Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-28A2330

Original Issue: April 02, 2012

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Engine Fuel Suction Feed Operational Test

Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15

CFR 300-774). An export license may be required before it is used for development, production or use by foreign

persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2012 Boeing.

Unpublished Work. All Rights Reserved.

Treatment of this document and its content is governed by contract with Boeing. Rights to use this document

are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and Boeing

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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 18

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 19

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

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BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Summary Number: 747-28A2330

Original Issue: April 02, 2012

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Engine Fuel Suction Feed Operational Test

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin provides instructions to operators to perform an Engine Fuel Suction Feed Operational Test

on each engine individually. This test is required in order to protect against engine flameout during suction feed

operations. The instructions given in this service bulletin are provided to detect and correct failure of the engines

fuel suction feed of the fuel system, which could result in dual engine flameout and inability to restart the engines,

and consequent forced landing of the airplane.

Accomplishing the fuel system suction feed test and continuing to repeat the testing within the specified compliance

times will reduce the possibility of an engine flameout resulting from air ingestion into the engine fuel feed system

during low fuel level conditions with inoperative boost pumps .

An operator reported a 737-400 Engine No. 1 flameout during cruise. The Engine No. 2 continued to operate

normally. The flight crew conducted two restart attempts within the start envelope with no success then diverted

uneventfully. Another operator reported a 737-300 Engine No. 2 shut down when the start lever was placed in

the idle position during taxi to the gate. The Engine number 1 continued to operate normally. Maintenance

performed a vacuum test of the engine fuel feed system and found a crack in a fuel feed tube. The fuel feed

tube was replaced and the vacuum test of the fuel feed system was performed and passed successfully.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

AD Related Yes Paragraph 1.E., Compliance

ACTION

The WORK PACKAGES can be done in any order.

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Each engine must successfully complete the Fuel Suction Feed - Operational Test.

WORK PACKAGE 1 - ENGINE NO. 1 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 1 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test

Before Further Flight.

WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 2 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test

Before Further Flight.

WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 3 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test

Before Further Flight.

WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 4 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test

Before Further Flight.

EFFECTIVITY

747-400, 747-400D, 747-400F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2007-NM-357-AD, is related to

this service bulletin.

Boeing recommends that the Engine Suction Fuel Feed Operational Test given in this service bulletin be done

30,000 Flight Hours after the original date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the Operational Test given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

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MATERIAL INFORMATION

None.

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ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 747

Service Bulletin

ALERT

Number: 747-28A2330

Original Issue: April 02, 2012

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Engine Fuel Suction Feed Operational Test

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplane(s) shown below.

Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 747-400, 747-400D, 747-400F airplanes

Airplane Models:

747-400, 747-400D, 747-400F

Variable Number Group

RF001 - RF006 1

RL401 - RL403 1

RL411 - RL436 1

RL451 - RL456 1

RL461 - RL462 1

RL471 - RL481 1

RL491 - RL492 1

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Variable Number Group

RL501 - RL502 1

RL511 - RL516 1

RL521 - RL522 1

RL531 - RL534 1

RL551 1

RL561 - RL568 1

RL571 - RL572 1

RL576 - RL577 1

RL579 1

RL581 - RL586 1

RL651 - RL655 1

RL671 - RL675 1

RL681 - RL684 1

RL751 - RL752 1

RM001 - RM007 1

RM010 - RM013 1

RM021 - RM024 1

RM026 - RM030 1

RM036 - RM045 1

RM051 - RM053 1

RM071 1

RM081 - RM084 1

RM091 1

RM096 - RM097 1

RM116 - RM117 1

RM126 - RM132 1

RM136 - RM147 1

RM156 - RM158 1

RM166 - RM177 1

RM191 - RM192 1

RM231 - RM233 1

RM241 - RM246 1

RM261 - RM264 1

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Variable Number Group

RM316 - RM318 1

RM331 - RM333 1

RM341 1

RM351 - RM355 1

RM366 - RM367 1

RM401 - RM403 1

RM426 1

RM431 1

RM441 - RM443 1

RM445 1

RM801 - RM803 1

RM811 - RM813 1

RM851 - RM859 1

RM861 - RM863 1

RM871 - RM899 1

RM901 - RM906 1

RM911 1

RR701 1

RR721 - RR724 1

RR746 - RR748 1

RR851 - RR856 1

RR861 - RR862 1

RR951 - RR952 1

RT001 - RT014 1

RT021 - RT022 1

RT031 - RT035 1

RT041 - RT047 1

RT061 1

RT071 - RT075 1

RT101 - RT103 1

RT121 1

RT131 - RT137 1

RT151 - RT152 1

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Variable Number Group

RT161 - RT168 1

RT401 - RT412 1

RT431 - RT447 1

RT451 - RT469 1

RT471 - RT499 1

RT501 - RT535 1

RT551 - RT568 1

RT571 - RT591 1

RT601 - RT657 1

RT671 - RT673 1

RT681 - RT682 1

RT691 - RT699 1

RT701 - RT704 1

RT711 - RT717 1

RT741 - RT757 1

RT776 - RT777 1

RT781 - RT784 1

RT801 - RT803 1

RT811 - RT814 1

RT831 - RT837 1

RT861 - RT864 1

RT876 - RT880 1

RT931 - RT932 1

RT945 - RT949 1

RT951 - RT955 1

RT966 - RT967 1

RU001 - RU006 1

RU016 - RU017 1

RU031 - RU032 1

RU051 - RU052 1

RU059 - RU062 1

RU081 - RU083 1

RU101 - RU102 1

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Variable Number Group

RU121 - RU132 1

RU801 - RU809 1

RU831 - RU841 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin provides instructions to operators to perform an Engine Fuel Suction Feed

Operational Test on each engine individually. This test is required in order to protect against engine

flameout during suction feed operations. The instructions given in this service bulletin are provided to

detect and correct failure of the engines fuel suction feed of the fuel system, which could result in dual

engine flameout and inability to restart the engines, and consequent forced landing of the airplane.

Accomplishing the fuel system suction feed test and continuing to repeat the testing within the specified

compliance times will reduce the possibility of an engine flameout resulting from air ingestion into the

engine fuel feed system during low fuel level conditions with inoperative boost pumps .

An operator reported a 737-400 Engine No. 1 flameout during cruise. The Engine No. 2 continued to

operate normally. The flight crew conducted two restart attempts within the start envelope with no

success then diverted uneventfully. Another operator reported a 737-300 Engine No. 2 shut down when

the start lever was placed in the idle position during taxi to the gate. The Engine number 1 continued

to operate normally. Maintenance performed a vacuum test of the engine fuel feed system and found

a crack in a fuel feed tube. The fuel feed tube was replaced and the vacuum test of the fuel feed system

was performed and passed successfully.

D. Description

The work packages can be done in any order.

WORK PACKAGE 1 - ENGINE NO. 1 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 1 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the

test Before Further Flight.

WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 2 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the

test Before Further Flight.

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BOEING SERVICE BULLETIN 747-28A2330

ALERT ALERT
WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 3 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the

test Before Further Flight.

WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST

1. Do the Engine No. 4 - Fuel Suction Feed - Operational Test.

2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the

test Before Further Flight.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

747-400, 747-400D, 747-400F 221, 222

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2007-NM-357-AD, is

related to this service bulletin.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Table 1: ENGINE NO. 1 - FUEL SUCTION FEED - OPERATIONAL TEST

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 30,000 flight 30,000 flight hours

hours after the

original issue date

of this service bulletin.

Do the Engine No. 1 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 1.

All airplanes

Before Further -

Flight

Isolate the cause of the

leak, repair, and repeat

the Engine No 1 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 1.

If the Engine No. 1 Fuel

Suction Feed - Operational

Test fails

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ALERT ALERT
Table 2: ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 30,000 flight 30,000 flight hours

hours after the

original issue date

of this service bulletin.

Do the Engine No. 2 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 2.

All airplanes

Before Further -

Flight

Isolate the cause of the

leak, repair, and repeat

the Engine No. 2 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 2.

If the Engine No. 2 Fuel

Suction Feed - Operational

Test fails

Table 3: ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 30,000 flight 30,000 flight hours

hours after the

original issue date

of this service bulletin.

Do the Engine No. 3 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 3.

All airplanes

Before Further -

Flight

Isolate the cause of the

leak, repair, and repeat

the Engine No. 3 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 3.

If the Engine No. 3 Fuel

Suction Feed - Operational

Test fails

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BOEING SERVICE BULLETIN 747-28A2330

ALERT ALERT
Table 4: ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 30,000 flight 30,000 flight hours

hours after the

original issue date

of this service bulletin.

Do the Engine No. 4 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 4.

All airplanes

Before Further -

Flight

Isolate the cause of the

leak, repair, and repeat

the Engine No. 4 Fuel

Suction Feed - Operational Test in accordance

with Accomplishment Instructions, paragraph

3.B., Work Instructions,

Work Package 4.

If the Engine No. 4 Fuel

Suction Feed - Operational

Test fails

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

WORK PACKAGE 1 - ENGINE NO - 1 - FUEL SUCTION FEED - OPERATIONAL TEST

Task Number of Persons Task Hours Elapsed Hours

Test 3 3.00 1.00

Repair (a)

TOTAL FOR ENGINE NO.1 (a) 3.00 1.00

(a) Totals given assume no repairs necessary.

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WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST

Task Number of Persons Task Hours Elapsed Hours

Test 3 3.00 1.00

Repair (a)

TOTAL FOR ENGINE NO.2 (a) 3.00 1.00

(a) Totals given assume no repairs necessary

WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST

Task Number of Persons Task Hours Elapsed Hours

Test 3 3.00 1.00

Repair (a)

TOTAL FOR ENGINE NO.3 (a) 3.00 1.00

(a) Totals given assume no repairs necessary.

WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST

Task Number of Persons Task Hours Elapsed Hours

Test 3 3.00 1.00

Repair (a)

TOTAL FOR ENGINE NO.4 (a) 3.00 1.00

(a) Totals given assume no repairs necessary.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) NPRM

2007-NM-357-AD

b. Service Bulletin Index D6-30300

c. 747-400 Aircraft Maintenance Manual 747-400 AMM 28-22-00, 28-22-07, 28-26-00, 49-11-00,

71-00-00.

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BOEING SERVICE BULLETIN 747-28A2330

ALERT ALERT
2. Data Supplied with this Service Bulletin:

None.

3. Installation Drawings Used in the Preparation of this Service Bulletin:

None.

K. Publications Affected

1. Publications:

Publication Chapter-Section

747 Aircraft Maintenance Manual 28-22

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

M. Software Accomplishment Summary

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the test an/or repair configuration changes given in this

service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

None.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently.

4. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

5. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

6. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

7. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

B. WORK INSTRUCTIONS

Prepare for tests.

1. Do the "Engine Ground Safety Precautions". Refer to 747-400 AMM 71-00-00

2. Do the "Prepare for the Power Plant Operation". Refer to 747-400 AMM 71-00-00

3. Make sure that the hydraulic pump switches are as shown below:

a. HYD PUMPS ENGINE 1 - OFF

b. HYD PUMPS ENGINE 2 - OFF

c. HYD PUMPS ENGINE 3 - OFF

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ALERT ALERT
d. HYD PUMPS ENGINE 4 - OFF

e. HYD PUMPS DEMAND 1 - OFF

f. HYD PUMPS DEMAND 2 - OFF

g. HYD PUMPS DEMAND 3 - OFF

h. HYD PUMPS DEMAND 4 - AUX.

NOTE: The fuel quantity values given in the following work packages are at or below the fuel

level necessary to cover the hydraulic heat exchangers. The hydraulic system pumps

must be set as given above when you operate the engines for the fuel suction feed -

operational tests. The No. 4 engine auxiliary hydraulic pump must remain on to supply

pressure for the parking brake.

WORK PACKAGE 1 - ENGINE NO. 1 - FUEL SUCTION FEED - OPERATIONAL TEST

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON AND

STAYS ON. THIS CONDITION CAN CAUSE THE IGNITION OF THE FUEL FUMES IN

THE FUEL TANK. A FIRE OR AN EXPLOSION CAN CAUSE INJURIES TO PERSONNEL

AND DAMAGE TO EQUIPMENT.

WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR

EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE

GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.

1. Make sure that these quantities of fuel are in the fuel tanks

TANK FUEL QUANTITY

Center Tank 38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)

Main Tank No. 1 2,200 +/- 200 Lbs (1000 +/- 100 Kgs)

Main Tank No. 2 1,600 +/- 200 Lbs (700 +/- 100 Kgs)

Reserve Tank No. 1 and No. 4 No Restriction

Auxiliary Tank (if installed) No Restriction

NOTE: Excess fuel can be transferred to Main Tank 3 and 4. Refer to "Tank to Tank Fuel Transfer"

747-400 AMM 28-26-00.

2. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are open

3. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are closed

4. Make sure all Fuel boost pump switches are OFF

5. Turn on No. 1 Main Tank FWD and AFT boost pumps

6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-400 AMM

71-00-00

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ALERT ALERT
7. Make sure the APU is shut down. Refer to 747-400 AMM 49-11-00

8. After the two minute minimum warm-up period, monitor and record engine parameters:

a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow

b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow

9. Turn OFF the No. 1 Main Tank FWD and AFT boost pumps to begin the suction feed test

10. Make sure the engine continues to operate for a minimum of 5 minutes and engine parameters:

a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease

b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease

c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters

N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:

(1) Turn on No. 1 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

(3) Isolate the cause of the leak, refer to "Engine Fuel-Feed Manifold Air Pressure Leak

Check" 747-400 AMM 28-22-07 or "Boost Pump Bypass Fuel-Feed Line Vacuum Test"

747-400 AMM 28-22-00 and repair

(4) After repair repeat this suction feed test.

d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,

N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:

(1) Turn on No. 1 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

11. Do all of the remaining Work Packages

12. If this is the last Work Package, put the airplane back to a serviceable condition.

WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON AND

STAYS ON. THIS CONDITION CAN CAUSE THE IGNITION OF THE FUEL FUMES IN

THE FUEL TANK. A FIRE OR AN EXPLOSION CAN CAUSE INJURIES TO PERSONNEL

AND DAMAGE TO EQUIPMENT

WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR

EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE

GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.

1. Make sure that these quantities of fuel are in the fuel tanks

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BOEING SERVICE BULLETIN 747-28A2330

ALERT ALERT
TANK FUEL QUANTITY

Center Tank 38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)

Main Tank No. 1 2,200 +/- 200 Lbs (1000 +/- 100 Kgs)

Main Tank No. 2 1,600 +/- 200 Lbs (700 +/- 100 Kgs)

Reserve Tank No. 1 and No. 4 No Restriction

Auxiliary Tank (If Installed) No Restriction

NOTE: Excess fuel can be transferred to Main Tank 3 and 4. Refer to 747-400 AMM 28-26-00.

2. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are open

3. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are closed

4. Make sure all Fuel boost pump switches are OFF

5. Turn on No. 2 Main Tank FWD and AFT boost pump

6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-400 AMM

71-00-00

7. Make sure the APU is shut down. Refer to 747-400 AMM 49-11-00

8. After the two minute minimum warm-up period, monitor and record engine parameters:

a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow

b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow

9. Turn OFF the No. 2 Main Tank FWD and AFT boost pumps to begin the suction feed test

10. Make sure engine continues to operate for a minimum of 5 minutes and engine parameters:

a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease

b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease

c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters

N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:

(1) Turn on No. 2 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

(3) Isolate the cause of the leak, refer to "Engine Fuel-Feed Manifold Air Pressure Leak

Check" 747-400 AMM 28-22-07 or "Boost Pump Bypass Fuel-Feed Line Vacuum Test"

747-400 AMM 28-22-00 and repair

(4) After repair repeat this suction feed test

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BOEING SERVICE BULLETIN 747-28A2330

ALERT ALERT
d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,

N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:

(1) Turn on No. 2 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

11. Do all of the remaining Work Packages

12. If this is the last Work Package, put the airplane back to a serviceable condition.

WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON AND

STAYS ON. THIS CONDITION CAN CAUSE THE IGNITION OF THE FUEL FUMES IN

THE FUEL TANK. A FIRE OR AN EXPLOSION CAN CAUSE INJURIES TO PERSONNEL

AND DAMAGE TO EQUIPMENT

WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR

EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE

GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.

1. Make sure that these quantities of fuel are in the fuel tanks

TANK FUEL QUANTITY

Center Tank 38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)

Main Tank No. 4 2,200 +/- 200 Lbs (1000 +/- 100 Kgs)

Main Tank No. 3 1,600 +/- 200 Lbs (700 +/- 100 Kgs)

Reserve Tank No. 1 and No. 4 No Restriction

Auxiliary Tank (if installed) No Restriction

NOTE: Excess fuel can be transferred to Main Tank 1 and 2. Refer to 747-400 AMM 28-26-00.

2. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are open

3. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are closed

4. Make sure all Fuel boost pump switches are OFF

5. Turn on No. 3 Main Tank FWD and AFT boost pump

6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-400 AMM

71-00-00

7. Make sure the APU is shut down. Refer to AMM 747-400 AMM 49-11-00

8. After the two minute minimum warm-up period, monitor and record engine parameters:

a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow

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ALERT ALERT
b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow

9. Turn OFF the No. 3 Main Tank FWD and AFT boost pumps to begin the suction feed test

10. Make sure engine continues to operate for a minimum of 5 minutes and engine parameters:

a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease

b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease

c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters

N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:

(1) Turn on No. 3 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

(3) Isolate the cause of the leak, refer to "Engine Fuel-Feed Manifold Air Pressure Leak

Check" 747-400 AMM 28-22-07 or "Boost Pump Bypass Fuel-Feed Line Vacuum Test"

747-400 AMM 28-22-00 and repair

(4) After repair repeat this suction feed test

d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,

N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:

(1) Turn on No. 3 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

11. Do all of the remaining Work Packages

12. If this is the last Work Package, put the airplane back to a serviceable condition.

WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON AND

STAYS ON. THIS CONDITION CAN CAUSE THE IGNITION OF THE FUEL FUMES IN

THE FUEL TANK. A FIRE OR AN EXPLOSION CAN CAUSE INJURIES TO PERSONNEL

AND DAMAGE TO EQUIPMENT

WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR

EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE

GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.

1. Make sure that these quantities of fuel are in the fuel tanks

TANK FUEL QUANTITY

Center Tank 38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)

Main Tank No. 4 2,200 +/- 200 Lbs (1000 +/- 100 Kgs)

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ALERT ALERT
TANK FUEL QUANTITY

Main Tank No. 3 1,600 +/- 200 Lbs (700 +/- 100 Kgs)

Reserve Tank No. 1 and No. 4 No Restriction

Auxiliary Tank (if installed) No Restriction

NOTE: Excess fuel can be transferred to Main Tank 1 and 2. Refer to 747-400 AMM 28-26-00.

2. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are open

3. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are closed

4. Make sure all Fuel boost pump switches are OFF

5. Turn on No. 4 Main Tank FWD and AFT boost pump

6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-400 AMM

71-00-00

7. Make sure the APU is shut down. Refer to 747-400 AMM 49-11-00

8. After the two minute minimum warm-up period, monitor and record engine parameters:

a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow

b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow

9. Turn OFF the No. 4 Main Tank FWD and AFT boost pumps to begin the suction feed test

10. Make sure engine continues to operate for a minimum of 5 minutes and engine parameters:

a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease

b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease

c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters

N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:

(1) Turn on No. 4 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

(3) Isolate the cause of the leak, refer to "Engine Fuel-Feed Manifold Air Pressure Leak

Check" 747-400 AMM 28-22-07 or "Boost Pump Bypass Fuel-Feed Line Vacuum Test"

747-400 AMM 28-22-00 and repair

(4) After repair repeat this suction feed test

d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,

N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:

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ALERT ALERT
(1) Turn on No. 4 Main Tank FWD and AFT boost pumps

(2) Shut down the engine. Refer to 747-400 AMM 71-00-00

11. Do all of the remaining Work Packages

12. If this is the last Work Package, put the airplane back to a serviceable condition.

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ALERT ALERT