# Boeing Alert Service Bulletin 737-53A1358: SB-737-53A1358-00-BOEING

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- Document: [Boeing Alert Service Bulletin 737-53A1358](https://openairdocs.org/service-documents/boeing/737-53a1358.md)
- Title as filed: SB-737-53A1358-00-BOEING
- Pages: 270
- PDF: https://openairdocs.org/files/sha256/c6/53/c65331a5673a8a67659699ac26766bd7221e143c7b835f4ce221e1411978eeff
- Page: https://openairdocs.org/service-documents/boeing/737-53a1358/file/c65331a5673a

## Text

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### Page 1

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1358
Original Issue: April 27, 2017
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
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2017 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
S u m m a r y  ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A . E f f e c t i v i t y  ............................................... 1 1
1. Airplanes ............................................ 1 1
2 . S p a r e s  A f f e c t e d  ........................................ 2 5
B. Concurrent Requirements ...................................... 2 5
C. Reason ................................................ 2 5
D. Description .............................................. 2 6
E. Compliance .............................................. 2 7
F . A p p r o v a l  ............................................... 3 3
G. Manpower .............................................. 3 3
H. Weight and Balance Changes .................................... 4 4
I. Electrical Load Data ......................................... 4 4
J . R e f e r e n c e s  .............................................. 4 5
1. Existing Data: ......................................... 4 5
2. Data Supplied with this Service Bulletin: ........................... 4 5
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 5
K. Publications Affected ........................................ 4 6
L. Interchangeability and Intermixability of Parts ........................... 4 6
M. Software Accomplishment Summary ................................ 4 6
2. MATERIAL INFORMATION ........................................ 4 7
A. Material - Price and Availability ................................... 4 7
B. Industry Support Information .................................... 7 2
C. Parts Necessary for Each Airplane ................................. 7 2
1 . K i t s / P a r t s  ............................................ 7 2
2. Parts and Materials Supplied by the Operator ........................ 9 5
3. Parts Modified and Reidentified ................................ 9 7
4. Parts Removed and Not Replaced .............................. 9 7
D. Parts Necessary to Change Spares ................................. 9 7
E. Special Tooling - Price and Availability ............................... 9 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 9 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 9 9
A. GENERAL INFORMATION ..................................... 9 9
B. WORK INSTRUCTIONS ...................................... 1 0 1
FIGURE 1: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 1-2] . . . 122
FIGURE 2: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 3-4] . . . 124
FIGURE 3: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 5] .... 1 2 6
FIGURE 4: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 6-7] . . . 128
FIGURE 5: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 8-9] . . . 130
FIGURE 6: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 10-11] . . 132
FIGURE 7: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 12] .... 1 3 4
FIGURE 8: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 13] .... 1 3 6
FIGURE 9: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 14-16] . . 138
FIGURE 10: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 17] .... 1 4 0
FIGURE 11: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 18] .... 1 4 2
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FIGURE 12: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 19] .... 1 4 4
FIGURE 13: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 20] .... 1 4 6
FIGURE 14: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 21] .... 1 4 8
FIGURE 15: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 22] . . . 150
FIGURE 16: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 23] . . . 152
FIGURE 17: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 24] . . . 154
FIGURE 18: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 25] . . . 156
FIGURE 19: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 26] . . . 158
FIGURE 20: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 27] . . . 160
FIGURE 21: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 500C [Group 28] . . . 162
FIGURE 22: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 29-31] . . 164
FIGURE 23: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 32] .... 1 6 6
FIGURE 24: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 33-35, 37] . 168
FIGURE 25: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 36, 39] . . 170
FIGURE 26: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 38, 40] . . 172
FIGURE 27: INSPECTION AREA FROM S-10L TO S-10R FROM STA 360 TO 540 [Group 41] .... 1 7 4
FIGURE 28: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI .............. 1 7 6
FIGURE 29: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 1-4] . 182
FIGURE 30: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 5] . 184
FIGURE 31: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 6-7] . 186
FIGURE 32: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 8, 10, 12-14,
1 7 - 2 1 ]  ............................................. 1 8 8
FIGURE 33: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 9, 11, 16]
................................................. 1 9 0
FIGURE 34: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 15] . 192
FIGURE 35: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727G AND 908 [Group 22-28]
................................................. 1 9 4
FIGURE 36: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 29-30, 33,
3 5 - 3 6 ,  3 8 ,  4 0 - 4 1 ]  ....................................... 1 9 6
FIGURE 37: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 31, 37]
................................................. 1 9 8
FIGURE 38: INSPECTION AREA FROM S-10L TO S-10R BETWEEN STA 727 AND 908 [Group 32, 34, 39]
................................................. 2 0 0
FIGURE 39: INSPECTION OF CHEM-MILL POCKETS ADJACENT TO CRACK LOCATION ..... 2 0 2
FIGURE 40: DAMAGED SKIN REMOVAL ................................. 2 0 4
FIGURE 41: CUT SURFACE AND FASTENER HOLES INSPECTION ................. 2 0 5
F I G U R E  4 2 : I N S U R A N C E  C U T  A N D  S U R F A C E  T R E A T M E N T ..................... 2 0 7
FIGURE 43: CATEGORY C REPAIR INSTALLATION .......................... 2 0 9
FIGURE 44: CATEGORY C REPAIR INSPECTION ........................... 2 1 3
FIGURE 45: PRE-REPAIR CONVERSION INSPECTION ........................ 2 1 4
FIGURE 46: OPTION 1 TO MAKE CATEGORY C REPAIR PERMANENT WITH SOLID FASTENERS AND
T E A R  S T R A P  D O U B L E R S .................................. 2 1 5
FIGURE 47: OPTION 2 TO MAKE CATEGORY C REPAIR PERMANENT WITH A LARGER DOUBLER,
S O L I D  F A S T E N E R S  A N D  T E A R  S T R A P  D O U B L E R S ................... 2 2 0
FIGURE 48: POST REPAIR LFEC INSPECTION OF SB REPAIR, OPTION 1 ............. 2 2 6
FIGURE 49: POST REPAIR LFEC INSPECTION OF SB REPAIR, OPTION 2 ............. 2 2 8
FIGURE 50: SKIN BUTT JOINT INSPECTION AT STA 360 ....................... 2 3 0
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FIGURE 51: SKIN BUTT JOINT INSPECTION AT STA 540 ....................... 2 3 2
FIGURE 52: SKIN BUTT JOINT INSPECTION AT STA 727 ....................... 2 3 4
FIGURE 53: SKIN BUTT JOINT INSPECTION AT STA 908 ....................... 2 3 6
FIGURE 54: SKIN BUTT JOINT INSPECTION AT STA 500C ...................... 2 3 8
FIGURE 55: SKIN BUTT JOINT INSPECTION AT STA 727G ...................... 2 4 0
APPENDIX A: L OGIC 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) .......................... 2 4 2
APPENDIX B: LOGIC DIAGRAM FOR TABLE 2 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF CATEGORY C REPAIR ......................... 2 4 5
APPENDIX C: LOGIC DIAGRAM FOR TABLE 3 OF PARAGRAPH 1.E, COMPLIANCE: POST REPAIR
INSPECTION OF SB REPAIRS INSTALLED IN ACCORDANCE WITH PART 6: CHANGE
CATEGORY C REPAIR TO SB REPAIR OF THIS SERVICE BULLETIN ......... 2 4 7
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)
................................................. 2 4 9
APPENDIX E: SKIN PANEL INSTALLATION DRAWINGS ......................... 2 5 0
APPENDIX F: PART DEMAND INTENT ................................... 2 7 0
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Commercial 
Airplanes
737
Service Bulletin
ALERT
SummaryNumber: 737-53A1358Original Issue: April 27, 2017
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 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 737 FTD 53-15007 is related to this service bulletin.
The fuselage crown skin has been determined to be structure that is susceptible to WFD.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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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).
SB 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 SB.
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:
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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Group 1- 41: 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 SB 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 SB Repair.
Group 1- 41: If any SB 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 SB Repair for any crack.
Group 1- 41: 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:
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.
EFFECTIVITY
737-200/-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 this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and repair procedures given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
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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BOEING SERVICE BULLETIN 737-53A1358
ALERT  ALERT
STA
908
STA
540  STA
STA
360  INSPECTION AND SKIN
REPLACEMENT AREAS FOR
GROUPS 1-21 AND 29-41
DO A NON-DESTRUCTIVE INSPECTION (NDI) OF THE
CROWN SKIN ADJACENT TO CHEM-MILL STEPS FOR
ANY CRACK, IF NO CRACK IS FOUND, REPEAT THE
FRAME  NDI FOR ANY CRACK. IF ANY CRACK IS FOUND,
INSTALL AN SRM REPAIR OR A CATEGORY C REPAIR
AND REPEAT THE NDI AT ALL UNREPAIRED AREAS.
INSPECT ALI  _ CATEGORY C REPAIRS FOR ANY
LOOSE OR  TENERS. REPLACE ANY
_OOSE OR  TENERS. CHANGE ALL
& STRINGER  CATEGOR  TO SB REPAIRS AND DO A
POST-REPAIR  UENCY EDDY CURRENT
(LFEC) INSPEC  FOR ANY CRACK. IF ANY CRACK
IS FOUND. COI  THE BOEING COMPANY FOR
REPAIR INSTRUC  ONS AND DO THE REPAIR.
REPEAT THE LFEC INSPE  TION AT ALL OTHER SB
REPAIR LOCATIONS.  NO CRACK IS FOUND
€ STRINGER  REPEAT THE POST-REPAIR  LFEC INSPECTION FOR
ANY CRACK.
REPLACE ALL SIX CROWN SKIN PANEL ASSEMBLIES.
OUTBOARD VIEW OF SKIN
(TYPICAL)
STA  STA
500C  908
STA
727G
STA
360  INSPECTION AND SKIN
REPLACEMENT AREAS FOR
GROUPS 22-28
2483009
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### Page 11

Commercial 
Airplanes
737
Service Bulletin
ALERT
Number: 737-53A1358
Original Issue: April 27, 2017
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 service bulletin is applicable to 737-200/-200C/-300/-400/-500 Airplanes, line numbers 292-2552
in 41 Groups. 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.
-4
737-200 Airplanes without chem-milled pockets from S-4L and S-4R.-5
737-200C Airplanes.-6
737-200C Airplanes and a different surface finish than Group 6
airplanes.
-7
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DESCRIPTIONCONFIGURATIONGROUP
737-300 Airplanes with no antenna provisions.-8
737-300 Airplanes with no antenna provisions and no chem-milled
pockets from STA 540 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 540 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 540 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 unique configuration at STA 420 to STA 430.-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
737-400 Airplanes with TCAS, ATC and MLS antenna provisions.-26
737-400 Airplanes with TCAS, ATC and Broadcast antenna
provisions.
-27
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DESCRIPTIONCONFIGURATIONGROUP
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 and MLS antenna provisions and no
chem-milled pockets from STA 540 to STA 727C at S-4L to S-10L
and S-4R to S-10R.
-31
737-500 Airplanes with ATC, MLS and ELT antenna provisions.-32
737-500 Airplanes with TCAS and ATC antenna provisions.-33
737-500 Airplanes with TCAS, ATC and ELT antenna provisions.-34
737-500 Airplanes with TCAS and ATC antenna provisions and with
different production skin assemblies to airplanes in Group 33.
-35
737-500 Airplanes with TCAS, ATC and MLS antenna provisions.-36
737-500 Airplanes with TCAS, ATC and MLS antenna provisions and
no chem-milled pockets from STA 540 to STA 727C at S-4L to S-10L
and S-4R to S-10R.
-37
737-500 Airplanes with TCAS, ATC and GPS 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
Airplane Models:
737-200, 737-200C, 737-300, 737-400, 737-500
GroupVariable Number
1PG584 - PG586
1PH001
1PH011 - PH013
1PH021 - PH024
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GroupVariable Number
1PH743
1PJ003 - PJ009
1PJ105 - PJ118
2PJ119
5PJ201 - PJ219
22PJ301 - PJ302
22PJ551
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
1PK431 - PK433
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GroupVariable Number
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
2PK750 - PK765
1PK771 - PK775
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GroupVariable Number
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
2PL491
2PL501 - PL506
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GroupVariable Number
2PL551 - PL562
2PL581
3PL601
4PL602 - PL603
2PL611
2PL621 - PL626
2PL631 - PL632
1PL717 - PL744
2PL745 - PL747
1PL756
1PL758
1PL761 - PL770
1PL781 - PL782
2PL783 - PL788
1PL793
2PM001 - PM006
3PM016 - PM017
1PM021
2PM022 - PM023
2PM051 - PM066
2PM101 - PM119
2PM141 - PM142
2PM171
2PM181
2PM251 - PM255
2PM281 - PM283
8PM381 - PM388
10PM389 - PM391
14PM392 - PM399
14PM401 - PM417
14PM541 - PM542
22PM551 - PM564
2PN001 - PN002
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GroupVariable Number
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
8PP150 - PP169
8PP181 - PP197
10PP198 - PP199
8PP201 - PP205
10PP221
8PP231 - PP243
8PP281 - PP286
8PP301 - PP305
8PP351 - PP353
8PP376 - PP384
8PP391 - PP393
8PP401 - PP440
8PP471 - PP475
8PP501 - PP504
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GroupVariable Number
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
8PP991
10PP993
12PQ001 - PQ012
18PQ013 - PQ016
8PQ026 - PQ037
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GroupVariable Number
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
14PQ481
14PQ486 - PQ487
14PQ491 - PQ493
14PQ771
14PQ791 - PQ793
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GroupVariable Number
20PQ801 - PQ805
15PQ931 - PQ932
14PS601 - PS615
19PS616
14PS631
17PS636 - PS638
10PS641 - PS642
19PS643 - PS644
14PS651 - PS657
10PS666 - PS667
14PS668 - PS669
14PS691 - PS692
14PS701 - PS703
8PS751 - 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
38PT161 - PT170
34PT181
39PT182 - PT187
35PT211 - PT220
39PT295
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GroupVariable Number
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 - PV055
22PV201 - PV203
28PV231 - PV237
22PV271 - PV272
22PV281 - PV283
22PW001 - PW026
23PW027
22PW028
23PW029 - PW032
22PW033 - PW050
23PW051
22PW052 - PW054
23PW061 - PW063
22PW064 - PW068
22PW072
23PW091 - PW093
22PW094
22PW101 - PW102
22PW106
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GroupVariable Number
23PW111 - PW117
22PW118 - PW120
22PW156 - PW157
22PW161 - PW167
22PW201 - PW244
22PW261
22PW265 - PW268
22PW278
22PW281
22PW293
22PW296
22PW301 - PW327
22PW461
28PW462
22PW463 - PW467
23PW501 - PW502
22PW503 - PW504
23PW511 - PW515
24PW516 - PW518
26PW519 - PW520
26PW526
25PW531 - PW537
27PW538 - PW546
27PW556 - PW557
23PW561 - PW563
22PW564
24PW571 - PW574
28PW575 - PW576
24PW591 - PW594
26PW595 - PW596
23PW611 - PW613
22PW614 - PW620
26PW631 - PW634
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GroupVariable Number
22PW661 - PW662
22PW681 - PW683
22PW701
28PW702
22PW711 - PW717
22PW741 - PW742
22PW761
28PW771
6PY022
6PY036 - PY037
6PY046 - PY048
6PY051 - PY053
7PY056 - PY057
6PY101 - PY103
6PY111 - PY113
6PY131 - PY135
6PY141 - PY143
6PY151 - PY153
7PY154
6PY156 - PY157
6PY161 - PY162
6PY166
6PY191
6PY201
6PY221 - PY222
6PY231
6PY241 - PY244
6PY270 - PY275
6PY281
6PY286
6PY401
7PY409 - PY410
6PY411
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GroupVariable Number
6PY421
7PY422
6PY441
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.
Boeing Service Related Problem (SRP) 737-SRP-53-0517 is related to this service bulletin.
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Boeing Fleet Team Digest (FTD) 737 FTD 53-15007 is 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
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).
SB 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 SB.
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:
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- 41: 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 SB
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 SB Repair.
Group 1- 41: If any SB 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 SB Repair
for any crack.
Group 1- 41: 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.
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Group 22-28:
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.
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:
Affected Maintenance Zones
ZoneModel
107, 108737-400
Group 29-41:
Affected Maintenance Zones
ZoneModel
107, 108737-500
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
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### Page 28

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.
Logic diagrams showing compliance tasks and compliance times are included as aids in APPENDIX
A, APPENDIX B, APPENDIX C and APPENDIX D.
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)
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.
1,800 flight cycles.
(b)
-Repeat PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack.(a)
CONDITION 1: NO
CRACK FOUND.
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### Page 29

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)
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.
(b) (d)
-OPTION 1 (ACTION 2):
Repeat PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack. (a)
-Before further flight.OPTION 2 (ACTION 1):
Do PART 3: CATEGORY
C REPAIR. (e) (f)
1,800 flight cycles.
(b) (g)
-OPTION 2 (ACTION 2):
Repeat PART 1: CROWN
SKIN CHEM-MILL STEP
INTERNAL/EXTERNAL
NON-DESTRUCTIVE IN-
SPECTION (NDI) for any
crack.(a)
(a) It is not required to inspect the chem-mill steps under existing repair doublers provided either:
1. The installed repair 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 mini-
mum 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 was approved by the FAA or by a Boeing Company authorized repre-
sentative who was authorized by the FAA to make such findings; and
– The repair 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
– The repair 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.
(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 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
and 737-500 SRM 53-00-01 Repair 31.
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### Page 30

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)
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(d) Accomplishment of PART 2: SRM REPAIR is terminating action to the 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.
(g) Accomplishment of PART 3: CATEGORY C REPAIR is terminating action to the 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 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.
(a) (b)
-CONDITION 3 (ACTION
2): Repeat PART 4:
POST REPAIR INSPEC-
TION OF CATEGORY C
REPAIR for any loose or
missing fastener.
-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 SB 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.
(a) (b)
-CONDITION 4 (ACTION
1): Repeat PART 4:
POST REPAIR INSPEC-
TION OF CATEGORY C
REPAIR for any loose or
missing fastener.
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 SB REPAIR. (b) (c)
(d)
(a) Accomplishment of PART 6: CHANGE CATEGORY C REPAIR TO SB 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 SB REPAIR.
(c) The applicability limitations of the SB Repair are in PART 6: CHANGE CATEGORY C REPAIR TO SB
REPAIR.
(d) Compliance times for inspection of SB Repairs done in accordance with PART 6: CHANGE CATEGORY
C REPAIR TO SB REPAIR are in Table 3.
Table 3: POST REPAIR INSPECTION OF SB REPAIRS INSTALLED IN ACCORDANCE WITH PART 6:
CHANGE CATEGORY C REPAIR TO SB REPAIR 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 SB REPAIR, Option 1.
Do PART 7: POST RE-
PAIR LOW FREQUENCY
EDDY CURRENT (LFEC)
INSPECTION OF SB
REPAIR for any crack. (a)
Airplanes with any SB Re-
pair installed in accordance
with PART 6: CHANGE
CATEGORY C REPAIR
TO SB REPAIR, Option 1.
-Within 60,000 flight cycles after
accomplishment of PART 6:
CHANGE CATEGORY C REPAIR
TO SB REPAIR, Option 2.
Do PART 7: POST RE-
PAIR LOW FREQUENCY
EDDY CURRENT (LFEC)
INSPECTION OF SB
REPAIR for any crack. (a)
Airplanes with any SB Re-
pair installed in accordance
with PART 6: CHANGE
CATEGORY C REPAIR
TO SB REPAIR, Option 2.
-Before further flight.Contact The Boeing
Company for repair in-
structions and do the re-
pair.
CONDITION 5: ANY
CRACK FOUND.
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### Page 32

Table 3: POST REPAIR INSPECTION OF SB REPAIRS INSTALLED IN ACCORDANCE WITH PART 6:
CHANGE CATEGORY C REPAIR TO SB REPAIR OF THIS SERVICE BULLETIN
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
5,000 flight cycles.
(a)
-Repeat PART 7: POST
REPAIR LOW FREQUEN-
CY EDDY CURRENT
(LFEC) INSPECTION OF
SB REPAIR for any
crack.
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 SB 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)
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
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 Aircraft Certification Office (ACO) 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 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) 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 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.
The Manager of the FAA Los Angeles ACO 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 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.
All provisions of AD 2013-18-08, AD 2011-24-12, AD 2015-21-06, AD 2016-16-13 and AD 2003-14-06
that are not specifically referenced in the above statements remain fully applicable and must be complied
with.
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
• Time to cure the materials
• Time to make the parts
• Time to find the tools.
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### Page 34

Group 1-2:
Table 1: PART 1: CROWN SKIN CHEM-MILL STEP INTERNAL/EXTERNAL NDI
Elapsed HoursTask HoursNumber of PersonsTask
18.50185.0010OPEN ACCESS
28.75115.004FIGURE 28 ( FIGURE 1 and
FIGURE 29, 860 bays)
18.50185.0010CLOSE ACCESS
65.75485.00TOTAL 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
28.25113.004FIGURE 28 ( FIGURE 2 and
FIGURE 29, 858 bays)
18.50185.0010CLOSE ACCESS
65.25483.00TOTAL 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
20.0080.004FIGURE 28 ( FIGURE 3 and
FIGURE 30, 572 bays)
18.50185.0010CLOSE ACCESS
57.00450.00TOTAL 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, 630 bays)
18.50185.0010CLOSE ACCESS
59.25459.00TOTAL FOR EACH AIRPLANE
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### Page 35

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
29.75119.004FIGURE 28 ( FIGURE 6 and
FIGURE 33, 844 bays)
18.50185.0010CLOSE ACCESS
66.75489.00TOTAL FOR EACH AIRPLANE
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### Page 36

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
32.50130.004FIGURE 28 ( FIGURE 8 and
FIGURE 32, 944 bays)
18.50185.0010CLOSE ACCESS
69.50500.00TOTAL 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
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
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### Page 37

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
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, 960 bays)
18.50185.0010CLOSE ACCESS
70.75505.00TOTAL FOR EACH AIRPLANE
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### Page 38

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
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
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### Page 39

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
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
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### Page 40

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
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
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### Page 41

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
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
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### Page 42

Group 38, 40:
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
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
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Table 37: DAMAGED SKIN REMOVAL
Elapsed HoursTask HoursNumber of PersonsTask
(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
(a) Total time required is dependent upon the number of repairs that require inspection.
Table 42: PART 6: CHANGE CATEGORY C REPAIR TO SB REPAIR, OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
(a)(a)-OPEN ACCESS
16.0032.002FIGURE 45
8.0016.002FIGURE 46
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Table 42: PART 6: CHANGE CATEGORY C REPAIR TO SB REPAIR, OPTION 1
Elapsed HoursTask HoursNumber of PersonsTask
(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 SB 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 SB 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 SB REPAIR, OPTION 2
Elapsed HoursTask HoursNumber of PersonsTask
0.501.002FIGURE 49
(a)(a)TOTAL FOR EACH AIRPLANE
(a) Total time required is dependent upon the number of repairs that require inspection.
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.
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### Page 45

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
c. Boeing Service Related Problem (SRP) 737-SRP-53-0517
d. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2003-14-06, 2011-24-12,
2013-18-08, 2015-21-06, 2016-16-13
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
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) 25-20-01, 25-21-51, 25-21-61, 25-21-71,
55-32-11
j. 737-100/200 Structural Repair Manual (SRM) 51-10-1, 51-30-2, 51-30-3, 51-30-8, 51-50-1,
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
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
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
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
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TitleDrawing Number
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
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 SB 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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### Page 47

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.
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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
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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.
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### Page 51

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
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### Page 52

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
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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
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### Page 54

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
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### Page 55

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
737-53A1358
55 of 270
BOEING SERVICE BULLETIN 737-53A1358
ALERTALERT

### Page 56

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
737-53A1358
56 of 270
BOEING SERVICE BULLETIN 737-53A1358
ALERTALERT

### Page 57

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
65-45772-167
(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
737-53A1358
57 of 270
BOEING SERVICE BULLETIN 737-53A1358
ALERTALERT

### Page 58

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
737-53A1358
58 of 270
BOEING SERVICE BULLETIN 737-53A1358
ALERTALERT

### Page 59

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
737-53A1358
59 of 270
BOEING SERVICE BULLETIN 737-53A1358
ALERTALERT

### Page 60

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
737-53A1358
60 of 270
BOEING SERVICE BULLETIN 737-53A1358
ALERTALERT

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