# Boeing Alert Service Bulletin 737-54A1044: Revision 2

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2010-0855; AD 2011-01-12 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-54A1044](https://openairdocs.org/service-documents/boeing/737-54a1044.md)
- Title as filed: U.S. DOT/FAA - Service Information
- Pages: 57
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## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-54A1044
Original Issue: December 10, 2007
Revision 2: January 20, 2010
ATA System: 5410
SUBJECT: NACELLES/PYLONS - Nacelle Strut - Midspar Fuse Pin - Inspection, Repair and
Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 © 2007 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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 the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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6.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 7
B. Concurrent Requirements ...................................... 1 7
C. Reason ................................................ 1 7
D. Description .............................................. 1 8
E. Compliance .............................................. 1 9
F. Approval ............................................... 2 7
G. Manpower .............................................. 2 8
H. Weight and Balance Changes .................................... 2 8
I. Electrical Load Data ......................................... 2 8
J. References .............................................. 2 9
1. Existing Data: ......................................... 2 9
2. Data supplied with this Service Bulletin: ........................... 2 9
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 9
K. Publications Affected ........................................ 2 9
L. Interchangeability and Intermixability of Parts ........................... 2 9
2. MATERIAL INFORMATION ........................................ 3 1
A. Material - Price and Availability ................................... 3 1
B. Industry Support Information .................................... 3 1
C. Parts Necessary For Each Airplane ................................. 3 1
1. Kits/Parts: ........................................... 3 1
2. Parts and Materials Supplied by the Operator: ........................ 3 1
3. Parts Modified and Reidentified: ............................... 3 1
4. Parts Removed and Not Replaced: .............................. 3 2
D. Parts Necessary to Change Spares ................................. 3 2
E. Special Tooling - Price and Availability ............................... 3 2
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 2
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 3
A. GENERAL INFORMATION ..................................... 3 3
B. WORK INSTRUCTIONS ....................................... 3 3
FIGURE 1: LEFT SIDE ENGINE STRUT - INBOARD AND OUTBOARD - MIDSPAR FUSE PIN -
INSPECTION .......................................... 4 1
FIGURE 2: RIGHT SIDE ENGINE STRUT - INBOARD AND OUTBOARD - MIDSPAR FUSE PIN -
INSPECTION .......................................... 4 3
FIGURE 3: MIDSPAR FUSE PIN - REPAIR ................................ 4 5
FIGURE 4: LEFT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN ..................................... 4 6
FIGURE 5: LEFT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN ..................................... 4 9
FIGURE 6: RIGHT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN ..................................... 5 2
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FIGURE 7: RIGHT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN ..................................... 5 5
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 737-54A1044Original Issue: December 10, 2007
Revision 2: January 20, 2010
ATA System: 5410
SUBJECT: NACELLES/PYLONS - Nacelle Strut - Midspar Fuse Pin - Inspection, Repair and
Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-21-03, is related to this service bulletin.
No more work is necessary on airplanes changed as shown in Revision 1 of this service bulletin.
REASON FOR REVISION
This revision is sent to change the compliance table number referenced in the second paragraph in Section F.
Approval, from Table 7 to Table 1.
These sections were changed:
1. Paragraph 1.E., Compliance: added that AD 2008-21-03 is related to this service bulletin.
2. Paragraph 1.F., Approval: revised Table 7 to Table 1 and added "or revision 2", in the AMOC paragraph.
3. Paragraph 1.K., Publications Affected: added the damage tolerance statement that was at the bottom of
the compliance table.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
December 10, 2007Original Issue:
November 26, 2008Revision 1:
January 20, 2010Revision 2:
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ALERTALERT
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-54A1044Original Issue: December 10, 2007
Revision 2: January 20, 2010
ATA System: 5410
SUBJECT: NACELLES/PYLONS - Nacelle Strut - Midspar Fuse Pin - Inspection, Repair and
Replacement
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 gives instructions to replace or to inspect the left and right side engine strut, inboard and
outboard midspar fuse pins for any cracking, pitting, corrosion and chrome plate damage. If the work given in
this service bulletin is not accomplished, damage to the midspar fuse pins may go undetected. Undetected
damage could result in the loss of structural integrity of the midspar fuse pins and cause an engine breakaway
from the airplane.
One operator found one 737-300 airplane with all four engine strut midspar fuse pins with corrosion damage.
One of the midspar fuse pins had corrosion common to the chrome run out on the head side. Also, a large
portion of the chrome plate was missing from the corroded area of the shank. The airplane had a total of 28,621
flight cycles.
Boeing Service Related Problem (SRP) 737-SRP-54-0115 is related to this service bulletin.
ACTION (PRR 35005-273RS)
Identify the part numbers of the left and right side engine strut, inboard and outboard midspar fuse pins.
Remove 311A1092-2 midspar fuse pins and install 311A1092-3 midspar fuse pins.
Alternatively, for a limited time, do a detailed inspection of 311A1092-2 midspar fuse pins for any cracking,
pitting, corrosion or chrome plate damage. If damage is found, discard or repair the damaged midspar fuse pins.
Install new or serviceable midspar fuse pins and do the repeat inspection at the specified interval.
EFFECTIVITY
All 737-300, -400, -500 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.
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COMPLIANCE
Refer to Paragraph 1.E., Compliance.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-21-03 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
IDENTIFY THE LEFT AND RIGHT SIDE, INBOARD AND OUTBOARD MIDSPAR
FUSE PINS.
REPLACE ALL OLD MATERIAL FUSE PINS WITH NEW MATERIAL FUSE PINS.
ALTERNATIVELY, FOR A LIMITED TIME, DO A DETAILED INSPECTION OF THE
MIDSPAR FUSE PINS FOR ANY CRACKING, PITTING, CORROSION OR CHROME
PLATE DAMAGE. IF DAMAGE IS FOUND, DISCARD OR REPAIR THE DAMAGED  MIDSPAR FUSE PINS. INSTALL NEW OR SERVICEABLE MIDSPAR FUSE PINS.  1544673
Original Issue: December 10, 2007
Revision 2: January 20, 2010  737-54A1044
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737-54A1044Revision 2: January 20, 2010
10 of 57
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ALERTALERT
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Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-54A1044
Original Issue: December 10, 2007
Revision 2: January 20, 2010
ATA System: 5410
SUBJECT: NACELLES/PYLONS - Nacelle Strut - Midspar Fuse Pin - Inspection, Repair and
Replacement
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 airplanes shown below. Refer to PRR 35005-273RS for data about
this change.
Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
All 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
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GroupVariable Number
1PM381 - PM399
1PM401 - PM417
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
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GroupVariable Number
1PP993
1PQ001 - PQ016
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
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GroupVariable Number
1PR041 - PR045
1PR061 - PR072
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
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GroupVariable Number
1PT021 - PT031
1PT041 - PT064
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
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GroupVariable Number
1PU311 - PU313
1PV001 - PV055
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
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GroupVariable Number
1PW461 - PW467
1PW501 - PW504
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 gives instructions to replace or to inspect the left and right side engine strut, inboard
and outboard midspar fuse pins for any cracking, pitting, corrosion and chrome plate damage. If the
work given in this service bulletin is not accomplished, damage to the midspar fuse pins may go
undetected. Undetected damage could result in the loss of structural integrity of the midspar fuse pins
and cause an engine breakaway from the airplane.
One operator found one 737-300 airplane with all four engine strut midspar fuse pins with corrosion
damage. One of the midspar fuse pins had corrosion common to the chrome run out on the head side.
Also, a large portion of the chrome plate was missing from the corroded area of the shank. The airplane
had a total of 28,621 flight cycles.
BOEING PROPRIETARY -
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Original Issue: December 10, 2007
737-54A1044Revision 2: January 20, 2010
17 of 57
BOEING SERVICE BULLETIN 737-54A1044
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Boeing Service Related Problem (SRP) 737-SRP-54-0115 is related to this service bulletin.
Revision 1 is sent to add new replacement midspar fuse pins. The 311A1092-3 midspar fuse pins are
manufactured from 15-5PH CRES material and do not require repeat inspections. Refer to Paragraph
1.E., Compliance.
These sections were changed:
1. Paragraph 1.C., Reason: Information is added for the installation of the new material midspar fuse
pins.
2. Paragraph 1.D., Description: Information is added for the installation of the new material midspar
fuse pins.
3. Paragraph 1.E., Compliance: Information is added for the installation of the new material midspar
fuse pins and the termination of repeat inspections.
4. Paragraph 1.J., References: Boeing CMM 54-50-01 and 737-300/400/500 SRM Chapter 51 are
added to Existing Data.
5. Paragraph 2.K., Publications Affected: Boeing CMM 54-50-01 is added.
6. Paragraph 2.C., Parts Necessary for Each Airplane: A new replacement midspar fuse pin is added
to Parts and Materials Supplied by the Operator.
7. Paragraph 3.B., Work Instructions: Instructions are added for the installation of the new material
midspar fuse pins.
8. Figures 4 to 7: These figures are added to install the new material midspar fuse pins.
Revision 2 is sent to change the compliance table number referenced in the second paragraph in
Section F. Approval, from Table 7 to Table 1.
These sections were changed:
1. Paragraph 1.E., Compliance: added that AD 2008-21-03 is related to this service bulletin.
2. Paragraph 1.F., Approval: revised Table 7 to Table 1 and added "or revision 2", in the AMOC
paragraph.
3. Paragraph 1.K., Publications Affected: added the damage tolerance statement that was at the
bottom of the compliance table.
D. Description
Identify the part numbers of the left and right side engine strut, inboard and outboard midspar fuse
pins.
Remove 311A1092-2 midspar fuse pins and install 311A1092-3 midspar fuse pins.
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
737-54A1044Revision 2: January 20, 2010
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BOEING SERVICE BULLETIN 737-54A1044
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### Page 19

Alternatively, for a limited time, do a detailed inspection of 311A1092-2 midspar fuse pins for any
cracking, pitting, corrosion or chrome plate damage. If damage is found, discard or repair the damaged
midspar fuse pins. Install new or serviceable midspar fuse pins and do the repeat inspection at the
specified interval.
Revision 1 - More work is necessary on airplanes changed as shown in the original issue of this service
bulletin. Installation of 311A1092-3 midspar fuse pins is required after the specified time.
Revision 2 - No more work is necessary on airplanes changed in accordance with Revision 1 of this
service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
507, 607737-300, 737-400, 737-500
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-21-03 is related to this service
bulletin.
Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
----No action is required.Airplanes
with all en-
gine strut
midspar fuse
pins with part
number
311A1092-3.
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Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
---Within 120
months after
the date on
Revision 1 of
this service
bulletin.
On the left side engine strut: Install a
new inboard midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraphs 3.B.1.a.(2)(a) See
note (a)
Airplanes
with engine
strut midspar
fuse pins
with part
number
311A1092-2. On the left side engine strut: Install anew outboard midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraphs 3.B.2.a.(2)(a) See
note (a)
On the right side engine strut: Install a
new inboard midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraphs 3.B.3.a.(2)(a) See
note (a)
On the right side engine strut: Install a
new outboard midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraphs 3.B.4.a.(2)(a) See
note (a)
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Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
60 months.
See note
(b)
Within 24
months after
the date on
this service
bulletin.
Within 180
months from
date of previ-
ous pin re-
placement.
Within 180
months from
the date of is-
suance of
original stan-
dard certificate
of airworthi-
ness or origi-
nal export cer-
tificate of air-
worthiness.
On the left side engine strut: Do a de-
tailed inspection of the inboard midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.1.a.(2)(b)2) See notes (a) (b)
Airplanes
with engine
strut midspar
fuse pins
with part
number
311A1092-2. On the left side engine strut: Do a de-tailed inspection of the outboard
midspar fuse pin in accordance with
the Accomplishment Instructions para-
graph 3.B.2.a.(2)(b)2) See notes (a)
(b)
On the right side engine strut: Do a
detailed inspection of the inboard
midspar fuse pin in accordance with
the Accomplishment Instructions para-
graph 3.B.3.a.(2)(b)2) See notes (a)
(b)
On the right side engine strut: Do a
detailed inspection of the outboard
midspar fuse pin in accordance with
the Accomplishment Instructions para-
graph 3.B.4.a.(2)(b)2) See notes (a)
(b)
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Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
---Before further
flight.
On the left side engine strut inboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.1.a.(2)(b)3) See note (b)
If any crack
is found.
On the left side engine strut outboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.2.a.(2)(b)3) See note (b)
On the right side engine strut inboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.3.a.(2)(b)3) See note (b)
On the right side engine strut outboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.4.a.(2)(b)3) See note (b)
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Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
---Before further
flight
On the left side engine strut inboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.1.a.(2)(b)3) See note (b)
If any pitting
or corrosion
damage is
found in the
inner bore,
threads, or
under the
chromed
area.
On the left side engine strut outboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.2.a.(2)(b)3) See note (b)
On the right side engine strut inboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.3.a.(2)(b)3) See note (b)
On the right side engine strut outboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.4.a.(2)(b)3) See note (b)
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### Page 24

Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
---Before further
flight.
On the left side engine strut inboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.1.a.(2)(b)3) See note (b)
If any pitting
or corrosion
damage is
found not
common to
the inner
bore,
threads, or
under the
chromed
area and re-
quires a
blend depth
more than
0.010 inch.
On the left side engine strut outboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.2.a.(2)(b)3) See note (b)
On the right side engine strut inboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.3.a.(2)(b)3) See note (b)
On the right side engine strut outboard
midspar fuse pin: If the pin is damaged
install a new or serviceable midspar
fuse pin in accordance with the Accom-
plishment Instructions paragraph
3.B.4.a.(2)(b)3) See note (b)
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Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
---Before further
flight.
On the left side engine strut inboard
midspar fuse pin:
If any pitting
or corrosion
damage is
found not
common to
the inner
bore,
threads, or
under the
chromed
area and re-
quires a
blend depth
less than or
equal to
0.010 inch.
If the fuse pin is damaged, repair in
accordance with Accomplishment In-
structions paragraph
3.B.1.a.(2)(b)2)d){1} and install the
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.1.a.(2)(b)3)
Or
If the pin is damaged install a new or
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.1.a.(2)(b)3) See
note (b)
On the left side engine strut outboard
midspar fuse pin:
If the fuse pin is damaged, repair in
accordance with Accomplishment In-
structions paragraph
3.B.2.a.(2)(b)2)d){1}  and install the
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.2.a.(2)(b)3)
Or
If the pin is damaged install a new or
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.2.a.(2)(b)3) See
note (b)
On the right side engine strut inboard
midspar fuse pin:
If the fuse pin is damaged, repair in
accordance with Accomplishment In-
structions paragraph
3.B.3.a.(2)(b)2)d){1}  and install the
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.3.a.(2)(b)3)
Or
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Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
If the pin is damaged install a new or
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.3.a.(2)(b)3) See
note (b)
On the right side engine strut outboard
midspar fuse pin:
If the fuse pin is damaged, repair in
accordance with Accomplishment In-
structions paragraph
3.B.4.a.(2)(b)2)d){1}  and install the
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.4.a.(2)(b)3)
Or
If the pin is damaged install a new or
serviceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.4.a.(2)(b)3) See
note (b)
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### Page 27

Table 1: Engine strut midspar fuse pins replacement and detailed inspection
Repeat In-
terval (Not
to Ex-
ceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
---Before further
flight.
On the left side engine strut inboard
midspar fuse pin: Install a new or ser-
viceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.1.a.(2)(b)3) See
note (b)
If no crack-
ing, pitting,
corrosion or
chrome plate
damage is
found.
On the left side engine strut outboard
midspar fuse pin: Install a new or ser-
viceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.2.a.(2)(b)3) See
note (b)
On the right side engine strut inboard
midspar fuse pin: Install a new or ser-
viceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.3.a.(2)(b)3) See
note (b)
On the right side engine strut outboard
midspar fuse pin: Install a new or ser-
viceable midspar fuse pin in accor-
dance with the Accomplishment Instruc-
tions paragraph 3.B.4.a.(2)(b)3) See
note (b)
(a) No action is required if a midspar fuse pin with part number 311A1092-3 is already installed at this location.
(b) For each midspar fuse pin location, the installation of a new midspar fuse pin with part number 311A1092-
3 terminates the requirement for inspections at that location.
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.
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In addition, the Manager of the Seattle Aircraft Certification Office approves the accomplishment of the
inspections, repairs, and modifications specified in Section 1.E., Compliance, of SB 737-54-1044,
Revision 1 or SB 737-54A1044, Revision 2 as an AMOC to the applicable inspections and repairs
required by paragraph (f) of AD 2008-21-03. All provisions of AD 2008-21-03 that are not specifically
referenced in the preceding sentence remain fully applicable and must be complied with. Replacement
of the existing midspar fuse pin with the new dash number fuse pin per Section 1.E, Table 1, Note (b)
of Service Bulletin 737-54-1044, Revision 1, or 737-54A1044, Revision 2 terminates the inspections
required by paragraph (f) of AD 2008-21-03.
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
The table below shows an estimate of the task-hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task-hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Midspar Fuse Pin - Inspection and replacement
Elapsed HoursTask-HoursNumber of Per-
sons
Task
3.256.502Open Access (a)
1.501.501Figure 1
1.501.501Figure 2
3.256.502Close Access (b)
9.5016.00TOTAL FOR EACH AIRPLANE
(a) This includes time for the removal of the midspar fuse pins.
(b) This includes time for the installation of the midspar fuse pins.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Engineering Change Memo PRR 35005-273RS.
b. 737-300/400/500 Aircraft Maintenance Manual (AMM) 54-10-00, 54-10-01.
c. Boeing Drawing 65-88700.
d. Service Related Problem (SRP) 737-SRP-54-0115.
e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-42-10.
f. Boeing Component Maintenance Manual (CMM) 54-50-01
g. 737-300/400/500 Structural Repair Manual (SRM) Chapter 51
h. Federal Aviation Administration (FAA) Airworthiness Directive AD 2008-21-03
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
STRUT MOUNT INSTALLATION - CFM56-3 ENGINE310A1030
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
54-42737 Illustrated Parts Catalog
54-50-01Component 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 affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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### Page 31

2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes inspection, 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:
NotesNameQTYPart Number /
Specification
(b)(f)Fuse Pin1311A1092-3
(b)(f)Fuse Pin1311A1092-2
(a)(c)Primer4 OuncesBMS10-11, Type I
(c)(d)Low Hydrogen Embrittlement Stylus
Cadmium Plate
4 OuncesSPS-5070
(e)Methyl Ethyl Ketone (MEK) Solvent8 OuncesASTM D 740
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for sup-
plier data.
(b) This part is only necessary if the midspar fuse pin is replaced. The quantity shown is for one
midspar fuse pin replacement. There are four midspar fuse pins on an airplane.
(c) This part is only necessary if the midspar fuse pin is repaired. The quantity shown is an estimate
for one midspar fuse pin. There are four midspar fuse pins on an airplane.
(d) Refer to SOPM 20-42-10 for supplier details.
(e) Refer to SOPM 20-30-03 for supplier details.
(f) Part 311A1092-2 is optional to 311A1092-3 for a limited time, however the requirement for repeat
inspections is not terminated if 311A1092-2 is used. Refer to Paragraph 1.E., Compliance.
3. Parts Modified and Reidentified:
None.
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4. Parts Removed and Not Replaced:
NotesQTYNameExisting Part
Number
4WASHER311A1097-1
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. Unless shown differently, these dimensions and tolerances are used:
— Linear dimensions are in inches
— Torque limits to tighten nuts and bolts are given in 737 Structural Repair Manual,
Chapter 51.
4. For approved fastener and process material substitutions, refer to 737 Structural
Repair Manual, Chapter 51, Alternate fasteners are given in 737 Structural Repair
Manual Chapter 51 and Boeing Drawing 65-88700.
5. If the length of fasteners specified in this service bulletin do not meet the installation
standards, fasteners of the same specification, or an approved substitute, one grip
length longer or shorter may be used.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
7. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to ensure visual access to all surfaces in the
inspection area. This level of inspection is made under normal available lighting
conditions such as daylight, hangar lighting, flashlight or drop-light and may require
removal or opening of access panels or doors. Stands, ladders or platforms may be
required to gain proximity to the area being checked.
8. These work instructions refer to procedures included on 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.
B. WORK INSTRUCTIONS
1. PART 1 - LEFT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN
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a. Do a General Visual Inspection to identify the part number of the left side engine strut inboard
midspar fuse pin.
NOTE: The part number can be found on the head of the fuse pin.
(1) If the midspar fuse pin has part number 311A1092-3, no action is required.
(2) If the midspar fuse pin has part number 311A1092-2 or the part number cannot be found,
do one of the following:
(a) Install a midspar fuse pin with part number 311A1092-3:
NOTE: Installation of new midspar fuse pin with part number 311A1092-3 terminates
the requirement to do the repeat inspections of the left side engine strut
inboard midspar fuse pin. Refer to Paragraph 1.E., Compliance.
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the left side engine strut inboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
NOTE: As an option, remove the left side nacelle strut from the wing. Refer to
737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Install the left side engine strut inboard midspar fuse pin in accordance with
Figure 4.
(b) Inspect the midspar fuse pin that is currently installed:
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the left side engine strut inboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
NOTE: As an option, remove the left side nacelle strut from the wing. Refer to
737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Do a detailed inspection of the left side inboard midspar fuse pin for any cracking,
pitting, corrosion or chrome plate damage in accordance with Figure 1.
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a) If any cracking is found, then discard the midspar fuse pin.
b) If any pitting, corrosion or chrome plate damage is found in the inner bore,
threads, or under the chromed area, then discard the midspar fuse pin.
c) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth more than
0.010 inch, then discard the midspar fuse pin.
d) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth less than
or equal to 0.010 inch, then do one of the steps that follow:
{1} Repair the midspar fuse pin in accordance with Figure 3.
{2} Discard the midspar fuse pin.
e) If no cracking, pitting, corrosion or chrome plate damage is found, then the
midspar fuse pin is serviceable and can be kept for re-installation.
3) Do one of the following:
a) Install the left side engine strut inboard midspar fuse pin with new part
number 311A1092-3 in accordance with Figure 4.
NOTE: Installation of new midspar fuse pin with part number 311A1092-3
terminates the requirement to do the repeat inspections of the left
side engine strut inboard midspar fuse pin. Refer to Paragraph
1.E., Compliance.
b) Install the left side engine strut inboard midspar fuse pin with new part
number 311A1092-2 or serviceable midspar fuse pin. Do not install part
number 311A1097-1 special washer under the head of the midspar fuse
pin. Refer to 737-300/400/500 AMM 54-10-01 as an accepted procedure.
4) Do the repeat detailed inspection at the interval specified in Paragraph 1.E.,
Compliance.
2. PART 2 - LEFT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN
a. Do a General Visual Inspection to identify the part number of the left side engine strut outboard
midspar fuse pin.
NOTE: The part number can be found on the head of the fuse pin.
(1) If the midspar fuse pin has part number 311A1092-3, no action is required.
(2) If the midspar fuse pin has part number 311A1092-2 or the part number cannot be found,
do one of the following:
(a) Install a midspar fuse pin with part number 311A1092-3:
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NOTE: Installation of new midspar fuse pin with part number 311A1092-3 terminates
the requirement to do the repeat inspections of the left side engine strut
outboard midspar fuse pin. Refer to Paragraph 1.E., Compliance.
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the left side engine strut outboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
NOTE: As an option, remove the left side nacelle strut from the wing. Refer to
737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Install the left side engine strut outboard midspar fuse pin in accordance with
Figure 5.
(b) Inspect the midspar fuse pin that is currently installed:
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the left side engine strut outboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
NOTE: As an option, remove the left side nacelle strut from the wing. Refer to
737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Do a detailed inspection of the left side outboard midspar fuse pin for any
cracking, pitting, corrosion or chrome plate damage in accordance with Figure
1.
a) If any cracking is found, then discard the midspar fuse pin.
b) If any pitting, corrosion or chrome plate damage is found in the inner bore,
threads, or under the chromed area, then discard the midspar fuse pin.
c) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth more than
0.010 inch, then discard the midspar fuse pin.
d) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth less than
or equal to 0.010 inch, then do one of the steps that follow:
{1} Repair the midspar fuse pin in accordance with Figure 3.
{2} Discard the midspar fuse pin.
e) If no cracking, pitting, corrosion or chrome plate damage is found, then the
midspar fuse pin is serviceable and can be kept for re-installation.
3) Do one of the following:
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BOEING SERVICE BULLETIN 737-54A1044
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### Page 37

a) Install the left side engine strut outboard midspar fuse pin with new part
number 311A1092-3 in accordance with Figure 5.
NOTE: Installation of new midspar fuse pin with part number 311A1092-3
terminates the requirement to do the repeat inspections of the left
side engine strut outboard midspar fuse pin. Refer to Paragraph
1.E., Compliance.
b) Install the left side engine strut outboard midspar fuse pin with new part
number 311A1092-2 or serviceable midspar fuse pin. Do not install part
number 311A1097-1 special washer under the head of the midspar fuse
pin. Refer to 737-300/400/500 AMM 54-10-01 as an accepted procedure.
4) Do the repeat detailed inspection at the interval specified in Paragraph 1.E.,
Compliance.
3. PART 3 - RIGHT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN
a. Do a General Visual Inspection to identify the part number of the right side engine strut inboard
midspar fuse pin.
NOTE: The part number can be found on the head of the fuse pin.
(1) If the midspar fuse pin has part number 311A1092-3, no action is required.
(2) If the midspar fuse pin has part number 311A1092-2 or the part number cannot be found,
do one of the following:
(a) Install a midspar fuse pin with part number 311A1092-3:
NOTE: Installation of new midspar fuse pin with part number 311A1092-3 terminates
the requirement to do the repeat inspections of the right side engine strut
inboard midspar fuse pin. Refer to Paragraph 1.E., Compliance.
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the right side engine strut inboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
NOTE: As an option, remove the right side nacelle strut from the wing. Refer
to 737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Install the right side engine strut inboard midspar fuse pin in accordance with
Figure 6.
(b) Inspect the midspar fuse pin that is currently installed:
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the right side engine strut inboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
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### Page 38

NOTE: As an option, remove the right side nacelle strut from the wing. Refer
to 737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Do a detailed inspection of the right side inboard midspar fuse pin for any
cracking, pitting, corrosion or chrome plate damage in accordance with Figure
2.
a) If any cracking is found, then discard the midspar fuse pin.
b) If any pitting, corrosion or chrome plate damage is found in the inner bore,
threads, or under the chromed area, then discard the midspar fuse pin.
c) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth more than
0.010 inch, then discard the midspar fuse pin.
d) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth less than
or equal to 0.010 inch, then do one of the steps that follow:
{1} Repair the midspar fuse pin in accordance with Figure 3.
{2} Discard the midspar fuse pin.
e) If no cracking, pitting, corrosion or chrome plate damage is found, then the
midspar fuse pin is serviceable and can be kept for re-installation.
3) Do one of the following:
a) Install the right side engine strut inboard midspar fuse pin with new part
number 311A1092-3 in accordance with Figure 6.
NOTE: Installation of new midspar fuse pin with part number 311A1092-3
terminates the requirement to do the repeat inspections of the right
side engine strut inboard midspar fuse pin. Refer to Paragraph
1.E., Compliance.
b) Install the right side engine strut inboard midspar fuse pin with new part
number 311A1092-2 or serviceable midspar fuse pin. Do not install part
number 311A1097-1 special washer under the head of the midspar fuse
pin. Refer to 737-300/400/500 AMM 54-10-01 as an accepted procedure.
4) Do the repeat detailed inspection at the interval specified in Paragraph 1.E.,
Compliance.
4. PART 4 - RIGHT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN
a. Do a General Visual Inspection to identify the part number of the right side engine strut outboard
midspar fuse pin.
NOTE: The part number can be found on the head of the fuse pin.
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
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### Page 39

(1) If the midspar fuse pin has part number 311A1092-3, no action is required.
(2) If the midspar fuse pin has part number 311A1092-2 or the part number cannot be found,
do one of the following:
(a) Install a midspar fuse pin with part number 311A1092-3:
NOTE: Installation of new midspar fuse pin with part number 311A1092-3 terminates
the requirement to do the repeat inspections of the right side engine strut
outboard midspar fuse pin. Refer to Paragraph 1.E., Compliance.
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the right side engine strut outboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
NOTE: As an option, remove the right side nacelle strut from the wing. Refer
to 737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Install the right side engine strut outboard midspar fuse pin in accordance with
Figure 7.
(b) Inspect the midspar fuse pin that is currently installed:
WARNING: REMOVE ONLY ONE MIDSPAR FUSE PIN AT A TIME. INJURY TO
PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
1) Remove the right side engine strut outboard midspar fuse pin. Refer to
737-300/400/500 AMM 54-10-01 as an accepted procedure.
NOTE: As an option, remove the right side nacelle strut from the wing. Refer
to 737-300/400/500 AMM 54-10-00 as an accepted procedure.
2) Do a detailed inspection of the right side outboard midspar fuse pin for any
cracking, pitting, corrosion or chrome plate damage in accordance with Figure
2.
a) If any cracking is found, then discard the midspar fuse pin.
b) If any pitting, corrosion or chrome plate damage is found in the inner bore,
threads, or under the chromed area, then discard the midspar fuse pin.
c) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth more than
0.010 inch, then discard the midspar fuse pin.
d) If any pitting or corrosion damage is found not common to the inner bore,
threads, or under the chromed area and requires a blend depth less than
or equal to 0.010 inch, then do one of the steps that follow:
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
737-54A1044Revision 2: January 20, 2010
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### Page 40

{1} Repair the midspar fuse pin in accordance with Figure 3.
{2} Discard the midspar fuse pin.
e) If no cracking, pitting, corrosion or chrome plate damage is found, then the
midspar fuse pin is serviceable and can be kept for re-installation.
3) Do one of the following:
a) Install the right side engine strut outboard midspar fuse pin with new part
number 311A1092-3 in accordance with Figure 7.
NOTE: Installation of new midspar fuse pin with part number 311A1092-3
terminates the requirement to do the repeat inspections of the right
side engine strut outboard midspar fuse pin. Refer to Paragraph
1.E., Compliance.
b) Install the right side engine strut outboard midspar fuse pin with new part
number 311A1092-2 or serviceable midspar fuse pin. Do not install part
number 311A1097-1 special washer under the head of the midspar fuse
pin. Refer to 737-300/400/500 AMM 54-10-01 as an accepted procedure.
4) Do the repeat detailed inspection at the interval specified in Paragraph 1.E.,
Compliance.
b. Put the airplane back to a serviceable condition.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
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### Page 41 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
TYPICAL CHROME
PLATE DAMAGE
(2)
TYPICAL PITTING
AND CORROSION
DAMAGE
A—A  U78737
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary to inspect.
FIGURE 1: LEFT SIDE ENGINE STRUT - INBOARD AND OUTBOARD - MIDSPAR FUSE PIN - INSPECTION
(SHEET 1 OF 2)
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### Page 42

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)2311A1092-2Midspar Fuse PinClean1
(b)2311A1092-2Midspar Fuse Pin Inner BoreInspect2
(b)2311A1092-2Midspar Fuse Pin ThreadInspect3
(c)2311A1092-2Midspar Fuse Pin ShankInspect4
(b)2311A1092-2Midspar Fuse Pin HeadInspect5
(a) Use methyl ethyl ketone to remove all dirt and grease. Refer to SOPM 20-30-03 as an accepted procedure.
(b) Do a detailed inspection for any cracking, pitting or corrosion damage.
(c) Do a detailed inspection for any cracking, pitting, corrosion or chrome plate damage.
FIGURE 1: LEFT SIDE ENGINE STRUT - INBOARD AND OUTBOARD - MIDSPAR FUSE PIN - INSPECTION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
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BOEING SERVICE BULLETIN 737-54A1044
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
TYPICAL CHROME
PLATE DAMAGE
(2)
TYPICAL PITTING
AND CORROSION
DAMAGE
A-A  U78749
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary to inspect.
FIGURE 2: RIGHT SIDE ENGINE STRUT - INBOARD AND OUTBOARD - MIDSPAR FUSE PIN - INSPECTION
(SHEET 1 OF 2)
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Revision 2 January 20, 2010  BOEING PROPRIETARY -  737-54A1044
Copyright © Unpublished Work - See page 1 for details.  43 of 57

### Page 44

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)2311A1092-2Midspar Fuse PinClean1
(b)2311A1092-2Midspar Fuse Pin Inner BoreInspect2
(b)2311A1092-2Midspar Fuse Pin ThreadInspect3
(c)2311A1092-2Midspar Fuse Pin ShankInspect4
(b)2311A1092-2Midspar Fuse Pin HeadInspect5
(a) Use methyl ethyl ketone to remove all dirt and grease. Refer to SOPM 20-30-03 as an accepted procedure.
(b) Do a detailed inspection for any cracking, pitting or corrosion damage.
(c) Do a detailed inspection for any cracking, pitting, corrosion or chrome plate damage.
FIGURE 2: RIGHT SIDE ENGINE STRUT - INBOARD AND OUTBOARD - MIDSPAR FUSE PIN - INSPECTION
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
737-54A1044Revision 2 January 20, 2010
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BOEING SERVICE BULLETIN 737-54A1044
ALERTALERT

### Page 45

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a)(b)(c)--Pitting or Corrosion
Damage
Remove1
(d)--Blended AreasInspect2
(e)--Low Hydrogen
Embrittlement Sty-
lus Cadmium Plate
Apply3
(f)(g)--BMS 10-11, Type I
Primer
Apply4
(a) Blend out the pitting or corrosion damage from the midspar fuse pin. Make sure the blend depth is less
than or equal to 0.010 inch.
(b) Taper out the damage area with a 10:1 inch taper.
(c) Surface finish to a 63 microinch RA smoothness or better.
(d) Do a detailed inspection of the blended areas to make sure all corrosion damage has been removed.
Use a 10X magnifying lens to aid the inspection.
(e) To the damaged area. Refer to SOPM 20-42-10 as an accepted procedure.
(f) Apply two coats of primer to the blended areas and any other areas showing primer loss. Refer to SOPM
20-41-02 as an accepted procedure.
(g) Do not apply primer to the threads or chrome areas of the midspar fuse pin.
FIGURE 3: MIDSPAR FUSE PIN - REPAIR
(SHEET 1 OF 1)
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Copyright © Unpublished Work - See page 1 for details.
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
1544669
FIGURE 4: LEFT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 1 OF 3)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
WING  BUSHING
FITTING
WASHER  1) FUSE PIN
NUT
_ BOLT
COTTER
PIN
• WASHER
NUT
CAP
WASHER  BUSHING
MIDSPAR
ATTACH
FITTING
A-A
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of new parts necessary for this location.
FIGURE 4: LEFT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 2 OF 3)
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Revision 2 January 20, 2010  737-54A1044
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Copyright © Unpublished Work - See page 1 for details.  47 of 57

### Page 48

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)1311A1092-3Fuse PinInstall (New)1
(a) Do not install part number 311A1097-1 special washer under the head of the fuse pin.
(b) Refer to737-300/400/500 AMM 54-10-01as an accepted procedure.
FIGURE 4: LEFT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
737-54A1044Revision 2 January 20, 2010
48 of 57
BOEING SERVICE BULLETIN 737-54A1044
ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
1544088
FIGURE 5: LEFT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 1 OF 3)
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Revision 2 January 20, 2010  737-54A1044
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Copyright © Unpublished Work - See page 1 for details.  49 of 57

### Page 50 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
BUSHING  WING
FITTING
FUSE PIN (1)  WASHER
NUT
BOLTA
COTTER
PIN
WASHER
NUT
CAP
BUSHING  WASHER
MIDSPAR
ATTACH
FITTING
A-A  1544105
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of new parts necessary for this location.
FIGURE 5: LEFT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 2 OF 3)
Original Issue: December 10, 2007
Revision 2 January 20, 2010  737-54A1044
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Copyright © Unpublished Work - See page 1 for details.  50 of 57

### Page 51

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)1311A1092-3Fuse PinInstall (New)1
(a) Do not install part number 311A1097-1 special washer under the head of the fuse pin.
(b) Refer to 737-300/400/500 AMM 54-10-01 as an accepted procedure.
FIGURE 5: LEFT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
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51 of 57
BOEING SERVICE BULLETIN 737-54A1044
ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
1544671
FIGURE 6: RIGHT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 1 OF 3)
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Revision 2 January 20, 2010  737-54A1044
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Copyright © Unpublished Work - See page 1 for details.  52 of 57

### Page 53 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
BUSHING  WING
FITTING
FUSE PIN (1)  WASHER
NUT
BOLT_
COTTER
PIN
WASHER
• NUT
CAP
BUSHING  WASHER
MIDSPAR
ATTACH
FITTING
A-A  1544670
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of new parts necessary for this location.
FIGURE 6: RIGHT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 2 OF 3)
Original Issue: December 10, 2007
Revision 2 January 20, 2010  737-54A1044
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Copyright © Unpublished Work - See page 1 for details.  53 of 57

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)1311A1092-3Fuse PinInstall (New)1
(a) Do not install part number 311A1097-1 special washer under the head of the fuse pin.
(b) Refer to 737-300/400/500 AMM 54-10-01 as an accepted procedure.
FIGURE 6: RIGHT SIDE ENGINE STRUT - INBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
737-54A1044Revision 2 January 20, 2010
54 of 57
BOEING SERVICE BULLETIN 737-54A1044
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
1544672
FIGURE 7: RIGHT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 1 OF 3)
Original Issue: December 10, 2007
Revision 2 January 20, 2010  737-54A1044
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  55 of 57

### Page 56 (OCR)

BOEING SERVICE BULLETIN 737-54A1044
ALERT  ALERT
WING  BUSHING
FITTING
WASHER  1 FUSE PIN
NUT
_ BOLT
COTTER
PIN
WASHER
NUT
CAP
WASHER  BUSHING
MIDSPAR
ATTACH
FITTING
A-A  1544668
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of new parts necessary for this location.
FIGURE 7: RIGHT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 2 OF 3)
Original Issue: December 10, 2007
Revision 2 January 20, 2010  737-54A1044
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Copyright © Unpublished Work - See page 1 for details.  56 of 57

### Page 57

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)1311A1092-3Fuse PinInstall (New)1
(a) Do not install part number 311A1097-1 special washer under the head of the fuse pin.
(b) Refer to 737-300/400/500 AMM 54-10-01 as an accepted procedure.
FIGURE 7: RIGHT SIDE ENGINE STRUT - OUTBOARD - MIDSPAR FUSE PIN - INSTALLATION OF NEW
MATERIAL FUSE PIN
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 10, 2007
737-54A1044Revision 2 January 20, 2010
57 of 57
BOEING SERVICE BULLETIN 737-54A1044
ALERTALERT

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