# Boeing Alert Service Bulletin 747-28A2331: No revision named

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-28A2331
Original Issue: April 02, 2012
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Engine Fuel Suction Feed Operational Test
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
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Unpublished Work.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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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 4
B. Concurrent Requirements ...................................... 1 4
C. Reason ................................................ 1 4
D. Description .............................................. 1 5
E. Compliance .............................................. 1 6
F. Approval ............................................... 1 8
G. Manpower .............................................. 1 8
H. Weight and Balance Changes .................................... 1 9
I. Electrical Load Data ......................................... 1 9
J. References .............................................. 1 9
1. Existing Data: ......................................... 1 9
2. Data Supplied with this Service Bulletin: ........................... 1 9
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 9
K. Publications Affected ........................................ 1 9
L. Interchangeability and Intermixability of Parts ........................... 2 0
M. Software Accomplishment Summary ................................ 2 0
2. MATERIAL INFORMATION ........................................ 2 1
A. Material - Price and Availability ................................... 2 1
B. Industry Support Information .................................... 2 1
C. Parts Necessary for Each Airplane ................................. 2 1
1. Kits/Parts ............................................ 2 1
2. Parts and Materials Supplied by the Operator ........................ 2 1
3. Parts Modified and Reidentified ................................ 2 1
4. Parts Removed and Not Replaced .............................. 2 1
D. Parts Necessary to Change Spares ................................. 2 1
E. Special Tooling - Price and Availability ............................... 2 1
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 1
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 3
A. GENERAL INFORMATION ..................................... 2 3
B. WORK INSTRUCTIONS ....................................... 2 3
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-28A2331Original Issue: April 02, 2012
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Engine Fuel Suction Feed Operational Test
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin provides instructions to operators to perform an Engine Fuel Suction Feed Operational Test
on each engine individually. This test is required in order to protect against engine flameout during suction feed
operations. The instructions given in this service bulletin are provided to detect and correct failure of the engines
fuel suction feed of the fuel system, which could result in dual engine flameout and inability to restart the engines,
and consequent forced landing of the airplane.
Accomplishing the fuel system suction feed test and continuing to repeat the testing within the specified compliance
times will reduce the possibility of an engine flameout resulting from air ingestion into the engine fuel feed system
during low fuel level conditions with inoperative boost pumps .
An operator reported a 737-400 Engine No. 1 flameout during cruise. The Engine No. 2 continued to operate
normally. The flight crew conducted two restart attempts within the start envelope with no success then diverted
uneventfully. Another operator reported a 737-300 Engine No. 2 shut down when the start lever was placed in
the idle position during taxi to the gate. The Engine number 1 continued to operate normally. Maintenance
performed a vacuum test of the engine fuel feed system and found a crack in a fuel feed tube. The fuel feed
tube was replaced and the vacuum test of the fuel feed system was performed and passed successfully.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.E., ComplianceYesAD Related
ACTION
The WORK PACKAGES can be done in any order.
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Each engine must successfully complete the Fuel Suction Feed - Operational Test.
WORK PACKAGE 1 - ENGINE NO. 1 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 1 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test.
WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 2 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test.
WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 3 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test.
WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 4 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the test.
EFFECTIVITY
747-100/-100B/-100B SUD/-200B/200C/-200F/-300/747SP/747SR 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-356-AD, is related to
this service bulletin.
Boeing recommends that the Engine Suction Fuel Feed Operational Test given in this service bulletin be done
30,000 Flight Hours after the original issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the Operational Test given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
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MATERIAL INFORMATION
None.
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-28A2331
Original Issue: April 02, 2012
ATA System: 2822
SUBJECT: FUEL - Engine Fuel Feed System - Engine Fuel Suction Feed Operational Test
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplane(s) shown below.
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
747-100, 100B, -100 SUD, -200B, -200C, -200F, -300, 747SP and
747SR airplanes
-1
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP,
747SR
GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
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GroupVariable Number
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA731
1RA741 - RA745
1RA749 - RA750
1RA761 - RA762
1RA781 - RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
1RB101 - RB102
1RB411 - RB413
1RB421
1RB601 - RB607
1RB681 - RB697
1RB711
1RB721 - RB723
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GroupVariable Number
1RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD059
1RD071 - RD072
1RD081 - RD083
1RD091 - RD092
1RD101 - RD104
1RD121 - RD127
1RD131 - RD144
1RD166 - RD167
1RD171 - RD172
1RD181 - RD183
1RD201 - RD204
1RD221 - RD227
1RD231 - RD235
1RD241 - RD243
1RD251 - RD262
1RD271 - RD272
1RD291 - RD292
1RD301 - RD302
1RD311
1RD351 - RD358
1RD361 - RD366
1RD381 - RD383
1RD411 - RD414
1RD421 - RD426
1RD431 - RD435
1RD441 - RD442
1RD451 - RD456
1RD461
1RD471 - RD475
1RD513 - RD519
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GroupVariable Number
1RD531 - RD533
1RD551
1RD561
1RD571
1RD581 - RD583
1RD591 - RD593
1RD601 - RD607
1RD621 - RD623
1RD641 - RD649
1RD651 - RD659
1RD661
1RD671
1RD681 - RD682
1RD691 - RD692
1RD701 - RD702
1RD721 - RD722
1RD741 - RD742
1RD751 - RD755
1RD761
1RD771 - RD775
1RD781 - RD783
1RD791 - RD792
1RE001
1RG001 - RG009
1RG091
1RG095
1RG101 - RG104
1RG121 - RG126
1RG141 - RG142
1RG161 - RG164
1RG171 - RG174
1RG191 - RG193
1RG211 - RG213
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GroupVariable Number
1RG221 - RG222
1RH101 - RH102
1RH111 - RH112
1RH121 - RH122
1RJ131 - RJ133
1RJ151 - RJ152
1RJ301 - RJ303
1RJ321 - RJ322
1RJ331 - RJ333
1RR001 - RR005
1RR021 - RR025
1RR031
1RR201 - RR206
1RR221 - RR226
1RR261 - RR267
1RR301 - RR310
1RR331 - RR332
1RR336
1RR341 - RR345
1RR361 - RR362
1RR421 - RR422
1RR431 - RR432
1RR441 - RR442
1RR451
1RR501 - RR504
1RR521 - RR522
1RR526
1RR531
1RR551 - RR556
1RR561
1RR566
1RS001 - RS002
1RS201
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GroupVariable Number
1RS211 - RS212
1RS221 - RS222
1RS231 - RS241
1RS251 - RS259
1RS263
1RS265 - RS268
1RS271 - RS276
1RS291 - RS292
1RS301 - RS306
1RS311 - RS320
1RS331 - RS333
1RS341 - RS342
1RS699
1RS701 - RS703
1RS711 - RS713
1RS721 - RS722
1RS731 - RS732
1RS741 - RS743
1RS751 - RS752
1RS761 - RS762
1RS771
1RS781 - RS782
1RS786
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.
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Accomplishing the fuel system suction feed test and continuing to repeat the testing within the specified
compliance times will reduce the possibility of an engine flameout resulting from air ingestion into the
engine fuel feed system during low fuel level conditions with inoperative boost pumps .
An operator reported a 737-400 Engine No. 1 flameout during cruise. The Engine No. 2 continued to
operate normally. The flight crew conducted two restart attempts within the start envelope with no
success then diverted uneventfully. Another operator reported a 737-300 Engine No. 2 shut down when
the start lever was placed in the idle position during taxi to the gate. The Engine number 1 continued
to operate normally. Maintenance performed a vacuum test of the engine fuel feed system and found
a crack in a fuel feed tube. The fuel feed tube was replaced and the vacuum test of the fuel feed system
was performed and passed successfully.
D. Description
The work packages can be done in any order.
WORK PACKAGE 1 - ENGINE NO. 1 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 1 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the
test.
WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 2 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the
test.
WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 3 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the
test.
WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST
1. Do the Engine No. 4 - Fuel Suction Feed - Operational Test.
2. If the Fuel Suction Feed Operational Test fails isolate the cause of the leak, repair, and repeat the
test.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Affected Maintenance Zones
ZoneModel
221, 222747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C,
747-200F, 747-300, 747SP,
747SR
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2007-NM-356-AD, is
related to this service bulletin.
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Table 1: ENGINE NO. 1 - FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
30,000 flight hoursWithin 30,000 flight
hours 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,
Work Package 1.
All Airplanes
-Before Further
Flight
Isolate the cause of the
leak, repair, and repeat
the Engine Fuel Suction
Feed - Operational Test
in accordance with Ac-
complishment Instruc-
tions, paragraph 3.B.,
Work Instructions, Work
Package 1
If the Engine No. 1 Fuel
Suction Feed Operation
Test fails
Table 2: ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
30,000 flight hoursWithin 30,000 flight
hours 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,
Work Package 2.
All airplanes
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Table 2: ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before Further
Flight
Isolate the cause of the
leak, repair, and repeat
the Engine Fuel Suction
Feed - Operational Test
in accordance with Ac-
complishment Instruc-
tions, paragraph 3.B.,
Work Instructions, Work
Package 2.
If the Engine No. 2 Fuel
Suction Feed Operation
Test fails
Table 3: ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
30,000 flight hoursWithin 30,000 flight
hours after the
original issue date
of this service bul-
letin.
Do the Engine No. 3 Fuel
Suction Feed - Opera-
tional Test in accordance
with Accomplishment In-
structions, paragraph
3.B., Work Instructions,
Work Package 3.
All airplanes
-Before Further
Flight
Isolate the cause of the
leak, repair, and repeat
the Engine Fuel Suction
Feed - Operational Test
in accordance with Ac-
complishment Instruc-
tions, paragraph 3.B.,
Work Instructions, Work
Package 3.
If the Engine No. 3 Fuel
Suction Feed Operation
Test fails
Table 4: ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
30,000 flight hoursWithin 30,000 flight
hours after the
original issue date
of this service bul-
letin.
Do the Engine No. 4 Fuel
Suction Feed - Opera-
tional Test in accordance
with Accomplishment In-
structions, paragraph
3.B., Work Instructions,
Work Package 4.
All airplanes
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Table 4: ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before Further
Flight
Isolate the cause of the
leak, repair, and repeat
the Engine Fuel Suction
Feed - Operational Test
in accordance with Ac-
complishment Instruc-
tions, paragraph 3.B.,
Work Instructions, Work
Package 4.
If the Engine No. 4 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
WORK PACKAGE 1 - ENGINE NO - 1 - FUEL SUCTION FEED - OPERATIONAL TEST
Elapsed HoursTask HoursNumber of PersonsTask
1.003.003Test
Repair (a)
1.003.00TOTAL FOR ENGINE NO.1 (a)
(a) Totals given assume no repairs necessary.
WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST
Elapsed HoursTask HoursNumber of PersonsTask
1.003.003Test
Repair (a)
1.003.00TOTAL FOR ENGINE NO.2 (a)
(a) Totals given assume no repairs necessary.
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WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST
Elapsed HoursTask HoursNumber of PersonsTask
1.003.003Test
Repair (a)
1.003.00TOTAL FOR ENGINE NO.3 (a)
(a) Totals given assume no repairs necessary.
WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST
Elapsed HoursTask HoursNumber of PersonsTask
1.003.003Test
Repair (a)
1.003.00TOTAL FOR ENGINE NO.4 (a)
(a) Totals given assume no repairs necessary.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) NPRM
2007-NM-356-AD
b. Service Bulletin Index D6-30300
c. Aircraft Maintenance Manual (AMM) 747-100/200/300 AMM 28-22-00, 28-26-00, 49-11-00,
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:
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### Page 20

Chapter-SectionPublication
28-22747 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 an/or repair configuration changes given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
None.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 23

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms
2. Obey all of the warnings and cautions given in the specified manual sections
3. The work instructions are divided into work packages. Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower. You can do each work
package independently
4. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used
5. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools
6. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed
7. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
B. WORK INSTRUCTIONS
Prepare for tests.
1. Do the "Engine Ground Safety Precautions". Refer to 747-100/200/300 AMM 71-00-00
2. Do the "Power Plant Operation (Normal)". Refer to 747-100/200/300 AMM 71-00-00.
NOTE: The fuel quantity values given in the following work packages are at or below the fuel
level necessary to cover the hydraulic heat exchangers. The hydraulic system pumps
must be set to off when you operate the engines for the fuel suction feed - operational
tests. The No. 4 engine auxiliary hydraulic pump must remain on to supply pressure for
the parking brake.
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### Page 24

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. FUEL VAPORS IN THE FUEL TANK MAY IGNITE AND CAUSE A FIRE
OR AN EXPLOSION.
WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR
EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE
GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.
1. Make sure that these quantities of fuel are in the fuel tanks
FUEL QUANTITYTANK
38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)Center Tank
2,200 +/- 200 Lbs (1000 +/- 100 Kgs)Main Tank No. 1
1,600 +/- 200 Lbs (700 +/- 100 Kgs)Main Tank No. 2
No RestrictionReserve Tank No. 1 and No. 4
No RestrictionAuxiliary Tank (if installed)
NOTE: Excess fuel can be transferred to Main Tank 3 and 4. Refer to "Tank-to-Tank Fuel Transfer"
747-100/200/300 AMM 28-26-00.
2. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are open
3. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are closed
4. Make sure all Fuel boost pump switches are OFF
5. Turn on No. 1 Main Tank FWD and AFT boost pumps
6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-100/200/300
AMM 71-00-00
7. Make sure the APU is shut down by the master control switch. Refer to 747-100/200/300 AMM
49-11-00
8. After the two minute minimum warm-up period, monitor and record engine parameters:
a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow
b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow
9. Turn OFF the No. 1 Main Tank FWD and AFT boost pumps to begin the suction feed test
10. Make sure the engine continues to operate for a minimum of 5 minutes and engine parameters:
a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease
b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease
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### Page 25

c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters
N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:
(1) Turn on the No. 1 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00
(3) Isolate the cause of the leak, refer to "Engine Fuel Feed Lines / Couplings Vacuum Test"
747-100/200/300 AMM 28-22-00 and repair
(4) After repair repeat this suction feed test.
d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,
N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:
(1) Turn on the No. 1 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00
11. Do all of the remaining Work Packages
12. If this is the last Work Package, put the airplane back to a serviceable condition.
WORK PACKAGE 2 - ENGINE NO. 2 - FUEL SUCTION FEED - OPERATIONAL TEST
WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON AND
STAYS ON. FUEL VAPORS IN THE FUEL TANK MAY IGNITE AND CAUSE A FIRE
OR AN EXPLOSION.
WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR
EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE
GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.
1. Make sure that these quantities of fuel are in the fuel tanks
FUEL QUANTITYTANK
38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)Center Tank
2,200 +/- 200 Lbs (1000 +/- 100 Kgs)Main Tank No. 1
1,600 +/- 200 Lbs (700 +/- 100 Kgs)Main Tank No. 2
No RestrictionReserve Tank No. 1 and No. 4
No RestrictionAuxiliary Tank (If Installed)
NOTE: Excess fuel can be transferred to Main Tank 3 and 4. Refer to "Tank-to-Tank Fuel Transfer"
747-100/200/300 AMM 28-26-00.
2. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are open
3. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are closed
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### Page 26

4. Make sure all Fuel boost pump switches are OFF
5. Turn on No. 2 Main Tank FWD and AFT boost pump
6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-100/200/300
AMM 71-00-00
7. Make sure the APU is shut down by the master control switch. Refer to 747-100/200/300 AMM
49-11-00
8. After the two minute minimum warm-up period, monitor and record engine parameters:
a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow
b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow
9. Turn OFF the No. 2 Main Tank FWD and AFT boost pumps to begin the suction feed test
10. Make sure the engine continues to operate for a minimum of 5 minutes and engine parameters:
a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease
b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease
c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters
N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:
(1) Turn on the No. 2 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00
(3) Isolate the cause of the leak, refer to "Engine Fuel Feed Lines / Couplings Vacuum Test"
747-100/200/300 AMM 28-22-00 and repair
(4) After repair repeat this suction feed test.
d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,
N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:
(1) Turn on the No. 2 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00.
11. Do all of the remaining Work Packages
12. If this is the last Work Package, put the airplane back to a serviceable condition.
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### Page 27

WORK PACKAGE 3 - ENGINE NO. 3 - FUEL SUCTION FEED - OPERATIONAL TEST
WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON AND
STAYS ON. FUEL VAPORS IN THE FUEL TANK MAY IGNITE AND CAUSE A FIRE
OR AN EXPLOSION.
WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR
EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE
GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.
1. Make sure that these quantities of fuel are in the fuel tanks
FUEL QUANTITYTANK
38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)Center Tank
2,200 +/- 200 Lbs (1000 +/- 100 Kgs)Main Tank No. 4
1,600 +/- 200 Lbs (700 +/- 100 Kgs)Main Tank No. 3
No RestrictionReserve Tank No. 1 and No. 4
No RestrictionAuxiliary Tank (if installed)
NOTE: Excess fuel can be transferred to Main Tank 1 and 2. Refer to Tank-to-Tank Fuel Transfer"
747-100/200/300 AMM 28-26-00.
2. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are open
3. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are closed
4. Make sure all Fuel boost pump switches are OFF
5. Turn on No. 3 Main Tank FWD and AFT boost pump
6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-100/200/300
AMM 71-00-00
7. Make sure the APU is shut down by the master control switch. Refer to AMM 747-100/200/300
AMM 49-11-00
8. After the two minute minimum warm-up period, monitor and record engine parameters:
a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow
b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow
9. Turn OFF the No. 3 Main Tank FWD and AFT boost pumps to begin the suction feed test
10. Make sure the engine continues to operate for a minimum of 5 minutes and engine parameters:
a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease
b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease.
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### Page 28

c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters
N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:
(1) Turn on the No. 3 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00
(3) Isolate the cause of the leak, refer to "Engine Fuel Feed Lines / Couplings Vacuum Test"
747-100/200/300 AMM 28-22-00 and repair
(4) After repair repeat this suction feed test.
d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,
N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:
(1) Turn on the No. 3 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00
11. Do all of the remaining Work Packages
12. If this is the last Work Package, put the airplane back to a serviceable condition.
WORK PACKAGE 4 - ENGINE NO. 4 - FUEL SUCTION FEED - OPERATIONAL TEST
WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE LIGHT COMES ON AND
STAYS ON. FUEL VAPORS IN THE FUEL TANK MAY IGNITE AND CAUSE A FIRE
OR AN EXPLOSION.
WARNING: OBSERVE PROPER SAFETY PRECAUTIONS AROUND RUNNING ENGINE. WEAR
EAR PROTECTORS AND STAY CLEAR OF ENGINE HAZARD AREAS. SEE "ENGINE
GROUND SAFETY PRECAUTIONS" FOR ENGINE HAZARD DESCRIPTION.
1. Make sure that these quantities of fuel are in the fuel tanks
FUEL QUANTITYTANK
38,200 +/- 200 Lbs (17,300 +/- 200 Kgs)Center Tank
2,200 +/- 200 Lbs (1000 +/- 100 Kgs)Main Tank No. 4
1,600 +/- 200 Lbs (700 +/- 100 Kgs)Main Tank No. 3
No RestrictionReserve Tank No. 1 and No. 4
No RestrictionAuxiliary Tank (if installed)
NOTE: Excess fuel can be transferred to Main Tank 1 and 2. Refer to "Tank-to-Tank Fuel Transfer"
747-100/200/300 AMM 28-26-00.
2. Make sure the No. 1 and No. 4 engine fuel crossfeed valves are open
3. Make sure the No. 2 and No. 3 engine fuel crossfeed valves are closed
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### Page 29

4. Make sure all Fuel boost pump switches are OFF
5. Turn on No. 4 Main Tank FWD and AFT boost pump
6. Start and operate the engine at idle power for a minimum of two minutes. Refer to 747-100/200/300
AMM 71-00-00
7. Make sure the APU is shut down by the master control switch. Refer to 747-100/200/300 AMM
49-11-00
8. After the two minute minimum warm-up period, monitor and record engine parameters:
a. For Pratt and Whitney or GE engines record: N1, N2 and Fuel Flow
b. For Rolls Royce engines record: N1, N2, N3 and Fuel Flow
9. Turn OFF the No. 4 Main Tank FWD and AFT boost pumps to begin the suction feed test
10. Make sure the engine continues to operate for a minimum of 5 minutes and engine parameters:
a. For Pratt and Whitney or GE engines N1, N2 and Fuel Flow do not decrease
b. For Rolls Royce engines N1, N2, N3 and Fuel Flow do not decrease
c. If engine does not operate for the full 5 minutes or there is a decrease in engine parameters
N1, N2, N3 (Rolls Royce engines only) or a decrease in Fuel Flow, then do the following:
(1) Turn on the No. 4 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00
(3) Isolate the cause of the leak, refer to "Engine Fuel Feed Lines / Couplings Vacuum Test"
747-100/200/300 AMM 28-22-00 and repair
(4) After repair repeat this suction feed test.
d. If the engine operates for the full 5 minutes with no decrease in engine parameters N1, N2,
N3 (Rolls Royce engines only) or decrease in Fuel Flow, then do the following:
(1) Turn on the No. 4 Main Tank FWD and AFT boost pumps
(2) Shut down the engine. Refer to 747-100/200/300 AMM 71-00-00
11. Do all of the remaining Work Packages
12. If this is the last Work Package, put the airplane back to a serviceable condition.
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