# Boeing Alert Service Bulletin 737-28A1307: No revision named

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- Document: [Boeing Alert Service Bulletin 737-28A1307](https://openairdocs.org/service-documents/boeing/737-28a1307.md)
- Title as filed: U.S. DOT/FAA - SB-737-28A1307-00
- Pages: 31
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### Page 1

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.
9E991ECCN:
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Unpublished Work.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.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner™,
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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with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
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4.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ........................................ 1 3
B. Concurrent Requirements ...................................... 1 3
C. Reason ................................................ 1 3
D. Description .............................................. 1 4
E. Compliance .............................................. 1 4
F. Approval ............................................... 1 6
G. Manpower .............................................. 1 6
H. Weight and Balance Changes .................................... 1 7
I. Electrical Load Data ......................................... 1 7
J. References .............................................. 1 7
1. Existing Data: ......................................... 1 7
2. Data Supplied with this Service Bulletin: ........................... 1 8
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 8
K. Publications Affected ........................................ 1 8
L. Interchangeability and Intermixability of Parts ........................... 1 8
M. Software Accomplishment Summary ................................ 1 8
2. MATERIAL INFORMATION ........................................ 1 9
A. Material - Price and Availability ................................... 1 9
B. Industry Support Information .................................... 1 9
C. Parts Necessary for Each Airplane ................................. 1 9
1. Kits/Parts ............................................ 1 9
2. Parts and Materials Supplied by the Operator ........................ 1 9
3. Parts Modified and Reidentified ................................ 1 9
4. Parts Removed and Not Replaced .............................. 1 9
D. Parts Necessary to Change Spares ................................. 1 9
E. Special Tooling - Price and Availability ............................... 1 9
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 1
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-28A1307Original 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.
ReferenceAffectedPlanning Data
Paragraph 1.E., ComplianceYesAD Related
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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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### Page 7

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.
DESCRIPTIONCONFIGURATIONGROUP
737-300/400/500 airplanes-1
Airplane Models:
737-300, 737-400, 737-500
GroupVariable Number
1PJ301 - PJ302
1PJ551 - PJ561
1PJ601 - PJ615
1PJ811
1PJ816 - PJ817
1PM381 - PM399
1PM401 - PM417
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GroupVariable Number
1PM541 - PM564
1PP001 - PP054
1PP101 - PP169
1PP181 - PP199
1PP201 - PP205
1PP221
1PP231 - PP243
1PP281 - PP286
1PP301 - PP305
1PP351 - PP353
1PP376 - PP384
1PP391 - PP393
1PP401 - PP440
1PP471 - PP475
1PP501 - PP522
1PP631 - PP634
1PP651 - PP652
1PP671 - PP699
1PP701 - PP733
1PP771 - PP779
1PP801 - PP808
1PP821 - PP827
1PP831 - PP848
1PP851 - PP852
1PP861 - PP877
1PP891 - PP899
1PP901 - PP936
1PP946 - PP948
1PP951 - PP952
1PP961 - PP967
1PP981 - PP991
1PP993
1PQ001 - PQ016
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GroupVariable Number
1PQ026 - PQ041
1PQ051 - PQ092
1PQ101 - PQ199
1PQ201 - PQ202
1PQ221 - PQ237
1PQ241 - PQ243
1PQ251 - PQ267
1PQ281 - PQ299
1PQ301 - PQ307
1PQ331 - PQ332
1PQ341 - PQ348
1PQ361 - PQ373
1PQ391 - PQ395
1PQ401 - PQ418
1PQ421
1PQ431 - PQ438
1PQ447 - PQ448
1PQ451
1PQ454
1PQ471 - PQ475
1PQ479 - PQ481
1PQ486 - PQ487
1PQ491 - PQ493
1PQ771 - PQ772
1PQ791 - PQ793
1PQ801 - PQ805
1PQ931 - PQ935
1PQ951
1PQ971 - PQ997
1PR001 - PR017
1PR021 - PR034
1PR041 - PR045
1PR061 - PR072
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GroupVariable Number
1PR077 - PR082
1PR091 - PR092
1PR096
1PR101
1PR121 - PR122
1PR131 - PR132
1PR141 - PR143
1PR161 - PR172
1PR181
1PS601 - PS631
1PS636 - PS638
1PS641 - PS644
1PS651 - PS657
1PS666 - PS669
1PS691 - PS692
1PS701 - PS706
1PS751 - PS799
1PS811
1PS836 - PS837
1PS841 - PS846
1PS851 - PS852
1PS856
1PS861 - PS863
1PS866 - PS868
1PS871 - PS874
1PS896 - PS897
1PS901 - PS941
1PS956 - PS957
1PS961 - PS963
1PS971 - PS978
1PT001 - PT015
1PT021 - PT031
1PT041 - PT064
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GroupVariable Number
1PT101 - PT105
1PT121 - PT138
1PT146 - PT148
1PT161 - PT170
1PT181 - PT188
1PT211 - PT220
1PT295
1PT301 - PT309
1PT331 - PT360
1PT381 - PT399
1PT401 - PT438
1PT501 - PT517
1PT561 - PT565
1PT581 - PT586
1PT611 - PT621
1PT641 - PT644
1PT651 - PT656
1PT671 - PT672
1PT681 - PT685
1PT701 - PT703
1PT716 - PT717
1PT721 - PT725
1PT801 - PT834
1PT851 - PT854
1PT871 - PT886
1PT901 - PT930
1PT971 - PT973
1PT981 - PT985
1PT996
1PU001 - PU025
1PU301
1PU311 - PU313
1PV001 - PV055
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GroupVariable Number
1PV201 - PV209
1PV226 - PV229
1PV231 - PV237
1PV271 - PV272
1PV281 - PV287
1PV296
1PV301 - PV302
1PV351
1PV356 - PV357
1PW001 - PW054
1PW061 - PW068
1PW072
1PW086 - PW088
1PW091 - PW094
1PW101 - PW102
1PW106
1PW111 - PW120
1PW156 - PW157
1PW161 - PW171
1PW201 - PW252
1PW261 - PW268
1PW271 - PW276
1PW278
1PW281 - PW293
1PW296
1PW301 - PW327
1PW401 - PW408
1PW411 - PW418
1PW421 - PW424
1PW431 - PW435
1PW441 - PW450
1PW461 - PW467
1PW501 - PW504
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GroupVariable Number
1PW511 - PW522
1PW524 - PW550
1PW556 - PW557
1PW561 - PW564
1PW571 - PW576
1PW591 - PW596
1PW611 - PW622
1PW631 - PW637
1PW661 - PW662
1PW681 - PW683
1PW701 - PW702
1PW711 - PW717
1PW741 - PW742
1PW761
1PW771
1PW831
1PW851 - PW856
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 .
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### Page 14

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
ZoneModel
101, 102, 305, 405737-300, 737-400, 737-500
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.
Export Controlled ECCN: 9E991 - BOEING
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### Page 15

Table 1: ENGINE NO. 1, FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Whichever Oc-
curs First)
Compliance Time
(Whichever Oc-
curs First)
ActionCondition
7,500 Flight Hours
or 24 Months
Within 7,500 Flight
Hours or 24
Months after the
original issue date
of this service bul-
letin
Do the Engine No. 1 Fuel
Suction Feed - Opera-
tional Test in accordance
with Accomplishment In-
structions, paragraph
3.B., Work Instructions,
CONFIGURATION 1,
WORKPACKAGE 1 or
Accomplishment Instruc-
tions 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 accor-
dance with Accomplish-
ment Instructions, para-
graph 3.B., Work Instruc-
tions, CONFIGURATION
1, WORKPACKAGE 1 or
Accomplishment Instruc-
tions 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 Oc-
curs First)
Compliance Time
(Whichever Oc-
curs First)
ActionCondition
7,500 Flight Hours
or 24 Months
Within 7,500 Flight
Hours or 24
Months after the
original issue date
of this service bul-
letin
Do the Engine No. 2 Fuel
Suction Feed - Opera-
tional Test in accordance
with Accomplishment In-
structions, paragraph
3.B., Work Instructions,
CONFIGURATION 1,
WORKPACKAGE 2 or
Accomplishment Instruc-
tions, paragraph 3.B.,
CONFIGURATION 2,
WORKPACKAGE 4.
Group 1
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### Page 16

Table 2: ENGINE NO. 2, FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Whichever Oc-
curs First)
Compliance Time
(Whichever Oc-
curs First)
ActionCondition
-Before Further
Flight
Isolate the cause, repair,
and repeat the Engine
No. 2 Fuel Suction Feed
- Operation Test in accor-
dance with Accomplish-
ment Instructions, para-
graph 3.B., Work Instruc-
tions, CONFIGURATION
1, WORKPACKAGE 2 or
Accomplishment Instruc-
tions, 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
Elapsed HoursTask HoursNumber of PersonsTask
1.003.003Test, Accomplishment
Instructions, para-
graph 3.B., Work In-
structions, CONFIGU-
RATION 1, WORK-
PACKAGE 1 (a)
2.006.003Test, Accomplishment
Instructions, para-
graph 3.B., Work In-
structions, CONFIGU-
RATION 2, WORK-
PACKAGE 3 (b)
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### Page 17

TABLE 1 - ENGINE NO. 1, FUEL SUCTION FEED - OPERATIONAL TEST
Elapsed HoursTask HoursNumber of PersonsTask
--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
Elapsed HoursTask HoursNumber of PersonsTask
1.003.003Test, Accomplishment
Instructions, para-
graph 3.B., Work In-
structions, CONFIGU-
RATION 1, WORK-
PACKAGE 2 (a)
2.006.003Test, Accomplishment
Instructions, para-
graph 3.B., Work In-
structions, CONFIGU-
RATION 2, WORK-
PACKAGE 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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### Page 18

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:
Chapter-SectionPublication
28-22737 Aircraft Maintenance Manual
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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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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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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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:
FUEL QUANTITYTANK
0 Lb - 2000 Lb (0 Kg- 907 Kg)CENTER TANK
1500 Lb -1700 Lb (680 Kg - 771 Kg)MAIN TANK 1 (Left)
0 Lb - 200 Lb (0 Kg - 91 Kg)AUXILIARY TANK (If Installed)
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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(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:
FUEL QUANTITYTANK
0 Lb - 2000 Lb (0 Kg- 907 Kg)CENTER TANK
1500 Lb -1700 Lb (680 Kg - 771 Kg)MAIN TANK 2 (Right)
0 Lb - 200 Lb (0 Kg - 91 Kg)AUXILIARY TANK (If Installed)
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### Page 24

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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### Page 25

(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:
FUEL QUANTITYTANK
0 Lb - 2000 Lb (0 Kg- 907 Kg)CENTER TANK
Any quantity above 1700 Lb (771 Kg) and within 1000
Lb (454 Kg) of Main Tank 2
MAIN TANK 1 (Left)
0 Lb - 200 Lb (0 Kg - 91 Kg)AUXILIARY TANK (If Installed)
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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### Page 26

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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### Page 27

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:
FUEL QUANTITYTANK
Any quantity above 200 Lb (91 Kg)CENTER TANK
1500 Lb -1700 Lb (680 Kg - 771 Kg)MAIN TANK 1 (Left)
Any quantity above 200 Lb (91 Kg)AUXILIARY TANK (If Installed)
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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### Page 28

(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:
FUEL QUANTITYTANK
0 Lb - 2000 Lb (0 Kg- 907 Kg)CENTER TANK
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### Page 29

FUEL QUANTITYTANK
Any quantity above 1700 Lb (771 Kg) and within 1,000
Lb (454 Kg) of the Main Tank 1
MAIN TANK 2 (Right)
0 Lb - 200 Lb (0 Kg - 91 Kg)AUXILIARY TANK (If Installed)
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".
Export Controlled ECCN: 9E991 - BOEING
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### Page 30

(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:
FUEL QUANTITYTANK
Any quantity above 200 Lb (91 Kg)CENTER TANK
1500 Lb -1700 Lb (680 Kg - 771 Kg)MAIN TANK 2 (Right)
Any quantity above 200 Lb (91 Kg)AUXILIARY TANK (If Installed)
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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### Page 31

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
ALERTALERT

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