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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(SHEET 1 OF 3) Original Issue: February 27, 2018 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 287 of 545
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 repair 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540 BULKHEAD CHORD - SPLICE PREPARATION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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
More DataQtyIdentificationNameTaskStep Apply to all bare metal and open fastener holes. Refer to SOPM 20-43-03 as an accepted procedure.
-TYPE 2, CLASS ACHEMICAL CONVER-
SION COATING Apply6 Apply to all bare metal. Refer to SOPM 20-41-02 as an accepted procedure.
-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
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
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 procedure.
-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 table for torque values.
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 procedure.
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
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
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
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 procedure.
-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 table for torque values.
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 procedure.
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
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
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
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 procedure.
-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 table for torque values.
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 procedure.
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
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