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Commercial
Airplanes 737
Service Bulletin
ALERT
Number: 737-53A1358
Original Issue: April 27, 2017
Revision 1: February 26, 2021
ATA System: 5331
SUBJECT: FUSELAGE - Skin - 0.036 Inch Crown Skin Panels Between S-10L and S-10R, STA
360 to STA 540 and STA 727 to STA 908 - Inspection, Repair and Replacement
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Table of Contents
Revision Transmittal Sheet ............................................ 7
Summary ..................................................... 11
1. PLANNING INFORMATION ........................................ 17
A. Effectivity ............................................... 17
1. Airplanes ............................................ 17
2. Spares Affected ........................................ 24
B. Concurrent Requirements ...................................... 24
C. Reason ................................................ 24
D. Description .............................................. 25
E. Compliance .............................................. 28
F. Approval ............................................... 34
G. Manpower .............................................. 34
H. Weight and Balance Changes .................................... 46
I. Electrical Load Data ......................................... 46
J. References .............................................. 46
1. Existing Data: ......................................... 46
2. Data Supplied with this Service Bulletin: ........................... 47
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 47
K. Publications Affected ........................................ 48
L. Interchangeability and Intermixability of Parts ........................... 48
M. Software Accomplishment Summary ................................ 48
2. MATERIAL INFORMATION ........................................ 49
A. Material - Price and Availability ................................... 49
B. Industry Support Information .................................... 74
C. Parts Necessary for Each Airplane ................................. 74
1. Kits/Parts ............................................ 74
2. Parts and Materials Supplied by the Operator ........................ 98
3. Parts Modified and Reidentified ............................... 101
4. Parts Removed and Not Replaced .............................. 101
D. Parts Necessary to Change Spares ................................ 101
E. Special Tooling - Price and Availability .............................. 101
F. Special Tooling Necessary to do this Service Bulletin ...................... 101
3. ACCOMPLISHMENT INSTRUCTIONS ................................. 103
A. GENERAL INFORMATION .................................... 103
B. WORK INSTRUCTIONS ...................................... 105
FIGURE 1: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 1-2] . . . 131
FIGURE 2: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 3-4] . . . 133
FIGURE 3: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 5] .... 135
FIGURE 4: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 6-7] . . . 137
FIGURE 5: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 8-9] . . . 139
FIGURE 6: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 10-11] . . 141
FIGURE 7: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 12] .... 143
FIGURE 8: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 13] .... 145
FIGURE 9: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 14-16] . . 147
FIGURE 10: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 17] .... 149
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FIGURE 11: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 18] .... 151
FIGURE 12: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 19] .... 153
FIGURE 13: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 20] .... 155
FIGURE 14: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 21] .... 157
FIGURE 15: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 22] . . . 159
FIGURE 16: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 23] . . . 161
FIGURE 17: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 24] . . . 163
FIGURE 18: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 25] . . . 165
FIGURE 19: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 26] . . . 167
FIGURE 20: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 27] . . . 169
FIGURE 21: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 28] . . . 171
FIGURE 22: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 29-31] . . 173
FIGURE 23: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 32-34] . . 175
FIGURE 24: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 35-37] . . 177
FIGURE 25: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 38-39] . . 179
FIGURE 26: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 40] .... 181
FIGURE 27: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 41] .... 183
FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI .............. 185
FIGURE 29: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 1-4] . 191
FIGURE 30: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 5] . 193
FIGURE 31: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 6-7] . 195
FIGURE 32: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 8, 10, 12-14,
17-21] ............................................. 197
FIGURE 33: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 9, 11, 16]
................................................. 199
FIGURE 34: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 15] . 201
FIGURE 35: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727G AND 908 [Group 22-28,
42] ............................................... 203
FIGURE 36: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 29-30,
32-33, 35, 38, 40-41] ..................................... 205
FIGURE 37: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 31, 37]
................................................. 207
FIGURE 38: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 34, 36, 39]
................................................. 209
FIGURE 39: INSPECTION OF CHEM-MILL POCKETS ADJACENT TO CRACK LOCATION ..... 211
FIGURE 40: DAMAGED SKIN REMOVAL ................................. 213
FIGURE 41: CUT SURFACE AND FASTENER HOLES INSPECTION ................. 214
FIGURE 42: INSURANCE CUT AND SURFACE TREATMENT..................... 216
FIGURE 43: CATEGORY C REPAIR INSTALLATION .......................... 218
FIGURE 44: CATEGORY C REPAIR INSPECTION ........................... 222
FIGURE 45: PRE-REPAIR CONVERSION INSPECTION ........................ 223
FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
TEAR STRAP DOUBLERS.................................. 224
FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER,
SOLID FASTENERS AND TEAR STRAP DOUBLERS................... 230
FIGURE 48: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION 1 . . . 236
FIGURE 49: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION 2 . . . 238
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FIGURE 50: SKIN BUTT JOINT INSPECTION AT STA 360 ....................... 240
FIGURE 51: SKIN BUTT JOINT INSPECTION AT STA 540 ....................... 242
FIGURE 52: SKIN BUTT JOINT INSPECTION AT STA 727 ....................... 244
FIGURE 53: SKIN BUTT JOINT INSPECTION AT STA 908 ....................... 246
FIGURE 54: SKIN BUTT JOINT INSPECTION AT STA 500C ...................... 248
FIGURE 55: SKIN BUTT JOINT INSPECTION AT STA 727G ...................... 250
FIGURE 56: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 42] . . . 252
APPENDIX A: LOGIC DIAGRAM FOR TABLE 1 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN BONDED
DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-10L TO S-10R - STA
360 TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO STA 500C
AND 727G TO STA 908 (GROUP 22-28, 42) ........................ 254
APPENDIX B: LOGIC DIAGRAM FOR TABLE 2 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF CATEGORY C REPAIR ......................... 257
APPENDIX C: LOGIC DIAGRAM FOR TABLE 3 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF SERVICE BULLETIN REPAIRS INSTALLED IN ACCORDANCE WITH PART
6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR IN THE ORIGINAL
ISSUE OR ANY REVISION OF THIS SERVICE BULLETIN ................ 259
APPENDIX D: LOGIC DIAGRAM FOR TABLE 4 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN PANEL
REPLACEMENT FROM S-10L TO S-10R - STA 360 TO STA 540 AND STA 727 TO STA 908
(GROUP 1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO STA 908 (GROUP 22-28, 42)
................................................. 261
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS ......................... 262
APPENDIX F: PART DEMAND INTENT ................................... 282
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
BLANK PAGE
Commercial
Airplanes 737
Service Bulletin
ALERT
Revision Transmittal Sheet
Number: 737-53A1358
Original Issue: April 27, 2017
Revision 1: February 26, 2021
ATA System: 5331
SUBJECT: FUSELAGE - Skin - 0.036 Inch Crown Skin Panels Between S-10L and S-10R, STA
360 to STA 540 and STA 727 to STA 908 - Inspection, Repair and Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Service
Bulletin 737-53A1358 Revision 1. The Airworthiness Directive will make the compliance tasks and times given
in Service Bulletin 737-53A1358 Revision 1 mandatory.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-23-02 is related to this Service Bulletin
737-53A1358. The effective date of AD 2017-23-02 is December 20, 2017.
Airplane variable numbers PP150-PP160 and PS751-PS762 were transferred from Group 8 of service bulletin
737-53A1358 Original Issue to Group 16 of this service bulletin effectivity.
Airplane variable numbers PJ301-PJ302 PJ551-PJ551 PM551-PM564 PV021-PV055 PV201-PV203 PV271-PV272
PV281-PV283 PW028-PW028 PW033-PW050 PW052-PW054 PW064-PW068 PW072- PW072 PW094-PW094
PW101-PW102 PW106-PW106 PW118-PW120 PW156-PW157 PW161-PW167 PW201-PW244 PW261-PW261
PW265-PW268 PW278-PW278 PW281-PW281 PW293-PW293 PW296- PW296 PW301-PW327 PW461-PW461
PW463-PW467 PW504-PW504 PW564-PW564 PW614-PW620 PW661-PW662 PW681-PW683 PW701-PW701
PW711-PW717 PW741-PW742 PW761-PW761 were transferred from Group 22 of service bulletin 737-53A1358
Original Issue to new Group 42 of this service bulletin effectivity.
Effects of this Revision on airplanes on which the original issue was previously done:
ActionConditionGroup
Do service bulletin 737- 53A1358 Revi-
sion 1 PART 1: CROWN SKIN CHEM-
MILL STEP INTERNAL/EXTERNAL NDI.
Airplanes that have accomplished PART
1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NDI in accor-
dance with service bulletin 737-53A1358
original issue.
All Airplanes.
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REASON FOR REVISION
This revision is sent to make changes described in the Table below:
NOTE: For all Groups the initial inspection threshold, initial repeat, initial grace period and methods remain
unchanged.
ReasonGroup
The original issue inspection figures show incorrect chem-mill locations.
Changes are made to some of the inspection locations.
Airplanes in Group 32, 33, 34, 36,
38.
The original issue incorrectly identified some airplanes in Group 8.
Changes are made to transfer the affected airplanes to Group 16. (a)
Some of the airplanes in Group 8.
The original issue incorrectly identified some airplanes in Group 22.
Changes are made to transfer affected airplanes to new Group 42. (b)
Some of the airplanes in Group 22.
The original issue inspection figures show incorrect chem-mill locations.
Changes are made to inspection locations between STA 727 and STA
908.
Airplanes in Group 5.
The original issue inspection figures show incorrect chem-mill locations.
Changes are made to inspection locations between S-4 and S-5.
Airplanes in Group 1- 42.
(a) Airplane variable numbers PP150-PP160 and PS751-PS762 were transferred from Group 8 of service
bulletin 737-53A1358 Original Issue to Group 16 of this service bulletin effectivity.
(b) Airplane variable numbers PJ301-PJ302 PJ551-PJ551 PM551-PM564 PV021-PV055 PV201-PV203
PV271-PV272 PV281-PV283 PW028-PW028 PW033-PW050 PW052-PW054 PW064-PW068 PW072-
PW072 PW094-PW094 PW101-PW102 PW106-PW106 PW118-PW120 PW156-PW157 PW161-PW167
PW201-PW244 PW261-PW261 PW265-PW268 PW278-PW278 PW281-PW281 PW293-PW293 PW296-
PW296 PW301-PW327 PW461-PW461 PW463-PW467 PW504-PW504 PW564-PW564 PW614-PW620
PW661-PW662 PW681-PW683 PW701-PW701 PW711-PW717 PW741-PW742 PW761-PW761 were
transferred from Group 22 of service bulletin 737-53A1358 Original Issue to new Group 42 of this service
bulletin effectivity.
These sections were changed:
1. In Summary, Background, updated background statement and added Boeing Service Related Problem
(SRP) and Boeing Fleet Team Digest (FTD).
2. In Summary, Action, added new Group 42 and Group 43.
3. In Summary, Effectivity, added airplane sub-model.
4. In Summary, Compliance, added FAA Airworthiness Directive (AD).
5. In Summary Illustration, added new Group 42.
6. In Paragraph 1.A.1., Airplanes, changed Group Configuration Table.
7. In Paragraph 1.A.1., Airplane Models, changed incorrect effectivities.
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
8. In Paragraph 1.C., Reason, updated reason statement and added references to Boeing Service Related
Problem (SRP) and Boeing Fleet Team Digest (FTD).
9. In Paragraph 1.D., Description, added new Group 42 and 43 and added Effects of this service bulletin
Revision 1 Table.
10. In Paragraph 1.E., Compliance, added FAA Airworthiness Directive and new Group 43 and updated
the Compliance Table 1.
11. In Paragraph 1.F., Approval, updated approval statement.
12. In Paragraph 1.G., Manpower, changed the incorrect bay quantity and Group information in Tables
and added new Tables 46 and 47.
13. In Paragraph 1.J.1., Existing Data, added service bulletin, Boeing Service Related Problem (SRP),
FAA Airworthiness Directive (AD) and Fleet Team Digest (FTD). Changed 737-100/200 Aircraft
Maintenance Manual (AMM) and 737-1000/200 Structural Repair Manual (SRM) references.
14. In Paragraph 1.J.3., Installation Drawings Used in the Preparation of this service bulletin, added drawing
to the Table.
15. In Paragraph 2.A., Material - Price and Availability, updated latest part numbers for Tables and added
Group 42 Table.
16. In Paragraph 2.C.1., Kits/Parts, changed incorrect part number for Group 1 Table, updated latest part
numbers for Group 18-21, 31 Tables and added Group 42 Table.
17. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, changed Tables.
18. In Paragraph 3.A., General Information, added new general note 21.
19. In Paragraph 3.B., Work Instructions, updated work instructions, added new Groups 42 and 43 and
changed 737-100/200 Aircraft Maintenance Manual (AMM) and 737-100/200 Structural Repair Manual
(SRM) references.
20. In Figures, changed Figures 1-38, 43, 46-55 and added Figure 56.
21. In Appendices, changed Appendices A, D and E.
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.
The data given in Information Notice 737-53A1358 IN01 is included in this revision.
Pages with no vertical lines have no changes.
REVISION HISTORY
April 27, 2017Original Issue:
February 26, 2021Revision 1:
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BLANK PAGE
Commercial
Airplanes 737
Service Bulletin
ALERT
Summary
Number: 737-53A1358
Original Issue: April 27, 2017
Revision 1: February 26, 2021
ATA System: 5331
SUBJECT: FUSELAGE - Skin - 0.036 Inch Crown Skin Panels Between S-10L and S-10R, STA
360 to STA 540 and STA 727 to STA 908 - Inspection, Repair 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
This service bulletin gives instructions for inspection, repair, and replacement of 0.036 inch fuselage crown skin
panels where cracking at the chem-mill steps can occur between stringer (S)-10L and S-10R from station (STA)
360 to STA 540 and from STA 727 to STA 908 for 737-200/200C/300/500 airplanes and from STA 360 to STA
500C and from STA 727G to STA 908 for 737-400 airplanes. On these skin panels, the bonded doubler is
chemically milled to create pockets. At these locations, the loads could cause a condition where cracks could
form along the longitudinal edges of the doubler at the step of the chem-mill pockets. The inspection, in accordance
with this service bulletin, will allow early detection of cracks in the crown skin panels and prevent Widespread
Fatigue Damage (WFD) by reducing the chance of multiple adjacent chem-mill step cracks from linking with
each other. The repair of cracks in accordance with this service bulletin will restore the structural integrity of the
skin panel. If the skin cracks propagate without detection, they could adversely affect the structural integrity of
the airplane.
An operator of a 737-300 airplane reported multiple chem-mill step cracks in adjacent bays of the fuselage crown
skin. These cracks were discovered by visual inspection only 855 flight cycles after the last detailed inspection
in accordance with Boeing Alert Service Bulletin (SB) 737-53A1210. The initial visual inspection revealed three
cracks varying in length from 1.8 inches to 8.5 inches. Further inspection using Ultrasonic Phased Array revealed
nine additional sub-surface cracks. The airplane had 55,232 flight cycles.
Boeing Service Related Problem (SRP) 737-SRP-53-0517 and 737-SRP-53-0607 are related to this service
bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-15007 and 737 FTD 53-19002 are related to this service bulletin.
The fuselage crown skin has been determined to be structure that is susceptible to WFD.
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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 ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications 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/PartsYesKits/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
Classification of repairs in this service bulletin
DESCRIPTIONREPAIR TYPE
A Category B repair for which supplemental inspections are necessary at the
specified threshold and repeat intervals in accordance with the Structural Repair
Manual (SRM).
SRM Repair
A Category C repair that has been changed to a Category B repair for which
supplemental inspections are necessary at the specified threshold and repeat in-
tervals in accordance with this Service Bulletin (SB).
Service Bul-
letin Repair
A time-limited repair which must be replaced or reworked within a specified time
limit. Also supplemental inspections are necessary at a specified threshold and
repeat interval in accordance with this service bulletin.
Category C
Group 1-21, 29-41:
Do a Non-Destructive Inspection (NDI) for any crack of the crown skin adjacent to the chem-mill steps in the
area from S-10L to S-10R, from STA 360 to STA 540 and from STA 727 to STA 908. If any crack is found, install
a SRM Repair or install a Category C Repair and repeat the external NDI of the crown skin for any crack. If no
crack is found, repeat the NDI inspections for any crack.
Group 22-28, 42:
Do a Non-Destructive Inspection (NDI) for any crack of the crown skin adjacent to the chem-mill steps in the
area from S-10L to S-10R, from STA 360 to STA 500C and from STA 727G to STA 908. If any crack is found,
install a SRM Repair or install a Category C Repair and repeat the external NDI of the crown skin for any crack.
If no crack is found, repeat the NDI inspections for any crack.
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 1-42:
If any Category C Repair is installed, do an external detailed inspection for any loose or missing fasteners.
Replace any loose or missing fasteners and change the Category C repair to a service bulletin Repair. If no
loose or missing fasteners are found, repeat the external detailed inspection for any loose or missing fasteners
and change the Category C repair to a service bulletin Repair.
Group 1-42:
If any service bulletin Repair is installed, do a post-repair external Low Frequency Eddy Current (LFEC) inspection
for any crack. If any crack is found, contact The Boeing Company for repair instructions and do the repair. If no
crack is found, repeat the post-repair external LFEC inspection of the service bulletin Repair for any crack.
Group 1-42:
If any SRM repair is installed, do post repair inspections in accordance with the SRM.
Group 1-21, 29-41:
Replace all six crown skin panel assemblies in the area from S-10L to S-10R, from STA 360 to STA 540 and
from STA 727 to STA 908.
Group 22-28, 42:
Replace all six crown skin panel assemblies in the area from S-10L to S-10R, from STA 360 to STA 500C and
from STA 727G to STA 908.
Group 43:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends immediate
and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated
under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for airplanes
that have accumulated flight cycles beyond the LOV. Airplanes in Group 43 (line number 1-291) have accumulated
flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of
an airplane beyond its LOV.
EFFECTIVITY
737-100/-200/-200C/-300/-400/-500 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected
airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Service
Bulletin 737-53A1358 Revision 1. The Airworthiness Directive will make the compliance tasks and times given
in Service Bulletin 737-53A1358 Revision 1 mandatory.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-23-02 is related to this Service Bulletin
737-53A1358. The effective date of AD 2017-23-02 is December 20, 2017.
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
Refer to Paragraph 1.G., Manpower.
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MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Operators are encouraged to complete the survey provided in APPENDIX F of this service bulletin to help Boeing
predict the quantity and timing of the Boeing Supplied Kits/Parts.
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BLANK PAGE
Commercial
Airplanes 737
Service Bulletin
ALERT
Number: 737-53A1358
Original Issue: April 27, 2017
Revision 1: February 26, 2021
ATA System: 5331
SUBJECT: FUSELAGE - Skin - 0.036 Inch Crown Skin Panels Between S-10L and S-10R, STA
360 to STA 540 and STA 727 to STA 908 - Inspection, Repair 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 737-100, 737-200, 737-200C, 737-300, 737-400, 737-500 Airplane(s),
line number(s) 1-2552 in 43 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.
The airplanes are grouped by crown skin configurations. The Variable Numbers and Group
Information for the applicable airplanes is given below.
Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
737-200 Airplanes without UHF/VHF antenna provision.-1
737-200 Airplanes without UHF/VHF antenna provision and a different
surface finish than Group 1 airplanes
-2
737-200 Airplanes with UHF/VHF antenna provision.-3
737-200 Airplanes with UHF/VHF antenna provision and unique
configuration from STA 847 to STA 857 at stringers 5L and 5R.
-4
737-200 Airplanes without chem-milled pockets from S-4L and S-4R.-5
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DESCRIPTIONCONFIGURATIONGROUP
737-200C Airplanes.-6
737-200C Airplanes and a different surface finish than Group 6
airplanes.
-7
737-300 Airplanes with no antenna provisions.-8
737-300 Airplanes with no antenna provisions and no chem-milled
pockets from STA 727 to STA 727E at S-4L to S-10L and S-4R to
S-10R.
-9
737-300 Airplanes with ATC antenna provision.-10
737-300 Airplanes with ATC antenna provision and no chem-milled
pockets from STA 727 to STA 727E at S-4L to S-10L and S-4R to
S-10R.
-11
737-300 Airplanes with ADF antenna provision.-12
737-300 Airplanes with ATC and MLS antenna provisions.-13
737-300 Airplanes with TCAS and ATC antenna provisions.-14
737-300 Airplanes with TCAS, ATC and ELT antenna provisions.-15
737-300 Airplanes with TCAS and ATC antenna provisions and no
chem-milled pockets from STA 727 to STA 727E at S-4L to S-10L
and S-4R to S-10R.
-16
737-300 Airplanes with TCAS, ATC and MLS antenna provisions.-17
737-300 Airplanes with ATC and Broadcast antenna provisions.-18
737-300 Airplanes with TCAS, ATC and GPS antenna provisions.-19
737-300 Airplanes with TCAS, ATC, MLS and GPS antenna
provisions.
-20
737-300 Airplanes with ATC antenna provision and unique
configuration at STA 420 to STA 430 between S-1 to S-2R.
-21
737-400 Airplanes with no antenna provisions.-22
737-400 Airplanes with ATC antenna provision.-23
737-400 Airplanes with ATC and MLS antenna provisions.-24
737-400 Airplanes with ATC and Broadcast antenna provisions.-25
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DESCRIPTIONCONFIGURATIONGROUP
737-400 Airplanes with TCAS, ATC and MLS antenna provisions.-26
737-400 Airplanes with TCAS, ATC and Broadcast antenna
provisions.
-27
737-400 Airplanes with TCAS, ATC, MLS and GPS antenna
provisions.
-28
737-500 Airplanes with ATC antenna provision.-29
737-500 Airplanes with ATC antenna provision and with different
production skin assemblies to airplanes in Group 29.
-30
737-500 Airplanes with ATC antenna provision with no chem-milled
pockets from STA 727 to STA 727C at S-4L to S-10L and S-4R to
S-10R.
-31
737-500 Airplanes with ATC and MLS antenna provisions.-32
737-500 Airplanes with ATC and MLS antenna provisions and with
different production skin assemblies to airplanes in Group 32.
-33
737-500 Airplanes with ATC, MLS and ELT antenna provisions.-34
737-500 Airplanes with TCAS and ATC antenna provisions.-35
737-500 Airplanes with TCAS, ATC and ELT antenna provisions.-36
737-500 Airplanes with TCAS and ATC antenna provisions and no
chem-milled pockets from STA 727 to STA 727C at S-4L to S-10L
and S-4R to S-10R.
-37
737-500 Airplanes with TCAS , ATC and MLS antenna provisions.-38
737-500 Airplanes with TCAS, ATC, MLS and ELT antenna
provisions.
-39
737-500 Airplanes with TCAS, ATC and GPS antenna provisions.-40
737-500 Airplanes with TCAS, ATC, MLS and GPS antenna
provisions.
-41
737-400 Airplanes with TCAS and ATC antenna provisions.-42
737-100/-200/-200C Airplane line numbers 1-291 beyond the Limit
of Validity (LOV).
-43
Airplane Models:
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737-100, 737-200, 737-200C, 737-300, 737-400, 737-500
GroupVariable Number
43PA001 - PA022
43PA099
43PA231 - PA232
43PC001 - PC005
43PG001 - PG075
43PG199
43PG201 - PG230
43PG251 - PG255
43PG271 - PG279
43PG301 - PG314
43PG331 - PG332
43PG351 - PG356
43PG375
43PG401 - PG403
43PG431 - PG442
43PG471 - PG475
43PG501 - PG505
43PG571 - PG583
1PG584 - PG586
43PG621 - PG630
43PG651 - PG652
43PG701 - PG705
1PH001
1PH011 - PH013
1PH021 - PH024
43PH701 - PH715
43PH731 - PH732
43PH741 - PH742
1PH743
43PJ001 - PJ002
1PJ003 - PJ009
43PJ031 - PJ032
GroupVariable Number
43PJ071 - PJ072
43PJ101 - PJ104
1PJ105 - PJ118
2PJ119
5PJ201 - PJ219
42PJ301 - PJ302
42PJ551
1PK026 - PK029
1PK041 - PK053
1PK061 - PK070
1PK081 - PK082
1PK091 - PK099
1PK101 - PK103
1PK111 - PK120
1PK141 - PK146
1PK201 - PK204
1PK211 - PK214
2PK215 - PK220
1PK221 - PK223
1PK231 - PK239
2PK240
1PK241
1PK251 - PK258
1PK271 - PK273
2PK274
1PK281 - PK289
1PK291
1PK301 - PK318
1PK341
1PK351 - PK360
2PK361
1PK391
GroupVariable Number
1PK431 - PK433
1PK451 - PK452
1PK461 - PK469
1PK495
1PK501 - PK503
2PK504
1PK511 - PK513
2PK514 - PK515
3PK519
1PK521 - PK524
2PK525 - PK528
1PK541 - PK552
2PK553 - PK560
1PK561 - PK562
2PK563 - PK565
1PK581
1PK591 - PK599
1PK601 - PK602
2PK603 - PK610
1PK611 - PK615
2PK616 - PK617
1PK621 - PK626
2PK627 - PK637
1PK641 - PK642
1PK661
2PK662 - PK666
1PK671 - PK674
2PK675 - PK681
1PK691 - PK693
2PK694 - PK697
1PK711 - PK716
1PK731 - PK749
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GroupVariable Number
2PK750 - PK765
1PK771 - PK775
2PK776 - PK779
2PK801 - PK804
2PK819
1PK820 - PK822
2PK823 - PK827
1PK830
1PK861
2PK862 - PK863
1PK871
2PK872 - PK874
1PK881 - PK882
2PK883 - PK884
1PK901 - PK908
2PK909 - PK938
2PK971 - PK974
1PL001 - PL018
2PL019 - PL028
2PL061
2PL081
2PL101 - PL113
2PL151
2PL171 - PL172
2PL201 - PL203
2PL221
1PL401 - PL405
2PL406 - PL417
1PL421
1PL441
1PL451 - PL452
2PL453 - PL456
2PL471
GroupVariable Number
2PL491
2PL501 - PL506
2PL551 - PL562
2PL581
3PL601
4PL602 - PL603
2PL611
2PL621 - PL626
2PL631 - PL632
43PL711 - PL712
43PL716
1PL717 - PL744
2PL745 - PL747
1PL756
1PL758
1PL761 - PL770
1PL781 - PL782
2PL783 - PL788
1PL793
43PL801 - PL803
2PM001 - PM006
3PM016 - PM017
1PM021
2PM022 - PM023
2PM051 - PM066
2PM101 - PM119
2PM141 - PM142
2PM171
2PM181
2PM251 - PM255
2PM281 - PM283
8PM381 - PM388
10PM389 - PM391
GroupVariable Number
14PM392 - PM399
14PM401 - PM417
14PM541 - PM542
42PM551 - PM564
2PN001 - PN002
2PN021 - PN043
2PN081 - PN086
2PN101 - PN117
2PN131 - PN163
2PN401 - PN420
2PN431 - PN433
2PN451 - PN456
2PN471 - PN474
2PN481
2PN491 - PN493
2PN501 - PN502
2PN511 - PN512
2PN521
8PP001 - PP047
14PP048 - PP054
8PP101 - PP126
9PP127 - PP139
11PP140 - PP148
16PP149 - PP160
8PP161 - PP169
8PP181 - PP197
10PP198 - PP199
8PP201 - PP205
10PP221
8PP231 - PP243
8PP281 - PP286
8PP301 - PP305
8PP351 - PP353
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GroupVariable Number
8PP376 - PP384
8PP391 - PP393
8PP401 - PP440
8PP471 - PP475
8PP501 - PP504
21PP505 - PP507
10PP508 - PP510
14PP511 - PP517
8PP521 - PP522
8PP631 - PP634
8PP651 - PP652
8PP671 - PP699
8PP701 - PP733
8PP771 - PP779
8PP801 - PP804
13PP805 - PP808
8PP821 - PP827
8PP831 - PP848
8PP851 - PP852
8PP861 - PP873
14PP874 - PP875
8PP891 - PP899
8PP901 - PP909
10PP910 - PP927
14PP928 - PP930
8PP931 - PP936
8PP946 - PP948
10PP951 - PP952
8PP961 - PP965
10PP966 - PP967
8PP981 - PP983
10PP984 - PP986
14PP987 - PP990
GroupVariable Number
8PP991
10PP993
12PQ001 - PQ012
18PQ013 - PQ016
8PQ026 - PQ037
10PQ038 - PQ041
8PQ051 - PQ068
10PQ069 - PQ073
14PQ074 - PQ085
8PQ086 - PQ092
10PQ101 - PQ187
14PQ188 - PQ199
14PQ201 - PQ202
8PQ221 - PQ229
14PQ230
8PQ231 - PQ236
14PQ237
8PQ241 - PQ243
10PQ251 - PQ257
14PQ258 - PQ267
10PQ281 - PQ289
14PQ290 - PQ296
10PQ301 - PQ305
14PQ306 - PQ307
14PQ331 - PQ332
19PQ341 - PQ344
14PQ361 - PQ369
14PQ401 - PQ406
19PQ407
14PQ411 - PQ413
14PQ421
14PQ471 - PQ472
8PQ479 - PQ480
GroupVariable Number
14PQ481
14PQ486 - PQ487
14PQ491 - PQ493
14PQ771
14PQ791 - PQ793
20PQ801 - PQ805
15PQ931 - PQ932
14PS601 - PS615
19PS616
14PS631
17PS636 - PS638
10PS641 - PS642
19PS643 - PS644
14PS651 - PS657
10PS666 - PS667
14PS668 - PS669
14PS691 - PS692
14PS701 - PS703
16PS751 - PS762
33PT001 - PT003
38PT004 - PT005
41PT006 - PT011
32PT021 - PT022
33PT023 - PT024
41PT025 - PT028
30PT041 - PT042
35PT043 - PT063
32PT101
33PT102 - PT104
38PT105
29PT121
35PT122 - PT125
35PT146 - PT148
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GroupVariable Number
38PT161 - PT170
34PT181
39PT182 - PT187
35PT211 - PT220
39PT295
35PT301 - PT306
40PT331 - PT360
35PT381 - PT399
35PT401 - PT438
40PT501 - PT512
35PT561 - PT565
38PT581 - PT584
35PT611 - PT621
38PT641 - PT642
35PT651 - PT655
35PT671 - PT672
36PT701 - PT703
31PU001 - PU007
37PU008 - PU025
22PV001 - PV020
42PV021 - PV055
42PV201 - PV203
28PV231 - PV237
42PV271 - PV272
42PV281 - PV283
22PW001 - PW026
23PW027
42PW028
23PW029 - PW032
42PW033 - PW050
23PW051
42PW052 - PW054
23PW061 - PW063
GroupVariable Number
42PW064 - PW068
42PW072
23PW091 - PW093
42PW094
42PW101 - PW102
42PW106
23PW111 - PW117
42PW118 - PW120
42PW156 - PW157
42PW161 - PW167
42PW201 - PW244
42PW261
42PW265 - PW268
42PW278
42PW281
42PW293
42PW296
42PW301 - PW327
42PW461
28PW462
42PW463 - PW467
23PW501 - PW502
22PW503
42PW504
23PW511 - PW515
24PW516 - PW518
26PW519 - PW520
26PW526
25PW531 - PW537
27PW538 - PW546
27PW556 - PW557
23PW561 - PW563
42PW564
GroupVariable Number
24PW571 - PW574
28PW575 - PW576
24PW591 - PW594
26PW595 - PW596
23PW611 - PW613
42PW614 - PW620
26PW631 - PW634
42PW661 - PW662
42PW681 - PW683
42PW701
28PW702
42PW711 - PW717
42PW741 - PW742
42PW761
28PW771
43PX071
43PX701
43PY001 - PY008
43PY021
6PY022
43PY031
6PY036 - PY037
6PY046 - PY048
6PY051 - PY053
7PY056 - PY057
6PY101 - PY103
6PY111 - PY113
6PY131 - PY135
6PY141 - PY143
6PY151 - PY153
7PY154
6PY156 - PY157
6PY161 - PY162
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GroupVariable Number
6PY166
6PY191
6PY201
6PY221 - PY222
6PY231
6PY241 - PY244
6PY270 - PY275
6PY281
6PY286
43PY301 - PY304
GroupVariable Number
43PY321 - PY323
43PY341 - PY346
43PY361 - PY362
43PY381
6PY401
7PY409 - PY410
6PY411
6PY421
7PY422
6PY441
GroupVariable Number
6PY451
7PY461 - PY463
7PY591 - PY595
6PY611 - PY612
6PY621
7PY631
7PY651
7PY671 - PY672
7PY721
7PY741
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions for inspection, repair, and replacement of 0.036 inch fuselage
crown skin panels where cracking at the chem-mill steps can occur between stringer (S)-10L and S-10R
from station (STA) 360 to STA 540 and from STA 727 to STA 908 for 737-200/200C/300/500 airplanes
and from STA 360 to STA 500C and from STA 727G to STA 908 for 737-400 airplanes. On these skin
panels, the bonded doubler is chemically milled to create pockets. At these locations, the loads could
cause a condition where cracks could form along the longitudinal edges of the doubler at the step of
the chem-mill pockets. The inspection, in accordance with this service bulletin, will allow early detection
of cracks in the crown skin panels and prevent Widespread Fatigue Damage (WFD) by reducing the
chance of multiple adjacent chem-mill step cracks from linking with each other. The repair of cracks in
accordance with this service bulletin will restore the structural integrity of the skin panel. If the skin
cracks propagate without detection, they could adversely affect the structural integrity of the airplane.
An operator of a 737-300 airplane reported multiple chem-mill step cracks in adjacent bays of the
fuselage crown skin. These cracks were discovered by visual inspection only 855 flight cycles after the
last detailed inspection in accordance with Boeing Alert Service Bulletin (SB) 737-53A1210. The initial
visual inspection revealed three cracks varying in length from 1.8 inches to 8.5 inches. Further inspection
using Ultrasonic Phased Array revealed nine additional sub-surface cracks. The airplane had 55,232
flight cycles.
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Revision 1 is sent to make changes as in the Table below:
NOTE: For all Groups the initial inspection threshold, initial repeat, initial grace period and methods
remain unchanged.
ReasonGroup
The original issue inspection figures show incorrect chem-mill locations.
Changes are made to some of the inspection locations.
Airplanes in Group 32, 33, 34, 36,
38.
The original issue incorrectly identified some airplanes in Group 8.
Changes are made to transfer the affected airplanes to Group 16. (a)
Some of the airplanes in Group 8.
The original issue incorrectly identified some airplanes in Group 22.
Changes are made to transfer affected airplanes to new Group 42. (b)
Some of the airplanes in Group 22.
The original issue inspection figures show incorrect chem-mill locations.
Changes are made to inspection locations between STA 727 and STA
908.
Airplanes in Group 5.
The original issue inspection figures show incorrect chem-mill locations.
Changes are made to inspection locations between S-4 and S-5.
Airplanes in Group 1- 42.
(a) Airplane variable numbers PP150-PP160 and PS751-PS762 were transferred from Group 8 of service
bulletin 737-53A1358 Original Issue to Group 16 of this service bulletin effectivity.
(b) Airplane variable numbers PJ301-PJ302 PJ551-PJ551 PM551-PM564 PV021-PV055 PV201-PV203
PV271-PV272 PV281-PV283 PW028-PW028 PW033-PW050 PW052-PW054 PW064-PW068 PW072-
PW072 PW094-PW094 PW101-PW102 PW106-PW106 PW118-PW120 PW156-PW157 PW161-PW167
PW201-PW244 PW261-PW261 PW265-PW268 PW278-PW278 PW281-PW281 PW293-PW293 PW296-
PW296 PW301-PW327 PW461-PW461 PW463-PW467 PW504-PW504 PW564-PW564 PW614-PW620
PW661-PW662 PW681-PW683 PW701-PW701 PW711-PW717 PW741-PW742 PW761-PW761 were
transferred from Group 22 of service bulletin 737-53A1358 Original Issue to new Group 42 of this service
bulletin effectivity.
Boeing Service Related Problem (SRP) 737-SRP-53-0517 and 737-SRP-53-0607 are related to this
service bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-15007 and 737 FTD 53-19002 are related to this service
bulletin.
The fuselage crown skin has been determined to be structure that is susceptible to WFD.
D. Description
Classification of repairs in this service bulletin
DESCRIPTIONREPAIR TYPE
A Category B repair for which supplemental inspections
are necessary at the specified threshold and repeat inter-
vals in accordance with the Structural Repair Manual
(SRM).
SRM Repair
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Classification of repairs in this service bulletin
DESCRIPTIONREPAIR TYPE
A Category C repair that has been changed to a Category
B repair for which supplemental inspections are neces-
sary at the specified threshold and repeat intervals in
accordance with this Service Bulletin (SB).
Service Bul-
letin Repair
A time-limited repair which must be replaced or reworked
within a specified time limit. Also supplemental inspec-
tions are necessary at a specified threshold and repeat
interval in accordance with this service bulletin.
Category C
Group 1-21, 29-41:
Do a Non-Destructive Inspection (NDI) for any crack of the crown skin adjacent to the chem-mill steps
in the area from S-10L to S-10R, from STA 360 to STA 540 and from STA 727 to STA 908. If any crack
is found, install a SRM Repair or install a Category C Repair and repeat the external NDI of the crown
skin for any crack. If no crack is found, repeat the NDI inspections for any crack.
Group 22-28, 42:
Do a Non-Destructive Inspection (NDI) for any crack of the crown skin adjacent to the chem-mill steps
in the area from S-10L to S-10R, from STA 360 to STA 500C and from STA 727G to STA 908. If any
crack is found, install a SRM Repair or install a Category C Repair and repeat the external NDI of the
crown skin for any crack. If no crack is found, repeat the NDI inspections for any crack.
Group 1-42:
If any Category C Repair is installed, do an external detailed inspection for any loose or missing
fasteners. Replace any loose or missing fasteners and change the Category C repair to a service
bulletin Repair. If no loose or missing fasteners are found, repeat the external detailed inspection for
any loose or missing fasteners and change the Category C repair to a service bulletin Repair.
Group 1-42:
If any service bulletin Repair is installed, do a post-repair external Low Frequency Eddy Current (LFEC)
inspection for any crack. If any crack is found, contact The Boeing Company for repair instructions and
do the repair. If no crack is found, repeat the post-repair external LFEC inspection of the service bulletin
Repair for any crack.
Group 1-42:
If any SRM repair is installed, do post repair inspections in accordance with the SRM.
Group 1-21, 29-41:
Replace all six crown skin panel assemblies in the area from S-10L to S-10R, from STA 360 to STA
540 and from STA 727 to STA 908.
Group 22-28, 42:
Replace all six crown skin panel assemblies in the area from S-10L to S-10R, from STA 360 to STA
500C and from STA 727G to STA 908.
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Group 43:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends
immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or
not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance
instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 43
(line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14
CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
Revision 1 - Effects of this Revision on airplanes on which the Original Issue was previously done:
ActionConditionGroup
Do service bulletin 737- 53A1358 Revi-
sion 1 PART 1: CROWN SKIN CHEM-
MILL STEP INTERNAL/EXTERNAL NDI.
Airplanes that have accomplished PART
1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NDI in accor-
dance with service bulletin 737-53A1358
original issue.
All Airplanes.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1-5:
Affected Maintenance Zones
ZoneModel
1-7, 1-8737-200
Group 6-7:
Affected Maintenance Zones
ZoneModel
1-7, 1-8737-200C
Group 8-21:
Affected Maintenance Zones
ZoneModel
107, 108737-300
Group 22-28, 42:
Affected Maintenance Zones
ZoneModel
107, 108737-400
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Group 29-41:
Affected Maintenance Zones
ZoneModel
107, 108737-500
Group 43:
Affected Maintenance Zones
ZoneModel
1-7, 1-8737-100, 737-200, 737-200C
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Service Bulletin 737-53A1358 Revision 1. The Airworthiness Directive will make the compliance tasks
and times given in Service Bulletin 737-53A1358 Revision 1 mandatory.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2017-23-02 is related to this Service
Bulletin 737-53A1358. The effective date of AD 2017-23-02 is December 20, 2017.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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.
Group 43:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and recommends
immediate and permanent removal from service of any airplanes upon reaching the LOV, whether or
not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance
instructions for airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 43
(line number 1-291) have accumulated flight cycles beyond the LOV of the maintenance program. 14
CFR 121.1115 and 129.115 prohibit operation of an airplane beyond its LOV.
Logic diagrams showing compliance tasks and compliance times are included as aids in APPENDIX
A, APPENDIX B, APPENDIX C and APPENDIX D.
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Table 1: CROWN SKIN BONDED DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-
10L TO S-10R - STA 360 TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO
STA 500C AND 727G TO STA 908 (GROUP 22-28, 42)
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 2,600 flight cycles after the
original issue date of this service
bulletin.
Contact The Boeing
Company for work instruc-
tions and do the work.
Airplanes that have had a
crown skin panel replaced
with a production skin pan-
el before 47,000 total flight
cycles and have a record
of the skin panel replace-
ment.
--No further action required
for the replacement skin
panel.
Airplanes that have had a
crown skin panel replaced
with a production skin pan-
el after 46,999 total flight
cycles and have a record
of the skin panel replace-
ment.
-Within 2,600
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 50,000
total flight cy-
cles.
Do PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack on the production
skin panel. (a)(b)
Airplanes that have a
crown skin panel that has
never been replaced or if
the operator has no record
of the production skin panel
replacement and have not
accomplished inspections
in accordance with the
original issue of this service
bulletin.
-Within 1,800 FC after prior inspec-
tions done in accordance with the
original issue of this service bul-
letin PART 1.
Do PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack on the production
skin panel. (a)(b)
Airplanes that have a
crown skin panel that has
never been replaced or if
the operator has no record
of the production skin panel
replacement and have ac-
complished inspections in
accordance with the origi-
nal issue of this service
bulletin.
1,800 flight cycles.-Repeat PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack. (a)(b)
CONDITION 1: NO
CRACK FOUND.
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Table 1: CROWN SKIN BONDED DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-
10L TO S-10R - STA 360 TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO
STA 500C AND 727G TO STA 908 (GROUP 22-28, 42)
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.OPTION 1 (ACTION 1):
Do PART 2: SRM RE-
PAIR. (c)
CONDITION 2: ANY
CRACK FOUND.
1,800 flight cycles.-OPTION 1 (ACTION 2):
Repeat PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack. (a)(b)(d)
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3: CATEGORY
C REPAIR. (e)(f)
1,800 flight cycles.-OPTION 2 (ACTION 2):
Repeat PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack.(a)(b)(g)
(a) It is not required to inspect the chem-mill steps under existing repair doublers provided either:
1. The installed repair or modification was approved by the FAA or by a Boeing Company authorized
representative who was authorized by the FAA to make such findings, and the installed repair
extends a minimum of three rows of fasteners on each side of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA or by a Boeing Company
authorized representative who was authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of 3/16 inch diameter fasteners on
each side of the chem-mill step in the circumferential direction with 5-6D fastener spacing;
and either:
– The repair or modification is similar to 737-100/200 SRM 53-30-3 Figure 48 or 737-
300 SRM 53-00-01 Repair 31 or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM
53-00-01 Repair 31 with regard to fastener type, size, layout and pitch, repair part
thickness and material, and repair installation; or
– The repair or modification is similar to 737-300/400/500 SRM 53-60-01 Repair 9 or
Repair 14 with regard to fastener type, size, layout and pitch, repair part thickness and
material, and repair installation.
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Table 1: CROWN SKIN BONDED DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-
10L TO S-10R - STA 360 TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO
STA 500C AND 727G TO STA 908 (GROUP 22-28, 42)
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(b) Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to the initial and repeat
PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION
(NDI) inspections.
(c) The applicability limitations and post repair inspection requirements of PART 2: SRM REPAIR are in
PART 2 and 737-100/200 SRM 53-30-3 Figure 48, 737-300 SRM 53-00-01 Repair 31, 737-400 SRM 53-
00-01 Repair 31 or 737-500 SRM 53-00-01 Repair 31.
(d) Accomplishment of PART 2: SRM REPAIR is terminating action to the service bulletin repeat inspections
at the SRM repair location only.
(e) The applicability limitations of the Category C repair are in PART 3: CATEGORY C REPAIR.
(f) Compliance times for post-repair inspections of Category C repairs done in accordance with PART 3:
CATEGORY C REPAIR are in Table 2 of Paragraph 1.E., Compliance.
(g) Accomplishment of PART 3: CATEGORY C REPAIR is terminating action to the service bulletin repeat
PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION
(NDI) inspections under the Category C repair location only.
Table 2: POST REPAIR INSPECTION OF CATEGORY C REPAIR
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 3,000 flight cycles after ac-
complishment of PART 3: CATE-
GORY C REPAIR.
Do PART 4: POST RE-
PAIR INSPECTION OF
CATEGORY C REPAIR
for any loose or missing
fastener. (a)(b)
Airplanes with any Catego-
ry C repair installed in ac-
cordance with the Original
Issue or any revision of this
service bulletin
-Before further flight.CONDITION 3 (ACTION
1): Do PART 5: POST
CATEGORY C REPAIR
FASTENER REPLACE-
MENT.
CONDITION 3: ANY
LOOSE OR MISSING
FASTENER FOUND.
3,000 flight cycles.-CONDITION 3 (ACTION
2): Repeat PART 4:
POST REPAIR INSPEC-
TION OF CATEGORY C
REPAIR for any loose or
missing fastener. (a)(b)
-Within 6,000 flight cycles after ac-
complishment of PART 3: CATE-
GORY C REPAIR.
CONDITION 3 (ACTION
3): Do PART 6: CHANGE
CATEGORY C REPAIR
TO SERVICE BULLETIN
REPAIR. (b)(c)(d)
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Table 2: POST REPAIR INSPECTION OF CATEGORY C REPAIR
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
3,000 flight cycles.-CONDITION 4 (ACTION
1): Repeat PART 4:
POST REPAIR INSPEC-
TION OF CATEGORY C
REPAIR for any loose or
missing fastener. (a)(b)
CONDITION 4: NO LOOSE
OR MISSING FASTENER
FOUND.
-Within 6,000 flight cycles after ac-
complishment of PART 3: CATE-
GORY C REPAIR.
CONDITION 4 (ACTION
2): Do PART 6: CHANGE
CATEGORY C REPAIR
TO SERVICE BULLETIN
REPAIR. (b)(c)(d)
(a) Accomplishment of PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR is
terminating action to initial and repeat PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
inspections at the repaired location only.
(b) Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to PART 4: POST
REPAIR INSPECTION OF CATEGORY C REPAIR and terminates the requirement to do PART 6:
CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR.
(c) The applicability limitations of the service bulletin repairs are in PART 6: CHANGE CATEGORY C REPAIR
TO SERVICE BULLETIN REPAIR.
(d) Compliance times for inspection of service bulletin repairs done in accordance with PART 6: CHANGE
CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR are in Table 3 of Paragraph 1.E., Compliance.
Table 3: POST REPAIR INSPECTION OF SERVICE BULLETIN REPAIRS INSTALLED IN ACCORDANCE
WITH PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR IN THE ORIGINAL ISSUE
OR ANY REVISION OF THIS SERVICE BULLETIN
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 5,000 flight cycles after ac-
complishment of PART 6:
CHANGE CATEGORY C REPAIR
TO SERVICE BULLETIN RE-
PAIR, Option 1.
Do PART 7: POST RE-
PAIR LOW FREQUENCY
EDDY CURRENT (LFEC)
INSPECTION OF SER-
VICE BULLETIN REPAIR
for any crack. (a)
Airplanes with any Service
Bulletin Repair installed in
accordance with PART 6:
CHANGE CATEGORY C
REPAIR TO SERVICE
BULLETIN REPAIR, Op-
tion 1.
-Within 60,000 flight cycles after
accomplishment of PART 6:
CHANGE CATEGORY C REPAIR
TO SERVICE BULLETIN RE-
PAIR, Option 2.
Do PART 7: POST RE-
PAIR LOW FREQUENCY
EDDY CURRENT (LFEC)
INSPECTION OF SER-
VICE BULLETIN REPAIR
for any crack. (a)
Airplanes with any Service
Bulletin Repair installed in
accordance with PART 6:
CHANGE CATEGORY C
REPAIR TO SERVICE
BULLETIN REPAIR, Op-
tion 2.
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Table 3: POST REPAIR INSPECTION OF SERVICE BULLETIN REPAIRS INSTALLED IN ACCORDANCE
WITH PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR IN THE ORIGINAL ISSUE
OR ANY REVISION OF THIS SERVICE BULLETIN
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 5: ANY
CRACK FOUND.
5,000 flight cycles.-Repeat PART 7: POST
REPAIR LOW FREQUEN-
CY EDDY CURRENT
(LFEC) INSPECTION OF
SERVICE BULLETIN
REPAIR for any crack. (a)
CONDITION 6: NO
CRACK FOUND.
(a) Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to the initial and repeat
PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF SERVICE
BULLETIN REPAIR inspections.
Table 4: CROWN SKIN PANEL REPLACEMENT FROM S-10L TO S-10R - STA 360 TO STA 540 AND STA
727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO STA 908 (GROUP 22-28,
42)
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
--No further action required
for the replacement skin
panel.
Airplanes that have had a
crown skin panel replaced
with a production skin pan-
el after 46,999 total flight
cycles and have a record
of the skin panel replace-
ment.
-Within 6,000
flight cycles af-
ter the original
issue date of
this service bul-
letin but not be-
fore 47,000 total
flight cycles.
Before 66,000
total flight cycles
but not before
47,000 total
flight cycles.
Do PART 8: SKIN PANEL
REPLACEMENT.
Airplanes that have a
crown skin panel that has
never been replaced or the
operator has no record of
the skin panel replacement.
-Within 6,000
flight cycles af-
ter the original
issue date of
this service bul-
letin.
Before 66,000
total flight cy-
cles.
Contact The Boeing
Company for work instruc-
tions and do the work.
Airplanes that have had a
crown skin panel replaced
before 47,000 total flight
cycles with a production
skin panel and the operator
has a record of the skin
panel replacement.
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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
Union 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.
The Manager of the FAA Los Angeles ACO Branch approves the accomplishment of the inspections
of the fuselage crown skin panels in accordance with Part 1 of the Accomplishment Instructions of this
service bulletin revision 1 as an Alternative Method of Compliance (AMOC) to the inspections of the
skin at the horizontal chem milled steps required by paragraphs (g), (p), and (q) of Airworthiness
Directive (AD) 2013-18-08 and paragraphs (g) and (j) of AD 2011-24-12, for the inspection areas defined
by Part 1 of the Accomplishment Instructions of this service bulletin revision 1 only. These AMOCs are
only applicable after accomplishment of the initial inspection in accordance with PART 1: CROWN
SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) specified
in Paragraph 1.E., Compliance of this service bulletin revision 1.
The Manager of the FAA Los Angeles ACO Branch approves the accomplishment of the replacement
of the fuselage crown skin panels in accordance with Part 8 of the Accomplishment Instructions of this
service bulletin revision 1 as an AMOC to the inspections required by paragraph (g), (p), (q), and (r)
of AD 2013-18-08, the stringer S-4R and S-4L lap splice repairs required by paragraphs (g) and (h) of
AD 2015-21-06, the inspections required by paragraphs (g) and (j) of AD 2011-24-12, the inspection
and the modification required by paragraph (i) of AD 2016-16-13, and the inspections required by
paragraph (a) of AD 2003-14-06 for the replaced skin panels only.
The Manager of the FAA Los Angeles ACO Branch approves the accomplishment of Part 1 of the
Accomplishment Instructions of this service bulletin revision as an Alternative Method of Compliance
(AMOC) to the paragraph (g) of AD 2017-23-02.
The Manager of the FAA Los Angeles ACO Branch approves the accomplishment of Part 2, 3, 6 and
8 of the Accomplishment Instructions of this service bulletin revision as an Alternative Method of
Compliance (AMOC) to the paragraph (i) of AD 2017-23-02.
All provisions of AD 2013-18-08, AD 2011-24-12, AD 2015-21-06, AD 2016-16-13, AD 2003-14-06 and
AD 2017-23-02 that are not specifically referenced in the above statements remain fully applicable and
must be complied with accordingly.
G. Manpower
The tables below show an estimate of the task hours necessary to do the inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
• Time to adjust to the workplace
• Time to schedule the work
• Time to inspect the work
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• Time to cure the materials
• Time to make the parts
• Time to find the tools.
Group 1-2:
Table 1: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
26.50106.004FIGURE 28 ( FIGURE 1 and
FIGURE 29, 788 bays)
18.50185.0010CLOSE ACCESS
63.50476.00TOTAL FOR EACH AIRPLANE
Group 3-4:
Table 2: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
26.00104.004FIGURE 28 ( FIGURE 2 and
FIGURE 29, 786 bays)
18.50185.0010CLOSE ACCESS
63.00474.00TOTAL FOR EACH AIRPLANE
Group 5:
Table 3: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
18.5074.004FIGURE 28 ( FIGURE 3 and
FIGURE 30, 524 bays)
18.50185.0010CLOSE ACCESS
55.50444.00TOTAL FOR EACH AIRPLANE
Group 6-7:
Table 4: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.2589.004FIGURE 28 ( FIGURE 4 and
FIGURE 31, 627 bays)
18.50185.0010CLOSE ACCESS
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Group 6-7:
Table 4: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
59.25459.00TOTAL FOR EACH AIRPLANE
Group 8:
Table 5: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
34.25137.004FIGURE 28 ( FIGURE 5 and
FIGURE 32, 968 bays)
18.50185.0010CLOSE ACCESS
71.25507.00TOTAL FOR EACH AIRPLANE
Group 9:
Table 6: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
30.00120.004FIGURE 28 ( FIGURE 5 and
FIGURE 33, 848 bays)
18.50185.0010CLOSE ACCESS
67.00490.00TOTAL FOR EACH AIRPLANE
Group 10:
Table 7: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
34.00136.004FIGURE 28 ( FIGURE 6 and
FIGURE 32, 964 bays)
18.50185.0010CLOSE ACCESS
71.00506.00TOTAL FOR EACH AIRPLANE
Group 11:
Table 8: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
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Group 11:
Table 8: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
29.75119.004FIGURE 28 ( FIGURE 6 and
FIGURE 33, 844 bays)
18.50185.0010CLOSE ACCESS
66.75489.00TOTAL FOR EACH AIRPLANE
Group 12:
Table 9: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
34.00136.004FIGURE 28 ( FIGURE 7 and
FIGURE 32, 966 bays)
18.50185.0010CLOSE ACCESS
71.00506.00TOTAL FOR EACH AIRPLANE
Group 13:
Table 10: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
33.00132.004FIGURE 28 ( FIGURE 8 and
FIGURE 32, 962 bays)
18.50185.0010CLOSE ACCESS
70.00502.00TOTAL FOR EACH AIRPLANE
Group 14:
Table 11: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
34.00136.004FIGURE 28 ( FIGURE 9 and
FIGURE 32, 963 bays)
18.50185.0010CLOSE ACCESS
71.00506.00TOTAL FOR EACH AIRPLANE
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Group 15:
Table 12: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
33.50134.004FIGURE 28 ( FIGURE 9 and
FIGURE 34, 961 bays)
18.50185.0010CLOSE ACCESS
70.50504.00TOTAL FOR EACH AIRPLANE
Group 16:
Table 13: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
29.25117.004FIGURE 28 ( FIGURE 9 and
FIGURE 33, 843 bays)
18.50185.0010CLOSE ACCESS
66.25487.00TOTAL FOR EACH AIRPLANE
Group 17:
Table 14: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
33.50134.004FIGURE 28 ( FIGURE 10 and
FIGURE 32, 961 bays)
18.50185.0010CLOSE ACCESS
70.50504.00TOTAL FOR EACH AIRPLANE
Group 18:
Table 15: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
33.75135.004FIGURE 28 ( FIGURE 11 and
FIGURE 32, 962 bays)
18.50185.0010CLOSE ACCESS
70.75505.00TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Group 19:
Table 16: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
33.75135.004FIGURE 28 ( FIGURE 12 and
FIGURE 32, 961 bays)
18.50185.0010CLOSE ACCESS
70.75505.00TOTAL FOR EACH AIRPLANE
Group 20:
Table 17: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
33.25133.004FIGURE 28 ( FIGURE 13 and
FIGURE 32, 959 bays)
18.50185.0010CLOSE ACCESS
70.25503.00TOTAL FOR EACH AIRPLANE
Group 21:
Table 18: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
34.25137.004FIGURE 28 ( FIGURE 14 and
FIGURE 32, 968 bays)
18.50185.0010CLOSE ACCESS
71.25507.00TOTAL FOR EACH AIRPLANE
Group 22:
Table 19: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.7591.004FIGURE 28 ( FIGURE 15 and
FIGURE 35, 680 bays)
18.50185.0010CLOSE ACCESS
59.75461.00TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 39 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 23:
Table 20: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.7591.004FIGURE 28 ( FIGURE 16 and
FIGURE 35, 676 bays)
18.50185.0010CLOSE ACCESS
59.75461.00TOTAL FOR EACH AIRPLANE
Group 24:
Table 21: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.7591.004FIGURE 28 ( FIGURE 17 and
FIGURE 35, 674 bays)
18.50185.0010CLOSE ACCESS
59.75461.00TOTAL FOR EACH AIRPLANE
Group 25:
Table 22: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.2589.004FIGURE 28 ( FIGURE 18 and
FIGURE 35, 674 bays)
18.50185.0010CLOSE ACCESS
59.25459.00TOTAL FOR EACH AIRPLANE
Group 26:
Table 23: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.2589.004FIGURE 28 ( FIGURE 19 and
FIGURE 35, 673 bays)
18.50185.0010CLOSE ACCESS
59.25459.00TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 40 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 27:
Table 24: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.2589.004FIGURE 28 ( FIGURE 20 and
FIGURE 35, 673 bays)
18.50185.0010CLOSE ACCESS
59.25459.00TOTAL FOR EACH AIRPLANE
Group 28:
Table 25: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.2589.004FIGURE 28 ( FIGURE 21 and
FIGURE 35, 671 bays)
18.50185.0010CLOSE ACCESS
59.25459.00TOTAL FOR EACH AIRPLANE
Group 29-30:
Table 26: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.25109.004FIGURE 28 ( FIGURE 22 and
FIGURE 36, 784 bays)
18.50185.0010CLOSE ACCESS
64.25479.00TOTAL FOR EACH AIRPLANE
Group 31:
Table 27: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
25.25101.004FIGURE 28 ( FIGURE 22 and
FIGURE 37, 712 bays)
18.50185.0010CLOSE ACCESS
62.25471.00TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 41 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 32-33:
Table 28: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.50110.004FIGURE 28 ( FIGURE 23 and
FIGURE 36, 782 bays)
18.50185.0010CLOSE ACCESS
64.50480.00TOTAL FOR EACH AIRPLANE
Group 34:
Table 29: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.00108.004FIGURE 28 ( FIGURE 23 and
FIGURE 38, 780 bays)
18.50185.0010CLOSE ACCESS
64.00478.00TOTAL FOR EACH AIRPLANE
Group 35:
Table 30: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.50110.004FIGURE 28 ( FIGURE 24 and
FIGURE 36, 783 bays)
18.50185.0010CLOSE ACCESS
64.50480.00TOTAL FOR EACH AIRPLANE
Group 36:
Table 31: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.00108.004FIGURE 28 ( FIGURE 24 and
FIGURE 38, 781 bays)
18.50185.0010CLOSE ACCESS
64.00478.00TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 42 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 37:
Table 32: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
25.00100.004FIGURE 28 ( FIGURE 24 and
FIGURE 37, 711 bays)
18.50185.0010CLOSE ACCESS
62.00470.00TOTAL FOR EACH AIRPLANE
Group 38:
Table 33: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.50110.004FIGURE 28 ( FIGURE 25 and
FIGURE 36, 781 bays)
18.50185.0010CLOSE ACCESS
64.50480.00TOTAL FOR EACH AIRPLANE
Group 39:
Table 34: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.00108.004FIGURE 28 ( FIGURE 25 and
FIGURE 38, 779 bays)
18.50185.0010CLOSE ACCESS
64.00478.00TOTAL FOR EACH AIRPLANE
Group 41:
Table 35: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.00108.004FIGURE 28 ( FIGURE 27 and
FIGURE 36, 779 bays)
18.50185.0010CLOSE ACCESS
64.00478.00TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Table 36: INSPECTION OF CHEM-MILL POCKETS ADJACENT TO CRACK LOCATION
Elapsed HoursTask HoursNumber of PersonsTask
0.50 (a)1.00 (a)2FIGURE 39
0.50 (a)1.00 (a)TOTAL FOR EACH AIRPLANE
(a) The time given is for one repair location.
Table 37: DAMAGED SKIN REMOVAL
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)-FIGURE 40
(a)(a)TOTAL FOR EACH AIRPLANE
(a) The time for one repair is considered variable due to location and size.
Table 38: CUT SURFACE AND FASTENER HOLES INSPECTION
Elapsed HoursTask HoursNumber of PersonsTask
2.50 (a)5.00 (a)2FIGURE 41
2.50 (a)5.00 (a)TOTAL FOR EACH AIRPLANE
(a) The time given is for one repair location.
Table 39: INSURANCE CUT AND SURFACE TREATMENT
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)FIGURE 42
(a)(a)TOTAL FOR EACH AIRPLANE
(a) The time required is considered variable due to location and size.
Table 40: PART 3: CATEGORY C REPAIR INSTALLATION
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)-FIGURE 43
(a)(a)TOTAL FOR EACH AIRPLANE
(a) The time for one repair is considered variable due to location and size.
Table 41: PART 4: CATEGORY C REPAIR INSPECTION
Elapsed HoursTask HoursNumber of PersonsTask
2.502.501FIGURE 44
(a)(a)TOTAL FOR EACH AIRPLANE
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Table 41: PART 4: CATEGORY C REPAIR INSPECTION
Elapsed HoursTask HoursNumber of PersonsTask
(a) Total time required is dependent upon the number of repairs that require inspection.
Table 42: PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, OPTION
1
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)-OPEN ACCESS
16.0032.002FIGURE 45
8.0016.002FIGURE 46
(a)(a)-CLOSE ACCESS
(a)(a)TOTAL FOR EACH AIRPLANE
(a) Total time required is dependent upon the number of repairs that are changed.
Table 43: PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, OPTION
2
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)-OPEN ACCESS
16.0032.002FIGURE 45
8.0016.002FIGURE 47
(a)(a)-CLOSE ACCESS
(a)(a)TOTAL FOR EACH AIRPLANE
(a) Total time required is dependent upon the number of repairs that are changed.
Table 44: PART 7: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION
1
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002FIGURE 48
(a)(a)TOTAL FOR EACH AIRPLANE
(a) Total time required is dependent upon the number of repairs that require inspection.
Table 45: PART 7: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION
2
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002FIGURE 49
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Table 45: PART 7: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION
2
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)TOTAL FOR EACH AIRPLANE
(a) Total time required is dependent upon the number of repairs that require inspection.
Group 40:
Table 46: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
27.25109.004FIGURE 28 ( FIGURE 26 and
FIGURE 36, 781 bays)
18.50185.0010CLOSE ACCESS
64.25479.00TOTAL FOR EACH AIRPLANE
Group 42:
Table 47: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
22.5090.004FIGURE 28 ( FIGURE 56 and
FIGURE 35, 675 bays)
18.50185.0010CLOSE ACCESS
59.50460.00TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
Weight and Balance changes affected by incorporation of this service bulletin are dependent on the
inspection, number of flight cycles, condition, and type of repairs, number and location of repairs done
on each particular airplane. Weight and Balance are to be calculated by the operator by weighing parts
installed or removed. Operators should make necessary revisions to the appropriate weight and balance
report.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Bulletin 737-53A1177, 737-53A1210, 737-53A1262, 737-53A1266
b. Boeing Service Letter 737-SL-00-018, 737-SL-51-042
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
c. Boeing Service Related Problem (SRP) 737-SRP-53-0517, 737-SRP-53-0607
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2003-14-06, 2011-24-12,
2013-18-08, 2015-21-06, 2016-16-13, 2017-23-02
e. Service Bulletin Index D6-19567
f. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-41-05, 20-43-03,
20-44-01, 20-44-04, 20-50-01, 20-50-12, 20-50-19
g. 737 Fleet Team Digest (FTD) 53-15007, 53-19002
h. 737 Non-Destructive Testing (NDT) Manual Part 4, 53-30-05, Part 4, 53-30-06, Part 6, 51-00-00,
Part 6, 53-30-00, Part 6, 53-30-19, Part 6, 53-30-22, Part 6, 53-30-23, Part 6, 53-30-25, Part
6, 53-30-39
i. 737-100/200 Aircraft Maintenance Manual (AMM) 25-21, 25-22-00, 55-32-11
j. 737-100/200 Structural Repair Manual (SRM) 51-30-2, 51-30-3, 51-30-8, 51-50-1, 51-70,
53-30-3
k. 737-300/400/500 Aircraft Maintenance Manual (AMM) 25-21-39, 25-21-45, 25-21-46, 25-22-00,
55-32-11
l. 737-300 Structural Repair Manual (SRM) 51-10-01, 51-40-02, 51-40-03, 51-40-08, 51-50-02,
53-00-01, 53-60-01
m. 737-400 Structural Repair Manual (SRM) 51-10-01, 51-40-02, 51-40-03, 51-40-08, 51-50-02,
53-00-01, 53-60-01
n. 737-500 Structural Repair Manual (SRM) 51-10-01, 51-40-02, 51-40-03, 51-40-08, 51-50-02,
53-00-01, 53-60-01
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Skin Diagram Body - Model 73765-73742
Skin Panel INSTL S-10L to S-10R, STA 727 to STA 101665-45772
Skin Panel INSTL S-10L to S-10R, STA 360 - STA 54065-45765
Skin ASSY - S-10L to S-10R STA 360 - STA 54065C32355
Skin ASSY - S-10L to S-10R STA 727 to STA 90865C32362
Skin Panel INSTL S-10L to S-10R, STA 360 - STA 540 (Rework
Drawing)
65C33816
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
The table above lists applicable drawings used to prepare this service bulletin. These drawings
are not necessary to make the specified changes, and are not supplied with this service bulletin.
These drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected
are contained in 737-100/200 SRM 53-30-3, Figure 48; 737-300 SRM 53-00-01 Repair 31; 737-400
SRM 53-00-01 Repair 31; 737-500 SRM 53-00-01 Repair 31; for the SRM repair. DTI requirements
for the structure affected are contained in Paragraph 1.E., Compliance for the Service Bulletin
Repair. Category C repairs must be modified within the compliance time given in Paragraph 1.E.,
Compliance.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
2. MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The parts are subject to the terms and conditions of the Boeing standard purchase order
acknowledgment. Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
Group 1:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765-609
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765-610
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-611
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772-1001
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772-1002
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-597
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 49 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 2:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765-724
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765-725
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-726
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772-157
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772-158
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-159
(a) ROLT and price information are not available at the time of publication.
Group 3:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765-724
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765-725
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-729
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772-157
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772-158
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-159
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 50 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 3:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 4:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765-724
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765-725
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-729
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772-161
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772-162
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-159
(a) ROLT and price information are not available at the time of publication.
Group 5:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765-609
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Group 5:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765-610
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-618
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772-1001
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772-1002
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-1017
(a) ROLT and price information are not available at the time of publication.
Group 6:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765-606
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765-603
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-602
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772-1005
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772-1006
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-596
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 52 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 7:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765-723
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765-722
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-721
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772-153
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772-154
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-156
(a) ROLT and price information are not available at the time of publication.
Group 8:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765Y98
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 53 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 8:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 9:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765Y98
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y231
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y232
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Group 10:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 54 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 10:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-141
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Group 11:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-141
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y231
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y232
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 55 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 12:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-146
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Group 13:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-227
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 56 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 13:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 14:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765Y233
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Group 15:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 57 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 15:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765Y233
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772-320
(a) ROLT and price information are not available at the time of publication.
Group 16:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765Y233
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y231
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y232
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 58 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 17:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-236
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Group 18:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765Y240
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 59 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 18:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 19:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-289
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Group 20:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 60 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 20:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65-45765-300
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Group 21:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65-45765Y99
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65-45765Y100
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C33816-1
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65-45772Y167
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65-45772Y168
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65-45772Y166
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 61 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 22:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355Y1
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
(a) ROLT and price information are not available at the time of publication.
Group 23:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355-20
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 62 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 23:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 24:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355-30
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
(a) ROLT and price information are not available at the time of publication.
Group 25:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 63 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 25:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355-37
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
(a) ROLT and price information are not available at the time of publication.
Group 26:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355-39
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 64 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 27:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355-45
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
(a) ROLT and price information are not available at the time of publication.
Group 28:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355-53
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 65 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 28:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 29:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355Y27
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Group 30:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 66 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 30:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-47
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Group 31:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355Y27
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y31
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y32
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 67 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 32:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-32
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Group 33:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-48
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 68 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 33:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 34:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-32
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362-33
(a) ROLT and price information are not available at the time of publication.
Group 35:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 69 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 35:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355Y40
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Group 36:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355Y40
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362-33
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 70 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 37:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355Y40
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y31
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y32
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Group 38:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-41
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 71 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 38:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a) ROLT and price information are not available at the time of publication.
Group 39:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-41
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362-33
(a) ROLT and price information are not available at the time of publication.
Group 40:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 72 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 40:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-49
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Group 41:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 540
65C32355Y21
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 540
65C32355Y22
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 540
65C32355-51
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727 TO STA 908
65C32362Y19
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727 TO STA 908
65C32362Y20
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 727
TO STA 908
65C32362Y21
(a) ROLT and price information are not available at the time of publication.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 73 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 42:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original issue
date of this Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
360 TO STA 500C
65C32355Y3
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
360 TO STA 500C
65C32355Y4
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA 360
TO STA 500C
65C32355-34
(a)(a)SKIN PANEL ASSY S-4L TO S-10L, STA
727G TO STA 908
65C32362Y5
(a)(a)SKIN PANEL ASSY S-4R TO S-10R, STA
727G TO STA 908
65C32362Y6
(a)(a)SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
65C32362Y2
(a) ROLT and price information are not available at the time of publication.
Operators are encouraged to complete the survey provided in APPENDIX F of this service bulletin to
help Boeing predict the quantity and timing of the Boeing Supplied Parts.
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and repair procedures given in this
service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Group 1:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765-609
-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765-610
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 74 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 1:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-611
-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772-1001
-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772-1002
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-597
Group 2:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765-724
-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765-725
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-726
-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772-157
-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772-158
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-159
Group 3:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765-724
-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765-725
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-729
-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772-157
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 3:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772-158
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-159
Group 4:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765-724
-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765-725
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-729
-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772-161
-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772-162
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-159
Group 5:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765-609
-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765-610
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-618
-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772-1001
-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772-1002
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-1017
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 76 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 6:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765-606
-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765-603
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-602
-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772-1005
-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772-1006
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-596
Group 7:
NotesExisting Part
Number
NameQTYNew Part Number
-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765-723
-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765-722
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-721
-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772-153
-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772-154
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-156
Group 8:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 77 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 8:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765Y98
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 9:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765Y98
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y231
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y232
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 78 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 10:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-141
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 11:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-141
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y231
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y232
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 79 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 11:
NotesExisting Part
Number
NameQTYNew Part Number
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 12:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-146
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 13:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-227
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 80 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 13:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 14:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765Y233
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 15:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765Y233
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772-320
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 16:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765Y233
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y231
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y232
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 82 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 16:
NotesExisting Part
Number
NameQTYNew Part Number
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 17:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-236
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 18:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765Y240
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 83 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 18:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 19:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-289
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 84 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 20:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165-45765-300
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 21:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165-45765Y99
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165-45765Y100
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C33816-1
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165-45772Y167
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165-45772Y168
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165-45772Y166
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 85 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 21:
NotesExisting Part
Number
NameQTYNew Part Number
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 22:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355Y1
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 23:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355-20
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 86 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 23:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 24:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355-30
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 87 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 25:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355-37
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 26:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355-39
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 88 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 26:
NotesExisting Part
Number
NameQTYNew Part Number
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 27:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355-45
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 28:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355-53
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 89 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 28:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 29:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355Y27
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 90 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 30:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-47
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 31:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355Y27
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y31
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y32
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 91 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 31:
NotesExisting Part
Number
NameQTYNew Part Number
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 32:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-32
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 33:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-48
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 92 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 33:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 34:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-32
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362-33
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 93 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Group 35:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355Y40
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 36:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355Y40
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362-33
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Group 36:
NotesExisting Part
Number
NameQTYNew Part Number
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 37:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355Y40
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y31
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y32
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 38:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-41
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Group 38:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 39:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-41
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362-33
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
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Group 40:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-49
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 41:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 540
165C32355Y21
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 540
165C32355Y22
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 540
165C32355-51
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727 TO STA 908
165C32362Y19
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727 TO STA 908
165C32362Y20
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727 TO STA 908
165C32362Y21
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Group 41:
NotesExisting Part
Number
NameQTYNew Part Number
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
Group 42:
NotesExisting Part
Number
NameQTYNew Part Number
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 360 TO STA 500C
165C32355Y3
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 360 TO STA 500C
165C32355Y4
-SKIN PANEL ASSY S-4L TO S-4R, STA
360 TO STA 500C
165C32355-34
(a)-SKIN PANEL ASSY S-4L TO S-10L,
STA 727G TO STA 908
165C32362Y5
(a)-SKIN PANEL ASSY S-4R TO S-10R,
STA 727G TO STA 908
165C32362Y6
(a)-SKIN PANEL ASSY S-4L TO S-4R, STA
727G TO STA 908
165C32362Y2
(a) To make installation easier, some Boeing parts are sent in an 'interim' configuration. Boeing
will identify these interim configurations with a 'U', 'W' or 'Y' in place of the '-' (dash) in the
part number. Interim parts are changed to the 'dash' configuration when installed as given
in the Accomplishment Instructions of this service bulletin. Refer to Boeing Drawing
005W0900 "INTERIM PARTS - SPARES" and Boeing Service Letter 737-SL-00-018 for
more information.
2. Parts and Materials Supplied by the Operator
Table 1: PART 3: CATEGORY C REPAIR
NotesNameQtyPart Number/ Specifica-
tion
(a)(b)Repair DoublerAs required2024-T3 CLAD SHEET
0.050 INCH
(b)(g)Chemical Conversion
Coating
1 PintChemical Conversion
Coating, type 2, Class A
(b)(c)(e)(h)Primer1 QuartBMS 10-79, Type III
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Table 1: PART 3: CATEGORY C REPAIR
NotesNameQtyPart Number/ Specifica-
tion
(b)(c)(d)Sealant1 PintBMS 5-95, Class B
(b)(f)Blind Rivet113BACR15FR5F()R or
BACR15FR6F()R
(a) Make in accordance with FIGURE 43.
(b) Parts required for one Category C repair. Operator should keep sufficient quantity in stock for possible
crack findings. Quantities listed are only recommendations, more or less can be stocked at Operator dis-
cretion.
(c) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
(d) Refer to SOPM 20-50-12 for a list of suppliers.
(e) Refer to SOPM 20-44-04.
(f) BACR15FR6F()R is an optional alternative fastener if hole enlargement is required or is a required fastener
if the production fastener is 3/16 inch diameter, unless stated otherwise.
(g) Refer to SOPM 20-43-03 for a list of suppliers and alternates.
(h) Some conversion coatings contain Chromium trioxide/Chromic acid and will not be available in the European
Union after September 2017 without an authorization. EU operators are encouraged to ensure their sup-
pliers are authorized to provide the material after the sunset date and that downstream users comply with
the risk mitigation measures and operational conditions.
Table 2: PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, OPTION 1
NotesNameQtyPart Number/ Specifica-
tion
(a)(b)Internal Tear Strap Dou-
bler / Tapered Filler
As required2024-T3 CLAD SHEET
0.040 INCH
(b)(c)Chemical Conversion
Coating
1 PintChemical Conversion
Coating, Type 2, Class A
(b)(d)(g)(h)Primer1 QuartBMS 10-11, Type I
(b)(d)(e)Sealant1 PintBMS 5-95, Class B
(b)(d)Organic Corrosion Inhibit-
ing Compound
1 QuartBMS 3-23, Type II, Class
2
(b)(f)Rivet92BACR15BB6D()C or
BACR15BB7AD()C
(b)(f)Rivet34BACR15BB6AD()C or
BACR15BB7AD()C
(a) Make in accordance with FIGURE 46.
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Table 2: PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, OPTION 1
NotesNameQtyPart Number/ Specifica-
tion
(b) Parts required for changing one Category C repair to Service Bulletin Repair, Option 1. Operator should
keep sufficient quantity in stock for possible crack findings. Quantities listed are only recommendations,
more or less can be stocked at Operator discretion.
(c) Refer to SOPM 20-43-03 for a list of suppliers and alternates.
(d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
(e) Refer to SOPM 20-50-12 for a list of suppliers.
(f) BACR15BB7AD()C is an optional alternative fastener if hole enlargement is required, unless stated other-
wise.
(g) Refer to SOPM 20-41-02.
(h) Some conversion coatings contain Chromium trioxide/Chromic acid and will not be available in the European
Union after September 2017 without an authorization. EU operators are encouraged to ensure their sup-
pliers are authorized to provide the material after the sunset date and that downstream users comply with
the risk mitigation measures and operational conditions.
Table 3: PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, OPTION 2
NotesNameQtyPart Number/ Specifica-
tion
(a)(b)Repair DoublerAs required2024-T3 CLAD SHEET
0.050 INCH
(a)(b)Internal Tear Strap Dou-
bler / Tapered Filler
As required2024-T3 CLAD SHEET
0.040 INCH
(b)(c)Chemical Conversion
Coating
1 PintChemical Conversion
Coating, Type 2, Class A
(b)(d)(g)(h)Primer1 QuartBMS 10-79, Type III
(b)(d)(e)Sealant1 PintBMS 5-95, Class B
(b)(d)Organic Corrosion Inhibit-
ing Compound
1 QuartBMS 3-23, Type II, Class
2
(b)(f)Rivet134BACR15BB6D()C or
BACR15BB7AD()C
(b)(f)Rivet42BACR15BB6AD()C or
BACR15BB7AD()C
(a) Make in accordance with FIGURE 47.
(b) Parts required for changing one Category C repair to Service Bulletin Repair, Option 2. Operator should
keep sufficient quantity in stock for possible crack findings. Quantities listed are only recommendations,
more or less can be stocked at Operator discretion.
(c) Refer to SOPM 20-43-03 for a list of suppliers and alternates.
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Table 3: PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, OPTION 2
NotesNameQtyPart Number/ Specifica-
tion
(d) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
(e) Refer to SOPM 20-50-12 for a list of suppliers.
(f) BACR15BB7AD()C is an optional alternative fastener if hole enlargement is required, unless otherwise
stated.
(g) Refer to SOPM 20-44-04.
(h) Some conversion coatings contain Chromium trioxide/Chromic acid and will not be available in the European
Union after September 2017 without an authorization. EU operators are encouraged to ensure their sup-
pliers are authorized to provide the material after the sunset date and that downstream users comply with
the risk mitigation measures and operational conditions.
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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BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF
METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED
MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE
BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES
CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE.
CAUTION
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– 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 737 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 737
Aircraft Maintenance Manual (AMM).
— Values for engine maintenance tasks are included in Chapter 70 of 737
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
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.
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7. A General Visual Inspection is defined as: A visual examination of an interior or
exterior area, installation or assembly to detect obvious damage, failure or irregularity.
This level of inspection is made from within touching distance unless otherwise
specified. A mirror may be necessary to enhance visual access to all exposed surfaces
in the inspection area. This level of inspection is made under normally available
lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may
require removal or opening of access panels or doors. Stands, ladders or platforms
may be required to gain proximity to the area being checked.
8. Any inspection of horizontal chem-mill steps applies to chem-mill steps that are less
than 45 degrees from horizontal.
9. 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.
10. Boeing Service Letter 737-SL-51-042, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
11. Refer to APPENDIX E production skin panel installation drawings for approved
replacement skin panels.
12. Refer to APPENDIX A, APPENDIX B, APPENDIX C, and APPENDIX D 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.
13. 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.
14. 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.
15. 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.
16. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is
permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'
(dash) part number. Boeing Drawing 005W0900 contains more data.
17. Use of colors in Figures is based on guidance from the ATA e-Business Program
(ATA) iSpec 2200.
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18. 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.
19. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
20. 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.
21. Refer to Airplane Flight Manual Appendix entitled "PERFORMANCE ADJUSTMENTS
FOR OPERATIONS WITH EXTENSIVE FUSELAGE REPAIRS" for performance
adjustment guidance.
B. WORK INSTRUCTIONS
1. Airplanes that have had a crown skin panel replaced with a production skin panel before 47,000
total flight cycles and have a record of the skin panel replacement
a. RC - Contact The Boeing Company for work instructions and do the work.
2. Airplanes that have had a crown skin panel replaced with a production skin panel after 46,999
total flight cycles and have a record of the skin panel replacement.
a. No further action required for the replacement skin panel.
3. Airplanes that have a crown skin panel that has never been replaced or if the operator has no
record of the production skin panel replacement and have not accomplished inspections in
accordance with the original issue of this service bulletin.
a. RC - Do PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL
NON-DESTRUCTIVE INSPECTION (NDI) for any crack on the production skin panel.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers provided
either:
1. The installed repair or modification was approved by the FAA or by a Boeing
Company authorized representative who was authorized by the FAA to
make such findings, and the installed repair extends a minimum of three
rows of fasteners on each side of the chem-mill line; or
2. The external repair doubler satisfies the following:
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– The installed repair or modification was approved by the FAA or by a
Boeing Company authorized representative who was authorized by
the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of 3/16 inch
diameter fasteners on each side of the chem-mill step in the
circumferential direction with 5-6D fastener spacing; and either:
– The repair or modification is similar to 737-100/200 SRM 53-30-3
Figure 48 or 737-300 SRM 53-00-01 Repair 31 or 737-400 SRM
53-00-01 Repair 31 or 737-500 SRM 53-00-01 Repair 31 with
regard to fastener type, size, layout and pitch, repair part thickness
and material, and repair installation; or
– The repair or modification is similar to 737-300/400/500 SRM
53-60-01 Repair 9 or Repair 14 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and repair
installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to
the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) inspections.
(1) CONDITION 1: NO CRACK FOUND.
(a) Repeat PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL
NON-DESTRUCTIVE INSPECTION (NDI) for any crack at the times specified in
Paragraph 1.E., Compliance.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers
provided either:
1. The installed repair or modification was approved by the FAA or
by a Boeing Company authorized representative who was
authorized by the FAA to make such findings, and the installed
repair extends a minimum of three rows of fasteners on each side
of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA
or by a Boeing Company authorized representative who was
authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of
3/16 inch diameter fasteners on each side of the chem-mill
step in the circumferential direction with 5-6D fastener spacing;
and either:
– The repair or modification is similar to 737-100/200 SRM
53-30-3 Figure 48 or 737-300 SRM 53-00-01 Repair 31
or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM
53-00-01 Repair 31 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and
repair installation; or
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 106 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
– The repair or modification is similar to 737-300/400/500
SRM 53-60-01 Repair 9 or Repair 14 with regard to
fastener type, size, layout and pitch, repair part thickness
and material, and repair installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections.
(2) CONDITION 2: ANY CRACK FOUND.
(a) OPTION 1 (ACTION 1): Do PART 2: SRM REPAIR.
NOTE: The applicability limitations and post repair inspection requirements of PART
2: SRM REPAIR are in PART 2 and 737-100/200 SRM 53-30-3 Figure 48,
737-300 SRM 53-00-01 Repair 31, 737-400 SRM 53-00-01 Repair 31 or
737-500 SRM 53-00-01 Repair 31.
(b) OPTION 1 (ACTION 2): Repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) for any crack at
the times specified in Paragraph 1.E., Compliance.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers
provided either:
1. The installed repair or modification was approved by the FAA or
by a Boeing Company authorized representative who was
authorized by the FAA to make such findings, and the installed
repair extends a minimum of three rows of fasteners on each side
of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA
or by a Boeing Company authorized representative who was
authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of
3/16 inch diameter fasteners on each side of the chem-mill
step in the circumferential direction with 5-6D fastener spacing;
and either:
– The repair or modification is similar to 737-100/200 SRM
53-30-3 Figure 48 or 737-300 SRM 53-00-01 Repair 31
or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM
53-00-01 Repair 31 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and
repair installation; or
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PROPRIETARY - Copyright © Unpublished
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 107 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
– The repair or modification is similar to 737-300/400/500
SRM 53-60-01 Repair 9 or Repair 14 with regard to
fastener type, size, layout and pitch, repair part thickness
and material, and repair installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections.
NOTE: Accomplishment of PART 2: SRM REPAIR is terminating action to the
service bulletin repeat inspections at the SRM repair location only.
(c) OPTION 2 (ACTION 1): Do PART 3: CATEGORY C REPAIR.
NOTE: The applicability limitations of the Category C repair are in PART 3:
CATEGORY C REPAIR.
NOTE: Compliance times for post-repair inspections of Category C repairs done
in accordance with PART 3: CATEGORY C REPAIR are in Table 2 of
Paragraph 1.E., Compliance.
(d) OPTION 2 (ACTION 2): Repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) for any crack at
the times specified in Paragraph 1.E., Compliance.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers
provided either:
1. The installed repair or modification was approved by the FAA or
by a Boeing Company authorized representative who was
authorized by the FAA to make such findings, and the installed
repair extends a minimum of three rows of fasteners on each side
of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA
or by a Boeing Company authorized representative who was
authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of
3/16 inch diameter fasteners on each side of the chem-mill
step in the circumferential direction with 5-6D fastener spacing;
and either:
– The repair or modification is similar to 737-100/200 SRM
53-30-3 Figure 48 or 737-300 SRM 53-00-01 Repair 31
or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM
53-00-01 Repair 31 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and
repair installation; or
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 108 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
– The repair or modification is similar to 737-300/400/500
SRM 53-60-01 Repair 9 or Repair 14 with regard to
fastener type, size, layout and pitch, repair part thickness
and material, and repair installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections.
NOTE: Accomplishment of PART 3: CATEGORY C REPAIR is terminating action
to the service bulletin repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections under the Category C repair location only.
4. Airplanes that have a crown skin panel that has never been replaced or if the operator has no
record of the production skin panel replacement and have accomplished inspections in accordance
with the original issue of this service bulletin.
a. RC - Do PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL
NON-DESTRUCTIVE INSPECTION (NDI) for any crack on the production skin panel.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers provided
either:
1. The installed repair or modification was approved by the FAA or by a Boeing
Company authorized representative who was authorized by the FAA to
make such findings, and the installed repair extends a minimum of three
rows of fasteners on each side of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA or by a
Boeing Company authorized representative who was authorized by
the FAA to make such findings; and.
– The repair or modification extends a minimum of 2 rows of 3/16 inch
diameter fasteners on each side of the chem-mill step in the
circumferential direction with 5-6D fastener spacing; and either:
– The repair or modification is similar to 737-100/200 SRM 53-30-3
Figure 48 or 737-300 SRM 53-00-01 Repair 31 or 737-400 SRM
53-00-01 Repair 31 or 737-500 SRM 53-00-01 Repair 31 with
regard to fastener type, size, layout and pitch, repair part thickness
and material, and repair installation; or
– The repair or modification is similar to 737-300/400/500 SRM
53-60-01 Repair 9 or Repair 14 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and repair
installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to
the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) inspections.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
(1) CONDITION 1: NO CRACK FOUND.
(a) Repeat PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL
NON-DESTRUCTIVE INSPECTION (NDI) for any crack at the times specified in
Paragraph 1.E., Compliance.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers
provided either:
1. The installed repair or modification was approved by the FAA or
by a Boeing Company authorized representative who was
authorized by the FAA to make such findings, and the installed
repair extends a minimum of three rows of fasteners on each side
of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA
or by a Boeing Company authorized representative who was
authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of
3/16 inch diameter fasteners on each side of the chem-mill
step in the circumferential direction with 5-6D fastener spacing;
and either:
– The repair or modification is similar to 737-100/200 SRM
53-30-3 Figure 48 or 737-300 SRM 53-00-01 Repair 31
or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM
53-00-01 Repair 31 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and
repair installation; or
– The repair or modification is similar to 737-300/400/500
SRM 53-60-01 Repair 9 or Repair 14 with regard to
fastener type, size, layout and pitch, repair part thickness
and material, and repair installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections.
(2) CONDITION 2: ANY CRACK FOUND.
(a) OPTION 1 (ACTION 1): Do PART 2: SRM REPAIR.
NOTE: The applicability limitations and post repair inspection requirements of PART
2: SRM REPAIR are in PART 2 and 737-100/200 SRM 53-30-3 Figure 48,
737-300 SRM 53-00-01 Repair 31, 737-400 SRM 53-00-01 Repair 31 or
737-500 SRM 53-00-01 Repair 31.
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
(b) OPTION 1 (ACTION 2): Repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) for any crack at
the times specified in Paragraph 1.E., Compliance.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers
provided either:
1. The installed repair or modification was approved by the FAA or
by a Boeing Company authorized representative who was
authorized by the FAA to make such findings, and the installed
repair extends a minimum of three rows of fasteners on each side
of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA
or by a Boeing Company authorized representative who was
authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of
3/16 inch diameter fasteners on each side of the chem-mill
step in the circumferential direction with 5-6D fastener spacing;
and either:
– The repair or modification is similar to 737-100/200 SRM
53-30-3 Figure 48 or 737-300 SRM 53-00-01 Repair 31
or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM
53-00-01 Repair 31 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and
repair installation; or
– The repair or modification is similar to 737-300/400/500
SRM 53-60-01 Repair 9 or Repair 14 with regard to
fastener type, size, layout and pitch, repair part thickness
and material, and repair installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections.
NOTE: Accomplishment of PART 2: SRM REPAIR is terminating action to the
service bulletin repeat inspections at the SRM repair location only.
(c) OPTION 2 (ACTION 1): Do PART 3: CATEGORY C REPAIR.
NOTE: The applicability limitations of the Category C repair are in PART 3:
CATEGORY C REPAIR.
NOTE: Compliance times for post-repair inspections of Category C repairs done
in accordance with PART 3: CATEGORY C REPAIR are in Table 2 of
Paragraph 1.E., Compliance.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 111 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
(d) OPTION 2 (ACTION 2): Repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) for any crack at
the times specified in Paragraph 1.E., Compliance.
NOTE: It is not required to inspect the chem-mill steps under existing repair doublers
provided either:
1. The installed repair or modification was approved by the FAA or
by a Boeing Company authorized representative who was
authorized by the FAA to make such findings, and the installed
repair extends a minimum of three rows of fasteners on each side
of the chem-mill line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification repair approved by the
FAA or by a Boeing Company authorized representative who
was authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of
3/16 inch diameter fasteners on each side of the chem-mill
step in the circumferential direction with 5-6D fastener spacing;
and either:
– The repair or modification is similar to 737-100/200 SRM
53-30-3 Figure 48 or 737-300 SRM 53-00-01 Repair 31
or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM
53-00-01 Repair 31 with regard to fastener type, size,
layout and pitch, repair part thickness and material, and
repair installation; or
– The repair or modification is similar to 737-300/400/500
SRM 53-60-01 Repair 9 or Repair 14 with regard to
fastener type, size, layout and pitch, repair part thickness
and material, and repair installation.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections.
NOTE: Accomplishment of PART 3: CATEGORY C REPAIR is terminating action
to the service bulletin repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI)
inspections under the Category C repair location only.
5. Airplanes with any Category C repair installed in accordance with the Original Issue or any revision
of this service bulletin.
a. RC - Do PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR for any loose or
missing fastener.
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 112 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
NOTE: Accomplishment of PART 6: CHANGE CATEGORY C REPAIR TO SERVICE
BULLETIN REPAIR is terminating action to initial and repeat PART 4: POST REPAIR
INSPECTION OF CATEGORY C REPAIR inspections at the repaired location only.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to
PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR and terminates
the requirement to do PART 6: CHANGE CATEGORY C REPAIR TO SERVICE
BULLETIN REPAIR.
(1) CONDITION 3: ANY LOOSE OR MISSING FASTENER FOUND.
(a) CONDITION 3 (ACTION 1): Do PART 5: POST CATEGORY C REPAIR FASTENER
REPLACEMENT.
(b) CONDITION 3 (ACTION 2): Repeat PART 4: POST REPAIR INSPECTION OF
CATEGORY C REPAIR for any loose or missing fastener at the times specified in
Paragraph 1.E., Compliance.
NOTE: Accomplishment of PART 6: CHANGE CATEGORY C REPAIR TO
SERVICE BULLETIN REPAIR is terminating action to initial and repeat
PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
inspections at the repaired location only.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
and terminates the requirement to do PART 6: CHANGE CATEGORY C
REPAIR TO SERVICE BULLETIN REPAIR.
(c) CONDITION 3 (ACTION 3): Do PART 6: CHANGE CATEGORY C REPAIR TO
SERVICE BULLETIN REPAIR at the times specified in Paragraph 1.E., Compliance.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
and terminates the requirement to do PART 6: CHANGE CATEGORY C
REPAIR TO SERVICE BULLETIN REPAIR.
NOTE: The applicability limitations of the Service Bulletin Repair are in PART 6:
CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR.
NOTE: Compliance times for inspection of Service Bulletin Repairs done in
accordance with PART 6: CHANGE CATEGORY C REPAIR TO SERVICE
BULLETIN REPAIR are in Table 3 of Paragraph 1.E., Compliance.
(2) CONDITION 4: NO LOOSE OR MISSING FASTENER FOUND.
(a) CONDITION 4 (ACTION 1): Repeat PART 4: POST REPAIR INSPECTION OF
CATEGORY C REPAIR for any loose or missing fastener at the times specified in
Paragraph 1.E., Compliance.
NOTE: Accomplishment of PART 6: CHANGE CATEGORY C REPAIR TO
SERVICE BULLETIN REPAIR is terminating action to initial and repeat
PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
inspections at the repaired location only.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 113 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
and terminates the requirement to do PART 6: CHANGE CATEGORY C
REPAIR TO SERVICE BULLETIN REPAIR.
(b) CONDITION 4 (ACTION 2): Do PART 6: CHANGE CATEGORY C REPAIR TO
SERVICE BULLETIN REPAIR at the times specified in Paragraph 1.E., Compliance.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
and terminates the requirement to do PART 6: CHANGE CATEGORY C
REPAIR TO SERVICE BULLETIN REPAIR.
NOTE: The applicability limitations of the Service Bulletin Repair are in PART 6:
CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR.
NOTE: Compliance times for inspection of Service Bulletin Repairs done in
accordance with PART 6: CHANGE CATEGORY C REPAIR TO SERVICE
BULLETIN REPAIR are in Table 3 of Paragraph 1.E., Compliance.
6. Airplanes with any Service Bulletin Repair installed in accordance with PART 6: CHANGE
CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, Option 1.
a. RC - Do PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION
OF SERVICE BULLETIN REPAIR for any crack.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to
the initial and repeat PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTION OF SERVICE BULLETIN REPAIR inspections.
(1) CONDITION 5: ANY CRACK FOUND.
(a) Contact The Boeing Company for repair instructions and do the repair.
(2) CONDITION 6: NO CRACK FOUND.
(a) Repeat PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT (LFEC)
INSPECTION OF SERVICE BULLETIN REPAIR for any crack at the times specified
in Paragraph 1.E., Compliance.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 7: POST REPAIR LOW FREQUENCY
EDDY CURRENT (LFEC) INSPECTION OF SERVICE BULLETIN REPAIR
inspections.
7. Airplanes with any Service Bulletin Repair installed in accordance with PART 6: CHANGE
CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR, Option 2.
a. RC - Do PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION
OF SERVICE BULLETIN REPAIR for any crack.
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Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 114 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating action to
the initial and repeat PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT
(LFEC) INSPECTION OF SERVICE BULLETIN REPAIR inspections.
(1) CONDITION 5: ANY CRACK FOUND.
(a) Contact The Boeing Company for repair instructions and do the repair.
(2) CONDITION 6: NO CRACK FOUND.
(a) Repeat PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT (LFEC)
INSPECTION OF SERVICE BULLETIN REPAIR for any crack at the times specified
in Paragraph 1.E., Compliance.
NOTE: Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 7: POST REPAIR LOW FREQUENCY
EDDY CURRENT (LFEC) INSPECTION OF SERVICE BULLETIN REPAIR
inspections.
8. Airplanes that have had a crown skin panel replaced with a production skin panel after 46,999
total flight cycles and have a record of the skin panel replacement.
a. No further action required for the replacement skin panel.
9. Airplanes that have a crown skin panel that has never been replaced or the operator has no record
of the skin panel replacement.
a. RC - Do PART 8: SKIN PANEL REPLACEMENT.
10. Airplanes that have had a crown skin panel replaced before 47,000 total flight cycles with a
production skin panel and the operator has a record of the skin panel replacement.
a. RC - Contact The Boeing Company for work instructions and do the work.
11. Group 43:
The Boeing Company endorses the new FAA rules related to Limit of Validity (LOV) and
recommends immediate and permanent removal from service of any airplanes upon reaching the
LOV, whether or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer
provides maintenance instructions for airplanes that have accumulated flight cycles beyond the
LOV. Airplanes in Group 43 (line number 1-291) have accumulated flight cycles beyond the LOV
of the maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane
beyond its LOV.
12. Put the airplane back to serviceable condition.
PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
1. RC Exempt - Get access to the crown skin.
2. Group 1-2:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 1, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
3. Group 3-4:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 2, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
4. Group 5:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 3, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
5. Group 6-7:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 4, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
6. Group 8-9:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 5, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
7. Group 10-11:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 6, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
8. Group 12:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 7, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
9. Group 13:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 8, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
10. Group 14-16:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 9, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
11. Group 17:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 10, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
12. Group 18:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 11, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
13. Group 19:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 12, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
14. Group 20:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 13, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
15. Group 21:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 14, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
16. Group 22:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 15, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
17. Group 23:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 16, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
18. Group 24:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 17, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
19. Group 25:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 18, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
20. Group 26:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 19, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
21. Group 27:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 20, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
22. Group 28:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 21, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
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23. Group 29-31:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 22, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
24. Group 32-34:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 23, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
25. Group 35-37:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 24, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
26. Group 38-39:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 25, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
27. Group 40:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 26, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
28. Group 41:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 540 in accordance
with FIGURE 27, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
29. Group 42:
Find the skin pockets in the area from S-10L to S-10R and from STA 360 to STA 500C in
accordance with FIGURE 56, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
30. Group 1-4:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 29, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
31. Group 5:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 30, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
32. Group 6-7:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 31, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
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33. Group 8, 10, 12-14, 17-21:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 32, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
34. Group 9, 11, 16:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 33, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
35. Group 15:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 34, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
36. Group 22-28, 42:
Find the skin pockets in the area from S-10L to S-10R and from STA 727G to STA 908 in
accordance with FIGURE 35, and do a non-destructive inspection of each chem-mill step for any
crack in accordance with FIGURE 28.
37. Group 29-30, 32-33, 35, 38, 40-41:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 36, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
38. Group 31, 37:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 37, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
39. Group 34, 36, 39:
Find the skin pockets in the area from S-10L to S-10R and from STA 727 to STA 908 in accordance
with FIGURE 38, and do a non-destructive inspection of each chem-mill step for any crack in
accordance with FIGURE 28.
PART 2: SRM REPAIR
1. RC Exempt - Get access to the internal side of the skin at the crack location, as follows:
Group 1-7:
a. Remove and keep the passenger seats. Refer to 737-100/200 AMM 25-22-00 as an accepted
procedure.
b. Remove and keep the cabin lining and insulation. Refer to 737-100/200 AMM 25-21 as an
accepted procedure.
c. Remove and keep the ceiling lining. Refer to 737-100/200 AMM 25-21 as an accepted
procedure.
d. Remove and keep the ceiling insulation. Refer to 737-100/200 AMM 25-21 as an accepted
procedure.
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Group 8-42:
a. Remove and keep the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an
accepted procedure.
b. Remove and keep the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM
25-21-46 as an accepted procedure.
c. Remove and keep the sculptured ceiling panels. Refer to 737-300/400/500 AMM 25-21-45
as an accepted procedure.
d. Remove and keep the sidewall and ceiling insulation. Refer to 737-300/400/500 AMM 25-21-39
as an accepted procedure.
NOTE: SRM 737-300/-400/500 Repair 31 for chem-mill cracks cannot be used if the repair
will extend into dorsal fin area for 737-300/-400/-500 Airplanes: in the area from S-2L
to S-2R, and from STA 855 to STA 908.
2. Group 1-7:
Repair chem-mill cracks in accordance with 737-100/200 SRM 53-30-3, Figure 48.
3. Group 8-21:
Repair chem-mill cracks in accordance with 737-300 SRM 53-00-01, Repair 31.
4. Group 22-28, 42:
Repair chem-mill cracks in accordance with 737-400 SRM 53-00-01, Repair 31.
5. Group 29-41:
Repair chem-mill cracks in accordance with 737-500 SRM 53-00-01, Repair 31.
6. RC Exempt - Install the furnishings that were removed for access:
Group 1-7:
a. Install kept ceiling insulation. Refer to 737-100/200 AMM 25-21 as an accepted procedure.
b. Install kept ceiling lining. Refer to 737-100/200 AMM 25-21 as an accepted procedure.
c. Install kept cabin lining and insulation. Refer to 737-100/200 AMM 25-21 as an accepted
procedure.
d. Install kept passenger seats. Refer to 737-100/200 AMM 25-22-00 as an accepted procedure.
Group 8-42:
a. Install kept sidewall and ceiling insulation. Refer to 737-300/400/500 AMM 25-21-39 as an
accepted procedure.
b. Install kept sculptured ceiling panels. Refer to 737-300/400/500 AMM 25-21-45 as an accepted
procedure.
c. Install kept passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an
accepted procedure.
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d. Install kept passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted
procedure.
PART 3: CATEGORY C REPAIR
1. The Category C repair option has the limitations that follow:
a. This repair cannot be used if the repair will extend into the following locations:
(1) 737-200/-200C Airplanes: in the area from S-4L to S-4R, and from STA 727 to STA 727+8.
(2) 737-300 Airplanes: in the area from S-4L to S-4R, and from STA 727 to STA 727C.
(3) 737-500 Airplanes: in the area from S-4L to S-4R, and from STA 727 to 727A+8.
(4) 737-300/400/500 Airplanes: in the area from S-2L to S-2R, and from STA 855 to STA
908.
b. This repair can only be used to repair chem-mill cracking in one skin pocket at a time. This
repair cannot be used in areas where there is an existing repair within 40 inches. If multiple
repairs are being installed, make sure that the repairs are at least 40 inches away from each
other.
c. This repair cannot be used if the fasteners that exist are larger than 3/16 inch diameter.
d. This repair cannot be used in areas where hi-loks, lockbolts or other bolts were installed in
production.
e. The category c repair cannot be installed in an area where it would be common to fuselage
skin lap joint, butt joint and within 3 inches of the fuselage skin cutout.
f. The category C repair cannot be used where it would be common to the door cutout bear
strap locations.
g. If PART 3: CATEGORY C REPAIR cannot be accomplished due to the reasons stated above,
do PART 2: SRM REPAIR.
h. All NDI inspections common to and in the bays adjacent to the repair required by this bulletin
were accomplished in this maintenance check.
2. Do a detailed inspection of the skin in the chem-mill pockets adjacent to the repair area for any
corrosion or disbonded doublers in accordance with FIGURE 39. Do NDI of the skin in the chem-mill
pockets adjacent to the repair area for any crack in accordance with FIGURE 39. NDI of the skin
in the chem-mill pockets adjacent to the cracked chem-mill pocket is not required if PART 1:
CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI has been accomplished in these
chem-mill pockets during this maintenance visit.
a. For any corrosion or any disbond found, contact The Boeing Company for repair instructions
and do the repair.
b. For any crack found, do PART 2: SRM REPAIR.
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c. For no corrosion and no disbond, and no crack in the adjacent chem-milled pockets is found;
remove fasteners and damaged skin in accordance with FIGURE 40.
3. Do a High Frequency Eddy Current (HFEC) inspection of the edge of the cut skin surface, and of
the production fastener holes and the production fasteners' countersink surfaces common to the
repair area for any crack in accordance with FIGURE 41.
a. For any crack found in the edge of the cut skin surface, repeat the steps that follow until the
crack is removed:
(1) Make the skin cutout larger to remove the crack.
(2) Do a HFEC inspection of the edge of the cut skin surface for any crack in accordance
with FIGURE 41.
b. For skin cutouts that extend into the production bonded doubler, do PART 2: SRM REPAIR.
c. For any crack found in the production fastener holes common to the repair area or in the
production fasteners' countersink surfaces common to the repair area, do PART 2: SRM
REPAIR.
4. For skin cutouts that do not extend into the production bonded doubler after crack removal, and
for no crack found in the production fastener holes and the production fasteners' countersink
surfaces common to the repair area, do the steps that follow:
a. Do the insurance cut and surface treatment in accordance with FIGURE 42.
(1) For any skin cutout that will extend into the production bonded doubler, do PART 2: SRM
REPAIR.
5. Do the Category C repair in accordance with FIGURE 43.
PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
1. Do a general visual inspection for any loose or missing fastener in accordance with FIGURE 44.
PART 5: POST CATEGORY C REPAIR FASTENER REPLACEMENT
1. Replace all loose or missing fasteners with the same size and type used during the Category C
repair installation. Refer to FIGURE 43 for the fastener size and type used during the PART 3:
CATEGORY C REPAIR installation.
PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR
1. RC Exempt - Get access to the internal side of the Category C repair:
Group 1-7:
a. Remove and keep the passenger seats. Refer to 737-100/200 AMM 25-22-00 as an accepted
procedure.
b. Remove and keep the cabin lining and insulation. Refer to 737-100/200 AMM 25-21 as an
accepted procedure.
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c. Remove and keep the ceiling lining. Refer to 737-100/200 AMM 25-21 as an accepted
procedure.
d. Remove and keep the ceiling insulation. Refer to 737-100/200 AMM 25-21 as an accepted
procedure.
Group 8-42:
a. Remove and keep the passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an
accepted procedure.
b. Remove and keep the passenger cabin sidewall panels. Refer to 737-300/400/500 AMM
25-21-46 as an accepted procedure.
c. Remove and keep the sculptured ceiling panels. Refer to 737-300/400/500 AMM 25-21-45
as an accepted procedure.
d. Remove and keep the sidewall and ceiling insulation. Refer to 737-300/400/500 AMM 25-21-39
as an accepted procedure.
2. Do pre-repair conversion inspections for any crack in accordance with FIGURE 45.
3. Do one of the permanent repair options that follow:
OPTION 1: MAKE THE CATEGORY C REPAIR PERMANENT BY INSTALLING SOLID
FASTENERS AND INSTALLING INTERNAL TEAR STRAP DOUBLERS
a. Make the Category C repair permanent in accordance with FIGURE 46.
OPTION 2: MAKE THE CATEGORY C REPAIR PERMANENT BY REMOVING THE EXISTING
REPAIR DOUBLER AND INSTALLING INTERNAL TEAR STRAP DOUBLERS, A LARGER
EXTERNAL REPAIR DOUBLER AND SOLID FASTENERS
a. The OPTION 2 repair has the limitations that follow:
(1) This repair cannot be used if the fasteners that exist are larger than 3/16 inch diameter.
(2) This repair cannot be used in locations common to fuselage cutouts, lap joints or butt
joints.
(3) This repair cannot be used if the repair will extend into the following locations:
(a) 737-200/-200C Airplanes: in the area from S-4L to S-4R and from STA 727 to STA
727+8.
(b) 737-300 Airplanes: in the area from S-4L to S-4R and from STA 727 to STA 727C.
(c) 737-500 Airplanes: in the area from S-4L to S-4R, and from STA 727 to 727A+8.
(d) 737-300/400/500 Airplanes: in the area from S-2L to S-2R, and from STA 855 to
STA 908.
b. Make the Category C repair permanent in accordance with FIGURE 47.
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4. RC Exempt - Install the furnishings that were removed for access:
Group 1-7:
a. Install kept ceiling insulation. Refer to 737-100/200 AMM 25-21 as an accepted procedure.
b. Install kept ceiling lining. Refer to 737-100/200 AMM 25-21 as an accepted procedure.
c. Install kept cabin lining and insulation. Refer to 737-100/200 AMM 25-21 as an accepted
procedure.
d. Install kept passenger seats. Refer to 737-100/200 AMM 25-22-00 as an accepted procedure.
Group 8-42:
a. Install kept sidewall and ceiling insulation. Refer to 737-300/400/500 AMM 25-21-39 as an
accepted procedure.
b. Install kept sculptured ceiling panels. Refer to 737-300/400/500 AMM 25-21-45 as an accepted
procedure.
c. Install kept passenger cabin sidewall panels. Refer to 737-300/400/500 AMM 25-21-46 as an
accepted procedure.
d. Install kept passenger seats. Refer to 737-300/400/500 AMM 25-22-00 as an accepted
procedure.
PART 7: POST REPAIR LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION OF SERVICE
BULLETIN REPAIR
1. Do one of the inspections that follow based on the Service Bulletin Repair Option installed:
a. For service bulletin repairs installed in accordance with PART 6: CHANGE CATEGORY C
REPAIR TO SERVICE BULLETIN REPAIR, Option 1, do an external LFEC inspection of the
skin at the critical fastener row of the repair doubler for any crack in accordance with FIGURE
48.
b. For service bulletin repairs installed in accordance with PART 6: CHANGE CATEGORY C
REPAIR TO SERVICE BULLETIN REPAIR, Option 2, do an external LFEC inspection of the
skin at the critical fastener row of the repair doubler for any crack in accordance with FIGURE
49.
PART 8: SKIN PANEL REPLACEMENT
DO NOT REMOVE MORE THAN ONE SKIN PANEL AT A TIME.
WARNING
1. Group 1-7:
a. For each of the skin panels in the following locations, do the steps that follow:
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(1) STA 360 to STA 540, S-4L to S-4R.
(2) STA 360 to STA 540, S-4L to S-10L.
(3) STA 360 to STA 540, S-4R to S-10R.
(4) STA 727 to STA 908, S-4L to S-4R.
(5) STA 727 to STA 908, S-4L to S-10L.
(6) STA 727 to STA 908, S-4R to S-10R.
b. Support the airplane in jig position in accordance with 737-100/200 SRM 51-50-1.
c. If replacing the skin panel between STA 727 and STA 908, between stringers S-4L and S-4R,
remove and keep the dorsal fin. Refer to 737-100/200 AMM 55-32-11 as an accepted
procedure.
d. Remove fasteners from the production skin panel that is being replaced. Refer to 737-100/200
SRM 51-30-2 as an accepted procedure.
e. Remove any lap joint modification (repair) or any splice doubler of the window belt that is
attached to the skin panel that is being replaced.
f. Remove the skin panel.
g. Where skin panels have been removed from STA 360 to STA 540:
NOTE: A scribe line is defined as a narrow, shallow, distinct line of damage (up to 0.006
inch deep), usually associated with the removal of a fillet or gap seal (lap joints and
butt splices, respectively). Scribe lines can be both tactile (your fingernail will catch
on the scribe) and non-tactile (your fingernail will not catch on the scribe).
Discoloration of the aluminum clad layer or small surface imperfections do not qualify
as a scribe. A lightning strike at a lap joint or butt splice does not qualify as a scribe.
(1) Do a detailed inspection for any scribe line on the splice plate at STA 360 in accordance
with FIGURE 50:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
(2) Do a detailed inspection for any scribe line on the frame at STA 540 in accordance with
FIGURE 51:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
h. Where skin panels have been removed from STA 727 to STA 908:
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NOTE: A scribe line is defined as a narrow, shallow, distinct line of damage (up to 0.006
inch deep), usually associated with the removal of a fillet or gap seal (lap joints and
butt splices, respectively). Scribe lines can be both tactile (your fingernail will catch
on the scribe) and non-tactile (your fingernail will not catch on the scribe).
Discoloration of the aluminum clad layer or small surface imperfections do not qualify
as a scribe. A lightning strike at a lap joint or butt splice does not qualify as a scribe.
(1) Do a detailed inspection for any scribe line on the frame at STA 727 in accordance with
FIGURE 52:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
(2) Do a detailed inspection for any scribe line on the splice plate at STA 908 in accordance
with FIGURE 53:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
i. Identify the replacement skin panel assembly number with the part number given in Paragraph
2.C., Parts Necessary for Each Airplane.
j. Where any lap joint modification (repair) was removed at S-10, cut the new skin panel
and reinstall the lap joint modification (repair) in accordance with Boeing Service Bulletin
737-53A1177, Revision 7.
(1)
(2) Where any splice doubler of the window belt was removed at S-9, cut the new skin panel
and reinstall the splice doubler of the window belt in accordance with Boeing Service
Bulletin 737-53A1177, Revision 7.
NOTE: S-4 lap joint repair is not required if the skin panel replacement is accomplished
in accordance with this service bulletin.
k. For production configuration locations, install fasteners in accordance with the skin panel
installation drawings in APPENDIX E.
(1)
(2) For any lap joint modification (repair) locations and/or window belt replacement locations,
install fasteners in accordance with Boeing Service Bulletin 737-53A1177, Revision 7.
NOTE: 1. Maximum permitted fastener hole size is 1/32 inch larger than
production diameter.
2. Maintain 1.7D edge margin with existing fastener hole locations.
3. Fastener substitution permitted in accordance with 737-100/200 SRM
51-30-3.
l. Where the dorsal fin was removed, install the kept dorsal fin. Refer to 737-100/200 AMM
55-32-11 as an accepted procedure.
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2. Group 8-21, 29-41:
a. For each of the skin panels in the following locations, do the steps that follow:
(1) STA 360 to STA 540, S-4L to S-4R.
(2) STA 360 to STA 540, S-4L to S-10L.
(3) STA 360 to STA 540, S-4R to S-10R.
(4) STA 727 to STA 908, S-4L to S-4R.
(5) STA 727 to STA 908, S-4L to S-10L.
(6) STA 727 to STA 908, S-4R to S-10R.
b. Support the airplane in jig position in accordance with 737-300 SRM 51-50-02 or 737-500
SRM 51-50-02.
c. If replacing the skin panel between STA 727 and STA 908, between stringers S-4L and S-4R,
remove and keep the dorsal fin. Refer to 737-300/400/500 AMM 55-32-11 as an accepted
procedure.
d. Remove fasteners from the production skin panel that is being replaced. Refer to 737-300
SRM 51-40-02 or 737-500 SRM 51-40-02 as an accepted procedure.
e. Remove any lap joint modification (repair) or any splice doubler of the window belt that is
attached to the skin panel that is being replaced.
f. Remove the skin panel.
g. Where skin panels have been removed from STA 360 to STA 540:
NOTE: A scribe line is defined as a narrow, shallow, distinct line of damage (up to 0.006
inch deep), usually associated with the removal of a fillet or gap seal (lap joints and
butt splices, respectively). Scribe lines can be both tactile (your fingernail will catch
on the scribe) and non-tactile (your fingernail will not catch on the scribe).
Discoloration of the aluminum clad layer or small surface imperfections do not qualify
as a scribe. A lightning strike at a lap joint or butt splice does not qualify as a scribe.
(1) Do a detailed inspection for any scribe line on the splice plate at STA 360 in accordance
with FIGURE 50:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
(2) Do a detailed inspection for any scribe line on the frame at STA 540 in accordance with
FIGURE 51:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
h. Where skin panels have been removed from STA 727 to STA 908:
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NOTE: A scribe line is defined as a narrow, shallow, distinct line of damage (up to 0.006
inch deep), usually associated with the removal of a fillet or gap seal (lap joints and
butt splices, respectively). Scribe lines can be both tactile (your fingernail will catch
on the scribe) and non-tactile (your fingernail will not catch on the scribe).
Discoloration of the aluminum clad layer or small surface imperfections do not qualify
as a scribe. A lightning strike at a lap joint or butt splice does not qualify as a scribe.
(1) Do a detailed inspection for any scribe line on the frame at STA 727 in accordance with
FIGURE 52:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
(2) Do a detailed inspection for any scribe line on the splice plate at STA 908 in accordance
with FIGURE 53:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
i. Identify the replacement skin panel assembly number with the part number given in Paragraph
2.C., Parts Necessary for Each Airplane.
j. Where any lap joint modification (repair) was removed at S-10, cut the new skin panel
and reinstall the lap joint modification (repair) in accordance with Boeing Service Bulletin
737-53A1177, Revision 7.
(1)
(2) Where any splice doubler of the window belt was removed at S-9, cut the new skin panel
and reinstall the splice doubler of the window belt in accordance with Boeing Service
Bulletin 737-53A1177, Revision 7.
NOTE: S-4 lap joint repair is not required if the skin panel replacement is accomplished
in accordance with this service bulletin.
k. For production configuration locations, install fasteners in accordance with the skin panel
installation drawings in APPENDIX E.
(1)
(2) For any lap joint modification (repair) locations and/or window belt replacement locations,
install fasteners in accordance with Boeing Service Bulletin 737-53A1177, Revision 7.
NOTE: 1. Maximum permitted fastener hole size is 1/32 inch larger than
production diameter.
2. Maintain 1.7D edge margin with existing fastener hole locations.
3. Fastener substitution permitted in accordance with 737-300 SRM
51-40-03 or 737-500 SRM 51-40-03.
l. Where skin panels have been replaced between STA 727 and STA 908, between S-4L and
S-4R, install new dorsal fin wear strips and the kept dorsal fin in accordance with Boeing
Service Bulletin 737-53A1266.
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
3. Group 22-28, 42:
a. For each of the skin panels in the following locations, do the steps that follow:
(1) STA 360 to STA 500C, S-4L to S-4R.
(2) STA 360 to STA 500C, S-4L to S-10L.
(3) STA 360 to STA 500C, S-4R to S-10R.
(4) STA 727G to STA 908, S-4L to S-4R.
(5) STA 727G to STA 908, S-4L to S-10L.
(6) STA 727G to STA 908, S-4R to S-10R.
b. Support the airplane in jig position in accordance with 737-400 SRM 51-50-02.
c. If replacing the skin panel between STA 727G and STA 908, between stringers S-4L and
S-4R, remove and keep the dorsal fin. Refer to 737-300/400/500 AMM 55-32-11 as an accepted
procedure.
d. Remove fasteners from the production skin panel that is being replaced. Refer to 737-400
SRM 51-40-02 as an accepted procedure.
e. Remove any lap joint modification (repair) or any splice doubler of the window belt that is
attached to the skin panel that is being replaced.
f. Remove the skin panel.
g. Where skin panels have been removed from STA 360 to STA 500C:
NOTE: A scribe line is defined as a narrow, shallow, distinct line of damage (up to 0.006
inch deep), usually associated with the removal of a fillet or gap seal (lap joints and
butt splices, respectively). Scribe lines can be both tactile (your fingernail will catch
on the scribe) and non-tactile (your fingernail will not catch on the scribe).
Discoloration of the aluminum clad layer or small surface imperfections do not qualify
as a scribe. A lightning strike at a lap joint or butt splice does not qualify as a scribe.
(1) Do a detailed inspection for any scribe line on the splice plate at STA 360 in accordance
with FIGURE 50:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
(2) Do a detailed inspection for any scribe line on the splice plate at STA 500C in accordance
with FIGURE 54:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
h. Where skin panels have been removed from STA 727G to STA 908:
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
NOTE: A scribe line is defined as a narrow, shallow, distinct line of damage (up to 0.006
inch deep), usually associated with the removal of a fillet or gap seal (lap joints and
butt splices, respectively). Scribe lines can be both tactile (your fingernail will catch
on the scribe) and non-tactile (your fingernail will not catch on the scribe).
Discoloration of the aluminum clad layer or small surface imperfections do not qualify
as a scribe. A lightning strike at a lap joint or butt splice does not qualify as a scribe.
(1) Do a detailed inspection for any scribe line on the splice plate at STA 727G in accordance
with FIGURE 55:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
(2) Do a detailed inspection for any scribe line on the splice plate at STA 908 in accordance
with FIGURE 53:
(a) If any scribe line is found, contact The Boeing Company for work instructions and
do the work.
i. Identify the replacement skin panel assembly number with the part number given in Paragraph
2.C., Parts Necessary for Each Airplane.
j. Where any lap joint modification (repair) was removed at S-4 and S-10, cut the new skin
panel and reinstall the lap joint modification (repair) in accordance with Boeing Service
Bulletin 737-53A1177, Revision 7.
(1)
(2) Where any splice doubler of the window belt was removed at S-9, cut the new skin panel
and reinstall the splice doubler of the window belt in accordance with Boeing Service
Bulletin 737-53A1177, Revision 7.
k. For production configuration locations, install fasteners in accordance with the skin panel
installation drawings in APPENDIX E.
(1)
(2) For any lap joint modification (repair) locations and/or window belt replacement locations,
install fasteners in accordance with Boeing Service Bulletin 737-53A1177, Revision 7.
NOTE: 1. Maximum permitted fastener hole size is 1/32 inch larger than
production diameter.
2. Maintain 1.7D edge margin with existing fastener hole locations.
3. Fastener substitution permitted in accordance with 737-400 SRM
51-40-03.
l. Where skin panels have been replaced between STA 727G and STA 908, between S-4L and
S-4R, install new dorsal fin wear strips and the kept dorsal fin in accordance with Boeing
Service Bulletin 737-53A1266.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1: February 26, 2021 130 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 1-2.
FIGURE 1: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 131 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 1: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 132 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 3-4.
FIGURE 2: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 133 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 2: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 134 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 5.
FIGURE 3: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 135 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 3: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 136 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 6-7.
FIGURE 4: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 137 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 4: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 138 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 8-9.
FIGURE 5: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 139 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 5: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 140 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 10-11.
FIGURE 6: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 141 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 6: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 142 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 12.
FIGURE 7: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 143 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 7: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 144 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 13.
FIGURE 8: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 145 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 8: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 146 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 14-16.
FIGURE 9: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 147 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 9: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 148 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 17.
FIGURE 10: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 149 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 10: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 150 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 18.
FIGURE 11: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 151 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 11: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 152 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 19.
FIGURE 12: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 153 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 12: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 154 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 20.
FIGURE 13: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 155 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 13: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 156 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 21.
FIGURE 14: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 157 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 14: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 158 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 22.
FIGURE 15: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 159 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 15: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 160 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 23.
FIGURE 16: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 161 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 16: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 162 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 24.
FIGURE 17: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 163 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 17: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 164 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 25.
FIGURE 18: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 165 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 18: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 166 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 26.
FIGURE 19: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 167 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 19: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 168 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 27.
FIGURE 20: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 169 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 20: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 170 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 28.
FIGURE 21: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 171 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 21: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 172 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 29-31.
FIGURE 22: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 173 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 22: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 174 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 32-34.
FIGURE 23: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 175 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 23: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 176 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 35-37.
FIGURE 24: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 177 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 24: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 178 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
This Figure applies only to: Group 38-39.
FIGURE 25: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 179 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 25: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
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This Figure applies only to: Group 40.
FIGURE 26: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
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FIGURE 26: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
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This Figure applies only to: Group 41.
FIGURE 27: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 1 OF 2)
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FIGURE 27: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540
(SHEET 2 OF 2)
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FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
(SHEET 1 OF 6)
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FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
(SHEET 2 OF 6)
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FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
(SHEET 3 OF 6)
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FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
(SHEET 4 OF 6)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage SkinInspect1
(b)(c)(d)--Fuselage SkinInspect2
(a) Do one of the External Inspection options that follow for any crack:
External Medium Frequency Eddy Current (MFEC) inspection in accordance with 737 NDT Manual Part
6, 53-30-23.
or
Magneto Optical Imaging (MOI) Inspection in accordance with 737 NDT Manual Part 6, 53-30-19. Do not
use this method within 4 inches of any external skin doubler or tripler;
or
C-Scan Inspection in accordance with 737 NDT Manual Part 6, 53-30-25. Do not use this method within
4 inches of any external skin doubler or tripler;
or
Sliding Probe Inspection in accordance with 737 NDT Manual Part 6, 53-30-39. Do not use this method
within 4 inches of any external skin doubler or tripler.
(b) Do one of the Internal Inspection options that follow for any crack in the horizontal chem-mill steps:
Ultrasonic Phased Array (UTPA) inspection in accordance with 737 NDT Manual Part 4, 53-30-06;
or
Ultrasonic inspection in accordance with 737 NDT Manual Part 4, 53-30-05
and
High Frequency Eddy Current inspection in accordance with 737 NDT Manual Part 6, 53-30-22.
(c) At locations where repair fasteners prevent ultrasonic inspections being done in accordance with 737
NDT Manual Part 4, 53-30-06 or 737 NDT Manual Part 4, 53-30-05 across the full length of the chem-mill
step, do one of the inspections where the probe will fit between the fasteners and do an Eddy Current
inspection for any crack in accordance with 737 NDT Manual Part 6, 53-30-22 along the full length of the
chem-mill step.
FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
(SHEET 5 OF 6)
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More DataQtyIdentificationNameTaskStep
(d) It is not necessary to inspect the chem-mill steps under existing repair doublers for repairs that obey one
of conditions that follow:
1. The installed repair or modification was approved by the FAA or by a Boeing Company authorized
representative who was authorized by the FAA to make such findings, and the installed repair
extends a minimum of three rows of fasteners on each side of the chem-mill line;
or
2. The external repair doubler satisfies the following:
a. The installed repair or modification was approved by the FAA or by a Boeing Company autho-
rized representative who was authorized by the FAA to make such findings;
and
b. The repair or modification extends a minimum of 2 rows of 3/16 inch diameter fasteners on
each side of the chem-mill step in the circumferential direction with 5-6D fastener spacing; and
either:
– The repair or modification is similar to 737-100/200 SRM 53-30-3 Figure 48 or 737-300 SRM
53-00-01 Repair 31 or 737-400 SRM 53-00-01 Repair 31 or 737-500 SRM 53-00-01 Repair
31 with regard to fastener type, size, layout and pitch, repair part thickness and material,
and repair installation;
or
– The repair or modification is similar to 737-300/400/500 SRM 53-60-01 Repair 9 or Repair
14 with regard to fastener type, size, layout and pitch, repair part thickness and material,
and repair installation.
FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
(SHEET 6 OF 6)
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This Figure applies only to: Group 1-4.
FIGURE 29: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 29: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 5.
FIGURE 30: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 30: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 6-7.
FIGURE 31: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 31: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 8, 10, 12-14, 17-21.
FIGURE 32: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 32: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 9, 11, 16.
FIGURE 33: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 33: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 15.
FIGURE 34: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 34: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 22-28, 42.
FIGURE 35: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727G AND 908
(SHEET 1 OF 2)
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FIGURE 35: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727G AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 29-30, 32-33, 35, 38, 40-41.
FIGURE 36: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 36: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 31, 37.
FIGURE 37: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 37: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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This Figure applies only to: Group 34, 36, 39.
FIGURE 38: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 1 OF 2)
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FIGURE 38: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908
(SHEET 2 OF 2)
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FIGURE 39: INSPECTION OF CHEM-MILL POCKETS ADJACENT TO CRACK LOCATION
(SHEET 1 OF 2)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a) (b)--Fuselage SkinInspect1
(a) Do one of the External Inspections that follow for any crack:
External Medium Frequency Eddy Current (MFEC) inspection in accordance with 737 NDT Manual Part
6, 53-30-23.
or
Magneto Optical Imaging (MOI) Inspection in accordance with 737 NDT Manual Part 6, 53-30-19. Do not
use this method within 4 inches of any external skin doubler or tripler;
or
C-Scan Inspection in accordance with 737 NDT Manual Part 6, 53-30-25. Do not use this method within
4 inches of any external skin doubler or tripler;
or
Sliding Probe Inspection in accordance with 737 NDT Manual Part 6, 53-30-39. Do not use this method
within 4 inches of any external skin doubler or tripler.
(b) Do a detailed inspection of the skin in the chem-mill pockets adjacent to the repair area for any corrosion
or disbonded doublers. Look for bulging, white powder, or a thin black line.
FIGURE 39: INSPECTION OF CHEM-MILL POCKETS ADJACENT TO CRACK LOCATION
(SHEET 2 OF 2)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--FastenerRemove1
(b)--Fuselage SkinCut2
-1-Fuselage SkinRemove
(a) Remove fasteners common to the stringer in the repair area. Refer to 737-100/200 SRM 51-30-2, 737-
300 SRM 51-40-02, 737-400 SRM 51-40-02 or 737-500 SRM 51-40-02 as an accepted procedure.
(b) Cut out the full horizontal length of the chem-mill step regardless of the crack size, provided the crack is
contained within the cutout area. Keep a minimum 0.5 inch radius. If the cutout extends into the bonded
doubler, do PART 2: SRM REPAIR.
FIGURE 40: DAMAGED SKIN REMOVAL
(SHEET 1 OF 1)
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FIGURE 41: CUT SURFACE AND FASTENER HOLES INSPECTION
(SHEET 1 OF 2)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage SkinInspect1
(b)--Fuselage SkinInspect2
(a) Do a HFEC inspection of the edge of the cut surface for any crack in accordance with 737 NDT Manual
Part 6, 51-00-00 Procedure 4 or 23.
(b) Do an open hole HFEC inspection of the production fastener holes common to the repair area for any
crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 16. Do a HFEC inspection of the
countersink surface of each production fastener hole common to the repair area for any crack in accordance
with 737 NDT Manual Part 6, 53-30-00 Procedure 3 or 4.
FIGURE 41: CUT SURFACE AND FASTENER HOLES INSPECTION
(SHEET 2 OF 2)
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FIGURE 42: INSURANCE CUT AND SURFACE TREATMENT
(SHEET 1 OF 2)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)(b)--Fuselage SkinCut1
(c)-TYPE 2, CLASS AChemical Conversion
Coating
Apply2
(d)-BMS 10-11, TYPE IPrimerApply3
(a) Cut a minimum of 0.040 inch of material from the edge of the cut surface as an insurance cut. Keep a
minimum 2D edge margin. If the cutout extends into the bonded doubler, do PART 2: SRM REPAIR.
(b) Deburr and break all sharp edges. Keep a surface roughness of 63 Ra or better.
(c) Apply chemical conversion coating to all cut edges of the fuselage skin. Refer to SOPM 20-43-03 as an
accepted procedure.
(d) Apply one layer of primer to all cut edges of the fuselage skin. Refer to SOPM 20-41-02 as an accepted
procedure.
FIGURE 42: INSURANCE CUT AND SURFACE TREATMENT
(SHEET 2 OF 2)
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FIGURE 43: CATEGORY C REPAIR INSTALLATION
(SHEET 1 OF 4)
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FIGURE 43: CATEGORY C REPAIR INSTALLATION
(SHEET 2 OF 4)
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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 this figure. The QTY numbers shown below are
the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
USE CAUTION WHEN LOCATING BLIND FASTENERS RELATIVE TO HIDDEN INTER-
NAL STRUCTURE. DRILLING INTO HIDDEN INTERNAL STRUCTURE OR EQUIPMENT
MAY RESULT IN DOWNTIME FOR EXTENSIVE REPAIR.
CAUTION
(a)(b)(c)(l)12024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerMake1
(d)(l)12024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerChamfer
(e)-TYPE 2, CLASS AChemical Conversion
Coating
Apply2
(f)-BMS 10-79, TYPE IIIPrimerApply
(a)(m)--HolesDrill3
(g)12024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerClean4
(g)--Fuselage SkinClean
(h)-BMS 5-95, CLASS BSealantApply
(i)12024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerInstall (New)
(j)-BMS 5-95, CLASS BSealantApply5
(k)--FinishApply6
(a) Keep a minimum edge margin of two times the fastener diameter at new fastener locations, and a 1.7
times fastener diameter edge margin at existing fastener locations.
(b) Keep a minimum inside corner radius of 2 inches and outside corner radius of 0.5 inch.
(c) Pre-form to match the contour of the fuselage.
(d) Chamfer the outer edges of the repair doubler. Refer to 737-100/200 SRM 51-70, 737-300 SRM 51-10-
01, 737-400 SRM 51-10-01 or 737-500 SRM 51-10-01 as an accepted procedure.
(e) Apply chemical conversion coating to the repair doubler. Refer to SOPM 20-43-03 as an accepted proce-
dure.
(f) Apply one layer of primer to the repair doubler. Refer to SOPM 20-44-04 as an accepted procedure.
(g) Clean the faying surfaces of the fuselage skin and repair parts. Refer to SOPM 20-30-03 as an accepted
procedure.
(h) Apply faying surface sealant on all mating parts. Refer to SOPM 20-50-19 as an accepted procedure.
FIGURE 43: CATEGORY C REPAIR INSTALLATION
(SHEET 3 OF 4)
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More DataQtyIdentificationNameTaskStep
(i) Shim all gaps from 0.01 to 0.04 inch prior to fastener installation. For gaps greater than 0.04 inch, contact
The Boeing Company for shim installation instructions and do the instructions. Do not install shims between
the skin and the Repair Doubler.
(j) Apply a fillet seal around the edges of the repair doubler. Refer to SOPM 20-50-19 as an accepted proce-
dure.
(k) Apply finish to repair area to match adjacent structure. Refer to SOPM 20-44-01 as an accepted procedure.
(l) Deburr and break all sharp edges. Keep a surface roughness of 125 Ra or better.
(m) Remove all nicks, burrs and sharp edges from hole edges. Keep a surface roughness of 125 Ra or better.
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The parts that follow are used to
accomplish a typical Category C skin repair. Number of fasteners, size, type, and grip length may vary depending
on the specific repair.
More DataHole DiaQtyIdentificationNameCode
(a)(b)0.176 - 0.18012BACR15FR5F()RBLIND RIVETA
(a)(c)(e)0.205 - 0.209-BACR15FR6F()RBLIND RIVET
(d)(f)0.176 - 0.180101BACR15FR5F()RBLIND RIVETB
(a) Install countersink repair washer to fill the existing countersink under the repair doubler. Refer to 737-
100/200 SRM 51-30-8 or 737-300 SRM 51-40-08 or 737-400 SRM 51-40-08 or 737-500 SRM 51-40-08
as an accepted procedure.
(b) Install if the production fastener was 5/32 inch diameter.
(c) Install if the production fastener was 3/16 inch diameter.
(d) Use caution when locating these fasteners common to the tear straps. Keep a minimum edge margin of
1.7 times the fastener diameter from the edge of the tear strap.
(e) It is permitted to increase the hole diameter to remove damage and install this fastener if the original/pro-
duction fastener was 5/32 inch diameter.
(f) At new fastener locations not common to a tear strap, the fastener spacing is 0.93 inch to 1.20 inches.
FIGURE 43: CATEGORY C REPAIR INSTALLATION
(SHEET 4 OF 4)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--Repair DoublerInspect1
(a) Do a general visual inspection for any loose or missing fastener.
FIGURE 44: CATEGORY C REPAIR INSPECTION
(SHEET 1 OF 1)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--FastenerRemove1
(b)--Fuselage SkinInspect2
(c)--Fuselage SkinInspect3
(d)--Fuselage SkinInspect4
(a) Remove all fasteners common to the Category C repair. Refer to 737-100/200 SRM 51-30-2 or 737-300
SRM 51-40-02 or 737-400 SRM 51-40-02 or 737-500 SRM 51-40-02 as an accepted procedure.
(b) Do an open hole HFEC inspection of all fastener holes common to the Category C repair for any crack
in accordance with 737 NDT Manual Part 6, 51-00-00, Procedure 16. For any crack found, contact The
Boeing Company for repair instructions and do the repair.
(c) Do External Medium Frequency Eddy Current (MFEC) inspection of the skin in the horizontal chem-mill
steps adjacent to the repair area for any crack in accordance with 737 NDT Manual Part 6, 53-30-23. For
any crack found, contact The Boeing Company for repair instructions and do the repair.
(d) Do an internal detailed inspection of the skin in the chem-mill pockets adjacent to the repair area for any
corrosion or disbonded doublers. Look for bulging, white powder, or a thin black line. For any corrosion
or disbond found, contact The Boeing Company for work instructions and do the work.
FIGURE 45: PRE-REPAIR CONVERSION INSPECTION
(SHEET 1 OF 1)
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FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
TEAR STRAP DOUBLERS
(SHEET 1 OF 6)
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FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
TEAR STRAP DOUBLERS
(SHEET 2 OF 6)
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FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
TEAR STRAP DOUBLERS
(SHEET 3 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 226 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
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 this figure.
More DataQtyIdentificationNameTaskStep
(a)(b)(c)(d)(e)42024-T3 CLAD SHEET
0.040 INCH THICK
Internal Tear Strap
Doubler
Make1
(c)(e)-2024 -T3 CLAD SHEET
0.040 INCH THICK
Tapered FillerMake2
(g)-TYPE 2, CLASS AChemical Conversion
Coating
Apply3
(h)-BMS 10-11, TYPE IPrimerApply
(e)(f)--HolesDrill4
(d)(i)(j)(k)42024-T3 CLAD SHEET
0.040 INCH THICK
Internal Tear Strap
Doubler
Install (New)5
(i)(j)(k)-2024 -T3 CLAD SHEET
0.040 INCH THICK
Tapered FillerInstall (New)6
(m)-BMS 5-95, CLASS BSealantApply7
(l)-BMS 3-23, TYPE IICorrosion Inhibiting
Compound
Apply8
(a) Size the tear strap doublers to maintain a minimum edge margin of two times the fastener diameter at
the fastener locations.
(b) Maintain a minimum inside corner radius of 2 inches and outside corner radius of 0.50 inch.
(c) If the end fastener of the tear strap doubler ends common to a stringer, extend the length of the tear strap
doubler by one fastener row as shown in view B or D. Install tapered fillers on each side of the tear strap
doubler between the skin and the stringers. Make the tapered filler from 0.040" thick 2024-T3 clad sheet
with a 50:1 taper ratio.
(d) If the tear strap is common to any part of the lower skin doubler tear strap tab, located above the lap joint
make sure all six fastener locations are used. Install the same type and size fastener as required in pro-
duction.
(e) Remove all nicks, burrs and sharp edges from the repair parts, tear strap and skin/doubler. All repair parts
must have a surface roughness of 125 Ra or better.
(f) Maintain a minimum edge margin of 2 times the fastener diameter for new fastener locations and 1.7
times the fastener diameter for fastener locations that exist.
(g) Apply chemical conversion coating to internal tear strap doubler and tapered filler. Refer to SOPM 20-43-
03 as an accepted procedure.
(h) Apply two layers of primer to internal tear strap doubler and tapered filler. Refer to SOPM 20-41-02 as
an accepted procedure.
(i) Shim all gaps from 0.01 to 0.04 inch prior to fastener installation. For gaps greater than 0.04 inch, contact
The Boeing Company for shim installation instructions and do the instructions. Do not install shims between
the skin and the Repair Doubler.
FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
TEAR STRAP DOUBLERS
(SHEET 4 OF 6)
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More DataQtyIdentificationNameTaskStep
(j) Clean the faying surfaces of the fuselage skin and repair parts before sealant application. Refer to SOPM
20-30-03 as an accepted procedure.
(k) Apply BMS 5-95, class B faying surface sealant on all mating parts. Refer to SOPM 20-50-19 as an ac-
cepted procedure.
(l) Apply one layer of corrosion inhibiting compound onto the internal surface of the entire repair area. Use
BMS 3-23, Type II Class 2, or an equivalent corrosion inhibiting compound. Refer to SOPM 20-41-05 as
an accepted procedure.
(m) Apply fillet seal around the edges of repair parts. Refer to SOPM 20-50-19 as accepted procedure.
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
maximum number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(b)0.190 - 0.19616BACR15BB6D()CRivetA
(a)0.190 - 0.19634BACR15BB6AD()CRivetB
(a)(c)0.225 - 0.231-BACR15BB7AD()CRivet
(a)0.190 - 0.19612BACR15BB6D()CRivetC
(a)(c)0.225 - 0.231-BACR15BB7AD()CRivet
(a)(d)(e)0.190 - 0.19664BACR15BB6D()CRivetD
(a)(c)(d)(f)0.225 - 0.231-BACR15BB7AD()CRivet
(a) The minimum diameter of the driven head of the fastener is 1.4 times the fastener diameter.
(b) It is not permitted to install a fastener with a larger diameter at these locations.
(c) It is permitted to increase the hole diameter to remove damage and install this fastener.
(d) Do not install a fastener that is more than 1/32 inch larger than the production hole diameter at these lo-
cations.
(e) Replace the 5/32 inch diameter Blind Fastener common to the repair.
FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
TEAR STRAP DOUBLERS
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING
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More DataHole DiaQtyIdentificationNameCode
(f) Replace the 3/16 inch diameter Blind Fastener common to the repair.
FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
TEAR STRAP DOUBLERS
(SHEET 6 OF 6)
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FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER, SOLID
FASTENERS AND TEAR STRAP DOUBLERS
(SHEET 1 OF 6)
Export Controlled ECCN: 9E991 - BOEING
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER, SOLID
FASTENERS AND TEAR STRAP DOUBLERS
(SHEET 2 OF 6)
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER, SOLID
FASTENERS AND TEAR STRAP DOUBLERS
(SHEET 3 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 232 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
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 this figure.
More DataQtyIdentificationNameTaskStep
(a)(b)(c)(d)12024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerMake1
(d)(q)12024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerChamfer
(d)(e)(p)42024-T3 CLAD SHEET
0.040 INCH THICK
Internal Tear Strap
Doubler
Make2
(d)(e)-2024 -T3 CLAD SHEET
0.040 INCH THICK
Tapered FillerMake3
(h)-TYPE 2, CLASS AChemical Conversion
Coating
Apply4
(i)-BMS 10-79, TYPE IIIPrimerApply
(f)(g)--HolesDrill5
(j)--Fuselage SkinClean6
(j)-2024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerClean
(j)-2024-T3 CLAD SHEET
0.040 INCH THICK
Internal Tear Strap
Doubler
Clean
(j)-2024 -T3 CLAD SHEET
0.040 INCH THICK
Tapered FillerClean
(k)-BMS 5-95, CLASS BSealantApply7
(l)12024-T3 CLAD SHEET
0.050 INCH THICK
Repair DoublerInstall (New)8
(l)(p)42024-T3 CLAD SHEET
0.040 INCH THICK
Internal Tear Strap
Doubler
Install (New)9
-2024 -T3 CLAD SHEET
0.040 INCH THICK
Tapered FillerInstall (New)10
(m)-BMS 5-95, CLASS BSealantApply11
(n)-BMS 3-23, TYPE IICorrosion Inhibiting
Compound
Apply12
(o)--FinishApply13
(a) Size the repair parts to keep a minimum edge margin of 2 times the fastener diameter at new fastener
locations, and 1.7 times the diameter at existing fastener locations.
(b) Maintain a minimum inside corner radius of 2 inches and outside corner radius of 0.50 inch.
(c) Pre-form to match the contour of the fuselage.
FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER, SOLID
FASTENERS AND TEAR STRAP DOUBLERS
(SHEET 4 OF 6)
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
More DataQtyIdentificationNameTaskStep
(d) Deburr and break all sharp edges. Keep a surface roughness of 125 Ra or better.
(e) If the end fastener of the tear strap doubler ends common to a stringer, extend the length of the tear strap
doubler by one fastener row. Install tapered fillers as required on each side of the tear strap doubler between
the skin and the stringers. Make the tapered fillers from 0.040 inch thick 2024-T3 clad sheet with a 50:1
taper ratio.
(f) Remove all nicks, burrs and sharp edges from hole edges. Keep a surface roughness of 125 Ra or better.
(g) Keep a minimum edge margin of 2 times the fastener diameter for new fastener locations and 1.7 times
the fastener diameter for fastener locations that exist.
(h) Apply chemical conversion coating to all repair parts. Refer to SOPM 20-43-03 as an accepted procedure.
(i) Apply one layer of primer to External Repair Doubler and two layers of primer to all other repair parts.
Refer to SOPM 20-44-04 as an accepted procedure.
(j) Clean the faying surfaces of the fuselage skin and repair parts. Refer to SOPM 20-30-03 as an accepted
procedure.
(k) Apply faying surface sealant to all mating parts. Refer to SOPM 20-50-19 as an accepted procedure.
(l) Shim all gaps from 0.01 to 0.04 inch prior to fastener installation. For gaps greater than 0.04 inch, contact
The Boeing Company for shim installation instructions and do the instructions. Do not install shims between
the skin and the Repair Doubler.
(m) Apply fillet seal around the edges of repair parts. Refer to SOPM 20-50-19 as an accepted procedure.
(n) Apply corrosion inhibiting compound onto the internal surface of the entire repair area. Refer to SOPM
20-41-05 as an accepted procedure.
(o) Apply finish onto the external surfaces to match adjacent structure. Refer to SOPM 20-44-01 as an ac-
cepted procedure.
(p) If the internal tear strap doubler is common to any part of the lower skin doubler tear strap tab, located
above the lap joint, make sure that all six fastener locations are used. Install the same size and type fas-
tener as required in production.
(q) Chamfer the outer edges of the repair doubler. Refer to 737-100/200 SRM 51-70, 737-300 SRM 51-10-
01, 737-400 SRM 51-10-01 or 737-500 SRM 51-10-01 as an accepted procedure.
FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER, SOLID
FASTENERS AND TEAR STRAP DOUBLERS
(SHEET 5 OF 6)
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.
A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the
maximum number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(b)0.190 - 0.19616BACR15BB6D()CRivetA
(a)0.190 - 0.19642BACR15BB6AD()CRivetB
(a)0.190 - 0.19612BACR15BB6D()CRivetC
(a)(c)0.225 - 0.231-BACR15BB7AD()CRivet
(a)(d)(e)0.190 - 0.196104BACR15BB6D()CRivetD
(a)(c)(d)(f)0.225 - 0.231-BACR15BB7AD()CRivet
(a) The minimum diameter of the driven head of the fastener is 1.4 times the fastener diameter.
(b) It is not permitted to install a fastener with a larger diameter at these locations.
(c) Optional fastener, if it is necessary to make the hole larger to remove damage.
(d) Do not install a fastener that is more than 1/32 inch larger than the production hole diameter at these lo-
cations.
(e) Replace 5/32 inch diameter blind fastener common to the repair.
(f) Replace 3/16 inch diameter blind fastener common to the repair.
FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER, SOLID
FASTENERS AND TEAR STRAP DOUBLERS
(SHEET 6 OF 6)
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BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
FIGURE 48: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION 1
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 236 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage SkinInspect1
(a) Do external Low Frequency Eddy Current (LFEC) inspection of the fuselage skin at the critical fastener
row of the repair for any crack in accordance with 737 NDT Manual Part 6, 53-30-00, Procedure 5.
FIGURE 48: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION 1
(SHEET 2 OF 2)
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FIGURE 49: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION 2
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 238 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage SkinInspect1
(a) Do external Low Frequency Eddy Current (LFEC) inspection of the fuselage skin at the critical fastener
row of the repair for any crack in accordance with 737 NDT Manual Part 6, 53-30-00, Procedure 5.
FIGURE 49: POST REPAIR LFEC INSPECTION OF SERVICE BULLETIN REPAIR, OPTION 2
(SHEET 2 OF 2)
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FIGURE 50: SKIN BUTT JOINT INSPECTION AT STA 360
(SHEET 1 OF 2)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--SealantRemove1
(b)(c)--Splice PlateInspect2
(a) Remove sealant from within the gap of the butt joints in accordance with Service Bulletin 737-53A1262,
APPENDIX A. Do not remove primer and paint, if present, from the splice plate.
(b) Do a detailed inspection of the splice plate for any scribe lines using 10X magnifying lenses.
(c) Do the inspection of the splice plate common to the removed skin panel only.
FIGURE 50: SKIN BUTT JOINT INSPECTION AT STA 360
(SHEET 2 OF 2)
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FIGURE 51: SKIN BUTT JOINT INSPECTION AT STA 540
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--SealantRemove1
(b)(c)--FrameInspect2
(a) Remove sealant from within the gap of the butt joints in accordance with Service Bulletin 737-53A1262,
APPENDIX A. Do not remove primer and paint, if present, from the frame.
(b) Do a detailed inspection of the frame for any scribe lines using 10X magnifying lenses.
(c) Do the inspection of the frame common to the removed skin panel only.
FIGURE 51: SKIN BUTT JOINT INSPECTION AT STA 540
(SHEET 2 OF 2)
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FIGURE 52: SKIN BUTT JOINT INSPECTION AT STA 727
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--SealantRemove1
(b)(c)--FrameInspect2
(a) Remove sealant from within the gap of the butt joints in accordance with Service Bulletin 737-53A1262,
APPENDIX A. Do not remove primer and paint, if present, from the frame.
(b) Do a detailed inspection of the frame for any scribe lines using 10X magnifying lenses.
(c) Do the inspection of the frame common to the removed skin panel only.
FIGURE 52: SKIN BUTT JOINT INSPECTION AT STA 727
(SHEET 2 OF 2)
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FIGURE 53: SKIN BUTT JOINT INSPECTION AT STA 908
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--SealantRemove1
(b)(c)--Splice PlateInspect2
(a) Remove sealant from within the gap of the butt joints in accordance with Service Bulletin 737-53A1262,
APPENDIX A. Do not remove primer and paint, if present, from the splice plate.
(b) Do a detailed inspection of the splice plate for any scribe lines using 10X magnifying lenses.
(c) Do the inspection of the splice plate common to the removed skin panel only.
FIGURE 53: SKIN BUTT JOINT INSPECTION AT STA 908
(SHEET 2 OF 2)
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FIGURE 54: SKIN BUTT JOINT INSPECTION AT STA 500C
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--SealantRemove1
(b)(c)--Splice PlateInspect2
(a) Remove sealant from within the gap of the butt joints in accordance with Service Bulletin 737-53A1262,
APPENDIX A. Do not remove primer and paint, if present, from the splice plate.
(b) Do a detailed inspection of the splice plate for any scribe lines using 10X magnifying lenses.
(c) Do the inspection of the splice plate common to the removed skin panel only.
FIGURE 54: SKIN BUTT JOINT INSPECTION AT STA 500C
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
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FIGURE 55: SKIN BUTT JOINT INSPECTION AT STA 727G
(SHEET 1 OF 2)
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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 this figure.
More DataQtyIdentificationNameTaskStep
(a)--SealantRemove1
(b)(c)--Splice PlateInspect2
(a) Remove sealant from within the gap of the butt joints in accordance with Service Bulletin 737-53A1262,
APPENDIX A. Do not remove primer and paint, if present, from the splice plate.
(b) Do a detailed inspection of the splice plate for any scribe lines using 10X magnifying lenses.
(c) Do the inspection of the splice plate common to the removed skin panel only.
FIGURE 55: SKIN BUTT JOINT INSPECTION AT STA 727G
(SHEET 2 OF 2)
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This Figure applies only to: Group 42.
FIGURE 56: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 1 OF 2)
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FIGURE 56: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C
(SHEET 2 OF 2)
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Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NON-DESTRUC-
TIVE INSPECTION (NDI).
PART 1
SRM REPAIR.PART 2
CATEGORY C REPAIR.PART 3
NO CRACK FOUND.CONDITION 1
ANY CRACK FOUND.CONDITION 2
2. The table below gives the description for the flag notes called out in the logic diagram.
DescriptionFlag Note Letter
It is not required to inspect the chem-mill steps under existing repair doublers
provided either:
(a)
1. The installed repair or modification was approved by the FAA or by
a Boeing Company authorized representative who was authorized
by the FAA to make such findings, and the installed repair extends
a minimum of three rows of fasteners on each side of the chem-mill
line; or
2. The external repair doubler satisfies the following:
– The installed repair or modification was approved by the FAA
or by a Boeing Company authorized representative who was
authorized by the FAA to make such findings; and
– The repair or modification extends a minimum of 2 rows of 3/16
inch diameter fasteners on each side of the chem-mill step in
the circumferential direction with 5-6D fastener spacing; and
either:
– The repair or modification is similar to 737-100/200 SRM
53-30-3 Figure 48 or 737-300 SRM 53-00-01 Repair 31 or
737-400 SRM 53-00-01 Repair 31 or 737-500 SRM 53-00-
01 Repair 31 with regard to fastener type, size, layout and
pitch, repair part thickness and material, and repair installa-
tion; or
– The repair or modification is similar to 737-300/400/500
SRM 53-60-01 Repair 9 or Repair 14 with regard to fastener
type, size, layout and pitch, repair part thickness and mate-
rial, and repair installation.
APPENDIX A: LOGIC DIAGRAM FOR TABLE 1 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN
BONDED DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-10L TO S-10R - STA 360
TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO
STA 908 (GROUP 22-28, 42)
(SHEET 1 OF 3)
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DescriptionFlag Note Letter
Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 1: CROWN SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) inspections.
(b)
The applicability limitations and post repair inspection requirements of PART
2: SRM REPAIR are in PART 2 and 737-100/200 SRM 53-30-3 Figure 48,
737-300 SRM 53-00-01 Repair 31, 737-400 SRM 53-00-01 Repair 31 or 737-
500 SRM 53-00-01 Repair 31.
(c)
Accomplishment of PART 2: SRM REPAIR is terminating action to the service
bulletin repeat inspections at the SRM repair location only.
(d)
The applicability limitations of the Category C repair are in PART 3: CATEGO-
RY C REPAIR.
(e)
Compliance times for post-repair inspections of Category C repairs done in
accordance with PART 3: CATEGORY C REPAIR are in Table 2 of Paragraph
1.E., Compliance.
(f)
Accomplishment of PART 3: CATEGORY C REPAIR is terminating action to
the service bulletin repeat PART 1: CROWN SKIN CHEM-MILL STEP INTER-
NAL/EXTERNAL NON-DESTRUCTIVE INSPECTION (NDI) inspections under
the Category C repair location only.
(g)
APPENDIX A: LOGIC DIAGRAM FOR TABLE 1 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN
BONDED DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-10L TO S-10R - STA 360
TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO
STA 908 (GROUP 22-28, 42)
(SHEET 2 OF 3)
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APPENDIX A: LOGIC DIAGRAM FOR TABLE 1 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN
BONDED DOUBLER CHEM-MILL STEP - INSPECTION AND REPAIR - FROM S-10L TO S-10R - STA 360
TO STA 540 AND STA 727 TO STA 908 (GROUP 1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO
STA 908 (GROUP 22-28, 42)
(SHEET 3 OF 3)
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Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
CATEGORY C REPAIR.PART 3
POST REPAIR INSPECTION OF CATEGORY C REPAIR.PART 4
POST CATEGORY C REPAIR FASTENER REPLACEMENT.PART 5
CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR.PART 6
ANY LOOSE OR MISSING FASTENER FOUND.CONDITION 3
NO LOOSE OR MISSING FASTENER FOUND.CONDITION 4
2. The table below gives the description for the flag notes called out in the logic diagram.
DescriptionFlag Note Letter
Accomplishment of PART 6: CHANGE CATEGORY C REPAIR TO SERVICE
BULLETIN REPAIR is terminating action to initial and repeat PART 4: POST
REPAIR INSPECTION OF CATEGORY C REPAIR inspections at the repaired
location only.
(a)
Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to PART 4: POST REPAIR INSPECTION OF CATEGORY C REPAIR
and terminates the requirement to do PART 6: CHANGE CATEGORY C
REPAIR TO SERVICE BULLETIN REPAIR.
(b)
The applicability limitations of the Service Bulletin Repair are in PART 6:
CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR.
(c)
Compliance times for inspection of Service Bulletin Repairs done in accordance
with PART 6: CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN
REPAIR are in Table 3 of Paragraph 1.E., Compliance.
(d)
APPENDIX B: LOGIC DIAGRAM FOR TABLE 2 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF CATEGORY C REPAIR
(SHEET 1 OF 2)
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APPENDIX B: LOGIC DIAGRAM FOR TABLE 2 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF CATEGORY C REPAIR
(SHEET 2 OF 2)
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Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
CHANGE CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR.PART 6
POST REPAIR LOW FREQUENCY EDDY CURRENT (LFEC) INSPECTION
OF SERVICE BULLETIN REPAIR.
PART 7
ANY CRACK FOUND.CONDITION 5
NO CRACK FOUND.CONDITION 6
2. The table below gives the description for the flag notes called out in the logic diagram.
DescriptionFlag Note Letter
Accomplishment of PART 8: SKIN PANEL REPLACEMENT is terminating
action to the initial and repeat PART 7: POST REPAIR LOW FREQUENCY
EDDY CURRENT (LFEC) INSPECTION OF SERVICE BULLETIN REPAIR
inspections.
(a)
APPENDIX C: LOGIC DIAGRAM FOR TABLE 3 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF SERVICE BULLETIN REPAIRS INSTALLED IN ACCORDANCE WITH PART 6: CHANGE
CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR IN THE ORIGINAL ISSUE OR ANY REVISION OF
THIS SERVICE BULLETIN
(SHEET 1 OF 2)
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APPENDIX C: LOGIC DIAGRAM FOR TABLE 3 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF SERVICE BULLETIN REPAIRS INSTALLED IN ACCORDANCE WITH PART 6: CHANGE
CATEGORY C REPAIR TO SERVICE BULLETIN REPAIR IN THE ORIGINAL ISSUE OR ANY REVISION OF
THIS SERVICE BULLETIN
(SHEET 2 OF 2)
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Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary
source for compliance times. Information contained in Paragraph 3.B., Work Instructions is the primary source
for tasks required for compliance.
1. The table below gives the description for the parts and conditions called out in the logic diagrams.
DescriptionTitle
SKIN PANEL REPLACEMENT.PART 8
APPENDIX D: LOGIC DIAGRAM FOR TABLE 4 OF PARAGRAPH 1.E, COMPLIANCE: CROWN SKIN
PANEL REPLACEMENT FROM S-10L TO S-10R - STA 360 TO STA 540 AND STA 727 TO STA 908 (GROUP
1-21, 29-41) OR STA 360 TO STA 500C AND 727G TO STA 908 (GROUP 22-28, 42)
(SHEET 1 OF 1)
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For Groups 1-21 and 29-41 a total of six skin panels are replaced in this service bulletin. Three skin panels are
replaced between STA 360 and STA 540 from S-10L to S-10R and three skin panels are replaced between STA
727 and STA 908 from S-10L to S-10R.
For Groups 22-28, and 42 a total of six skin panels are replaced in this service bulletin. Three skin panels are
replaced between STA 360 and STA 500C from S-10L to S-10R and three skin panels are replaced between
STA 727G and STA 908 from S-10L to S-10R.
The skin panels listed below are the production skin panels.
Skin Panel Installation Drawings- Group 1
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
18, 2065-4576565-45765-609STA 360 to STA 540, S-4L
to S-10L
18, 2065-4576565-45765-610STA 360 to STA 540, S-4R
to S-10R
19, 2065-4576565-45765-611STA 360 to STA 540, S-4L
to S-4R
16, 1865-4577265-45772-1001STA 727 to STA 908, S-4L
to S-10L
16, 1865-4577265-45772-1002STA 727 to STA 908, S-4R
to S-10R
15, 18, 2565-4577265-45772-597STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 2
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
18, 2065-4576565-45765-724STA 360 to STA 540, S-4L
to S-10L
18, 2065-4576565-45765-725STA 360 to STA 540, S-4R
to S-10R
19, 2065-4576565-45765-726STA 360 to STA 540, S-4L
to S-4R
16, 1865-4577265-45772-157STA 727 to STA 908, S-4L
to S-10L
16, 1865-4577265-45772-158STA 727 to STA 908, S-4R
to S-10R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 1 OF 20)
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Skin Panel Installation Drawings- Group 2
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
15, 18, 2565-4577265-45772-159STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 3
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
18, 2065-4576565-45765-724STA 360 to STA 540, S-4L
to S-10L
18, 2065-4576565-45765-725STA 360 to STA 540, S-4R
to S-10R
19, 2065-4576565-45765-729STA 360 to STA 540, S-4L
to S-4R
16, 1865-4577265-45772-157STA 727 to STA 908, S-4L
to S-10L
16, 1865-4577265-45772-158STA 727 to STA 908, S-4R
to S-10R
15, 18, 2565-4577265-45772-159STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 4
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
18, 2065-4576565-45765-724STA 360 to STA 540, S-4L
to S-10L
18, 2065-4576565-45765-725STA 360 to STA 540, S-4R
to S-10R
19, 2065-4576565-45765-729STA 360 to STA 540, S-4L
to S-4R
16, 18, 2265-4577265-45772-161STA 727 to STA 908, S-4L
to S-10L
16, 1865-4577265-45772-162STA 727 to STA 908, S-4R
to S-10R
15, 18, 2565-4577265-45772-159STA 727 to STA 908, S-4L
to S-4R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 2 OF 20)
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Skin Panel Installation Drawings- Group 5
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
18, 2065-4576565-45765-609STA 360 to STA 540, S-4L
to S-10L
18, 2065-4576565-45765-610STA 360 to STA 540, S-4R
to S-10R
19, 2065-4576565-45765-618STA 360 to STA 540, S-4L
to S-4R
16, 1865-4577265-45772-1001STA 727 to STA 908, S-4L
to S-10L
16, 1865-4577265-45772-1002STA 727 to STA 908, S-4R
to S-10R
15, 18, 2565-4577265-45772-1017STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 6
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
1765-4576565-45765-606STA 360 to STA 540, S-4L
to S-10L
1665-4576565-45765-603STA 360 to STA 540, S-4R
to S-10R
9, 1765-4576565-45765-602STA 360 to STA 540, S-4L
to S-4R
16, 1765-4577265-45772-1005STA 727 to STA 908, S-4L
to S-10L
16, 1765-4577265-45772-1006STA 727 to STA 908, S-4R
to S-10R
15, 17, 2565-4577265-45772-596STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 7
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
1765-4576565-45765-723STA 360 to STA 540, S-4L
to S-10L
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 3 OF 20)
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Skin Panel Installation Drawings-Group 7
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
1665-4576565-45765-722STA 360 to STA 540, S-4R
to S-10R
9, 1765-4576565-45765-721STA 360 to STA 540, S-4L
to S-4R
16, 1765-4577265-45772-153STA 727 to STA 908, S-4L
to S-10L
16, 1765-4577265-45772-154STA 727 to STA 908, S-4R
to S-10R
15, 17, 2565-4577265-45772-156STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 8
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 2665-4576565-45765-98STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 9
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 4 OF 20)
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Skin Panel Installation Drawings-Group 9
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
25, 2665-4576565-45765-98STA 360 to STA 540, S-4L
to S-4R
16, 24, 3065-4577265-45772-231STA 727 to STA 908, S-4L
to S-10L
16, 24, 3065-4577265-45772-232STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 10
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
21, 25, 2665-4576565-45765-141STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 11
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
21, 25, 2665-4576565-45765-141STA 360 to STA 540, S-4L
to S-4R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 5 OF 20)
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Skin Panel Installation Drawings-Group 11
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
16, 24, 3065-4577265-45772-231STA 727 to STA 908, S-4L
to S-10L
16, 24, 3065-4577265-45772-232STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 12
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 2665-4576565-45765-146STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 13
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 2665-4576565-45765-227STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 6 OF 20)
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Skin Panel Installation Drawings-Group 13
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 14
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 26, 3565-4576565-45765-233STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 15
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 26, 3565-4576565-45765-233STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 7 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 268 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 15
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
15, 23 & ADCN W565-4577265-45772-320STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 16
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 26 3565-4576565-45765-233STA 360 to STA 540, S-4L
to S-4R
16, 24, 3065-4577265-45772-231STA 727 to STA 908, S-4L
to S-10L
16, 24, 3065-4577265-45772-232STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 17
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 26, 3565-4576565-45765-236STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 8 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 269 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 18
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 26, 3565-4576565-45765-240STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 19
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 26, 3565-4576565-45765-289STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 20
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 9 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 270 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 20
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 26, 3565-4576565-45765-300STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 21
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
23, 2465-4576565-45765-99STA 360 to STA 540, S-4L
to S-10L
23, 2465-4576565-45765-100STA 360 to STA 540, S-4R
to S-10R
25, 2665-4576565C33816-1STA 360 to STA 540, S-4L
to S-4R
16, 2465-4577265-45772-167STA 727 to STA 908, S-4L
to S-10L
16, 2465-4577265-45772-168STA 727 to STA 908, S-4R
to S-10R
15, 2365-4577265-45772-166STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 22
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 10 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 271 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings- Group 22
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2765-4576565C32355-1STA 360 to STA 500C, S-4L
to S-4R
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 23
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
21, 2765-4576565C32355-20STA 360 to STA 500C, S-4L
to S-4R
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 24
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
27, 3665-4576565C32355-30STA 360 to STA 500C, S-4L
to S-4R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 11 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 272 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings- Group 24
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 25
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
8, 2765-4576565C32355-37STA 360 to STA 500C, S-4L
to S-4R
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 26
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
27, 3665-4576565C32355-39STA 360 to STA 500C, S-4L
to S-4R
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 12 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 273 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings- Group 26
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 27
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
8, 2765-4576565C32355-45STA 360 to STA 500C, S-4L
to S-4R
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 28
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
27, 3465-4576565C32355-53STA 360 to STA 500C, S-4L
to S-4R
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 13 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 274 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 28
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 29
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
3165-4576565C32355-27STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 30
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
37, 3865-4576565C32355-47STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 14 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 275 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 31
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
31,65-4576565C32355-27STA 360 to STA 540, S-4L
to S-4R
33, 34, 3565-4577265C32362-31STA 727 to STA 908, S-4L
to S-10L
33, 34, 3565-4577265C32362-32STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 32
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
31, 3765-4576565C32355-32STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 33
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 15 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 276 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 33
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
37, 3865-4576565C32355-48STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings- Group 34
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
31, 3765-4576565C32355-32STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 32, 3665-4577265C32362-33STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 35
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 16 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 277 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 35
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
3865-4576565C32355-40STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 36
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
3865-4576565C32355-40STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 32, 3665-4577265C32362-33STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 37
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
3865-4576565C32355-40STA 360 to STA 540, S-4L
to S-4R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 17 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 278 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 37
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
33, 34, 3565-4577265C32362-31STA 727 to STA 908, S-4L
to S-10L
33, 34, 3565-4577265C32362-32STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 38
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
37, 3865-4576565C32355-41STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 39
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
37, 3865-4576565C32355-41STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 18 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 279 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 39
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 32, 3665-4577265C32362-33STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 40
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
37, 3865-4576565C32355-49STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 41
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
32, 3365-4576565C32355-21STA 360 to STA 540, S-4L
to S-10L
32, 33, 3465-4576565C32355-22STA 360 to STA 540, S-4R
to S-10R
37, 3865-4576565C32355-51STA 360 to STA 540, S-4L
to S-4R
33, 3465-4577265C32362-19STA 727 to STA 908, S-4L
to S-10L
33, 3465-4577265C32362-20STA 727 to STA 908, S-4R
to S-10R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 19 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 280 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
Skin Panel Installation Drawings-Group 41
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
31, 3265-4577265C32362-21STA 727 to STA 908, S-4L
to S-4R
Skin Panel Installation Drawings-Group 42
Drawing Picture
Sheet(s)
Skin Panel Installation
Drawing
Skin Panel Assembly
Part Number
Location
2965-4576565C32355-3STA 360 to STA 500C, S-4L
to S-10L
2965-4576565C32355-4STA 360 to STA 500C, S-4R
to S-10R
27, 3465-4576565C32355-34STA 360 to STA 500C, S-4L
to S-4R
2965-4577265C32362-5STA 727G to STA 908, S-4L
to S-10L
2965-4577265C32362-6STA 727G to STA 908, S-4R
to S-10R
2765-4577265C32362-2STA 727G to STA 908, S-4L
to S-4R
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS
(SHEET 20 OF 20)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 281 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
APPENDIX F: PART DEMAND INTENT
(SHEET 1 OF 1)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 27, 2017 737-53A1358Revision 1 February 26, 2021 282 of 282
BOEING SERVICE BULLETIN 737-53A1358 ALERTALERT
