# Boeing Alert Service Bulletin 737-53A1368: No revision named, part 2 of 2

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2024-2315; AD 2025-05-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 737-53A1368](https://openairdocs.org/service-documents/boeing/737-53a1368.md)
- Title as filed: 737-53A1368_Part2
- Pages: 146
- PDF: https://openairdocs.org/files/sha256/0f/fa/0ffa539dc97d686f1b460da8b201e340eb0adccc36cb89418f16afe9e49a9a75
- Page: https://openairdocs.org/service-documents/boeing/737-53a1368/file/0ffa539dc97d

## Text

Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 4, Configuration 5.
STA
540  S-22L
(2)5
4 LOCATIONS
4 LOCATIONS
S-23L
2791883
FIGURE 45: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE PREPARATION
(SHEET 1 OF 3)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  287 of 545

### Page 2

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
Align the forward
edge of the splice
with the forward
edge of the lower
bulkhead chord.
1111A2203U5SPLICE PLATE -
FRONT SPAR, WING
CENTER SECTION
Align 1
(a)
Hole size 0.1986-
0.2006 inches.
-111A2203U5SPLICE PLATE -
FRONT SPAR, WING
CENTER SECTION
Drill 2
(b)
Hole size 00.1986-
0.2006 inches.
--STA 540 BULKHEAD
CHORD
Drill
(b)
Hole size 0.1986-
0.2006 inches.
--SKINDrill
(b)
Hole size 0.1986-
0.2006 inches.
-737-53A1368-2LDOUBLERDrill
Hole size 0.1986-
0.2006 inches.
-737-53A1368-3LTRIPLERDrill
Hole size 0.1986-
0.2006 inches.
-111A2203U5SPLICE PLATE -
FRONT SPAR, WING
CENTER SECTION
Drill 3
Hole size 0.1986-
0.2006 inches.
--STA 540 BULKHEAD
CHORD
Drill
Hole size 0.1986-
0.2006 inches.
--SKINDrill
Hole size 0.1986-
0.2006 inches.
-737-53A1368-2LDOUBLERDrill
Hole size 0.1986-
0.2006 inches.
-737-53A1368-3LTRIPLERDrill
- 1111A2203U5SPLICE PLATE -
FRONT SPAR, WING
CENTER SECTION
Remove / Keep4
Deburr all fastener
holes in the splice,
chords, skin and re-
pair parts.
--FASTENER HOLESDeburr5
FIGURE 45: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE PREPARATION
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
288 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 3

More DataQtyIdentificationNameTaskStep
Apply to all bare
metal and open fas-
tener holes. Refer to
SOPM 20-43-03 as
an accepted proce-
dure.
-TYPE 2, CLASS ACHEMICAL CONVER-
SION COATING
Apply6
Apply to all bare
metal. Refer to
SOPM 20-41-02 as
an accepted proce-
dure.
-BMS 10-11, TYPE IPRIMERApply
(a) Install splice plate with 0.010 inch or less pull-down. Shim in accordance with 737-700CONV SRM 51-
30-01, Figure 10.
(b) Refer to 737-700CONV SRM 51-40-06 for acceptable minimum edge margin.
FIGURE 45: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE PREPARATION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
289 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 4 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 1-3, Configuration 5.
STA  540  S-22L
S-23L
8 LOCATIONS 4
S-22L
S-23L
2791884
FIGURE 46: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 1 OF 3)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  737-53A1368
PROPRIETARY - Copyright © Unpublished  Work - See page 1 for details.  290 of 545

### Page 5

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
Apply to all mating
surfaces of the
chords and the
splice. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply1
(a) 1111A2203U3UNPILOTED SPLICE
PLATE - FRONT
SPAR, WING CENTER
SECTION
Install (New)2
- 8-BOLTInstall (New)
- 8-NUTInstall (New)
Refer to fastener ta-
ble for torque val-
ues.
8-NUTTorque
(b) -BMS 5-142, TYPE II,
CLASS B
LOW DENSITY
SEALANT
Apply3
(c) -BMS 5-142, TYPE II,
CLASS B
LOW DENSITY
SEALANT
Apply4
(a) Install splice plate with 0.010 inch or less pull-down. Shim in accordance with 737-600 SRM 51-30-01,
737-700 SRM 51-30-01, 737-700IGW (BBJ) SRM 51-30-01, 737-800 SRM 51-30-01 or 737-900 SRM
51-30-01, Figure 10.
(b) Apply sealant around the splice plate and replace any sealant removed from the chords. Refer to SOPM
20-50-19 as an accepted procedure.
(c) Replace any sealant that was removed from the stringer. Refer to SOPM 20-50-19 as an accepted proce-
dure.
FIGURE 46: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
291 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 6

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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(b)0.1986-0.20068BACB30NX6K11XBOLT, PROTRUDING
HD
A
Torque and re-torque to
39-41 inch-lbs.
- 8BACN10YT3CDNUT, SELF-LOCK,
HEX
(a) Maintain a minimum 2D edge margin. Install wet with BMS 5-95 TYPE I CLASS B sealant. Refer to SOPM
20-50-19 as an accepted procedure.
(b) It is acceptable to install a second oversize bolt of the same type in a 0.2142-0.2162 inch diameter hole.
FIGURE 46: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
292 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 7 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 1-4, Configuration 5.
STA
S-22R  540
S-23R
- 8 LOCATIONS
S-22R
S-23R  2791885
FIGURE 47: RIGHT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 1 OF 3)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  737-53A1368
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  293 of 545

### Page 8

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
Apply to all mating
surfaces of the
chords and the
splice. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply1
(a) 1111A2203U4UNPILOTED SPLICE
PLATE - FRONT
SPAR, WING CENTER
SECTION
Install (New)2
- 8-BOLTInstall (New)
- 8-NUTInstall (New)
Refer to fastener ta-
ble for torque val-
ues.
8-NUTTorque
(b) -BMS 5-142, TYPE II,
CLASS B
LOW DENSITY
SEALANT
Apply3
(c) -BMS 5-142, TYPE II,
CLASS B
LOW DENSITY
SEALANT
Apply4
(a) Install splice plate with 0.010 inch or less pull-down. Shim in accordance with 737-600 SRM 51-30-01,
737-700 SRM 51-30-01, 737-700CONV SRM 51-30-01, 737-700IGW (BBJ) SRM 51-30-01, 737-800 SRM
51-30-01 or 737-900 SRM 51-30-01, Figure 10.
(b) Apply sealant around the splice plate and replace any sealant removed from the chords. Refer to SOPM
20-50-19 as an accepted procedure.
(c) Replace any sealant that was removed from the stringer. Refer to SOPM 20-50-19 as an accepted proce-
dure.
FIGURE 47: RIGHT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
294 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 9

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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(b)0.1986-0.20068BACB30NX6K11XBOLT, PROTRUDING
HD
A
Torque and re-torque to
39-41 inch-lbs.
- 8BACN10YT3CDNUT, SELF-LOCK,
HEX
(a) Maintain a minimum 2D edge margin. Install wet with BMS 5-95 TYPE I CLASS B sealant. Refer to SOPM
20-50-19 as an accepted procedure.
(b) It is acceptable to install a second oversize bolt of the same type in a 0.2142-0.2162 inch diameter hole.
FIGURE 47: RIGHT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
295 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 10 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 4, Configuration 5.
STA  540  S-22L
S-23L
8 LOCATIONS 4
S-22L
S-23L
2791886
FIGURE 48: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 1 OF 3)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  737-53A1368
Work - See page 1 for details.  296 of 545

### Page 11

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
Apply to all mating
surfaces of the
chords and the
splice. Refer to
SOPM 20-50-19 as
an accepted proce-
dure.
-BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply1
(a) 1111A2203U5SPLICE PLATE -
FRONT SPAR, WING
CENTER SECTION
Install (New)2
- 8-BOLTInstall (New)
- 8-NUTInstall (New)
Refer to fastener ta-
ble for torque val-
ues.
8-NUTTorque
(b) -BMS 5-142, TYPE II,
CLASS B
LOW DENSITY
SEALANT
Apply3
(c) -BMS 5-142, TYPE II,
CLASS B
LOW DENSITY
SEALANT
Apply4
(a) Install splice plate with 0.010 inch or less pull-down. Shim in accordance with 737-700CONV SRM 51-
30-01, Figure 10.
(b) Apply sealant around the splice plate and replace any sealant removed from the chords. Refer to SOPM
20-50-19 as an accepted procedure.
(c) Replace any sealant that was removed from the stringer. Refer to SOPM 20-50-19 as an accepted proce-
dure.
FIGURE 48: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 2 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
297 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 12

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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(b)0.1986-0.20068BACB30NX6K11XBOLT, PROTRUDING
HD
A
Torque and re-torque to
39-41 inch-lbs.
- 8BACN10YT3CDNUT, SELF-LOCK,
HEX
(a) Maintain a minimum 2D edge margin. Install wet with BMS 5-95 TYPE I CLASS B sealant. Refer to SOPM
20-50-19 as an accepted procedure.
(b) It is acceptable to install a second oversize bolt of the same type in a 0.2142-0.2162 inch diameter hole.
FIGURE 48: LEFT SIDE - STA 540 BULKHEAD CHORD - SPLICE INSTALLATION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
298 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 13 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 2, 4-5; Group 3, Configuration 2, 4-5; Group 4,
Configuration 2, 4-5; Group 5, 7-8.
STA
540
STRINGER S-21L
STRINGER S-22L
STRINGER S-23L
FAIRING SUPPORT
INBD  STRUCTURE
VIEW LOOKING AFT
SIA 500
STA 520  STA 540
• S-21L
******  •-S-22L
RAM AIR INLET
FUSELAGE SKIN -
REPAIR DOUBLER
REPAIR TRIPLER  - S-23L
FAIRING SUPPORT STRUCTURE NOT SHOWN  2588034
A-A
FIGURE 49: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 1 OF 6)
Original Issue: February 27, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1368
Work - See page 1 for details.  299 of 545

### Page 14 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
REPAIR TRIPLER
REPAIR DOUBLER
FUSELAGE SKIN
0.43
S-22L
9 EQ SF
6F
STIFFENER
D  E -  RAM AIR INLET
•RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
B-B
X10
0.46  1.20
0.40  1.00
STA 520
S-22L
R 0.50 MIN
REPAIR ANGLE
S-22L'  • FUSELAGE SKIN
• REPAIR DOUBLER
RAM AIR INLET
• REPAIR TRIPLER
C-C
2588035
FIGURE 49: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 2 OF 6)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  737-53A1368
Work - See page 1 for details.  300 of 545

### Page 15 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
• STRINGER 22
-S-22L
• FUSELAGE SKIN
S-22L
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
• RAM AIR INLET
FUSELAGE SKIN
D-D
S-22L  REPAIR
DOUBLER
8 / 12
RAM AIR INLET
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
• RAM AIR INLET
REPAIR  DOUBLER  E-E
5/8
REPAIR
TRIPLER
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
• RAM AIR INLET
F-F  2588084
FIGURE 49: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 3 OF 6)
Original Issue: February 27, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1368
Work - See page 1 for details.  301 of 545

### Page 16

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a) --RAM AIR INLET
FLANGE
Cut 1
(b) --RAM AIR INLET
FLANGE
Deburr2
(h) 1737-53A1368-3L-SMSHIMLocate3
(h) 1737-53A1368-5L-SMSHIMLocate4
(e)(f) 1737-53A1368-1L-RAREPAIR ANGLELocate5
(h) 1737-53A1368-3L-SMSHIMInstall (New)6
(h) 1737-53A1368-5L-SMSHIMInstall (New)7
(e)(f)(g)1737-53A1368-1L-RAREPAIR ANGLEInstall (New)8
(m) One Coat-BMS 10-11, TYPE IPRIMERApply9
(n) -BMS 10-86, TYPE I OR
II
ABRASION RESIS-
TANT TEFLON COAT-
ING
Apply10
(c)(d)(i)(j)(k)-BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply11
(l)(o) -BMS 3-23 TYPE IICORROSION INHIBIT-
ING COMPOUND
Apply12
(a) Maintain 2.25 X fastener diameter plus 0.08 inch minimum edge margin from fastener centerline to the
edge of ram air inlet.
(b) Sand/deburr trimmed edges smooth with 280/300 medium grit abrasive cloth or with a scotchbrite abrasive
pad.
(c) Seal trimmed edge. Refer to SOPM 20-50-19 as an accepted procedure.
(d) BMS 5-92, Type I adhesive can be used as an alternative to BMS 5-95 sealant.
(e) Make sure that the repair angle does not interfere with the existing structure.
(f) Maintain minimum edge margin in accordance with 737-600 SRM 51-40-06, 737-700 SRM 51-40-06,
737-700CONV SRM 51-40-06, 737-700IGW (BBJ) SRM 51-40-06 or 737-800 SRM 51-40-06.
(g) Provide fillet relief under the head of protruding hex-drive bolts in the repair angle in accordance with 737-
600 SRM 51-40-05, 737-700 SRM 51-40-05, 737-700CONV SRM 51-40-05, 737-700IGW (BBJ) SRM
51-40-05 or 737-800 SRM 51-40-05.
FIGURE 49: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 4 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
302 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 17

More DataQtyIdentificationNameTaskStep
(h) Shim all gaps greater than 0.005 inch up to a max of 0.04 inch prior to fastener installation with 2024-T3
clad sheet.
– Refer to SOPM 20-50-20 as an accepted procedure for shim installation.
– Apply BMS 5-95 faying surface seal to both sides of shim. Refer to SOPM 20-50-19 as an accepted
procedure.
(i) Fillet seal all edges along the repair. Refer to SOPM 20-50-19 as an accepted procedure.
(j) Apply sealant to all faying surfaces. Refer to SOPM 20-50-19 as an accepted procedure.
(k) Fill all gaps and voids.
(l) Apply to the repair area after the repair has been installed. Refer to SOPM 20-41-05 as an accepted
procedure.
(m) Apply to all exposed fastener surfaces up to two inches outside the fastener row centerline. Refer to
SOPM 20-41-02 as an accepted procedure.
(n) Apply to area where primer was applied. Refer to SOPM 20-44-01, Type 27, as an accepted procedure.
(o) Can be applied after a minimum of 8 hours curing time following BMS 10-86 abrasion resistant teflon
coating application or immediately after BMS 5-95 sealant application.
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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(e)(f)0.1900 -
0.1930
10BACB30NX6K3BOLT, PROTRUDING
HD
A
(b)(c)(e)(f)0.1895-0.190510BACB30NX6K3BOLT, PROTRUDING
HD
(f)- 10BACC30M6COLLAR
FIGURE 49: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
303 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 18

More DataHole DiaQtyIdentificationNameCode
(a)(e)0.2030 -
0.2060
3BACB30NX6K5XBOLT, PROTRUDING
HD
B
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
-- 3BACC30M6COLLAR
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
C
-- 3BACC30M6COLLAR
(a) Hole size in fiberglass ram air inlet.
(b) Hole size in repair angle.
(c) Close ream hole in repair angle.
(d) Hole size in repair angle, shims, fuselage skin and stringer.
(e) Install fastener with wet sealant. Refer to SOPM 20-50-19, Method 3 as an accepted procedure.
(f) Cap seal fastener. Apply BMS 5-95 sealant to the bolt end and collar and to the bolt head. Refer to SOPM
20-50-19 as an accepted procedure.
FIGURE 49: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
304 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 19 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 2-3, 5; Group 3, Configuration 2-3, 5; Group 4,
Configuration 2-3, 5; Group 5, 7-8.
STA
540
STRINGER S-21R
STRINGER S-22R
STRINGER S-23R
FAIRING SUPPORT,
STRUCTURE  INBD
VIEW LOOKING AFT
STA 500
STA 540  STA 520
S-21R
S-22R  *******
RAM AIR INLET
FUSELAGE SKIN
REPAIR DOUBLER
S-23R  REPAIR TRIPLER
FAIRING SUPPORT STRUCTURE NOT SHOWN  2588247
A-A
FIGURE 50: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 1 OF 6)
Original Issue: February 27, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1368
Work - See page 1 for details.  305 of 545

### Page 20 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
REPAIR TRIPLER
REPAIR DOUBLER
FUSELAGE SKIN
4J  D  S-22R
9 EQ SP
• STIFFENER
RAM AIR INLET  • E  D
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
B-B
0.46
1.00  0.40
STA
520
S-22R
R 0.50 MIN
REPAIR ANGLE
FUSELAGE SKIN  S-22R
REPAIR DOUBLER •
RAM AIR INLET
REPAIR TRIPLER
C-C
2588248
FIGURE 50: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 2 OF 6)
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Work - See page 1 for details.  306 of 545

### Page 21 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STRINGER 22 C-
S-22R -
FUSELAGE SKIN
S-22R
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
RAM AIR INLET•
FUSELAGE SKIN
D-D
REPAIR  S-22R
DOUBLER
5) 8
RAM AIR INLET
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
RAM AIR INLET
E-E  REPAIR  DOUBLER
REPAIR
TRIPLER
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
RAM AIR INLET-
F-F  2588265
FIGURE 50: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 3 OF 6)
Original Issue: February 27, 2018
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PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  307 of 545

### Page 22

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a) --RAM AIR INLET
FLANGE
Cut 1
(b) --RAM AIR INLET
FLANGE
Deburr2
(h) 1737-53A1368-3R-SMSHIMLocate3
(h) 1737-53A1368-5R-SMSHIMLocate4
(e)(f) 1737-53A1368-2R-RAREPAIR ANGLELocate5
(h) 1737-53A1368-3R-SMSHIMInstall (New)6
(h) 1737-53A1368-5R-SMSHIMInstall (New)7
(e)(f)(g)1737-53A1368-2R-RAREPAIR ANGLEInstall (New)8
(m) One Coat-BMS 10-11, TYPE IPRIMERApply9
(n) -BMS 10-86, TYPE I OR
II
ABRASION RESIS-
TANT TEFLON COAT-
ING
Apply10
(c)(d)(i)(j)(k)-BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply11
(l)(o) -BMS 3-23 TYPE IICORROSION INHIBIT-
ING COMPOUND
Apply12
(a) Maintain 2.25 X fastener diameter plus 0.08 inch minimum edge margin from fastener centerline to the
edge of ram air inlet.
(b) Sand/deburr trimmed edges smooth with 280/300 medium grit abrasive cloth or with a scotchbrite abrasive
pad.
(c) Seal trimmed edge. Refer to SOPM 20-50-19 as an accepted procedure.
(d) BMS 5-92, Type I adhesive can be used as an alternative to BMS 5-95 sealant.
(e) Make sure that the repair angle does not interfere with the existing structure.
(f) Maintain minimum edge margin in accordance with 737-600 SRM 51-40-06, 737-700 SRM 51-40-06,
737-700CONV SRM 51-40-06, 737-700IGW (BBJ) SRM 51-40-06 or 737-800 SRM 51-40-06.
(g) Provide fillet relief under the head of protruding hex-drive bolts in the repair angle in accordance with 737-
600 SRM 51-40-05, 737-700 SRM 51-40-05, 737-700CONV SRM 51-40-05, 737-700IGW (BBJ) SRM
51-40-05 or 737-800 SRM 51-40-05.
FIGURE 50: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 4 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
308 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 23

More DataQtyIdentificationNameTaskStep
(h) Shim all gaps greater than 0.005 inch up to a max of 0.04 inch prior to fastener installation with 2024-T3
clad sheet.
– Refer to SOPM 20-50-20 as an accepted procedure for shim installation.
– Apply BMS 5-95 faying surface seal to both sides of shim. Refer to SOPM 20-50-19 as an accepted
procedure.
(i) Fillet seal all edges along the repair. Refer to SOPM 20-50-19 as an accepted procedure.
(j) Apply sealant to all faying surfaces. Refer to SOPM 20-50-19 as an accepted procedure.
(k) Fill all gaps and voids.
(l) Apply to the repair area after the repair has been installed. Refer to SOPM 20-41-05 as an accepted
procedure.
(m) Apply to all exposed fastener surfaces up to two inches outside the fastener row centerline. Refer to
SOPM 20-41-02 as an accepted procedure.
(n) Apply to area where primer was applied. Refer to SOPM 20-44-01, Type 27, as an accepted procedure.
(o) Can be applied after a minimum of 8 hours curing time following BMS 10-86 abrasion resistant teflon
coating application or immediately after BMS 5-95 sealant application.
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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(e)(f)0.1900 -
0.1930
10BACB30NX6K3BOLT, PROTRUDING
HD
A
(b)(c)(e)(f)0.1895-0.190510BACB30NX6K3BOLT, PROTRUDING
HD
(f)- 10BACC30M6COLLAR
FIGURE 50: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
309 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 24

More DataHole DiaQtyIdentificationNameCode
(a)(e)0.2030 -
0.2060
3BACB30NX6K5XBOLT, PROTRUDING
HD
B
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
-- 3BACC30M6COLLAR
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
C
-- 3BACC30M6COLLAR
(a) Hole size in fiberglass ram air inlet.
(b) Hole size in repair angle.
(c) Close ream hole in repair angle.
(d) Hole size in repair angle, shims, fuselage skin and stringer.
(e) Install fastener with wet sealant. Refer to SOPM 20-50-19, Method 3 as an accepted procedure.
(f) Cap seal fastener. Apply BMS 5-95 sealant to the bolt end and collar and to the bolt head. Refer to SOPM
20-50-19 as an accepted procedure.
FIGURE 50: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
310 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 25 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 2, 4-5; Group 6.
STA
540
STRINGER S-21L
STRINGER S-22L
STRINGER S-23L
FAIRING SUPPORT
INBD  STRUCTURE
VIEW LOOKING AFT
STA 500
STA 520  STA 540
- S-21L
*******  1 7-S-22L
RAM AIR INLET
FUSELAGE SKIN -
REPAIR DOUBLER
REPAIR TRIPLER  - S-23L
FWD
FAIRING SUPPORT STRUCTURE NOT SHOWN  2737770
A-A
FIGURE 51: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 1 OF 6)
Original Issue: February 27, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1368
Work - See page 1 for details.  311 of 545

### Page 26 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
REPAIR TRIPLER
REPAIR DOUBLER
FUSELAGE SKIN
S-22L 0.43-
9 EQ SP
STIFFENER
E -  RAM AIR INLET
•RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
B-B
9 10
0.46  1.20
0.40  1.00
STA 520
S-22L
R 0.50 MIN
REPAIR ANGLE
S-22L'  • FUSELAGE SKIN
• REPAIR DOUBLER
RAM AIR INLET
• REPAIR TRIPLER
C-C
2717750
FIGURE 51: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 2 OF 6)
Original Issue: February 27, 2018
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Work - See page 1 for details.  312 of 545

### Page 27 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
• STRINGER 22
-S-22L
• FUSELAGE SKIN
S-22L
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
• RAM AIR INLET
FUSELAGE SKIN
D-D
S-22L  REPAIR
DOUBLER
8 / 12
RAM AIR INLET
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
• RAM AIR INLET
REPAIR  DOUBLER  E-E
5/8
REPAIR
TRIPLER
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
• RAM AIR INLET
F-F  2737782
FIGURE 51: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 3 OF 6)
Original Issue: February 27, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1368
Work - See page 1 for details.  313 of 545

### Page 28

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a) --RAM AIR INLET
FLANGE
Cut 1
(b) --RAM AIR INLET
FLANGE
Deburr2
(h) 1737-53A1368-3L-SMSHIMLocate3
(h) 1737-53A1368-5L-SMSHIMLocate4
(e)(f) 1737-53A1368-1L-RAREPAIR ANGLELocate5
(h) 1737-53A1368-3L-SMSHIMInstall (New)6
(h) 1737-53A1368-5L-SMSHIMInstall (New)7
(e)(f)(g)1737-53A1368-1L-RAREPAIR ANGLEInstall (New)8
(m) One Coat-BMS 10-11, TYPE IPRIMERApply9
(n) -BMS 10-86, TYPE I OR
II
ABRASION RESIS-
TANT TEFLON COAT-
ING
Apply10
(c)(d)(i)(j)(k)-BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply11
(l)(o) -BMS 3-23 TYPE IICORROSION INHIBIT-
ING COMPOUND
Apply12
(a) Maintain 2.25 X fastener diameter plus 0.08 inch minimum edge margin from fastener centerline to the
edge of ram air inlet.
(b) Sand/deburr trimmed edges smooth with 280/300 medium grit abrasive cloth or with a scotchbrite abrasive
pad.
(c) Seal trimmed edge. Refer to SOPM 20-50-19 as an accepted procedure.
(d) BMS 5-92, Type I adhesive can be used as an alternative to BMS 5-95 sealant.
(e) Make sure that the repair angle does not interfere with the existing structure.
(f) Maintain minimum edge margin in accordance with 737-600 SRM 51-40-06, 737-700 SRM 51-40-06,
737-700CONV SRM 51-40-06, 737-700IGW (BBJ) SRM 51-40-06 or 737-800 SRM 51-40-06.
(g) Provide fillet relief under the head of protruding hex-drive bolts in the repair angle in accordance with 737-
600 SRM 51-40-05, 737-700 SRM 51-40-05, 737-700CONV SRM 51-40-05, 737-700IGW (BBJ) SRM
51-40-05 or 737-800 SRM 51-40-05.
FIGURE 51: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 4 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
314 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 29

More DataQtyIdentificationNameTaskStep
(h) Shim all gaps greater than 0.005 inch up to a max of 0.04 inch prior to fastener installation with 2024-T3
clad sheet.
– Refer to SOPM 20-50-20 as an accepted procedure for shim installation.
– Apply BMS 5-95 faying surface seal to both sides of shim. Refer to SOPM 20-50-19 as an accepted
procedure.
(i) Fillet seal all edges along the repair. Refer to SOPM 20-50-19 as an accepted procedure.
(j) Apply sealant to all faying surfaces. Refer to SOPM 20-50-19 as an accepted procedure.
(k) Fill all gaps and voids.
(l) Apply to the repair area after the repair has been installed. Refer to SOPM 20-41-05 as an accepted
procedure.
(m) Apply to all exposed fastener surfaces up to two inches outside the fastener row centerline. Refer to
SOPM 20-41-02 as an accepted procedure.
(n) Apply to area where primer was applied. Refer to SOPM 20-44-01, Type 27, as an accepted procedure.
(o) Can be applied after a minimum of 8 hours curing time following BMS 10-86 abrasion resistant teflon
coating application or immediately after BMS 5-95 sealant application.
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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(e)(f)0.1900 -
0.1930
10BACB30NX6K3BOLT, PROTRUDING
HD
A
(b)(c)(e)(f)0.1895-0.190510BACB30NX6K3BOLT, PROTRUDING
HD
(f)- 10BACC30M6COLLAR
FIGURE 51: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
315 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 30

More DataHole DiaQtyIdentificationNameCode
(a)(e)0.2030 -
0.2060
3BACB30NX6K5XBOLT, PROTRUDING
HD
B
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
-- 3BACC30M6COLLAR
(a)(e)0.2030 -
0.2060
3BACB30NX6K5XBOLT, PROTRUDING
HD
C
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
-- 3BACC30M6COLLAR
(a) Hole size in fiberglass ram air inlet.
(b) Hole size in repair angle.
(c) Close ream hole in repair angle.
(d) Hole size in repair angle, shims, fuselage skin and stringer.
(e) Install fastener with wet sealant. Refer to SOPM 20-50-19, Method 3 as an accepted procedure.
(f) Cap seal fastener. Apply BMS 5-95 sealant to the bolt end and collar and to the bolt head. Refer to SOPM
20-50-19 as an accepted procedure.
FIGURE 51: LEFT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
316 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 31 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 2-3, 5; Group 6.
STA
540
STRINGER S-21R
STRINGER S-22R
STRINGER S-23R
FAIRING SUPPORT
STRUCTURE  INBD
VIEW LOOKING AFT
STA 500
STA 540  STA 520
S-21R-
S-22R -  ******
RAM AIR INLET
- FUSELAGE SKIN
• REPAIR DOUBLER
S-23R -  REPAIR TRIPLER
WD
FAIRING SUPPORT STRUCTURE NOT SHOWN  2737771
A-A
FIGURE 52: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 1 OF 6)
Original Issue: February 27, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1368
Work - See page 1 for details.  317 of 545

### Page 32 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
REPAIR TRIPLER
REPAIR DOUBLER
FUSELAGE SKIN
_S-22R
9 EQ SP
• STIFFENER
RAM AIR INLET  • E  D
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
B-B
0.46
1.00  0.40
STA
DE  520
• S-22R
R 0.50 MIN
REPAIR ANGLE
FUSELAGE SKIN  S-22R
REPAIR DOUBLER •
RAM AIR INLET
REPAIR TRIPLER
C-C
2717752
FIGURE 52: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 2 OF 6)
Original Issue: February 27, 2018
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Work - See page 1 for details.  318 of 545

### Page 33 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STRINGER 22 C-
S-22R -
FUSELAGE SKIN
S-22R
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
RAM AIR INLET•
FUSELAGE SKIN
D-D
REPAIR  S-22R
DOUBLER
€ 3
RAM AIR INLET
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
RAM AIR INLET
E-E  REPAIR  DOUBLER
REPAIR
TRIPLER
RAM AIR INLET CLOSEOUT
PANEL INSTALLATION
RAM AIR INLET-
F-F  2737783
FIGURE 52: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 3 OF 6)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  737-53A1368
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  319 of 545

### Page 34

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
More DataQtyIdentificationNameTaskStep
(a) --RAM AIR INLET
FLANGE
Cut 1
(b) --RAM AIR INLET
FLANGE
Deburr2
(h) 1737-53A1368-3R-SMSHIMLocate3
(h) 1737-53A1368-5R-SMSHIMLocate4
(e)(f) 1737-53A1368-2R-RAREPAIR ANGLELocate5
(h) 1737-53A1368-3R-SMSHIMInstall (New)6
(h) 1737-53A1368-5R-SMSHIMInstall (New)7
(e)(f)(g)1737-53A1368-2R-RAREPAIR ANGLEInstall (New)8
(m) One Coat-BMS 10-11, TYPE IPRIMERApply9
(n) -BMS 10-86, TYPE I OR
II
ABRASION RESIS-
TANT TEFLON COAT-
ING
Apply10
(c)(d)(i)(j)(k)-BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply11
(l)(o) -BMS 3-23 TYPE IICORROSION INHIBIT-
ING COMPOUND
Apply12
(a) Maintain 2.25 X fastener diameter plus 0.08 inch minimum edge margin from fastener centerline to the
edge of ram air inlet.
(b) Sand/deburr trimmed edges smooth with 280/300 medium grit abrasive cloth or with a scotchbrite abrasive
pad.
(c) Seal trimmed edge. Refer to SOPM 20-50-19 as an accepted procedure.
(d) BMS 5-92, Type I adhesive can be used as an alternative to BMS 5-95 sealant.
(e) Make sure that the repair angle does not interfere with the existing structure.
(f) Maintain minimum edge margin in accordance with 737-600 SRM 51-40-06, 737-700 SRM 51-40-06,
737-700CONV SRM 51-40-06, 737-700IGW (BBJ) SRM 51-40-06 or 737-800 SRM 51-40-06.
(g) Provide fillet relief under the head of protruding hex-drive bolts in the repair angle in accordance with 737-
600 SRM 51-40-05, 737-700 SRM 51-40-05, 737-700CONV SRM 51-40-05, 737-700IGW (BBJ) SRM
51-40-05 or 737-800 SRM 51-40-05.
FIGURE 52: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 4 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
320 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 35

More DataQtyIdentificationNameTaskStep
(h) Shim all gaps greater than 0.005 inch up to a max of 0.04 inch prior to fastener installation with 2024-T3
clad sheet.
– Refer to SOPM 20-50-20 as an accepted procedure for shim installation.
– Apply BMS 5-95 faying surface seal to both sides of shim. Refer to SOPM 20-50-19 as an accepted
procedure.
(i) Fillet seal all edges along the repair. Refer to SOPM 20-50-19 as an accepted procedure.
(j) Apply sealant to all faying surfaces. Refer to SOPM 20-50-19 as an accepted procedure.
(k) Fill all gaps and voids.
(l) Apply to the repair area after the repair has been installed. Refer to SOPM 20-41-05 as an accepted
procedure.
(m) Apply to all exposed fastener surfaces up to two inches outside the fastener row centerline. Refer to
SOPM 20-41-02 as an accepted procedure.
(n) Apply to area where primer was applied. Refer to SOPM 20-44-01, Type 27, as an accepted procedure.
(o) Can be applied after a minimum of 8 hours curing time following BMS 10-86 abrasion resistant teflon
coating application or immediately after BMS 5-95 sealant application.
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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)(e)(f)0.1900 -
0.1930
10BACB30NX6K3BOLT, PROTRUDING
HD
A
(b)(c)(e)(f)0.1895-0.190510BACB30NX6K3BOLT, PROTRUDING
HD
(f)- 10BACC30M6COLLAR
FIGURE 52: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
321 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 36

More DataHole DiaQtyIdentificationNameCode
(a)(e)0.2030 -
0.2060
3BACB30NX6K5XBOLT, PROTRUDING
HD
B
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
-- 3BACC30M6COLLAR
(a)(e)0.2030 -
0.2060
3BACB30NX6K5XBOLT, PROTRUDING
HD
C
(d)(e)0.2026 -
0.2036
3BACB30NX6K5XBOLT, PROTRUDING
HD
-- 3BACC30M6COLLAR
(a) Hole size in fiberglass ram air inlet.
(b) Hole size in repair angle.
(c) Close ream hole in repair angle.
(d) Hole size in repair angle, shims, fuselage skin and stringer.
(e) Install fastener with wet sealant. Refer to SOPM 20-50-19, Method 3 as an accepted procedure.
(f) Cap seal fastener. Apply BMS 5-95 sealant to the bolt end and collar and to the bolt head. Refer to SOPM
20-50-19 as an accepted procedure.
FIGURE 52: RIGHT SIDE - STA 540 - RAM AIR INLET REPAIR
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
322 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 37 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 2, 4-5; Group 5.
STRINGER S-22L
STRINGER S-23L
FAIRING SUPPORT
STRUCTURE
INBD
VIEW LOOKING AFT
STA 500
STA 520  STA 540
- S-21L
-S-22L
- S-23L
FWD
FAIRING SUPPORT STRUCTURE NOT SHOWN  2585679
A-A
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 1 OF 9)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  737-53A1368
PROPRIETARY - Copyright © Unpublished
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STA 500
S-21L-
4194944994494
S-22L -
FWD
) 8 LOCATIONS
7799949
WING SKIN  VIEW LOOKING UP  FWD  2585680
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 2 OF 9)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STA 520
STA 540
- S-21L
- S-23L
FWD  2585683
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 3 OF 9)
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Work - See page 1 for details.  325 of 545

### Page 40

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 1643A0062-1DRAG LINK ASSYAlign 1
Refer to fastener
code table for hole
sizes.
-643A0062-1DRAG LINK ASSYDrill 2
Refer to fastener
code table for hole
sizes. (b)
--LOWER WING
STRUCTURE
ColdWork
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 4 OF 9)
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737-53A1368
326 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 41

More DataQtyIdentificationNameTaskStep
(e) -BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply3
(a)(c)(d)1643A0062-1DRAG LINK ASSYInstall (New)4
(a) Maintain a minimum 2D edge margin. Refer to fastener code table for fastener information.
(b) Cold work the fastener hole only if a 2nd oversize fastener is used.
(c) Install wet with BMS 5-95, TYPE I, CLASS B between mating surfaces of drag link assembly, fillers and
wing skin and between drag link assembly and fuselage skin or wing skin. Refer to SOPM 20-50-19 as
an accepted procedure.
(d) Make sure that no preload or pull-down in excess of 0.010 inch exists during installation. Shim in accordance
with 737-600 SRM 51-30-01 or 737-700 SRM 51-30-01 or 737-800 SRM 51-30-01, Figure 10.
(e) Fillet seal the edges of the repair parts in accordance with 737-600 SRM 51-20-05 or 737-700 SRM 51-
20-05 or 737-800 SRM 51-20-05.
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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)0.2510-0.25311BACB30WR4K3LBOLTA
Torque and re-torque to
85-95 in-lbs.
- 1BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K3LXBOLT, RADIUS LEAD-
IN
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 5 OF 9)
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BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 42

More DataHole DiaQtyIdentificationNameCode
(a)0.2510-0.25313BACB30WR4K4LBOLT, RADIUS LEAD-
IN
B
Torque and re-torque to
85-95 in-lbs.
- 3BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K4LXBOLT, RADIUS LEAD-
IN
(a)0.2510-0.253121BACB30WR4K6LBOLT, RADIUS LEAD-
IN
C
Torque and re-torque to
85-95 in-lbs.
- 21BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K6LXBOLT, RADIUS LEAD-
IN
-0.2510-0.25314-FASTENER HOLESD
Hole size for optional first
oversize fastener
0.2606-0.2627--FASTENER HOLES
Hole size for optional sec-
ond oversize fastener
0.2762-0.2783--FASTENER HOLES
-0.3136-0.31563-FASTENER HOLESE
Hole size for optional first
oversize fastener
0.3231-0.3253--FASTENER HOLES
Hole size for optional sec-
ond oversize fastener
0.3387-0.3408--FASTENER HOLES
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2510-
0.2530. (a)(h)
0.2465-0.2485
in existing
structure.
2BACB30YK8K14BOLT, HEX DRIVEF
Torque and re-torque to
80-95 in-lbs.
- 2BACN11CC4KNUT
Optional oversize fasten-
er.
0.2621-0.2641
in existing
structure.
-BACB30YK8K14XHI LOK O/S
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2666-
0.2686. (a)(b)(d)(f)(h)
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 6 OF 9)
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ALERTALERT

### Page 43

More DataHole DiaQtyIdentificationNameCode
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3140-
0.3160. (a)(h)
0.3090-0.3110
in existing
structure.
5BACB30NX10K9BOLT, PROTRUDING
HD
G
Torque and re-torque to
150-200 in-lbs.
- 5BACN10YT5KNUT, SELF-LOCKING
Optional oversize fasten-
er.
0.3246-0.3266
in existing
structure.
-BACB30NX10K9XBOLT, PROTRUDING
HD
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3296-
0.3316. (a)(b)(e)(g)(h)
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 7 OF 9)
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### Page 44

More DataHole DiaQtyIdentificationNameCode
For 737-600/-800 air-
planes.
0.3090-0.3110
in existing
structure.
1BACB30NX10K14BOLT, PROTRUDING
HD
H
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3140-
0.3160. (a)(h)
Torque and re-torque to
150-200 in-lbs.
- 1BACN10YT5KNUT, SELF-LOCKING
For 737-600/-800 air-
planes.
0.3246-0.3266
in existing
structure.
-BACB30NX10K14XBOLT, PROTRUDING
HD
Optional oversize fastener
(a)(b)(e)(g)
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3296-
0.3316. (h)
For 737-600/-800 air-
planes.
- -BACW10CA5PVKWASHER, SELF-
ALIGN
Oversize Washer
BACW10CA51PVK
For 737-600/-800 air-
planes.
- -BACW10CA5CCKWASHER, SELF-
ALIGN
Oversize Washer
BACW10CA6CCK
For 737-700 airplanes.0.2465-0.2485
in existing
structure.
1BACB30NX8K13BOLT, PROTRUDING
HD Ream hole in drag angle
assembly and filler to final
hole diameter 0.2510-
0.2530. (a)(h)
Torque and re-torque to
80-95 in-lb.
- 1BACN10YT4KNUT, SELF-LOCKING
For 737-700 airplanes.0.2621-0.2641
in existing
structure
-BACB30NX8K13XBOLT, PROTRUDING
HD Optional oversize fastener
(a)(b)(d)(f)
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2666-
0.2686. (h)
For 737-700 airplanes.- -BACW10CA104PVKWASHER, SELF-
ALIGN Oversize Washer
BACW10CA41PVK
For 737-700 airplanes.- -BACW10CA104CCKWASHER, SELF-
ALIGN
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 8 OF 9)
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ALERTALERT

### Page 45

More DataHole DiaQtyIdentificationNameCode
Oversize Washer
BACW10CA5CCK
(a)0.2510-0.25312BACB30WR4K9LBOLT, RADIUS LEAD-
IN
I
Torque and re-torque to
85-95 in-lbs.
- 2BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K9LXBOLT, RADIUS LEAD-
IN
-0.2510-0.25312-FASTENER HOLESJ
Hole size for optional first
oversize fastener
0.2606-0.2627--FASTENER HOLES
-0.2510-0.25311-FASTENER HOLEK
Hole size for optional first
oversize fastener
0.2606-0.2627--FASTENER HOLE
(a) Install wet with BMS5-95, TYPE I, CLASS B sealant. Refer to SOPM 20-50-19 as an accepted procedure.
(b) These oversized fasteners are supplied as substitutes for the nominal diameter fasteners. Refer to Para-
graph 2.C.1., Kits/Parts for quantities supplied.
(c) It is acceptable to install a second oversize bolt of the same type in a 0.2762-0.2783 inch diameter hole.
(d) It is acceptable to install a second oversize bolt of the same type if the existing structure is cold worked.
Final hole diameter after cold work is 0.2777-0.2797. Do not cold work the drag angle assembly and filler.
Ream hole in drag angle assembly and filler to 0.2822-0.2842
(e) It is acceptable to install a second oversize bolt of the same type if the existing structure is cold worked.
Final hole diameter after cold work is 0.3402-0.3422. Do not cold work the drag angle assembly and filler.
Ream hole in drag angle assembly and filler to 0.3452-0.3472.
(f) Existing wing structure is cold worked in production. The drag angle assembly is not cold-worked. The
existing hole diameter can be increased to 0.2641 inch maximum without the requirement to re-cold work
the hole. If the existing hole diameter is increased beyond the maximum, re-cold work the hole. Use class
1 cold working with a starting hole diameter of 0.2660-0.2690 inch in accordance with 737-600 SRM 51-
40-09, 737-700 SRM 51-40-09 or 737-800 SRM 51-40-09.
(g) Existing wing structure is cold worked in production. The drag angle assembly is not cold-worked. The
existing hole diameter can be increased to 0.3266 inch maximum without the requirement to re-cold work
the hole. If the existing hole diameter is increased beyond the maximum, re-cold work the hole. Use class
1 cold working with a starting hole diameter of 0.3280-0.3310 inch in accordance with 737-600 SRM 51-
40-09, 737-700 SRM 51-40-09 or 737-800 SRM 51-40-09.
(h) Cap seal collar fastener. Apply with BMS5-45, CLASS B sealant in accordance with 737-600 SRM 51-80-
01, 737-700 SRM 51-80-01 or 737-800 SRM 51-80-01.
FIGURE 53: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 9 OF 9)
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ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 1, Configuration 2-3, 5; Group 5.
STRINGER S-22R
STRINGER S-23R
FAIRING SUPPORT
STRUCTURE
NBD
VIEW LOOKING AFT
STA 500
STA 540  STA 520
S-21R -
S-22R
S-23R •
FWD
FAIRING SUPPORT STRUCTURE NOT SHOWN  2585982
A-A
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 1 OF 9)
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STA 500
- S-21R
C
S-22R
FWD
8 LOCATIONS 2
79944
3 4
VIEW LOOKING UP
WING SKIN  WD  2585989
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 2 OF 9)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STA 520
STA 540
S-21R
44444444
47777
S-23R -
2585992
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 3 OF 9)
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### Page 49

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) 1643A0062-2DRAG LINK ASSYAlign 1
Refer to fastener
code table for hole
sizes.
-643A0062-2DRAG LINK ASSYDrill 2
Refer to fastener
code table for hole
sizes. (b)
--LOWER WING
STRUCTURE
ColdWork
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 4 OF 9)
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ALERTALERT

### Page 50

More DataQtyIdentificationNameTaskStep
(e) -BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply3
(a)(c)(d)1643A0062-2DRAG LINK ASSYInstall (New)4
(a) Maintain a minimum 2D edge margin. Refer to fastener code table for fastener information.
(b) Cold work the fastener hole only if a 2nd oversize fastener is used.
(c) Install wet with BMS 5-95, TYPE I, CLASS B between mating surfaces of drag link assembly, fillers and
wing skin and between drag link assembly and fuselage skin or wing skin. Refer to SOPM 20-50-19 as
an accepted procedure.
(d) Make sure that no preload or pull-down in excess of 0.010 inch exists during installation. Shim in accordance
with 737-600 SRM 51-30-01 or 737-700 SRM 51-30-01 or 737-800 SRM 51-30-01, Figure 10.
(e) Fillet seal the edges of the repair parts in accordance with 737-600 SRM 51-20-05 or 737-700 SRM 51-
20-05 or 737-800 SRM 51-20-05.
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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)0.2510-0.25311BACB30WR4K3LBOLTA
Torque and re-torque to
85-95 in-lbs.
- 1BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K3LXBOLT, RADIUS LEAD-
IN
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 5 OF 9)
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ALERTALERT

### Page 51

More DataHole DiaQtyIdentificationNameCode
(a)0.2510-0.25313BACB30WR4K4LBOLT, RADIUS LEAD-
IN
B
Torque and re-torque to
85-95 in-lbs.
- 3BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K4LXBOLT, RADIUS LEAD-
IN
(a)0.2510-0.253121BACB30WR4K6LBOLT, RADIUS LEAD-
IN
C
Torque and re-torque to
85-95 in-lbs.
- 21BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K6LXBOLT, RADIUS LEAD-
IN
-0.2510-0.25314-FASTENER HOLESD
Hole size for optional first
oversize fastener
0.2606-0.2627--FASTENER HOLES
Hole size for optional sec-
ond oversize fastener
0.2762-0.2783--FASTENER HOLES
-0.3136-0.31563-FASTENER HOLESE
Hole size for optional first
oversize fastener
0.3231-0.3253--FASTENER HOLES
Hole size for optional sec-
ond oversize fastener
0.3387-0.3408--FASTENER HOLES
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2510-
0.2530. (a)(h)
0.2465-0.2485
in existing
structure.
2BACB30YK8K14BOLT, HEX DRIVEF
Torque and re-torque to
80-95 in-lbs.
- 2BACN11CC4KNUT
Optional oversize fasten-
er.
0.2621-0.2641
in existing
structure.
-BACB30YK8K14XHI LOK O/S
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2666-
0.2686. (a)(b)(d)(f)(h)
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 6 OF 9)
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### Page 52

More DataHole DiaQtyIdentificationNameCode
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3140-
0.3160. (a)(h)
0.3090-0.3110
in existing
structure.
5BACB30NX10K9BOLT, PROTRUDING
HD
G
Torque and re-torque to
150-200 in-lbs.
- 5BACN10YT5KNUT, SELF-LOCKING
Optional oversize fasten-
er.
0.3246-0.3266
in existing
structure.
-BACB30NX10K9XBOLT, PROTRUDING
HD
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3296-
0.3316. (a)(b)(e)(g)(h)
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 7 OF 9)
Export Controlled ECCN: 9E991 - BOEING
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ALERTALERT

### Page 53

More DataHole DiaQtyIdentificationNameCode
For 737-600/-800 air-
planes.
0.3090-0.3110
in existing
structure.
1BACB30NX10K14BOLT, PROTRUDING
HD
H
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3140-
0.3160. (a)(h)
Torque and re-torque to
150-200 in-lbs.
- 1BACN10YT5KNUT, SELF-LOCKING
For 737-600/-800 air-
planes.
0.3246-0.3266
in existing
structure.
-BACB30NX10K14XBOLT, PROTRUDING
HD
Optional oversize fastener
(a)(b)(e)(g)
Ream hole in drag angle
assembly and filler to final
hole diameter 0.3296-
0.3316. (h)
For 737-600/-800 air-
planes.
- -BACW10CA5PVKWASHER, SELF-
ALIGN
Oversize Washer
BACW10CA51PVK
For 737-600/-800 air-
planes.
- -BACW10CA5CCKWASHER, SELF-
ALIGN
Oversize Washer
BACW10CA6CCK
For 737-700 airplanes.0.2465-0.2485
in existing
structure.
1BACB30NX8K13BOLT, PROTRUDING
HD Ream hole in drag angle
assembly and filler to final
hole diameter 0.2510-
0.2530. (a)(h)
Torque and re-torque to
80-95 in-lb.
- 1BACN10YT4KNUT, SELF-LOCKING
For 737-700 airplanes.0.2621-0.2641
in existing
structure
-BACB30NX8K13XBOLT, PROTRUDING
HD Optional oversize fastener
(a)(b)(d)(f)
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2666-
0.2686. (h)
For 737-700 airplanes.- -BACW10CA104PVKWASHER, SELF-
ALIGN Oversize Washer
BACW10CA41PVK
For 737-700 airplanes.- -BACW10CA104CCKWASHER, SELF-
ALIGN
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 8 OF 9)
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### Page 54

More DataHole DiaQtyIdentificationNameCode
Oversize Washer
BACW10CA5CCK
(a)0.2510-0.25312BACB30WR4K9LBOLT, RADIUS LEAD-
IN
I
Torque and re-torque to
85-95 in-lbs.
- 2BACN10HY4MSELF-LOCKING NUT
Optional oversize fastener
(a)(b)(c)
0.2606-0.2627-BACB30WR4K9LXBOLT, RADIUS LEAD-
IN
-0.2510-0.25312-FASTENER HOLESJ
Hole size for optional first
oversize fastener
0.2606-0.2627--FASTENER HOLES
-0.2510-0.25311-FASTENER HOLEK
Hole size for optional first
oversize fastener
0.2606-0.2627--FASTENER HOLE
(a) Install wet with BMS5-95, TYPE I, CLASS B sealant. Refer to SOPM 20-50-19 as an accepted procedure.
(b) These oversized fasteners are supplied as substitutes for the nominal diameter fasteners. Refer to Para-
graph 2.C.1., Kits/Parts for quantities supplied.
(c) It is acceptable to install a second oversize bolt of the same type in a 0.2762-0.2783 inch diameter hole.
(d) It is acceptable to install a second oversize bolt of the same type if the existing structure is cold worked.
Final hole diameter after cold work is 0.2777-0.2797. Do not cold work the drag angle assembly and filler.
Ream hole in drag angle assembly and filler to 0.2822-0.2842
(e) It is acceptable to install a second oversize bolt of the same type if the existing structure is cold worked.
Final hole diameter after cold work is 0.3402-0.3422. Do not cold work the drag angle assembly and filler.
Ream hole in drag angle assembly and filler to 0.3452-0.3472.
(f) Existing wing structure is cold worked in production. The drag angle assembly is not cold-worked. The
existing hole diameter can be increased to 0.2641 inch maximum without the requirement to re-cold work
the hole. If the existing hole diameter is increased beyond the maximum, re-cold work the hole. Use class
1 cold working with a starting hole diameter of 0.2660-0.2690 inch in accordance with 737-600 SRM 51-
40-09, 737-700 SRM 51-40-09 or 737-800 SRM 51-40-09.
(g) Existing wing structure is cold worked in production. The drag angle assembly is not cold-worked. The
existing hole diameter can be increased to 0.3266 inch maximum without the requirement to re-cold work
the hole. If the existing hole diameter is increased beyond the maximum, re-cold work the hole. Use class
1 cold working with a starting hole diameter of 0.3280-0.3310 inch in accordance with 737-600 SRM 51-
40-09, 737-700 SRM 51-40-09 or 737-800 SRM 51-40-09.
(h) Cap seal collar fastener. Apply with BMS5-45, CLASS B sealant in accordance with 737-600 SRM 51-80-
01, 737-700 SRM 51-80-01 or 737-800 SRM 51-80-01.
FIGURE 54: RIGHT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 9 OF 9)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
340 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
This Figure applies only to: Group 3, Configuration 2, 4-5; Group 4, Configuration 2, 4-5; Group 7-8.
STRINGER S-22L
STRINGER S-23L
FAIRING SUPPORT
STRUCTURE
INBD
VIEW LOOKING AFT
STA 500
STA 520  STA 540
- S-21L
-S-22L
- S-23L
FWD
FAIRING SUPPORT STRUCTURE NOT SHOWN
A-A
FIGURE 55: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 1 OF 8)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  737-53A1368
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  341 of 545

### Page 56 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STA 500
S-21L-
4194944994494
S-22L -
FWD
) 8 LOCATIONS
1779 9 9 99
VIEW LOOKING UP
WING SKIN  2585709
FIGURE 55: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 2 OF 8)
Original Issue: February 27, 2018
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  737-53A1368
Work - See page 1 for details.  342 of 545

### Page 57 (OCR)

BOEING SERVICE BULLETIN 737-53A1368
ALERT  ALERT
STA 520
STA 540
- S-21L
- S-23L
FWD  2585715
FIGURE 55: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 3 OF 8)
Original Issue: February 27, 2018
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  737-53A1368
Work - See page 1 for details.  343 of 545

### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
(a) 1643A0062-5DRAG LINK ASSYAlign 1
Refer to fastener
code table for hole
sizes.
-643A0062-5DRAG LINK ASSYDrill 2
Refer to fastener
code table for hole
sizes. (b)
--LOWER WING
STRUCTURE
ColdWork
FIGURE 55: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 4 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
344 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 59

More DataQtyIdentificationNameTaskStep
(e) -BMS 5-95, TYPE I,
CLASS B
PRESSURE AND ENVI-
RONMENTAL
SEALANT
Apply3
(a)(c)(d)1643A0062-5DRAG LINK ASSYInstall (New)4
(a) Maintain a minimum 2D edge margin. Refer to fastener code table for fastener information.
(b) Cold work the fastener hole only if a 2nd oversize fastener is used.
(c) Install wet with BMS 5-95, TYPE I, CLASS B between drag link assembly and fuselage skin or wing skin.
Refer to SOPM 20-50-19 as an accepted procedure.
(d) Make sure that no preload or pull-down in excess of 0.010 inch exists during installation. Shim as necessary
in accordance with 737-700CONV SRM 51-30-01 or 737-700IGW (BBJ) SRM 51-30-01, Figure 10.
(e) Fillet seal the edges of the repair parts in accordance with 737-700CONV SRM 51-20-05 or 737-700IGW
(BBJ) SRM 51-20-05.
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
number of fasteners necessary for this figure.
More DataHole DiaQtyIdentificationNameCode
(a)0.2510-0.25311BACB30WR4K3LBOLTA
Torque and re-torque to
85-95 in-lbs.
- 1BACN10HY4MSELF-LOCKING NUT
Optional oversize fasten-
er. (a)(b)(c)
0.2606-0.2627-BACB30WR4K3LXBOLT, RADIUS LEAD-
IN
FIGURE 55: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 5 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
345 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

### Page 60

More DataHole DiaQtyIdentificationNameCode
(a)0.2510-0.25313BACB30WR4K4LBOLT, RADIUS LEAD-
IN
B
Torque and re-torque to
85-95 in-lbs.
- 3BACN10HY4MSELF-LOCKING NUT
Optional oversize fasten-
er. (a)(b)(c)
0.2606-0.2627-BACB30WR4K4LXBOLT, RADIUS LEAD-
IN
(a)0.2510-0.253121BACB30WR4K6LBOLT, RADIUS LEAD-
IN
C
Torque and re-torque to
85-95 in-lbs.
- 21BACN10HY4MSELF-LOCKING NUT
Optional oversize fasten-
er. (a)(b)(c)
0.2606-0.2627-BACB30WR4K6LXBOLT, RADIUS LEAD-
IN
-0.2510-0.25314-FASTENER HOLESD
Hole size for optional first
oversize fastener
0.2606-0.2627--FASTENER HOLES
Hole size for optional sec-
ond oversize fastener
0.2762-0.2783--FASTENER HOLES
-0.3136-0.31563-FASTENER HOLESE
Hole size for optional first
oversize fastener
0.3231-0.3253--FASTENER HOLES
Hole size for optional sec-
ond oversize fastener
0.3387-0.3408--FASTENER HOLES
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2510-
0.2530. (a)(h)
0.2465-0.2485
in existing
structure.
2BACB30YK8K14BOLT, HEX DRIVEF
Torque and re-torque to
80-95 in-lb.
- 2BACN11CC4KNUT
Optional oversize fasten-
er.
0.2621-0.2641
in existing
structure.
-BACB30YK8K14XHI LOK O/S
Ream hole in drag angle
assembly and filler to final
hole diameter 0.2666-
0.2686.(a)(b)(d)(f)(h)
FIGURE 55: LEFT SIDE - STA 540 - DRAG LINK ASSEMBLY INSTALLATION
(SHEET 6 OF 8)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: February 27, 2018
737-53A1368
346 of 545
BOEING SERVICE BULLETIN 737-53A1368
ALERTALERT

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