# Boeing Alert Service Bulletin 747-57A2360: FAA-2017-0559_SB-747-57A2360

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2017-0559; AD 2017-18-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 747-57A2360](https://openairdocs.org/service-documents/boeing/747-57a2360.md)
- Title as filed: FAA-2017-0559_SB-747-57A2360
- Pages: 68
- PDF: https://openairdocs.org/files/sha256/26/c6/26c64dbad5b9a155705b1e2b8d43977c9a50caaa84b8b783f4c21a3765e487b0
- Page: https://openairdocs.org/service-documents/boeing/747-57a2360/file/26c64dbad5b9

## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-57A2360
Original Issue: January 20, 2017
ATA System: 5715
SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement
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 © 2017 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Unpublished Work.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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19
D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20
E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25
H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 27
K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27
L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29
2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 29
3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31
F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 31
3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33
B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
FIGURE 1: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN . . . . . . . . . . . . . . . . . 39
FIGURE 2: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41
FIGURE 3: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45
FIGURE 4: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49
FIGURE 5: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
FIGURE 6: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55
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FIGURE 7: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG -
INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59
APPENDIX A: COMPLIANCE LOGIC DIAGRAMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63
APPENDIX B: JACKING PROCEDURE FOR FUSE PIN REMOVAL . . . . . . . . . . . . . . . . . . . . 68
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-57A2360Original Issue: January 20, 2017
ATA System: 5715
SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will make sure there is no crack in the fuse pin of the wing landing gear
beam end fitting. An undetected crack in a fuse pin can cause the fuse pin to break. A broken fuse pin will not
support the wing landing gear beam, causing damage to the surrounding structure, including flight control cables
and hydraulic systems. Damage to the hydraulic systems and control cables could result in loss of controllability
of the airplane.
One operator reported to Boeing that during a walk-around after a flight, the operator found damage to the lower
trailing edge panels of the left wing of a 747-400 airplane. Further inspection revealed that the left wing landing
gear beam end fitting fuse pin had broken into two pieces. The airplane had 17,879 flight cycles and 102,793
flight hours at the time of the failure. Boeing has done an analysis and determined that the fuse pin broke as a
result of fatigue. This is the only report Boeing has received of a broken fuse pin in this location in the entire 747
fleet.
This service bulletin gives instructions to inspect and replace cracked fuse pins of the wing landing gear support
beam end fittings. Repeat inspections or replacements are necessary to make sure that there is no crack in the
fuse pin.
Boeing Service Related Problem (SRP) 747-57-0290 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 57-15008 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
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ReferenceAffectedPlanning Data
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Do one of the following options and repeat OPTION 1, OPTION 2, or OPTION 3 thereafter:
OPTION 1: FUSE PIN REPLACEMENT
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
2. Install new fuse pin.
3. Close access.
OPTION 2: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and do a MPI of the fuse pin.
2. Do a MPI of the fuse pin for any crack.
a. If no crack is found, install a serviceable fuse pin.
b. If any crack is found, install a new fuse pin.
3. Close access.
OPTION 3: SURFACE HIGH-FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF FUSE PIN
1. Get access and remove the grease plug on the fuse pin.
NOTE: Jacking of the airplane is not necessary to do a surface HFEC inspection of the fuse pin.
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2. Do a surface HFEC inspection of the fuse pin for any crack.
a. If no crack is found, install kept grease plug.
b. If any crack is found, remove and install a new fuse pin.
3. Close access.
EFFECTIVITY
All 747-100/-100B/-100B SUD/-200B/-200C/-200F/-300/-400/-400D/-400F/747SP/747SR Airplanes. 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.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin.
MANPOWER
OPTION 1: FUSE PIN REPLACEMENT
Elapsed HoursTotal Task HoursAirplanes
10.3045.50All airplanes
OPTION 2: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
Elapsed HoursTotal Task HoursAirplanes
12.3047.50All airplanes
OPTION 3: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION
OF FUSE PIN
Elapsed HoursTotal Task HoursAirplanes
10.1010.10All airplanes
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
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BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
Refer to Paragraph 2.A., Material - Price and Availability.
LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE
BEAM UPPER
_ FLAP TRACK  CHORD
LANDING GEAR SUPPORT
BEAM GATE FITTING
ASSEMBLY  WEB
FUSE PIN
END FITTING
BEAM LOWER
CHORD
REAR SPAR  WING LANDING GEAR
TRUNNION BEARING
DO ONE OF THE FOLLOWING OPTIONS AND REPEAT OPTIONS 1, OPTION 2, OR OPTION 3 THEREAFTER:
OPTION 1: FUSE PIN REPLACEMENT.
OPTION 2: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN.  2533095
OPTION 3: SURFACE HFEC INSPECTION OF FUSE PIN.
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### Page 9

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-57A2360
Original Issue: January 20, 2017
ATA System: 5715
SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is applicable to all 747-100/-100B/-100B
SUD/-200B/-200C/-200F/-300/-400/-400D/-400F/747SP/747SR Airplanes, line numbers 1-1419
in 7 Group(s). The Variable Numbers and Group Information for the applicable airplanes is given
below.
Refer to Service Bulletin Index D6-30300 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
747-100/-200B/-200C/-200F/747SR airplanes with 65B11261-1 fuse
pins installed in production.
-1
747-100B/-100B SUD/-200B/-200C/-200F/-300/747SR airplanes with
65B11261-2 fuse pins installed in production.
-2
747-400/-400F airplanes with 65B11261-6 fuse pins installed in
production.
-3
747-400/-400D/-400F airplanes with 65B11261-5 fuse pins installed
in production.
-4
747-200B/-200F/-300 airplanes with 65B11261-4 fuse pins installed
in production.
-5
747-400 airplanes with 65B11261-3 fuse pins installed in production.-6
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DESCRIPTIONCONFIGURATIONGROUP
747SP airplanes with 65B19191-1 fuse pins installed in production.-7
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SP, 747SR
GroupVariable Number
1RA001 - RA034
1RA101 - RA115
1RA161 - RA164
1RA201 - RA203
1RA216 - RA217
1RA245 - RA246
1RA251 - RA266
1RA301 - RA318
1RA351 - RA360
1RA369 - RA373
1RA401 - RA418
1RA501 - RA502
1RA521 - RA528
1RA532 - RA543
2RA544 - RA548
1RA551 - RA552
1RA559 - RA561
1RA581 - RA582
1RA585
1RA601 - RA602
1RA631 - RA635
1RA651 - RA652
1RA671 - RA677
1RA701 - RA702
1RA721 - RA725
2RA726 - RA731
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GroupVariable Number
1RA741 - RA745
1RA749
2RA750
1RA761 - RA762
1RA781 - RA783
2RA784
1RA901 - RA916
1RB001 - RB016
1RB041 - RB044
1RB071 - RB075
1RB101 - RB102
2RB411 - RB413
2RB421
1RB601 - RB607
2RB681 - RB697
2RB711
2RB721 - RB723
2RB741 - RB748
1RD001 - RD004
1RD021 - RD022
1RD041 - RD045
2RD046 - RD059
1RD071 - RD072
2RD081 - RD083
2RD091 - RD092
1RD101 - RD104
1RD121
2RD122 - RD127
1RD131
2RD132 - RD144
2RD166 - RD167
2RD171 - RD172
2RD181 - RD183
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GroupVariable Number
2RD201 - RD204
2RD221 - RD227
2RD231 - RD234
5RD235
2RD241 - RD243
2RD251 - RD262
2RD271 - RD272
2RD291 - RD292
2RD301 - RD302
2RD311
2RD351 - RD358
2RD361 - RD366
2RD381 - RD383
2RD411 - RD414
2RD421 - RD426
2RD431 - RD435
2RD441 - RD442
2RD451 - RD456
2RD461
2RD471 - RD475
2RD513 - RD519
2RD531 - RD533
2RD551
2RD561
2RD571
2RD581 - RD583
2RD591 - RD593
1RD601 - RD602
2RD603 - RD607
1RD621 - RD623
1RD641
2RD642 - RD649
2RD651 - RD659
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GroupVariable Number
2RD661
2RD671
1RD681
2RD682
2RD691 - RD692
2RD701 - RD702
2RD721 - RD722
2RD741 - RD742
2RD751 - RD755
2RD761
2RD771 - RD775
2RD781 - RD783
2RD791 - RD792
2RE001
3RF001 - RF006
7RG001 - RG009
7RG091
7RG095
7RG101 - RG104
7RG121 - RG126
7RG141 - RG142
7RG161 - RG164
7RG171 - RG174
7RG191 - RG193
7RG211 - RG213
7RG221 - RG222
7RH101 - RH102
7RH111 - RH112
7RH121 - RH122
1RJ131 - RJ133
1RJ151
2RJ152
1RJ301 - RJ302
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GroupVariable Number
2RJ303
2RJ321 - RJ322
2RJ331 - RJ333
4RL401 - RL402
3RL403
4RL411 - RL419
3RL420 - RL436
3RL451 - RL456
3RL461 - RL462
3RL471 - RL481
3RL491 - RL492
3RL501 - RL502
3RL511 - RL516
3RL521 - RL522
3RL531 - RL534
3RL551
3RL561 - RL568
3RL571 - RL572
3RL576 - RL577
3RL579
3RL581 - RL586
4RL651 - RL654
3RL655
3RL671 - RL675
3RL681 - RL684
4RL751
3RL752
4RM001 - RM007
4RM010 - RM013
4RM021 - RM024
4RM026 - RM029
3RM030
4RM036 - RM045
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GroupVariable Number
4RM051 - RM052
3RM053
4RM071
4RM081 - RM084
4RM091
4RM096 - RM097
4RM116 - RM117
4RM126 - RM132
4RM136 - RM147
4RM156 - RM158
4RM166 - RM177
4RM191 - RM192
4RM231 - RM233
4RM241 - RM246
4RM261 - RM264
4RM316 - RM318
4RM331 - RM333
4RM341
4RM351 - RM355
4RM366 - RM367
3RM401 - RM403
3RM426
3RM431
3RM441 - RM443
3RM445
4RM801 - RM803
4RM811 - RM813
4RM851 - RM858
3RM859
4RM861 - RM862
3RM863
4RM871 - RM876
3RM877 - RM880
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GroupVariable Number
4RM881 - RM886
3RM887 - RM890
4RM891 - RM899
4RM901 - RM905
3RM906
4RM911
2RR001 - RR005
2RR021 - RR023
5RR024 - RR025
2RR031
1RR201
2RR202 - RR206
1RR221 - RR222
2RR223 - RR226
1RR261
2RR262 - RR267
1RR301
2RR302 - RR307
5RR308 - RR310
2RR331 - RR332
2RR336
1RR341 - RR343
2RR344 - RR345
2RR361 - RR362
2RR421 - RR422
2RR431 - RR432
2RR441
5RR442
5RR451
2RR501 - RR504
2RR521
5RR522
5RR526
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GroupVariable Number
2RR531
2RR551 - RR554
5RR555 - RR556
2RR561
2RR566
4RR701
4RR721 - RR724
4RR746 - RR748
4RR851 - RR856
4RR861 - RR862
4RR951 - RR952
2RS001 - RS002
2RS201
2RS211 - RS212
2RS221 - RS222
2RS231 - RS241
2RS251 - RS259
5RS263
2RS265 - RS268
2RS271 - RS276
2RS291 - RS292
2RS301 - RS306
2RS311 - RS320
2RS331 - RS333
2RS341 - RS342
2RS699
2RS701 - RS703
2RS711 - RS713
2RS721 - RS722
2RS731 - RS732
2RS741 - RS743
2RS751 - RS752
2RS761
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GroupVariable Number
5RS762
2RS771
2RS781
5RS782
2RS786
4RT001 - RT014
4RT021 - RT022
4RT031 - RT035
4RT041 - RT047
4RT061
4RT071 - RT075
4RT101 - RT103
4RT121
4RT131 - RT137
4RT151 - RT152
4RT161 - RT168
6RT401 - RT402
4RT403 - RT412
6RT431
4RT432 - RT447
6RT451
4RT452 - RT469
4RT471 - RT499
4RT501 - RT535
4RT551 - RT568
4RT571 - RT591
4RT601 - RT657
4RT671 - RT673
4RT681 - RT682
4RT691 - RT699
4RT701 - RT704
4RT711 - RT717
4RT741 - RT757
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GroupVariable Number
4RT776 - RT777
4RT781 - RT784
4RT801 - RT803
4RT811 - RT814
4RT831 - RT837
4RT861 - RT864
4RT876 - RT880
4RT931 - RT932
4RT945 - RT949
4RT951 - RT955
4RT966 - RT967
4RU001 - RU006
4RU016 - RU017
4RU031 - RU032
4RU051 - RU052
4RU059 - RU062
4RU081 - RU083
4RU101 - RU102
4RU121 - RU132
4RU801 - RU809
4RU831 - RU841
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will make sure there is no crack in the fuse pin of the wing
landing gear beam end fitting. An undetected crack in a fuse pin can cause the fuse pin to break. A
broken fuse pin will not support the wing landing gear beam, causing damage to the surrounding
structure, including flight control cables and hydraulic systems. Damage to the hydraulic systems and
control cables could result in loss of controllability of the airplane.
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One operator reported to Boeing that during a walk-around after a flight, the operator found damage
to the lower trailing edge panels of the left wing of a 747-400 airplane. Further inspection revealed that
the left wing landing gear beam end fitting fuse pin had broken into two pieces. The airplane had 17,879
flight cycles and 102,793 flight hours at the time of the failure. Boeing has done an analysis and
determined that the fuse pin broke as a result of fatigue. This is the only report Boeing has received
of a broken fuse pin in this location in the entire 747 fleet.
This service bulletin gives instructions to inspect for and replace cracked fuse pins of the wing landing
gear support beam end fittings. Repeat inspections or replacements are necessary to make sure that
there is no crack in the fuse pin.
Boeing Service Related Problem (SRP) 747-57-0290 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 747 FTD 57-15008 is related to this service bulletin.
D. Description
Do one of the following options and repeat OPTION 1, OPTION 2, or OPTION 3 thereafter:
OPTION 1: FUSE PIN REPLACEMENT
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
2. Install new fuse pin.
3. Close access.
OPTION 2: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and do a MPI of the fuse pin.
2. Do a MPI of the fuse pin for any crack.
a. If no crack is found, install a serviceable fuse pin.
b. If any crack is found, install a new fuse pin.
3. Close access.
OPTION 3: SURFACE HIGH-FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF FUSE PIN
1. Get access and remove the grease plug on the fuse pin.
NOTE: Jacking of the airplane is not necessary to do a surface HFEC inspection of the fuse pin.
2. Do a surface HFEC inspection of the fuse pin for any crack.
a. If no crack is found, install kept grease plug.
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b. If any crack is found, remove and install a new fuse pin.
3. Close access.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
572, 672747-100, 747-200B, 747-200C,
747-200F, 747SR
Group 2:
Affected Maintenance Zones
ZoneModel
572, 672747-100B, 747-100B SUD, 747-
200B, 747-200C, 747-200F,
747-300, 747SR
Group 3:
Affected Maintenance Zones
ZoneModel
572, 672747-400, 747-400F
Group 4:
Affected Maintenance Zones
ZoneModel
572, 672747-400, 747-400D, 747-400F
Group 5:
Affected Maintenance Zones
ZoneModel
572, 672747-200B, 747-200F, 747-300
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Group 6:
Affected Maintenance Zones
ZoneModel
572, 672747-400
Group 7:
Affected Maintenance Zones
ZoneModel
572, 672747SP
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.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
NOTE: After the accomplishment of an OPTION, it is acceptable to accomplish a different OPTION
within the given compliance time or repeat interval.
A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX
A.
The conditions and associated actions given in Paragraph 3.B., Work Instructions can be different on
the left wing and right wing of the airplane. Because the conditions found may not be the same on left
wing and right wing of the airplane, the required actions may be different between the left wing and
right wing of the airplane and can be done independently.
Accomplish the required actions, based on the applicable conditions in Table 1, in accordance with
Paragraph 3. Accomplishment Instructions.
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Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 24
months or 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin, whichever
occurs first.
Before 12,000
total flight cy-
cles.
OPTION 1: Do PART 5:
NEW FUSE PIN INSTAL-
LATION
Airplanes with original fuse
pins
-OPTION 2: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN
-OPTION 3: Do PART 4:
SURFACE HFEC IN-
SPECTION OF FUSE
PIN
-Within 24
months or 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin, whichever
occurs first.
Within 12,000
fuse pin flight
cycles
OPTION 1: Do PART 5:
NEW FUSE PIN INSTAL-
LATION
Airplanes with replaced
fuse pins with new or
known flight cycles on the
fuse pin -OPTION 2: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN
-OPTION 3: Do PART 4:
SURFACE HFEC IN-
SPECTION OF FUSE
PIN
--Within 24
months or 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin, whichever
occurs first.
OPTION 1: Do PART 5:
NEW FUSE PIN INSTAL-
LATION
Airplanes with replaced
fuse pins with unknown
flight cycles on the fuse pin
-OPTION 2: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN
-OPTION 3: Do PART 4:
SURFACE HFEC IN-
SPECTION OF FUSE
PIN
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Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flightACTION 1: Do PART 6:
SERVICEABLE FUSE
PIN INSTALLATION
CONDITION 1: NO
CRACK FOUND DURING
MAGNETIC PARTICLE
INSPECTION (a)Within 2,400 flight cycles after the
most recent magnetic particle in-
spection
ACTION 2 (OPTION 1):
Do PART 5: NEW FUSE
PIN INSTALLATION
2,400 flight cycles
(b)
-ACTION 2 (OPTION 2):
Repeat PART 3: MAG-
NETIC PARTICLE IN-
SPECTION OF FUSE
PIN
(a)Within 2,400 flight cycles after the
most recent magnetic particle in-
spection
ACTION 2 (OPTION 3):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN
(a)Within 1,200 flight cycles after the
most recent surface HFEC inspec-
tion.
OPTION 1: Do PART 5:
NEW FUSE PIN INSTAL-
LATION
CONDITION 2: NO
CRACK FOUND DURING
SURFACE HFEC INSPEC-
TION (a)Within 1,200 flight cycles after the
most recent surface HFEC inspec-
tion.
OPTION 2: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN
1,200 flight cycles
(b)
-OPTION 3: Repeat PART
4: SURFACE HFEC IN-
SPECTION OF FUSE
PIN
(a)Before further flight.Do PART 5: NEW FUSE
PIN INSTALLATION
CONDITION 3: ANY
CRACK FOUND
12,000 flight cycles
(b)
-OPTION 1: Repeat PART
5: NEW FUSE PIN IN-
STALLATION
CONDITION 4: NEW
FUSE PIN INSTALLED
(a)Within 12,000 flight cycles after
installation of the new fuse pin.
OPTION 2: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN
(a)Within 12,000 flight cycles after
installation of the new fuse pin.
OPTION 3: Do PART 4:
SURFACE HFEC IN-
SPECTION OF FUSE
PIN
(a) This is not a terminating action. Refer to the applicable condition for further actions.
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Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) It is acceptable to change the repeat action from this OPTION to any other OPTION under this CONDI-
TION. Operators must comply with the compliance time given for the chosen OPTION under this CON-
DITION.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this Service Bulletin for an
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 inspect the work
• Time to cure the materials
• Time to make the parts
• Time to find the tools
OPTION 1: FUSE PIN REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
6.9034.505Open Access
(PART 1)
1.002.002Remove Fuse Pin
(PART 2)
1.002.002Install Fuse Pin
(PART 5)
1.407.005Close Access
(PART 7)
10.3045.50TOTAL FOR EACH AIRPLANE
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OPTION 2: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
Elapsed HoursTask HoursNumber of PersonsTask
6.9034.505Open Access
(PART 1)
1.002.002Remove Fuse Pin
(PART 2)
1.001.001FIGURE 1
(PART 3 - Left Side)
1.001.001FIGURE 1
(PART 3 - Right
Side)
1.002.002Install Fuse Pin
(PART 6)
1.407.005Close Access
(PART 7)
12.3047.50TOTAL FOR EACH AIRPLANE
OPTION 3: SURFACE HFEC INSPECTION OF FUSE PIN
Elapsed HoursTask HoursNumber of PersonsTask
2.002.001Open Access
(PART 1)
0.500.501FIGURE 2 (PART 1)
0.500.501FIGURE 3 (PART 1)
2.002.001FIGURE 4
(PART 4)
2.002.001FIGURE 5
(PART 4)
0.550.551FIGURE 6 (PART 7)
0.550.551FIGURE 7 (PART 7)
2.002.001Close Access
(PART 7)
10.1010.10TOTAL FOR EACH AIRPLANE (a)
(a) The task hours to replace any cracked fuse pin is not included in the estimate.
Refer to the applicable table for task hours related to fuse pin replacement.
H. Weight and Balance Changes
None.
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I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Related Problem (SRP) 747-57-0290
b. Service Bulletin Index D6-30300
c. Standard Overhaul Practices Manual (SOPM) 20-20-01, 20-30-03
d. 747 Fleet Team Digest (FTD) 57-15008
e. 747 Non-Destructive Testing (NDT) Manual Part 6, 57-10-40
f. 747-100/200/300 Aircraft Maintenance Manual (AMM) 07-11-01, 12-09-08, 32-00-15, 32-00-30,
57-15-01
g. 747-400 Aircraft Maintenance Manual (AMM) 06-09-08, 07-11-01, 32-00-15, 32-00-30, 57-15-01
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
BEARING INSTALLATION - SUPPORT BEAM, WING LANDING
GEAR
65B01185
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
57-15, 57-41747 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
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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. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin
does not show the Boeing price and supply data.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
NotesNameQTYPart Number /
Specification
-Grease1 QtMIL-PRF-
23827/NATO G-
345
The following tables show parts necessary for replacement of a fuse pin for each group. Only Qty
1 fuse pin from the applicable table is necessary for a replacement. There are two fuse pins on
an airplane, one on each wing.
Group 1:
NotesExisting Part NumberNameQTYPart Number /
Specification
65B11261-1Bearing Pin (Fuse Pin)165B11261-1
(a)65B11261-1Bearing Pin (Fuse Pin)165B11261-2
(a)65B11261-1Bearing Pin (Fuse Pin)165B11261-4
(a) You can use the existing part to replace the new part.
Group 2:
NotesExisting Part NumberNameQTYPart Number /
Specification
65B11261-2Bearing Pin (Fuse Pin)165B11261-2
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Group 2:
NotesExisting Part NumberNameQTYPart Number /
Specification
(a)65B11261-2Bearing Pin (Fuse Pin)165B11261-4
(a) You can use the existing part to replace the new part.
Group 3:
NotesExisting Part NumberNameQTYPart Number /
Specification
65B11261-6Bearing Pin (Fuse Pin)165B11261-6
Group 4:
NotesExisting Part NumberNameQTYPart Number /
Specification
(a)65B11261-5Bearing Pin (Fuse Pin)165B11261-3
65B11261-5Bearing Pin (Fuse Pin)165B11261-5
(a) You can use the existing part to replace the new part.
Group 5:
NotesExisting Part NumberNameQTYPart Number /
Specification
(a)65B11261-4Bearing Pin (Fuse Pin)165B11261-2
65B11261-4Bearing Pin (Fuse Pin)165B11261-4
(a) You can use the existing part to replace the new part.
Group 6:
NotesExisting Part NumberNameQTYPart Number /
Specification
65B11261-3Bearing Pin (Fuse Pin)165B11261-3
(a)65B11261-3Bearing Pin (Fuse Pin)165B11261-5
(a) You can use the existing part to replace the new part.
Group 7:
NotesExisting Part NumberNameQTYPart Number /
Specification
65B19191-1Bearing Pin (Fuse Pin)165B19191-1
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3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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### Page 33

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 747 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 747
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
5. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
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. 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.
8. Refer to APPENDIX A for logic diagrams. Logic diagrams are provided as an aid
only. Information contained in Paragraph 1.E., Compliance is the primary source for
compliance times. Information in Paragraph 3.B., Work Instructions is the primary
source for tasks required for compliance.
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9. Refer to APPENDIX B for jacking and shoring instructions for OPTION 1: FUSE PIN
REPLACEMENT and OPTION 2: MAGNETIC PARTICLE INSPECTION (MPI) OF
FUSE PIN. Jacking is not necessary for OPTION 3: SURFACE HIGH FREQUENCY
EDDY CURRENT (HFEC) INSPECTION OF FUSE PIN.
10. 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.
11. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
12. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
14. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
15. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
16. The conditions and associated actions given in Paragraph 3.B., Work Instructions
can be different on the left wing and right wing of the airplane. Because the conditions
found may not be the same on left wing and right wing of the airplane, the required
actions may be different between the left wing and right wing of the airplane and can
be done independently.
17. Some steps in the Work Instructions are labeled as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
labeled as RC, including sub-steps under an RC step and any figures identified in
an RC step, must be done to comply with the AD. If a step or sub-step is labeled
"RC Exempt," then the RC requirement is removed from that step or sub-step. An
Alternative Method of Compliance (AMOC) is required for any deviations to RC steps,
including sub-steps and identified figures. Steps not labeled as RC may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC. This is provided that
the RC steps, including sub-steps and identified figures, can still be done as specified,
and the airplane can be put back in an airworthy condition.
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 35

18. The part "Fuse Pin" is located at and installed in the Wing Landing Gear Beam End
Fitting. The affected fuse pin part numbers 65B11261-( ) (Groups 1-6) or 65B19191-(
) (Group 7), are shown in Paragraph 2.C.2., Parts and Materials Supplied by the
Operator.
B. WORK INSTRUCTIONS
Do one of the following options:
OPTION 1: FUSE PIN REPLACEMENT
1. Do PART 1: OPEN ACCESS.
2. Do PART 2: FUSE PIN REMOVAL.
3. RC - Do PART 5: NEW FUSE PIN INSTALLATION.
a. CONDITION 4: NEW PIN INSTALLED
(1) Repeat OPTION 1, or do OPTION 2 or OPTION 3 at the compliance times specified in
Paragraph 1.E., Compliance.
4. Do PART 7: CLOSE ACCESS.
5. Put the airplane back to a serviceable condition.
OPTION 2: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
1. Do PART 1: OPEN ACCESS.
2. Do PART 2: FUSE PIN REMOVAL.
3. RC - Do PART 3: MAGNETIC PARTICLE INSPECTION OF FUSE PIN.
a. CONDITION 1: NO CRACK FOUND DURING MAGNETIC PARTICLE INSPECTION
(1) ACTION 1: Do PART 6: SERVICEABLE FUSE PIN INSTALLATION.
(2) ACTION 2: Do OPTION 1, repeat OPTION 2, or do OPTION 3 at the compliance times
specified in Paragraph 1.E., Compliance.
b. CONDITION 3: ANY CRACK FOUND
(1) Do PART 5: NEW FUSE PIN INSTALLATION.
(a) CONDITION 4: NEW FUSE PIN INSTALLED
1) Repeat OPTION 1, or do OPTION 2 or OPTION 3 at the compliance times
specified in Paragraph 1.E., Compliance.
4. Do PART 7: CLOSE ACCESS.
5. Put the airplane back to a serviceable condition.
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### Page 36

OPTION 3: SURFACE HFEC INSPECTION OF FUSE PIN
1. Do PART 1: OPEN ACCESS.
2. RC - Do PART 4: SURFACE HFEC INSPECTION OF FUSE PIN.
a. CONDITION 2: NO CRACK FOUND DURING SURFACE HFEC INSPECTION
(1) Do OPTION 1 or OPTION 2, or repeat OPTION 3 at the compliance times specified in
Paragraph 1.E., Compliance.
b. CONDITION 3: ANY CRACK FOUND
(1) Do PART 5: NEW FUSE PIN INSTALLATION.
NOTE: Additional access and removal of the fuse pin are necessary to do PART 5. Go
to OPTION 1: FUSE PIN REPLACEMENT for access and fuse pin removal
instructions to do PART 5.
(a) CONDITION 4: NEW FUSE PIN INSTALLED
1) Repeat OPTION 1, or do OPTION 2 or OPTION 3 at the compliance times
specified in Paragraph 1.E., Compliance.
3. Do PART 7: CLOSE ACCESS.
4. Put the airplane back to a serviceable condition.
PART 1: OPEN ACCESS
1. For Fuse Pin Replacement (OPTION 1) and MPI of Fuse Pin (OPTION 2):
a. Install Nose and Main Landing Gear ground locks in all landing gear. Refer to 747-100/200/300
AMM 32-00-15 or 747-400 AMM 32-00-15 as an accepted procedure.
b. Install door locks in the doors of the wing and body landing gear. Refer to 747-100/200/300
AMM 32-00-30 or 747-400 AMM 32-00-30 as an accepted procedure.
c. Remove and keep upper and lower access panels to expose support beam, walking beam
support, and gate fitting. Refer to 747-100/200/300 AMM 12-09-08 or 747-400 AMM 06-09-08
as an accepted procedure, and to the following table for a list of access panels to remove:
Right WingLeft Wing
671AB, 672AB, 672BB, 672CB,
672DB, 672EB, 671DT, 671ET
571AB, 572AB, 572BB, 572CB,
572DB, 572EB, 571DT, 571ET
d. Jack airplane. Refer to 747-100/200/300 AMM 07-11-01 or 747-400 AMM 07-11-01 as an
accepted procedure, and APPENDIX B for additional instructions.
2. For Surface HFEC Inspection of Fuse Pin (OPTION 3):
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### Page 37

a. Install Nose and Main Landing Gear ground locks in all landing gear. Refer to 747-100/200/300
AMM 32-00-15 or 747-400 AMM 32-00-15 as an accepted procedure.
b. Install door locks in the doors of the wing and body landing gear. Refer to 747-100/200/300
AMM 32-00-30 or 747-400 AMM 32-00-30 as an accepted procedure.
c. Remove and keep upper and lower access panels to expose support beam, walking beam
support, and gate fitting. Refer to 747-100/200/300 AMM 12-09-08 or 747-400 AMM 06-09-08
as an accepted procedure, and to the following table for a list of access panels to remove:
Right WingLeft Wing
671AB, 672AB, 672BB, 672CB,
672DB, 672EB, 671DT, 671ET
571AB, 572AB, 572BB, 572CB,
572DB, 572EB, 571DT, 571ET
d. Get access to the inside of the fuse pin. Refer to the figures on the following table:
Right WingLeft Wing
FIGURE 3FIGURE 2
PART 2: FUSE PIN REMOVAL
1. Remove and keep the fuse pin on the left and right wing. Refer to 747-100/200/300 AMM 57-15-01
or 747-400 AMM 57-15-01 as an accepted procedure.
PART 3: MAGNETIC PARTICLE INSPECTION OF FUSE PIN
1. Do a Magnetic Particle Inspection (MPI) of the fuse pin removed and kept from the left and right
wing for any crack in accordance with FIGURE 1.
PART 4: SURFACE HFEC INSPECTION OF FUSE PIN
1. Do a surface HFEC inspection of the fuse pin for any crack in accordance with the figures in the
following table:
Right WingLeft Wing
FIGURE 5FIGURE 4
PART 5: NEW FUSE PIN INSTALLATION
1. Install new fuse pin on the left wing and right wing. Refer to 747-100/200/300 AMM 57-15-01 or
747-400 AMM 57-15-01 as an accepted procedure.
PART 6: SERVICEABLE FUSE PIN INSTALLATION
1. Install serviceable fuse pin on the left wing and right wing. Refer to 747-100/200/300 AMM 57-15-01
or 747-400 AMM 57-15-01 as an accepted procedure. A serviceable fuse pin is defined as a fuse
pin that has been inspected in accordance with PART 3 with no crack found and no corrosion
found.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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ALERTALERT

### Page 38

PART 7: CLOSE ACCESS
1. For Fuse Pin Replacement (OPTION 1) and MPI of Fuse Pin (OPTION 2):
a. De-jack airplane. Refer to 747-100/200/300 AMM 07-11-01 or 747-400 AMM 07-11-01 as an
accepted procedure, and APPENDIX B for additional instructions.
b. Install removed access panels.
c. Remove door locks from the doors of the wing and body landing gear. Refer to 747-100/200/300
AMM 32-00-30 or 747-400 AMM 32-00-30 as an accepted procedure.
d. Remove Nose and Main Landing Gear ground locks from all landing gear. Refer to
747-100/200/300 AMM 32-00-15 or 747-400 AMM 32-00-15 as an accepted procedure.
2. For Surface HFEC Inspection of Fuse Pin (OPTION 3):
a. Close access to the inside of the fuse pin. Refer to the figures on the following table:
Right WingLeft Wing
FIGURE 7FIGURE 6
b. Install removed access panels.
c. Remove door locks from the doors of the wing and body landing gear. Refer to 747-100/200/300
AMM 32-00-30 or 747-400 AMM 32-00-30 as an accepted procedure.
d. Remove Nose and Main Landing Gear ground locks from all landing gear. Refer to
747-100/200/300 AMM 32-00-15 or 747-400 AMM 32-00-15 as an accepted procedure.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: January 20, 2017
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ALERTALERT

### Page 39 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
FUSE PIN
CHROME PLATE
THREADED
THREADED
INSPECTION AREA
TYPICAL  A-A  2533101
FIGURE 1: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
(SHEET 1 OF 2)
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### Page 40

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 for each fuse pin.
More DataQtyIdentificationNameTaskStep
(a)1-Fuse PinClean1
(b)1-Fuse PinInspect2
(a) Remove grease from interior of fuse pin and clean the inspection area. Refer to SOPM 20-30-03 as an
accepted procedure.
(b) Do a MPI for any crack. Do the inspection full 360 degrees in the area shown. Refer to SOPM 20-20-01
as an accepted procedure.
During the MPI, do a detailed inspection for corrosion to make sure the fuse pin is in a serviceable condition.
A serviceable fuse pin is defined as a fuse pin with no crack found and no corrosion found. If any corrosion
is found, discard the fuse pin and install a new fuse pin in accordance with PART 5.
FIGURE 1: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
(SHEET 2 OF 2)
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ALERTALERT

### Page 41 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
LANDING GEAR  FLAP TRACK  BEAM UPPER  CHORD
SUPPORT BEAM
GATE FITTING
ASSEMBLY  WEB
END FITTING
BEAM LOWER
CHORD
REAR SPAR  WING LANDING GEAR
TRUNNION BEARING
LANDING GEAR SUPPORT BEAM
2533106
FIGURE 2: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 1 OF 4)
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### Page 42

FIGURE 2: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 2 OF 4)
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Work - See page 1 for details.
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ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
RETENTION HARDWARE
WITH LOCK PIN AND
LOCK CLIP
@ PIN
RETENTION
HARDWARE WITH PIN
RETAINER ASSEMBLY
Ç HINGE
A-A
2533139
FIGURE 2: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 3 OF 4)
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Work - See page 1 for details.  43 of 68

### Page 44

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 for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a)--Retention HardwareRemove / Keep1
(a)1-Grease PlugRemove / Keep2
(a) Refer to 747-100/200/300 AMM 57-15-01 or 747-400 AMM 57-15-01 as an accepted procedure.
FIGURE 2: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 4 OF 4)
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ALERTALERT

### Page 45 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
BEAM UPPER
CHORD  FLAP TRACK  LANDING GEAR
SUPPORT BEAM
GATE FITTING
ASSEMBLY
WẸB
END FITTING
BEAM LOWER
CHORD
WING LANDING GEAR  REAR SPAR
TRUNNION BEARING
LANDING GEAR SUPPORT BEAM
2533143
FIGURE 3: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 1 OF 4)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
RETENTION HARDWARE
WITH LOCK PIN AND
LOCK CLIP
RETENTION
HARDWARE WITH PIN
RETAINER ASSEMBLY
2533147
FIGURE 3: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 2 OF 4)
Original Issue: January 20, 2017
Export Controlled ECCN: 9E991 - BOEING  747-57A2360
PROPRIETARY - Copyright © Unpublished
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
RETENTION HARDWARE
WITH LOCK PIN AND
LOCK CLIP
PINET
RETENTION
HARDWARE WITH PIN
RETAINER ASSEMBLY
& HINGE
A-A
FIGURE 3: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 3 OF 4)
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Work - See page 1 for details.  47 of 68

### Page 48

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 for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a)--Retention HardwareRemove / Keep1
(a)1-Grease PlugRemove / Keep2
(a) Refer to 747-100/200/300 AMM 57-15-01 or 747-400 AMM 57-15-01 as an accepted procedure.
FIGURE 3: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
(SHEET 4 OF 4)
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ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
LANDING GEAR  FLAP TRACK  BEAM UPPER  CHORD
SUPPORT BEAM
GATE FITTING
ASSEMBLY  WEB
END FITTING
BEAM LOWER
CHORD
REAR SPAR  WING LANDING GEAR
TRUNNION BEARING
LANDING GEAR SUPPORT BEAM
2533295
FIGURE 4: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
(SHEET 1 OF 3)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
SAME AS INTERNAL
HORIZONTAL SURFACE
THREADED
- EPIN
@ HINGE
TYPICAL  2533297
A-A
FIGURE 4: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
(SHEET 2 OF 3)
Original Issue: January 20, 2017
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### Page 51

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 for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a)1-Fuse PinClean1
(b)1-Fuse PinInspect2
(a) Remove grease from interior of fuse pin and clean the inspection area. Refer to SOPM 20-30-03 as an
accepted procedure.
(b) Do a surface HFEC inspection for any crack in accordance with 747 NDT Manual Part 6, 57-10-40. Do
the inspection full 360 degrees of the inner surface in the area shown.
FIGURE 4: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
(SHEET 3 OF 3)
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ALERTALERT

### Page 52 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
BEAM UPPER
CHORD  FLAP TRACK  LANDING GEAR
SUPPORT BEAM
GATE FITTING
WEB  ASSEMBLY
END FITTING
BEAM LOWER
CHORD
WING LANDING GEAR REAR SPAR
TRUNNION BEARING
LANDING GEAR SUPPORT BEAM
2533298
FIGURE 5: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
(SHEET 1 OF 3)
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
SAME AS INTERNAL
HORIZONTAL SURFACE
THREADED
PINET
HINGEC
TYPICAL
A-A
FIGURE 5: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
(SHEET 2 OF 3)
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### Page 54

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 for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a)1-Fuse PinClean1
(b)1-Fuse PinInspect2
(a) Remove grease from interior of fuse pin and clean the inspection area. Refer to SOPM 20-30-03 as an
accepted procedure.
(b) Do a surface HFEC inspection for any crack in accordance with 747 NDT Manual Part 6, 57-10-40. Do
the inspection full 360 degrees of the inner surface in the area shown.
FIGURE 5: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN - SURFACE HFEC INSPECTION
(SHEET 3 OF 3)
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ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
LANDING GEAR  FLAP TRACK  BEAM UPPER  CHORD
SUPPORT BEAM
GATE FITTING
ASSEMBLY  WEB
END FITTING
BEAM LOWER
CHORD
REAR SPAR  WING LANDING GEAR
TRUNNION BEARING
LANDING GEAR SUPPORT BEAM
2533306
FIGURE 6: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
(SHEET 1 OF 4)
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### Page 56

FIGURE 6: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
(SHEET 2 OF 4)
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ALERTALERT

### Page 57 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
RETENTION HARDWARE
WITH LOCK PIN AND
LOCK CLIP,
RETENTION
HARDWARE WITH PIN
RETAINER ASSEMBLY
ÇHINGE
A-A
2533314
FIGURE 6: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
(SHEET 3 OF 4)
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### Page 58

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 for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a) (b)-MIL-PRF-23827/NATO
G-345
GreaseApply1
(b)1-Grease PlugInstall (Kept)2
(b)--Retention HardwareInstall (Kept)3
(a) Fully fill the empty space of the fuse pin with the grease.
(b) Refer to 747-100/200/300 AMM 57-15-01 or 747-400 AMM 57-15-01 as an accepted procedure.
FIGURE 6: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
(SHEET 4 OF 4)
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ALERTALERT

### Page 59 (OCR)

BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
BEAM UPPER
CHORD  FLAP TRACK  LANDING GEAR
SUPPORT BEAM
GATE FITTING
ASSEMBLY
WẸB
END FITTING
BEAM LOWER
CHORD
WING LANDING GEAR  REAR SPAR
TRUNNION BEARING
LANDING GEAR SUPPORT BEAM
2533315
FIGURE 7: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
(SHEET 1 OF 4)
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### Page 60

FIGURE 7: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
(SHEET 2 OF 4)
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ALERTALERT

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