# Boeing Alert Service Bulletin 747-57A2360: Revision 1

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2022-1054; AD 2022-24-15 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: SB-747-57A2360 Rev 01
- Pages: 206
- PDF: https://openairdocs.org/files/sha256/02/05/02052d1e45126a51f2ea6801663746a376ec33c58c1611fcf585a16c59ef7f5b
- Page: https://openairdocs.org/service-documents/boeing/747-57a2360/file/02052d1e4512

## Text

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### Page 1

Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-57A2360
Original Issue: January 20, 2017
Revision 1: February 09, 2022
ATA System: 5715
SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement
EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations
(EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for
export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per
Supp.1 to Part 740 of the EAR.
9E991ECCN:
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Unpublished Work.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.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
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Table of Contents
Revision Transmittal Sheet ............................................ 5
S u m m a r y  ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 5
A . E f f e c t i v i t y  ............................................... 1 5
1. Airplanes ............................................ 1 5
2 . S p a r e s  A f f e c t e d  ........................................ 1 9
B. Concurrent Requirements ...................................... 1 9
C. Reason ................................................ 1 9
D. Description .............................................. 2 0
E. Compliance .............................................. 2 3
F . A p p r o v a l  ............................................... 7 8
G. Manpower .............................................. 7 9
H. Weight and Balance Changes .................................... 8 1
I. Electrical Load Data ......................................... 8 1
J . R e f e r e n c e s  .............................................. 8 1
1. Existing Data: ......................................... 8 1
2. Data Supplied with this Service Bulletin: ........................... 8 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 8 2
K. Publications Affected ........................................ 8 2
L. Interchangeability and Intermixability of Parts ........................... 8 2
M. Software Accomplishment Summary ................................ 8 2
2. MATERIAL INFORMATION ........................................ 8 3
A. Material - Price and Availability ................................... 8 3
B. Industry Support Information .................................... 8 3
C. Parts Necessary for Each Airplane ................................. 8 3
1 . K i t s / P a r t s  ............................................ 8 3
2. Parts and Materials Supplied by the Operator ........................ 8 3
3. Parts Modified and Reidentified ................................ 8 5
4. Parts Removed and Not Replaced .............................. 8 5
D. Parts Necessary to Change Spares ................................. 8 5
E. Special Tooling - Price and Availability ............................... 8 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 8 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 8 7
A. GENERAL INFORMATION ..................................... 8 7
B. WORK INSTRUCTIONS ....................................... 8 9
FIGURE 1: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN ................. 9 6
FIGURE 2: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
.................................................. 9 8
FIGURE 3: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - REMOVAL
................................................. 1 0 2
FIGURE 4: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF FUSE PIN . 106
F I G U R E  5 : D E L E T E D........................................... 1 0 8
FIGURE 6: LEFT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG - INSTALLATION
................................................. 1 0 9
FIGURE 7: RIGHT WING - LANDING GEAR SUPPORT BEAM - FUSE PIN GREASE PLUG -
INSTALLATION ........................................ 1 1 3
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FIGURE 8: ULTRASONIC (UT) INSPECTION OF FUSE PIN ...................... 1 1 7
APPENDIX A: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 1 [Group 8] ..... 1 1 9
APPENDIX B: JACKING PROCEDURE FOR FUSE PIN REMOVAL [Group 1-8] ............. 1 2 8
APPENDIX C: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 2 [Group 3] ..... 1 2 9
APPENDIX D: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 3 [Group 3] ..... 1 4 3
APPENDIX E: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 4 [Group 9] ..... 1 5 4
APPENDIX F: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 5 [Group 8] ..... 1 5 9
APPENDIX G: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 6 [Group 9] ..... 1 6 8
APPENDIX H: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 7 [Group 1-2, 5, 7] . 177
APPENDIX I: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 8 [Group 1-2, 5, 7] . 183
APPENDIX J: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 9 [Group 4, 6] .... 1 8 4
APPENDIX K: LOGIC DIAGRAM FOR PARAGRAPH 1.E., COMPLIANCE TABLE 10 [Group 4, 6] . . . 195
APPENDIX L: JACKING PROCEDURE FOR FUSE PIN REMOVAL [Group 9] .............. 2 0 6
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 747-57A2360Original Issue: January 20, 2017
Revision 1: February 09, 2022
ATA System: 5715
SUBJECT: WINGS - Landing Gear Support Beam - Fuse Pin - Inspection and Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-18-05 is related to this service bulletin.
The effective date of AD 2017-18-05 is October 5, 2017.
The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service
bulletin mandatory.
Effects of this Revision on airplanes on which Original Issue was previously done:
Airplanes in groups 1-8 with CRES fuse pin installed requires ultrasonic testing (UT) inspection when performing
surface HFEC inspection of fuse pin and airplanes with Alloy Steel fuse pin installed requires replacement with
new Alloy Steel fuse pin.
Airplanes with line numbers 1308-1308 1313-1313 1315-1315 1317-1318 1320-1321 1326-1326 1328-1331
1338-1338 1340-1341 1344-1344 1347-1347 1350-1350 1361-1361 1365-1365 1368-1368 1375-1377 1380-1383
1386-1387 1389-1389 1391-1392 1395-1395 1398-1400 1402-1402 1404-1404 1409-1409 1413-1417 1419-1419
were moved from Group 3 to Group 8 of this service bulletin effectivity.
Airplanes with line numbers 1420-1574 were added to Group 9 of this service bulletin effectivity.
REASON FOR REVISION
This revision is sent to add 747-8/-8F airplanes, with 115U8227-1 fuse pins installed in production, to the effectivity
of this service bulletin and revise the service bulletin effectivity for 747-400/-400F airplanes. 747-8/-8F airplanes
have a similar fuse pin in the same location as on the 747-400. Analysis shows these fuse pins to be susceptible
to fatigue cracks on the inner and outer surfaces.
The data given in Information Notice 747-57A2360 IN 01 is included in this revision.
These sections were changed:
1. Summary, Background, added new 747-8 information and Boeing Service Related Problem (SRP).
2. Summary, Action, added ultrasonic testing (UT) inspection.
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3. Summary, Effectivity, statement updated.
4. Summary, Compliance, added information and Federal Aviation Authority (FAA) Airworthiness Directive
(AD) reference.
5. Paragraph 1.A.1., Airplanes, added airplanes, new group and new configurations.
6. Paragraph 1.C., Reason, added Revision 1 information and Boeing Service Related Problem (SRP).
7. Paragraph 1.D., Description, added ultrasonic testing (UT) inspection.
8. Paragraph 1.E., Compliance, added FAA AD reference and logic diagram information.
9. Paragraph 1.E., Compliance Tables 1-10, revised compliance for groups 1-8, added new compliance
for new airplanes, and UT inspection added.
10. Paragraph 1.F., Approval, added FAA AD Alternative Method of Compliance statement.
11. Paragraph 1.G., Manpower, changed for new work.
12. Paragraph 1.J., References, added references.
13. Paragraph 2.C.2., Parts and Materials Supplied by the Operator, updated and added additional tables
for new airplanes.
14. Paragraph 3.A., General Information, revised information.
15. Paragraph 3.B., Work Instructions, changed work instructions to include new UT inspection, added
information and applicability.
16. Figure 1: Changed illustration inspection area.
17. Figure 2: Added AMM procedure.
18. Figure 3: Added AMM procedure.
19. Figure 4: Changed HFEC inspection requirements.
20. Figure 5: Deleted.
21. Figure 6: Added AMM procedure.
22. Figure 7: Added AMM procedure.
23. Figure 8: Added new UT inspection.
24. Appendix A: Added applicability and revised logic diagram.
25. Appendix B: Added applicability.
26. Appendix C-G: Added new logic diagram.
27. Appendix G: Added applicability and jacking information.
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The data given in Information Notice 747-57A2360 IN 01 is included in this revision.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
January 20, 2017Original Issue:
February 09, 2022Revision 1:
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Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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Commercial 
Airplanes
747
Service Bulletin
ALERT
SummaryNumber: 747-57A2360Original Issue: January 20, 2017
Revision 1: February 09, 2022
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. 747-8/-8F airplanes have a similar fuse pin in the same location as on the 747-400. Analysis shows these
fuse pins to be susceptible to fatigue cracks on the inner surface of the fuse pins, as well as the outer surface
originating at the lubrication hole. Due to potential cracks originating at the lubrication hole, ultrasonic inspection
(UT) is required in addition to the surface HFEC inspection of fuse pin.
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) 747-8-57-0329 is related to this service bulletin.
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.
Boeing Fleet Team Digest (FTD) 747 FTD 57-18002 is related to this service bulletin.
Export Controlled ECCN: 9E991
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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
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 (PRR 86901-2RS)
Do one of the following options and repeat OPTION 1, OPTION 2, OPTION 3, or OPTION 4 thereafter:
Group 1-6, 8-9:
OPTION 1: NEW CRES FUSE PIN INSTALLATION
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 CRES fuse pin.
3. Close access.
Group 1-7:
OPTION 2: NEW STEEL ALLOY FUSE PIN INSTALLATION
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 steel alloy fuse pin.
3. Close access.
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Group 1-6, 8-9:
OPTION 3: 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 new or serviceable CRES fuse pin.
b. If any crack is found, install a new or serviceable CRES fuse pin.
3. Close access.
Group 1-6, 8-9:
OPTION 4: SURFACE HIGH-FREQUENCY EDDY CURRENT (HFEC) AND ULTRASONIC TESTING (UT)
INSPECTION OF FUSE PIN
1. Get access to the fuse pin.
NOTE: Jacking of the airplane is not necessary to do a surface HFEC and UT inspection of the fuse
pin as removal is not necessary.
2. Do a surface HFEC and UT 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 or serviceable CRES fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
3. Close access.
Group 1-6, 8-9:
OPTION 5: SERVICEABLE CRES FUSE PIN INSTALLATION
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
2. Install serviceable CRES fuse pin.
3. Close access.
EFFECTIVITY
All 747-100/-100B/-100B SUD/-200B/-200C/-200F/-300/-400/-400D/-400F/747SP/747SR/-8/-8F Airplanes. Refer
to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
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COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-18-05 is related to this service bulletin.
The effective date of AD 2017-18-05 is October 5, 2017.
The Federal Aviation Administration (FAA) will possibly release an additional 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: NEW CRES FUSE PIN INSTALLATION
Elapsed HoursTotal Task HoursAirplanes
10.3045.50All airplanes
OPTION 2: NEW STEEL ALLOY FUSE PIN INSTALLATION
Elapsed HoursTotal Task HoursAirplanes
10.3045.50All airplanes
OPTION 3: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
Elapsed HoursTotal Task HoursAirplanes
12.3047.50All airplanes
OPTION 4: SURFACE HIGH-FREQUENCY EDDY CURRENT (HFEC) AND ULTRA-
SONIC TESTING (UT) INSPECTION OF FUSE PIN
Elapsed HoursTotal Task HoursAirplanes
10.1010.10All airplanes
OPTION 5: SERVICEABLE CRES FUSE PIN INSTALLATION
Elapsed HoursTotal Task HoursAirplanes
10.3045.50All airplanes
Refer to Paragraph 1.G., Manpower.
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BOEING SERVICE BULLETIN 747-57A2360
ALERT  ALERT
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
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 OPTION 1, OPTION 2, OPTION 3, OPTION 4 OR
OPTION 5 THEREAFTER:
OPTION 1: NEW CRES FUSE PIN INSTALLATION
OPTION 2: NEW STEEL ALLOY FUSE PIN INSTALLATION
OPTION 3: MAGNETIC PARTICLE INSPECTION (MPI) OF FUSE PIN
OPTION 4: SURFACE HIGH FREQUENCY EDDY CURRENT (HFEC) AND ULTRASONIC TESTING (UT)  2533095
INSPECTION OF FUSE PIN
OPTION 5: SERVICEABLE CRES FUSE PIN INSTALLATION
Original Issue: January 20, 2017
Revision 1: February 09, 2022  747-57A2360
Export Controlled ECCN: 9E991
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Commercial 
Airplanes
747
Service Bulletin
ALERT
Number: 747-57A2360
Original Issue: January 20, 2017
Revision 1: February 09, 2022
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 bulletin is applicable to 747-8, 747-8F, 747-100, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, 747SR Airplane(s), line
number(s) 1-1574 in 9 Group(s). Where the effectivity is presented with hyphens between line
numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers 1-9 means
line numbers 1 through 9 inclusive.
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 non-ER 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
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DESCRIPTIONCONFIGURATIONGROUP
747-400 airplanes with 65B11261-3 fuse pins installed in production.-6
747SP airplanes with 65B19191-1 fuse pins installed in production.-7
747-400/-400F ER airplanes with 65B11261-6 fuse pins installed in
production.
-8
747-8/-8F airplanes with 115U8227-1 fuse pins installed in production.-9
Airplane Models:
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, 747-8, 747-8F, 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
GroupVariable Number
1RA671 - RA677
1RA701 - RA702
1RA721 - RA725
2RA726 - RA731
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
GroupVariable Number
9RC001 - RC009
9RC021 - RC040
9RC051 - RC060
9RC066 - RC072
9RC076 - RC077
9RC501 - RC514
9RC521 - RC528
9RC531 - RC541
9RC546 - RC566
9RC571 - RC582
9RC601 - RC610
9RC641 - RC644
9RC651 - RC652
9RC661
9RC671 - RC674
9RC681 - RC696
9RC701 - RC704
1RD001 - RD004
1RD021 - RD022
1RD041 - RD045
2RD046 - RD059
1RD071 - RD072
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GroupVariable Number
2RD081 - RD083
2RD091 - RD092
1RD101 - RD104
1RD121
2RD122 - RD127
1RD131
2RD132 - RD144
2RD166 - RD167
2RD171 - RD172
2RD181 - RD183
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
GroupVariable Number
2RD561
2RD571
2RD581 - RD583
2RD591 - RD593
1RD601 - RD602
2RD603 - RD607
1RD621 - RD623
1RD641
2RD642 - RD649
2RD651 - RD659
2RD661
2RD671
1RD681
2RD682
2RD691 - RD692
2RD701 - RD702
2RD721 - RD722
2RD741 - RD742
2RD751 - RD755
2RD761
2RD771 - RD775
2RD781 - RD783
2RD791 - RD792
2RE001
8RF001 - RF006
7RG001 - RG009
7RG091
7RG095
7RG101 - RG104
7RG121 - RG126
7RG141 - RG142
7RG161 - RG164
7RG171 - RG174
GroupVariable Number
7RG191 - RG193
7RG211 - RG213
7RG221 - RG222
7RH101 - RH102
7RH111 - RH112
7RH121 - RH122
1RJ131 - RJ133
1RJ151
2RJ152
1RJ301 - RJ302
2RJ303
2RJ321 - RJ322
2RJ331 - RJ333
4RL401 - RL402
3RL403
4RL411 - RL419
3RL420 - RL436
8RL451 - RL456
3RL461 - RL462
3RL471 - RL481
3RL491 - RL492
3RL501 - RL502
8RL511 - RL516
8RL521 - RL522
8RL531 - RL534
3RL551
3RL561 - RL568
8RL571 - RL572
8RL576 - RL577
8RL579
8RL581 - RL586
4RL651 - RL654
3RL655
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
17 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 18

GroupVariable Number
8RL671 - RL675
8RL681 - RL684
4RL751
3RL752
4RM001 - RM007
4RM010 - RM013
4RM021 - RM024
4RM026 - RM029
3RM030
4RM036 - RM045
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
GroupVariable Number
3RM441 - RM443
3RM445
4RM801 - RM803
4RM811 - RM813
4RM851 - RM858
3RM859
4RM861 - RM862
3RM863
4RM871 - RM876
3RM877 - RM878
8RM879 - RM880
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
GroupVariable Number
2RR344 - RR345
2RR361 - RR362
2RR421 - RR422
2RR431 - RR432
2RR441
5RR442
5RR451
2RR501 - RR504
2RR521
5RR522
5RR526
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
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
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18 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 19

GroupVariable Number
2RS311 - RS320
2RS331 - RS333
2RS341 - RS342
2RS699
2RS701 - RS703
2RS711 - RS713
2RS721 - RS722
2RS731 - RS732
2RS741 - RS743
2RS751 - RS752
2RS761
5RS762
2RS771
2RS781
5RS782
2RS786
4RT001 - RT014
4RT021 - RT022
4RT031 - RT035
4RT041 - RT047
4RT061
4RT071 - RT075
GroupVariable Number
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
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.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
19 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 20

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. 747-8/-8F airplanes have a similar fuse pin
in the same location as on the 747-400. Analysis shows these fuse pins to be susceptible to fatigue
cracks on the inner surface of the fuse pins, as well as the outer surface originating at the lubrication
hole.
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) 747-8-57-0329 is related to this service bulletin.
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.
Boeing Fleet Team Digest (FTD) 747 FTD 57-18002 is related to this service bulletin.
Revision 1 is sent to add 747-8/-8F airplanes, with 115U8227-1 fuse pins installed in production, to the
effectivity of this service bulletin and revise the service bulletin effectivity for 747-400/-400F airplanes.
747-8/-8F airplanes have a similar fuse pin in the same location as on the 747-400. Analysis shows
these fuse pins to be susceptible to fatigue cracks on the inner and outer surfaces.
The data given in Information Notice 747-57A2360 IN 01 is included in this revision.
D. Description
Do one of the following options and repeat OPTION 1, OPTION 2, OPTION 3, or OPTION 4 thereafter:
Group 1-6, 8-9:
OPTION 1: NEW CRES FUSE PIN INSTALLATION
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 CRES fuse pin.
3. Close access.
Group 1-7:
OPTION 2: NEW STEEL ALLOY FUSE PIN INSTALLATION
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 steel alloy fuse pin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 21

3. Close access.
Group 1-6, 8-9:
OPTION 3: 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 new or serviceable CRES fuse pin.
b. If any crack is found, install a new or serviceable CRES fuse pin.
3. Close access.
Group 1-6, 8-9:
OPTION 4: SURFACE HIGH-FREQUENCY EDDY CURRENT (HFEC) AND ULTRASONIC TESTING
(UT) INSPECTION OF FUSE PIN
1. Get access to the fuse pin.
NOTE: Jacking of the airplane is not necessary to do a surface HFEC and UT inspection of the
fuse pin as removal is not necessary.
2. Do a surface HFEC and UT 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 or serviceable CRES fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
3. Close access.
Group 1-6, 8-9:
OPTION 5: SERVICEABLE CRES FUSE PIN INSTALLATION
1. Get access and remove the fuse pin.
NOTE: Jacking of the airplane is necessary to remove and replace the fuse pin.
2. Install serviceable CRES fuse pin.
3. Close access.
Effects of this Revision on airplanes on which Original Issue was previously done:
Airplanes in groups 1-8 with CRES fuse pin installed requires ultrasonic testing (UT) inspection when
performing surface HFEC inspection of fuse pin and airplanes with Alloy Steel fuse pin installed requires
replacement with new Alloy Steel fuse pin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
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21 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 22

Airplanes with line numbers 1308-1308 1313-1313 1315-1315 1317-1318 1320-1321 1326-1326
1328-1331 1338-1338 1340-1341 1344-1344 1347-1347 1350-1350 1361-1361 1365-1365 1368-1368
1375-1377 1380-1383 1386-1387 1389-1389 1391-1392 1395-1395 1398-1400 1402-1402 1404-1404
1409-1409 1413-1417 1419-1419 were moved from Group 3 to Group 8 of this service bulletin effectivity.
Airplanes with line numbers 1420-1574 were added to Group 9 of this service bulletin effectivity.
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, 8:
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
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
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BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 23

Group 6:
Affected Maintenance Zones
ZoneModel
572, 672747-400
Group 7:
Affected Maintenance Zones
ZoneModel
572, 672747SP
Group 9:
Affected Maintenance Zones
ZoneModel
572, 672747-8, 747-8F
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-18-05 is related to this service
bulletin. The effective date of AD 2017-18-05 is October 5, 2017.
The Federal Aviation Administration (FAA) will possibly release an additional 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, APPENDIX C, APPENDIX D, APPENDIX E, APPENDIX F and APPENDIX G.
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 Tables 1 through 10, in
accordance with Paragraph 3. Accomplishment Instructions.
NOTE: Compliance Times are based on fuse pin flight cycles and fuse pin flight hours, and not airplane
flight cycles and flight hours.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
23 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 24

Group 8:
Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. 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 CRES FUSE PIN
INSTALLATION.
Airplanes with original fuse
pins that have not per-
formed inspection or re-
placement in accordance
with the original issue of
this service bulletin.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK
FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK FOR ANY
CRACK.
-Whichever occurs later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK FOR ANY
CRACK.
1. Before 12,000 total fuse pin
flight cycles or 115,000 total fuse
pin flight hours, whichever occurs
first.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. Within 24
months or 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin, whichever
occurs first.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 25

Group 8:
Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. 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 CRES FUSE PIN
INSTALLATION.
Airplanes with replaced
fuse pins with new or
known flight cycles on the
fuse pin that have not per-
formed inspection or re-
placement in accordance
with the original issue of
this service bulletin.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK
FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK FOR ANY
CRACK.
-Whichever occurs later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK FOR ANY
CRACK.
1. Before 12,000 total fuse pin
flight cycles or 115,000 total fuse
pin flight hours, whichever occurs
first.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. Within 24
months or 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin, whichever
occurs first.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 26

Group 8:
Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
PART 3: MAGNETIC PAR-
TICLE INSPECTION OF
FUSE PIN in accordance
with the original issue of
this service bulletin.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK FOR ANY
CRACK.
-Whichever occurs later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
1. Within 2,400 fuse pin flight cy-
cles after the last magnetic particle
inspection.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
-Within 2,400 fuse pin flight cycles
after the last magnetic particle in-
spection.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 27

Group 8:
Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 1,200
fuse pin flight
cycles after the
last surface
HFEC inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
PART 4: SURFACE HFEC
INSPECTION OF FUSE
PIN FOR ANY CRACK in
accordance with the origi-
nal issue of this service
bulletin.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
-Whichever occurs later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
1. Within 1,200 fuse pin flight cy-
cles after the last surface HFEC
inspection.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
-Within 1,200 fuse pin flight cycles
after the last surface HFEC inspec-
tion.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
-At the times specified in table 5.Do the actions specified
in Table 5.
CONDITION 1: NO
CRACK FOUND DURING
OPTION 3: PART 3: MAG-
NETIC PARTICLE INSPEC-
TION.
-At the times specified in table 5.Do the actions specified
in Table 5.
CONDITION 2: NO
CRACK FOUND DURING
OPTION 4: PART 4: SUR-
FACE HFEC INSPECTION
AND PART 7: ULTRASON-
IC TESTING (UT).
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
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27 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 28

Group 8:
Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):
Do PART 5: NEW CRES
FUSE PIN INSTALLA-
TION.
CONDITION 3: ANY
CRACK FOUND.
-At the times specified in table 5.OPTION 1 (ACTION 2):
Do the actions specified
in Table 5.
-Before further flight.OPTION 5 (ACTION 1):
Do PART 8: SERVICE-
ABLE CRES FUSE PIN
INSTALLATION.
-At the times specified in table 5.OPTION 5 (ACTION 2):
Do the actions specified
in Table 5.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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28 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 29

Group 8:
Table 1: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-At the times specified in table 5.Do the actions specified
in Table 5.
CONDITION 4: OPTION 1:
PART 5: NEW CRES
FUSE PIN INSTALLATION
ACCOMPLISHED.
-At the times specified in table 5.Do the actions specified
in Table 5.
CONDITION 6: OPTION 5:
PART 8: SERVICEABLE
CRES FUSE PIN INSTAL-
LATION ACCOMPLISHED.
Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. 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 CRES FUSE PIN
INSTALLATION.
Airplanes with original fuse
pin that have not performed
inspection or replacement
in accordance with the
original issue of this service
bulletin.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK
FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK FOR ANY
CRACK.
-Whichever occurs later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK FOR ANY
CRACK.
1. Before 12,000 total fuse pin
flight cycles or 115,000 total fuse
pin flight hours, whichever occurs
first.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
29 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 30

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. Within 24
months or 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin, whichever
occurs first.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
-Before 80,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
Whichever oc-
curs later:
1. Before
10,000 total
fuse pin flight
cycles.
2. Before
12,000 total
fuse pin flight
cycles or within
24 months after
the Revision 1
date of this ser-
vice bulletin,
whichever oc-
curs first.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with replaced
fuse pin part numbers
65B11261-5 with new or
known flight cycles on the
fuse pin that have not per-
formed inspection or re-
placement in accordance
with the original issue of
this service bulletin.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
30 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 31

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. 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 CRES FUSE PIN
INSTALLATION.
Airplanes with replaced
fuse pin part number
65B11261-6 with new or
known flight cycles on the
fuse pin that have not per-
formed inspection or re-
placement in accordance
with the original issue of
this service bulletin.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK
FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK FOR ANY
CRACK.
-Whichever occurs later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK FOR ANY
CRACK.
1. Before 12,000 total fuse pin
flight cycles or 115,000 total fuse
pin flight hours, whichever occurs
first.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
At the later of:
1. Before
12,000 total
fuse pin flight
cycles.
or
2. Within 24
months or 1,200
flight cycles af-
ter the original
issue date of
this service bul-
letin, whichever
occurs first.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
31 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 32

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with fuse pin part
number 65B11261-5 in-
stalled that performed
PART 3: MAGNETIC PAR-
TICLE INSPECTION OF
FUSE PIN in accordance
with the original issue of
this service bulletin.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
--Within 1,200
fuse pin flight
cycles after the
last surface
HFEC inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with fuse pin part
number 65B11261-5 in-
stalled that performed
PART 4: SURFACE HFEC
INSPECTION OF FUSE
PIN FOR ANY CRACK in
accordance with the origi-
nal issue of this service
bulletin.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
32 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 33

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
Before 12,000
total fuse pin
flight cycles.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with new fuse pin
part number 65B11261-6
installed in accordance with
the original issue of this
service bulletin. OPTION 2: Do PART 6:NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
-Whichever Occurs Later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
1. Before 12,000 total fuse pin
flight cycles or 115,000 total fuse
pin flight hours, whichever occurs
first.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
-Before 115,000
total fuse pin
flight hours or
within 24
months after the
Revision 1 date
of this service
bulletin,
whichever oc-
curs later.
Before 12,000
total fuse pin
flight cycles.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
33 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 34

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with fuse pin part
number 65B11261-6 in-
stalled and performed
PART 3: MAGNETIC PAR-
TICLE INSPECTION OF
FUSE PIN in accordance
with the original issue of
this service bulletin.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
-Whichever Occurs Later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
1. Within 2,400 fuse pin flight cy-
cles after the last magnetic particle
inspection.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
--Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
34 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 35

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 1,200
fuse pin flight
cycles after the
last surface
HFEC inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with fuse pin part
number 65B11261-6 in-
stalled and performed
PART 4: SURFACE HFEC
INSPECTION OF FUSE
PIN FOR ANY CRACK in
accordance with the origi-
nal issue of this service
bulletin.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
-Whichever Occurs Later:OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
1. Within 1,200 fuse pin flight cy-
cles after the last surface HFEC
inspection.
2. Within 24 months after the Re-
vision 1 date of this service bul-
letin.
--Within 1,200
fuse pin flight
cycles after the
last surface
HFEC inspec-
tion.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
-At the times specified in table 3.Do the actions specified
in Table 3.
CONDITION 1: NO
CRACK FOUND DURING
OPTION 3: PART 3: MAG-
NETIC PARTICLE INSPEC-
TION.
-At the times specified in table 3.Do the actions specified
in Table 3.
CONDITION 2: NO
CRACK FOUND DURING
OPTION 4: PART 4: SUR-
FACE HFEC INSPECTION
AND PART 7: ULTRASON-
IC TESTING (UT).
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
35 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 36

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):
Do PART 5: NEW CRES
FUSE PIN INSTALLA-
TION.
CONDITION 3: ANY
CRACK FOUND.
-At the times specified in table 3.OPTION 1 (ACTION 2):
Do the actions specified
in Table 3.
-Before further flight.OPTION 2 (ACTION 1):
Do PART 6: NEW STEEL
ALLOY FUSE PIN IN-
STALLATION.
-At the times specified in table 3.OPTION 2 (ACTION 2):
Do the actions specified
in Table 3.
-Before further flight.OPTION 5 (ACTION 1):
Do PART 8: SERVICE-
ABLE CRES FUSE PIN
INSTALLATION
-At the times specified in table 3.OPTION 5 (ACTION 2):
Do the actions specified
in Table 3.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
36 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 37

Group 3:
Table 2: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
-At the times specified in table 3.Do the actions specified
in Table 3.
CONDITION 4: OPTION 1:
PART 5: NEW CRES
FUSE PIN INSTALLATION
ACCOMPLISHED.
-At the times specified in table 3.Do the actions specified
in Table 3.
CONDITION 5: OPTION 2:
PART 6: NEW STEEL AL-
LOY FUSE PIN INSTALLA-
TION ACCOMPLISHED.
-At the times specified in table 3.Do the actions specified
in Table 3.
CONDITION 6: OPTION 5:
PART 8: SERVICEABLE
CRES FUSE PIN INSTAL-
LATION ACCOMPLISHED.
Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours.
Before 12,000
total fuse pin
flight cycles.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with new fuse pin
installed by OPTION 1 in
accordance with Revision
1 of this service bulletin. OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
37 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 38

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
-Before 80,000
total fuse pin
flight hours.
Before 10,000
total fuse pin
flight cycles.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with new fuse pin
installed by OPTION 2 in
accordance with Revision
1 of this service bulletin. OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
--Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
OPTION 3: MAGNETIC
PARTICLE INSPECTION
OF FUSE PIN in accor-
dance with Revision 1 of
this service bulletin and NO
CRACK FOUND.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
38 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 39

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 1,200
fuse pin flight
cycles after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
OPTION 4: SURFACE
HIGH FREQUENCY EDDY
CURRENT (HFEC) AND
ULTRASONIC TESTING
(UT) INSPECTION in accor-
dance with Revision 1 of
this service bulletin and NO
CRACK FOUND.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
39 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 40

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 2,400
fuse pin flight
cycles after
SERVICEABLE
CRES FUSE
PIN INSTALLA-
TION.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with serviceable
fuse pin installed by OP-
TION 5 in accordance with
Revision 1 of this service
bulletin. OPTION 2: Do PART 6:NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
40 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 41

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 2,400 fuse pin flight cycles
after the last magnetic particle in-
spection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 1: NO
CRACK FOUND DURING
OPTION 3: PART 3: MAG-
NETIC PARTICLE INSPEC-
TION. (a)Within 2,400 fuse pin flight cyclesafter the last magnetic particle in-
spection.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
2,400 fuse pin
flight cycles. (b)
-OPTION 3: Repeat PART
3: MAGNETIC PARTI-
CLE INSPECTION OF
FUSE PIN FOR ANY
CRACK FOR ANY
CRACK.
(a)-Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
(a)Within 2,400 fuse pin flight cycles
after the last magnetic particle in-
spection.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
41 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 42

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 1,200 fuse pin flight cycles
after the last surface HFEC and
ultrasonic testing (UT) inspection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 2: NO
CRACK FOUND DURING
OPTION 4: PART 4: SUR-
FACE HFEC INSPECTION
AND PART 7: ULTRASON-
IC TESTING (UT).
(a)Within 1,200 fuse pin flight cycles
after the last surface HFEC and
ultrasonic testing (UT) inspection.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
(a)Within 1,200 fuse pin flight cycles
after the last surface HFEC and
ultrasonic testing (UT) inspection.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
1,200 fuse pin
flight cycles. (b)
--OPTION 4 (ACTION 1):
Repeat PART 4: SUR-
FACE HFEC INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 4 (ACTION 2):
Repeat PART 7: ULTRA-
SONIC TESTING IN-
SPECTION OF FUSE
PIN FOR ANY CRACK.
(a)Within 1,200 fuse pin flight cycles
after the last surface HFEC and
ultrasonic testing (UT) inspection.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
(a)Before further flight.OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 3: ANY
CRACK FOUND.
(a)Before further flight.OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
(a)Before further flight.OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
42 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 43

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
12,000 fuse pin
flight cycles or
115,000 fuse pin
flight hours,
whichever occurs
first. (b)
-OPTION 1: Repeat PART
5: NEW CRES FUSE PIN
INSTALLATION.
CONDITION 4: OPTION 1:
PART 5: NEW CRES
FUSE PIN INSTALLATION
ACCOMPLISHED.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 12,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 12,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 12,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 12,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 44

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 80,000
fuse pin flight
hours after
NEW STEEL
ALLOY FUSE
PIN INSTALLA-
TION.
Within 10,000
fuse pin flight
cycles after
NEW STEEL
ALLOY FUSE
PIN INSTALLA-
TION.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 5: OPTION 2:
PART 6: NEW STEEL AL-
LOY FUSE PIN INSTALLA-
TION ACCOMPLISHED.
10,000 fuse pin
flight cycles or
80,000 fuse pin
flight hours,
whichever occurs
first. (b)
-OPTION 2: Repeat PART
6: NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
(a)Within 80,000
fuse pin flight
hours after
NEW STEEL
ALLOY FUSE
PIN INSTALLA-
TION.
Within 10,000
fuse pin flight
cycles after
NEW STEEL
ALLOY FUSE
PIN INSTALLA-
TION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
44 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 45

Group 3:
Table 3: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Boeing Recommended
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 2,400 fuse pin flight cycles
after SERVICEABLE CRES FUSE
PIN INSTALLATION.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 6: OPTION 5:
PART 8: SERVICEABLE
CRES FUSE PIN INSTAL-
LATION ACCOMPLISHED. (a)Within 2,400 fuse pin flight cycles
after SERVICEABLE CRES FUSE
PIN INSTALLATION.
OPTION 2: Do PART 6:
NEW STEEL ALLOY
FUSE PIN INSTALLA-
TION.
(a)Within 2,400 fuse pin flight cycles
after SERVICEABLE CRES FUSE
PIN INSTALLATION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
(a)-Within 2,400
fuse pin flight
cycles after
SERVICEABLE
CRES FUSE
PIN INSTALLA-
TION.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
2,400 fuse pin
flight cycles. (a)
-OPTION 5: Repeat PART
8: SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
(a) This is not a terminating action. Refer to the applicable condition for further actions.
(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.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
45 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 46

Group 9:
Table 4: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before 1,800 to-
tal fuse pin flight
cycles or within
36 months after
the Revision 1
date of this ser-
vice bulletin,
whichever oc-
curs first.
Before 20,000
total fuse pin
flight cycles or
115,000 total
fuse pin flight
hours, whichev-
er occurs first.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with original fuse
pins.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
46 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 47

Group 9:
Table 4: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before 1,800 to-
tal fuse pin flight
cycles or within
36 months after
the Revision 1
date of this ser-
vice bulletin,
whichever oc-
curs first.
Before 20,000
total fuse pin
flight cycles or
115,000 total
fuse pin flight
hours, whichev-
er occurs first.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with replaced
fuse pins with new or
known flight cycles on the
fuse pin. OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
-At the times specified in table 6.Do the actions specified
in Table 6.
CONDITION 1: NO
CRACK FOUND DURING
OPTION 3: PART 3: MAG-
NETIC PARTICLE INSPEC-
TION.
-At the times specified in table 6.Do the actions specified
in Table 6.
CONDITION 2: NO
CRACK FOUND DURING
OPTION 4: PART 4: SUR-
FACE HFEC INSPECTION
AND PART 7: ULTRASON-
IC TESTING (UT).
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
47 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 48

Group 9:
Table 4: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):
Do PART 5: NEW CRES
FUSE PIN INSTALLA-
TION.
CONDITION 3: ANY
CRACK FOUND.
-At the times specified in table 6.OPTION 1 (ACTION 2):
Do the actions specified
in Table 6.
-Before further flight.OPTION 5 (ACTION 1):
Do PART 8: SERVICE-
ABLE CRES FUSE PIN
INSTALLATION.
-At the times specified in table 6.OPTION 5 (ACTION 2):
Do the actions specified
in Table 6.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
48 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 49

Group 9:
Table 4: Wing Landing Gear Beam End Fitting Fuse Pin - Magnetic Particle Inspection, Surface HFEC
Inspection, Ultrasonic Testing Inspection, and Installation
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-At the times specified in table 6.Do the actions specified
in Table 6.
CONDITION 4: OPTION 1:
PART 5: NEW CRES
FUSE PIN INSTALLATION
ACCOMPLISHED.
-At the times specified in table 6.Do the actions specified
in Table 6.
CONDITION 6: OPTION 5:
PART 8: SERVICEABLE
CRES FUSE PIN INSTAL-
LATION ACCOMPLISHED.
Group 8:
Table 5: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours.
Before 12,000
total fuse pin
flight cycles.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with new fuse pin
installed by OPTION 1 in
accordance with Revision
1 of this service bulletin. OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
49 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 50

Group 8:
Table 5: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
OPTION 3: MAGNETIC
PARTICLE INSPECTION
OF FUSE PIN in accor-
dance with Revision 1 of
this service bulletin and NO
CRACK FOUND.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
--Within 1,200
fuse pin flight
cycles after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
OPTION 4: SURFACE
HIGH FREQUENCY EDDY
CURRENT (HFEC) AND
ULTRASONIC TESTING
(UT) INSPECTION in accor-
dance with Revision 1 of
this service bulletin and NO
CRACK FOUND.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
50 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 51

Group 8:
Table 5: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
--Within 2,400
fuse pin flight
cycles after
SERVICEABLE
CRES FUSE
PIN INSTALLA-
TION.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with serviceable
fuse pin installed by OP-
TION 5 in accordance with
Revision 1 of this service
bulletin. OPTION 3: Do PART 3:MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
51 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 52

Group 8:
Table 5: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 2,400 fuse pin flight cycles
after the last magnetic particle in-
spection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 1: NO
CRACK FOUND DURING
OPTION 3: PART 3: MAG-
NETIC PARTICLE INSPEC-
TION. 2,400 fuse pinflight cycles. (b)-OPTION 3: Repeat PART3: MAGNETIC PARTI-
CLE INSPECTION OF
FUSE PIN FOR ANY
CRACK.
(a)-Within 2,400
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
(a)Within 2,400 fuse pin flight cycles
after the last magnetic particle in-
spection.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
52 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 53

Group 8:
Table 5: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 1,200 fuse pin flight cycles
after the last surface HFEC and
ultrasonic testing (UT) inspection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 2: NO
CRACK FOUND DURING
OPTION 4: PART 4: SUR-
FACE HFEC INSPECTION
AND PART 7: ULTRASON-
IC TESTING (UT).
(a)Within 1,200 fuse pin flight cycles
after the last surface HFEC and
ultrasonic testing (UT) inspection.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
1,200 fuse pin
flight cycles. (b)
--OPTION 4 (ACTION 1):
Repeat PART 4: SUR-
FACE HFEC INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 4 (ACTION 2):
Repeat PART 7: ULTRA-
SONIC TESTING IN-
SPECTION OF FUSE
PIN FOR ANY CRACK.
(a)Within 1,200 fuse pin flight cycles
after the last magnetic particle in-
spection.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
(a)Before further flight.OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 3: ANY
CRACK FOUND.
(a)Before further flight.OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
53 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 54

Group 8:
Table 5: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
12,000 fuse pin
flight cycles or
115,000 fuse pin
flight hours,
whichever occurs
first. (b)
-OPTION 1: Repeat PART
5: NEW CRES FUSE PIN
INSTALLATION.
CONDITION 4: OPTION 1:
PART 5: NEW CRES
FUSE PIN INSTALLATION
ACCOMPLISHED.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 12,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 12,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 12,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
54 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 55

Group 8:
Table 5: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 2,400 fuse pin flight cycles
after SERVICEABLE CRES FUSE
PIN INSTALLATION.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 6: OPTION 5:
PART 8: SERVICEABLE
CRES FUSE PIN INSTAL-
LATION ACCOMPLISHED. (a)Within 2,400 fuse pin flight cycles
after SERVICEABLE CRES FUSE
PIN INSTALLATION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
(a)-Within 2,400
fuse pin flight
cycles after
SERVICEABLE
CRES FUSE
PIN INSTALLA-
TION.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
2,400 fuse pin
flight cycles. (b)
-OPTION 5: Repeat PART
8: SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
(a) This is not a terminating action. Refer to the applicable condition for further actions.
(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.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
55 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 56

Group 9:
Table 6: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Before 115,000
total fuse pin
flight hours.
Before 20,000
total fuse pin
flight cycles.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with new fuse pin
installed by OPTION 1 in
accordance with Revision
1 of this service bulletin. OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
-Within 36,000
fuse pin flight
hours after the
last magnetic
particle inspec-
tion.
Within 7,200
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
OPTION 3: MAGNETIC
PARTICLE INSPECTION
OF FUSE PIN in accor-
dance with Revision 1 of
this service bulletin and NO
CRACK FOUND.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
56 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 57

Group 9:
Table 6: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
-Within 19,500
fuse pin flight
hours after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection
Within 3,900
fuse pin flight
cycles after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes that performed
OPTION 4: SURFACE
HIGH FREQUENCY EDDY
CURRENT (HFEC) AND
ULTRASONIC TESTING
(UT) INSPECTION in accor-
dance with Revision 1 of
this service bulletin and NO
CRACK FOUND.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
-Within 36,000
fuse pin flight
hours after
SERVICEABLE
CRES FUSE
PIN INSTALLA-
TION.
Within 7,200
fuse pin flight
cycles after
SERVICEABLE
CRES FUSE
PIN INSTALLA-
TION.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
Airplanes with serviceable
fuse pin installed by OP-
TION 5 in accordance with
Revision 1 of this service
bulletin. OPTION 3: Do PART 3:MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
57 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 58

Group 9:
Table 6: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 36,000
fuse pin flight
hours after the
last magnetic
particle inspec-
tion.
Within 7,200
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 1: NO
CRACK FOUND DURING
OPTION 3: PART 3: MAG-
NETIC PARTICLE INSPEC-
TION.
7,200 fuse pin
flight cycles or
36,000 fuse pin
flight hours,
whichever occurs
first. (b)
-OPTION 3: Repeat PART
3: MAGNETIC PARTI-
CLE INSPECTION OF
FUSE PIN FOR ANY
CRACK.
(a)Within 36,000
fuse pin flight
hours after the
last magnetic
particle inspec-
tion.
Within 7,200
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
(a)Within 36,000
fuse pin flight
hours after the
last magnetic
particle inspec-
tion.
Within 7,200
fuse pin flight
cycles after the
last magnetic
particle inspec-
tion.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
58 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 59

Group 9:
Table 6: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
(a)Within 19,500
fuse pin flight
hours after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
Within 3,900
fuse pin flight
cycles after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 2: NO
CRACK FOUND DURING
OPTION 4: PART 4: SUR-
FACE HFEC INSPECTION
AND PART 7: ULTRASON-
IC TESTING (UT).
(a)Within 19,500
fuse pin flight
hours after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
Within 3,900
fuse pin flight
cycles after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
3,900 fuse pin
flight cycles or
19,500 fuse pin
flight hours,
whichever occurs
first. (b)
--OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
(a)Within 19,500
fuse pin flight
hours after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
Within 3,900
fuse pin flight
cycles after the
last surface
HFEC and ultra-
sonic testing
(UT) inspection.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
(a)Before further flight.OPTION 1: Do PART 5:
NEW CRES FUSE PIN
INSTALLATION.
CONDITION 3: ANY
CRACK FOUND.
(a)Before further flight.OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
59 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

### Page 60

Group 9:
Table 6: Wing Landing Gear Beam End Fitting Fuse Pin - Post Initial Inspection Actions
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs First)
ActionCondition
20,000 fuse pin
flight cycles or
115,000 fuse pin
flight hours,
whichever occurs
first. (b)
-OPTION 1: Repeat PART
5: NEW CRES FUSE PIN
INSTALLATION.
CONDITION 4: OPTION 1:
PART 5: NEW CRES
FUSE PIN INSTALLATION
ACCOMPLISHED.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 20,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 3: Do PART 3:
MAGNETIC PARTICLE
INSPECTION OF FUSE
PIN FOR ANY CRACK.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 20,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 4 (ACTION 1):
Do PART 4: SURFACE
HFEC INSPECTION OF
FUSE PIN FOR ANY
CRACK.
OPTION 4 (ACTION 2):
Do PART 7: ULTRASON-
IC TESTING INSPEC-
TION OF FUSE PIN FOR
ANY CRACK.
(a)Within 115,000
fuse pin flight
hours after
NEW CRES
FUSE PIN IN-
STALLATION.
Within 20,000
fuse pin flight
cycles after
NEW CRES
FUSE PIN IN-
STALLATION.
OPTION 5: Do PART 8:
SERVICEABLE CRES
FUSE PIN INSTALLA-
TION.
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: January 20, 2017
747-57A2360Revision 1: February 09, 2022
60 of 206
BOEING SERVICE BULLETIN 747-57A2360
ALERTALERT

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