Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-28A1307

Original Issue: May 14, 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Unpublished Work.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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liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection

with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management

Company.

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BOEING SERVICE BULLETIN 737-28A1307

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BLANK PAGE
Table of Contents

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

1. PLANNING INFORMATION ........................................ 7

A. Effectivity ................................................ 7

1. Airplanes ............................................. 7

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

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

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

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 737

Service Bulletin

ALERT

Summary Number: 737-28A1307

Original Issue: May 14, 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 flameout during taxi to the gate when the start

lever was placed in the idle position. Maintenance performed a vacuum test of the fuel feed system and found

a crack in the fuel feed tube. The fuel feed tube was replaced, and a 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

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ACTION

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, repair, and repeat the Engine No. 1

Fuel Suction Feed - Operational Test.

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, repair, and repeat the Engine No. 2

Fuel Suction Feed - Operational Test.

EFFECTIVITY

737-300/400/500 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-351-AD, is related to

this service bulletin.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the test and/or repair procedures given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

None.

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BOEING SERVICE BULLETIN 737-28A1307

ALERT ALERT
Commercial 

Airplanes 737

Service Bulletin

ALERT

Number: 737-28A1307

Original Issue: May 14, 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 D6-19567 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

1 - 737-300/400/500 airplanes

Airplane Models:

737-300, 737-400, 737-500

Variable Number Group

PJ301 - PJ302 1

PJ551 - PJ561 1

PJ601 - PJ615 1

PJ811 1

PJ816 - PJ817 1

PM381 - PM399 1

PM401 - PM417 1

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Variable Number Group

PM541 - PM564 1

PP001 - PP054 1

PP101 - PP169 1

PP181 - PP199 1

PP201 - PP205 1

PP221 1

PP231 - PP243 1

PP281 - PP286 1

PP301 - PP305 1

PP351 - PP353 1

PP376 - PP384 1

PP391 - PP393 1

PP401 - PP440 1

PP471 - PP475 1

PP501 - PP522 1

PP631 - PP634 1

PP651 - PP652 1

PP671 - PP699 1

PP701 - PP733 1

PP771 - PP779 1

PP801 - PP808 1

PP821 - PP827 1

PP831 - PP848 1

PP851 - PP852 1

PP861 - PP877 1

PP891 - PP899 1

PP901 - PP936 1

PP946 - PP948 1

PP951 - PP952 1

PP961 - PP967 1

PP981 - PP991 1

PP993 1

PQ001 - PQ016 1

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BOEING SERVICE BULLETIN 737-28A1307

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Variable Number Group

PQ026 - PQ041 1

PQ051 - PQ092 1

PQ101 - PQ199 1

PQ201 - PQ202 1

PQ221 - PQ237 1

PQ241 - PQ243 1

PQ251 - PQ267 1

PQ281 - PQ299 1

PQ301 - PQ307 1

PQ331 - PQ332 1

PQ341 - PQ348 1

PQ361 - PQ373 1

PQ391 - PQ395 1

PQ401 - PQ418 1

PQ421 1

PQ431 - PQ438 1

PQ447 - PQ448 1

PQ451 1

PQ454 1

PQ471 - PQ475 1

PQ479 - PQ481 1

PQ486 - PQ487 1

PQ491 - PQ493 1

PQ771 - PQ772 1

PQ791 - PQ793 1

PQ801 - PQ805 1

PQ931 - PQ935 1

PQ951 1

PQ971 - PQ997 1

PR001 - PR017 1

PR021 - PR034 1

PR041 - PR045 1

PR061 - PR072 1

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BOEING SERVICE BULLETIN 737-28A1307

ALERT ALERT
Variable Number Group

PR077 - PR082 1

PR091 - PR092 1

PR096 1

PR101 1

PR121 - PR122 1

PR131 - PR132 1

PR141 - PR143 1

PR161 - PR172 1

PR181 1

PS601 - PS631 1

PS636 - PS638 1

PS641 - PS644 1

PS651 - PS657 1

PS666 - PS669 1

PS691 - PS692 1

PS701 - PS706 1

PS751 - PS799 1

PS811 1

PS836 - PS837 1

PS841 - PS846 1

PS851 - PS852 1

PS856 1

PS861 - PS863 1

PS866 - PS868 1

PS871 - PS874 1

PS896 - PS897 1

PS901 - PS941 1

PS956 - PS957 1

PS961 - PS963 1

PS971 - PS978 1

PT001 - PT015 1

PT021 - PT031 1

PT041 - PT064 1

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Variable Number Group

PT101 - PT105 1

PT121 - PT138 1

PT146 - PT148 1

PT161 - PT170 1

PT181 - PT188 1

PT211 - PT220 1

PT295 1

PT301 - PT309 1

PT331 - PT360 1

PT381 - PT399 1

PT401 - PT438 1

PT501 - PT517 1

PT561 - PT565 1

PT581 - PT586 1

PT611 - PT621 1

PT641 - PT644 1

PT651 - PT656 1

PT671 - PT672 1

PT681 - PT685 1

PT701 - PT703 1

PT716 - PT717 1

PT721 - PT725 1

PT801 - PT834 1

PT851 - PT854 1

PT871 - PT886 1

PT901 - PT930 1

PT971 - PT973 1

PT981 - PT985 1

PT996 1

PU001 - PU025 1

PU301 1

PU311 - PU313 1

PV001 - PV055 1

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Variable Number Group

PV201 - PV209 1

PV226 - PV229 1

PV231 - PV237 1

PV271 - PV272 1

PV281 - PV287 1

PV296 1

PV301 - PV302 1

PV351 1

PV356 - PV357 1

PW001 - PW054 1

PW061 - PW068 1

PW072 1

PW086 - PW088 1

PW091 - PW094 1

PW101 - PW102 1

PW106 1

PW111 - PW120 1

PW156 - PW157 1

PW161 - PW171 1

PW201 - PW252 1

PW261 - PW268 1

PW271 - PW276 1

PW278 1

PW281 - PW293 1

PW296 1

PW301 - PW327 1

PW401 - PW408 1

PW411 - PW418 1

PW421 - PW424 1

PW431 - PW435 1

PW441 - PW450 1

PW461 - PW467 1

PW501 - PW504 1

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Variable Number Group

PW511 - PW522 1

PW524 - PW550 1

PW556 - PW557 1

PW561 - PW564 1

PW571 - PW576 1

PW591 - PW596 1

PW611 - PW622 1

PW631 - PW637 1

PW661 - PW662 1

PW681 - PW683 1

PW701 - PW702 1

PW711 - PW717 1

PW741 - PW742 1

PW761 1

PW771 1

PW831 1

PW851 - PW856 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 .

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1307

ALERT ALERT
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 flameout during

taxi to the gate when the start lever was placed in the idle position. Maintenance performed a vacuum

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

and a vacuum test of the fuel feed system was performed and passed successfully

D. Description

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, repair, and repeat the Engine

No. 1 Fuel Suction Feed - Operational Test.

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, repair, and repeat the Engine

No. 2 Fuel Suction Feed - Operational Test.

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

Affected Maintenance Zones

Model Zone

737-300, 737-400, 737-500 101, 102, 305, 405

E. 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-351-AD, is

related to this service bulletin.

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BOEING SERVICE BULLETIN 737-28A1307

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

Repeat Interval

(Whichever Occurs First)

Compliance Time

(Whichever Occurs First)

Condition Action

7,500 Flight Hours

or 24 Months

Within 7,500 Flight

Hours or 24

Months 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,

CONFIGURATION 1,

WORKPACKAGE 1 or

Accomplishment Instructions paragraph 3.B.,

CONFIGURATION 2,

WORKPACKAGE 3.

Group 1

Before Further -

Flight

Isolate the cause, repair,

and repeat the Engine

No. 1 Fuel Suction Feed

- Operation Test in accordance with Accomplishment Instructions, paragraph 3.B., Work Instructions, CONFIGURATION

1, WORKPACKAGE 1 or

Accomplishment Instructions paragraph 3.B.,

CONFIGURATION 2,

WORKPACKAGE 3.

If the Engine No. 1 Fuel

Suction Feed Operation

Test fails

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

Repeat Interval

(Whichever Occurs First)

Compliance Time

(Whichever Occurs First)

Condition Action

7,500 Flight Hours

or 24 Months

Within 7,500 Flight

Hours or 24

Months 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,

CONFIGURATION 1,

WORKPACKAGE 2 or

Accomplishment Instructions, paragraph 3.B.,

CONFIGURATION 2,

WORKPACKAGE 4.

Group 1

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BOEING SERVICE BULLETIN 737-28A1307

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

Repeat Interval

(Whichever Occurs First)

Compliance Time

(Whichever Occurs First)

Condition Action

Before Further -

Flight

Isolate the cause, repair,

and repeat the Engine

No. 2 Fuel Suction Feed

- Operation Test in accordance with Accomplishment Instructions, paragraph 3.B., Work Instructions, CONFIGURATION

1, WORKPACKAGE 2 or

Accomplishment Instructions, paragraph 3.B.,

CONFIGURATION 2,

WORKPACKAGE 4.

If the Engine No. 2 Fuel

Suction Feed Operation

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

TABLE 1 - ENGINE NO. 1, FUEL SUCTION FEED - OPERATIONAL TEST

Task Number of Persons Task Hours Elapsed Hours

Test, Accomplishment 3 3.00 1.00

Instructions, paragraph 3.B., Work Instructions, CONFIGURATION 1, WORKPACKAGE 1 (a)

Test, Accomplishment 3 6.00 2.00

Instructions, paragraph 3.B., Work Instructions, CONFIGURATION 2, WORKPACKAGE 3 (b)

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BOEING SERVICE BULLETIN 737-28A1307

ALERT ALERT
TABLE 1 - ENGINE NO. 1, FUEL SUCTION FEED - OPERATIONAL TEST

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR ENGINE NO.1 (c) - -

(a) The Fuel Suction Feed Operational Test provided in Configuration 1, Workpackage 1

requires only one engine run.

(b) The Fuel Suction Feed Operational Test provided in Configuration 2, Workpackage 3

requires two engine runs and may not require fuel to be removed from the aircraft.

(c) Use the Task Hours for the test you accomplished to obtain Total Task hours.

TABLE 2 - ENGINE NO. 2, FUEL SUCTION FEED - OPERATIONAL TEST

Task Number of Persons Task Hours Elapsed Hours

Test, Accomplishment 3 3.00 1.00

Instructions, paragraph 3.B., Work Instructions, CONFIGURATION 1, WORKPACKAGE 2 (a)

Test, Accomplishment 3 6.00 2.00

Instructions, paragraph 3.B., Work Instructions, CONFIGURATION 2, WORKPACKAGE 4 (b)

TOTAL FOR ENGINE NO.2 (c) - -

(a) The Fuel Suction Feed Operational Test provided in Configuration 1, Workpackage 2

requires only one engine run.

(b) The Fuel Suction Feed Operational Test provided in Configuration 2, Workpackage 4

requires two engine runs and may not require fuel to be removed from the aircraft.

(c) Use the Task Hours for the test you accomplished to obtain Total Task hours.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Letter 737-SL-51-042

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BOEING SERVICE BULLETIN 737-28A1307

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

2007-NM-351-AD

c. Service Bulletin Index D6-19567

d. 737-300/400/500 Aircraft Maintenance Manual (AMM) 28-22-00, 71-00-00

a. Boeing Service Letter 737-SL-51-042

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

2007-NM-351-AD

c. Service Bulletin Index D6-19567

d. 737-300/400/500 Aircraft Maintenance Manual (AMM) 12-11-02, 28-22-00, 28-23-00, 71-00-00

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

737 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

Not affected.

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BOEING SERVICE BULLETIN 737-28A1307

ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the test and/or repair procedures 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
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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. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design

Guidelines, is an acceptable procedure to request information from Boeing for

additional structural repair instructions. The Service Letter describes what information

must be provided to Boeing before a structural repair can be provided.

6. 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.

7. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

B. WORK INSTRUCTIONS

1. ENGINE FUEL SUCTION FEED OPERATIONAL TEST - CONFIGURATION 1 PROCEDURE

NOTE: If the fuel quantities exceed the limits shown in Configuration 1, remove fuel to meet the

fuel quantities provided, or do the Engine Fuel Suction Feed tests in accordance with

Configuration 2.

NOTE: The Fuel Suction Feed Operational Tests provided in Configuration 1, Workpackage 1

and Workpackage 2 require only one engine run for each engine.

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BOEING SERVICE BULLETIN 737-28A1307

ALERT ALERT
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.

a. Do the "Engine Fuel Suction Feed - Operational Test". Refer to 737-300/400/500 AMM 28-22-00

as an accepted procedure. During the Test you must meet the following requirements:

(1) Make sure that these quantities of fuel are in the fuel tanks:

TANK FUEL QUANTITY

CENTER TANK 0 Lb - 2000 Lb (0 Kg- 907 Kg)

MAIN TANK 1 (Left) 1500 Lb -1700 Lb (680 Kg - 771 Kg)

AUXILIARY TANK (If Installed) 0 Lb - 200 Lb (0 Kg - 91 Kg)

NOTE: The fuel quantity values given above are at or below the fuel level needed to

cover the hydraulic heat exchangers. You must set the hydraulic system pumps

"Off" when you operate the engines for this test.

NOTE: If there is more fuel in the Center Tank and/or Main Tank 1 (Left) than

recommended in the tables above, transfer the excess fuel as necessary or

remove fuel from the fuel tanks. If defueling is not an option, the Engine No.1

Fuel Suction Feed Operational Test can be done twice in accordance with

"Engine Fuel Suction Feed Operational Test - Configuration 2". To remove fuel

refer to 737-300/400/500 AMM 28-23-00 - "Fuel Tank Defueling" as an accepted

procedure. To transfer fuel refer to 737-300/400/500 AMM 28-23-00 - "Fuel

Transfer from One Tank to a Different Tank" as an accepted procedure. To add

fuel refer to 737-300/400/500 AMM 12-11-02 - "Pressure Refuel Procedure" as

an accepted procedure.

(2) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before the

test.

NOTE: For Airplanes with Auxiliary Tank the FWD and AFT Auxiliary Tank Fuel Boost

Pumps switches on the P5 overhead panel should also be in the OFF position.

(3) The CROSSFEED valve switch, on the P5 Overhead Panel, is set to the CLOSED position.

(4) The APU switch on the overhead panel, P5, is in the OFF position.

(5) With at least one Main Tank 1 fuel boost pump ON, operate Engine No. 1 at idle power

for a minimum of two (2.0) minutes. Make a record of the engine parameters (N1, N2,

and Fuel Flow).

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ALERT ALERT
(6) With the fuel boost pumps OFF, make sure that the Engine No. 1 continues to operate

for a minimum of five (5.0) minutes and the engine parameters (N1, N2, and Fuel Flow)

do not decrease.

b. If the engine does not operate for the full five (5.0) minutes or there is a decrease in N1, N2,

or Fuel Flow, then do the following:

(1) Set the two Main Tank 1 (Left) fuel boost pumps switches on the P5 Overhead Panel to

the ON position.

(2) Shut down the Engine No. 1. Refer to 737-300/400/500 AMM 71-00-00 as an acceptable

procedure.

(3) If the Engine Fuel Suction Feed Operational Test fails, Isolate the cause, repair, and

repeat the "Engine Fuel Suction Feed - Operational Test". To troubleshoot refer to

737-300/400/500 AMM 28-22-00, "Engine Fuel Feed Lines/Coupling Vacuum Test".

c. If the engine operates for the full five (5) minutes with no decrease in N1, N2, or Fuel Flow,

then do the following:

(1) Set the two Main Tank 1 (Left) fuel boost pumps switches on the P5 Overhead Panel to

the ON position.

(2) Shut down the Engine No. 1. Refer to 737-300/400/500 AMM 71-00-00 as an accepted

procedure.

(3) Put the airplane back to 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.

a. Do the "Engine Fuel Suction Feed - Operational Test". Refer to 737-300/400/500 AMM 28-22-00

as an accepted procedure. During the Test you must meet the following requirements:

(1) Make sure that these quantities of fuel are in the fuel tanks:

TANK FUEL QUANTITY

CENTER TANK 0 Lb - 2000 Lb (0 Kg- 907 Kg)

MAIN TANK 2 (Right) 1500 Lb -1700 Lb (680 Kg - 771 Kg)

AUXILIARY TANK (If Installed) 0 Lb - 200 Lb (0 Kg - 91 Kg)

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ALERT ALERT
NOTE: The fuel quantity values given above are at or below the fuel level needed to

cover the hydraulic heat exchangers. You must set the hydraulic system pumps

"Off" when you operate the engines for this test.

NOTE: If there is more fuel in the Center Tank and/or Main Tank 2 (Right) than

recommended in the tables above, transfer the excess fuel as necessary or

remove fuel from the fuel tanks. If defueling is not an option, the Engine No.2

Fuel Suction Feed Operational Test can be done twice in accordance with

"Engine Fuel Suction Feed Operational Test - Configuration 2". To remove fuel

refer to 737-300/400/500 AMM 28-23-00 - "Fuel Tank Defueling" as an accepted

procedure. To transfer fuel refer to 737-300/400/500 AMM 28-23-00 - "Fuel

Transfer from One Tank to a Different Tank" as an accepted procedure. To add

fuel refer to 737-300/400/500 AMM 12-11-02 - "Pressure Refuel Procedure" as

an accepted procedure.

(2) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before the

test.

NOTE: For Airplanes with Auxiliary Tank the FWD and AFT Auxiliary Tank Fuel Boost

Pumps switches on the P5 overhead panel should also be in the OFF position.

(3) The CROSSFEED valve switch, on the P5 Overhead Panel, is set to the CLOSED position.

(4) The APU switch on the overhead panel, P5, is in the OFF position.

(5) With at least one Main Tank 2 fuel boost pump ON, operate Engine No. 2 at idle power,

with the boost pumps on for a minimum of two (2.0) minutes. Make a record of the engine

parameters (N1, N2, and Fuel Flow).

(6) With the fuel boost pumps OFF, make sure that the Engine No. 2 continues to operate

for a minimum of five (5.0) minutes and the engine parameters (N1, N2, and Fuel Flow)

do not decrease.

b. If the engine does not operate for the full five (5.0) minutes or there is a decrease in N1, N2,

or Fuel Flow, then do the following:

(1) Set the two Main Tank 2 (Right) fuel boost pumps switches on the P5 Overhead Panel

to the ON position.

(2) Shut down the Engine No. 2. Refer to 737-300/400/500 AMM 71-00-00 as an acceptable

procedure.

(3) If the Engine Fuel Suction Feed Operational Test fails, Isolate the cause, repair, and

repeat the "Engine Fuel Suction Feed - Operational Test". To troubleshoot refer to

737-300/400/500 AMM 28-22-00, "Engine Fuel Feed Lines/Coupling Vacuum Test".

c. If the engine operates for the full five (5.0) minutes with no decrease in N1, N2, or Fuel Flow,

then do the following:

(1) Set the two Main Tank 2 (Right) fuel boost pumps switches on the P5 Overhead Panel

to the ON position.

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ALERT ALERT
(2) Shut down the Engine No. 2. Refer to 737-300/400/500 AMM 71-00-00 as an acceptable

procedure.

(3) Put the airplane back to serviceable condition.

2. ENGINE FUEL SUCTION FEED OPERATIONAL TEST - CONFIGURATION 2 PROCEDURE

NOTE: The Fuel Suction Feed Operational Test provided in Configuration 2, Workpackage 3

and Workpackage 4 require two engine runs for each engine and may not require fuel to

be removed from the aircraft.

NOTE: If the fuel quantities exceed the limits shown in Configuration 1 and defueling is not an

option, Engine Fuel Suction Feed Operational Test must be accomplished twice on each

engine. The first test must meet the requirements of CONFIGURATION 2, ENGINE RUN

1 which will test the center tank fuel feed plumbing, and the second test must meet the

requirements of CONFIGURATION 2, ENGINE RUN 2 which will test the Main Tank fuel

feed plumbing.

a. WORKPACKAGE 3

ENGINE NO. 1, FUEL SUCTION FEED - OPERATIONAL TEST, ENGINE RUN 1

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) Do the "Engine Fuel Suction Feed - Operational Test". Refer to 737-300/400/500 AMM

28-22-00 as an accepted procedure. During the Test you must meet the following

requirements:

(a) Make sure that these quantities of fuel are in the fuel tanks:

TANK FUEL QUANTITY

CENTER TANK 0 Lb - 2000 Lb (0 Kg- 907 Kg)

Any quantity above 1700 Lb (771 Kg) and within 1000

Lb (454 Kg) of Main Tank 2

MAIN TANK 1 (Left)

AUXILIARY TANK (If Installed) 0 Lb - 200 Lb (0 Kg - 91 Kg)

NOTE: The fuel quantity values given above are at or below the fuel level needed

to cover the hydraulic heat exchangers. You must set the hydraulic system

pumps "Off" when you operate the engines for this test.

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ALERT ALERT
NOTE: If there is more fuel in the Center Tank and/or Main Tank 1 (Left) than

recommended in the tables above, transfer the excess fuel as necessary

or remove fuel from the fuel tanks. To remove fuel refer to 737-300/400/500

AMM 28-23-00 - "Fuel Tank Defueling" as an accepted procedure. To

transfer fuel refer to 737-300/400/500 AMM 28-23-00 - "Fuel Transfer from

One Tank to a Different Tank" as an accepted procedure. To add fuel refer

to 737-300/400/500 AMM 12-11-02 - "Pressure Refuel Procedure" as an

accepted procedure.

(b) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before

the test.

NOTE: For Airplanes with Auxiliary Tank the FWD and AFT Auxiliary Tank Fuel

Boost Pumps switches on the P5 overhead panel should also be in the OFF

position.

(c) The CROSSFEED valve switch, on the P5 Overhead Panel, is set to the CLOSED

position.

(d) The APU switch on the overhead panel, P5, is in the OFF position.

(e) With at least one Main Tank 1 fuel boost pump ON, operate Engine No. 1 at idle

power, with the boost pumps on for a minimum of two (2.0) minutes. Make a record

of the engine parameters (N1, N2, and Fuel Flow).

(f) With the fuel boost pumps OFF, make sure that the Engine No. 1 continues to operate

for a minimum of five (5.0) minutes and the engine parameters (N1, N2, and Fuel

Flow) do not decrease.

(2) If the engine does not operate for the full five (5.0) minutes or there is a decrease in N1,

N2, or Fuel Flow, then do the following:

(a) Set the two Main Tank 1 (Left) fuel boost pumps switches on the P5 Overhead Panel

to the ON position.

(b) Shut down the Engine No. 1. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

(c) If the Engine Fuel Suction Feed Operational Test fails, Isolate the cause, repair, and

repeat the "Engine Fuel Suction Feed - Operational Test". To troubleshoot refer to

737-300/400/500 AMM 28-22-00, "Engine Fuel Feed Lines/Coupling Vacuum Test".

(3) If the engine operates for the full five (5) minutes with no decrease in N1, N2, or Fuel

Flow, then do the following:

(a) Set the two Main Tank 1 (Left) fuel boost pumps switches on the P5 Overhead Panel

to the ON position.

(b) Shut down the Engine No. 1. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

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ALERT ALERT
ENGINE NO. 1, FUEL SUCTION FEED - OPERATIONAL TEST, ENGINE RUN 2

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) Do the "Engine Fuel Suction Feed - Operational Test". Refer to 737-300/400/500 AMM

28-22-00 as an accepted procedure. During the Test you must meet the following

requirements:

(a) Make sure that these quantities of fuel are in the fuel tanks:

TANK FUEL QUANTITY

CENTER TANK Any quantity above 200 Lb (91 Kg)

MAIN TANK 1 (Left) 1500 Lb -1700 Lb (680 Kg - 771 Kg)

AUXILIARY TANK (If Installed) Any quantity above 200 Lb (91 Kg)

NOTE: The fuel quantity values given above are at or below the fuel level needed

to cover the hydraulic heat exchangers. You must set the hydraulic system

pumps "Off" when you operate the engines for this test.

NOTE: If there is more fuel in the Center Tank and/or Main Tank 1 (Left) than

recommended in the tables above, transfer the excess fuel as necessary

or remove fuel from the fuel tanks. To remove fuel refer to 737-300/400/500

AMM 28-23-00 - "Fuel Tank Defueling" as an accepted procedure. To

transfer fuel refer to 737-300/400/500 AMM 28-23-00 - "Fuel Transfer from

One Tank to a Different Tank" as an accepted procedure. To add fuel refer

to 737-300/400/500 AMM 12-11-02 - "Pressure Refuel Procedure" as an

accepted procedure.

(b) All fuel switches on P5 Overhead Panel are in the OFF position before the test.

NOTE: For Airplanes with Auxiliary Tank the FWD and AFT Auxiliary Tank Fuel

Boost Pumps switches on the P5 overhead panel should also be in the OFF

position.

(c) The CROSSFEED valve switch, on the P5 Overhead Panel, is set to the CLOSED

position.

(d) The APU switch on the overhead panel, P5, is in the OFF position.

(e) With at least one Main Tank 1 fuel boost pump ON, operate Engine No. 1 at idle

power, with the boost pumps on for a minimum of two (2.0) minutes. Make a record

of the engine parameters (N1, N2, and Fuel Flow).

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ALERT ALERT
(f) With the fuel boost pumps OFF, make sure that the Engine No. 1 continues to operate

for a minimum of five (5.0) minutes and the engine parameters (N1, N2, and Fuel

Flow) do not decrease.

(2) If the engine does not operate for the full five (5.0) minutes or there is a decrease in N1,

N2, or Fuel Flow, then do the following:

(a) Set the two Main Tank 1 (Left) fuel boost pumps switches on the P5 Overhead Panel

to the ON position.

(b) Shut down the Engine No. 1. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

(c) If the Engine Fuel Suction Feed Operational Test fails, Isolate the cause, repair, and

repeat the "Engine Fuel Suction Feed - Operational Test". To troubleshoot refer to

737-300/400/500 AMM 28-22-00, "Engine Fuel Feed Lines/Coupling Vacuum Test".

(3) If the engine operates for the full five (5) minutes with no decrease in N1, N2, or Fuel

Flow, then do the following:

(a) Set the two Main Tank 1 (Left) fuel boost pumps switches on the P5 Overhead Panel

to the ON position.

(b) Shut down the Engine No. 1. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

(c) Put the airplane back to serviceable condition.

b. WORKPACKAGE 4

ENGINE NO. 2, FUEL SUCTION FEED - OPERATIONAL TEST, ENGINE RUN 1

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) Do the "Engine Fuel Suction Feed - Operational Test". Refer to 737-300/400/500 AMM

28-22-00 as an accepted procedure. During the Test you must meet the following

requirements:

(a) Make sure that these quantities of fuel are in the fuel tanks:

TANK FUEL QUANTITY

CENTER TANK 0 Lb - 2000 Lb (0 Kg- 907 Kg)

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ALERT ALERT
TANK FUEL QUANTITY

Any quantity above 1700 Lb (771 Kg) and within 1,000

Lb (454 Kg) of the Main Tank 1

MAIN TANK 2 (Right)

AUXILIARY TANK (If Installed) 0 Lb - 200 Lb (0 Kg - 91 Kg)

NOTE: The fuel quantity values given above are at or below the fuel level needed

to cover the hydraulic heat exchangers. You must set the hydraulic system

pumps "Off" when you operate the engines for this test.

NOTE: If there is more fuel in the Center Tank and/or Main Tank 2 (Right) than

recommended in the tables above, transfer the excess fuel as necessary

or remove fuel from the fuel tanks. To remove fuel refer to 737-300/400/500

AMM 28-23-00 - "Fuel Tank Defueling" as an accepted procedure. To

transfer fuel refer to 737-300/400/500 AMM 28-23-00 - "Fuel Transfer from

One Tank to a Different Tank" as an accepted procedure. To add fuel refer

to 737-300/400/500 AMM 12-11-02 - "Pressure Refuel Procedure" as an

accepted procedure.

(b) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before

the test.

NOTE: For Airplanes with Auxiliary Tank the FWD and AFT Auxiliary Tank Fuel

Boost Pumps switches on the P5 overhead panel should also be in the OFF

position.

(c) The CROSSFEED valve switch, on the P5 Overhead Panel, is set to the CLOSED

position.

(d) The APU switch on the overhead panel, P5, is in the OFF position.

(e) With at least one Main Tank 2 fuel boost pump ON, operate Engine No. 2 at idle

power, with the boost pumps on for a minimum of two (2.0) minutes. Make a record

of the engine parameters (N1, N2, and Fuel Flow).

(f) With the fuel boost pumps OFF, make sure that the Engine No. 2 continues to operate

for a minimum of five (5.0) minutes and the engine parameters (N1, N2, and Fuel

Flow) do not decrease.

(2) If the engine does not operate for the full five (5.0) minutes or there is a decrease in N1,

N2, or Fuel Flow, then do the following:

(a) Set the two Main Tank 2 (Right) fuel boost pumps switches on the P5 Overhead

Panel to the ON position.

(b) Shut down the engine No. 2. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

(c) If the Engine Fuel Suction Feed Operational Test fails, Isolate the cause, repair, and

repeat the "Engine Fuel Suction Feed - Operational Test". To troubleshoot refer to

737-300/400/500 AMM 28-22-00, "Engine Fuel Feed Lines/Coupling Vacuum Test".

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ALERT ALERT
(3) If the engine operates for the full five (5.0) minutes with no decrease in N1, N2, or Fuel

Flow, then do the following:

(a) Set the two Main Tank 2 (Right) fuel boost pumps switches on the P5 Overhead

Panel to the ON position.

(b) Shut down the Engine No. 2. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

ENGINE NO. 2, FUEL SUCTION FEED - OPERATIONAL TEST, ENGINE RUN 2

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) Do the "Engine Fuel Suction Feed - Operational Test". Refer to 737-300/400/500 AMM

28-22-00 as an accepted procedure. During the Test you must meet the following

requirements:

(a) Make sure that these quantities of fuel are in the fuel tanks:

TANK FUEL QUANTITY

CENTER TANK Any quantity above 200 Lb (91 Kg)

MAIN TANK 2 (Right) 1500 Lb -1700 Lb (680 Kg - 771 Kg)

AUXILIARY TANK (If Installed) Any quantity above 200 Lb (91 Kg)

NOTE: The fuel quantity values given above are at or below the fuel level needed

to cover the hydraulic heat exchangers. You must set the hydraulic system

pumps "Off" when you operate the engines for this test.

NOTE: If there is more fuel in the Center Tank and/or Main Tank 2 (Right) than

recommended in the tables above, transfer the excess fuel as necessary

or remove fuel from the fuel tanks. To remove fuel refer to 737-300/400/500

AMM 28-23-00 - "Fuel Tank Defueling" as an accepted procedure. To

transfer fuel refer to 737-300/400/500 AMM 28-23-00 - "Fuel Transfer from

One Tank to a Different Tank" as an accepted procedure. To add fuel refer

to 737-300/400/500 AMM 12-11-02 - "Pressure Refuel Procedure" as an

accepted procedure.

(b) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before

the test.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1307

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NOTE: For Airplanes with Auxiliary Tank the FWD and AFT Auxiliary Tank Fuel

Boost Pumps switches on the P5 overhead panel should also be in the OFF

position.

(c) The CROSSFEED valve switch, on the P5 Overhead Panel, is set to the CLOSED

position.

(d) The APU switch on the overhead panel, P5, is in the OFF position.

(e) With at least one Main Tank 2 fuel boost pump ON, operate Engine No. 2 at idle

power, with the boost pumps on for a minimum of two (2.0) minutes. Make a record

of the engine parameters (N1, N2, and Fuel Flow).

(f) With the fuel boost pumps OFF, make sure that the Engine No. 2 continues to operate

for a minimum of five (5.0) minutes and the engine parameters (N1, N2, and Fuel

Flow) do not decrease.

(2) If the engine does not operate for the full five (5.0) minutes or there is a decrease in N1,

N2, or Fuel Flow, then do the following:

(a) Set the two Main Tank 2 (Right) fuel boost pumps switches on the P5 Overhead

Panel to the ON position.

(b) Shut down the Engine No.2. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

(c) If the Engine Fuel Suction Feed Operational Test fails, Isolate the cause, repair, and

repeat the "Engine Fuel Suction Feed - Operational Test". To troubleshoot refer to

737-300/400/500 AMM 28-22-00, "Engine Fuel Feed Lines/Coupling Vacuum Test".

(3) If the engine operates for the full five (5.0) minutes with no decrease in N1, N2, or Fuel

Flow, then do the following:

(a) Set the two Main Tank 2 (Right) fuel boost pumps switches on the P5 Overhead

Panel to the ON position.

(b) Shut down the Engine No. 2. Refer to 737-300/400/500 AMM 71-00-00 as an

acceptable procedure.

(c) Put the airplane back to serviceable condition.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: May 14, 2012

737-28A1307

31 of 31

BOEING SERVICE BULLETIN 737-28A1307

ALERT ALERT