prepare for the Tank-to-Tank Transfer1. Make sure that the aircraft has a ground attitude of -0.78° ± 2.0° (nose-down) pitch and 0.0° ±

2.0°roll.NOTE : A ground attitude of -0.78° (nose-down) pitch and 0.0° roll lets you defuel the maximum

quantity of fuel from the tanks.

WARNING: DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONS TOTHE AIRCRAFT DURING ATMOSPHERIC ELECTRICAL ACTIVITY ORSTRONG RADIATIVE FIELDS. LIGHTNING STRIKE AND HIGH DISCHARGECURRENTS CAN CAUSE SEVERE INJURY.

WARNING: DO NOT OPERATE THE HF SYSTEMWHILE THE AIRCRAFT IS REFUELEDOR DEFUELED. AN EXPLOSION CAN CAUSE INJURIES TO PERSONNELAND DAMAGE TO THE AIRCRAFT.

WARNING: DO NOT PUT GROUND EQUIPMENT BELOW THE WINGTIPS WHILE YOUREFUEL THE AIRCRAFT. THE WEIGHT OF THE FUEL CAN CAUSE THEWINGS TO MOVE DOWN. BECAUSE THE FUEL TANK VENTS ARE NEARTHEWINGTIPS, EXPLOSIVE FUMESAROUND THEWINGTIP CANOCCUR.GROUND EQUIPMENT CAN CAUSE AN EXPLOSION WHICH CAN CAUSEINJURIES TO PERSONNEL AND DAMAGE TO EQUIPMENT.

CAUTION: DO NOT OPERATE THE HYDRAULIC SYSTEMS UNLESS THE FUEL LEVELIS HIGHER THAN THE HEAT EXCHANGERS. WITHOUT SUFFICIENT FUEL,THE HEAT EXCHANGER WILL BECOME TO HOT. DAMAGE TO THEHYDRAULIC SYSTEM WILL OCCUR.

2. Obey the applicable precautions for this procedure.3. Make sure Electrical Power is activated.4. Bond the aircraft to an approved ground.

WARNING: DO THE DEACTIVATION PROCEDURE FOR THE LEADING EDGE SLATS.THE SLATS RETRACT QUICKLY. THIS CAN CAUSE INJURIES TOPERSONNEL OR DAMAGE TO EQUIPMENT.

5. Make sure the leading edge slats are deactivated.6. Open the RCP - 521FB-Fixed LE Outboard of Nacelle Strut Panel. Refer to Figure 26.01-1.7. Make sure that the utility lights for the RCP come on.

NOTE : This shows that there is 28V DC.

a. If the lights do not come on, put the POWER switch, on the RCP, to the BATTERY position.8. Push and hold the TEST switch to the PANEL position.

NOTE : This does a test of the fuel quantity indicators, load select displays, the overfill indicationlight, and the valve position lights.




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b. If one of the displays does not come on, use the applicable load select display to see thefuel quantity for that tank.(1) If the applicable load select display does not show that fuel quantity of the tank, then do

this task to refuel the aircraft. Refer to Section 26.01.5.c. Make sure that all of the LEDs on the load select displays come on.

NOTE : The load select displays will go back to their usual condition when you release theTEST switch.

d. Make sure that the six blue refuel valve position lights come on and then go off.e. Make sure that the red OVERFILL indication light comes on and then goes off.f. Release the TEST switch.

C. Procedure1. Put the DEFUEL VALVES switch to the OPEN position.

a. Make sure the LOAD SELECT display shows "DEFUEL."2. If the GND TEST switch on the P5 panel is in the NORM position, set the GND TEST switch to

the ENABLE position.NOTE : If the GND TEST switch is in the DATALOAD/ENABLE position, do not move the switch.

The DATALOAD/ENABLE position is satisfactory. A data load must be started againif the switch position is changed during the data load.

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMESON AND STAYS ON. THIS CONDITION CAN CAUSE THE IGNITION OF THEFUEL FUMES IN THE FUEL TANK. A FIRE OR AN EXPLOSION CAN CAUSEINJURIES TO PERSONNEL AND DAMAGE TO EQUIPMENT.

3. To operate any of the fuel pumps, you must be in the flight compartment to continuously monitorthe fuel quantity and low pressure indication in the applicable tank.a. Immediately set the applicable fuel pump switch-light(s) to OFF if the amber PRESS light

comes on and stays on.4. If the left or right main fuel tank supplies the fuel, do these steps:

a. Push the applicable FWD and AFT PUMPS switch-lights, on the P5 Overhead Panel, to theON position.NOTE : This puts pressure in the refuel manifold.

b. To move fuel to the center fuel tank, put the CENTER VALVES switch, on the RCP, to theOPEN position.

c. To move fuel to the opposite main tank, put the applicable MANUAL FUELING valve switch,on the RCP, to the OPEN position:(1) LEFT VALVES(2) RIGHT VALVES

5. If the center fuel tank supplies the fuel, do these steps:a. Push the L and R CENTER PUMPS switch-lights, on the P5 Overhead Panel, to the ON

position.NOTE : This puts pressure in the refuel manifold.

b. To move fuel to the left or right main fuel tank, put the applicable MANUAL FUELING switch,on the RCP, to the OPEN position:(1) LEFT VALVES



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(2) RIGHT VALVES6. Monitor the quantity of fuel in the fuel tanks on the fuel quantity indicators of the RCP or on the

EICAS display.NOTE : The Load Select Display will show "DEFUEL" "TRANSFER" while the refuel valves are

open.

7. Push the applicable FWD/AFT PUMPS or L/R CENTER PUMPS switch(es) to the OFF positionwhen the necessary quantity of fuel is moved.

8. Put the DEFUEL VALVES switch to the CLOSE position.9. Put the applicable LEFT/CENTER/RIGHT MANUAL FUELING valve switch, on the RCP, to the

CLOSE position to close the refuel valves.10. If you must defuel the tank(s) fully, make sure that Fuel Tank Entry Preparation is completed.

26.01.8 Defueling

NOTE : Product defueled from an aircraft for purposes other than contamination should be returned tothe airline from which it was removed. Defueled product may not be delivered to anothercompany's aircraft without its approval. Defueling aircraft directly into joint use fueling systemis not authorized unless a procedure has been unanimously approved by all system users.

A. Aircraft (Center Tank Alternative Method)1. General

a. This procedure can make it easier to defuel the center tank when you will remove all the fuelfrom the tank. After a standard defueling procedure, there will be approximately 1,200 lbs.(550 kg) of fuel in the center tank, which you must remove through the sump drain valves.With this procedure, only approximately 300 lbs. (150 kg) of fuel will stay in the center tank.(1) It uses the standard defueling procedure to remove sufficient fuel from the main tanks

to make space to scavenge the fuel from the center tank.(2) After the fuel is moved out of the center tank, it uses the standard defueling procedure

again to remove the remaining fuel from the main tanks.b. When thunderstorms or lightning are in the area (approximately a 10 mi (16 km) radius), you

must stop the defueling operation.c. Defueling operations must stop if there are strong wind conditions.

NOTE : Strong wind conditions can cause static electricity to collect. Large quantities ofstatic electricity can collect on support equipment while parked, from the movementof dust particles and air currents during strong wind conditions.

NOTE : Strong wind conditions can also cause the unwanted movement of items orequipment, which can cause injury to personnel and damage to the aircraft.

2. Prepare for the Defueling Operation.a. Make sure that the aircraft has a ground attitude of -0.78° ± 2.0° (nose-down) pitch and 0.0°

± 2.0°roll.NOTE : A ground attitude of -0.78° (nose-down) pitch and 0.0° roll lets you defuel the

maximum quantity of fuel from the tanks.

WARNING: DO NOT CONNECT A HEADSET AND DO NOT TOUCH CONNECTIONSTO THE AIRCRAFT DURING ATMOSPHERIC ELECTRICAL ACTIVITYOR STRONG RADIATIVE FIELDS. LIGHTNING STRIKE AND HIGHDISCHARGE CURRENTS CAN CAUSE SEVERE INJURY.



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WARNING: DO NOT OPERATE THE HF SYSTEM WHILE THE AIRCRAFT ISREFUELEDORDEFUELED. ANEXPLOSIONCANCAUSE INJURIES TOPERSONNEL AND DAMAGE TO THE AIRCRAFT.

WARNING: DO NOT PUT GROUND EQUIPMENT BELOW THE WINGTIPS WHILEYOUREFUELTHEAIRCRAFT. THEWEIGHTOFTHEFUELCANCAUSETHEWINGS TOMOVE DOWN. BECAUSE THE FUEL TANK VENTS ARENEAR THE WINGTIPS, EXPLOSIVE FUMES AROUND THE WINGTIPCAN OCCUR. GROUND EQUIPMENT CAN CAUSE AN EXPLOSIONWHICH CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TOEQUIPMENT.

CAUTION: DO NOT OPERATE THE HYDRAULIC SYSTEMS UNLESS THE FUELLEVEL IS HIGHER THAN THE HEAT EXCHANGERS. WITHOUTSUFFICIENT FUEL, THE HEAT EXCHANGERWILL BECOME TOO HOT.DAMAGE TO THE HYDRAULIC SYSTEM WILL OCCUR.

b. Obey the applicable precautions for this procedure.c. Make sure Electrical Power is activated.

WARNING: DO THE DEACTIVATION PROCEDURE FOR THE LEADING EDGESLATS. THE SLATS RETRACT QUICKLY. THIS CAN CAUSE INJURIESTO PERSONNEL OR DAMAGE TO EQUIPMENT.

d. Make sure the leading edge slats are deactivated.WARNING: OBEY THE APPLICABLE PRECAUTIONS WHEN YOU ATTACH THE

BONDINGCABLES. INSTALL THEBONDINGCABLESATANAPPROVEDAIRCRAFT GROUND CONNECTION TO MAKE SURE THAT THEELECTRICALBOND ISSUFFICIENT. IF THEFUELSERVICEEQUIPMENTAND AIRCRAFT DO NOT HAVE A SUFFICIENT ELECTRICAL BOND, AFIRE OR EXPLOSION CAN OCCUR.

CAUTION: ATTACH THE BONDING CABLES ONLY TO THE SPECIFIED POINTSON THE AIRCRAFT. THE ATTACHED BONDING CABLES THAT ARENOTCORRECTLYATTACHEDCANCAUSECORROSIONANDCRACKSON THE STRESSED PARTS. THE BOND WIRES ATTACHED TO THEDOORS OR THE FAIRINGS THAT ARE MADE FROM THE COMPOSITEMATERIALS DO NOT GIVE A GOOD BOND. THIS WILL PREVENTDAMAGE TO THE AIRCRAFT.

e. Make sure to bond and ground the aircraft and the fuel servicing equipment using StandardPractices:NOTE : If the fuel servicing equipment has a permanently attached grounding/bonding

cable, you can use it in this step.

(1) Connect a bonding cable between the fuel servicing equipment and the aircraft.(2) Connect a bonding cable between the aircraft and the ground.(3) Connect a bonding cable between the fuel servicing equipment and the ground.

f. Open the RCP - 521FB-Fixed LE Outboard of Nacelle Strut Panel. Refer to Figure 26.01-1.g. Make sure that the utility lights for the RCP come on.


(1) If the lights do not come on, put the POWER switch, on the RCP, to the BATTERYposition.



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h. Connect the bonding cable, attached to the fuel nozzle, to an approved aircraft electricalground.NOTE : This bonding cable is not necessary if there is electrical continuity between the

fuel servicing equipment and the fueling nozzle.

(1) Make sure to bond the aircraft using Standard Practices.3. Connect the refuel nozzles to the refuel adapters.4. If it is necessary, put the POWER switch on the RCP, to the applicable position to set the power

source.5. Push and hold the TEST switch to the PANEL position to do a test of the fuel quantity indicators.


b. Make sure that all of the LEDs on the load select displays come on.NOTE : The load select displays will go back to their usual condition when you release the

TEST switch.

c. Release the TEST switch.6. Do these steps to make sure that the refuel valves are closed:

a. Make sure that the boost pumps and the override/jettison pumps are off.b. Make sure that all of the MANUAL FUELING valve switches are in the CLOSE position.

7. Put the REFUEL/DEFUEL handle, on the refuel adapters, to the DEFUEL position.8. Put the DEFUEL VALVES switch to the OPEN position.

a. Make sure the LOAD SELECT display shows "DEFUEL."9. If the GND TEST switch on the P5 panel is in the NORM position, set the GND TEST switch to

the ENABLE position.NOTE : If the GND TEST switch is in the DATALOAD/ENABLE position, do not move the switch.

The DATALOAD/ENABLE position is satisfactory. A data load must be started againif the switch position is changed during the data load.

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMESON AND STAYS ON. THIS CONDITION CAN CAUSE THE IGNITION OF THEFUEL FUMES IN THE FUEL TANK. A FIRE OR AN EXPLOSION CAN CAUSEINJURIES TO PERSONNEL AND DAMAGE TO EQUIPMENT.

10. To operate any of the fuel pumps, you must be in the flight compartment to continuously monitorthe fuel quantity and low pressure indication in the applicable tank.a. Immediately set the applicable fuel pump switch-light(s) to OFF if the amber PRESS light

comes on and stays on.11. Do these steps to make sure that the fuel quantities are in the necessary ranges:

a. Make sure that the main fuel tank(s) that will receive fuel from the center tank contain aquantity of fuel in this range:NOTE : A fuel quantity in this range will let the fuel scavenge system operate and leave

sufficient space for the scavenged fuel from the center tank.

(1) A minimum of 5,200 lbs. (2,400 kg) of fuel.



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(2) A maximum of 34,500 lbs. (15,600 kg) of fuel.NOTE : The maximum quantity of fuel that you can remove from the center tank with

34,500 lbs. (15,600 kg) of fuel in each main tank is approximately 6,000 lbs.(2,700 kg). If you will remove more fuel than this from the center tank, defuelthe main tanks to the necessary level.

b. Make sure that the center fuel tank contains a minimum of 1,000 lbs. (500 kg) of fuel.c. If it is necessary, do the applicable task to get the necessary fuel quantities:

(1) aircraft (Pressure Method) - Defueling (refer to Section 26.01.8.2.)(2) Tank-to-Tank Fuel Transfer - Operation (refer to Section 26.01.7.)

12. Put the DEFUEL VALVES switch, on the RCP, to the CLOSE position.13. Close this access panel: 521FB - Fixed LE Outboard Of Nacelle Strut Panel. (Refer to

Figure 26.01-1.)a. Action/Condition - Make sure that these circuit breakers are closed:


CE2822817SCAVENGE ISLNVLV CLOSE-L


CE2822819SCAVENGE ISLNVLV CLOSE-R


CE2822818SCAVENGE ISLNVLV OPEN-L


CE2822820SCAVENGE ISLNVLV OPEN-R


14. Do these steps to let the fuel scavenge system move the fuel from the center tank to the maintanks:a. To move fuel to the left main tank, push one of these switch-lights to the ON position:

(1) L PUMPS FWD(2) L PUMPS AFT

b. To move fuel to the right main tank, push one of these switch-lights to the ON position:(1) R PUMPS FWD(2) R PUMPS AFT

c. Make sure the Primary Display System displays the Fuel Management Maintenance Page.(1) Make sure that the STATUS for the applicable fuel scavenge valve(s) is OPEN.

15. Make sure the Primary Display System displays the Fuel Management Maintenance Page.a. Monitor the fuel quantity for the center tank.b. When the center tank fuel quantity stops changing, push the switch-light(s) for the applicable

fuel boost pump(s) to the OFF position:(1) L PUMPS FWD(2) L PUMPS AFT(3) R PUMPS FWD(4) R PUMPS AFT

16. Make sure to complete the defueling operation. Refer to "Aircraft (Pressure Method) Defueling"step below.



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B. Aircraft (Pressure Method) Defueling1. General

a. This procedure uses the main tank fuel boost pumps and the center tank override/jettisonpumps to remove fuel from the fuel tanks.

b. The system lets you monitor the fuel quantity at the RCP or on the EICAS display.c. The sequence in which you defuel the fuel tanks for maintenance is not important. During

ground operations, one wing can be full while the other wing is empty.d. When thunderstorms or lightning are in the area (approximately a 10 mi (16 km) radius), you

must stop the defueling operation.e. Defueling operations must stop if there are strong wind conditions.

NOTE : Strong wind conditions can cause static electricity to collect. Large quantities ofstatic electricity can collect on support equipment while parked, from the movementof dust particles and air currents during strong wind conditions.

NOTE : Strong wind conditions can also cause the unwanted movement of items orequipment, which can cause injury to personnel and damage to the aircraft.

f. To defuel the tanks fully, drain the remaining fuel through the sump drain valves and makesure that Fuel Tank Entry Preparation is completed.

2. Prepare for the Pressure Defueling.a. Make sure that the aircraft has a ground attitude of -0.78° ± 2.0° (nose-down) pitch and 0.0°

± 2.0°roll.NOTE : A ground attitude of -0.78° (nose-down) pitch and 0.0° roll lets you defuel the









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d. Make sure the leading edge slats are deactivated.WARNING: OBEY THE APPLICABLE PRECAUTIONS WHEN YOU ATTACH THE

BONDINGCABLES. INSTALL THEBONDINGCABLESATANAPPROVEDAIRCRAFT GROUND CONNECTION TO MAKE SURE THAT THEELECTRICALBOND ISSUFFICIENT. IF THEFUELSERVICEEQUIPMENTAND AIRCRAFT DO NOT HAVE A SUFFICIENT ELECTRICAL BOND, AFIRE OR EXPLOSION CAN OCCUR.





f. Open the RCP - 521FB-Fixed LE Outboard of Nacelle Strut Panel. Refer to Figure 26.01-1.g. Make sure that the utility lights for the RCP come on.


(1) If the lights do not come on, put the POWER switch, on the RCP, to the BATTERYposition.



(1) Make sure to bond the aircraft using Standard Practices.3. Pressure Defueling

a. Connect the refuel nozzles to the refuel adapters.b. If it is necessary, put the POWER switch on the RCP to the applicable position, to set the

power source.c. Push and hold the TEST switch to the PANEL position to do a test of the fuel quantity

indicators.(1) Make sure that these fuel quantities show on the three fuel quantity indicators while you

hold the TEST switch in the PANEL position:a) RIGHT - 88.8 lbs.b) CENTER - 88.8 lbs.



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c) LEFT - 88.8 lbs.(2) Make sure that all of the LEDs on the load select displays come on.

NOTE : The load select displays will go back to their usual condition when you releasethe TEST switch.

(3) Release the TEST switch.d. Do these steps to make sure that the refuel valves are closed:

(1) Make sure that the boost pumps and the override/jettison pumps are off.(2) Make sure that all of the MANUAL FUELING valve switches are in the CLOSE position.

e. Put the REFUEL/DEFUEL handle, on the refuel adapters, to the DEFUEL position.f. Put the DEFUEL VALVES switch to the OPEN position.

(1) Make sure the LOAD SELECT display shows "DEFUEL."g. If the GND TEST switch on the P5 panel is in the NORM position, set the GND TEST switch

to the ENABLE position.NOTE : If the GND TEST switch is in the DATALOAD/ENABLE position, do not move the

switch. The DATALOAD/ENABLE position is satisfactory. A data load must bestarted again if the switch position is changed during the data load.

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHTCOMES ON AND STAYS ON. THIS CONDITION CAN CAUSE THEIGNITION OF THE FUEL FUMES IN THE FUEL TANK. A FIRE OR ANEXPLOSION CAN CAUSE INJURIES TO PERSONNEL AND DAMAGETO EQUIPMENT.

h. To operate any of the fuel pumps, you must be in the flight compartment to continuouslymonitor the fuel quantity and low pressure indication in the applicable tank.(1) Immediately set the applicable fuel pump switch-light(s) to OFF if the amber PRESS

light comes on and stays on.CAUTION: DO NOT USE TRUCK SUCTION WHEN YOU DO THE PRESSURE

DEFUELING PROCEDURE. IF YOU USE TRUCK SUCTION WITHFUEL PUMP PRESSURE, THE FLOW RATE CAN BE MORE THANTHE MAXIMUM PERMITTED FLOW RATE. THIS CAN CAUSEDAMAGE TO EQUIPMENT.

i. Make sure that the suction at the fuel truck is off.j. Push the applicable FWD and AFT PUMPS, or L and R CENTER PUMPS switch-lights, on

the P5 Overhead Panel, to the ON position.NOTE : This starts the defueling operation.

WARNING: DO NOT MOVE THE REFUEL/DEFUEL HANDLE TO STOP THE FLOWOF FUEL FROM THE AIRCRAFT. IF YOU MOVE THE HANDLE DURINGTHE DEFUELING OPERATION, THE FUEL FLOW CAN CAUSE THEVALVE TO CLOSE VERY QUICKLY. THIS CAN CAUSE INJURY TOPERSONNEL AND DAMAGE TO EQUIPMENT.

(1) To stop the defueling operation, you will stop the pumps and close the defuel valves.a) Do not stop the defueling operation with the REFUEL/DEFUEL handle.

WARNING: DO THESE STEPS IF FUEL SPILLAGE OCCURS DURINGDEFUELING. INJURY TO PERSONS AND DAMAGE TOEQUIPMENT CAN OCCUR.



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k. If fuel spills, do these steps:(1) Stop the defueling operation.(2) Stop APU operation using the Normal Method.(3) Follow the fire department and operator-provided emergency procedures for spilled fuel

and fire protection.(4) Find and correct the cause of the spilled fuel.(5) Do an inspection of all closed spaces in the area to make sure that they are free of fuel

fumes.(6) Do not start the defuel operation or start the APU again until the fire department or the

person(s) with authority has given approval.l. Monitor the quantity of fuel in the fuel tanks on the fuel quantity indicators of the RCP or on

the EICAS display.m. Push the applicable FWD and AFT PUMPS, or L and R CENTER PUMPS switch-lights to

the OFF position when the necessary quantity of fuel is defueled.NOTE : Defueling operation can be stopped if the DEFUEL VALVES are switched to the

CLOSED position.

n. Put the DEFUEL VALVES switch to the CLOSE position.o. If the tank(s) must be defueled fully, make sure that Fuel Tank Entry Preparation is completed.

4. Put the Aircraft Back to Its Usual Conditiona. Put the REFUEL/DEFUEL handle, on the refuel adapters, to the REFUEL position.b. Disconnect the fueling nozzles.

(1) Make sure that there is no fuel leakage at the refuel adapters.c. If it is installed, disconnect the bonding cable from the refueling station.d. Close this access panel: 521FB - Fixed LE Outboard Of Nacelle Strut Panel. Refer to

Figure 26.01-1.e. Disconnect the bonding cable between the fuel servicing equipment and the aircraft.f. Disconnect the grounding cables for the fuel servicing equipment and the aircraft.

WARNING: KEEP PERSONNEL AWAY FROM THE LEADING EDGE SLATS WHENYOU DO THE REACTIVATION PROCEDURE. THE SLATS MOVEQUICKLY AND CAN CAUSE INJURIES TO PERSONNEL OR DAMAGETO EQUIPMENT.

g. Make sure to reactivate the leading edge slats.h. If it is not necessary for other maintenance tasks, make sure to deactivate electrical power

from the aircraft.C. Aircraft (Suction Method)

1. Generala. This procedure removes fuel from the aircraft without the aircraft fuel pumps. Most of the

fuel can be removed by suction defueling with a fueling truck. The remaining fuel must bedrained from the fuel tanks manually.(1) Suction defueling the main fuel tanks through the suction feed inlets. This requires the

defuel/isolation valves to be open.(2) Suction defueling the center fuel tank through the refuel manifold outlets for the center

tank.b. The system lets you monitor the fuel quantity at the RCP or on the EICAS display.



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c. When thunderstorms or lightning are in the area (approximately a 10 mi (16 km) radius), youmust stop the defueling operation.

d. Defueling operations must stop if there are strong wind conditions.NOTE : Strong wind conditions can cause static electricity to collect. Large quantities of

static electricity can collect on support equipment while parked, from the movementof dust particles and air currents during strong wind conditions.

NOTE : Strong wind conditions also cause the unwanted movement of items or equipment,which can cause injury to personnel and damage to the aircraft.

e. To defuel the tanks fully, drain the remaining fuel through the sump drain valves and makesure the Fuel Tank Entry Preparation is completed.

2. Prepare for the Suction Defuelinga. Make sure that the aircraft has a ground attitude of -0.78° ± 2.0° (nose-down) pitch and 0.0°

± 2.0° roll.NOTE : A ground attitude of -0.78° (nose-down) pitch and 0.0° roll lets you defuel the








d. Do this task to deactivate the leading edge slats: Leading Edge Slat System - Deactivation,AMM B787-A-27-81-00-24A-510B-A.WARNING: OBEY THE APPLICABLE PRECAUTIONS WHEN YOU ATTACH THE

BONDINGCABLES. INSTALL THEBONDINGCABLESATANAPPROVEDAIRCRAFT GROUND CONNECTION TO MAKE SURE THAT THEELECTRICALBOND ISSUFFICIENT. IF THEFUELSERVICEEQUIPMENT



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AND AIRCRAFT DO NOT HAVE A SUFFICIENT ELECTRICAL BOND, AFIRE OR EXPLOSION CAN OCCUR.





f. Open RCP - 521FB-Fixed LE Outboard of Nacelle Strut Panel. Refer to Figure 26.01-1.g. Make sure that the utility lights for the RCP come on.




(1) Make sure to bond the aircraft using Standard Practices.WARNING: MAKE SURE THAT THERE IS NO TENSION ON THE HOSE. THE

HOSEMUST HANG FREELY FROM THE REFUEL ADAPTER, WITHNO FORCE ON IT. TENSION ON THE HOSE CAN CAUSE DAMAGETO THE FUEL RECEPTACLE AND CAUSE THE HOSE TODISCONNECT. INJURIES TO PERSONNEL AND DAMAGE TOEQUIPMENT CAN OCCUR.

i. Connect the refuel nozzle to the refuel adapters.j. Push and hold the TEST switch to the PANEL position to do a test of the fuel quantity

indicators.(1) Make sure that these fuel quantities show on the three fuel quantity indicators while you

hold the TEST switch in the PANEL position:a) RIGHT - 88.8 lbs.b) CENTER - 88.8 lbs.c) LEFT - 88.8 lbs.

(2) Make sure that all of the LEDs on the load select displays come on.NOTE : The load select displays will go back to their usual condition when you release

the TEST switch.

(3) Release the TEST switch.



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CAUTION: DO NOT USE FUEL PUMP PRESSURE WHEN YOU DO THESUCTION DEFUELING PROCEDURE. IF YOU USE FUEL PUMPPRESSURE WITH TRUCK SUCTION, THE FLOW RATE CAN BEMORE THAN THE MAXIMUM PERMITTED FLOW RATE. THIS CANCAUSE DAMAGE TO EQUIPMENT.

k. Make sure that the boost pumps and the override/jettison pumps are off.l. Make sure that all of the MANUAL FUELING valve switches are in the CLOSE position.m. Put the REFUEL/DEFUEL handle, on the refuel adapters, to the DEFUEL position.

3. Procedure - Main Fuel Tanksa. Make sure that all of the MANUAL FUELING VALVES switches are in the CLOSE position.b. Put the DEFUEL VALVES switch to the OPEN position.

(1) Make sure the LOAD SELECT display shows "DEFUEL."c. Push the CROSSFEED switch-light, on the P5 Overhead Panel, to the OPEN position.d. Start the fueling truck suction.

NOTE : This starts the suction defueling operation.

NOTE : If you apply a suction pressure of less than -2.2 psi (-15.2 kPa) to the system, aircan get into the manifold through the center tank pump inlets. If this occurs, thesuction defueling rate can decrease or suction defueling can stop.

WARNING: DO NOT MOVE THE REFUEL/DEFUEL HANDLE TO STOP THE FLOWOF FUEL FROM THE AIRCRAFT. IF YOU MOVE THE HANDLE DURINGTHE DEFUELING OPERATION, THE FUEL FLOW CAN CAUSE THEVALVE TO CLOSE VERY QUICKLY. THIS CAN CAUSE INJURY TOPERSONNEL AND DAMAGE TO EQUIPMENT.

(1) To stop the defueling operation, you will close the defuel valves and stop the fuelingtruck suction.a) Do not stop the defueling operation with the REFUEL/DEFUEL handle.

e. Monitor the quantity of fuel in the fuel tanks on the fuel quantity indicators of the RCP.NOTE : The maximum quantity of fuel will be removed from the main fuel tanks if the loads

in the left and right tanks are equivalent.

(1) Put the DEFUEL VALVES switch to the CLOSE position when one of these two eventsoccurs:a) The necessary quantity of fuel is defueled.b) The fuel quantity does not change.

NOTE : Defueling will stop when the fuel level in one of the main fuel tanks goesbelow the suction feed inlet in that tank.

f. Stop the fueling truck suction.g. Push the CROSSFEED switch-light, on the P5 Overhead Panel, to the CLOSED position.h. Make sure to remove the remaining fuel in the center tank.

4. Suction Defueling - Center Fuel Tanka. Make sure that the DEFUEL VALVES switch is in the CLOSE position.

NOTE : This procedure defuels the center tank without putting the aircraft in the defuelmode. If you put the DEFUEL VALVES switch to the OPEN position, suction



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defueling of the center tank can stop before the maximum quantity of fuel isremoved.

b. Put the CENTER MANUAL FUELING VALVES switch to the OPEN position.NOTE : This opens the refuel valves between the refuel adapters and the center fuel tank.

c. Start the fueling truck suction.NOTE : This starts the suction defueling operation.

d. Monitor the quantity of fuel in the fuel tanks on the fuel quantity indicators of the RCP.(1) Put the CENTER MANUAL FUELING VALVES switch to the CLOSE position when one

of these two events occurs:a) The necessary quantity of fuel is defueled.b) The fuel quantity for the center tank does not change.

NOTE : Suction defueling will stop when the fuel level in the center tank goesbelow one of outlet tubes for the center tank refuel manifold. This willoccur when the center tank fuel quantity is approximately 64,700 lbs.(29,300 kg).

e. Stop the fueling truck suction.f. Make sure to remove the remaining fuel in the center tank.g. Put the REFUEL/DEFUEL handle, on the refuel adapters, to the REFUEL position.h. Disconnect the fueling nozzles.i. If the POWER switch is in the BATTERY position, put the switch to the NORMAL position.j. Close this access panel: 521FB - Fixed LE Outboard Of Nacelle Strut Panel. Refer to

Figure 26.01-1.

END



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Section 26.02 - Fuel Sump - OperationA. Fuel Tank Sump Locations

1. There are two sump drain valves installed in the center fuel tank, one sump drain valve in eachmain fuel tank and one sump drain valve in each surge tank. There are six sump drain valves intotal installed on the airplane.


with scheduled maintenance checks.NOTE : A ground attitude of -0.78° (nose-down) pitch and 0.0° roll lets you defuel the maximum

quantity of fuel from the tanks.

C. Drain the Main Fuel Tank Sumps



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Figure 26.02-1: Fuel Sump Drain Valve Servicing (Page 1 of 2)



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Figure 26.02-2: Fuel Sump Drain Valve Servicing (Page 2 of 2)

END



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Table of contents

27.01 FUELING MANUAL - E190GENERAL..........................................................................................................................1

27.02 GENERAL FUELINGGENERAL..........................................................................................................................1

27.03 FUEL TANK SUMPINGGENERAL..........................................................................................................................1

27.04 NORMAL FULING (AUTO)PROCEDURE....................................................................................................................1

27.05 MANUAL FUELINGGENERAL..........................................................................................................................1

27.06 GRAVITY REFUEL OPERATIONPROCEDURE....................................................................................................................1

27.07 REFUELING WITH ENGINE OPERATIONGENERAL..........................................................................................................................1PROCEDURES - STATIONS NOT EQUIPPED WITH JETWAYS.....................................1PROCEDURES - STATIONS USING JETWAYS...............................................................2

27.08 FUEL TRANSFERGENERAL - WITH AC POWER ON AIRCRAFT...............................................................1

27.09 PRESSURE/SUCTION DEFUELINGGENERAL..........................................................................................................................1

27.10 FUELING WITH INOPERATIVE FUEL GAUGESINACCURATE OR INOPERATIVE FUELING QUANTITY INDICATORS..........................1OPERATION OF LEVELING SCALE AND MAGNETIC LEVEL INDICATORS (MLIS).....1CALCULATING FUEL QUANTITY.....................................................................................6DETERMINING FUEL QUANTITY BY MEASURING STICK............................................7

27.11 MAGNETIC LEVEL INDICATING TABLES

TOCFueling Manual - E190


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Section 27.01 - Fueling Manual - E19027.01.1 General

WARNING: DO NOT OPERATE THE HF COMMUNICATION SYSTEM WHILE FUELING THEAIRPLANE. A FIRE OR AN EXPLOSION CAN OCCUR.

GROUND EQUIPMENT MUST NOT BE POSITIONED UNDER WING TIPS DURINGFUELING OPERATION.

FUELING VEHICLE MUST BE PROPERLY BONDED TO AIRCRAFT BEFORE ANYFUELING/DEFUELING OPERATION.

WHEN THERE IS AN INACCURATE/INOPERATIVE OR A SUSPICION OF A GAUGENOT INDICATING PROPERLY, STOP FUELING AND NOTIFY AIRCRAFTMAINTENANCE IMMEDIATELY.

NOTE : If a fuel component(s) is currently onMinimumEquipment List (MEL) placard as being inoperative,aircraft maintenance does not need to be notified, unless specific procedures during fuelingoperations require the attention of aircraft maintenance.

WARNING: IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION, NOTIFY AIRCRAFT MAINTENANCE IMMEDIATELY. DO NOT STARTOR RESUME FUELING OPERATIONS UNTIL CORRECTIVE ACTION HAS BEENTAKEN.

DO NOT START OR SHUT DOWN AUXILIARY POWER UNIT (APU) IF FUEL SPILLOCCURS.

DEFUELING OR TRANSFERRING FUEL WITH PASSENGERS ONBOARD THEAIRCRAFT IS PROHIBITED, EXCEPT UNDER CERTAIN CONDITIONS.

Table 27.01-1: Usable Fuel

Mass (lbs)Volume (gal)

28637.84275.03Total Usable Fuel

14318.92137.15Left Tank

14318.92137.15Right Tank

Table 27.01-2: Refueling Limitations

Under Leading Edge Right WingFuel Panel Location Primary

Flight Deck IndicatorsQuantity System Maximum

800 lbsAsymmetrical Load Maximum

40 psigPrimary Fuel Pressure

50 psigMaximum Secondary Fuel Pressure

35 psigMinimal Fuel Pressure

Max Refuel Time 15 MinutesMaximum Refuel Rate

NOTE : Fuel pressure should not exceed a constant 50 psig at any time during the fueling operation.

A. Two fuel tanks integral with the wings.

Section 27.01Fueling Manual - E190


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B. Tanks isolated by a common boundary on the centerline of the aircraft.C. Tanks are independently gauged and refueled.

Figure 27.01-1: Fuel Tank Diagram

END

Section 27.01Fueling Manual - E190


Rev. 07


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Section 27.02 - General Fueling27.02.1 General

NOTE : The following material will outline the procedures for fueling American Airlines (AA) EMB 190aircraft. These procedures outline the necessary steps to make sure a safe and efficient fuelingoperation.

NOTE : The use of JP-4 and Jet B is prohibited on all E190 aircraft.

A. Obtain a Jet Fuel Service Record (Fuel Slip). Refer to Section 15.01.1. Aircraft engines must be shut down and wheel chocks must be in place before positioning fueling

equipment around aircraft.B. Properly position the refueling vehicle as outlined in Figure 27.02-1, or as designated by local authority.

1. Maintain 5 feet separation between aircraft and refueler.2. Never back refueler (tank truck) towards or away from the aircraft without a guide person.

NOTE : For vehicles equipped with an operating back up video camera and monitor, the useof a guide person is not required.

3. Never position refueler under aircraft during fueling, with the exception of stationary hydrant hosefueling units. (Delineation of the location of the unit must be approved by Fuel Engineering).CAUTION: ATTACH BONDING CABLES ONLY TO SPECIFIED POINTS ON THE

AIRPLANE. INCORRECTLY ATTACHED BONDING CABLES CAN CAUSESCRATCHES. THESESCRATCHESCANCAUSECORROSIONANDCRACKSON STRESSED PARTS. BONDING CABLES ATTACHED TO COMPOSITEDOORS OR FAIRINGS DO NOT GIVE AN ELECTRICAL BOND.

C. Bond refueler to aircraft bonding lug on right main landing gear.



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Figure 27.02-1: Fuel Equipment Parking Positions

END



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Section 27.03 - Fuel Tank Sumping27.03.1 General

A. Fuel Tank Sump Locations1. There are two fuel sump drain valve locations, one on each collector tank.


with scheduled maintenance checks.

Figure 27.03-1: To Open (From CLOSED Position)

Section 27.03Fuel Tank Sumping


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Figure 27.03-2: To Close (From OPEN Position)



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Figure 27.03-3: For Maintenance (From CLOSED Position)



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Figure 27.03-4: Fuel Sump Drain Locations

END



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Section 27.04 - Normal Fuling (Auto)27.04.1 Procedure

NOTE : The following procedure should be performed with power on the aircraft and all fuel systemcomponents operative.

A. Bond the fueling equipment to the aircraft.B. Open fuel panel door. Refer to Figure 27.04-1 for door location.C. Legibly enter the gauge reading before fueling for each tank on the Jet Fuel Service Record (Fuel

Slip). Refer to Section 15.01.D. Make sure the left hand (LH) and right hand (RH) refueling lights are OFF.E. Make sure the defueling indication light is OFF.F. Set the refueling switch to the AUTO position.G. Set the repeater indicator to the required fuel quantity release load.H. Remove the cap from the pressure refueling/defueling adapter assembly.I. Connect the fuel nozzle to the pressure refueling/defueling adapter assembly.

CAUTION: BEFORE APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLES TO THELOCKED POSITION AND OPEN POPPET ACTUATING LEVER. ATTEMPT TOREMOVENOZZLE. IF NOZZLECANBEREMOVED, IT IS DEFECTIVEANDMUSTBE REMOVED FROM SERVICE.

J. Open the handle on the fuel nozzle.K. Pressurize the fuel system by operating the appropriate deadman device (minimum 35 psig, maximum

40 psig primary, 50 psig secondary, and fuel nozzle pressure).L. Make sure the LH and RH refueling indication lights are ON and there is no fuel flow.M. Set the refueling switch to the OPEN position and make sure the LH and RH refueling indication lights

go OFF.N. When the required fuel quantity release load is delivered, stop fueling by releasing the deadman (the

LH and RH refueling indication lights go ON).O. Set the refueling switch to the CLOSED position.P. Before closing the fuel nozzle valve, ensure all hose pressure is relieved. Close the handle to the fuel

nozzle.NOTE : If the pressure in the fuel hose fails to bleed, deactivate the fuel equipment deadman by

releasing the deadman switch or valve handle. Place the refueling switch to the OPENposition and increase the fuel quantity indicator until the pressure in the fuel hose releases.Place the refueling switch to the CLOSED position.

Q. Disconnect the fuel nozzle from the pressure refueling/defueling adapter assembly.R. Install the cap to the pressure refueling/defueling adapter assembly.S. Legibly complete all applicable fields on the Fuel Slip. Refer to Section 15.01.T. Close the fueling panel door.U. Remove the bonding cable.V. Perform a walk-around inspection, making sure that all fueling equipment is stowed and the fuel nozzle

adapter cap is replaced.

Section 27.04Normal Fuling (Auto)


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Figure 27.04-1: Fuel Panel

END

Section 27.04Normal Fuling (Auto)


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Section 27.05 - Manual Fueling27.05.1 General

A. Bond the fueling equipment to the aircraft.B. Open fuel panel door. Refer to Figure 27.05-1.C. Legibly enter the gauge reading before fueling for each tank on the Jet Fuel Service Record (Fuel

Slip). Refer to Section 15.01.D. Make sure the left hand (LH) and right hand (RH) refueling indication lights are OFF.E. Make sure the defueling indication light is OFF.F. Set the refueling switch to the MANUAL position.G. Remove the cap from the pressure refueling/defueling adapter assembly.H. Connect the fuel nozzle to the pressure refueling/defueling adapter assembly.I. Open the valve handle on the fuel nozzle.J. Pressurize the fuel system (minimum 35 pounds per square inch gauge (psig), maximum 40 psig,

primary 50 psig, and secondary fuel nozzle pressure).K. Make sure the LH and RH refueling indication lights are ON and there is no fuel flow. Using the fueling

equipment, pressurize the fuel system by operating the appropriate deadman device (minimum 35psig, maximum 40 psig primary, 50 psig secondary, and fuel nozzle pressure).

L. Set the refueling switch to the OPEN position and make sure the LH and RH refueling indication lightsgo OFF.

M. When the required fuel quantity release load is delivered, stop fueling by releasing the deadman. Setthe refueling switch to the CLOSED position.

N. Make sure the LH and RH refueling indication lights come ON and the fuel flow stops.O. Close the valve handle on the fuel nozzle.P. Disconnect the fuel nozzle from the pressure refueling/defueling adapter assembly.Q. Install the cap on the pressure refueling/defueling adapter assembly.R. Set the refueling switch to the AUTO position.S. Legibly complete all applicable fields on the Fuel Slip. Refer to Section 15.01.T. Close fueling panel door.U. Remove the bonding cable.V. Perform a walk-around inspection, making sure all fueling equipment is towed and the aircraft fuel

nozzle adapter cap is replaced and secure. Fuel panel door is closed and latched.

Section 27.05Manual Fueling


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END

Section 27.05Manual Fueling


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Section 27.06 - Gravity Refuel Operation27.06.1 Procedure

A. Observe general fueling procedures. Refer to Section 27.02.B. Use ladder or suitable stand at wing leading edge. Refer to Figure 27.06-1.C. Bond over wing fuel nozzle to the bond adapter on the wing.D. Remove fuel cap.E. When the required fuel load is delivered, remove nozzle.F. Replace fuel cap.G. Remove nozzle-bonding wire.

Figure 27.06-1: Fuel Tank - Gravity Fueling

END

Section 27.06Gravity Refuel Operation


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Section 27.07 - Refueling with Engine Operation27.07.1 General

NOTE : When the APU is "inoperative" and the aircraft is at a station where no ground power cart isavailable, the aircraft can be fueled with the No. 1 (left) engine operating at "idle."

NOTE : It is the responsibility of the Supervisor Maintenance or Manager Customer Service at thosestations not provided with maintenance, to make sure that, when conditions warrant fueling withNo. 1 (left) engine operating, the following is strictly enforced.

A. Before refueling operations with the No. 1 (left) engine operating, Maintenance Operations Control(MOC) must be contacted in person for approval.

B. Fuel servicing with No. 1 (left) engine running is allowed if there are no restrictive local ordinances.CAUTION: COMMUNICATIONBETWEENCOCKPITANDGROUNDPERSONNEL ISCRITICAL

AND MUST BE MAINTAINED THROUGHOUT THE ENTIRE OPERATION.

C. All servicing personnel must be thoroughly familiar with these procedures before arrival of the aircraft.This must include Flight, Maintenance, Customer Service, Catering and Fueling personnel. Safetypersonnel must be equipped with flashlights after dark.

D. Two pilots or qualified run-up personnel must be present in the cockpit during fueling.E. Observer/safety personnel must remain in positions for the entire fueling/servicing operation. Refer

to Figure 27.07-1 and Figure 27.07-2.F. During fueling operation, cockpit switches will be left "as is." Do not change cockpit fuel switches

during fueling operation.G. The fuel truck must be parked parallel to the fuselage and 10 feet from the right wing tip.H. All fuel safety procedures must be strictly adhered to.I. In the event of a fuel spill, the operating engine must be shut down.

27.07.2 Procedures - Stations not Equipped with Jetways

A. On arrival of the aircraft at the gate, the No. 2 (right) engine will remain operating and the No. 1 (left)engine will be shut down.

B. When the No. 1 (left) engine is shut down, the flight crew will signal ground personnel that it is safeto approach the aircraft for chocking wheels and deplaning passengers.

C. Customer Service/Maintenance personnel will assume safety positions to warn off all personnel andvehicles from the right side of the aircraft until the engine is shut down and passenger off-loading iscompleted. Refer to Figure 27.07-1.

D. After all passengers (including thru passengers) are deplaned, the No. 1 (left) engine can be startedand the No. 2 (right) engine shut down.CAUTION: TAIL SAFETY PERSONNELWILL MOVE TO LEFTWING TIP BEFORE STARTING

THE NO. 1 (LEFT) ENGINE.

E. Customer Service/Maintenance Personnel will assume positions to warn off all personnel and vehiclesfrom the left side of the aircraft. Refer to Figure 27.07-2.

F. Normal baggage handling and aircraft fueling can be done with the No. 1 (left) engine running.G. On completion of fueling, catering, cargo, etc., the No. 2 (right) engine will be started and the No. 1

(left) engine shut down.CAUTION: TAIL SAFETY WILL MOVE TO RIGHT WING TIP POSITION BEFORE STARTING

THE NO. 2 (RIGHT) ENGINE.

Section 27.07Refueling with Engine Operation


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H. Customer Service/Maintenance Personnel will resume positions until departure. Refer to Figure 27.07-1.I. Passengers can be loaded with No. 2 (right) engine running and No. 1 (left) engine shut down.

27.07.3 Procedures - Stations Using Jetways

A. On arrival of the aircraft at the gate, the No. 1 (left) engine can be shut down.B. Customer Service/Maintenance Personnel will chock the aircraft from the right side and locate safety

personnel. Refer to Figure 27.07-2.NOTE : Safety personnel must remain in position until departure.

C. The Jetway can be moved into position and all passengers deplaned.D. Servicing operations can be done as normal from the right side of the aircraft.E. On completion of fuel servicing, passengers can be boarded.



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Figure 27.07-1: Right Engine Running

Figure 27.07-2: Left Engine Running

END



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Section 27.08 - Fuel Transfer27.08.1 General - With AC Power on Aircraft

A. Open fuel panel door. Refer to Figure 27.08-2.B. Make sure the power selection switch is set to NORMAL.C. Make sure the left hand (LH) and right hand (RH) refueling indication lights are OFF.D. Make sure the defueling indication light is OFF.E. Select the defuel switch to the OPEN position. Defuel OPEN light will come on.

CAUTION: DAMAGE TO THE FUEL PUMP WILL OCCUR IF IT IS OPERATED DRY.

NOTE : All switches and circuit breakers in the Flight Deck must be operated by the Flight Crew orMaintenance personnel.

F. Pull the circuit breaker (Refuel 2) for the left to right transfer or (Refuel 1) for right to left transfer.G. Make sure the AC PUMP 1 and AC PUMP 2 switches are in AUTO. Refer to Figure 27.08-1.H. Place the XFEED switch to - LOW 2 for left to right transfer or LOW 1 for right to left transfer.I. When desired, quantity of fuel is transferred.J. Select the XFEED switch to OFF and reset the circuit breaker that was pulled.K. Select the defuel shutoff switch to the CLOSED position.L. The defuel OPEN light will go OFF.M. Close fuel panel door.



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Figure 27.08-1: Flight Deck Fuel Panel



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END



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Section 27.09 - Pressure/Suction Defueling27.09.1 General

A. Perform General Fueling Procedures. Refer to Section 27.02.1.B. Open fuel access doors. Refer to Figure 27.09-1.C. Make sure the defueling indication light is OFF.D. Remove the cap from the pressure refueling/defueling adapter assembly.E. Connect the fuel nozzle to the pressure refueling/defueling adapter assembly.F. Open the valve handle on the fuel nozzle.G. Set the defuel switch to the OPEN position and make sure the defueling indication light comes ON.H. On the fuel control panel, set the XFEED switch as applicable:

1. To defuel both tanks, set the switch to the LOW 2 position.2. To defuel left hand (LH) tank, set the switch to the LOW 2 position.3. To defuel right hand (RH) tank, set the switch to the OFF position.

I. Apply suction to the fuel nozzle or set the AC pumps switches on the fuel control panel, as applicable:1. To defuel both tanks, set AC pump 1 and AC pump 2 switches to the ON position.2. To defuel the LH tank, set AC pump 1 switch to the ON position.3. To defuel the RH tank, set AC pump 2 switch to the ON position.

J. After completion of the defueling operation, set the defueling switch to the CLOSED position and makesure the defueling indication light goes OFF.

K. Set the XFEED switch to the OFF position.L. Set the AC pump 1 and AC pump 2 switches to the AUTO position.M. Close the valve handle on the fuel nozzle.N. Disconnect the fuel nozzle from the pressure refueling/defueling adapter assembly.O. Install the cap to the pressure refueling/defueling adapter assembly.P. Close fueling panel door.Q. Remove the grounding cable.

Section 27.09Pressure/Suction Defueling


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Figure 27.09-1: Control Panels and Locations

END

Section 27.09Pressure/Suction Defueling


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Section 27.10 - Fueling with Inoperative Fuel Gauges27.10.1 Inaccurate or Inoperative Fueling Quantity Indicators

A. Method 1 - Not applicable (N/A) to E190 aircraft.B. Method 2 - For use on main tanks (wings) when the aircraft is within the level range of - 2.0 degrees

(°) to 0.0° pitch and from 0.0° to 1.0° roll and when fuel on board can be determined using fuelmeasuring sticks both before and after the refueling operation. Refer to Section 15.01.1. Determine if aircraft is within the above limits of pitch and roll. These are the limits of the MLI

tables used to convert the MLI readings.2. Before fueling, determine existing fuel tank quantity with the measuring stick(s) of the affected

tank. Refer to Section 27.10.2. Subtract this quantity from the tank quantity required and convertto gallons. Fuel the tank to desired level, using the fueling equipment meter and overwing fueling.Use measuring stick(s) to verify tank quantity. Refer to Section 27.10.4.NOTE : If the fueling equipment dispenses in liters, convert the required liters to gallons, to

deliver the desired known quantity. Refer to Section 15.01.

3. Give flight crew completed copy of fuel slip and an Inoperative Fuel Quantity Indicator servicerecord making sure all required entries and signatures are legible and in place as early aspracticable, before departure.

C. Method 3 - For use on main tanks (wings) to verify the known quantity when fuel on board cannot bedetermined using fuel measuring sticks both before and after the refueling operation. Refer to Section15.01.1. Completely defuel tank with the inoperative indicator by transferring fuel to other tank or defueling.

Refer to Section 27.08 and Section 27.09.WARNING: MAKE SURE THAT THE AIRCRAFT IS IN A SAFE CONDITION BEFORE YOU

DO THE PROCEDURES. THIS IS TO PREVENT INJURY TO PERSONSAND/OR DAMAGE TO THE EQUIPMENT.

CAUTION: MAKE SURE THAT THE NACA AIR INTAKE IS NOT BLOCKED AND THATTHE NACA AIR INTAKE IS FREE FROM BLOCKAGE. FAILURE TO OBEYTHESE CAUTIONS CAN DAMAGE THE AIRCRAFT.

CAUTION: OBEY THE MAXIMUM PERMITTED CAPACITY OF THE TANK DURING THEFUEL TRANSFER. IF YOU DO NOT MONITOR THE FUEL QUANTITY, ANOVERFILLING CAN OCCUR.

2. Fuel tank with inoperative indicator separately. Transfer from the tank with the operational indicationor overwing fueling as gauged by the fueling equipment meter to quantity of fuel required.

3. Fill the tank with operative indicator to quantity of fuel required.NOTE : Use of Method 3 requires final verification by measuring stick. Refer to Section 27.10.4.

4. Give the flight crew the completed copy of fuel slip and an Inoperative Fuel Quantity Indicatorservice record, making sure all required entries and signatures are legible and in place, as earlyas practicable before departure. Refer to Section 15.01.

27.10.2 Operation of Leveling Scale and Magnetic Level Indicators (MLIs)

A. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), aVendor Supervisor, Lead or Supervisor/Lead, Designated Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

B. MLIs show the amount of fuel in the tank using mechanically operated measuring sticks.

Section 27.10Fueling with Inoperative Fuel Gauges


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C. The MLIs are installed on the skin of the lower wing. There are three in each wing.D. The following procedures are performed with power on the aircraft (for example, ground, auxiliary

power unit (APU) or aircraft batteries).E. Make sure the aircraft is within the pitch and roll limits performing a Pitch and Roll Check. This task

can be performed by:1. The Pitch and Roll Leveling Scale is installed in the left-hand side of the main landing gear wheel

well. Refer to Figure 27.10-1. To do this task, a plumb bob is needed, which is located in thePlumb Bob Kit stored in the aircraft flight deck.WARNING: MAKE SURE THAT THE LANDING GEAR SAFETY PINS ARE INSTALLED.

THIS IS TOPREVENT INJURIESTOPERSONSANDDAMAGETOMATERIAL.

CAUTION: MAKE SURE THAT YOU READ THE CORRECT VALUE. IF YOU READ AWRONG VALUE, THE FUEL QUANTITY WILL STAY INCORRECT. FAILURETO OBEY THIS PRECAUTION CAN DAMAGE THE EQUIPMENT ANDINJURIES TO PERSONS CAN OCCUR.

NOTE : Coordinate with Aircraft Maintenance to open/close the landing gear doors andinstall/remove the safety pins.

a. Make sure that the GSE 039 indication is from - 2.0 degrees (°) to 0.0° pitch and from 0.0°to 1.0° roll, on the leveling scale.

2. The Inertial Reference System (IRS) (through Multifunction Control Display Unit (MCDU)). Referto Figure 27.10-2.NOTE : Operation of the IRS (through MCDU) in the cockpit must be done by the Flight Crew

or Aircraft Maintenance.

a. On MCDU 1, push the NAV key, MCDU 1 shows the NAV INDEX page.b. On MCDU 1, push the LSK (POS SENSORS), MCDU 1 shows the POS SENSORS page.c. On MCDU 1, push the LSK (IRS 1 STATUS) to see the status of IRS 1, MCDU 1 shows the

IRS 1 STATUS page.WARNING: MAKE SURE THAT YOU READ THE CORRECT VALUE. IF YOU READ

A WRONG VALUE, THE FUEL QUANTITY WILL STAY INCORRECT.FAILURETOOBEYTHISPRECAUTIONCANDAMAGETHEEQUIPMENTAND INJURIES TO PERSONS CAN OCCUR.

d. On the IRS 1 STATUS page, record the value and inclination direction of the aircraft pitch(1) and roll angle (2).NOTE : When the pitch and roll values are positive, the pitch and left wing are up. When

the pitch and roll values are negative, the pitch and left wing are down.

e. Make sure that the pitch indication is from - 2.0° to 0.0°.f. Make sure that the roll indication is from - 1.0° to 1.0°. In the tables, only positive roll values

are considered. Do the considerations that follow:(1) For negative roll values (consider them as positive values), the left wing is the low wing

and the right wing is the high wing.(2) For positive roll values, the left wing is the high wing and the right wing is the low wing.

F. The pitch and roll limits are -2.0° to 0.0° pitch and 0.0° to 1.0° roll on the Leveling Scale.1. If the pitch and roll calculations show the aircraft is beyond the allowable limits, the aircraft must

be moved to another location and checked again for level.



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a. If the aircraft cannot be repositioned, or a level position is not available, contact applicableOperations personnel in person and request the aircraft fuel release be amended to fuel thewings to the high level shut off. On completion of the high level shut off fueling operation,check the outboard #3 MLI Stick and verify the required fuel quantity is correct.

b. Aircraft can be overwing fueled to its full amount using the overwing procedures.G. Pitch and roll can differ from before fueling to after fueling. Make sure you take pitch and roll before

and after fueling.1. When the pitch and roll procedure is complete, remove the plumb bob from the main wheel well

adapter and return it to the Plumb Bob Kit.H. There are three MLIs in each wing. Refer to Figure 27.10-3.I. To release the MLIs, push and turn the MLI to the left.J. To find the fuel quantity in one of the wing tanks, examine each MLI in the direction of OUTBOARD

to INBOARD, until you have one that is not at its lower stop (0 on the calibrated rod).K. Lock the MLI by slowly pushing the indicator up until it meets the lower surface of the wing. Turn the

indicator to the right until it is in the LOCKED position.NOTE : Aircraft can be overwing fueled using the overwing procedures.



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Figure 27.10-1: Plumb Bob and Leveling Scale



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Figure 27.10-2: IRS (through MCDU)



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Figure 27.10-3: MLI

27.10.3 Calculating Fuel Quantity

NOTE : Refer to Section 15.01.

A. Record the pitch and roll attitudes derived from the leveling scale and Plumb Bob or IRS (throughMCDU) for before fueling readings on the Inoperative Fuel Quantity Indicator service record.

B. To obtain the amount of fuel in the desired tank before fueling, operate the applicable MLI. Read theindex number shown on the magna level indicator rod.

C. Record the number in units, in the applicable space provided on the Inoperative Fuel Quantity Indicatorservice record.

D. To identify the applicable MLI table (stick chart(s)) based on aircraft attitude, refer to Section 27.11.WARNING: MAKE SURE THE CORRECT VALUE IS READ. IF THEWRONG VALUE IS READ,

THE FUELQUANTITYWILL BE INCORRECTANDTHEACTUAL FUELQUANTITYMAY NOT BE SUFFICIENT TO COMPLETE THE FLIGHT.

E. Find the related fuel quantity in the applicable table, based on pitch, roll and stick index number.F. Record the amount of fuel in the tank (pounds, on the space provided) on the Inoperative Fuel Quantity

Indicator service record.G. Determine the amount of fuel that needs to be added to the desired wing fuel tank by subtracting the

amount of fuel in the tank before fueling (repeat the process "Find the related fuel quantity" above)from the total amount of fuel to be added to the desired wing fuel tank.



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H. Convert the amount of fuel in pounds to be added to a stick index number.I. Observe the movement of the MLI during the fueling operation. The required amount of fuel is delivered

when the index number desired is reached. Close the refueling switch.J. Do the process above, record the findings in the applicable AFTER FUELING portions of the Inoperative

Fuel Quantity Indicator service record.


A. Anytime fuel quantity is determined by measuring stick, the following procedure must be used:1. Determine the method, 2 or 3, (refer to Section 27.10.1) to be utilized to fuel the aircraft and check

the applicable box on the Inoperative Fuel Quantity Indicator Service Recorda. When using method 2, perform the following:



Fuel Quantity Indicator Service Record:a. Identify and record the tank with the inoperative quantity indicator (ex. L, LI, C,

ACT1, Trim, etc.) in the space provided below "TANK".b. Record the before fueling aircraft attitude (pitch & roll).c. Circle the stick(s) utilized before fueling (all aircraft) & applicable inner/outer cell

(Airbus 319/320 aircraft only).d. Record the units/inches read from the applicable stick(s) in the before fueling spaces.e. Record the before fueling quantity from the applicable stick chart in pounds on the




Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch & roll).b) Circle the stick(s) utilized after fueling (all aircraft) & applicable inner / outer cell

(Airbus 319/320 aircraft only).c) Record the units / inches read from the applicable stick(s) in the after fueling spaces.d) Record the after fueling quantity from the applicable stick chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Ensure all sticks are secured and initial where applicable; print your name, present

title, and company name followed by your complete signature (no initials).f) Legibly complete all applicable fields on the fuel slip - Refer to Section 15.01.


b. When using method 3, perform the following:



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(1) Empty the affected tank by defueling or transferring all remaining fuel to other tanks.Refer toSection 27.08.1 or Section 27.09.1.

(2) Record the before fueling information where applicable on the fuel slip and InoperativeFuel Quantity Indicator Service Record:a) Identify and record the tank with the inoperative quantity indicator (ex. L, LI, C,

ACT1, Trim, etc.) in the space provided below "TANK".b) Leave the before fueling aircraft attitude (pitch & roll) spaces blank and do not circle

any stick(s) utilized before fueling & applicable inner / outer cell tanks.c) Record the before fueling quantity of zero pounds on the fuel slip and the Inoperative




Fuel Quantity Indicator Service Record:a) Record the after fueling aircraft attitude (pitch & roll).b) Circle the stick(s) utilized after fueling (all aircraft) & applicable inner / outer cell

(Airbus 319/320 aircraft only)c) Record the units / inches read from the applicable stick(s) in the after fueling spaces.d) Record the after fueling quantity from the applicable stick chart in pounds on the

fuel slip and the Inoperative Fuel Quantity Indicator Service Record.e) Ensure all sticks are secured and initial where applicable; print your name, present

title, and company name followed by your complete signature (no initials).f) Legibly complete all applicable fields on the fuel slip - Refer to Section 15.01.g) The stick reading in inches and conversion to pounds must be verified by a cockpit

crew member by reviewing the completed fuel slip and Inoperative Fuel QuantityIndicator service record.

END



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Section 27.11 - Magnetic Level Indicating TablesA. Refer to E190 Magnetic Level Indicating Tables as follows:


END

Section 27.11Magnetic Level Indicating Tables


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Table of contents

28.01 FUELING MANUAL - MD-80GENERAL..........................................................................................................................1UNDERWING PRESSURE FUELING - AUTOMATIC OPERATION (WITH ELECTRICALPOWER)............................................................................................................................9UNDERWING PRESSURE FUELING - AUTO OVERRIDE OPERATION (WITHELECTRICAL POWER)...................................................................................................13UNDERWING PRESSURE FUELING - AUTOOVERRIDEOPERATIONWITH FUEL FILLVALVE ELECTRICALLY OPERATIVE.............................................................................14UNDERWING PRESSURE FUELING - MANUAL OPERATION (WITHOUT ELECTRICALPOWER)..........................................................................................................................16OVERWING (GRAVITY) FUELING - MAIN FUEL TANKS..............................................17TANK-TO-TANK GROUND TRANSFER OF FUEL.........................................................20INACCURATE OR INOPERATIVE MAIN AND CENTER TANK QUANTITY INDICATORSAND/OR FLIGHT DECK FUEL QUANTITY DISPLAY.....................................................22INACCURATE OR INOPERATIVE FWD AND/OR AFT AUXILIARY TANK QUANTITYINDICATORS...................................................................................................................26OPERATION OF FUEL QUANTITY MEASURING STICKS............................................30DETERMINING FUEL QUANTITY BY MEASURING STICK..........................................31DEFUELING....................................................................................................................32

28.02 MD-80 FUEL QUANTITY VERIFICATION CHART

TOCFueling Manual - MD-80


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Section 28.01 - Fueling Manual - MD-8028.01.1 General

NOTE : This section contains procedures to fuel the MD-80 series (MD-82, 83) aircraft. There may bea procedure that pertains to a particular aircraft within this series which will be noted as such.

NOTE : Only AMTs or aircraft crew members are authorized to open/close the NLG doors.

NOTE : The use of JP-4 and Jet B is prohibited on all MD-80 aircraft.

A. Fueling can be accomplished by the pressure or gravity method, with or without power, utilizingconventional ground support equipment. The airplane is normally fueled by the pressure method.Overwing gravity method should be considered as an emergency procedure.

B. The fuel system has two main tanks, one center tank, and, if equipped, one or two auxiliary tanks(FWD/AFT). There is also a vent surge tank located in each wing, outboard of the wing tank. Referto Figure 28.01-7.1. For all MD-80 aircraft:

a. Center tank has an approximate volume of 3,074 USgal.b. Main (wing) tanks each have an approximate volume of 1,383 USgal.c. If equipped, each auxiliary tank has an approximate volume of 565 USgal


CAUTION: MAIN TANKSMUSTNOTBEFILLEDTOCAPACITYWITHFUELOFDENSITYEXCEEDING 7.1 LBS/US GALLON, AT LOADING FUEL TEMPERATURE.

A)

B) THE ADDITION OF FUEL ADDITIVES SUCH AS PHILLIPS PFA-55MBDIRECTLY TO AIRCRAFT FUEL TANKS AS UNMIXED ADDITIVES, WILLCAUSE DAMAGE TO RUBBER FUEL BLADDERS, TANK SEALANTS, ANDCOMPONENTSEALS. ADDITIVEMIXING ISNORMALLYDONEBYTHEFUELSUPPLIER.

NOTE : Fuel trucks/tankers are not to be disconnected from a/c until all fueling discrepancies havebeen cleared.

WARNING: GROUND EQUIPMENT MUST NOT BE POSITIONED UNDER WING TIPSDURINGFUELINGOPERATION. THEWINGSAREDEFLECTEDDOWNWARD

A)

UNDER THE FUEL LOADWITH THEWING TIPS BEING DEFLECTEDMOST.FUEL TANKS ARE VENTED THROUGH THE WINGS TIPS WHICH MAYPRODUCEADANGEROUSANDEXPLOSIVEMIXTUREAROUNDTHEWINGTIPS.

B) DO NOT OPERATE RADIO, RADAR, OR ANY OTHERELECTRICAL/ELECTRONIC EQUIPMENT ON AIRCRAFT EXCEPT ASSPECIFIED.

C) RADAR AND HIGH-FREQUENCY EQUIPMENTOPERATING IN VICINITY OFAIRCRAFTDURINGREFUELING/DEFUELINGOPERATIONS ISHAZARDOUS.

D) DO NOT START OR SHUT DOWN APU SHOULD FUEL SPILL OCCUR.E) FUELING VEHICLEMUST BE PROPERLY BONDED TO AIRCRAFT BEFORE

ANY FUELING/DEFUELING OPERATION.F) WHEN THERE IS AN INACCURATE/INOPERATIVE OR A SUSPICION OF A

GAUGE NOT INDICATING PROPERLY, STOP FUELING AND NOTIFYAIRCRAFT MAINTENANCE IMMEDIATELY IN PERSON.

Section 28.01Fueling Manual - MD-80


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G) NOTE: IF A FUEL COMPONENT(S) IS CURRENTLY ON MEL PLACARD ASBEING INOPERATIVE, AIRCRAFT MAINTENANCE DOES NOT NEED TO BENOTIFIED, UNLESS SPECIFIC PROCEDURES DURING FUELINGOPERATIONS REQUIRE THE ATTENTION OF AIRCRAFT MAINTENANCE.

H) IF A CIRCUIT BREAKER IS TRIPPED, TRIPS OR OPENS DURING FUELINGOPERATION,NOTIFYAIRCRAFTMAINTENANCE IMMEDIATELY INPERSON.DO NOT START OR RESUME FUELING OPERATIONS UNTIL CORRECTIVEACTION HAS BEEN TAKEN.

CAUTION: A) CHECK THAT MAIN GEAR INBOARD DOORS ARE CLOSED BEFOREFUELING AIRCRAFT.

B) DO NOT FUEL MD-80 AIRCRAFT WITH TAIL SUPPORT INSTALLED.

C. Pressure Fueling1. Pressure fueling is accomplished through a single point pressure fueling receptacle, with or

without electrical power. The fueling station consists of one (1) pressure fueling receptacle andcontrol panel. The control panel is used for controlling andmonitoring the pressure fueling operationand contains fuel quantity indicators and switches (refer to Figure 28.01-1, Figure 28.01-2, andFigure 28.01-3).

2. Fuel flows through the pressure fueling receptacle (manifold) and is directed to any or all fueltanks desired through electrically or manually operated fuel tank fill valves which are containedin the fueling station.a. The aircraft fueling control panel is located in the right midwing leading edge, approximately

5 1/2 feet from ramp level. Access to the fueling control panel is through a forward swinginghinged access door located in the lower surface of the right wing leading edge (refer toFigure 28.01-1).

b. When pressure fueling with electrical power, the respective tank fill valves automaticallyclose when the tank fuel load equals the pressurized fuel quantity (load) selector setting.NOTE : If nose gear strut is near the fully extended position, the oleo switch will be actuated

and electrical power to fuel control panel will be off.

c. When pressure fueling without electrical power, the fill valves must be manually closed, whenthe desired fuel load in each tank, either partial or full, is attained.

d. Maximum allowable out-of-balance between fwd and aft auxiliary tanks for flight is 400 lbs.of fuel.

e. If both transfer pumps in either auxiliary tanks are inoperative, do not fuel auxiliary tanks.D. Gravity Fueling

1. The left and right main fuel tanks can be gravity fueled through the overwing fill receptacle locatedapproximately 10 feet inboard of each wing tip. Procedures for gravity fueling the left and rightmain tanks are identical.

2. Overwing gravity fueling of the aircraft fuel tanks becomes necessary only when pressure fuelingfacilities are not available.

3. The center tank, fwd and aft auxiliary tanks, can be filled by fuel transfer from the main tanks.E. Fuel Quantity Measuring

1. The primary measuring devices used in determining fuel quantity are the cockpit and underwingfuel quantity indicators. The underwing fuel quantity indicators, located on the control panel areused during normal fueling operations (refer to Figure 28.01-3 and Figure 28.01-4).



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2. An alternate means of determining fuel quantity may be obtained by the use of mechanicalmagnetic measuring sticks located on the bottom of themain wing and center fuel tanks. Measuringsticks are not provided for the fwd and aft auxiliary tanks (refer to Figure 28.01-13).

F. Minimum Fuel Requirement for Towing/Taxiing Operations1. To ensure a forward center of gravity to prevent the aircraft from becoming tail heavy, during all

towing and taxiing operations, one of the following must be used:a. A minimum of 5000 lbs. of fuel in the center tank. ORb. A minimum of 500 lbs. ballast in the forward cargo pit, FORWARD BULKHEAD.

(1) Authorized personnel must make Aircraft Maintenance Logbook (AML) entry for theaddition/removal of ballast to the forward cargo compartment.

2. This requirement does not apply to operational aircraft such as transit service, but does apply toovernight aircraft and aircraft on the ground for an extended period of time.

G. Warm Weather Fueling1. During prolonged flights, the MD-80 encounters significant (thermal contraction) temperature

changes to the fuel in the left and right wing tanks. This is caused by cold temperatures at highaltitudes and is known as "cold soaked" fuel. Upon arrival, the cold soaked fuel expands (thermalexpansion) by virtue of the warm ambient temperatures, and warm fuel being placed in the fueltanks.

2. This natural phenomena can cause fuel spills during and after fueling operations. Anothercontributing factor may be the design of the aircraft fuel system, since the center tank vents intothe same vent system as the wing tanks. When the wing tanks are at maximum capacity, thecenter tank may have difficulty in venting, contributing to the likelihood of a fuel spill. This is adistinct possibility during unusually warm days. In order to minimize the probability of fuel spills,the following procedures should be used during warm weather fueling operations:

3. PROCEDURESa. Fuel both wing tanks to 8,500 lbs. Cease fueling.b. Fuel center tank to required amount on fuel slip. Cease fueling.c. Return to wing tanks and slowly fill to required amount on fuel slip.d. Be vigilant during unusually warm weather fueling operations.

H. Special Fueling Procedure1. When fueling the MD-80 wing tanks to the maximum quantity of 9,266 lbs. and the tank fill valve

closes automatically prior to reaching the desired quantity, do not fill the tank manually. Placethe remaining amount of fuel in the center tank, providing the amount indicated on the fuel quantityindicator is not below 9,000 lbs. (See EXAMPLE 1.)

2. Should the tank fill valve close prior to reaching the maximum quantity of 9,266 lbs. and the fuelquantity indicator is below 9,000 lbs., manually fill the wing tanks to 9,000 lbs; then place theremaining amount of fuel in the center tank. (See EXAMPLE 2.)a. EXAMPLE 1. The tank fill valve closes at 9,000 lbs.- 266 lbs. short of the desired amount of

9,266 lbs. Place the remaining amount of 266 lbs. of fuel in the center tank.b. EXAMPLE 2. The tank fill valve closes at 8,800 lbs. - 466 lbs. short of the desired amount

of 9,266 lbs. Manually fuel to 9,000 lbs.; then place the remaining amount of fuel in the centertank.



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Figure 28.01-1: MD-82 Fueling Control Station



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Figure 28.01-2: MD-83 Fueling Control Station All Except A/C 9615-9654 (4XB-4YU)



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Figure 28.01-3: MD-83 Fueling Control Station Acft. 9615-9654 (4XB-4YU)



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Figure 28.01-4: MD-82 Fueling Control Station Components



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Figure 28.01-5: MD-83 Fueling Control Station Components All Except A/C 9615-9654(4XB-4YU)



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Figure 28.01-6: MD-83 Fueling Control Panel A/C 9615-9654 (4XB-4YU)

28.01.2 Underwing Pressure Fueling - Automatic Operation (With Electrical Power)

WARNING: IF ELECTRICAL POWER IS LOST AT GROUND FUELING STATION (BLUE LIGHTOUT), DISCONTINUE AUTOMATIC FUELING IMMEDIATELY, AND CONTINUE

1.

FUELING USING MANUAL MODE OF OPERATION, (REF. PARA. 28.01.5), ANDMAGNETIC MEASURING STICKS FOR MONITORING FUEL LOADS.

2. CENTER TANK AND LEFT MAIN TANK SHOULD BE TOPPEDOFF SEPARATELY,TO PREVENT INADVERTENT PRESSURIZATION OF VENT SYSTEM FROM 2TANKS AT ONCE.

A. Obtain the jet fuel service record (refer to Section 15.01).B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft. Aircraft bonding point is located on the main landing gear strut

(refer to Figure 28.01-7).D. Open fueling control panel access door.E. Ensure the fueling receptacle is clean.

1. Check locking mechanism of nozzle for evidence of wear or breakage.



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F. Connect fueling nozzle to aircraft pressure-refueling receptacle.CAUTION: PRIOR TO APPLYING FUEL PRESSURE; ROTATE NOZZLE HANDLES TO THE

LOCKED POSITION AND OPEN POPPET ACTUATING LEVER. ATTEMPT TOREMOVENOZZLE. IF NOZZLE CAN BE REMOVED IT IS DEFECTIVE ANDMUSTBE REMOVED FROM SERVICE.

G. Place refueling control panel POWER switch in ON position; verify that electrical power indicator bluelight, above the switch, comes on.NOTE : If external electrical power is not available to supply the aircraft load busses, aircraft battery

power will automatically be supplied to the ground fueling circuit when the fueling controlpanel POWER switch is placed in the ON position. Battery power should not be used ifexternal electrical power is available.



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Figure 28.01-7: Overview - Capacity and Bonding Lug Location

H. Do a functional check of the refueling control panel.1. The MD-83 (A/C 9615-9654 [4XB - 4YU]) refueling control panel will automatically do a built-in

test (BIT) when the power switch is turned to the ON position. At the completion of the test, thedisplay unit will display TEST PASSED, or, TEST FAILED. Dashes will be shown on the qualitydisplay to indicate a fuel quantity indication failure (refer to Figure 28.01-3).

2. To test the refueling control panel of the MD-82/83, (all except A/C 9615-9654 [4XB - 4YU]) dothe following:



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a. Place the FUNCTION switch in the SYSTEM TEST position to test the indicators. FUEL QTYdisplays will indicate 3000 (+/- 50) lbs. When the switch is placed in NORMAL position,indications will return to the original quantity. (refer to Figure 28.01-1 and Figure 28.01-2.)

b. Place FUNCTION switch in DIGIT TEST position. All displays should indicate 8’s. (SeeFigure 28.01-1 and Figure 28.01-2.)

I. Record FUEL QUANTITY in each tank in the "LBS. BEFORE FUELING" slots on the fuel slip.NOTE : Function switch must be placed in NORMAL position for this quantity reading. (refer to

Figure 28.01-1 and Figure 28.01-2.)

J. Determine fuel load per tank from fuel slip "LBS. AFTER FUELING" (refer to Figure 28.01-5).K. Position REFUEL knob to AUTO position. (refer to Figure 28.01-1, Figure 28.01-2, and Figure 28.01-3).L. Set the required amount of fuel by:

1. For MD-82/83, (all except A/C 9615-9654 [4XB - 4YU]) pull out SET knob and rotate until thedesired fuel load is indicated in each respective FUEL SELECT window. Push in each SET knobafter setting the quantity for each tank. (refer to Figure 28.01-4 and Figure 28.01-5).

2. For MD-83, (A/C 9615-9654 [4XB - 4YU]) push SELECT QTY buttons as necessary until thedesired total quantity is shown in the PRESELECT TOTAL window (refer to Figure 28.01-6).

M. Place respective fuel fill valve control switches to AUTO FILL position.NOTE : The fuel tanks can be fueled individually, as required, by placing the respective tank fuel

fill valve control switch in the AUTO FILL position.

N. Check position of fuel fill valve manual control levers; applicable fill valve manual control levers shouldbe in the open position. (refer to Figure 28.01-1, Figure 28.01-2, and Figure 28.01-3).NOTE : If one or more fuel fill valves are electrically inoperable (have not moved to the open position),

refer to paragraph Section 28.01.4.

O. Open fueling nozzle valve slowly; commence fueling by activating deadman control.1. Monitor applicable tank FUEL QTY indicators.

NOTE : 1. Quantity indicators will change in 50 lb. increments.2. Maximum allowable out-of-balance between fwd and aft auxiliary tanks for flight

is 400 lbs.

P. Verify that each tank fill valve closes when respective fuel quantity indicator equals preselected fuelload.NOTE : 1. The time required for the fill valves to close electrically is from 2 to 3 seconds.

2. Automatic shutoff of fuel valves may occur 75 to 100 lbs. short of "set in" quantity.

Q. When operation is complete stop fueling source by releasing deadman.R. Check that all fill valve control switches are in CLOSED position after fuel loading is accomplished.

1. If one or more fill valves fail to close, proceed as follows:a. Place respective tank fill valve control switch in CLOSED position.b. Place respective tank fill valve manual control lever to closed position.

S. For MD-82/83, (all except A/C 9615-9654 [4XB - 4YU]) pull out all set knobs and rotate until zero isindicated on FUEL QTY indicators. Push in SET knobs.

T. Close fueling nozzle valve: remove fueling nozzle.U. Place fueling control panel power switch to OFF position.V. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.W. Record the "gallons/liters added" from equipment meter on the fuel slip (refer to Section 15.01).



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X. Disconnect aircraft bonding and fueling vehicle bonding cable.

28.01.3 Underwing Pressure Fueling - Auto Override Operation (With Electrical Power)

NOTE : This procedure can be used for normal fueling and/or when the Automatic Fuel Shutoff Systemis inoperable.

CAUTION: THE AUTO OVERRIDE POSITION DEACTIVATES THE AUTOMATIC FUEL FILLSHUTOFF SYSTEM. ELECTRICAL PROTECTION IS STILL AVAILABLE TOPREVENT OVERFILL FUEL SPILLS.

1.

2. IF ELECTRICAL POWER IS LOST AT GROUND FUELING STATION (BLUE LIGHTOUT), DISCONTINUE AUTOMATIC FUELING IMMEDIATELY, AND CONTINUEFUELING USING MANUAL MODE OF OPERATION, (REF. SECTION 28.01.5),AND MAGNETIC MEASURING STICKS FOR MONITORING FUEL LOADS.

3. CENTER TANK AND LEFT MAIN TANK SHOULD BE TOPPEDOFF SEPARATELY,TO PREVENT INADVERTENT PRESSURIZATION OF VENT SYSTEM FROM 2TANKS AT ONCE.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control panel access door.E. Ensure the fueling receptacle is clean.

1. Check locking mechanism of nozzle for evidence of wear or breakage.F. Couple fueling nozzle to aircraft pressure refueling receptacle.

CAUTION: PRIOR TO APPLYING FUEL PRESSURE; ROTATE NOZZLE HANDLES TO THELOCKED POSITION AND OPEN POPPET ACTIVATING LEVER. ATTEMPT TOREMOVENOZZLE. IF NOZZLE CAN BE REMOVED IT IS DEFECTIVE ANDMUSTBE REMOVED FROM SERVICE.

G. Place refueling control panel POWER switch in ON position; verify that electrical power indicator bluelight, above the switch, comes on (refer to Figure 28.01-4 and Figure 28.01-5).NOTE : If external electrical power is not available to supply the aircraft load busses, aircraft battery

power will automatically be supplied to the ground fueling circuit when the fueling controlpanel POWER switch is placed in the ON position. Battery power should not be used ifexternal electrical power is available.


test (BIT) when the power switch is turned to the ON position. At the completion of the test, thedisplay unit will display TEST PASSED, or, TEST FAILED. Dashes will be shown on the quantitydisplay to indicate a fuel quantity indication failure (refer to Figure 28.01-3).

2. To test the refueling control panel of the MD-82/83, (all except A/C 9615-9654 [4XB - 4YU]) dothe following:a. Place the FUNCTION switch in the SYSTEM TEST position to test the indicators. FUEL QTY

displays will indicate 3000 (+/- 50) lbs. When the switch is placed in NORMAL position,indications will return to the original quantity (refer to Figure 28.01-1 and Figure 28.01-2).

b. Place FUNCTION switch in DIGIT TEST position. All displays should indicate 8’s (refer toFigure 28.01-1 and Figure 28.01-2).



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I. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING LBS" spaceson the fuel slip. Refer to Section 15.01.NOTE : FUNCTION switch must be placed in NORMAL position for this quantity reading.

J. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.

K. Position REFUEL knob to AUTO override position. (refer to Figure 28.01-1, Figure 28.01-2, andFigure 28.01-3).NOTE : All FUEL SELECT windows go blank.

L. Place applicable fuel fill valve control switch(es) to AUTO FILL position. The fill valves will drive to theOPEN position (down).NOTE : 1. If one or more fuel fill valves are electrically inoperable (have not moved to the open

position), refer to Section 28.01.4.2. The fuel tanks can be fueled individually, as required, by placing the respective tank

fuel fill valve control switch in the AUTO FILL position.

M. Open fueling nozzle valve slowly; commence fueling by activating deadman control.N. Monitor each tank’s FUEL QUANTITY" indicator for quantity desired from fuel service record "GATE

RELEASE QUANTITY REQUIRED - LBS."O. When each tank’s quantity is reached, position each respective TANK FILL VALVE switch to the

"CLOSED" position. The fill valves will drive to the CLOSED (up) position.1. If one or more fill valves fail to close, proceed as follows:

a. Place respective tank fill valve control switch in CLOSE position.b. Place respective tank fill valve manual control lever to closed position.

P. When operation is complete, stop fueling source by releasing deadman.Q. Close fueling nozzle valve: remove fueling nozzle.R. Place fueling control panel power switch to OFF position.S. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.T. Record the "gallons/liters added" from equipment meter on the fuel slip. Refer to Section 15.01.

NOTE : Ensure the completed fuel slip correctly filled out and legible.

U. Disconnect aircraft and fueling vehicle bonding cable.

28.01.4 Underwing Pressure Fueling - Auto Override Operation With Fuel Fill Valve ElectricallyOperative

NOTE : This procedure to be used when a fuel fill valve is electrically inoperative and the FUELQUANTITY indicators are operational.

WARNING: THE MASTER REFUEL SWITCH WILL BE IN "MANUAL FILL" IN THIS PROCEDURE.THIS REMOVES ELECTRICAL POWER FROM THE FUEL FILL VALVE MOTORS ANDTHE OVERFILL FLOAT SWITCHES. THERE IS NO ELECTRICAL PROTECTION TOPREVENT OVERFILL FUEL SPILLS.

CAUTION: IF ELECTRICAL POWER IS LOST AT GROUND FUELING STATION (BLUE LIGHTOUT), DISCONTINUEAUTOMATICFUELING IMMEDIATELY, ANDCONTINUEFUELINGUSING MANUAL MODE OF OPERATION, (REF. SECTION 28.01.5), AND MAGNETICMEASURING STICKS FOR MONITORING FUEL LOADS.



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CENTER TANK AND LEFT MAIN TANK SHOULD BE TOPPED OFF SEPARATELY,TO PREVENT INADVERTENT PRESSURIZATIONOF VENT SYSTEM FROM 2 TANKSAT ONCE.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control panel access door.E. Ensure the fueling receptacle is clean.

1. Check locking mechanism of nozzle for evidence of wear or breakage.F. Couple fueling nozzle to aircraft pressure-refueling receptacle.

CAUTION: PRIOR TO APPLYING FUEL PRESSURE; ROTATE NOZZLE HANDLES TO THELOCKED POSITION AND OPEN POPPET ACTIVATING LEVER. ATTEMPT TOREMOVENOZZLE. IF NOZZLECANBEREMOVED, IT IS DEFECTIVEANDMUSTBE REMOVED FROM SERVICE.

G. Place refueling control panel POWER switch in ON position; verify that electrical power indicator bluelight, above the switch, comes on (refer to Figure 28.01-3 and Figure 28.01-4).


test (BIT) when the power switch is turned to the ON position. At the completion of the test, thedisplay unit will display TEST PASSED, or, TEST FAILED. Dashes will be shown on the quantitydisplay to indicate a fuel quantity indication failure (refer to Figure 28.01-3).

2. To test the refueling control panel of the MD-82/83 (all except A/C 9615-9654 [4XB - 4YU]), dothe following:a. Place the FUNCTION switch in the SYSTEM TEST position to test the indicators. FUEL QTY

displays will indicate 3000 (+/- 50) lbs. When the switch is placed in NORMAL position,indications will return to the original quantity (refer to Figure 28.01-1 and Figure 28.01-2).

b. Place FUNCTION switch in DIGIT TEST position. All displays should indicate 8 "s (refer toFigure 28.01-1 and Figure 28.01-2).

I. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING LBS" spaceson the fuel slip. Refer to Section 15.01.NOTE : FUNCTION switch must be in NORMAL position.

J. Position REFUEL knob to AUTO OVERRIDE (refer to Figure 28.01-1, Figure 28.01-2, andFigure 28.01-3).

K. Position MASTER REFUEL switch to MANUAL FILL (refer to Figure 28.01-4, Figure 28.01-5, andFigure 28.01-6).NOTE : (1) ALL FUEL SELECT windows will be blank.

(2) MASTER REFUEL switch to "MANUAL FILL " will allow manual positioning of the fillvalves.

L. Manually position each FILL VALVE, down, to the OPEN position (refer to Figure 28.01-2 andFigure 28.01-3).

M. Open fueling nozzle valve slowly, commence fueling by activating deadman control.N. Monitor fuel tank quantity levels on the tank quantity indicators and manually position fill valves to

CLOSED when desired tank quantity is reached.



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CAUTION: WITH MASTER REFUEL SWITCH TO "MANUAL FILL " AND FILL VALVESMANUALLY OPENED, THERE IS NO ELECTRICAL PROTECTION TO PREVENTOVERFILL FUEL SPILLS.

O. When operation is complete, stop fuel source by releasing deadman.P. Position MASTER REFUEL switch to AUTO FILL, and place fueling control panel power switch to

OFF position.Q. Close fueling nozzle valve: remove fueling nozzle.R. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.S. Record the "gallons/liters added" from equipment meter on the fuel slip. Refer to Section 15.01.


T. Disconnect aircraft and fueling vehicle bonding cable.

28.01.5 Underwing Pressure Fueling - Manual Operation (Without Electrical Power)

WARNING: WITHOUT ELECTRICAL POWER, THERE IS NO ELECTRICAL PROTECTION TOPREVENT OVERFILL FUEL SPILLS.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Open fueling control panel access door.E. Ensure the fueling receptacle is clean.F. Connect fueling nozzle to aircraft pressure fueling receptacle.

CAUTION: PRIOR TO APPLYING FUEL PRESSURE; ROTATE NOZZLE HANDLES TO THELOCKED POSITION AND OPEN POPPET ACTIVATING LEVER. ATTEMPT TOREMOVENOZZLE. IF NOZZLECANBEREMOVED, IT IS DEFECTIVEANDMUSTBE REMOVED FROM SERVICE

THE CENTER TANK AND LEFT MAIN TANK SHOULD BE TOPPED OFFSEPARATELY TO PREVENT INADVERTENT PRESSURIZATION OF THE VENTSYSTEM FROM 2 TANKS AT ONCE.

G. The fuel tanks can be fueled individually, as required, by turning the respective tank fuel fill valvemanual control lever to the open position.

H. Prior to fueling, determine fuel load in each left and right main tank and center tank by using magneticmeasuring sticks (Refer to Section 28.01.8.NOTE : 1. Aircraft must be level (wings 0 degrees and nose 0 degrees) to obtain accurate fuel

tank quantities when using measuring sticks.2. Fwd and aft auxiliary tanks do not contain magnetic measuring sticks. Do not fuel these

tanks without electrical power on aircraft.

I. Record FUEL QUANTITY in each tank in the "GAUGE READING BEFORE FUELING LBS" spaceson the fuel slip. Refer to Section 15.01.

J. Determine fuel load per tank from fuel service record "GATE RELEASE QUANTITY REQUIRED -LBS." Refer to Section 15.01.

K. Manually position each applicable FILL VALVE lever down, to the OPEN position.L. Open fueling nozzle valve slowly; commence refueling by activating deadman control.M. Monitor fuel tank load levels with magnetic measuring sticks.



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WARNING: WITHOUT ELECTRICAL POWER, THERE IS NO ELECTRICAL PROTECTION TOPREVENT OVERFILL FUEL SPILLS.

NOTE : Maximum usable capacity loads at 6.7 Lb/Gal are:(1) 9266 lbs. (4212 kgs) each main tank.(2) 20596 lbs. (9362 kgs) for center tank.

N. Place respective tank fill valve manual control levers slowly to closed position when desired fuel loadin each tank is attained.

O. When operation is complete, stop fuel source by releasing deadman.P. Close fueling nozzle valve: remove fueling nozzle.Q. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.R. Record the "gallons/liters added" from equipment meter on the fuel slip. Refer to Section 15.01.


S. Disconnect aircraft and fueling vehicle bonding cable.

28.01.6 Overwing (Gravity) Fueling - Main Fuel Tanks

NOTE : Overwing fueling is considered an emergency fueling method, and shall be used only when thefollowing conditions exits:(1) No underwing (pressure) fueling vehicles available.(2) Aircraft underwing (pressure fuel system) components malfunctioning.(3) Other emergencies, as recognized by station management.

A. Obtain the jet fuel service record. Refer to Section 15.01.B. Position the fuel vehicle.C. Bond the fueling vehicle to the aircraft.D. Use ladder or suitable stand at wing leading edge to gain access to overwing fill receptacle (refer to

Figure 28.01-8).CAUTION: OBSERVE THE NO STEP AREAS ON WINGS.

E. Connect fueling nozzle grounding plug to aircraft ground receptacle and remove fill adapter cap.F. Insert fueling nozzle in fill receptacle. Slowly open fueling nozzle valve; commence fueling.G. When main tank maximum fuel load is desired, fuel each main tank until fuel level reaches overwing

fill receptacle screen retainer ring bead.NOTE : Maximum usable capacity loads at 6.7 Lb/Gal are 9266 lbs. (4212 kgs) for each main tank.

H. If main tanks are to be fueled to LESS THAN MAXIMUM capacity, use the following procedure:1. Open fueling control panel access door.2. Place fueling control panel POWER switch in ON position; verify that power indicator blue light

comes on (refer to Figure 28.01-1, Figure 28.01-2, and Figure 28.01-3).NOTE : If external electrical power is not available to supply the aircraft load busses, aircraft

battery power will automatically be supplied to the ground fueling circuit when thefueling control panel POWER switch is placed in the ON position. Conservative use ofaircraft battery power for fuel quantity indication is permissible.

3. For MD-82/83, (all except A/C 9615-9654 [4XB - 4YU]) place FUNCTION switch in SYSTEMTEST (indicator) position to test indicator; FUEL QTY displays will indicate 3000 (± " 50) lbs.When switch is placed in NORMAL position, indicators will return to original quantity.



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4. The MD-83 (A/C 9615-9654 [4XB - 4YU]) refueling control panel will automatically do a built-intest (BIT) when the power switch is turned to the ON position. At the completion of the test, thedisplay unit will display TEST PASSED, or, TEST FAILED. Dashes will be shown on the quantitydisplay to indicate a fuel quantity indication failure (refer to Figure 28.01-3).

5. Monitor main tank fuel quantity indicators (or magnetic measuring fuel sticks, if fuel quantityindicators are inoperative).

6. Continue fueling until desired fuel load in each main tank is attained.7. Place panel POWER switch in OFF position.8. Close access door.

I. Remove fueling nozzle.CAUTION: MAKE CERTAIN FILL ADAPTER CAP IS LOCKED.

J. Record "gallons/liters added" from the equipment meter on the fuel slip. Refer to Section 15.01.NOTE : Ensure the completed fuel slip is correctly filled out and legible.

K. Disconnect aircraft and fueling vehicle bonding cable.L. When fuel is required in the center, fwd and aft tanks, refer to Section 28.01.7.



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Figure 28.01-8: Overwing (Gravity) Fueling Adapter Location



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Figure 28.01-9: Overwing (Gravity) Fueling and Defuel Valve

28.01.7 Tank-To-Tank Ground Transfer Of Fuel

A. Ground transfer of fuel is accomplished by following the basic procedure used for defueling (refer toSection 28.01.12) and using the components used for pressure fueling. The fueling manifold ispressurized by fuel tank boost pumps and fuel fill valve(s) in the tank(s) selected to receive fuel isopened.NOTE : 1. The following operational procedures may be used when required, during the overwing

(gravity) fueling method. Tank-to-Tank fuel load adjustments may also be accomplishedby the following procedures:



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2. Maximum allowable out-of-balance between fwd and aft auxiliary tanks for flight is 400lbs of fuel.

3. If both transfer pumps in either auxiliary tanks are inoperative, do not fuel auxiliarytanks.

B. To transfer fuel from right main tank to left main, center, and/or auxiliary tanks. Refer to Figure 28.01-10.CAUTION: WHENAPU ISPOWERINGTHEAIRCRAFTANDFUEL ISBEINGTRANSFERRED

FROM RIGHT HAND FUEL TANK, PROVIDE AN ALTERNATE POWER SOURCETO AIRCRAFT TO PREVENT THE APU FROM SHUTTING DOWN DUE TO FUELSTARVATION.

1. Place refuel switch to AUTO OVERRIDE position.2. Place fuel fill valve switches for tank(s) to receive fuel in AUTO FILL position.3. Manually position defueling valve lever to OPEN. Refer to Figure 28.01-9.4. Place right main tank boost pump switches (cockpit) to ON.5. Monitor applicable fuel quantity indicators and place right main tank boost pump switches to OFF

when desired fuel quantity is obtained.6. Place fuel fill valve switches to CLOSED position.7. Top-off right main tank if required.

C. To transfer fuel from left main tank to right main; center and/or auxiliary tanks. Refer to Figure 28.01-10.1. Place refuel switch to AUTO OVERRIDE position.2. Place fuel fill valve switches for tank(s) to receive fuel in AUTO FILL position.3. Manually position defueling valve lever to OPEN.4. Place fuel crossfeed lever (cockpit) to ON.5. Place left main tank boost pump switches (cockpit) to ON.6. Monitor applicable fuel quantity indicators and place left main tank boost pump switches to OFF

when desired fuel quantity is obtained.7. Place fuel crossfeed lever to OFF.8. Place fuel fill valve switches to CLOSED position.9. Top-off left main tank if required.

D. To transfer fuel from center tank to left main, right main, and/or auxiliary tanks (refer to Figure 28.01-10):1. Place refuel switch to AUTO OVERRIDE position.2. Place fuel fill valve switches for tank(s) to receive fuel in AUTO FILL position.3. Manually position defueling valve lever to OPEN.4. Place center tank boost pump switches (cockpit) to ON.5. Monitor applicable fuel quantity indicators and place center tank boost pump switches to OFF

when desired fuel quantity is obtained.6. Place fuel fill valve switches to CLOSED position.7. Top-off center tank if required.

E. To transfer fuel from fwd and/or aft auxiliary tanks to center tank, left and right main tanks. Refer toFigure 28.01-10.NOTE : Auxiliary tank(s) fuel transfer is limited to the center tank only. Center tank must be below

approximately 13,000 lbs. for auxiliary tank(s) transfer pumps to operate.

1. Place refuel switch to AUTO OVERRIDE position.2. Place applicable fwd and/or aft auxiliary transfer pumps (cockpit) to AUTO position.



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3. Monitor applicable auxiliary tank(s) and center tank fuel quantity indicators. Place auxiliary tank(s)transfer pumps to OFF position when desired fuel quantity is obtained.

4. If left and right main tanks require fuel, transfer fuel from center tank as required. See above forcenter tank transfer procedures.

F. On completion of fuel transfer; check that all tank boost pumps, auxiliary tank transfer pumps, andfuel crossfeed lever are OFF in the cockpit.

G. Ensure that all fuel fill valve switches are CLOSED and power switch to OFF. Check that defuelingvalve is CLOSED; Closed all access doors.

Figure 28.01-10: Cockpit Fueling Controls

28.01.8 Inaccurate or Inoperative Main and Center Tank Quantity Indicators and/or Flight Deck FuelQuantity Display

NOTE : For applicable Method and Recording Requirements, refer to Section 15.01.

NOTE : Aircraft Maintenance will be utilized in determining if aircraft attitude is within "plus" (+) or "minus"(-) 0.50 degree of level.

NOTE : When there is an inoperative/inaccurate fuel quantity indicator and/or cockpit gauge(s), one ofthe following must be accomplished:



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1. Obtain a plumb bob and attach as per Figure 28.01-11. If aircraft is within ± " 0.50 degreesof level, then the stick verification charts in Section 28.02 can be used.

2. Some stations have the smart level device CPN LEV9002, which can be used as perFigure 28.01-12.

A. Method 1 For use when the flight deck fuel quantity display is operational and one or more of theunderwing panel fuel quantity displays are inoperative. Refer to Section 15.01.NOTE : Individual fuel tank quantity may be monitored and verified by the respective cockpit display

for the inoperative underwing panel indicator, provided respective cockpit display is verifiedoperational. Verification of fuel quantity, by measuring stick, is not required with Method 1.Use of Method 1 should be noted on the fuel slip, with a copy of the fuel slip provided tothe flight crew as early as practicable after fueling.

NOTE : All WARNINGS, CAUTIONS and NOTES under Section 28.01.1 General, must be observed.

1. Obtain the jet fuel service record. Refer to Section 15.01.2. Position the fuel vehicle.3. Bond the fueling vehicle to the aircraft.4. Open fueling control panel access door.5. Ensure the fueling receptacle is clean.6. Connect fueling nozzle to aircraft pressure fueling receptacle.

CAUTION: PRIOR TO APPLYING FUEL PRESSURE, ROTATE NOZZLE HANDLES TOTHELOCKEDPOSITIONANDOPENPOPPETACTUATINGLEVER. ATTEMPTTO REMOVE NOZZLE. IF NOZZLE CAN BE REMOVED, IT IS DEFECTIVEAND MUST BE REMOVED FROM SERVICE.

7. Place refueling control panel POWER switch in ON position; verify that electrical power indicatorblue light, above the switch, comes on.

8. Record FUELQUANTITY for each operational tank in the "GAUGEREADINGBEFOREFUELINGLBS" spaces on the fuel slip. Refer to Section 15.01.NOTE : Function switch must be placed in NORMAL position for this quantity reading (refer to

Figure 28.01-1 and Figure 28.01-2).

9. Position REFUEL knob to AUTO OVERRIDE position (refer to Figure 28.01-1, Figure 28.01-2,and Figure 28.01-3). FUEL SELECT and SET KNOBS must not be used when an indicator isinoperative.

10. Obtain pre-service reading from the cockpit, for the affected tank and record on fuel slip.11. From the wing panel, open fill valve switch for affected tank. An observer must be stationed in

the cockpit to observe the operative fuel quantity indicator during the fueling process. This willrequire a pre-determined means of signaling the wing panel operator when the desired quantityfor the affected tank has been reached. Caution must be exercised to prevent overfilling of theaffected tank.

12. Close fill valve switch for affected tank and, if necessary, finish fueling aircraft using operativewing panel indicators, and fill valve switches.

13. After fueling is complete, close all remaining fill valve switches.14. Close fueling nozzle valve; remove fueling nozzle.15. Place fueling control panel power switch to OFF position.16. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.



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17. Record the total "gallons/liters added" from equipment meter and complete the fuel slip. Refer toSection 15.01.NOTE : Make sure the completed fuel slip is correctly filled out and legible.

18. Disconnect fueling vehicle bonding cable from the aircraft.19. Provide flight crew with completed copy of fuel slip, ensuring all required entries and signatures

are legible and in place, as early as practicable before departure. Ensure use of Method 1 isnoted on the fuel slip.

B. Method 2 For use on main tanks (wings) and center tank when aircraft is within + 0.50 degree of level,the flight deck fuel quantity display is inoperative, one or more of the underwing panel fuel quantitydisplays are inoperative and fuel on board can be determined using fuel measuring sticks both beforeand after the refueling operation.NOTE : All Warnings, Cautions and Notes under Section 28.01.1, General, must be observed.

1. Obtain the jet fuel service record. Refer to Section 15.01.2. Position the fuel vehicle.3. Bond the fueling vehicle to the aircraft.4. Open fueling control panel access door.5. Ensure the refueling receptacle is clean.6. Connect fueling nozzle to aircraft pressure fueling receptacle.


7. Place refueling control panel POWER switch in ON position; verify that electrical power indicatorblue light, above the switch, comes on.




10. Determine if aircraft attitude is within + 0.50 degree of level (Refer to Section 28.01.8).11. Determine the pounds before fueling to be entered on the fuel slip, for the affected tank, by use

of fuel measuring stick. (Refer to 28.01.10 for operation of magnetic fuel sticks.)NOTE : Each main tank is equipped with four measuring sticks. If the fuel quantity is low, one

or more of the measuring sticks may not be readable. It is recommended thatdetermination of fuel level first be made from the outboard stick (number 1). If a readablelevel is not observed, operate the No. 2, No. 3, or No. 4 measuring sticks as required,until a readable fuel level is obtained. Measuring stick No. 5 will provide a readableindication of fuel level in the center wing tank in the normal range of airplane attitudes,except as limited at a near full or empty tank.

12. Read graduation on stick at point where stick graduation appears at bottom surface of tube.Convert reading obtained to pounds, using the fuel verification charts. (refer to Section 28.02),MD-80 Method 2 Fuel Quantity Verification Charts. Enter pre-service pounds obtained for theaffected tank in the appropriate area on the fuel slip.



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13. Subtract the pre-service pounds obtained by stick from the affected tank’s required pounds afterfueling and divide by the density shown on the fuel slip. This provides the number of gallons tobe metered into the affected tank.

14. Ensure all other fill valve switches are closed, with the exception of the affected tank being fueled.Fuel the tank to the desired level, using the truck meter. Close fill valve switch. Record actualgallons/liters metered into the affected tank on the fuel slip.

15. Open fill valve switches for remaining tanks and finish fueling aircraft to the amount indicated onthe fuel slip, using the operative fuel panel gauges. After completion, ensure all fill valves andswitches are in the closed position and POWER is off.

16. Record the total "gallons/liters added" from equipment meter on the fuel slip. Refer to Section15.01.NOTE : Ensure the fuel slip is correctly filled out and legible.

17. Use measuring sticks to verify the tank quantity. Refer to Figure 28.01-13 for location of sticks.Refer to Section 28.01.10 for operation of fuel sticks and refer to Section 28.01.11 for verificationprocedure and alternate procedure fuel slip entries.

18. Close fueling nozzle valve; remove fueling nozzle.19. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.20. Disconnect fueling vehicle bonding cable from aircraft.21. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity Indicator

Service Record, ensuring all required entries and signatures are legible and in place as early aspracticable before departure.

C. Method 3 For use on main tanks (wings) and center tank when aircraft is not level, when the flightdeck fuel quantity display is inoperative and one or two of the underwing panel fuel quantity displaysare inoperative.NOTE : AllWARNINGS, CAUTIONS andNOTES under Section 28.01.1, General, must be observed.

1. Obtain the jet fuel service record. Refer to Section 15.01.2. Position the fuel vehicle.3. Bond the fueling vehicle to the aircraft.4. Open fueling control panel access door.5. Completely defuel tank with the inoperative indicator by transferring fuel to other tanks or defueling.

Refer to Section 28.01.7 for transfer procedures.6. Enter 0 (zero) pounds of pre-service fuel on the fuel slip for the affected tank.

NOTE : If total fuel onboard is sufficient after defueling the affected tank, fueling of the affectedtank may be accomplished by transferring the required quantity of fuel from tank(s)with operative indicator(s). For fuel slip accuracy, pre-service readings for all tanksshould be entered after the initial transfer of fuel, from the tank with the inoperativeindicator, is complete.

7. Ensure the fueling receptacle is clean.8. Connect fueling nozzle to aircraft pressure fueling receptacle.


9. Place refueling control panel POWER switch in ON position; verify that electrical power indicatorblue light above the switch comes on. Refer to Section 15.01



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Function switch must be placed in NORMAL position for this quantity reading (refer toFigure 28.01-1 and Figure 28.01-2).

NOTE :


11. Note the affected tank’s required pounds after fueling and divide by the density shown on thefuel slip. This provides the number of gallons to be metered into the affected tank.

12. Ensure all other fill valve switches are closed, with the exception of the affected tank being fueled.Fuel the tank to the desired level, using the fueling equipment meter. Close fill valve switch.Record actual gallons metered into the affected tank on the fuel slip.

13. Open fill valve switches for the remaining tanks and finish fueling aircraft to the amount indicatedon the fuel slip, using the operative fuel panel gauges. After completion, ensure all fill valves andswitches are in the closed position and POWER is off.

14. Record the total "gallons/liters added" from fueling equipment meter on the fuel slip. Refer toSection 15.01.

15. Obtain the Pitch and Roll of the aircraft using a plumb bob or smart level. Aircraft Maintenancewill be utilized in determining if aircraft attitude. Refer to Figure 28.01-11.

16. Use measuring sticks to verify the tank quantity. Refer to Figure 28.01-13 for location of sticks.Reference Section 28.01.10 for operation of fuel sticks and reference Section 28.01.11 forverification procedure and alternate procedure fuel slip entries.

17. Convert the stick reading using the (MD-80 Method 3 Fuel Quantity Verification Charts) for otherthan level conditions. Refer to Fueling-Stick Charts MD-80 METHOD 3 Fuel Quantity Verificationchart.

18. Close fueling nozzle valve; remove fueling nozzle.19. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.20. Disconnect fueling vehicle bonding cable from aircraft.21. Provide flight crew with completed copy of fuel slip and an Inoperative Fuel Quantity Indicator

Service Record, ensuring all required entries and signatures are legible and in place as early aspracticable before departure.

28.01.9 Inaccurate Or Inoperative Fwd And/Or Aft Auxiliary Tank Quantity Indicators

NOTE : Fwd and aft auxiliary tanks do not contain magnetic measuring sticks.1.2. Maximum allowable out-of-balance between fwd and aft auxiliary tanks for flight is 400 lbs.

of fuel.3. If both transfer pumps in either auxiliary tanks are inoperative, do not fuel auxiliary tanks.

A. Method 1 For use when the flight deck fuel quantity display is operational and the FWD and/or AFTauxiliary underwing panel fuel quantity displays are inoperative.NOTE : Individual fuel tank quantity may be monitored and verified by the respective cockpit display

for the inoperative underwing panel indicator, provided respective cockpit display is verifiedoperational. Use of Method 1 should be noted on the fuel slip, with a copy of the fuel slipprovided to the flight crew as early as practicable after fueling.

NOTE : AllWARNINGS, CAUTIONSandNOTES under Section 28.01.1 , General, must be observed.

1. Obtain the jet fuel service record. Refer to Section 15.01.2. Position the fuel vehicle.3. Bond the fueling vehicle to the aircraft.



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4. Open fueling control panel access door.5. Ensure the fueling receptacle is clean.6. Connect fueling nozzle to aircraft pressure fueling receptacle.


7. Place refueling control panel POWER switch in ON position; verify that electrical power indicatorblue light above the switch comes on.




10. Obtain pre-service reading from the cockpit, for the affected tank, and record on fuel slip.11. From the wing panel, open fill valve switch for affected tank. An observer must be stationed in

the cockpit to observe the operative fuel quantity indicator during the fueling process. This willrequire a pre-determined means of signaling the wing panel operator when the desired quantityfor the affected tank has been reached. Caution must be exercised to prevent overfilling of theaffected tank.

12. Close fill valve switch for affected tank and, if necessary, finish fueling aircraft using operativewing panel indicators and fill valve switches.

13. After fueling is complete, close all remaining fill valve switches.14. Close fueling nozzle valve; remove fueling nozzle.15. Place fueling control panel power switch to OFF position.16. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.17. Record the "gallons/liters added" from equipment meter and complete the fuel slip. Refer to

Section 15.01.18. Disconnect fueling vehicle bonding cable from the aircraft.19. Provide flight crew with completed copy of fuel slip, ensuring all required entries and signatures

are legible and in place, as early as practicable before departure. Ensure use of Method 1 isnoted on the fuel slip.

B. Method 2 Not applicable on FWD and/or AFT auxiliary tanks.C. Method 3 For use when the flight deck fuel quantity display is inoperative and the FWD and/or AFT

auxiliary underwing panel fuel quantity displays are inoperative.NOTE : Completely defuel tank with the inoperative indicator by transferring fuel to the center tank.

NOTE : Auxiliary tank(s) fuel transfer is limited to the center tank only. Center tank must be belowapproximately 13,000 lbs. for auxiliary tank(s) transfer pumps to operate.

NOTE : All WARNINGS, CAUTIONS and NOTEs under Section 28.01.1 General, must be observed.

1. Obtain the jet fuel service record. Refer to Section 15.01.2. Position the fuel vehicle.3. Bond the fueling vehicle to the aircraft.



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4. Open fueling control panel access door.5. Completely defuel tank with the inoperative indicator by transferring fuel to center tank. Refer to

Section 28.01.7 for transfer procedures.6. Enter 0 (zero) pounds of pre-service fuel on the fuel slip, for the affected tank.

NOTE : If total fuel onboard is sufficient after defueling the affected tank, fueling of the affectedtank may be accomplished by transferring the required quantity of fuel using theoperative center tank gauge. For fuel slip accuracy, pre-service readings should beentered after the initial transfer of fuel from the tank with the inoperative indicator iscomplete.

7. Ensure the fueling receptacle is clean.8. Connect fueling nozzle to aircraft pressure fueling receptacle.


9. Place refueling control panel POWER switch in ON position; verify that electrical power indicatorblue light above the switch comes on.



11. Position REFUEL knob to AUTO OVERRIDE position (Refer to Figure 28.01-1, Figure 28.01-2,and Figure 28.01-3). FUEL SELECT and SET KNOBS must not be used when an indicator isinoperative.

12. Note the affected tank’s required pounds after fueling and divide by the density shown on thefuel slip. This provides the number of gallons to be metered into the affected tank.

13. Ensure all other fill valve switches are closed, with the exception of the affected tank being fueled.Fuel the tank to the desired level using the truck meter. Close fill valve switch. Record actualgallons metered into affected tank on the fuel slip.

14. Open fill valve switches for remaining tanks and finish fueling aircraft to the amount indicated onthe fuel slip, using the operative fuel panel gauges. After completion, ensure all fill valves andswitches are in the closed position and POWER is off.

15. Record the total "gallons/liters added" from equipment meter on the fuel slip. Refer to Section15.01.NOTE : Ensure the fuel slip is correctly filled out and legible.

16. Close fueling nozzle valve; remove fueling nozzle.17. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.18. Disconnect fueling vehicle bonding cable from aircraft.19. Provide flight crew with completed copy of fuel slip, ensuring all required entries and signatures

are legible and in place, as early as practicable before departure. Ensure use of Method 3, isnoted on the fuel slip by entering “Method 3 utilized for inoperative Aux Tank Indication” in theREMARKS area.



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Figure 28.01-11: Leveling Inclinometer Location - Grid



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Figure 28.01-12: Leveling Inclinometer Location - Smart Level

28.01.10 Operation Of Fuel Quantity Measuring Sticks

A. In general, the sticks are less accurate than the fuel quantity probe system. They should be used onlyas an alternate means of measuring fuel quantity, or to verify actual presence of fuel in the tank, andnot as a routine check on fuel quantity indicator readings.

B. In the event an abnormal refueling situation occurs (for example, inoperative fuel quantity display), aVendor Supervisor, Lead or Supervisor/Lead, or Designated Trainer performing the duties of aircraftrefueling must be present to oversee and coordinate the operation.

C. Each of the eight sticks in the main tanks is contained in a flanged housing mounted inside the tankon the lower wing skin. The center wing tank stick is mounted inside an access door. The door islocated forward of the left-hand main wheel-well, approximately 10 inches to the left of the aircraftcenterline.

D. The fuel level sticks are the magnetic dripless-type, consisting of a mounting, a tube housing, an innertube (indicator stick) graduated for determining fuel tank quantity, and a circular float. The float isinstalled on the tube housing and is free to move up and down with the fuel level in the tank. Refer toFigure 28.01-13. When the fuel level stick tip is magnetically coupled to the circular float, the stick ispositioned relative to the fuel level in the tank. A force of 5 ounces (minimum) is required to break themagnetic coupling between the stick and float.

E. Fuel quantities quoted in the fuel quantity charts are based on fuel with a density of 6.7 pounds perU.S. gallon. Use the Verification Chart to convert stick graduations to pounds.NOTE : When actual fuel density deviates greatly from the nominal chart value of 6.70 pounds per

gallon, it may be desirable to convert the chart derived pound value to "actual pound" valuebased on local station density (refer to Section 10.01.3).



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F. The stick is unlocked (released) or locked (stowed) by depressing the stick latch and turning the latch90 degrees in either direction. A flat-bit screwdriver can be used to depress and turn the latch. Theoperating procedures for all sticks are identical.NOTE : a) Fwd and aft auxiliary tanks do not contain magnetic measuring sticks.

b) Fuel level sticks one through four are identified by relative position outboard to inboardon each wing. Refer to Figure 28.01-13.

G. For stick No. 5 WING UP and WING DOWN refers to left wing only. For other sticks, WING UP andWING DOWN refers to the wing where the stick is located. Fuel loads above 19737 pounds areunstickable. Make final stick check at 33.0 and meter in the remaining quantity, using the refuelingtruck meters. (For A/C 9615-9654 [4TA-4YU], the max. verifiable load by stick is 20390 pounds.)

28.01.11 Determining Fuel Quantity By Measuring Stick

A. Any time fuel quantity is determined by measuring stick, this procedure is used.1. MD80 Series Aircraft EXCEPT 4TA Through 4YU

NOTE : When verifying fuel on board prior to fueling, round stick reading down (referenceexample below.)

Example: Stick indicates reading between 9" and 9.250". A 9" reading for the No. 3stick, using the stick verification chart, will be 7290 lbs.

a. The stick reading in inches and conversion to pounds must be verified by a cockpit crewmember by reviewing the completed fuel slip and Inoperative Fuel Quantity Indicator servicerecord.

b. Monitoring the stick verification shall include reading the selected stick and checking thefollowing items:(1) Stick reading in inches.(2) Correct conversion of stick reading from inches to pounds of fuel.

c. When the stick reading is taken, enter the applicable aircraft attitude, tank, stick number,reading and conversion to pounds on the Inoperative Fuel Quantity Indicator service record.Refer to Section 15.01.

2. MD80 Series Aircraft 4TA Through 4YUNOTE : When verifying fuel on board prior to fueling, round stick reading down.

Example: Stick indicates reading between 3800 lbs. and 3850 lbs. A 3800 lb readingfor the No. 3 stick, using the stick verification chart, will be 3838 lbs.

a. The stick reading in pounds and conversion to actual pounds must be verified by a cockpitcrew member by reviewing the completed fuel slip and Inoperative Fuel Quantity Indicatorservice record.

b. Monitoring the stick verification shall include reading the selected stick and checking thefollowing items:(1) Stick reading in pounds.(2) Correct conversion of stick reading to actual pounds of fuel.

c. When the stick reading is taken, enter the applicable aircraft attitude, tank, stick number,reading and conversion to pounds on the Inoperative Fuel Quantity Indicator service record.Refer to Section 15.01.



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28.01.12 Defueling

NOTE : Product defueled from an aircraft for purposes other than contamination should be returned tothe airline fromwhich it was removed. Defueled product may not be delivered to another company"s aircraft without its approval. Defueling aircraft directly into joint use fueling systems is notauthorized unless a procedure has been unanimously approved by all system users.

A. The defueling system consists of the individual fuel tank fill lines and an extension of the right enginefuel feed line which is connected to the pressure fueling receptacle at the fueling station. A manuallyoperated defueling valve and a defueling check valve are installed in the line inboard of the refuelingstation.1. Defueling can be accomplished by the suction method, boost pump pressure method, or by a

combination of both.2. Defueling by the suction method is used primarily to remove minimum quantities of fuel from the

tanks when adjusting fuel loads. This method is accomplished by using the fuel truck suction



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pump to withdraw fuel from the tanks through the tank fill lines and valves. Only partial defuelingcan be accomplished by this method.

3. The boost pump pressure method of defueling can be used for partial or maximum defueling ofthe center and/or main fuel tanks. Boost pump pressure defueling is the faster method, and isaccomplished by using the respective tank fuel boost pumps to pump fuel through the defuelingline as shown in Figure 28.01-14. Defueling unit suction can be used in conjunction with the boostpump pressure method to increase the fuel flow rate. Any residual fuel remaining in the tanksafter maximum defueling can be drained through the individual tank sump drain valves.NOTE : Fwd and aft auxiliary tanks can be pressure defueled into the center tank only. Center

tank must be below approximately 13,000 lbs. of fuel for auxiliary tank(s) transfer pumpsto operate.

4. The fueling station controls regulate defueling.5. Defueling should be done with the airplane in the normal attitude (Ref. MD-80 MM 12-11-01-3-1).6. Tank-to-tank transfer of fuel can be accomplished as outlined in Section 28.01.7.

B. SUCTION METHOD (Partial Defueling)1. Position the defueling vehicle.2. Bond the defueling vehicle to the aircraft.3. Open fueling control panel access door (refer to Figure 28.01-1, Figure 28.01-2, and

Figure 28.01-3).4. Ensure the fueling receptacle is clean.5. Couple fueling nozzle to aircraft pressure-refueling receptacle. Open fueling nozzle valve.

NOTE : Open tanker dome cover and place a monitor by the dome cover access to ensuretanker DOES NOT overfill.

6. Place fueling control panel POWER switch in ON position; verify that power indicator blue lightcomes on.NOTE : (1) If external electrical power is not available to supply the aircraft load busses, aircraft

battery power will automatically be supplied to the ground fueling circuit when thefueling control panel POWER switch is placed in the ON position. Battery powershould not be used if external electrical power is available.

(2) If nose gear strut is near the fully extended position, the oleo switch will be actuatedand electrical power to the fuel control station will be off.

7. Do a functional check of the refueling control panel.(1) The MD-83 (A/C 9615-9654 [4XB - 4YU]) refueling control panel will automatically do a

built-in test (BIT) when the power switch is turned to the ON position. At the completion ofthe test, the display unit will display TEST PASSED, or, TEST FAILED. Dashes will be shownon the quantity display to indicate a fuel quantity indication failure (refer to Figure 28.01-3).

(2) To test the refueling control panel of the MD-82/83, (all except A/C 9615-9654 [4XB - 4YU])do the following:(1) Place the FUNCTION switch in the SYSTEM TEST position to test the indicators. FUEL

QTY displays will indicate 3000 (+/- 50) lbs. When the switch is placed in NORMALposition, indications will return to the original quantity (refer to Figure 28.01-1 andFigure 28.01-2).

(2) Place FUNCTION switch in DIGIT TEST position. All displays should indicate 8’s (referto Figure 28.01-1 and Figure 28.01-2).

8. Determine fuel load.



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9. Place FUEL switch in AUTO OVERRIDE position.NOTE : All FUEL SELECT windows go blank.

10. For tank(s) to be defueled, place respective fuel fill valve control switch(es) to AUTO FILL position.The fill valves will drive to the OPEN position (down). (refer to Figure 28.01-1, Figure 28.01-2,and Figure 28.01-3).NOTE : If a fuel tank is at maximum capacity, its respective fuel fill valve may not open. Refer

to Section 28.01.4 of fueling instructions for manual operation.

11. Start defueling truck suction pump by activating deadman control.12. Monitor applicable tank FUEL quantity indicators in flight compartment, fuel control panel, or

magnetic measuring sticks. Indicators will change in 50 lb. increments.13. When each tanks desired quantity is reached, place each respective tank fill valve switch to

CLOSED position. The fill valves will drive to the CLOSED position (lever up). (refer toFigure 28.01-1, Figure 28.01-2, and Figure 28.01-3).

14. Stop defueling truck suction pump immediately by releasing deadman control.15. Close and latch the tanker unit dome cover.16. Close defueling nozzle valve; remove nozzle.17. Place fueling control power switch to OFF position.18. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.19. Disconnect aircraft and fueling vehicle bonding cable.

C. PRESSURE DEFUELING (Partial or Complete Defueling)CAUTION: IF INTERIOR FURNISHINGS ARE REMOVED, AND AIRCRAFT IS TO BE

COMPLETELYDEFUELED,MAINTAINSUFFICIENTWEIGHT IN FORWARDAREAOF FUSELAGE TO AVOID TAIL HEAVY OVERBALANCE CONDITION.

NOTE : When completely defueling, it is recommended to defuel the fwd auxiliary tank last, to helpavoid a possible tail heavy condition.

1. Position the defueling vehicle.2. Bond the defueling vehicle to the aircraft.3. Open fueling control station access door, and defueling shutoff valve access door. Refer to

Figure 28.01-9.4. Ensure the fueling receptacle is clean.5. Connect hose nozzle to aircraft pressure fueling receptacle. Open nozzle valve.

NOTE : Open the dome access cover and place a monitor by the dome cover access to ensuretanker DOES NOT overfill.

6. Place fueling control panel POWER switch in ON position; verify that power indicator blue lightcomes on.NOTE : If external electrical power is not available, aircraft battery power will automatically be

supplied, when the refueling control panel POWER switch is placed in the ON position.Battery power should not be used if external electrical power is available.

7. Do a functional check of the refueling control panel.a. The MD-83 (A/C 9615-9654 [4XB - 4YU]) refueling control panel will automatically do a

built-in test (BIT) when the power switch is turned to the ON position. At the completion ofthe test, the display unit will display TEST PASSED, or, TEST FAILED. Dashes will be shownon the quantity display to indicate a fuel quantity indication failure. Refer toFigure 28.01-9.



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b. To test the refueling control panel of the MD-82/83, (all except A/C 9615-9654 [4XB - 4YU])do the following:(1) Place the FUNCTION switch in the SYSTEM TEST position to test the indicators. FUEL

QTY displays will indicate 3000 (+/- 50) lbs. When the switch is placed in NORMALposition, indications will return to the original quantity (refer to Figure 28.01-1 andFigure 28.01-2).

(2) Place FUNCTION switch in DIGIT TEST position. All displays should indicate 8 "s (referto Figure 28.01-1 and Figure 28.01-2).

8. Determine fuel load.9. Place defueling shutoff valve control lever in OPEN position.10. If left main tank is to be defueled, place the fuel crossfeed control valve lever (cockpit) to ON

position. Refer to Figure 28.01-10.11. Place applicable left main, right main, and/or center tank boost pump switches (cockpit) to ON

position. Place applicable fwd and/or aft auxiliary tank transfer pumps to AUTO position. Referto Figure 28.01-10.NOTE : (1) If both center tank boost pumps are turned on, the center tank will empty first,

since they override the main tank boost pumps.(2) The fuel boost pump switches are located in the flight compartment on the forward

overhead switch panel.(3) The fuel tanks can be defueled individually or simultaneously as required.(4) Fwd and aft auxiliary tanks can be defueled into the center tank only. Center tank

must be below approximately 13,000 lbs. of fuel for auxiliary tanks transfer pumpsto operate.

12. To expedite the defueling process, place the fuel truck in the defuel mode.13. Monitor applicable fuel quantity indicators and continue defueling until desired fuel quantity

remains.14. Release deadman just prior to reaching desired fuel tank(s) quantity.15. Place applicable boost pump switches and auxiliary tank(s) transfer pump switches to OFF

position, when desired defueling of each tank is accomplished.16. If left main tank defueling was required, place crossfeed valve control lever in OFF position.17. Place defueling shutoff valve control lever to CLOSED position; close access door.

NOTE : Close and latch the tanker unit dome cover.

18. Close fueling nozzle valve; remove nozzle.19. Place fueling control power switch to OFF position.20. Ensure the fueling receptacle is not leaking after fueling is complete and close access door.21. If complete defueling is desired, drain applicable fuel tank sumps.22. Disconnect aircraft and fueling vehicle bonding cable.



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Figure 28.01-14: Defueling - Boost Pump Method - Schematic

END



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Section 28.02 - MD-80 Fuel Quantity Verification ChartA. Refer to MD-80 Fuel Quantity Verification Charts as follows:


END

Section 28.02MD-80 Fuel Quantity Verification Chart


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Table of contents

29.01 TERMS AND DEFINITIONSABBREVIATIONS AND ACRONYMS................................................................................1DEFINITIONS....................................................................................................................3

TOCTerms and Definitions


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Section 29.01 - Terms and Definitions29.01.1 Abbreviations and Acronyms

DefinitionTerm

Airlines for America(A4A)

Advisory CircularsAC

Airports Council InternationalACI

Aviation Fuel Quality Requirements for Jointly Operated SystemsAFQRJOS

Aeronautical Information PublicationAIP

American Petroleum InstituteAPI

Aerospace Recommended PracticeARP

Aerospace StandardAS

Aerospace Standard for Storage, Handling and Distribution of Jet Fuels at AirportsAS6401

American Society for Testing and Materials (now called ASTM International)ASTM

Air Transport Association of America, Inc. (now called Airlines for America (A4A))ATA

Coordinated Agency for Suppliers Evaluation, Inc.C.A.S.E.

European Committee for StandardizationCEN

Canadian General Standards BoardCGSB

Certificate of AnalysisCOA

Coordinating Research CouncilCRC

Canadian Standards AssociationCSA

Energy InstituteEI

Environmental Protection AgencyEPA

Energy InstituteEI

External Quality Assurance SchemeEQA

Executive Steering GroupESG

Federal Aviation AdministrationFAA

Fuel Quality Pool SoftwareFQPS

Aviation Fuel Operations CommitteeG16

Russian National StandardGOST

Ground Support ProviderGSP

Inspection AuthorizationIA

International Air Transport AssociationIATA

International Civil Aviation OrganizationICAO

Section 29.01Terms and Definitions


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DefinitionTerm

IATA (International Air Transportation) Fuel Quality PoolIFQP

International Organization for StandardizationISO

Joint Inspection GroupJIG

Multilateral AgreementMLS

Ministry of DefenseMOD

Material Safety Data SheetMSDS

National Bureau of StandardsNBS

National Fire Prevention AssociationNFPA

National Institute of Standards and TechnologyNIST

Original Equipment ManufacturerOEM

On the Job TrainingOJT

Policies, Standards and ProceduresPSPs

Periodic Test CertificatePTC

Quality AssuranceQA

Quality Assurance GroupQAG

Quality ControlQC

Quality ManualQM

Quality Management SystemQMS

Release CertificateRC

Recommended PracticeRP

Refinery Certificate of QualityRQC

Recertification Test CertificateRTC

Safety AssuranceSA

Safety Action GroupSAG

SAE InternationalSAE

Standards and Recommended Practices (ICAO)SARPs

Safety Data Collection and Processing SystemsSDCPS

Steering GroupSG

Safety Management ManualSMM

Safety Management SystemSMS

Safety Management Systems ManualSMSM

Standard Operating ProceduresSOPs



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DefinitionTerm

Safety Review BoardSRB

Safety Risk ManagementSRM

State Safety ProgramSSP

IATA Technical Fuel GroupTFG

United Kingdom Aviation Fuels CommitteeUK AFC

United Kingdom Ministry of DefenceUK MOD

29.01.2 Definitions

DefinitionTerm

A separation method where one component is concentrated on the surfaceof a porous solid. Surfactants (surface-active-agents) are separated from jetfuel by absorption on clay

Absorption

American Petroleum InstituteAPI

Units for fuel density measurementAPI Degrees

The petroleum industry's scale and method for measuring density of liquidpetroleum products

API Gravity

The air temperature surrounding a specific areaAmbient Temperature

American Society for Testing and MaterialsASTM

A filtration vessel equipped with bulk clay, clay bags, or clay canisters usedfor removing surfactants (surface-active-agents) from jet fuel

Clay Treatment Vessel

The property of a coalescer element to bring together very fine droplets offree and entrained water to form large droplets which are heavy enough tofall to the bottom (sump) of a filter/separator vessel

Coalescense

The first stage cartridge in a filter/separator vessel that removes solid particlesand coalesces free water from jet fuel. It is upstream of the separator cartridge

Coalescer Element

Substances either foreign or native which may be present ion a jet fuel thatdetracts from its performance

Contaminants

A device that uses the principal of centrifugal force to cause the contaminantin jet fuel to settle to the bottom of a vessel without the use of filtration media

Cyclone Separator

A control device which must be physically held open by the system operatorto allow fuel to flow. When released, fuel flow stops automatically.

Deadman Control

The amount of mass (weight) in a volume of materialDensiry

The measured difference in pressure between any two points, generallybetween inlet and outlet connections on filtration vessels

Differential Pressure (DeltaP)

A pressure gauge which automatically displays the differential pressurebetween the inlet and outlet connections of filtration vessels

Direct Reading DifferentialPressure Gauge



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DefinitionTerm

The rendering of elements in filtration systems incapable of performing theirdesigned functions, for example, coalescers incapable of coalescing waterand separator elements incapable of separating water from fuel

Disarming Action

Water which is in solution in jet fuel. This water is not free water and cannotbe removed by conventional means.

Dissolved Water

Stream of fluid at the outlet of filtration vesselsEffluent

A generic term given to different types of decontamination media installedin various types of filtration vessels

Elements

A dispersion of two dissimilar immiscible droplets in a continuous liquid phaseEmulsion

Small droplets of free water in suspension which may make jet fuel appearhazy or cloudy

Entrained Water

A decontamination device to remove solid particles from fuelFilter

A standard test in which jet fuel is passed through a small filter membranehoused in a plastic holder. The cleanliness of the fuel can be determined bymeasuring the residue or amount of solid contaminants left on themembrane.

Filter membrane (Millipore)Test

A filtration vessel which removes solids and coalesces free water from jetfuel. All filter/separators are equipped with two types of cartridges: coalescerelements (first stage) and separator elements (second stage).

Filter/Separator

Common title for aircraft tueling agents or vendors at airportsFixed Base Operator (FBO)

The lowest fuel temperature at which the vapor above the fuel will igniteFlash Point

Pump suction piping with flotation capability used to draw the cleanest productfrom the upper level of the fuel in a jet fuel storage tank

Floating suction

An area with associated restrictions that are established on the ramp aroundthe aircraft fueling receptacles, tank vents, and around the fueling equipmentduring aircraft fueling operations

Fueling Safety Zone

Water in fuel other than dissolved water. Free water may be in the form ofdroplets or haze suspended in fuel (entrained water or an emulsion) and/orwater layered at the bottom of the container holding the fuel

Free Water

The coldest fuel temperature at which the last fuel wax crystals disappearwhen fuel physically changes from a solid back to a liquid when warmed

Freeze Point

A service provider acting as the handling agent for one or more airlines,providing one or more of the ground services as defined in Multilateral IFQPPool Agreement

Groud Services Provider(GSP)

Any piece of mobile equipment, whether or not powered or self-propelled,that is purpose-designed, built and used for ground handling, servicing orfield maintenance of civil transport aircraft on the ramp and aircraft movementarea of an airport

Ground Support Equipment(GSE)

Attracts water or is water wetting. Has an affinity for water. Opposite ofhydrophobic.

Hydrophilic



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DefinitionTerm

Repels water or is non-water wetting. Resists attracting water. Opposite ofhydrophilic.

Hydrophobic

Liquids which are mutually insoluble. Opposite of miscible.Immiscible

Strem of fluid at the inlet of filtration vesselsInfluent

Where two or more users share and receive fuel from a common pipelinesystem

Joint Use Fueling Systems

A filtration vessel equipped with pleated paper cartridges designed to removesolid particles from aviation fuels

Micronic Filter

A unit of linear measurement. One micron is equal to 0.000039 inches andapproximately 25,400 microns equals one inch.

Micron (Micrometer)

Liquids which are mutually soluble. Opposite of immiscible.Miscible

Solid contaminants found in jet fuel, for example dirt, rust, sand fibers, etc.Particulates

A device used to check the operation of the automatic high level shut-offequipment on tank trucks for preventing fuel spills

Pre-check Valve

A high dirt holding capacity Micronic Filter with pleated paper cartridgesinstalled upstream of other filtration units. Prefilters are designed to extendthe useful life of other more expensive filtration media in a fuel distributionsystem exposed to high solid levels.

Prefilter

See Differential PressurePressure Drop

Unless indicated otherwise, it will mean jet fuel.Product

See Relative DensitySpecific Gravity

A chamber or depression installed at the bottom of a fuel storage tank orfiltration vessel to facilitate the collection and removal of contaminants

Sump

Fuel removed from storage tanks, filtration vessels, and aircraft refuelerswhile performing routine quality control tests and equipment maintenance

Sump Fuel

An acronym for surface-active-agents that are chemical substances ordetergent-like compounds frequently found in jet fuels. These chemicalsdisarm the water-removing capability of coalescer cartridges infilter/separators. Clay treatment is the primary means in removing surfactantsfrom jet fuel.

Surfactants

Small tanks that collect fuel from high pressure relief valves on hydrant trucksSurge Tanks

A hydrometer with a built-in thermometer used in determining fuel densityand measuring fuel temperature simultaneously.

Thermohydrometer

A small pump having suction line which extends to the low point of a fuelstorage tank for the purpose of drawing off water which may haveaccumulated

Thief (Sump) Pump

An amount large enough to be detected but not to be measuredTrace



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DefinitionTerm

Various kerosene and naptha-based fuels manufactured to be used in jetengines

Turbine Fuel

See Fixed Base Operator (FBO)Vendor

Fuel that is contaminated resulting from exposure to biological activity,surfactants, oil/water separators, chemicals, petroleum product mixes, surfacedrains, and from other various water/solid combinations

Waste Fuel

A device which senses the predetermined level of free water in filter-separatorsumps and automatically stops the flow of fuel to prevent downstreamcontamination

Water Defense System

A large amount of free waterWater Slug

The fuel storage tank being used to supply fuel to aircraft refueler tankertrucks or to hydrant systems

Working Tank

END



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