# Boeing Alert Service Bulletin 757-28A0131: No revision named

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- Title as filed: U.S. DOT/FAA - Service Bulletin (Boeing)
- Pages: 30
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### Page 1

Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-28A0131
Original Issue: May 04, 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Unpublished Work.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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5.0

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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 7
A. Effectivity ................................................ 7
1. Airplanes ............................................. 7
2. Spares Affected ........................................ 1 1
B. Concurrent Requirements ...................................... 1 1
C. Reason ................................................ 1 1
D. Description .............................................. 1 1
E. Compliance .............................................. 1 2
F. Approval ............................................... 1 3
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 5
K. Publications Affected ........................................ 1 5
L. Interchangeability and Intermixability of Parts ........................... 1 5
M. Software Accomplishment Summary ................................ 1 5
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 7
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 7
E. Special Tooling - Price and Availability ............................... 1 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 1 9
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Commercial 
Airplanes
757
Service Bulletin
ALERT
SummaryNumber: 757-28A0131Original Issue: May 04, 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
757-200/-200CB/-200PF/-300 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-352-AD, is related to
this service bulletin.
Refer to Paragraph 1.E., Compliance.
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.
MATERIAL INFORMATION
None.
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Commercial 
Airplanes
757
Service Bulletin
ALERT
Number: 757-28A0131
Original Issue: May 04, 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 D624N001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplane(s) shown below.
DESCRIPTIONCONFIGURATIONGROUP
757-200/-200CB/-200PF/-300 airplanes-1
Airplane Models:
757-200, 757-200CB, 757-200PF, 757-300
GroupVariable Number
1NA001 - NA028
1NA191 - NA199
1NA201 - NA239
1NA301 - NA305
1NA341 - NA352
1NA391 - NA399
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GroupVariable Number
1NA401 - NA408
1NA441 - NA447
1NA501 - NA586
1NB001 - NB004
1NB021 - NB023
1NB036 - NB041
1NB051 - NB053
1NB061 - NB073
1NB079
1NB131 - NB148
1NB161 - NB162
1NB166 - NB168
1NB201 - NB204
1NB221 - NB228
1NB230
1NB236
1NB239
1NB261 - NB267
1NB291 - NB299
1NB301 - NB302
1NB311 - NB312
1NB321 - NB331
1NB421 - NB438
1NB446
1NB451 - NB454
1NB501 - NB523
1NB561
1NB571
1NB581 - NB583
1NC001 - NC033
1NC041 - NC042
1NC051 - NC052
1NC056 - NC062
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GroupVariable Number
1NC066 - NC084
1NC091 - NC094
1NC151
1NC161
1NC901 - NC951
1NC971 - NC974
1ND001 - ND007
1ND011 - ND059
1ND111 - ND113
1ND161 - ND199
1ND201 - ND203
1ND221 - ND225
1ND241 - ND248
1ND301 - ND322
1ND401
1ND891
1ND895
1NE001 - NE008
1NE011 - NE088
1NE091 - NE094
1NE141 - NE150
1NE161 - NE177
1NE201 - NE204
1NE301 - NE302
1NE311 - NE325
1NJ001 - NJ004
1NJ031 - NJ032
1NJ551 - NJ555
1NL001 - NL002
1NL006 - NL017
1NL101 - NL109
1NL141
1NL601 - NL616
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GroupVariable Number
1NN001 - NN002
1NN051 - NN052
1NP901 - NP904
1NS601 - NS616
1NT001 - NT009
1NT201 - NT202
1NT231 - NT234
1NT237 - NT240
1NT242
1NT245 - NT248
1NT281 - NT289
1NT341 - NT347
1NT351 - NT360
1NT371 - NT373
1NT375 - NT379
1NT381 - NT386
1NT401 - NT409
1NT411 - NT412
1NT426 - NT427
1NT431 - NT432
1NT436 - NT438
1NT441 - NT442
1NT446
1NT701 - NT769
1NT791 - NT796
1NT861 - NT862
1NT881 - NT885
1NT901 - NT916
1NT971 - NT985
1NU031 - NU038
1NU701 - NU705
1NU721 - NU728
1NU731 - NU732
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2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin provides instructions to operators to perform an Engine Fuel Suction Feed
Operational Test on each engine individually. This test is required in order to protect against engine
flameout during suction feed operations. The instructions given in this service bulletin are provided to
detect and correct failure of the engines fuel suction feed of the fuel system, which could result in dual
engine flameout and inability to restart the engines, and consequent forced landing of the airplane.
Accomplishing the fuel system suction feed test and continuing to repeat the testing within the specified
compliance times will reduce the possibility of an engine flameout resulting from air ingestion into the
engine fuel feed system during low fuel level conditions with inoperative boost pumps .
An Operator reported a 737-400 Engine No. 1 flameout during cruise. The Engine No. 2 continued to
operate normally. The flight crew conducted two restart attempts within the start envelope with no
success then diverted uneventfully. Another Operator reported a 737-300 Engine No. 2 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.
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.
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Affected Maintenance Zones
ZoneModel
211, 212757-200, 757-200CB, 757-
200PF, 757-300
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-352-AD, is
related to this service bulletin.
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 36 Months
Within 7,500 Flight
Hours or 36
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., CONFIGURATION
1, WORKPACKAGE 1 or
Accomplishment Instruc-
tions, paragraph 3.B.,
CONFIGURATION 2,
WORKPACKAGE 3.
All Airplanes
-Before Further
Flight
Isolate the cause, repair,
and repeat the Engine
Fuel Suction Feed Opera-
tion Test in accordance
with Accomplishment In-
structions, paragraph
3.B., 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
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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 36 Months
Within 7,500 Flight
Hours or 36
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., CONFIGURATION
1, WORKPACKAGE 2 or
Accomplishment Instruc-
tions, paragraph 3.B.,
CONFIGURATION 2,
WORKPACKAGE 4.
All Airplanes
-Before Further
Flight
Isolate the cause, repair,
and repeat the Engine
Fuel Suction Feed Opera-
tion Test in accordance
with Accomplishment In-
structions, paragraph
3.B., 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.
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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)
--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.
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H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Letter 757-SL-51-022
b. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)
2007-NM-352-AD
c. Service Bulletin Index D624N001
d. 757 Aircraft Maintenance Manual (AMM) 28-22-00, 71-00-00
e. 757 Fault Isolation Manual (FIM) 28-22 FAULT TREE 818
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
28-22757 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
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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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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. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. 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.
6. Boeing Service Letter 757-SL-51-022, 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.
7. 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.
8. 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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### Page 20

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 757 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 - 6000 Lb (0 Kg - 2720 Kg)CENTER TANK
2200 Lb -2600 Lb (1000 Kg - 1180 Kg)MAIN TANK 1 (Left)
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, transfer the excess fuel to Main Tank 2 (Right) 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 757
AMM 28-26-00 - "Pressure Defueling" as an accepted procedure. To transfer
fuel refer to 757 AMM 28-26-00 - "Tank to Tank Transfer" as an accepted
procedure. To add fuel refer to 757 AMM 12-11-01 - "Pressure Refuel Operation"
as an accepted procedure.
(2) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before the
test.
(3) For Airplanes with Single System Valve Actuators:
(a) The CROSSFEED VALVE switch-light, on the Fuel Management Panel (P5 Overhead
Panel), is in the OFF position.
(4) For Airplanes with Dual System Valve Actuators:
(a) The FUEL XFEED VALVE - FWD switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
(b) The FUEL XFEED VALVE - AFT switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
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### Page 21

(5) The APU Master Control Switch on the P5 overhead panel, is in the OFF position.
NOTE: APU may be used to start the engine, but make sure that APU Master Control
Switch is in the OFF position during the test.
(6) With the two left fuel boost pumps ON, operate Engine No. 1 at idle power for a minimum
of two (2.0) minutes. Make a record of the engine parameters:
(a) For Pratt and Whitney engines record: N1, N2, and Fuel Flow.
(b) For Rolls Royce engines record: N1, N2, N3, and Fuel Flow.
(7) With the two left fuel boost pumps OFF, make sure that the Engine No. 1 continues to
operate for a minimum of five (5.0) minutes and:
(a) For Pratt and Whitney engines the engine parameters: N1, N2, or Fuel Flow do not
decrease.
(b) For Rolls Royce engines the engine parameters: N1, N2, N3, or 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,
N3 (Rolls Royce engines only), or Fuel Flow, then do the following:
(1) Set the two left fuel boost pumps switches on P5 overhead panel to the ON position.
(2) Shut down the engine. Refer to 757 AMM 71-00-00 as an accepted procedure.
(3) Isolate the cause, repair, and repeat the "Engine Fuel Suction Feed - Operational Test".
To troubleshoot refer to 757 FIM 28-22 FAULT TREE 818, "Right (Left) Engine Fails the
Suction Feed Test" as an accepted procedure.
c. If the engine operates for the full five (5.0) minutes with no decrease in N1, N2, N3 (Rolls
Royce engines only), or Fuel Flow, then do the following:
(1) Set the two left fuel boost pumps switches on P5 overhead panel to the ON position.
(2) Shut down the engine No. 1. Refer to 757 AMM 71-00-00 as an accepted procedure.
(3) Put the airplane back to serviceable condition.
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PROPRIETARY - Copyright © Unpublished
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### Page 22

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 757 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 - 6000 Lb (0 Kg - 2720 Kg)CENTER TANK
2200 Lb -2600 Lb (1000 Kg - 1180 Kg)MAIN TANK 2 (Right)
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, transfer the excess fuel to Main Tank 1 (Left) 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 757
AMM 28-26-00 - "Pressure Defueling" as an accepted procedure. To transfer
fuel refer to 757 AMM 28-26-00 - "Tank to Tank Transfer" as an accepted
procedure. To add fuel refer to 757 AMM 12-11-01 - "Pressure Refuel Operation"
as an accepted procedure.
(2) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before the
test.
(3) For Airplanes with Single System Valve Actuators:
(a) The CROSSFEED VALVE switch-light, on the Fuel Management Panel (P5 Overhead
Panel), is in the OFF position.
(4) For Airplanes with Dual System Valve Actuators:
(a) The FUEL XFEED VALVE - FWD switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
(b) The FUEL XFEED VALVE - AFT switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
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### Page 23

(5) The APU Master Control Switch on the P5 overhead panel, is in the OFF position.
NOTE: APU may be used to start the engine, but make sure that APU Master Control
Switch is in the OFF position during the test.
(6) With the two right fuel boost pumps ON, operate Engine No. 2 at idle power for a minimum
of two (2.0) minutes. Make a record of the engine parameters:
(a) For Pratt and Whitney engines record: N1, N2, and Fuel Flow.
(b) For Rolls Royce engines record: N1, N2, N3, and Fuel Flow.
(7) With the two right fuel boost pumps OFF, make sure that the Engine No. 2 continues to
operate for a minimum of five (5.0) minutes and:
(a) For Pratt and Whitney engines the engine parameters: N1, N2, or Fuel Flow do not
decrease.
(b) For Rolls Royce engines the engine parameters: N1, N2, N3, or Fuel Flow do not
decrease.
b. If the engine does not operate for the full five (5) minutes or there is a decrease in N1, N2,
N3 (Rolls Royce engines only), or Fuel Flow, then do the following:
(1) Set the two right fuel boost pumps switches on P5 overhead panel to the ON position.
(2) Shut down the engine. Refer to 757 AMM 71-00-00 as an accepted procedure.
(3) Isolate the cause, repair, and repeat the "Engine Fuel Suction Feed - Operational Test".
To troubleshoot refer to 757 FIM 28-22 FAULT TREE 818, "Right (Left) Engine Fails the
Suction Feed Test" as an accepted procedure.
c. If the engine operates for the full five (5.0) minutes with no decrease in N1, N2, N3 (Rolls
Royce engines only), or Fuel Flow, then do the following:
(1) Set the two right fuel boost pumps switches on P5 overhead panel to the ON position.
(2) Shut down the Engine No. 2. Refer to 757 AMM 71-00-00 as an accepted 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 does 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.
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### Page 24

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 757 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 - 6000 Lb (0 Kg - 2720 Kg)CENTER TANK
Any quantity above 2600 Lb (1180 Kg) and within 1000
Lb (454 Kg) of Main Tank 2
MAIN TANK 1 (Left)
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, transfer the excess fuel Main Tank 2 (Right) or remove fuel
from the fuel tanks. To remove fuel refer to 757 AMM 28-26-00 - "Pressure
Defueling" as an accepted procedure. To transfer fuel refer to 757 AMM
28-26-00 - "Tank to Tank Transfer" as an accepted procedure. To add fuel
refer to 757 AMM 12-11-01 - "Pressure Refuel Operation" as an accepted
procedure.
(b) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before
the test.
(c) For Airplanes with Single System Valve Actuators:
1) The CROSSFEED VALVE switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
(d) For Airplanes with Dual System Valve Actuators:
1) The FUEL XFEED VALVE - FWD switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
2) The FUEL XFEED VALVE - AFT switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
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### Page 25

(e) The APU Master Control switch on the P5 overhead panel, is in the OFF position.
NOTE: APU may be used to start the engine, but make sure that APU Master
Control Switch is in the OFF position during the test.
(f) With the two left fuel boost pumps ON, operate Engine No. 1 at idle power for a
minimum of two (2.0) minutes. Make a record of the engine parameters:
1) For Pratt and Whitney engines record: N1, N2, and Fuel Flow.
2) For Rolls Royce engines record: N1, N2, N3, and Fuel Flow.
(g) With the two left fuel boost pumps OFF, make sure that the Engine No. 1 continues
to operate for a minimum of five (5.0) minutes and:
1) For Pratt and Whitney engines the engine parameters: N1, N2, or Fuel Flow do
not decrease.
2) For Rolls Royce engines the engine parameters: N1, N2, N3, or Fuel Flow do
not decrease.
(2) If the engine does not operate for the full five (5) minutes or there is a decrease in N1,
N2, N3 (Rolls Royce engines only), or Fuel Flow, then do the following:
(a) Set the two left fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine. Refer to 757 AMM 71-00-00 as an accepted procedure.
(c) Isolate the cause, repair, and repeat the "Engine Fuel Suction Feed - Operational
Test". To troubleshoot refer to 757 FIM 28-22 FAULT TREE 818, "Right (Left) Engine
Fails the Suction Feed Test" as an accepted procedure.
(3) If the engine operates for the full five (5) minutes with no decrease in N1, N2, N3 (Rolls
Royce engines only), or Fuel Flow, then do the following:
(a) Set the two left fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine No. 1. Refer to 757 AMM 71-00-00 as an accepted procedure.
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 757 AMM 28-22-00 as
an accepted procedure. During the Test you must meet the following requirements:
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### Page 26

(a) Make sure these quantities of fuel are in the fuel tanks:
FUEL QUANTITYTANK
Any quantity above 200 Lb (91 Kg)CENTER TANK
2200 Lb -2600 Lb (1000 Kg - 1180 Kg)MAIN TANK 1 (Left)
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 Main Tank 1 (Left) than recommended, transfer
the excess fuel to Main Tank 2 (Right) or Center Tank or remove fuel from
the fuel tanks. To remove fuel refer to 757 AMM 28-26-00 - "Pressure
Defueling" as an accepted procedure. To transfer fuel refer to 757 AMM
28-26-00 - "Tank to Tank Transfer" as an accepted procedure. To add fuel
refer to 757 AMM 12-11-01 - "Pressure Refuel Operation" as an accepted
procedure.
(b) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before
the test.
(c) For Airplanes with Single System Valve Actuators:
1) The CROSSFEED VALVE switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
(d) For Airplanes with Dual System Valve Actuators:
1) The FUEL XFEED VALVE - FWD switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
2) The FUEL XFEED VALVE - AFT switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
(e) The APU Master Control Switch on the P5 overhead panel, is in the OFF position.
NOTE: APU may be used to start the engine, but make sure that APU Master
Control Switch is in the OFF position during the test.
(f) With the two left fuel boost pumps ON, operate Engine No. 1 at idle power for a
minimum of two (2.0) minutes. Make a record of the engine parameters:
1) For Pratt and Whitney engines record: N1, N2, and Fuel Flow.
2) For Rolls Royce engines record: N1, N2, N3, and Fuel Flow.
(g) With the two left fuel boost pumps OFF, make sure that the Engine No. 1 continues
to operate for a minimum of five (5.0) minutes and:
1) For Pratt and Whitney engines the engine parameters: N1, N2, or Fuel Flow do
not decrease.
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### Page 27

2) For Rolls Royce engines the engine parameters: N1, N2, N3, or Fuel Flow do
not decrease.
(2) If the engine does not operate for the full five (5) minutes or there is a decrease in N1,
N2, N3 (Rolls Royce engines only), or Fuel Flow, then do the following:
(a) Set the two left fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine. Refer to 757 AMM 71-00-00 as an accepted procedure.
(c) Isolate the cause, repair, and repeat the "Engine Fuel Suction Feed - Operational
Test". To troubleshoot refer to 757 FIM 28-22 FAULT TREE 818, "Right (Left) Engine
Fails the Suction Feed Test" as an accepted procedure.
(3) If the engine operates for the full five (5) minutes with no decrease in N1, N2, N3 (Rolls
Royce engines only), or Fuel Flow, then do the following:
(a) Set the two left fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine No. 1. Refer to 757 AMM 71-00-00 as an accepted 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 757 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 - 6000 Lb (0 Kg - 2720 Kg)CENTER TANK
Any quantity above 2600 Lb (1180 Kg) and within 1000
Lb (454 Kg) of Main Tank 1
MAIN TANK 2 (Right)
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 28

NOTE: If there is more fuel in the Center Tank and/or Main Tank 2 (Right) than
recommended, transfer the excess fuel to Main Tank 1 (Left) or remove
fuel from the fuel tanks. To remove fuel refer to 757 AMM 28-26-00 -
"Pressure Defueling" as an accepted procedure. To transfer fuel refer to
757 AMM 28-26-00 - "Tank to Tank Transfer" as an accepted procedure.
To add fuel refer to 757 AMM 12-11-01 - "Pressure Refuel Operation" as
an accepted procedure.
(b) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before
the test.
(c) For Airplanes with Single System Valve Actuators:
1) The CROSSFEED VALVE switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
(d) For Airplanes with Dual System Valve Actuators:
1) The FUEL XFEED VALVE - FWD switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
2) The FUEL XFEED VALVE - AFT switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
(e) Make sure the APU Master Control switch on the P5 overhead panel, is in the OFF
position.
NOTE: APU may be used to start the engine, but make sure that APU Master
Control Switch is in the OFF position during the test.
(f) With the two right fuel boost pumps ON, operate Engine No. 2 at idle power for a
minimum of two (2.0) minutes. Make a record of the engine parameters:
1) For Pratt and Whitney engines record: N1, N2, and Fuel Flow.
2) For Rolls Royce engines record: N1, N2, N3, and Fuel Flow.
(g) With the two right fuel boost pumps OFF, make sure that the Engine No. 2 continues
to operate for a minimum of five (5.0) minutes and:
1) For Pratt and Whitney engines the engine parameters: N1, N2, or Fuel Flow do
not decrease.
2) For Rolls Royce engines the engine parameters: N1, N2, N3, or 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, N3 (Rolls Royce engines only), or Fuel Flow, then do the following:
(a) Set the two right fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine.
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### Page 29

(c) Isolate the cause, repair, and repeat the "Engine Fuel Suction Feed - Operational
Test". To troubleshoot refer to 757 FIM 28-22 FAULT TREE 818, "Right (Left) Engine
Fails the Suction Feed Test" as an accepted procedure.
(3) If the engine operates for the full five (5) minutes with no decrease in N1, N2, N3 (Rolls
Royce engines only), or Fuel Flow, then do the following:
(a) Set the two right fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine No. 2. Refer to 757 AMM 71-00-00 as an accepted 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 757 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
2200 Lb -2600 Lb (1000 Kg - 1180 Kg)MAIN TANK 2 (Right)
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 Main Tank 2 (Right) than recommended, transfer the
excess fuel to Main Tank 1 (Left) or Center Tank or remove fuel from the
fuel tanks. To remove fuel refer to 757 AMM 28-26-00 - "Pressure Defueling"
as an accepted procedure. To transfer fuel refer to 757 AMM 28-26-00 -
"Tank to Tank Transfer" as an accepted procedure. To add fuel refer to 757
AMM 12-11-01 - "Pressure Refuel Operation" as an accepted procedure.
(b) All fuel boost pump switches on P5 Overhead Panel are in the OFF position before
the test.
(c) For Airplanes with Single System Valve Actuators:
1) The CROSSFEED VALVE switch-light, on the Fuel Management Panel (P5
Overhead Panel), is in the OFF position.
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### Page 30

(d) For Airplanes with Dual System Valve Actuators:
1) The FUEL XFEED VALVE - FWD switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
2) The FUEL XFEED VALVE - AFT switch-light, on the Fuel Management Panel
(P5 Overhead Panel), is in the OFF position.
(e) The APU Master Control Switch on the P5 overhead panel, is in the OFF position.
NOTE: APU may be used to start the engine, but make sure that APU Master
Control Switch is in the OFF position during the test.
(f) With the two right fuel boost pumps ON, operate Engine No. 2 at idle power for a
minimum of two (2.0) minutes. Make a record of the engine parameters:
1) For Pratt and Whitney engines record: N1, N2, and Fuel Flow.
2) For Rolls Royce engines record: N1, N2, N3, and Fuel Flow.
(g) With the two right fuel boost pumps OFF, make sure that the Engine No. 2 continues
to operate for a minimum of five (5.0) minutes and:
1) For Pratt and Whitney engines the engine parameters: N1, N2, or Fuel Flow do
not decrease.
2) For Rolls Royce engines the engine parameters: N1, N2, N3, or Fuel Flow do
not decrease.
(2) If the engine does not operate for the full five (5) minutes or there is a decrease in N1,
N2, N3 (Rolls Royce engines only), or Fuel Flow, then do the following:
(a) Set the two right fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine. Refer to 757 AMM 71-00-00 as an accepted procedure.
(c) Isolate the cause, repair, and repeat the "Engine Fuel Suction Feed - Operational
Test". To troubleshoot refer to 757 FIM 28-22 FAULT TREE 818, "Right (Left) Engine
Fails the Suction Feed Test" as an accepted procedure.
(3) If the engine operates for the full five (5) minutes with no decrease in N1, N2, N3 (Rolls
Royce engines only), or Fuel Flow, then do the following:
(a) Set the two right fuel boost pumps switches on P5 overhead panel to the ON position.
(b) Shut down the engine No. 2. Refer to 757 AMM 71-00-00 as an accepted 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 04, 2012
757-28A0131
30 of 30
BOEING SERVICE BULLETIN 757-28A0131
ALERTALERT

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