Commercial

Airplanes 737

Service Bulletin

Number: 737-28A1216

Original Issue: July 29, 2010

Revision 3: July 16, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the

Center and Auxiliary Fuel Tank Boost Pumps

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.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2010 Boeing.

Unpublished Work. All Rights Reserved.

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are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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Revision 3: July 16, 2014 737-28A1216

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3.0
Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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BOEING SERVICE BULLETIN 737-28A1216

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 7

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 92

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 93

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 94

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . 127

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 128

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 129

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 129

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 129

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . 129

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 133

FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16] . . . . . . . . 163

FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 19-20] . . . . . . . . . . . 164

FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802

BOX ASSEMBLY [Group 1-13, 15-16] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 165

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 [Group 1-16, 21-29, 31] . . . . . . . . . 168

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 [Group 1-16, 21-29, 31] . . . . . . . . . 171

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 19-20]

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 174

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30] . . . . . . . . . . . . 177

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30] . . . . . . . . . . . . 180

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

3 of 490

BOEING SERVICE BULLETIN 737-28A1216
FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30] . . . . . . . . . . . . 183

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30] . . . . . . . . . . . . 186

FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16, 19-20] . 189

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 1-13, 15-16] . . . . . . . . . . 190

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 19-20] . . . . . . . . . . . . . 193

FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST [Group

1-13, 15-16, 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 196

FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS [Group 1-13,

15-16, 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 199

FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group

1-13, 15-16] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 201

FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group

19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 203

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS [Group 1-13, 15-16, 19-20] . . 205

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 1-16, 21-29, 31] . . . . . . 209

FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 1-16, 21-29, 31] . . . 211

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036 [Group 1, 21] . . . . . . . . . . . . . . . 212

FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036 [Group 2-3, 22-23] . . . . . . . . . . . . 215

FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036 [Group 4-5, 24] . . . . . . . . . . . . . . 218

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036 [Group 6-7, 25] . . . . . . . . . . . . . . 221

FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036 [Group 8, 26] . . . . . . . . . . . . . . . 224

FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 [Group 9, 31] . . . . . . . . . . . . . . . 227

FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036 [Group 10-11, 27-28] . . . . . . . . . . . 230

FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036 [Group 12, 29] . . . . . . . . . . . . . . 233

FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036 [Group 13] . . . . . . . . . . . . . . . . 236

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036 [Group 14] . . . . . . . . . . . . . . . . 239

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036 [Group 15] . . . . . . . . . . . . . . . . 242

FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036 [Group 16] . . . . . . . . . . . . . . . . 245

FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 17-20, 30] . . . . . . . . . 248

FIGURE 34: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 17-20, 30] . . . . . . 250

FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] . . . . . . . . . . . . . . 251

FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] . . . . . . . . . . . . . . 254

FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30] . . . . . . . . . . . . . . 257

FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] . . . . . . . . . . . . . . . . 260

FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] . . . . . . . . . . . . . . . . 263

FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036 [Group 17] . . . . . . . . . . . . . . . . 266

FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] . . . . . . . . . . . . . . 269

FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] . . . . . . . . . . . . . . 272

FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20] . . . . . . . . . . . . . . 275

FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 1-16, 21-29, 31] . . . 278

FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044 [Group 1, 21] . . . . . . . . . . . . . . . 279

FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 1] . . . . . . 281

FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 2] . . . . . . 283

FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044 [Group 3, 16, 23] . . . . . . . . . . . . . 285

FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 1] . . . . . . . . 287

FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 2] . . . . . . . . 289

FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 [Group 5, 8, 24, 26] . . . . . . . . . . . . 291

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

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FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 1] . . . . . . 293

FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 2] . . . . . . 296

FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044 [Group 9, 31] . . . . . . . . . . . . . . . 299

FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044 [Group 10, 27] . . . . . . . . . . . . . . 302

FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 1] . . . . . 305

FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 2] . . . . . 308

FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044 [Group 13] . . . . . . . . . . . . . . . . 311

FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044 [Group 7] . . . . . . . . . . . . . . . . . 314

FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 1] . . . . . . . 317

FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 2] . . . . . . . 319

FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 1] . . . . . 321

FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 2] . . . . . 323

FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 1] . . . . . . . 325

FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 2] . . . . . . . 327

FIGURE 66: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 17-20, 30] . . . . . . 329

FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 1] . . . . . . . 330

FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] . . . . . . . 333

FIGURE 69: CONNECTION OF WIRE BUNDLE W044 [Group 17, Configuration 1] . . . . . . . . . . 336

FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2] . . . . . . . 339

FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] . . . . . . . 342

FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] . . . . . . . 345

FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1] . . . . . . . 348

FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2] . . . . . . . 351

FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30] . . . . . . . . . . . . . . 354

FIGURE 76: CONNECTION OF WIRE BUNDLE W044 [Group 19, 30, Configuration 1] . . . . . . . . 357

FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30, Configuration 2] . . . . . 360

FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] . . . . . . . 363

FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] . . . . . . . 366

FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1] . . . . . . . 369

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2] . . . . . . . 372

FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 [Group 1-13, 15-16,

19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 375

FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 1-16, 21-29, 31] . . . . . 379

FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 17-20, 30] . . . . . . . . 382

FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 8, 16, 26] . . . . . . . . . . . 385

FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 1-7, 9-15, 21-25, 27-29, 31] . 387

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 17-20, 30] . . . . . . . . . . 389

FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group

1-13, 15-16] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 392

FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group

19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 395

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 1-16, 21-29, 31] . . . . . . 398

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 17-20, 30] . . . . . . . . . 400

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14,

21-29, 31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 402

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18,

30] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 406

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

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FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14,

21-29, 31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 410

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18,

30] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 418

FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] . . . . . . . . . . . . . . . . . . . 426

FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] . . . . . . . . . . . . . . . . . . . . . 430

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] . . . . . . . . . . . 434

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] . . . . . . . . . . . . . . 442

FIGURE 100: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR

AIRPLANE WITH AIRSTAIRS [Group 14, 21-29, 31] . . . . . . . . . . . . . . . . . . . . 450

FIGURE 101: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR

AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] . . . . . . . . . . . . . . . . . . . . . 452

FIGURE 102: INSTALLATION OF THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS

FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] . . . . . . . . . . . . . . . . 454

FIGURE 103: INSTALLATION OF THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS

FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] . . . . . . . . . . . . . . . . . . 456

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

[Group 14, 17-18, 21-31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 458

FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH

AIRSTAIRS [Group 14, 17-18, 21-31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . 465

FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH

AIRSTAIRS [Group 14, 21-29, 31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 471

FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH

AIRSTAIRS [Group 17-18, 30] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 473

FIGURE 108: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION -

INSPECTION [Group 14, 17-18, 21-31] . . . . . . . . . . . . . . . . . . . . . . . . . . . 475

FIGURE 109: ELECTRONICS COMPARTMENT - MOISTURE SHROUD ANGLE AND STRAP - INSPECTION

[Group 14, 17-18, 21-31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 477

FIGURE 110: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION

CHANGE [Group 14, 17-18, 21-31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 479

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE [Group 14, 17-18, 21-31] . . . . . . . . . . . . . . . . . . . . . . . . . 482

APPENDIX A: KIT ORDERING FLOW CHART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 489

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

6 of 490

BOEING SERVICE BULLETIN 737-28A1216
Commercial

Airplanes 737

Service Bulletin

Revision Transmittal Sheet Number: 737-28A1216

Original Issue: July 29, 2010

Revision 3: July 16, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the

Center and Auxiliary Fuel Tank Boost Pumps

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-189-AD, is related to

this service bulletin.

No more work is necessary on the airplane(s) changed in accordance with Revision 2 of this service bulletin.

More work is necessary for airplanes in Groups 17-18, that were changed in accordance with Part 7 of Revision

1 of this service bulletin. These airplanes also need to do the Auxiliary Fuel Boost Pump Auto Shutoff Functional

Test in accordance with PART 8 if the Auxiliary Tank is installed.

REASON FOR REVISION

This revision is sent to tell the operators that airplanes fitted with Airstairs will have improved instructions for the

installation of the J2802 Box Assembly. Operators have identified that within the main electronics compartment,

the current installation procedure of the J2802 Box Assembly can cause it to touch the adjacent Moisture Shroud

structure which can be mounted in different locations. Therefore, additional and updated Figures and Work

Instructions are required to prevent this, and let the operator complete this service bulletin. This revision also

changes the routing of cable bundles, W0368 and W1764, to the P5 overhead panel, Connector D4202, to help

installation of Splice, SP4510. New top kits are introduced to replace existing top kits that are applicable to

airplanes fitted with Airstairs. A new Supplemental Kit is also introduced for operators who have previously

ordered existing top kits but are yet to accomplish this service bulletin.

Also this revision corrects typographical errors in the Kit/Parts tables, Work Instructions, Figures and Step/Flag

Tables.

Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph

3.A., General Information - Notes.

These sections are changed:

1. Summary Background: Planning Data table added.

2. Summary Action: PART 2, PART 4 and PART 5, Work Package 1 updated.

3. Summary Compliance: Statement updated with new recommendation related to Revision 3.

4. Paragraph 1.D., Description: PART 2, PART 4 and PART 5, Work Package 1 updated.

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5. Paragraph 1.E., Compliance: Statement updated with new recommendation related to Revision 3.

6. Paragraph 1.G., Manpower: Existing tables for Groups 14, 17 - 18 and 21 - 31 updated with addition

of new Figures 108 - 111.

7. Paragraph 1.I., Electrical Load Data: More information added to tables.

8. Paragraph 1.J., References: Installation drawings added to table.

9. Paragraph 1.K., Publications Affected: Table updated.

10. Paragraph 2.A., Material - Price and Availability: Pricing and ROLT data updated and two new Top Kits

and a Supplementary Kit added.

11. Paragraph 2.C.1., Kits/Parts: New table added with new Top and Supplementary Kits.

12. Paragraph 2.C.2., Parts and Materials Supplied by the Operator: Table updated with additional

components.

13. Paragraph 3.A., General Information: Notes updated to latest standard and additional information

added.

14. Paragraph 3.B., Work Instructions: Parts 1 - 5 updated with additional instructions, and Parts 7, 8 and

9 updated with amended Figure references.

15. FIGURE 1 and FIGURE 2: Step table note updated.

16. FIGURE 3: Illustration change and Step table updated.

17. FIGURE 4 and FIGURE 5: Flag note updated and footnote added in table.

18. FIGURE 6: Illustration change and Step table updated.

19. FIGURE 7 to FIGURE 10: Flag note updated and footnote added in table.

20. FIGURE 11 to FIGURE 15 and FIGURE 18: Step table More Data column updated.

21. FIGURE 82: Illustration update showing cable bundle re-route.

22. FIGURE 83 to FIGURE 87: Flag table footnotes updated.

23. FIGURE 88: Airplane Applicability updated. Illustration updated.

24. FIGURE 89: Illustration updated.

25. FIGURE 92 to FIGURE 104: Illustration changed and Step tables updated to correct assembly

procedures.

26. FIGURE 105: Illustration update showing cable bundle re-route. Step table updated to correct assembly

procedure and wire bundle part number.

27. FIGURE 106 and FIGURE 107: Illustration change and Step table update.

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BOEING SERVICE BULLETIN 737-28A1216
28. FIGURE 108 to FIGURE 111: Added to service bulletin due to update to assembly procedure.

29. APPENDIX A: Added to service bulletin to aid Kit procurement.

The data given in Information Notice 737-28A1216 IN 04 is included in this revision.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,

to show the location of all content changes.

Pages with no vertical lines have no changes.

REVISION HISTORY

Original Issue: July 29, 2010

Revision 1: March 26, 2012

Revision 2: November 12, 2012

Revision 3: July 16, 2014

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BOEING SERVICE BULLETIN 737-28A1216

BLANK PAGE
Commercial

Airplanes 737

Service Bulletin

Summary Number: 737-28A1216

Original Issue: July 29, 2010

Revision 3: July 16, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the

Center and Auxiliary Fuel Tank Boost Pumps

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B., Concurrent Requirements.

BACKGROUND

This service bulletin is the result of the safety analysis done by Boeing under SFAR 88, "Fuel Tank System Fault

Tolerance Evaluation Requirements." Initial results from the fuel system safety analysis shows that fuel boost

pumps that run dry could cause an overheat condition external of the fuel pump explosion resistance area that

is open to the fuel pump inlet. An overheat condition in this area could possibly cause an unwanted ignition

source for the fuel vapors in the fuel tank and could cause a fire or explosion.

This service bulletin gives the instructions and a kit of parts to install an automatic (auto) shut-off system for the

fuel boost pumps. The fuel boost pumps are installed in the center fuel tank and if equipped, also in the auxiliary

fuel tank. Time delay relays are installed in the new J2802 Box Assembly that will shut off the fuel boost pumps

if the pumps operate with continuous low pressure for 15 seconds. The 15 second time delay relay prevents

extended dry operation of the fuel boost pumps and allows for sufficient time for fuel pump inlet reprime to

prevent nuisance automatic shutoff. The flight crew stays in primary control, with the auto shutoff system as a

backup, to stop the fuel boost pumps after a low pressure indication.

The change installs an automatic shut off system that gives fuel boost pump inlet protection in the fuel tank

against sparks possibly caused by friction overheat damage.

This change affects the Fuel Systems Airworthiness Limitations section of Boeing document

"737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance Requirements

(CMRs), D6-38278-CMR." New AWL "28-AWL-20" will be added to include an operational check of the boost

pump automatic shutoff system for the center fuel tank. AWL "28-AWL-21" will be added to include an operational

check of the fuel boost pump automatic shutoff system for the auxiliary fuel tank, if installed by Boeing. This

change also affects Section 1 and Section 3 of the FAA Approved Airplane Flight Manual (AFM).

This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

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Planning Data Affected Reference

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed Yes Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew Yes Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR 35442-RS)

The work instructions are divided into 31 airplane groups, 9 parts.

PART 1, PART 2, PART 3, PART 4, and PART 5 work instructions are divided into 3 work packages because

of the different wire bundle changes and airplanes without and with Airstairs.

PART 6 work instructions are for Operators that already ordered the kit from the Original Issue, and want to

re-work the kit for airplanes with Airstairs.

PART 7, PART 8, PART 9 provide instructions to change the J2802 Box Assembly for airplanes that incorporated

the Original Issue of the service bulletin.

NOTE: When submitting a Publication Change Request (PCR) to Boeing to incorporate this service bulletin in

the affected manuals, please notify Boeing if Auxiliary Tanks are installed on these airplanes. If Boeing

is not notified about the Auxiliary Tanks, Boeing will assume that the airplanes in these groups do not

have Auxiliary (AUX) tanks and no AUX Tank changes to the affected manuals will be done.

Group 1-13, 15-16:

PART 1 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL TANKS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install

the J2802 Box Assembly.

3. Work Package 3:

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BOEING SERVICE BULLETIN 737-28A1216
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 Box

Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318

and R3321.

Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.

Group 17-18:

PART 2 - AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX) FUEL

TANKS, AND AIRSTAIRS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

NOTE: For Operators that ordered and received the kit at the Original Issue of this service bulletin

but have not accomplished the service bulletin, it will be necessary to change J2802 Box

Assembly supplied in the kit in accordance with PART 6, before its installation.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install

the J2802 Box Assembly.

3. Work Package 3:

NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary

Tank installation. Operators that installed AUX tanks with Fuel Boost Pumps on these airplanes

need to install an Auto Shutoff system. The FAA may release an AD to require that all airplanes

that have AUX tanks with Fuel Boost Pumps install an Auto Shutoff system.

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44. For the airplanes that have an auxiliary fuel tank, between the P6 disconnect panel and

the fuel boost pump relays R146 and R147, make a change to the wire bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 Box

Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 box assembly, install the time delay relays R3318

and R3321. For the airplanes that have auxiliary fuel tank, at the J2802 Box Assembly, install the time

delay relays R3327 and R3329.

Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.

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BOEING SERVICE BULLETIN 737-28A1216
Group 19-20:

PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install

the J2802 Box Assembly.

3. Work Package 3:

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147, make

a change to the wire bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 Box

Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays R3318

and R3321. At the J2802 box assembly, install the time delay relays R3327 and R3329.

Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.

Group 14, 21-29, 31:

PART 4 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL TANKS,

AND AIRSTAIRS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

NOTE: For Operators that ordered and received the kit at the Original Issue of this service bulletin

but have not accomplished the service bulletin, it will be necessary to change J2802 Box

Assembly supplied in the kit in accordance with PART 6, before its installation.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install

the J2802 Box Assembly.

3. Work Package 3:

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44.

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BOEING SERVICE BULLETIN 737-28A1216
In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 Box

Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays R3318

and R3321.

Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.

Group 30:

PART 5 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

NOTE: For Operators that ordered and received the kit at the Original Issue of this service bulletin

but have not accomplished the service bulletin, it will be necessary to change J2802 Box

Assembly supplied in the kit in accordance with PART 6, before its installation.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts, install

the J2802 Box Assembly.

3. Work Package 3:

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147, make

a change to the wire bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802 Box

Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays R3318

and R3321. At the J2802 Box Assembly, install the time delay relays R3327 and R3329.

Do a functional test of the fuel boost pumps to make sure the changed control system operates correctly.

Group 14, 17-18, 21-31:

PART 6 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS

1. Change J2802 Box Assembly for airplanes with Airstairs.

NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given in

the Original Issue of this service bulletin can use the J2802 Box Assembly received in the kit

but they need to change the J2802 Box Assembly for airplanes with airstairs.

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BOEING SERVICE BULLETIN 737-28A1216
Group 1-16, 21-29, 31:

PART 7- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED THE

ORIGINAL ISSUE OF THE SERVICE BULLETIN

1. Install Labels on the J2802 Box Assembly, change wire W1760 termination at switch S3318, change

wire W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire W368-031-20,

and do the Center Fuel Boost Pump Auto Shutoff Functional Test.

NOTE: Only airplanes that were in Group 1 through 16 of the Original Issue of this service bulletin

and incorporated the changes provided in the Original Issue of the service bulletin have to do

the work provided in PART 7.

Group 17-18:

PART 8- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED THE

ORIGINAL ISSUE OF THE SERVICE BULLETIN

1. Install the Labels on the J2802 Box Assembly, change wire W1760 termination at switch S3318, change

wire W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire W368-031-20,

do the Center Fuel Boost Pump Auto Shutoff Functional Test, do the Auxiliary Fuel Boost Pump Auto

Shutoff Functional Test for airplanes with Auxiliary Tank installed.

NOTE: Only airplanes that were in Group 17 and 18 of the Original Issue of this service bulletin and

incorporated the changes provided in the Original Issue of the service bulletin have to do the

work provided in PART 8.

NOTE: Airplanes in Group 17 and 18 have been delivered without Auxiliary Tanks but with wire

provisions for Auxiliary Tank Installation. It was necessary to do the change given in Figure

7 of the Original Issue of the service bulletin only if Auxiliary Tank with Fuel Boost Pumps

were installed on the airplane. If Auxiliary Tank is not installed, it is not necessary to do the

changes of wire W1760 in accordance with Figure 7 of this revision.

Group 19-20, 30:

PART 9- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED THE

ORIGINAL ISSUE OF THE SERVICE BULLETIN

1. Install the Labels on the J2802 Box Assembly, change wire W1760 termination at switch S3318, change

wire W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire W368-031-20,

do the Center Fuel Boost Pump Auto Shutoff Functional Test, do the Auxiliary Fuel Boost Pump Auto

Shutoff Functional Test.

NOTE: Only airplanes that were in Group 19 through 20 of the Original Issue of this service bulletin

and incorporated the changes provided in the Original Issue of the service bulletin have to do

the work provided in PART 9.

Accomplishment of this service bulletin changes the flight deck and/or operations of the airplane. Refer to

Paragraph 1.K., Publications Affected, for affected publications.

EFFECTIVITY

737-300/400/500 airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

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BOEING SERVICE BULLETIN 737-28A1216
COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-189-AD, is related to

this service bulletin.

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.

Boeing recommends that the change given in this service bulletin be done within 24 months after the Revision

3 date of this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 737-28A1216
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BOEING SERVICE BULLETIN 737-28A1216
Commercial

Airplanes 737

Service Bulletin

Number: 737-28A1216

Original Issue: July 29, 2010

Revision 3: July 16, 2014

ATA System: 2822

SUBJECT: FUEL - Engine Fuel Feed System - Installation of the Auto Shutoff Protection for the

Center and Auxiliary Fuel Tank Boost Pumps

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent

production airplanes. Refer to PRR 35442-RS for data about this change.

Refer to Service Bulletin Index Document D6-19567 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary

Tank installation. Operators that installed AUX tanks with Fuel Boost Pumps on these

airplanes need to install an Auto Shutoff system. The FAA may release an AD to require

that all airplanes that have AUX tanks with Fuel Boost Pumps install an Auto Shutoff

system.

GROUP CONFIGURATION DESCRIPTION

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

1 -

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels.

2 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

3 -

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GROUP CONFIGURATION DESCRIPTION

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels.

4 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

5 -

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels.

6 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

7 -

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

8 -

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

9 -

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

10 -

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels.

11 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels.

12 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

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BOEING SERVICE BULLETIN 737-28A1216
GROUP CONFIGURATION DESCRIPTION

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

13 -

Airplanes with Airstairs that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels.

14 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels.

15 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes that do not have the auxiliary fuel tanks and have different

wiring configurations at the P5 and P6 panels, and with or without

SB 737-28A1212 Original Issue or R1 incorporated.

16 -

Airplanes with Airstairs, delivered with wire provision for Auxiliary

Tank installation and have different wiring configurations at the P5

and P6 panels.

17 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes with Airstairs, delivered with wire provision for Auxiliary

Tank installation and have different wiring configurations at the P5

and P6 panels.

18 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes that have the auxiliary fuel tanks and have different wiring

configurations at the P5 and P6 panels.

19 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

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BOEING SERVICE BULLETIN 737-28A1216
GROUP CONFIGURATION DESCRIPTION

Airplanes that have the auxiliary fuel tanks and have different wiring

configurations at the P5 and P6 panels.

20 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels, and

with or without SB 737-28A1212 Original Issue or R1 incorporated.

21 -

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels.

22 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels, and

with or without SB 737-28A1212 Original Issue or R1 incorporated.

23 -

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels, and

with or without SB 737-28A1212 Original Issue or R1 incorporated.

24 -

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels.

25 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels, and

with or without SB 737-28A1212 Original Issue or R1 incorporated.

26 -

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels, and

with or without SB 737-28A1212 Original Issue or R1 incorporated.

27 -

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels.

28 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

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GROUP CONFIGURATION DESCRIPTION

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels.

29 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes with Airstairs, that have the auxiliary fuel tanks and have

different wiring configurations at the P5 and P6 panels.

30 -

1 Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated.

2 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated.

Airplanes with Airstairs, that do not have the auxiliary fuel tanks and

have different wiring configurations at the P5 and P6 panels, and

with or without SB 737-28A1212 Original Issue or R1 incorporated.

31 -

Airplane Models:

737-300, 737-400, 737-500

Variable Number Group

PJ301 - PJ302 1

PJ551 - PJ561 1

PJ601 - PJ615 1

PJ811 19

PJ816 - PJ817 21

PM381 - PM399 22

PM401 - PM417 22

PM541 - PM550 22

PM551 - PM564 23

PP001 - PP054 6

PP101 29

PP102 - PP169 12

PP181 - PP187 6

PP188 - PP199 7

PP201 - PP205 25

PP221 14

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Variable Number Group

PP231 - PP243 6

PP281 - PP286 6

PP301 - PP305 6

PP351 - PP353 25

PP376 - PP384 25

PP391 - PP393 25

PP401 - PP440 6

PP471 - PP475 20

PP501 - PP520 18

PP521 - PP522 25

PP631 - PP634 6

PP651 - PP652 25

PP671 - PP689 6

PP690 - PP694 20

PP695 - PP699 6

PP701 - PP706 6

PP707 - PP716 20

PP717 - PP733 6

PP771 - PP779 6

PP801 - PP808 25

PP821 - PP827 25

PP831 - PP848 22

PP851 - PP852 28

PP861 - PP877 11

PP891 - PP899 28

PP901 - PP936 28

PP946 - PP948 28

PP951 - PP952 28

PP961 - PP965 11

PP966 - PP967 3

PP981 - PP982 11

PP983 - PP990 3

PP991 11

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BOEING SERVICE BULLETIN 737-28A1216
Variable Number Group

PP993 23

PQ001 - PQ016 11

PQ026 - PQ041 11

PQ051 - PQ092 11

PQ101 - PQ199 11

PQ201 - PQ202 11

PQ221 - PQ230 23

PQ231 - PQ232 11

PQ233 - PQ237 10

PQ241 - PQ242 28

PQ243 27

PQ251 - PQ267 27

PQ281 - PQ291 27

PQ292 - PQ297 10

PQ298 27

PQ299 10

PQ301 - PQ307 10

PQ331 - PQ332 10

PQ341 - PQ348 10

PQ361 - PQ373 27

PQ391 - PQ395 27

PQ401 - PQ418 27

PQ421 27

PQ431 - PQ438 10

PQ447 - PQ448 27

PQ451 10

PQ454 10

PQ471 10

PQ472 - PQ475 27

PQ479 - PQ481 10

PQ486 - PQ487 10

PQ491 - PQ493 10

PQ771 - PQ772 10

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BOEING SERVICE BULLETIN 737-28A1216
Variable Number Group

PQ791 - PQ793 10

PQ801 - PQ805 16

PQ931 - PQ935 16

PQ951 27

PQ971 - PQ997 27

PR001 - PR017 23

PR021 - PR030 23

PR031 - PR034 3

PR041 - PR045 3

PR061 - PR072 3

PR077 - PR080 3

PR081 - PR082 23

PR091 - PR092 23

PR096 23

PR101 23

PR121 - PR122 23

PR131 - PR132 23

PR141 - PR143 23

PR161 - PR172 23

PR181 16

PS601 - PS631 22

PS636 - PS638 22

PS641 - PS642 22

PS643 - PS644 2

PS651 - PS657 23

PS666 - PS669 10

PS691 - PS692 3

PS701 - PS706 11

PS751 - PS799 12

PS811 23

PS836 - PS837 23

PS841 - PS846 22

PS851 - PS852 22

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BOEING SERVICE BULLETIN 737-28A1216
Variable Number Group

PS856 22

PS861 - PS863 17

PS866 - PS868 17

PS871 - PS874 22

PS896 - PS897 22

PS901 - PS941 15

PS956 - PS957 17

PS961 - PS963 23

PS971 - PS978 23

PT001 - PT015 3

PT021 - PT031 3

PT041 - PT064 23

PT101 - PT105 3

PT121 - PT138 23

PT146 - PT148 23

PT161 - PT170 23

PT181 - PT185 31

PT186 - PT188 9

PT211 - PT220 23

PT295 23

PT301 - PT309 3

PT331 - PT360 10

PT381 - PT399 3

PT401 - PT438 3

PT501 - PT517 27

PT561 - PT565 3

PT581 - PT586 3

PT611 - PT621 10

PT641 - PT644 3

PT651 - PT656 3

PT671 - PT672 27

PT681 - PT685 3

PT701 - PT703 13

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Variable Number Group

PT716 - PT717 3

PT721 - PT725 23

PT801 - PT834 10

PT851 - PT854 3

PT871 - PT886 23

PT901 - PT930 10

PT971 - PT973 10

PT981 - PT985 3

PT996 23

PU001 - PU025 10

PU301 23

PU311 - PU313 23

PV001 4

PV002 - PV055 5

PV201 - PV209 1

PV226 - PV229 1

PV231 - PV237 8

PV271 - PV272 1

PV281 - PV287 1

PV296 21

PV301 - PV302 21

PV351 1

PV356 - PV357 31

PW001 - PW054 21

PW061 21

PW062 - PW068 1

PW072 21

PW086 - PW088 21

PW091 - PW094 21

PW101 - PW102 21

PW106 21

PW111 - PW120 21

PW156 - PW157 21

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BOEING SERVICE BULLETIN 737-28A1216
Variable Number Group

PW161 - PW171 21

PW201 - PW252 1

PW261 - PW268 21

PW271 - PW276 21

PW278 21

PW281 - PW293 21

PW296 21

PW301 - PW327 26

PW401 - PW408 1

PW411 - PW418 1

PW421 - PW424 1

PW431 - PW435 1

PW441 - PW450 8

PW461 - PW467 1

PW501 - PW504 21

PW511 - PW522 19

PW524 19

PW525 - PW529 1

PW530 19

PW531 - PW550 5

PW556 - PW557 24

PW561 - PW564 1

PW571 - PW576 1

PW591 - PW596 21

PW611 - PW622 5

PW631 - PW637 5

PW661 - PW662 24

PW681 - PW683 5

PW701 - PW702 30

PW711 - PW717 1

PW741 - PW742 24

PW761 5

PW771 1

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BOEING SERVICE BULLETIN 737-28A1216
Variable Number Group

PW831 31

PW851 - PW856 31

2. Spares Affected

None.

B. Concurrent Requirements

The service bulletin(s) listed below must be done before or at the same time as this service bulletin:

Company Service Bulletin Description

Gives instruction to install a new printed

circuit assembly in the P5-2 fuel system

module assembly to supply Low fuel pressure master caution Annunciation.

BAE Systems SB 69-37335-28-04, Revision

3

BAE

Gives instruction to replace the P5-2 fuel

system module assembly to supply Low fuel

pressure master caution Annunciation.

737-28A1210, Original Issue, Revision 1 or

Revision 2

Boeing

C. Reason

This service bulletin is the result of the safety analysis done by Boeing under SFAR 88, "Fuel Tank

System Fault Tolerance Evaluation Requirements." Initial results from the fuel system safety analysis

shows that fuel boost pumps that run dry could cause an overheat condition external of the fuel pump

explosion resistance area that is open to the fuel pump inlet. An overheat condition in this area could

possibly cause an unwanted ignition source for the fuel vapors in the fuel tank and could cause a fire

or explosion.

This service bulletin gives the instructions and a kit of parts to install an automatic (auto) shut-off system

for the fuel boost pumps. The fuel boost pumps are installed in the center fuel tank and if equipped,

also in the auxiliary fuel tank. Time delay relays are installed in the new J2802 Box Assembly that will

shut off the fuel boost pumps if the pumps operate with continuous low pressure for 15 seconds. The

15 second time delay relay prevents extended dry operation of the fuel boost pumps and allows for

sufficient time for fuel pump inlet reprime to prevent nuisance automatic shutoffs. The flight crew stays

in primary control, with the auto shut off system as a backup, to stop the fuel boost pumps after a low

pressure indication.

The change installs an automatic shut off system that gives fuel boost pump inlet protection in the fuel

tank against sparks possibly caused by friction overheat damage.

This change affects the Fuel Systems Airworthiness Limitations section of Boeing document

"737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification Maintenance

Requirements (CMRs), D6-38278-CMR." New AWL "28-AWL-20" will be added to include an operational

check of the boost pump automatic shutoff system for the center fuel tank. AWL "28-AWL-21" will be

added to include an operational check of the fuel boost pump automatic shutoff system for the auxiliary

fuel tank, if installed by Boeing. This change also affects Section 1 and Section 3 of the FAA Approved

Airplane Flight Manual (AFM).

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BOEING SERVICE BULLETIN 737-28A1216
Other related airplane service bulletins are Service Bulletin 737-28A1228 for the 737-100/200 airplanes

and Service Bulletin 737-28A1206 for the 737-600/700/800/900 airplanes.

Revision 1:

This revision is sent to tell the operators that for airplanes with Airstairs the J2802 Box Assembly

provided in the Original Issue can not be installed in the main equipment compartment on the E2 and

E3 support posts in accordance with Figure 12 or Figure 13. When J2802 Box Assembly is installed

in accordance with Figure 12 or 13, the forward face of the box interferes with the Airstairs and the

Airstairs support structure. Also there is no good access to the Airstairs relays, and to the wires

connected to the Airstairs relays. A new J2802 Box Assembly was designed and added to this revision

that can be installed on airplanes with Airstairs with no interference with Airstairs and the Airstairs

support structure. The airplanes with Airstairs were moved from the existing groups into new groups

based on the wires configuration and Auxiliary Tank installation. Figures 92 through 107 were added

for airplanes with Airstairs.

This revision is also sent to tell the Operators that the switches S03318 and S03321 installed on J2802

Box Assembly have two positions (for each switch) identified as "POS 1" and "POS 2". POS 1 of the

test switch S03318 is for Left Fuel Boost Pump of the Center Tank. POS 1 of the test switch S03321

is for Right Fuel Boost Pump of the Center Tank. POS 2 of the test switches S03318 and S03321 are

only used for airplanes with Auxiliary Tanks. POS 2 of the test switch S03318 is for Aft Fuel Boost

Pump of the Auxiliary Tank. POS 2 of the test switch S03321 is for Fwd Fuel Boost Pump of the Auxiliary

Tank. The wires terminated at switches S03318 and S03321 were incorrectly terminated in Figures 4,

5, 7, 8, 9, 10. The wire terminations at switches S03318 and S03321 are changed in order for the

switches to function as indicated.

New steps are added to Figure 3 that instruct the operators to install markers on the J2802 Box Assembly

that will identify S03318 and S003321 as "TEST SWITCHES". Also instructions are added to install

markers that will identify the function of the switch S03318 POS 1 as "CTR-L", and the function of the

switch S03321 POS 1 as "CTR-R".

New steps are added to Figure 6 that instruct the operators to install markers on the J2802 Box Assembly

that will identify S03318 and S003321 as "TEST SWITCHES". Also instructions are added to install

markers that will identify the functions of the switch S03318 as follows: POS 1 as "CTR-L", and POS

2 as "AUX-AFT". Also instructions are added to install markers that will identify the functions of the

switch S03321 as follows: POS 1 as "CTR-R", and POS 2 as "AUX-FWD".

Also this revision moves airplanes with airstairs from existing groups in new groups, Group 21 through

31. All airplanes in Groups 14, 17, and 18 have airstairs.

Some wires W368-031-20 delivered in the kits have been identified incorrectly. The wire I.D Tapes

Part Number 61-74478-10906 installed on both ends of the wire W368-031-20 may be imprinted

incorrectly as "W036-031-20". Instructions are added to Figure 83 and Figure 84 to check the imprinted

text on the wire I.D Tapes before installation and correct the text from "W036-031-20" to "W0368-031-20".

The data given in Information Notice 737-28A1216 IN 01, 737-28A1216 IN 02, and 737-28A1216 IN

03 are included in this revision.

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BOEING SERVICE BULLETIN 737-28A1216
Revision 2:

This revision is sent to tell the operators that Figures 8, 10, 84, 87, 94, 95, 98, 99, 100, 101, 102, 103

have been revised to incorporate minor typographical changes. This revision also changes the Weight

and Moments table based on airplanes with and without AUX Tank. Also the Electrical Load Data tables

are identified with titles, and missing airplane groups are added to the applicability. This revision also

changes supplemental kit 65C37854-16 for manufacturing purpose. The quantity of the labels in the

kit drawing 65C38484-30 is changed from 2 to 1 and, the quantity of the 65C38484-30 is changed from

1 to 2 in the supplemental kit 65C37854-16. Also PART 7, PART 8, and PART 9 are added to Summary,

Action paragraph, and to Planning, Description paragraph.

Revision 3:

This revision is sent to tell the operators that airplanes fitted with Airstairs will have improved instructions

for the installation of the J2802 Box Assembly. Operators have identified that within the main electronics

compartment, the current installation procedure of the J2802 Box Assembly can cause it to touch the

adjacent Moisture Shroud structure which can be mounted in different locations. Therefore, additional

and updated Figures and Work Instructions are required to prevent this, and let the operator complete

this service bulletin. This revision also changes the routing of cable bundles, W0368 and W1764, to

the P5 overhead panel, Connector D4202, to help installation of Splice, SP4510. New top kits are

introduced to replace existing top kits that are applicable to airplanes fitted with Airstairs. A new

Supplemental Kit is also introduced for operators who have previously ordered existing top kits but are

yet to accomplish this service bulletin.

Also this revision corrects typographical errors in the Kit/Parts tables, Work Instructions, Figures and

Step/Flag Tables.

The data given in Information Notice 737-28A1216 IN 04 is included in this revision.

D. Description

The work instructions are divided into 31 airplane groups and 9 parts.

PART 1, PART 2, PART 3, PART 4, and PART 5 work instructions are divided into 3 work packages

because of the different wire bundle changes and airplanes without and with Airstairs.

PART 6 work instructions are for Operators that already ordered the kit from the Original Issue, and

want to re-work the kit for airplanes with Airstairs.

PART 7, PART 8, PART 9 provide instructions to change the J2802 Box Assembly for airplanes that

incorporated the Original Issue of the service bulletin.

NOTE: When submitting a Publication Change Request (PCR) to Boeing to incorporate this service

bulletin in the affected manuals, please notify Boeing if Auxiliary Tanks are installed on these

airplanes. If Boeing is not notified about the Auxiliary Tanks, Boeing will assume that the

airplanes in these groups do not have Auxiliary (AUX) tanks and no AUX Tank changes to

the affected manuals will be done.

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BOEING SERVICE BULLETIN 737-28A1216
Group 1-13, 15-16:

PART 1 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL

TANKS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts,

install the J2802 Box Assembly.

3. Work Package 3:

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802

Box Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays

R3318 and R3321.

Do a functional test of the fuel boost pumps to make sure the changed control system operates

correctly.

Group 17-18:

PART 2 - AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX)

FUEL TANKS, AND AIRSTAIRS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

NOTE: For Operators that ordered and received the kit at the Original Issue of this service bulletin

but have not accomplished the service bulletin, it will be necessary to change J2802 Box

Assembly supplied in the kit in accordance with PART 6, before its installation.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts,

install the J2802 Box Assembly.

3. Work Package 3:

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary

Tank installation. Operators that installed AUX tanks with Fuel Boost Pumps on these

airplanes need to install an Auto Shutoff system. The FAA may release an AD to require

that all airplanes that have AUX tanks with Fuel Boost Pumps install an Auto Shutoff

system.

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44. For the airplanes that have an auxiliary fuel tank, between the P6 disconnect panel

and the fuel boost pump relays R146 and R147, make a change to the wire bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802

box assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays

R3318 and R3321. For the airplanes that have auxiliary fuel tank, at the J2802 Box Assembly,

install the time delay relays R3327 and R3329.

Do a functional test of the fuel boost pumps to make sure the changed control system operates

correctly.

Group 19-20:

PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts,

install the J2802 Box Assembly.

3. Work Package 3:

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147,

make a change to the wire bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802

Box Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays

R3318 and R3321. At the J2802 Box Assembly, install the time delay relays R3327 and R3329.

Do a functional test of the fuel boost pumps to make sure the changed control system operates

correctly.

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BOEING SERVICE BULLETIN 737-28A1216
Group 14, 21-29, 31:

PART 4 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL

TANKS, AND AIRSTAIRS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

NOTE: For Operators that ordered and received the kit at the Original Issue of this service bulletin

but have not accomplished the service bulletin, it will be necessary to change J2802 Box

Assembly supplied in the kit in accordance with PART 6, before its installation.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts,

install the J2802 Box Assembly.

3. Work Package 3:

In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802

box assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays

R3318 and R3321.

Do a functional test of the fuel boost pumps to make sure the changed control system operates

correctly.

Group 30:

PART 5 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS

1. Work Package 1:

In the J2802 Box Assembly, install the wire bundles W1760 and W1770.

NOTE: For Operators that ordered and received the kit at the Original Issue of this service bulletin

but have not accomplished the service bulletin, it will be necessary to change J2802 Box

Assembly supplied in the kit in accordance with PART 6, before its installation.

2. Work Package 2:

Get access into the main electronics compartment. Between the E2 and E3 rack support posts,

install the J2802 Box Assembly.

3. Work Package 3:

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BOEING SERVICE BULLETIN 737-28A1216
In the flight compartment, get access to the P5 overhead panel, P6 relay panel or P6 relay modules.

Above the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between

the P6 disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire

bundle W44. Between the P6 disconnect panel and the fuel boost pump relays R146 and R147,

make a change to the wire bundle W44.

In the flight and main electronics compartments, between the P6 disconnect panel and the J2802

Box Assembly, install the new wire bundles W1764 and W1774.

In the main electronics compartment, at the J2802 Box Assembly, install the time delay relays

R3318 and R3321. At the J2802 Box Assembly, install the time delay relays R3327 and R3329.

Do a functional test of the fuel boost pumps to make sure the changed control system operates

correctly.

Group 14, 17-18, 21-31:

PART 6 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS

1. Change J2802 Box Assembly for airplanes with Airstairs.

NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given

in the Original Issue of this service bulletin can use the J2802 Box Assembly received in

the kit but they need to change the J2802 Box for airplanes with airstairs.

Group 1-16, 21-29, 31:

PART 7- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED

THE ORIGINAL ISSUE OF THE SERVICE BULLETIN

1. Install Labels on the J2802 Box Assembly, change wire W1760 termination at switch S3318,

change wire W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire

W368-031-20, and Do the Center Fuel Boost Pump Auto Shutoff Functional Test.

NOTE: Only airplanes that were in Group 1 through 16 of the Original Issue of this service bulletin

and incorporated the changes provided in the Original Issue of the service bulletin have

to do the work provided in PART 7.

Group 17-18:

PART 8- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED

THE ORIGINAL ISSUE OF THE SERVICE BULLETIN

1. Install the Labels on the J2802 Box Assembly, change wire W1760 termination at switch S3318,

change wire W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire

W368-031-20, do the Center Fuel Boost Pump Auto Shutoff Functional Test, do the Auxiliary Fuel

Boost Pump Auto Shutoff Functional Test for airplanes with Auxiliary Tank installed..

NOTE: Only airplanes that were in Group 17 and 18 of the Original Issue of this service bulletin

and incorporated the changes provided in the Original Issue of the service bulletin have

to do the work provided in PART 8.

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Airplanes in Group 17 and 18 have been delivered without Auxiliary Tanks but with wire

provisions for Auxiliary Tank Installation. It was necessary to do the change given in

Figure 7 of the Original Issue of the service bulletin only if Auxiliary Tank with Fuel Boost

Pumps were installed on the airplane. If Auxiliary Tank is not installed, it is not necessary

to do the changes of wire W1760 in accordance with Figure 7 of this revision.

Group 19-20, 30:

PART 9- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED

THE ORIGINAL ISSUE OF THE SERVICE BULLETIN

1. Install the Labels on the J2802 Box Assembly, change wire W1760 termination at switch S3318,

change wire W1770 termination at switch S3321, inspect the imprinted text on the ID tape of wire

W368-031-20, do the Center Fuel Boost Pump Auto Shutoff Functional Test, do the Auxiliary Fuel

Boost Pump Auto Shutoff Functional Test.

NOTE: Only airplanes that were in Group 19 through 20 of the Original Issue of this service

bulletin and incorporated the changes provided in the Original Issue of the service bulletin

have to do the work provided in PART 9.

Revision 1: More work was necessary on the airplane(s) changed in accordance with the original issue

of this service bulletin. Operators that incorporated the original issue of this SB, have to change the

labels and wire termination in the J2802 Box Assembly in accordance with Figures 3, 4, 5, 6, 7,8, 9,

or 10 as applicable, and do a functional test within the compliance time specified in Paragraph 1.E.,

Compliance. Also, operators have to inspect the imprinted text on the ID tape of wire W368-031-20

installed in accordance with Figures 82 and 83 or Figures 82 and 84 within the compliance time specified

in Paragraph 1.E., Compliance. Some wires W368-031-20 delivered in the kits have been identified

incorrectly as"W036-031-20". If they are imprinted as "W036-031-20", then correct that text of the I.D.

tapes to"W0368-031-20" using a permanent marker.

Revision 2: No more work was necessary on the airplane(s) Groups 1-16, 19-31 changed in accordance

with Revision1 of this service bulletin. More work is necessary for airplanes in Groups 17-18, that were

changed in accordance with Part 7 of Revision 1 of this service bulletin. These airplanes need to do

also the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test in accordance with PART 8 if the

Auxiliary Tank is installed.

Revision 3: No more work is necessary on the airplane(s) changed in accordance with Revision 2 of

this service bulletin. But, more work is necessary for airplanes in Groups 17-18 that changed the

airplanes in accordance with Part 7 of Revision 1 of this service bulletin. These airplanes also need to

do the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test in accordance with PART 8 if the

Auxiliary Tank is installed.

Accomplishment of this service bulletin changes the flight deck and/or operations of the airplane. Refer

to Paragraph 1.K., Publications Affected, for affected publications.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1, 4-5, 8, 19, 21, 24, 26, 30:

Affected Maintenance Zones

Model Zone

737-400 102, 205

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BOEING SERVICE BULLETIN 737-28A1216
Group 2, 6-7, 11-12, 14-18, 20, 22, 25, 28-29:

Affected Maintenance Zones

Model Zone

737-300 102, 205

Group 3, 10:

Affected Maintenance Zones

Model Zone

737-300, 737-500 102, 205

Group 9, 13, 31:

Affected Maintenance Zones

Model Zone

737-500 102, 205

Group 23:

Affected Maintenance Zones

Model Zone

737-300, 737-400, 737-500 102, 205

Group 27:

Affected Maintenance Zones

Model Zone

737-300 102, 105, 205

Group 27:

Affected Maintenance Zones

Model Zone

737-500 105, 205

Group 31:

Affected Maintenance Zones

Model Zone

737-400 105, 205

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BOEING SERVICE BULLETIN 737-28A1216
E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2010-NM-189-AD, is

related to this service bulletin.

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.

Boeing recommends that the change given in this service bulletin be done within 24 months after the

Revision 3 date of this service bulletin.

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.

This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft

Certification Office approves the installation of the automatic shutoff system for the center tank fuel

pumps in accordance with this service bulletin and the installation of a modified P5-2 Fuel System

Module in accordance with Service Bulletin 737-28A1210, Revision 2, as an alternative method of

compliance (AMOC) to the requirements of paragraph (a) of AD 2001-08-24. Compliance with the

conditions of this AMOC approval requires concurrent incorporation of the associated revisions to

Airplane Flight Manual Sections 1 and 3 and incorporation of Airworthiness Limitations (AWL) 28-AWL-20

in Boeing document "737-100/200/200C/300/400/500 Airworthiness Limitations (AWLs) and Certification

Maintenance Requirements (CMRs), D6-38278-CMR," into the operator's maintenance documentation.

In order to operate a mixed fleet of airplanes, some having automatic shutoff installed and others without

automatic shutoff, it will be necessary to install a placard in the flight deck of airplanes that do not have

automatic shutoff installed to alert the crew that the procedures required by paragraph(a) of AD

2001-08-24 must be followed on that airplane. The placard should read as follows (alternative placard

wording may be used if approved by an appropriate FAA Principal Operations Inspector):

"AD 2001-08-24 fuel usage restrictions required"

If an operator would like to use a different method of placarding their airplanes for operation as a mixed

fleet, a request for approval of an AMOC should be submitted to the Seattle Aircraft Certification Office.

All provisions of AD 2001-08-24 that are not specifically referenced in the above statement remain fully

applicable and must be complied with.

G. Manpower

The table below shows an estimate of the task-hours necessary to do this change 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:

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BOEING SERVICE BULLETIN 737-28A1216
— Time to adjust to the workplace

— Time to schedule the work

— Time to inspect the work

— Time to cure the materials

— Time to find the tools.

Group 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 21 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 45 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

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BOEING SERVICE BULLETIN 737-28A1216
Group 2, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 46 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 2, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

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BOEING SERVICE BULLETIN 737-28A1216
Group 2, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 47 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 3:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

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BOEING SERVICE BULLETIN 737-28A1216
Group 3:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 48 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 4, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216
Group 4, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 49 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 4, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 50 1 3.80 3.80

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BOEING SERVICE BULLETIN 737-28A1216
Group 4, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 5:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216
Group 5:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 6, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 52 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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BOEING SERVICE BULLETIN 737-28A1216
Group 6, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 6, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 53 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

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Group 7:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 59 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 8:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

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BOEING SERVICE BULLETIN 737-28A1216
Group 8:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 25 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 85 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 9:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

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BOEING SERVICE BULLETIN 737-28A1216
Group 9:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 26 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 54 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 10:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

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Group 10:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 55 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 11, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 62 1 3.80 3.80

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BOEING SERVICE BULLETIN 737-28A1216
Group 11, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 11, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 63 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216
Group 11, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 12, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 56 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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BOEING SERVICE BULLETIN 737-28A1216
Group 12, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 12, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 57 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

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BOEING SERVICE BULLETIN 737-28A1216
Group 13:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 29 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 58 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 14, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216
Group 14, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 20 (a) 2 - -

FIGURE 30 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 60 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

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BOEING SERVICE BULLETIN 737-28A1216
Group 14, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 30 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 61 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

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BOEING SERVICE BULLETIN 737-28A1216
Group 14, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 15, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 31 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 64 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

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BOEING SERVICE BULLETIN 737-28A1216
Group 15, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 31 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 65 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 16:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

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BOEING SERVICE BULLETIN 737-28A1216
Group 16:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 32 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 48 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 85 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 17, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 38 2 5.50 2.75

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BOEING SERVICE BULLETIN 737-28A1216
Group 17, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 39 (b) 2 4.60 2.30

FIGURE 40 (b) 2 4.60 2.30

FIGURE 66 (a) 2 - -

FIGURE 67 1 3.80 3.80

FIGURE 69 (b) 2 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.60

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (g) 1 0.75 0.75

FIGURE 111 (h) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2.00 1.00

TOTAL FOR EACH AIRPLANE 130.75 72.40

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the

total "Task-Hours" and total "Elapsed Hours" time.

(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

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BOEING SERVICE BULLETIN 737-28A1216
Group 17, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(e) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(f) See related wire connection figure for wire routing task hours.

(g) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(h) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 17, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 38 2 5.50 2.75

FIGURE 39 (b) 2 4.60 2.30

FIGURE 40 (b) 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 68 1 3.80 3.80

FIGURE 70 (b) 1 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

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BOEING SERVICE BULLETIN 737-28A1216
Group 17, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.75

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (g) 1 0.75 0.75

FIGURE 111 (h) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 130.75 72.40

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the

total "Task-Hours" and total "Elapsed Hours" time.

(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

(e) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(f) See related wire connection figure for wire routing task hours.

(g) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(h) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 18, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

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BOEING SERVICE BULLETIN 737-28A1216
Group 18, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 (b) 2 4.60 2.30

FIGURE 43 (b) 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 71 1 3.80 3.80

FIGURE 73 (b) 1 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.75

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (g) 1 0.75 0.75

FIGURE 111 (h) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 130.75 72.40

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the

total "Task-Hours" and total "Elapsed Hours" time.

(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

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BOEING SERVICE BULLETIN 737-28A1216
Group 18, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

(e) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(f) See related wire connection figure for wire routing task hours.

(g) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(h) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 18, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 (b) 2 4.60 2.30

FIGURE 43 (b) 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 72 1 3.80 3.80

FIGURE 74 (b) 1 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

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BOEING SERVICE BULLETIN 737-28A1216
Group 18, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.75

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (g) 1 0.75 0.75

FIGURE 111 (h) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 130.75 72.40

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) This figure is only applicable if Auxiliary Tank is installed. They are not counted in the

total "Task-Hours" and total "Elapsed Hours" time.

(c) It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

(d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 given

in this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

(e) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(f) See related wire connection figure for wire routing task hours.

(g) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(h) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 19, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 2 1 0.15 0.15

FIGURE 6 (a) 2 - -

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BOEING SERVICE BULLETIN 737-28A1216
Group 19, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 76 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 19, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 2 1 0.15 0.15

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BOEING SERVICE BULLETIN 737-28A1216
Group 19, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 6 (a) 2 - -

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 77 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Group 20, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Group 20, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 2 1 0.15 0.15

FIGURE 6 (a) 2 - -

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 2 4.60 2.30

FIGURE 43 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 78 1 3.80 3.80

FIGURE 80 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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BOEING SERVICE BULLETIN 737-28A1216
Group 20, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 2 1 0.15 0.15

FIGURE 6 (a) 2 - -

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 2 4.60 2.30

FIGURE 43 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 79 1 3.80 3.80

FIGURE 81 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Group 21:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 21 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 45 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216
Group 21:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 22, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 46 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: July 29, 2010

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72 of 490

BOEING SERVICE BULLETIN 737-28A1216
Group 22, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 22, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 47 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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BOEING SERVICE BULLETIN 737-28A1216
Group 22, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 23:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 48 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

Export Controlled ECCN: 9E991 - BOEING

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Revision 3: July 16, 2014 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216
Group 23:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 24:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Group 24:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 25, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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BOEING SERVICE BULLETIN 737-28A1216
Group 25, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) - - -

FIGURE 52 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) - - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

77 of 490

BOEING SERVICE BULLETIN 737-28A1216
Group 25, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 25, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) - - -

FIGURE 53 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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BOEING SERVICE BULLETIN 737-28A1216
Group 25, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 26:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 25 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 85 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

79 of 490

BOEING SERVICE BULLETIN 737-28A1216
Group 26:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 27:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 55 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216
Group 27:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 28, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 62 1 3.80 3.80

FIGURE 83 2 16.40 8.20

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

81 of 490

BOEING SERVICE BULLETIN 737-28A1216
Group 28, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 28, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

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Group 28, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 63 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

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BOEING SERVICE BULLETIN 737-28A1216
Group 29, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 56 1 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.40 52.65

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Group 29, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 29, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 57 1 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

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BOEING SERVICE BULLETIN 737-28A1216
Group 29, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

TOTAL FOR EACH AIRPLANE 95.40 52.65

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 30, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 76 1 3.80 3.80

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (b) 1 3.00 3.00

FIGURE 95 (b) 1 2.80 2.80

FIGURE 97 (c) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

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BOEING SERVICE BULLETIN 737-28A1216
Group 30, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 107 1 0.75 0.75

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 133.75 75.4

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Group 30, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

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BOEING SERVICE BULLETIN 737-28A1216
Group 30, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 77 1 3.80 3.80

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (b) 1 3.00 3.00

FIGURE 95 (b) 1 2.80 2.80

FIGURE 97 (c) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 107 1 0.75 0.75

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 130.75 72.40

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Group 31:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 26 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 54 1 3.80 3.80

FIGURE 83 1 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

FIGURE 108 1 0.10 0.10

FIGURE 109 1 0.10 0.10

FIGURE 110 (d) 1 0.75 0.75

FIGURE 111 (e) 1 3.00 3.00

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 99.20 56.45

(a) This figure shows wire routes only. See the related wire connection figure for task hours.

(b) The task hours for this figure to be used only if operators ordered and received the Top

Kits given in the Original Issue of this service bulletin and they need to change the J2802

Box Assembly.

(c) See related wire connection figure for wire routing task hours.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Group 31:

Number of Per- Task-Hours Elapsed Hours

sons

Task

(d) The task hours for this figure to be used only if the operator must change the E2 Support

Post.

(e) The task hours for this figure to be used only if the operator must change the Moisture

Shroud Angle and Strap on the E3 Support Post.

H. Weight and Balance Changes

Group 1-18, 21-29, 31:

AIRPLANES WITH NO AUX TANK

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

Each 737-300 (a) +6.0 +1,300

Each 737-400 +6.0 +900

Each 737-500 +6.0 +1,650

(a) For Groups 17 and 18 that did not install an AUX TANK use

the weights and moments given in this table.

Group 17-20, 30:

AIRPLANES WITH AUX TANK

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

Each 737-300 (a) +10.0 +2,200

Each 737-400 +10.0 +1,500

Each 737-500 +10.0 +2,750

(a) For Groups 17 and 18 that installed an AUX TANK use the

weights and moments given in this table.

I. Electrical Load Data

1. Direct Current (DC) Load Changes

Group 1-16, 21-29, 31:

AIRPLANES WITH NO AUX TANK

Circuit Nomenclature Bus Action Load Data Duty Cycle AMPS

Breaker

+150 Milliampere

Intermittent

ON/OFF

Connected 100%

Cruise,Hold and

Land

28V DC Add

Bus 1

C3318 Fuel Cont Auto Shut Off CTR-L

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BOEING SERVICE BULLETIN 737-28A1216
Group 1-16, 21-29, 31:

AIRPLANES WITH NO AUX TANK

Circuit Nomenclature Bus Action Load Data Duty Cycle AMPS

Breaker

+150 MilliampereIntermittent

ON/OFF

Connected 100%

Cruise,Hold and

Land

28V DC Add

Bus 2

C3320 Fuel Cont Auto Shut Off CTR-R

Group 17-20, 30:

AIRPLANES WITH AUX TANK

Circuit Nomenclature Bus Action Load Data Duty Cycle AMPS

Breaker

+150 MilliampereIntermittent

ON/OFF

Connected

100%

Cruise,Hold and

Land

28V DC Add

Bus 1

C3318 Fuel Cont Auto Shut Off CTR-L

+150 MilliampereIntermittent

ON/OFF

Connected

100%

Cruise,Hold and

Land

28V DC Add

Bus 2

C3320 Fuel Cont Auto Shut Off CTR-R

+150 MilliampereIntermittent

ON/OFF

Connected

100%

Cruise,Hold and

Land

28V DC Add

Bus 1

C3327 Fuel Cont Auto Shut Off AUX AFT

+150 MilliampereIntermittent

ON/OFF

Connected

100%

Cruise,Hold and

Land

28V DC Add

Bus 2

C3329 Fuel Cont Auto Shut Off AUX FWD

2. Alternating Current (AC) Load Changes

None.

3. Type

Intermittent.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 35442-RS

b. Boeing Service Bulletin 737-28A1206, 737-28A1210, 737-28A1228

c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2001-08-24

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BOEING SERVICE BULLETIN 737-28A1216
d. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM)

2010-NM-189-AD

e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-43-03, 20-44-01,

20-50-01, 20-50-09, 20-50-10, 20-50-12, 20-50-19

f. Standard Wiring Practices Manual (SWPM) 20-00-08, 20-10-04, 20-10-04, 20-10-11, 20-10-11,

20-10-12, 20-10-12, 20-10-14, 20-10-18, 20-10-19, 20-10-19, 20-20-00, 20-20-00, 20-20-10,

20-20-11, 20-30-00, 20-30-11, 20-30-12, 20-60-00, 20-60-08, 20-61-11, 20-81-11, 20-81-17,

20-81-19, 20-81-22, 20-90-11

g. 737-300/400/500 Aircraft Maintenance Manual (AMM) 12-31-11, 24-22-00, 24-31-11, 25-10-00,

25-11-21, 25-31-11, 25-51-01, 28-22-00, 32-00-01, 52-48-41, 52-61-00, 52-61-10

h. 737-300/400/500 Wiring Diagram Manual (WDM) 28-23-01, 28-23-02, 28-43-01

i. 737-300 Structural Repair Manual (SRM) 51-40-02, 51-40-05, 51-40-06

j. 737-400 Structural Repair Manual (SRM) 51-40-02, 51-40-05, 51-40-06

k. 737-500 Structural Repair Manual (SRM) 51-40-02, 51-40-05, 51-40-06

l. BAE Systems Service Bulletin 69-37335-28-04

2. Data Supplied with this Service Bulletin:

None.

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BOEING SERVICE BULLETIN 737-28A1216
3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

61-74478 Kit- Wire Installation, Auto Shut Off System

65-48315 Wire Bundle Installation- Flight Compartment

65-48322 Wire Bundle Installation- Flight Compartment

65-48325 Wire Bundle Installation- Flight Compartment

65-49731 Disconnect Panel Installation- Flight Compartment

65-63811 Support Post Installation- E2 and E3 Rack

65-78950 Moisture Shroud Instl - Elec/Elex Racks (E2 and E3)

65C38471 Top Kit- Fuel Boost Pump, Auto Shut Off System, Center Fuel Tank

65C38484 Kit- J2802 Box Installation, Auto Shut Off System,

Wire Bundle attach Point Loc. - Electronics Equipment Bay, Section

51 and 53

65-49791

69-71787 Switch Instl - Test, L.E. Warning

These drawings were 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

Publication Chapter-Section

737 Airplane Flight Manual Section 1 and Section 3.1

737 Operations Manual 12 and NP

737 Maintenance Manual 28-22

737 Wiring Diagram Manual 28-23, 28-43, Equipment List

737 System Schematic Manual 28-23, 28-43

737 Illustrated Parts Catalog 28-22

737 Dispatch Deviation Guide 28

737 Minimum Equipment List 28

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 does not affect FCS, therefore DTIs are not necessary.

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BOEING SERVICE BULLETIN 737-28A1216
L. Interchangeability and Intermixability of Parts

None.

M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 737-28A1216
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits 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 kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days.

NOTE: Operators are advised to check the Group Configuration tables given in Paragraph 1.A.,

Effectivity and APPENDIX A before ordering kits.

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 1-13, 15-16:

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 Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost 05/05/10 200 539 $9,869.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-7 (a)

(c) 05/12/10 100

05/19/10 13

08/16/12 50

08/30/12 50

09/14/12 50

09/28/12 50

Supplemental Kit - New 07/17/12 105 139 $239.00

Labels For J2802 Relay

Box

65C37854-16 (b)

(c)

(a) Operators that have already received Top Kit 65C38471-7, but have not accomplished this service bulletin,

Supplemental Kit 65C37854-16 is also necessary, to change the J2802 Box Assembly.

(b) This Supplemental Kit is necessary for operators that have received Top Kit 65C38471-7.

(c) Top Kit 65C38471-7 and Supplemental Kit 65C37854-16 are both necessary for operators to accomplish

this service bulletin.

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given in

the Original Issue of this service bulletin can use the J2802 Box Assembly received in the kit

but they need to change the J2802 Box for airplanes with airstairs. Refer to Paragraph 1.A.,

Effectivity and APPENDIX A before ordering kits.

Group 17-18:

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 Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost 05/05/10 10 539 $10,719.00

Pump Auto Shut Off System, Center and Auxiliary

Fuel Tanks

65C38471-8 (a)

(b)

Top Kit- Fuel Tank Boost Not Available for procurement

Pump Auto Shut Off System, Center and Auxiliary

Fuel Tanks

65C38471-12 (c)

(e)

Top Kit- Fuel Tank Boost - - 539 $16,236.00

Pump Auto Shut Off System, Center and Auxiliary

Fuel Tanks

65C38471-14 (d)

(h)

Supplemental Kit - J2802 07/19/12 25 203 $1,059.00

Relay Box Modification

For Airplanes With

Airstairs

65C37854-15 (f)

Supplemental Kit - New 07/17/12 105 139 $239.00

Labels For J2802 Relay

Box

65C37854-16 (f)

Supplemental Kit-Boost - - 147 $59.00

Pump, Auto S/O, CTR

Tank, Airstairs 737-300/-

400/-500

65C38471-15 (g)

(a) This Top Kit is replaced by new Top Kit 65C38471-14. Operators that have already received Top Kit

65C38471-8, but have not accomplished this service bulletin, Supplemental Kits 65C37854-15, 65C37854-

16, and 65C38471-15 are also necessary. Top Kit 65C38471-8 plus Supplemental Kits 65C37854-15,

65C37854-16, and 65C38471-15 are equivalent to new Top Kit 65C38471-14.

(b) Airplanes have been delivered with wire provisions for Auxiliary Tanks installation. If Auxiliary Tanks have

been installed on these airplanes operators need to order this kit. If Auxiliary Tanks have not been installed

on these airplanes there are more parts than necessary in this kit. Operators need to order only the necessary parts to incorporate the Auto Shutoff system for the Center Tanks. The necessary parts can be

ordered as end item parts. Contact Boeing Spares for ordering the necessary end item parts from kit

65C38471-8.

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Group 17-18:

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 Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

(c) This Top Kit is replaced by new Top Kit 65C38471-14. Operators that have already received Top Kit

65C38471-12, but have not accomplished this service bulletin, Supplemental Kit 65C38471-15 is also

necessary. Top Kit 65C38471-12 plus Supplemental Kit 65C38471-15 are equivalent to new Top Kit

65C38471-14.

(d) This Top Kit is necessary for operators that have not received Top Kit 65C38471-8 or Top Kit 65C38471-

12 and have not accomplished this service bulletin. New Top Kit 65C38471-14 supersedes Top Kit

65C38471-8 and Top Kit 65C38471-12

(e) Airplanes have been delivered with wire provisions for Auxiliary Tanks installation. If Auxiliary Tanks have

been installed on these airplanes operators need to order this kit. If Auxiliary Tanks have not been installed

on these airplanes there are more parts than necessary in this kit. Operators need to order only the necessary parts to incorporate the Auto Shutoff system for the Center Tanks. The necessary parts can be

ordered as end item parts. Contact Boeing Spares for ordering the necessary end item parts from kit

65C38471-12.

(f) This Supplemental Kit is necessary for operators that have received Top Kit 65C38471-8.

(g) This Supplemental Kit is necessary for operators that have received either Top Kit 65C38471-8 or Top

Kit 65C38471-12.

(h) Airplanes have been delivered with wire provisions for Auxiliary Tanks installation. If Auxiliary Tanks have

been installed on these airplanes operators need to order this kit. If Auxiliary Tanks have not been installed

on these airplanes there are more parts than necessary in this kit. Operators need to order only the necessary parts to incorporate the Auto Shutoff system for the Center Tanks. The necessary parts can be

ordered as end item parts. Contact Boeing Spares for ordering the necessary end item parts from kit

65C38471-14.

Group 19-20:

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 Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost 05/05/10 10 539 $10,719.00

Pump Auto Shut Off System, Center and Auxiliary

Fuel Tanks

65C38471-8 (a)

(c)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Revision 3: July 16, 2014 737-28A1216

97 of 490

BOEING SERVICE BULLETIN 737-28A1216
Group 19-20:

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 Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

Supplemental Kit - New 07/17/12 105 139 $239.00

Labels For J2802 Relay

Box

65C37854-16 (b)

(c)

(a) Operators that have already received Top Kit 65C38471-8, but have not accomplished this service bulletin,

Supplemental Kit 65C37854-16 is also necessary.

(b) This Supplemental Kit is necessary for operators that have received Top Kit 65C38471-8.

(c) Top Kit 65C38471-8 and Supplemental Kit 65C37854-16 are both necessary for operators to accomplish

this service bulletin.

NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given in

the Original Issue of this service bulletin can use the J2802 Box Assembly received in the kit

but they need to change the J2802 Box for airplanes with airstairs. Refer to Paragraph 1.A.,

Effectivity and APPENDIX A before ordering kits.

Group 14, 21-29, 31:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost 05/05/10 200 539 $9,869.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-7 (a)

05/12/10 100

05/19/10 13

08/16/12 50

08/30/12 50

09/14/12 50

09/28/12 50

Top Kit- Fuel Tank Boost Not Available for procurement

Pump Auto Shut Off System, Center Fuel Tank

65C38471-11 (b)

Top Kit- Fuel Tank Boost - - 539 $22,414.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-13 (c)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Revision 3: July 16, 2014 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216
Group 14, 21-29, 31:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

Supplemental Kit - J2802 07/19/12 25 203 $1,059.00

Relay Box Modification

For Airplanes With

Airstairs

65C37854-15 (d)

Supplemental Kit - New 03/09/12 105 139 $239.00

Labels For J2802 Relay

Box

65C37854-16 (d)

Supplemental Kit-Boost - - 147 $59.00

Pump, Auto S/O, CTR

Tank, Airstairs 737-300/-

400/-500

65C38471-15 (e)

(a) This Top Kit is replaced by new Top Kit 65C38471-13. Operators that have already received Top Kit

65C38471-7, but have not accomplished this service bulletin, Supplemental Kits 65C37854-15, 65C37854-

16, and 65C38471-15 are also necessary. Top Kit 65C38471-7 plus Supplemental Kits 65C37854-15,

65C37854-16, and 65C38471-15 are equivalent to new Top Kit 65C38471-13.

(b) This Top Kit is replaced by new Top Kit 65C38471-13. Operators that have already received Top Kit

65C38471-11, but have not accomplished this service bulletin, Supplemental Kit 65C38471-15 is also

necessary. Top Kit 65C38471-11 plus Supplemental Kit 65C38471-15 are equivalent to new Top Kit

65C38471-13.

(c) This Top Kit is necessary for operators that have not received Top Kit 65C38471-7 or Top Kit 65C38471-

11 and have not accomplished this service bulletin. New Top Kit 65C38471-13 supersedes Top Kit

65C38471-7 and Top Kit 65C38471-17.

(d) This Supplemental Kit is necessary for operators that have received Top Kit 65C38471-7.

(e) This Supplemental Kit is necessary for operators that have received either Top Kit 65C38471-7 or Top

Kit 65C38471-11.

NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given in

the Original Issue of this service bulletin can use the J2802 Box Assembly received in the kit

but they need to change the J2802 Box for airplanes with airstairs. Refer to Paragraph 1.A.,

Effectivity and APPENDIX A before ordering kits.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Revision 3: July 16, 2014 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216
Group 30:

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the Revision 03

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 03 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost 05/05/10 10 539 $10,719.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-8 (a)

Top Kit- Fuel Tank Boost Not Available for procurement

Pump Auto Shut Off System, Center and Auxiliary

Fuel Tanks

65C38471-12 (b)

Top Kit- Fuel Tank Boost - - 539 $16,236.00

Pump Auto Shut Off System, Center and Auxiliary

Fuel Tanks

65C38471-14 (c)

Supplemental Kit - J2802 07/19/12 25 203 $1,059.00

Relay Box Modification

For Airplanes With

Airstairs

65C37854-15 (d)

Supplemental Kit - New 07/17/12 105 139 $239.00

Labels For J2802 Relay

Box

65C37854-16 (d)

Supplemental Kit-Boost - - 147 $59.00

Pump, Auto S/O, CTR

Tank, Airstairs 737-300/-

400/-500

65C38471-15 (e)

(a) This Top Kit is replaced by new Top Kit 65C38471-14. Operators that have already received Top Kit

65C38471-8, but have not accomplished this service bulletin, Supplemental Kits 65C37854-15, 65C37854-

16, and 65C38471-15 are also necessary. Top Kit 65C38471-8 plus Supplemental Kits 65C37854-15,

65C37854-16, and 65C38471-15 are equivalent to new Top Kit 65C38471-14.

(b) This Top Kit is replaced by new Top Kit 65C38471-14. Operators that have already received Top Kit

65C38471-12, but have not accomplished this service bulletin, Supplemental Kit 65C38471-15 is also

necessary. Top Kit 65C38471-12 plus Supplemental Kit 65C38471-15 are equivalent to new Top Kit

65C38471-14.

(c) This Top Kit is necessary for operators that have not received Top Kit 65C38471-8 or Top Kit 65C38471-

12 and have not accomplished this service bulletin. New Top Kit 65C38471-14 supersedes Top Kit

65C38471-8 and Top Kit 65C38471-12.

(d) This Supplemental Kit is necessary for operators that have received Top Kit 65C38471-8.

(e) This Supplemental Kit is necessary for operators that have received either Top Kit 65C38471-8 or Top

Kit 65C38471-12.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts:

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

Kit 65C38471

Existing Part Notes

Number

New Part Number QTY Name

-7 -8 -11 -12

TOP KIT-BOOST (a)

PUMP, AUTO S/O,

CTR TANK,

AIRSTAIRS 737-300/-

400/-500

65C38471-11 . . - .

TOP KIT-BOOST (a)

PUMP, AUTO S/O,

CTR & AUX TANK,

AIRSTAIRS 737-3/-4/-

5

65C38471-12 . . . -

TOP KIT-FUEL BOOST

PUMP, AUTO SHUT

OFF SYSTEM, CENTER TANK 737-300/-

400/-500

65C38471-7 - . . .

TOP KIT-FUEL BOOST

PUMP, AUTO SHUT

OFF SYSTEM, CTR &

AUX TANK 737-300/-

400/-500

65C38471-8 . - . .

61-74478-1 1 . 1 . WIRE KIT

61-74478-2 . 1 . 1 WIRE KIT

KIT - JBOX INSTALLATION FOR AIRPLANES WITHOUT

Auxiliary TANK

65C38484-22 . . 1 .

KIT - JBOX INSTALLATION FOR AIRPLANES WITH Auxiliary TANK

65C38484-23 . . . 1

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 65C38471

Existing Part Notes

Number

New Part Number QTY Name

-7 -8 -11 -12

KIT - JBOX INSTALLATION FOR AIRPLANES WITHOUT

AUX TANK

65C38484-8 1 . . .

KIT - JBOX INSTALLATION FOR AIRPLANES WITH AUX

TANK

65C38484-9 . 1 . .

(a) Kit no longer available for purchase.

Kit 65C38471

Existing Part Notes

Number

New Part Number QTY Name

-13 -14 -15

REPLACEMENT

KIT-BOOST

PUMP, AUTO S/O,

CTR TANK,

AIRSTAIRS 737-

300/-400/-500

65C38471-13 - . .

REPLACEMENT

KIT-BOOST

PUMP, AUTO S/O,

CTR & AUX TANK,

AIRSTAIRS 737-3/-

4/-5

65C38471-14 . - .

SUPPLEMENTAL

KIT-BOOST

PUMP, AUTO S/O,

CTR TANK,

AIRSTAIRS 737-

300/-400/-500

65C38471-15 . . -

287T0011-1 4 4 4 CLAMP OLYMPIC

61-74478-1 1 . . WIRE KIT

61-74478-2 . 1 . WIRE KIT

KIT - JBOX INSTALLATION FOR

AIRPLANES

WITHOUT AUXILIARY TANK

65C38484-22 1 . .

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 65C38471

Existing Part Notes

Number

New Part Number QTY Name

-13 -14 -15

KIT - JBOX INSTALLATION FOR

AIRPLANES WITH

AUXILIARY TANK

65C38484-23 . 1 .

NUT, SPACER

PLATE, LIGHT

DUTY

BACN10TL3A10 3 3 3

NUT SPACER

PLATE

BACN10TL3A14 2 2 2

NUT, SPACER

PLATE

BACN10TL3A4 2 2 2

RIVET, UNIVERSAL HDBACR15BB4D3C 8 8 8

BACR15BB4D4C 2 2 2 RIVET

BACS12HN3-8 5 5 5 BOLT

NAS1149D0316H 5 5 5 WASHER

Kit 65C37854

Existing Part Notes

Number

New Part Number QTY Name

-15 -16

Supplemental Kit -

J2802 Box Assembly Modification For

Airplanes With

Airstairs

65C37854-15 - .

Supplemental Kit -

New Labels For

J2802 Box Assembly

65C37854-16 . -

287T0011-1 2 . CLAMP OLYMPIC

65C38484-18 1 . BRACKET

65C38484-19 1 . BRACKET

J2802 PANEL

COVER

65C38484-20 1 .

J2802 Relay Box

Label - J2802

65C38484-30 . 2

J2802 Relay Box

Label - CTR-L

65C38484-31 . 1

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 65C37854

Existing Part Notes

Number

New Part Number QTY Name

-15 -16

J2802 Relay Box

Label - CTR-R

65C38484-32 . 1

J2802 Relay Box

Label - NOT-USED

65C38484-33 . 2

J2802 Relay Box

Label - AUX-FWD

65C38484-34 . 1

J2802 Relay Box

Label - AUX-AFT

65C38484-35 . 1

J2802 Relay Box

Label - TEST

SWITCHES

65C38484-36 . 1

J2802 Relay Box

Label - AUTO

SHUTOFF

65C38484-37 . 1

J2802 PANEL

COVER SEAL

65C38484-7 2 .

BACB30NX6K6 6 . BOLT

BACC30BH6 6 . COLLAR

BACF3F008E013NN 1 . FILLER

BACF3F013E043NN 1 . FILLER, FLAT

BACG20Z- 4 . GROMMET

B001275

BACJ40AB20-8 1 . JUMPER

NUT, SPACER

PLATE, LIGHT

DUTY

BACN10TL3A10 2 .

NUT SPACER

PLATE

BACN10TL3A14 2 .

BACN10YR3CD 12 . NUT

BACS12HN3-10 2 . BOLT

BACS12HN3-8 12 . BOLT

NAS1149D0316H 28 . WASHER

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-1 -2

61-74478-1 - . WIRE KIT

61-74478-2 . - WIRE KIT

61-74478-101 1 . ASSY - W036

61-74478-102 . 1 ASSY - W036

61-74478-103 1 . ASSY - W044

61-74478-104 . 1 ASSY - W044

61-74478-105 1 . ASSY - W1760

61-74478-106 . 1 ASSY - W1760

61-74478-107 1 . ASSY - W1770

61-74478-108 . 1 ASSY - W1770

ASSY - W368,

W1764

61-74478-109 1 .

ASSY - W368,

W1764

61-74478-110 . 1

ASSY - W386,

W1774

61-74478-111 1 .

ASSY - W386,

W1774

61-74478-112 . 1

LACING TAPE -

WHITE

61-74478-2001 1 1

LACING TAPE -

RED

61-74478-2002 1 1

LACING TAPE -

YELLOW

61-74478-2003 1 1

THERMOFIT

SLEEVE - 0.125

I.D.

61-74478-2005 1 1

EXPANDABLE

SLEEVE, 0.5 IN.

I.D.

61-74478-2006 1 1

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

61-74478-101 - . . . . . ASSY - W036 (a)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

CONNECTOR I.D. (b)

TAPE - D04064P

61-74478-10101 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04076P

61-74478-10102 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04148P

61-74478-10103 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04180P

61-74478-10104 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04238P

61-74478-10105 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04240P

61-74478-10106 1 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM116

61-74478-10107 1 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM118

61-74478-10108 1 1 . . . .

61-74478-101W 1 . . . . . WIRE LIST

61-74478-102 . - . . . . ASSY - W036 (a)

CONNECTOR I.D. (b)

TAPE - D04026P

61-74478-10201 . 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04132P

61-74478-10202 . 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04154P

61-74478-10203 . 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04156P

61-74478-10204 . 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04212P

61-74478-10205 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM182

61-74478-10206 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM184

61-74478-10207 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM186

61-74478-10208 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM188

61-74478-10209 . 1 . . . .

61-74478-10210 . 1 . . . . FILLER WIRE (a) (d)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

61-74478-102W . 1 . . . . WIRE LIST

61-74478-103 . . - . . . ASSY - W044 (a)

CONNECTOR I.D. (b)

TAPE - D01606

61-74478-10301 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D01608

61-74478-10302 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04076J

61-74478-10305 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04148J

61-74478-10306 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04238J

61-74478-10307 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04240J

61-74478-10308 . . 1 1 . .

61-74478-10309 . . 1 1 . . FILLER WIRE (d)

61-74478-103W . . 1 . . . WIRE LIST

61-74478-104 . . . - . . ASSY - W044 (a)

CONNECTOR I.D. (b)

TAPE - D01818

61-74478-10401 . . . 1 . .

CONNECTOR I.D. (b)

TAPE - D01820

61-74478-10402 . . . 1 . .

61-74478-104W . . . 1 . . WIRE LIST

61-74478-105 . . . . - . ASSY - W1760 (a)

WIRE BUNDLE (e)

I.D. TAPE - 61-

31760-001

61-74478-10501 . . . . 1 .

CONNECTOR I.D. (b)

TAPE - D05208J

61-74478-10502 . . . . 1 1

CONNECTOR I.D. (b)

TAPE - D10966

61-74478-10503 . . . . 1 1

61-74478-105W . . . . 1 . WIRE LIST

61-74478-106 . . . . . - ASSY - W1760 (a)

CONNECTOR I.D. (b)

TAPE - D10970

61-74478-10601 . . . . . 1

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

WIRE BUNDLE (e)

I.D. TAPE - 61-

31760-002

61-74478-10602 . . . . . 1

61-74478-106W . . . . . 1 WIRE LIST

316-1616-634 . . 3 3 . . CONTACT (a)

SPLICE, PARAL- (a)

LEL, SOLISTRAND

34137 3 7 . . . .

BACC47CN1S 7 18 . . 4 7 CONTACT, PIN (a)

BACC47CN2 . 5 . . . . CONTACT, PIN (a)

CONTACT, SOCK- (a)

ET

BACC47CP1S 3 3 3 5 . .

BACC47CP2T . . 3 5 . . CONTACT (a)

BACC47DE1A . . . . 5 9 CONTACT (a)

BACC47DE4A . . 3 5 . . CONTACT (a)

BACC47DE7A . . 3 5 . . CONTACT, PIN (a)

CONTACT, SOCK- (a)

ET

BACC47ER1 . . . . 5 9

BACT12AR202 . . . . 3 5 TERMINAL (a)

BACT12AR203 . . . . 3 5 TERMINAL (a)

SLEEVE, SEALING, SPLICED-436-46 3 7 . . . .

CONTACT, PIN, (a)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 . . . . 4 7

MS27488-16-1 . . . . 22 22 PLUG (a)

MS27488-20-1 . . . . 27 28 PLUG (a)

(a) There are more parts in this kit than are necessary. Keep the part not used if there are other uses for it

or discard it.

(b) The identification (ID) tape is made from label BACT19( ). The ID tape is imprinted with the equipment

numbers.

(c) The identification (ID) sleeve is made from marker sleeve TMSSCE14-2-4. The ID sleeve is imprinted with

the equipment number.

(d) The filler wire is made from BMS13-48, Type 10, Class 1 and AWG 18. The total length is longer than

necessary. Cut to the final necessary length during the wiring installation.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

(e) The identification (ID) tape is made from label BACT19E-T6 or BACT19ET6. The ID tape is imprinted with

the wire bundle number.

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107 -108 -109 -110 -111 -112

61-74478-107 - . . . . . ASSY - W1770

WIRE BUNDLE (a)

I.D. TAPE - 61-

31770-001

61-74478-10701 1 . . . . .

CONNECTOR I.D. (b)

TAPE - D05210J

61-74478-10702 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D10968

61-74478-10703 1 1 . . . .

61-74478-107W 1 . . . . . WIRE LIST

61-74478-108 . - . . . . ASSY - W1770

CONNECTOR I.D. (b)

TAPE - D10972

61-74478-10801 . 1 . . . .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31770-002

61-74478-10802 . 1 . . . .

61-74478-108W . 1 . . . . WIRE LIST

ASSY - W368,

W1764

61-74478-109 . . - . . .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31764-001

61-74478-10901 . . 2 . . .

CONNECTOR I.D. (b)

TAPE - D04180J

61-74478-10902 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04202J

61-74478-10903 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D05208P

61-74478-10904 . . 1 1 . .

SPLICE I.D. (c)

SLEEVE - SP4510

61-74478-10905 . . 1 1 . .

WIRE I.D. TAPE - (d)

W0368-031-20

61-74478-10906 . . 2 2 . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

109 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107 -108 -109 -110 -111 -112

61-74478-109W . . 1 . . . WIRE LIST

ASSY - W368,

W1764

61-74478-110 . . . - . .

CONNECTOR I.D. (b)

TAPE - D04026J

61-74478-11001 . . . 1 . .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31764-002

61-74478-11002 . . . 2 . .

61-74478-110W . . . 1 . . WIRE LIST

ASSY - W386,

W1774

61-74478-111 . . . . - .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31774-001

61-74478-11101 . . . . 2 .

CONNECTOR I.D. (b)

TAPE - D04064J

61-74478-11102 . . . . 1 1

CONNECTOR I.D. (b)

TAPE - D04084J

61-74478-11103 . . . . 1 1

CONNECTOR I.D. (b)

TAPE - D05210P

61-74478-11104 . . . . 1 1

SPLICE I.D. (c)

SLEEVE - SP4512

61-74478-11105 . . . . 1 1

WIRE I.D. TAPE - (d)

W0386-032-20

61-74478-11106 . . . . 2 2

61-74478-111W . . . . 1 . WIRE LIST

ASSY - W386,

W1774

61-74478-112 . . . . . -

CONNECTOR I.D. (b)

TAPE - D04212J

61-74478-11201 . . . . . 1

WIRE BUNDLE (a)

I.D. TAPE - 61-

31774-002

61-74478-11202 . . . . . 2

61-74478-112W . . . . . 1 WIRE LIST

CONNECTOR,

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT24-43S . . 1 1 . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

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110 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107 -108 -109 -110 -111 -112

CONNECTOR, (e)

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT24- . . . . 1 1

43S6

BACC47CN1S 4 7 3 3 . . CONTACT, PIN (e)

CONTACT, SOCK- (e)

ET

BACC47CP1S . . 4 10 6 13

BACC47DE1A 5 9 . . . . CONTACT (e)

CONTACT, SOCK- (e)

ET

BACC47ER1 5 9 . . . .

BACT12AR202 3 5 . . . . TERMINAL (e)

BACT12AR203 3 5 . . . . TERMINAL (e)

D-436-37 . . 2 2 2 2 SPLICE (e)

CONTACT, PIN, (e)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 4 7 . . . .

MS27488-16-1 22 22 22 22 22 22 PLUG (e)

MS27488-20-1 27 28 22 19 22 19 PLUG (e)

(a) The identification (ID) tape is made from label BACT19E-T6 or BACT19ET6. The ID tape is imprinted with

the wire bundle number.

(b) The identification (ID) tape is made from label BACT19( ). The ID tape is imprinted with the equipment

numbers.

(c) The identification (ID) sleeve is made from marker sleeve TMSSCE14-2-4. The ID sleeve is imprinted with

the equipment number.

(d) The identification (ID) tape is made from label BACT19C-T or BACT19CT. The ID tape is imprinted with

the wire number.

(e) There are more parts in this kit than are necessary. Keep the part not used if there are other uses for it

or discard it.

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-2001 -2002 -2003 -2005 -2006 -10101

CONNECTOR I.D.

TAPE - D04064P

61-74478-10101 . . . . . -

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

111 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-2001 -2002 -2003 -2005 -2006 -10101

LACING TAPE - (a)

WHITE

61-74478-2001 - . . . . .

LACING TAPE - (b)

RED

61-74478-2002 . - . . . .

LACING TAPE - (c)

YELLOW

61-74478-2003 . . - . . .

THERMOFIT (d)

SLEEVE - 0.125

I.D.

61-74478-2005 . . . - . .

EXPANDABLE (e)

SLEEVE, 0.5 IN.

I.D.

61-74478-2006 . . . . - .

CONNECTOR I.D.

TAPE - D04064P

61-74478-10101 . . . . . -

BACT19C-T . . . . . 1 TAPE, ID

POLYOLEFIN, (f)

HEAT SHRINKABLE SLEEVE,

SEE RM PL FOR

COMPLETE DEFINITION

M23053/5-104-4 . . . 1 . .

NA374H2 1 . . . . . BMS 13-54 (g)

OBSOLETE, INAC- (f)

TIVE FOR NEW

DESIGN, MAY BE

USED FOR

SPARES/MODIFICATIONS

NA728R99 . . . . 1 .

OBSOLETE, INAC- (g)

TIVE FOR NEW

DESIGN, MAY BE

USED FOR

SPARES/MODIFICATIONS

NE597X7 . 1 . . . .

NN048A9 . . 1 . . . BMS 13-54 TAPE (g)

(a) The total length supplied is a minimum of 4,500 inches or one spool and is longer than it is necessary.

(b) The total length supplied is a minimum of 1,020 inches or one spool and is longer than it is necessary.

(c) The total length supplied is a minimum of 1,800 inches or one spool and is longer than it is necessary.

(d) The total length of the sleeve is 9 inches and is longer than is necessary.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

112 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-2001 -2002 -2003 -2005 -2006 -10101

(e) The supplied total length is a minimum of 276 inches or one spool and is longer than it is necessary.

(f) Cut each sleeve to the final necessary length during the wiring installation.

(g) Cut each tape to the final necessary length during the wiring installation.

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10102 -10103 -10104 -10105 -10106 -10107

CONNECTOR I.D.

TAPE - D04076P

61-74478-10102 - . . . . .

CONNECTOR I.D.

TAPE - D04148P

61-74478-10103 . - . . . .

CONNECTOR I.D.

TAPE - D04180P

61-74478-10104 . . - . . .

CONNECTOR I.D.

TAPE - D04238P

61-74478-10105 . . . - . .

CONNECTOR I.D.

TAPE - D04240P

61-74478-10106 . . . . - .

SPLICE I.D.

SLEEVE - SM116

61-74478-10107 . . . . . -

BACT19C-T 1 1 1 1 1 . TAPE, ID

TMSSCE14-2-4 . . . . . 1 MARKER SLEEVE

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10108 -10201 -10202 -10203 -10204 -10205

SPLICE I.D.

SLEEVE - SM118

61-74478-10108 - . . . . .

CONNECTOR I.D.

TAPE - D04026P

61-74478-10201 . - . . . .

CONNECTOR I.D.

TAPE - D04132P

61-74478-10202 . . - . . .

CONNECTOR I.D.

TAPE - D04154P

61-74478-10203 . . . - . .

CONNECTOR I.D.

TAPE - D04156P

61-74478-10204 . . . . - .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

113 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10108 -10201 -10202 -10203 -10204 -10205

CONNECTOR I.D.

TAPE - D04212P

61-74478-10205 . . . . . -

SPLICE I.D.

SLEEVE - SM118

61-74478-10108 - . . . . .

BACT19C-T . 1 1 1 1 1 TAPE, ID

TMSSCE14-2-4 1 . . . . . MARKER SLEEVE

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10206 -10207 -10208 -10209 -10210 -10301

SPLICE I.D.

SLEEVE - SM182

61-74478-10206 - . . . . .

SPLICE I.D.

SLEEVE - SM184

61-74478-10207 . - . . . .

SPLICE I.D.

SLEEVE - SM186

61-74478-10208 . . - . . .

SPLICE I.D.

SLEEVE - SM188

61-74478-10209 . . . - . .

61-74478-10210 . . . . - . FILLER WIRE

CONNECTOR I.D.

TAPE - D01606

61-74478-10301 . . . . . -

BACT19C-T . . . . . 1 TAPE, ID

BMS13- . . . . 1 . WIRE

48T10C01G018

TMSSCE14-2-4 1 1 1 1 . . MARKER SLEEVE

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10302 -10303 -10304 -10305 -10306 -10307

CONNECTOR I.D.

TAPE - D01608

61-74478-10302 - . . . . .

CONNECTOR I.D.

TAPE - D01606

61-74478-10303 . - . . . .

CONNECTOR I.D.

TAPE - D01608

61-74478-10304 . . - . . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

114 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10302 -10303 -10304 -10305 -10306 -10307

CONNECTOR I.D.

TAPE - D04076J

61-74478-10305 . . . - . .

CONNECTOR I.D.

TAPE - D04148J

61-74478-10306 . . . . - .

CONNECTOR I.D.

TAPE - D04238J

61-74478-10307 . . . . . -

BACT19C-T 1 1 1 1 1 1 TAPE, ID

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10308 -10309 -10401 -10402 -10403 -10404

CONNECTOR I.D.

TAPE - D04240J

61-74478-10308 - . . . . .

61-74478-10309 . - . . . . FILLER WIRE

CONNECTOR I.D.

TAPE - D01818

61-74478-10401 . . - . . .

CONNECTOR I.D.

TAPE - D01820

61-74478-10402 . . . - . .

CONNECTOR I.D.

TAPE - D01818

61-74478-10403 . . . . - .

CONNECTOR I.D.

TAPE - D01820

61-74478-10404 . . . . . -

BACT19C-T 1 . 1 1 1 1 TAPE, ID

BMS13- . 1 . . . . WIRE

48T10C01G018

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10501 -10502 -10503 -10601 -10602 -10701

WIRE BUNDLE

I.D. TAPE - 61-

31760-001

61-74478-10501 - . . . . .

CONNECTOR I.D.

TAPE - D05208J

61-74478-10502 . - . . . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

115 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10501 -10502 -10503 -10601 -10602 -10701

CONNECTOR I.D.

TAPE - D10966

61-74478-10503 . . - . . .

CONNECTOR I.D.

TAPE - D10970

61-74478-10601 . . . - . .

WIRE BUNDLE

I.D. TAPE - 61-

31760-002

61-74478-10602 . . . . - .

WIRE BUNDLE

I.D. TAPE - 61-

31770-001

61-74478-10701 . . . . . -

BACT19C-T . 1 1 1 . . TAPE, ID

BACT19E-T6 1 . . . 1 1 TAPE, ID

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10702 -10703 -10801 -10802 -10901 -10902

CONNECTOR I.D.

TAPE - D05210J

61-74478-10702 - . . . . .

CONNECTOR I.D.

TAPE - D10968

61-74478-10703 . - . . . .

CONNECTOR I.D.

TAPE - D10972

61-74478-10801 . . - . . .

WIRE BUNDLE

I.D. TAPE - 61-

31770-002

61-74478-10802 . . . - . .

WIRE BUNDLE

I.D. TAPE - 61-

31764-001

61-74478-10901 . . . . - .

CONNECTOR I.D.

TAPE - D04180J

61-74478-10902 . . . . . -

BACT19C-T 1 1 1 . . 1 TAPE, ID

BACT19E-T6 . . . 1 1 . TAPE, ID

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

116 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-10903 -10904 -10905 -10906 -11001 -11002

CONNECTOR I.D.

TAPE - D04202J

61-74478-10903 - . . . . .

CONNECTOR I.D.

TAPE - D05208P

61-74478-10904 . - . . . .

SPLICE I.D.

SLEEVE - SP4510

61-74478-10905 . . - . . .

WIRE I.D. TAPE -

W0368-031-20

61-74478-10906 . . . - . .

CONNECTOR I.D.

TAPE - D04026J

61-74478-11001 . . . . - .

WIRE BUNDLE

I.D. TAPE - 61-

31764-002

61-74478-11002 . . . . . -

BACT19C-T 1 1 . 1 1 . TAPE, ID

BACT19E-T6 . . . . . 1 TAPE, ID

TMSSCE14-2-4 . . 1 . . . MARKER SLEEVE

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-11101 -11102 -11103 -11104 -11105 -11106

WIRE BUNDLE

I.D. TAPE - 61-

31774-001

61-74478-11101 - . . . . .

CONNECTOR I.D.

TAPE - D04064J

61-74478-11102 . - . . . .

CONNECTOR I.D.

TAPE - D04084J

61-74478-11103 . . - . . .

CONNECTOR I.D.

TAPE - D05210P

61-74478-11104 . . . - . .

SPLICE I.D.

SLEEVE - SP4512

61-74478-11105 . . . . - .

WIRE I.D. TAPE -

W0386-032-20

61-74478-11106 . . . . . -

BACT19C-T . 1 1 1 . 1 TAPE, ID

BACT19E-T6 1 . . . . . TAPE, ID

TMSSCE14-2-4 . . . . 1 . MARKER SLEEVE

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

117 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-11201 -11202

CONNECTOR I.D.

TAPE - D04212J

61-74478-11201 - .

WIRE BUNDLE

I.D. TAPE - 61-

31774-002

61-74478-11202 . -

BACT19C-T 1 . TAPE, ID

BACT19E-T6 . 1 TAPE, ID

Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-101W -102W -103W -104W -105W -106W

61-74478-101W - . . . . . WIRE LIST

61-74478-102W . - . . . . WIRE LIST

61-74478-103W . . - . . . WIRE LIST

61-74478-104W . . . - . . WIRE LIST

61-74478-105W . . . . - . WIRE LIST

61-74478-106W . . . . . - WIRE LIST

61-74478-101W - . . . . . WIRE LIST

61-74478-102W . - . . . . WIRE LIST

61-74478-103W . . - . . . WIRE LIST

61-74478-104W . . . - . . WIRE LIST

61-74478-105W . . . . - . WIRE LIST

61-74478-106W . . . . . - WIRE LIST

BMS13- . . 1 1 . . WIRE (a) (d)

58T01C01G022

WIRE RMS (b) (d)

5454011752

BMS13- 1 1 . 1 1 1

58T1C1G20

WIRE RMS (c) (d)

5454011755

BMS13- 1 1 . . . .

58T5C1G24

(a) Made from the BMS13-58, Type 1, Class 1, AWG 22 wires.

(b) Made from the BMS13-58, Type 1, Class 1, Gage (AWG) 20 wires.

(c) Made from the BMS13-58, Type 5, Class 1, AWG 24 wires.

(d) Each cut and coded wire is longer than necessary. Cut the wire to the final necessary length during the

wiring installation. Some wiring installations possibly do not use this wire.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

118 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 61-74478

Existing Notes

Part

Number

New Part Number QTY Name

-107W -108W -109W -110W -111W -112W

61-74478-107W - . . . . . WIRE LIST

61-74478-108W . - . . . . WIRE LIST

61-74478-109W . . - . . . WIRE LIST

61-74478-110W . . . - . . WIRE LIST

61-74478-111W . . . . - . WIRE LIST

61-74478-112W . . . . . - WIRE LIST

61-74478-107W - . . . . . WIRE LIST

61-74478-108W . - . . . . WIRE LIST

61-74478-109W . . - . . . WIRE LIST

61-74478-110W . . . - . . WIRE LIST

61-74478-111W . . . . - . WIRE LIST

61-74478-112W . . . . . - WIRE LIST

WIRE RMS (a) (b)

5454011752

BMS13- 1 1 1 1 1 1

58T1C1G20

(a) Made from the BMS13-58, Type 1, Class 1, Gage (AWG) 20 wires.

(b) Each cut and coded wire is longer than necessary. Cut the wire to the final necessary length during the

wiring installation. Some wiring installations possibly do not use this wire.

Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

KIT ASSY - J2802

JBOX

65C38484-10 1 . - . . .

KIT ASSY - J2802

JBOX

65C38484-11 . 1 . - . .

J2802 PANEL ASSY65C38484-12 . . 1 1 - .

65C38484-13 . . . . 1 - J2802 PANEL

65C38484-14 1 1 . . . . KIT - SLEEVING

KIT - JBOX INSTALLATION FOR

AIRPLANES

WITHOUT AUX

TANK

65C38484-8 - . . . . .

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3: July 16, 2014 737-28A1216

119 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

KIT - JBOX INSTALLATION FOR

AIRPLANES WITH

AUX TANK

65C38484-9 . - . . . .

287T0011-1 4 4 . . . . CLAMP OLYMPIC

DISCONNECT ANGLE (1

BACD2010-640,

NO PILOT HOLES)

287U0016-185 . . 2 2 . .

KIT ASSY - J2802

JBOX

65C38484-10 1 . - . . .

KIT ASSY - J2802

JBOX

65C38484-11 . 1 . - . .

J2802 PANEL ASSY65C38484-12 . . 1 1 - .

65C38484-13 . . . . 1 - J2802 PANEL

65C38484-14 1 1 . . . . KIT - SLEEVING

J2802 PANEL

COVER

65C38484-6 . . 1 1 . .

J2802 PANEL

COVER SEAL

65C38484-7 . . 2 2 . .

BOLT, PROTRUDING HD

BACB30NX5HK6 6 6 . . . .

CIRCUIT BREAKERBACC18Z1R . . 2 4 . .

COLLAR,

PRELOAD

BACC30BH5 6 6 . . . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24-43P . . 1 1 . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24- . . 1 1 . .

43P6

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: July 29, 2010

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120 of 490

BOEING SERVICE BULLETIN 737-28A1216
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

CLAMP ASSEMBLYBACC49A2 . . 4 4 . .

BACG20Z- . . 4 4 . . GROMMET

B000400

BONDING

JUMPER

BACJ40AB20-6 1 1 . . . .

BACM15C3E . . 2 4 . . TERMINAL BLOCK

BACN10JC06CD . . 4 4 . . NUT

BACN10JN08 . . . . 16 . NUT PLATE

NUTPLATE, SELFLOCKBACN10JY3R . . 6 6 . .

BACN10NX32D4 . . 3 3 . . STANDOFF

BACN10YR3CD 6 6 . . . . NUT

BACR15BA3AD4C . . . . 32 . RIVET

BACR15BA3D4C . . 12 12 . . RIVET, 100 DEG

BACR15BA4D4C . . 8 8 . . RIVET

BACR15BA4D5C . . 14 14 . . RIVET, 100 DEG

BACR15BB5D5C . . 4 4 . . RIVET

BACS12HN06-7 . . 4 4 . . BOLT

BACS12HN3-7 2 2 . . . . BOLT

BACS12HN3-8 4 4 6 6 . . BOLT

BACS16AH1 . . 2 4 . . RELAY SOCKET

RINGPOST, WIRE

HARNESS

MOUNTING SUPPORT

BACS31H2B . . 3 3 . .

BACS38W2I 10 10 . . . . STRAP

(BACS38W2 optional)

BACT19J2 . . 20 26 . . TAPE, ID

BACT19J3 . . 38 38 . . TAPE, ID

BACT19J4 . . 2 2 . . TAPE, ID

BACT44B0700U . . 2 2 . . TRACK, TB MDL

MS24524-27 . . 2 2 . . SWITCH, TOGGLE

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Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

ALUMINUM ALLOY, CLAD

SHEET; SEE RM

PL REPORT FOR

COMPLETE DEFINITION

MX211F . . . . . 1

NAS1149D0316H 10 10 . . . . WASHER

NAS1149F0363P . . 6 6 . . WASHER, PLAIN

SPACERS FOR

RIVETS

NAS42DD6-16FC 6 6 . . . .

TIME DELAY RELAYTDH1852-1502 2 4 . . . .

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-33 . . 2 4 . .

YHLZG16-1 . . 2 2 . . GROUND BLOCK

Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-14 -15 -16 -17 -18 -19

65C38484-14 - . . . . . KIT - SLEEVING

KIT ASSY - J2802

JBOX

65C38484-15 . - . . . .

65C38484-16 . . - 1 . . J2802 PANEL

J2802 PANEL ASSY65C38484-17 . 1 . - . .

65C38484-18 . . . 1 - . BRACKET

65C38484-19 . . . 1 . - BRACKET

J2802 PANEL

COVER

65C38484-20 . 1 . . . .

287T0011-1 . 4 . . . . CLAMP OLYMPIC

DISCONNECT ANGLE (1

BACD2010-640,

NO PILOT HOLES)

287U0016-185 . 2 . . . .

J2802 PANEL

COVER SEAL

65C38484-7 . 2 . . . .

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Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-14 -15 -16 -17 -18 -19

CIRCUIT BREAKERBACC18Z1R . 4 . . . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24-43P . 1 . . . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24- . 1 . . . .

43P6

CLAMP ASSEMBLYBACC49A2 . 4 . . . .

BACG20Z- . 4 . . . . GROMMET

B000400

BACM15C3E . 4 . . . . TERMINAL BLOCK

BACN10JC06CD . 4 . . . . NUT

BACN10JN08 . . . 16 . . NUT PLATE

NUTPLATE, SELFLOCKBACN10JY3R . 6 . . . .

BACN10NX32D4 . 3 . . . . STANDOFF

NUT, SPACER

PLATE, LIGHT

DUTY

BACN10TL3A10 . 2 . . . .

NUT SPACER

PLATE

BACN10TL3A14 . 2 . . . .

BACN10YR3CD . 4 . 8 . . NUT

BACR15BA3AD4C . . . 32 . . RIVET

BACR15BA3D4C . 12 . . . . RIVET, 100 DEG

BACR15BA4D3C . 8 . . . . RIVET, 100 DEG

BACR15BA4D4C . 8 . . . . RIVET

BACR15BA4D5C . 14 . . . . RIVET, 100 DEG

BACS12HN06-7 . 4 . . . . BOLT

BACS12HN3-10 . 3 . . . . BOLT

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Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-14 -15 -16 -17 -18 -19

BACS12HN3-8 . 12 . 8 . . BOLT

BACS16AH1 . 4 . . . . RELAY SOCKET

RINGPOST, WIRE

HARNESS

MOUNTING SUPPORT

BACS31H2B . 3 . . . .

BACT19J2 . 26 . . . . TAPE, ID

BACT19J3 . 38 . . . . TAPE, ID

BACT19J4 . 2 . . . . TAPE, ID

BACT44B0700U . 2 . . . . TRACK, TB MDL

INSULATION

SLEEVING, HEAT

SHRINKABLE

PTFE.

M23053/12-514-C 1 . . . . .

MS24524-27 . 2 . . . . SWITCH, TOGGLE

ALUMINUM ALLOY, CLAD

SHEET; SEE RM

PL REPORT FOR

COMPLETE DEFINITION

MX211F . . 1 . 1 1

NAS1149D0316H . 12 . 16 . . WASHER

NAS1149F0363P . 6 . . . . WASHER, PLAIN

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-33 . 4 . . . .

YHLZG16-1 . 2 . . . . GROUND BLOCK

Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

65C38484-14 . . 1 1 KIT - SLEEVING

KIT ASSY - J2802

JBOX

65C38484-15 . . . 1

J2802 PANEL ASSY65C38484-17 . 1 . .

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Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

J2802 PANEL

COVER

65C38484-20 - 1 . .

KIT ASSY - J2802

JBOX

65C38484-21 . - 1 .

KIT - JBOX INSTALLATION FOR

AIRPLANES

WITHOUT Auxiliary

TANK

65C38484-22 . . - .

KIT - JBOX INSTALLATION FOR

AIRPLANES WITH

Auxiliary TANK

65C38484-23 . . . -

287T0011-1 . 4 4 4 CLAMP OLYMPIC

DISCONNECT ANGLE (1

BACD2010-640,

NO PILOT HOLES)

287U0016-185 . 2 . .

J2802 PANEL

COVER SEAL

65C38484-7 . 2 . .

BOLT, PROTRUDING HDBACB30NX5HK6 . . 6 6

BACB30NX6K6 . . 6 6 BOLT

CIRCUIT BREAKERBACC18Z1R . 2 . .

COLLAR,

PRELOAD

BACC30BH5 . . 6 6

BACC30BH6 . . 6 6 COLLAR

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24-43P . 1 . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24- . 1 . .

43P6

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Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

CLAMP ASSEMBLYBACC49A2 . 4 . .

BACF3F008E013NN . . 1 1 FILLER

BACF3F013E043NN . . 1 1 FILLER, FLAT

BACG20Z- . 4 . . GROMMET

B000400

BACJ40AB20-8 . . 1 1 JUMPER

BACM15C3E . 2 . . TERMINAL BLOCK

BACN10JC06CD . 4 . . NUT

NUTPLATE, SELFLOCKBACN10JY3R . 6 . .

BACN10NX32D4 . 3 . . STANDOFF

NUT, SPACER

PLATE, LIGHT

DUTY

BACN10TL3A10 . 2 . .

NUT SPACER

PLATE

BACN10TL3A14 . 2 . .

BACN10YR3CD . 4 6 6 NUT

BACR15BA3D4C . 12 . . RIVET, 100 DEG

BACR15BA4D3C . 8 . . RIVET, 100 DEG

BACR15BA4D4C . 8 . . RIVET

BACR15BA4D5C . 14 . . RIVET, 100 DEG

BACS12HN06-7 . 4 . . BOLT

BACS12HN3-10 . 3 . . BOLT

BACS12HN3-7 . . 2 2 BOLT

BACS12HN3-8 . 12 4 4 BOLT

BACS16AH1 . 2 . . RELAY SOCKET

RINGPOST, WIRE

HARNESS

MOUNTING SUPPORT

BACS31H2B . 3 . .

BACS38W2 . . 10 10 STRAP

BACT19J2 . 20 . . TAPE, ID

BACT19J3 . 38 . . TAPE, ID

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Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

BACT19J4 . 2 . . TAPE, ID

BACT44B0700U . 2 . . TRACK, TB MDL

MS24524-27 . 2 . . SWITCH, TOGGLE

ALUMINUM ALLOY, CLAD

SHEET; SEE RM

PL REPORT FOR

COMPLETE DEFINITION

MX211F 1 . . .

NAS1149D0316H . 12 10 10 WASHER

NAS1149F0363P . 6 . . WASHER, PLAIN

SPACERS FOR

RIVETS

NAS42DD6-16FC . . 6 6

TIME DELAY RELAYTDH1852-1502 . . 2 4

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-33 . 2 . .

YHLZG16-1 . 2 . . GROUND BLOCK

2. Parts and Materials Supplied by the Operator:

Part Number / Specifi- QTY Name Notes

cation

CHEMICAL CONVERSION (a) (b)

COATING

ALODINE TYPE 2, 2 Ounce

CLASS A OR TYPE 5,

CLASS F

BACS38W2I or 12 TIE STRAP (a)

BACS38W2

BMS10-11, Type I 1 Ounce PRIMER FINISH (a) (c)

BMS10-11, Type II, 1 Ounce ENAMEL FINISH (a) (c)

White Gloss

BMS5-95 2 Ounce SEALANT (a)

BAC 5010 TYPE 82 1 Ounce ADHESIVE (a)

BAC 5010 TYPE 77 1 Ounce ADHESIVE (a)

CLEAR SKYDROL RESIS- (a)

TANT TOPCOATING

BAC5710 TYPE 41 1 Ounce

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BOEING SERVICE BULLETIN 737-28A1216
Part Number / Specifi- QTY Name Notes

cation

TAPE, ELECTRICAL PAN- (a)

EL LABELING

BACT19J2 2

TAPE, ELECTRICAL PAN- (a)

EL LABELING

BACT19J4 6

MS27488-20-1 12 PLUG (d)

NAS1398D5AB4 1 RIVET, BLIND (a)

BACR15BB10D6C 1 RIVET (a)

BACS12GU3K10 1 SCREW (a)

BACW10EC3S 1 WASHER, LOCK (a)

NAS1149D0316H 2 WASHER, PROTECTIVE (a)

MS35650-305T 1 NUT, HEX (a)

BACG20Z-B001275 1 GROMMET (a)

BACR15BA6AD5C 2 RIVET (a)

BACR15BA5AD5C 2 RIVET (a)

(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

(b) Parker and Amchem, 32100 Stephenson Highway, Madison Heights, Michigan 48071

CAGE Code: 0V7E6.

(c) Essex Chemical Corp., Pro-seal Div., 19451 Susana Road, Compton, CA 90220

CAGE Code: V83527.

(d) Additional plugs may be necessary for airplanes with wire provision for AUX Tank

and no AUX Tank installed.

3. Parts Modified and Reidentified:

Existing Part QTY Name New Part Number Notes

Number

65C38484-10 (a) - J2802 Box Assembly 65C38484-16 (c) (b) (d)

65C38484-11 (a) - J2802 Box Assembly 65C38484-16 (c) (b) (d)

(a) Operators that have airplanes with Airstairs that ordered and received the Top Kits given

in the Original Issue of this service bulletin can use the J2802 Box Assembly received in

the kit but they need to change the J2802 Box Assembly for airplanes with airstairs.

(b) Make the change in accordance with this service bulletin.

(c) This is the part number after the change is done in accordance with this service bulletin.

(d) This part is not used in production.

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4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN 737-28A1216

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently or at the same time, except Work Package 3, which must

be done last.

4. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 737 Structural Repair Manual,

Chapter 51.

— Values for airframe maintenance tasks are included in Chapter 20 of 737

Airplane Maintenance Manual (AMM).

— Values for electrical maintenance tasks are included in Chapter 20 of

Standard Wiring Practices Manual (SWPM).

— Values for engine maintenance tasks are included in Chapter 70 of 737

Airplane Maintenance Manual (AMM).

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

5. Use the approved fastener and process material substitutions in accordance with

SRM Chapter 51.

6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

7. The necessary conditions for selection of clamp type and size are included in SWPM

20-10-12. If any wire bundle support clamp specified in this service bulletin does not

make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted

procedure to select a clamp that fits correctly.

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BOEING SERVICE BULLETIN 737-28A1216
8. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

9. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

10. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

11. The instructions in Paragraph 3.B., Work Instructions and the figures can include

operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated

Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing

Index contain data on versions of the tools or test equipment that you can use. It is

permitted to use replaced tools. It is not permitted to use superseded tools.

12. If it is necessary to remove more parts for access, you can remove those parts. If

you can get access without removing identified parts, it is not necessary to remove

all of the identified parts. Jacking and shoring limitations must be observed.

13. Where the work instructions include installation of a kept part, a new or serviceable

part with the same part number can be installed as an alternative to the kept part.

14. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

15. If shading is used, shaded areas in Figures are to separate the non-critical and

non-authoritative information from the critical and authoritative information.

16. Wiring in this bulletin conforms to the requirements of Airworthiness Limitations (AWL)

28-AWL-05 in Boeing document "737-100/200/200C/300/400/500 Airworthiness

Limitations (AWLs)and Certification Maintenance Requirements (CMRs),

D6-38278-CMR.

17. The work instructions are divided into 31 airplane groups and 9 PARTS. In addition,

where applicable, 3 Work Packages are included within the PARTS because of

different changes.

PART 1, PART 2, and PART 3, PART 4, and PART 5 work instructions are divided

into 3 Work Packages because of the different wire bundle changes.

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BOEING SERVICE BULLETIN 737-28A1216
PART 6 provides instructions for Operators that have airplanes with Airstairs and

have ordered and received the Top Kits given in the Original Issue of this service

bulletin. They can use the J2802 Box Assembly received in the kit but they need to

change the J2802 Box Assembly.

PART 7, PART 8, PART 9 provide instructions to change the J2802 Box Assembly

for airplanes that incorporated the Original Issue of the service bulletin.

The table below gives the work necessary to be accomplished for each airplane

group by showing applicable PARTS and Work Packages.

Airplane Groups Part Do Work Packages

1 Through 13, 15 and 1 1, 2, 3

16

17 Through 18 2 1, 2, 3

19 Through 20 3 1, 2, 3

14, 21 Through 29 and 4 1, 2, 3

31

30 5 1, 2, 3

14, 17, 18, 21 Through 6 -

31

1-16, 21-29, 31 7 -

17-18 8 -

19-20, 30 9 -

B. WORK INSTRUCTIONS

1. Group 1-13, 15-16:

PART 1- AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL

TANKS

NOTE: The production delivered fuel boost pump power relays were not polarity sensitive. The

fuel boost pump power control wire has not been connected on the same relay contact

on all 737 classic airplanes. Some airplanes have the power wire connected to contact

X1 of the relay, and the ground connected to contact X2 of the relay. Other airplanes

have the power wire connected to contact X2 of the relay, and the ground connected to

contact X1 of the relay. The Ground Fault Interrupter (GFI) relays are polarity sensitive

relays and require power to be connected to contact X1 of the relays.

Airplane Groups that had the fuel boost pump power wire connected in production to

contact X2 and the ground wire connected to contact X1 are divided in two configurations.

Airplane without the GFI service bulletin 737-28A1212 incorporated do not have the fuel

boost pump power wire moved from contact X2 to X1 and are placed in Configuration 1

airplanes. These airplanes need to replace the ground wire connected to contact X1 with

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BOEING SERVICE BULLETIN 737-28A1216
a new wire in accordance with this service bulletin. The airplanes with GFI service bulletin

737-28A1212 incorporated have the fuel boost pump power wire moved from contact X2

to X1 and are placed in Configuration 2 airplanes. These airplanes need to replace the

ground wire connected to contact X2 with a new wire in accordance with this service

bulletin.

For Airplane Groups that had the fuel boost pump power wire connected in production

to contact X1 and ground wire connected to contact X2 it is not necessary to swap the

wires between contact X1 and X2 when service bulletin 737-28A1212 is incorporated.

For these Airplane Groups it is only necessary to remove the ground wire from contact

X2 and install a new wire in accordance with this service bulletin. These airplanes have

only one configuration regardless if the GFI service bulletin 737-28A1212 has been

incorporated or not.

a. WORK PACKAGE 1: INSTALLATION OF WIRE BUNDLES IN THE J2802 BOX ASSEMBLY

(1) Remove and keep the cover from the J2802 Box Assembly in accordance with FIGURE

1.

(2) Install the labels on the face of the J2802 Box Assembly, and the wire bundle W1760 in

the J2802 box assembly in accordance with FIGURE 3 and FIGURE 4.

(3) Install the wire bundle W1770 in the J2802 Box Assembly in accordance with FIGURE

3 and FIGURE 5.

(4) Install the kept cover on the J2802 Box Assembly in accordance with FIGURE 11.

b. WORK PACKAGE 2: INSTALLATION OF THE J2802 BOX ASSEMBLY IN THE AIRPLANE

(1) Do these steps to get access.

(a) At the lower forward fuselage, below the access door of main electronics

compartment, open the access door. Refer to 737-300/400/500 AMM 52-48-41 as

an accepted procedure.

(b) Remove and keep the moisture shroud from above the access door to get access

to the wire bundle installation area if it is not already removed. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(2) Do these steps to install the J2802 Box Assembly.

(a) In the main electronics compartment, attach the J2802 Box Assembly on the E2 and

E3 Support Posts and drill holes in the E2 Support Post in accordance with FIGURE

12.

(b) Drill holes through the J2802 Box Assembly and the E3 Support Post in accordance

with FIGURE 14.

(c) Prepare the open holes in the E2 and E3 Support Posts and J2802 Box Assembly

in accordance with FIGURE 15.

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BOEING SERVICE BULLETIN 737-28A1216
(d) Install the J2802 Box Assembly on the E2 and E3 Support Posts in accordance with

FIGURE 16.

(e) Install the clamps and a bonding jumper in accordance with FIGURE 18.

(f) If the airplane is to be put in a serviceable condition before Work Package 3, do

these steps.

1) Install the kept moisture shrouds if removed. Refer to 737-300/400/500 AMM

25-51-01 as an accepted procedure.

2) Close the access door to the main electronics compartment. Refer to

737-300/400/500 AMM 52-48-41 as an accepted procedure.

3) Put the airplane back to a serviceable condition.

c. WORK PACKAGE 3: INSTALLATION OF WIRES AND TEST OF THE CHANGED FUEL

SYSTEM

(1) Do these steps to get access.

(a) At the lower forward fuselage, below the main electronics compartment, open the

access door if it is closed. Refer to 737-300/400/500 AMM 52-48-41 as an accepted

procedure.

(b) Remove and keep the moisture shroud from above the access door to get access

to the wire bundle installation area if it is not already removed. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(c) Remove and keep the moisture shroud from above the E3 rack if it is not already

removed. Refer to the 737-300/400/500 AMM 25-51-01 as an accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(e) In the main electronics compartment, disconnect the battery power cables from the

battery. Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(f) In the nose wheel well, remove and keep the right access panels, 3103R and 3105R.

Refer to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(g) In the flight compartment, move the first officer's seat to the forward position. Refer

to 737-300/400/500 AMM 25-10-00 as an accepted procedure.

(h) Remove and keep the ceiling linings adjacent and forward of the P6 load control

panel. Refer to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(i) Remove and keep the aft and mid center ceiling panels. Refer to 737-300/400/500

AMM 25-11-21 as an accepted procedure.

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NOTE: As an optional procedure, to get improved access to the P6 Top Disconnect

Panel, Galley No.1 can be removed. Refer to 737-300/400/500 AMM 25-31-11

as an accepted procedure.

(2) Do these steps to change the wire bundles in the airplane.

(a) In the flight compartment, at the P6 load control panel, loosen the relay panel, remove

and keep the covers, panels and relays in accordance with FIGURE 19.

(b) Between the P5 overhead and P6 top disconnect panels, change the wire bundle

W0036.

1) Group 1:

In accordance with FIGURE 20 and FIGURE 21.

2) Group 2-3:

In accordance with FIGURE 20 and FIGURE 22.

3) Group 4-5:

In accordance with FIGURE 20 and FIGURE 23.

4) Group 6-7:

In accordance with FIGURE 20 and FIGURE 24.

5) Group 8:

In accordance with FIGURE 20 and FIGURE 25.

6) Group 9:

In accordance with FIGURE 20 and FIGURE 26.

7) Group 10-11:

In accordance with FIGURE 20 and FIGURE 27.

8) Group 12:

In accordance with FIGURE 20 and FIGURE 28.

9) Group 13:

In accordance with FIGURE 20 and FIGURE 29.

10) Group 15:

In accordance with FIGURE 20 and FIGURE 31.

11) Group 16:

In accordance with FIGURE 20 and FIGURE 32.

(c) Between the P6 top disconnect panel and the P6 relay panel, change the wire bundle

W0044.

1) Group 1:

In accordance with FIGURE 44 and FIGURE 45.

2) Group 2, Configuration 1:

In accordance with FIGURE 44 and FIGURE 46.

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3) Group 2, Configuration 2:

In accordance with FIGURE 44 and FIGURE 47.

4) Group 3, 16:

In accordance with FIGURE 44 and FIGURE 48.

5) Group 4, Configuration 1:

In accordance with FIGURE 44 and FIGURE 49.

6) Group 4, Configuration 2:

In accordance with FIGURE 44 and FIGURE 50.

7) Group 5, 8:

In accordance with FIGURE 44 and FIGURE 51.

8) Group 6, Configuration 1:

In accordance with FIGURE 44 and FIGURE 52.

9) Group 6, Configuration 2:

In accordance with FIGURE 44 and FIGURE 53.

10) Group 7:

In accordance with FIGURE 44 and FIGURE 59.

11) Group 9:

In accordance with FIGURE 44 and FIGURE 54.

12) Group 10:

In accordance with FIGURE 44 and FIGURE 55.

13) Group 11, Configuration 1:

In accordance with FIGURE 44 and FIGURE 62.

14) Group 11, Configuration 2:

In accordance with FIGURE 44 and FIGURE 63.

15) Group 12, Configuration 1:

In accordance with FIGURE 44 and FIGURE 56.

16) Group 12, Configuration 2:

In accordance with FIGURE 44 and FIGURE 57.

17) Group 13:

In accordance with FIGURE 44 and FIGURE 58.

18) Group 15, Configuration 1:

In accordance with FIGURE 44 and FIGURE 64.

19) Group 15, Configuration 2:

In accordance with FIGURE 44 and FIGURE 65.

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(d) Between the flight and main electronics compartments, change the wire bundle

W0368 and install the wire bundle W1764 in accordance with FIGURE 82 and

FIGURE 83.

(e) Change the wire bundle W0386 and install the wire bundle W1774:

1) Group 1-7, 9-13, 15:

In accordance with FIGURE 82 and FIGURE 86.

2) Group 8, 16:

In accordance with FIGURE 82 and FIGURE 85.

(f) In the main electronics compartment, at the J2802 Box Assembly, install the relays

R3318, R3321, sleeve, grommets and tie straps in accordance with FIGURE 88.

(g) In the flight compartment, at the P6 load control panel, install the kept relays, covers,

panels and the loosened relay panel in accordance with FIGURE 90.

(3) Do these steps to make sure the changed fuel control system operates correctly.

(a) In the main electronics compartment, connect the battery power cables to the battery.

Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(b) Apply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(4) Do these steps to close access.

(a) If removed, install Galley No.1. Refer to 737-300/400/500 AMM 25-31-11 as an

accepted procedure.

(b) In the flight compartment, install the kept aft and mid center ceiling panels. Refer to

737-300/400/500 AMM 25-11-21 as an accepted procedure.

(c) Install the kept ceiling linings adjacent and forward of the P6 load control panel. Refer

to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(d) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM

25-10-00 as an accepted procedure.

(e) In the nose wheel well, install the kept right access panels, 3103R and 3105R. Refer

to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(f) In the main electronics compartment, install the kept moisture shrouds where

removed. Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

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(g) Close the access door to the main electronics compartment. Refer to 737-300/400/500

AMM 52-48-41 as an accepted procedure.

(5) Put the airplane back to a serviceable condition.

2. Group 17-18:

PART 2- AIRPLANES WITH CENTER TANKS AND WIRE PROVISION FOR AUXILIARY (AUX)

FUEL TANKS, AND WITH AIRSTAIRS

NOTE: Airplanes in group 17 and 18 have been delivered with provisional wires for future Auxiliary

Tank installation. Operators that installed AUX tanks with Fuel Boost Pumps on these

airplanes need to install an Auto Shutoff system. The FAA may release an AD to require

that all airplanes that have AUX tanks with Fuel Boost Pumps install an Auto Shutoff

system.

NOTE: The production delivered fuel boost pump power relays were not polarity sensitive. The

fuel boost pump power control wire has not been connected on the same relay contact

on all 737 classic airplanes. Some airplanes have the power wire connected to contact

X1 of the relay, and the ground connected to contact X2 of the relay. Other airplanes

have the power wire connected to contact X2 of the relay, and the ground connected to

contact X1 of the relay. The Ground Fault Interrupter (GFI) relays are polarity sensitive

relays and require power to be connected to contact X1 of the relays.

Airplane Groups that had the fuel boost pump power wire connected in production to

contact X2 and the ground wire connected to contact X1 are divided in two configurations.

Airplane without the GFI service bulletin 737-28A1212 incorporated do not have the fuel

boost pump power wire moved from contact X2 to X1 and are placed in Configuration 1

airplanes. These airplanes need to replace the ground wire connected to contact X1 with

a new wire in accordance with this service bulletin. The airplanes with GFI service bulletin

737-28A1212 incorporated have the fuel boost pump power wire moved from contact X2

to X1 and are placed in Configuration 2 airplanes. These airplanes need to replace the

ground wire connected to contact X2 with a new wire in accordance with this service

bulletin.

For Airplane Groups that had the fuel boost pump power wire connected in production

to contact X1 and ground wire connected to contact X2 it is not necessary to swap the

wires between contact X1 and X2 when service bulletin 737-28A1212 is incorporated.

For these Airplane Groups it is only necessary to remove the ground wire from contact

X2 and install a new wire in accordance with this service bulletin. These airplanes have

only one configuration regardless if the GFI service bulletin 737-28A1212 has been

incorporated or not.

a. WORK PACKAGE 1: INSTALLATION OF WIRING IN THE J2802 BOX ASSEMBLY

NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits

given in the Original Issue of this service bulletin can use the J2802 Box Assembly

received in the kit but they need to change the J2802 Box Assembly in accordance

with PART 6.

(1) If Top Kits given in the original release of this service bulletin have been ordered and

received change J2802 Box Assembly in accordance with PART 6.

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(2) Remove and keep the cover from the J2802 Box Assembly in accordance with FIGURE

97.

(3) Install the wire bundle W1760 in the J2802 Box Assembly in accordance with FIGURE

97, FIGURE 7 and FIGURE 8.

NOTE: Airplanes in Group 17 and Group 18 have been delivered without Auxiliary Tanks

but with wire provisions for Auxiliary Tank installation. It is necessary to do the

change given in FIGURE 7 only if Auxiliary Tanks with Fuel Boost pumps are

installed on the airplane.

(4) Install the wire bundle W1770 in the J2802 Box Assembly in accordance with FIGURE

97, FIGURE 9 and FIGURE 10.

NOTE: Airplanes in Group 17 and Group 18 have been delivered without Auxiliary Tanks

but with wire provisions for Auxiliary Tank installation. It is necessary to do the

change given in FIGURE 9 only if Auxiliary Tanks with Fuel Boost pumps are

installed on the airplane.

(5) Install the kept cover on the J2802 Box Assembly in accordance with FIGURE 97.

b. WORK PACKAGE 2: INSTALLATION OF THE J2802 BOX ASSEMBLY IN THE AIRPLANE

(1) Do these steps to get access.

(a) At the lower forward fuselage, below the main electronics compartment, open the

access door. Refer to 737-300/400/500 AMM 52-48-41 as an accepted procedure.

(b) Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the forward airstairs extension if the airstairs are retracted. Refer to

737-300/400/500 AMM 52-61-00 or 737-300/400/500 AMM 52-61-10 as an accepted

procedure.

(d) In the main electronics compartment, remove and keep the drain pan. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(e) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(2) Do these steps to prepare for and to install the J2802 Box Assembly.

(a) In the main electronics compartment, do a General Visual Inspection on the forward

face of the E2 Support Post to find the location of Ground stud GD00422A, in

accordance with FIGURE 108.

1) If Ground Stud GD00422A location meets or exceeds the minimum dimension

shown, no change of the E2 Support Post is necessary.

2) If Ground Stud GD00422A location does not meet the minimum dimension

shown, change the E2 Support Post in accordance with FIGURE 110.

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(b) In the main electronics compartment, do a General Visual Inspection on the forward

face of the E3 Support Post to find if the Moisture Shroud Angle, Strap and Shroud

protrude in front of the Leading Edge Test Switch Bracket or E3 Support Post, in

accordance with FIGURE 109.

1) If the Moisture Shroud Angle, Strap and Shroud do not protrude in front of the

Leading Edge Test Switch Bracket or E3 Support Post, no change will be

necessary.

2) If the Moisture Shroud Angle, Strap and Shroud do protrude in front of the

Leading Edge Test Switch Bracket or E3 Support Post, change in accordance

with FIGURE 111.

NOTE: Only change the Moisture Shroud Angle and Strap. Do not change the

Shroud as this is required to protect the Avionics racks from water

incursion.

(c) Attach the J2802 Box Assembly on the E2 and E3 Support Posts and drill holes

through the J2802 Box Assembly and the E2 and E3 Support Posts in accordance

with FIGURE 99.

(d) Prepare the open holes and J2802 Box Assembly and Support Posts in accordance

with FIGURE 101.

(e) Install the J2802 Box Assembly on the support posts in accordance with FIGURE

103.

(f) Install the clamps and a bonding jumper wire in accordance with FIGURE 104.

(g) If the airplane is to be put in a serviceable condition before Work Package 3, do

these steps to close access.

1) In the main electronics compartment, install the kept drain pan where removed.

Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

NOTE: To complete this step, supply electrical power to the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure. When

completed, remove electrical power from the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure.

2) Close the access door to the main electronics compartment. Refer to

737-300/400/500 AMM 52-48-41 as an accepted procedure.

3) Put the airplane back to a serviceable condition.

c. WORK PACKAGE 3: INSTALLATION OF WIRES AND TEST OF THE CHANGED FUEL

SYSTEM

(1) Do these steps to get access.

(a) At the nose landing gear, install the down lock pin. Refer to 737-300/400/500 AMM

32-00-01 as an accepted procedure.

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(b) At the lower forward fuselage, below the main electronics compartment, open the

access door if it is closed. Refer to 737-300/400/500 AMM 52-48-41 as an accepted

procedure.

(c) If the Airstairs are retracted, do these steps to get access to the work area.

1) Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

2) Do the forward airstairs extension. Refer to 737-300/400/500 AMM 52-61-00 or

737-300/400/500 AMM 52-61-10 as an accepted procedure.

3) In the main electronics compartment, remove and keep the airstairs drain pan.

Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(e) In the main electronics compartment, disconnect the battery power cables from the

battery. Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(f) Remove and keep the moisture shroud from above the E3 rack. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) In the nose wheel well, remove and keep the right access panels, 3103R and 3105R.

Refer to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(h) In the flight compartment, move the first officer's seat to the forward position. Refer

to 737-300/400/500 AMM 25-10-00 as an accepted procedure.

(i) Remove and keep the ceiling linings adjacent and forward of the P6 load control

panel. Refer to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(j) Remove and keep the aft and mid center ceiling panels. Refer to 737-300/400/500

AMM 25-11-21 as an accepted procedure.

NOTE: As an optional procedure to get improved access to the P6 Top Disconnect

Panel, Galley No.1 can be removed. Refer to 737-300/400/500 AMM 25-31-11

as an accepted procedure.

(2) Do these steps to change the wiring in the airplane.

(a) In the flight compartment, at the P6 load control panel, loosen the relay panel, remove

and keep the covers, panels and relays in accordance with FIGURE 33.

(b) Between the P5 overhead and P6 top disconnect panels, change the wire bundle

W0036.

1) Group 17:

In accordance with FIGURE 34, FIGURE 38, FIGURE 39 and FIGURE 40.

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NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but

with wire provisions for Auxiliary Tank installation. It is necessary to do

the change given in FIGURE 39 and FIGURE 40, only if Auxiliary Tanks

with Fuel Boost pumps are installed on the airplane.

2) Group 18:

In accordance with FIGURE 34, FIGURE 41, FIGURE 42 and FIGURE 43.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but

with wire provisions for Auxiliary Tank installation. It is necessary to do

the change given in FIGURE 42 and FIGURE 43, only if Auxiliary Tanks

with Fuel Boost pumps are installed on the airplane.

(c) Between the P6 top disconnect panel and the P6 relay panel, change the wire bundle

W0044.

1) Group 17, Configuration 1:

In accordance with FIGURE 66, FIGURE 67 and FIGURE 69.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but

with wire provisions for Auxiliary Tank installation. It is necessary to do

the change given in FIGURE 69, only if Auxiliary Tanks with Fuel Boost

pumps are installed on the airplane.

2) Group 17, Configuration 2:

In accordance with FIGURE 66, FIGURE 68 and FIGURE 70.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but

with wire provisions for Auxiliary Tank installation. It is necessary to do

the change given in FIGURE 70, only if Auxiliary Tanks with Fuel Boost

pumps are installed on the airplane.

3) Group 18, Configuration 1:

In accordance with FIGURE 66, FIGURE 71 and FIGURE 73.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but

with wire provisions for Auxiliary Tank installation. It is necessary to do

the change given in FIGURE 73, only if Auxiliary Tanks with Fuel Boost

pumps are installed on the airplane.

4) Group 18, Configuration 2:

In accordance with FIGURE 66, FIGURE 72, and FIGURE 74.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but

with wire provisions for Auxiliary Tank installation. It is necessary to do

the change given in FIGURE 74, only if Auxiliary Tanks with Fuel Boost

pumps are installed on the airplane.

(d) Between the P5 overhead disconnect panel in the flight compartment and the J2802

Box Assembly in the main equipment compartment, change the wire bundle W0368

and install the wire bundle W1764 in accordance with FIGURE 105 and FIGURE 84.

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NOTE: Only install wires, W1764-004-20, W1764-005-20, and W1764-006-20,

shown in FIGURE 84, if AUX tanks with Fuel Boost Pumps are installed on

these airplanes.

(e) Change the wire bundle W0386 and install the wire bundle W1774 in accordance

with FIGURE 105 and FIGURE 87.

NOTE: Only install wires, W1774-004-20, W1774-005-20, and W1774-006-20,

shown in FIGURE 87, if AUX tanks with Fuel Boost Pumps are installed on

these airplanes.

(f) In the main electronics compartment, at the J2802 Box Assembly, install the relays

R3318, R3321, R3327, R3329, sleeve, grommets and tie straps in accordance with

FIGURE 107.

(g) In the flight compartment, at the P6 load control panel, install the kept relays, covers,

panels and the loosened relay panel in accordance with FIGURE 91.

(3) Do these steps to make sure the changed fuel control system operates correctly.

(a) In the main electronics compartment, connect the battery power cables to the battery.

Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(b) Apply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

(d) Do the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

NOTE: Operators that installed AUX tanks with Fuel Boost Pumps after delivery

will not have an Auxiliary Fuel Boost Pump Auto Shutoff Functional Test in

the AMM if a publications change request was not submitted. Contact Boeing

to obtain an Auxiliary Fuel Boost Pump Auto Shutoff Functional Test.

(e) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(4) Do these steps to close access.

(a) If removed, install Galley No.1. Refer to 737-300/400/500 AMM 25-31-11 as an

accepted procedure.

(b) In the flight compartment, install the kept aft and mid center ceiling panels. Refer to

737-300/400/500 AMM 25-11-21 as an accepted procedure.

(c) Install the kept ceiling linings adjacent and forward of the P6 load control panel. Refer

to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(d) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM

25-10-00 as an accepted procedure.

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(e) In the nose wheel well, install the kept right access panels, 3103R and 3105R. Refer

to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(f) In the main electronics compartment, install the kept moisture shrouds. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) Install the kept drain pan. Refer to 737-300/400/500 AMM 25-51-01 as an accepted

procedure.

NOTE: To complete this step, supply electrical power to the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure. When

completed, remove electrical power from the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure.

(h) Close the access door to the main electronics compartment. Refer to 737-300/400/500

AMM 52-48-41 as an accepted procedure.

(5) Put the airplane back to a serviceable condition.

3. Group 19-20:

PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS

NOTE: The production delivered fuel boost pump power relays were not polarity sensitive. The

fuel boost pump power control wire has not been connected on the same relay contact

on all 737 classic airplanes. Some airplanes have the power wire connected to contact

X1 of the relay, and the ground connected to contact X2 of the relay. Other airplanes

have the power wire connected to contact X2 of the relay, and the ground connected to

contact X1 of the relay. The Ground Fault Interrupter (GFI) relays are polarity sensitive

relays and requires power to be connected to contact X1 of the relays.

Airplane Groups that had the fuel boost pump power wire connected in production to

contact X2 and the ground wire connected to contact X1 are divided in two configurations.

Airplanes without the GFI service bulletin 737-28A1212 incorporated do not have the fuel

boost pump power wire moved from contact X2 to X1 and are placed in Configuration 1

airplanes. These airplanes need to replace the ground wire connected to contact X1 with

a new wire in accordance with this service bulletin. The airplanes with GFI service bulletin

737-28A1212 incorporated have the fuel boost pump power wire moved from contact X2

to X1 and are placed in Configuration 2 airplanes. These airplanes need to replace the

ground wire connected to contact X2 with a new wire in accordance with this service

bulletin.

For Airplane Groups that had the fuel boost pump power wire connected in production

to contact X1 and ground wire connected to contact X2 it is not necessary to swap the

wires between contact X1 and X2 when service bulletin 737-28A1212 is incorporated.

For these Airplane Groups it is only necessary to remove the ground wire from contact

X2 and install a new wire in accordance with this service bulletin. These airplanes have

only one configuration regardless if the GFI service bulletin 737-28A1212 has been

incorporated or not.

a. WORK PACKAGE 1: INSTALLATION OF WIRING IN THE J2802 BOX ASSEMBLY

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(1) Remove and keep the cover from the J2802 Box Assembly in accordance with FIGURE

2.

(2) Install the labels on the face of the J2802 Box Assembly, and the wire bundle, W1760 in

the J2802 Box Assembly in accordance with FIGURE 6, FIGURE 7 and FIGURE 8.

(3) Install the wire bundle W1770 in the J2802 Box Assembly in accordance with FIGURE

6, FIGURE 9 and FIGURE 10.

(4) Install the kept cover on the J2802 Box Assembly in accordance with FIGURE 11.

b. WORK PACKAGE 2: INSTALLATION OF THE J2802 BOX ASSEMBLY IN THE AIRPLANE

(1) Do these steps to get access.

(a) At the lower forward fuselage, below the main electronics compartment, open the

access door. Refer to 737-300/400/500 AMM 52-48-41 as an accepted procedure.

(b) Remove and keep the moisture shroud from above the access door to get access

to the wire bundle installation area. Refer to 737-300/400/500 AMM 25-51-01 as an

accepted procedure.

(2) Do these steps to install the J2802 Box Assembly.

(a) In the main electronics compartment, attach the J2802 Box Assembly on the E2 and

E3 Support Posts and drill holes in the E2 Support Post in accordance with FIGURE

13.

(b) Drill holes on the J2802 Box Assembly and the E3 Support Post in accordance with

FIGURE 14.

(c) Prepare the open holes in the E2 and E3 Support Posts and J2802 Box Assembly

in accordance with FIGURE 15.

(d) Install the J2802 Box Assembly on the E2 and E3 Support Posts in accordance with

FIGURE 17.

(e) Install the clamps and a bonding jumper wire in accordance with FIGURE 18.

(f) If the airplane is to be put in a serviceable condition before Work Package 3, do

these steps to close access.

1) In the main electronics compartment, install the kept moisture shroud above the

access door. Refer to 737-300/400/500 AMM 25-51-01 as an accepted

procedure.

2) Close the access door to the main electronics compartment. Refer to

737-300/400/500 AMM 52-48-41 as an accepted procedure.

c. WORK PACKAGE 3: INSTALLATION OF WIRES AND TEST OF THE CHANGED FUEL

SYSTEM

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(1) Do these steps to get access.

(a) At the nose landing gear, install the down lock pin. Refer to 737-300/400/500 AMM

32-00-01 as an accepted procedure.

(b) At the lower forward fuselage, below the main electronics compartment, open the

access door if it is closed. Refer to 737-300/400/500 AMM 52-48-41 as an accepted

procedure.

(c) Remove and keep the moisture shroud from above the access door, if it is not already

removed, to get access to the wire bundle installation area. Refer to 737-300/400/500

AMM 25-51-01 as an accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(e) In the main electronics compartment, disconnect the battery power cables from the

battery. Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(f) Remove and keep the moisture shroud from above the E3 rack. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) In the nose wheel well, remove and keep the right access panels, 3103R and 3105R.

Refer to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(h) In the flight compartment, move the first officer's seat to the forward position. Refer

to 737-300/400/500 AMM 25-10-00 as an accepted procedure.

(i) Remove and keep the ceiling linings adjacent and forward of the P6 load control

panel. Refer to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(j) Remove and keep the aft and mid center ceiling panels. Refer to 737-300/400/500

AMM 25-11-21 as an accepted procedure.

NOTE: As an optional procedure to get improved access to the P6 Top Disconnect

Panel, Galley No.1 can be removed. Refer to 737-300/400/500 AMM 25-31-11

as an accepted procedure.

(2) Do these steps to change the wiring in the airplane.

(a) In the flight compartment, at the P6 load control panel, loosen the relay panel, remove

and keep the covers, panels and relays in accordance with FIGURE 33.

(b) Between the P5 overhead and P6 top disconnect panels, change the wire bundle

W0036.

1) Group 19:

In accordance with FIGURE 34, FIGURE 35, FIGURE 36 and FIGURE 37.

2) Group 20:

In accordance with FIGURE 34, FIGURE 41, FIGURE 42 and FIGURE 43.

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BOEING SERVICE BULLETIN 737-28A1216
(c) Between the P6 top disconnect panel and the P6 relay panel, change the wire bundle

W0044.

1) Group 19, Configuration 1:

In accordance with FIGURE 66, FIGURE 75 and FIGURE 76.

2) Group 19, Configuration 2:

In accordance with FIGURE 66, FIGURE 75 and FIGURE 77.

3) Group 20, Configuration 1:

In accordance with FIGURE 66, FIGURE 78 and FIGURE 80.

4) Group 20, Configuration 2:

In accordance with FIGURE 66, FIGURE 79, and FIGURE 81.

(d) Between the P5 overhead disconnect panel in the flight compartment and the J2802

Box Assembly in the main electronics compartment, change the wire bundle W0368

and install the wire bundle W1764 in accordance with FIGURE 82 and FIGURE 84.

(e) Change the wire bundle W0386 and install the wire bundle W1774 in accordance

with FIGURE 82 and FIGURE 87.

(f) In the main electronics compartment, at the J2802 Box Assembly, install the relays

R3318, R3321, R3327, R3329, sleeve, grommets and tie straps in accordance with

FIGURE 89.

(g) In the flight compartment, at the P6 load control panel, install the kept relays, covers,

panels and the loosened relay panel in accordance with FIGURE 91.

(3) Do these steps to make sure the changed fuel control system operates correctly.

(a) In the main electronics compartment, connect the battery power cables to the battery.

Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(b) Apply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

(d) Do the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

(e) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(4) Do these steps to close access.

(a) If removed, install Galley No.1. Refer to 737-300/400/500 AMM 25-31-11 as an

accepted procedure.

(b) In the flight compartment, install the kept aft and mid center ceiling panels. Refer to

737-300/400/500 AMM 25-11-21 as an accepted procedure.

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BOEING SERVICE BULLETIN 737-28A1216
(c) Install the kept ceiling linings adjacent and forward of the P6 load control panel. Refer

to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(d) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM

25-10-00 as an accepted procedure.

(e) In the nose wheel well, install the kept right access panels, 3103R and 3105R. Refer

to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(f) In the main electronics compartment, install the kept moisture shrouds, above the

E3 rack and access door. Refer to 737-300/400/500 AMM 25-51-01 as an accepted

procedure.

(g) Close the access door to the main electronics compartment. Refer to 737-300/400/500

AMM 52-48-41 as an accepted procedure.

(5) Put the airplane back to a serviceable condition.

4. Group 14, 21-29, 31:

PART 4- AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL

TANKS, AND WITH AIRSTAIRS

NOTE: The production delivered fuel boost pump power relays were not polarity sensitive. The

fuel boost pump power control wire has not been connected on the same relay contact

on all 737 classic airplanes. Some airplanes have the power wire connected to contact

X1 of the relay, and the ground connected to contact X2 of the relay. Other airplanes

have the power wire connected to contact X2 of the relay, and the ground connected to

contact X1 of the relay. The Ground Fault Interrupter (GFI) relays are polarity sensitive

relays and require power to be connected to contact X1 of the relays.

Airplane Groups that had the fuel boost pump power wire connected in production to

contact X2 and the ground wire connected to contact X1 are divided in two configurations.

Airplane without the GFI service bulletin 737-28A1212 incorporated do not have the fuel

boost pump power wire moved from contact X2 to X1 and are placed in Configuration 1

airplanes. These airplanes need to replace the ground wire connected to contact X1 with

a new wire in accordance with this service bulletin. The airplanes with GFI service bulletin

737-28A1212 incorporated have the fuel boost pump power wire moved from contact X2

to X1 and are placed in Configuration 2 airplanes. These airplanes need to replace the

ground wire connected to contact X2 with a new wire in accordance with this service

bulletin.

For Airplane Groups that had the fuel boost pump power wire connected in production

to contact X1 and ground wire connected to contact X2 it is not necessary to swap the

wires between contact X1 and X2 when service bulletin 737-28A1212 is incorporated.

For these Airplane Groups it is only necessary to remove the ground wire from contact

X2 and install a new wire in accordance with this service bulletin. These airplanes have

only one configuration regardless if the GFI service bulletin 737-28A1212 has been

incorporated or not.

a. WORK PACKAGE 1: INSTALLATION OF WIRE BUNDLES IN THE J2802 BOX ASSEMBLY

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits

given in the Original Issue of this service bulletin can use the J2802 Box Assembly

received in the kit but they need to change the J2802 Box Assembly in accordance

with PART 6.

(1) If Top Kits given in the Original Issue of this service bulletin have been ordered and

received, change the J2802 Box Assembly in accordance with PART 6.

(2) Remove and keep the cover from the J2802 Box Assembly in accordance with FIGURE

96.

(3) Install wire bundle W1760 in the J2802 Box Assembly in accordance with FIGURE 96

and FIGURE 4.

(4) Install the wire bundle W1770 in the J2802 Box Assembly in accordance with FIGURE

96 and FIGURE 5.

(5) Install the kept cover on the J2802 Box Assembly in accordance with FIGURE 96.

b. WORK PACKAGE 2: INSTALLATION OF THE J2802 BOX ASSEMBLY IN THE AIRPLANE

(1) Do these steps to get access.

(a) At the lower forward fuselage, below the main electronics compartment, open the

access door. Refer to 737-300/400/500 AMM 52-48-41 as an accepted procedure.

(b) Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the forward airstairs extension if the airstairs are retracted. Refer to

737-300/400/500 AMM 52-61-00 or 737-300/400/500 AMM 52-61-10 as an accepted

procedure.

(d) In the main electronics compartment, remove and keep the drain pan. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(e) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(2) Do these steps to prepare for and to install the J2802 Box Assembly.

(a) In the main electronics compartment do a General Visual Inspection on the forward

face of the E2 Support Post to find the location of Ground stud GD00422A, in

accordance with FIGURE 108.

1) If Ground Stud GD00422A location meets or exceeds the minimum dimension

shown, no change of the E2 Support Post is necessary.

2) If Ground Stud GD00422A location does not meet the minimum dimension

shown, change the E2 Support Post in accordance with FIGURE 110.

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BOEING SERVICE BULLETIN 737-28A1216
(b) In the main electronics compartment do a General Visual Inspection on the forward

face of the E3 Support Post to find if the Moisture Shroud Angle and Strap protrude

in front of the Leading Edge Test Switch Bracket or E3 Support Post, in accordance

with FIGURE 109.

1) If the Moisture Shroud Angle and Strap do not protrude in front of the Leading

Edge Test Switch Bracket or E3 Support Post, no change will be necessary.

2) If the Moisture Shroud Angle and Strap do protrude in front of the Leading Edge

Test Switch Bracket or E3 Support Post, change in accordance with FIGURE

111.

NOTE: Only change the Moisture Shroud Angle and Strap. Do not change the

Shroud as this is required to protect the Avionics racks from water

incursion.

(c) Attach the J2802 Box Assembly on the E2 and E3 Support Posts and drill holes

through the J2802 Box Assembly and the E2 and E3 Support Posts in accordance

with FIGURE 98.

(d) Prepare the open holes in the E2 and E3 Support Posts and J2802 Box Assembly

in accordance with FIGURE 100.

(e) Install the J2802 Box Assembly on the E2 and E3 Support Posts in accordance with

FIGURE 102.

(f) Install the clamps and a bonding jumper in accordance with FIGURE 104.

(g) If the airplane is to be put in a serviceable condition before Work Package 3, do

these steps.

1) In the main electronics compartment, install the kept moisture shrouds if removed.

Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

2) Install the kept airstairs drain pan. Refer to 737-300/400/500 AMM 25-51-01 as

an accepted procedure.

NOTE: To complete this step, supply electrical power to the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure. When

completed, remove electrical power from the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure.

3) Close the access door to the main electronics compartment. Refer to

737-300/400/500 AMM 52-48-41 as an accepted procedure.

4) Put the airplane back to a serviceable condition.

c. WORK PACKAGE 3: INSTALLATION OF WIRES AND TEST OF THE CHANGED FUEL

SYSTEM

(1) Do these steps to get access.

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BOEING SERVICE BULLETIN 737-28A1216
(a) At the nose landing gear, install the down lock pin. Refer to 737-300/400/500 AMM

32-00-01 as an accepted procedure.

(b) At the lower forward fuselage, below the main electronics compartment, open the

access door if it is closed. Refer to 737-300/400/500 AMM 52-48-41 as an accepted

procedure.

(c) If the Airstairs are retracted, do these steps to get access to the work area.

1) Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

2) Do the forward airstairs extension. Refer to 737-300/400/500 AMM 52-61-00 or

737-300/400/500 AMM 52-61-10 as an accepted procedure.

3) In the main equipment compartment, remove and keep the airstairs drain pan

if it is not already removed. Refer to 737-300/400/500 AMM 25-51-01 as an

accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(e) In the main electronics compartment, disconnect the battery power cables from the

battery. Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(f) Remove and keep the moisture shroud from above the E3 rack if it is not already

removed. Refer to the 737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) In the nose wheel well, remove and keep the right access panels, 3103R and 3105R.

Refer to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(h) In the flight compartment, move the first officer's seat to the forward position. Refer

to 737-300/400/500 AMM 25-10-00 as an accepted procedure.

(i) Remove and keep the ceiling linings adjacent and forward of the P6 load control

panel. Refer to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(j) Remove and keep the aft and mid center ceiling panels. Refer to 737-300/400/500

AMM 25-11-21 as an accepted procedure.

NOTE: As an optional procedure to get improved access to the P6 Top Disconnect

Panel, Galley No.1 can be removed. Refer to 737-300/400/500 AMM 25-31-11

as an accepted procedure.

(2) Do these steps to change the wire bundles in the airplane.

(a) In the flight compartment, at the P6 load control panel, loosen the relay panel, remove

and keep the covers, panels and relays in accordance with FIGURE 19.

(b) Between the P5 overhead and P6 top disconnect panels, change the wire bundle

W0036.

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BOEING SERVICE BULLETIN 737-28A1216
1) Group 14:

In accordance with FIGURE 20 and FIGURE 30.

2) Group 21:

In accordance with FIGURE 20 and FIGURE 21.

3) Group 22-23:

In accordance with FIGURE 20 and FIGURE 22.

4) Group 24:

In accordance with FIGURE 20 and FIGURE 23.

5) Group 25:

In accordance with FIGURE 20 and FIGURE 24.

6) Group 26:

In accordance with FIGURE 20 and FIGURE 25.

7) Group 31:

In accordance with FIGURE 20 and FIGURE 26.

8) Group 27-28:

In accordance with FIGURE 20 and FIGURE 27.

9) Group 29:

In accordance with FIGURE 20 and FIGURE 28.

(c) Between the P6 top disconnect panel and the P6 relay panel, change the wire bundle

W0044.

1) Group 14, Configuration 1:

In accordance with FIGURE 44 and FIGURE 60.

2) Group 14, Configuration 2:

In accordance with FIGURE 44 and FIGURE 61.

3) Group 21:

In accordance with FIGURE 44 and FIGURE 45.

4) Group 22, Configuration 1:

In accordance with FIGURE 44 and FIGURE 46.

5) Group 22, Configuration 2:

In accordance with FIGURE 44 and FIGURE 47.

6) Group 23:

In accordance with FIGURE 44 and FIGURE 48.

7) Group 24, 26:

In accordance with FIGURE 44 and FIGURE 51.

8) Group 25, Configuration 1:

In accordance with FIGURE 44 and FIGURE 52.

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9) Group 25, Configuration 2:

In accordance with FIGURE 44 and FIGURE 53.

10) Group 31:

In accordance with FIGURE 44 and FIGURE 54.

11) Group 27:

In accordance with FIGURE 44 and FIGURE 55.

12) Group 28, Configuration 1:

In accordance with FIGURE 44 and FIGURE 62.

13) Group 28, Configuration 2:

In accordance with FIGURE 44 and FIGURE 63.

14) Group 29, Configuration 1:

In accordance with FIGURE 44 and FIGURE 56.

15) Group 29, Configuration 2:

In accordance with FIGURE 44 and FIGURE 57.

(d) Between the flight and main electronics compartments, change the wire bundle

W0368 and install the wire bundle W1764 In accordance with FIGURE 105 and

FIGURE 83.

(e) Change the wire bundle W0386 and install the wire bundle W1774:

1) Group 14, 21-25, 27-29, 31:

In accordance with FIGURE 105 and FIGURE 86.

2) Group 26:

In accordance with FIGURE 105 and FIGURE 85.

(f) In the main equipment compartment, at the J2802 box assembly, install the relays

R3318, R3321, sleeve, grommets and tie straps In accordance with FIGURE 106.

(g) In the flight compartment, at the P6 load control panel, install the kept relays, covers,

panels and the loosened relay panel In accordance with FIGURE 90.

(3) Do these steps to make sure the changed fuel control system operates correctly.

(a) In the main electronics compartment, connect the battery power cables to the battery.

Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(b) Apply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

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BOEING SERVICE BULLETIN 737-28A1216
(4) Do these steps to close access.

(a) If removed, install Galley No.1. Refer to 737-300/400/500 AMM 25-31-11 as an

accepted procedure.

(b) In the flight compartment, install the kept aft and mid center ceiling panels. Refer to

737-300/400/500 AMM 25-11-21 as an accepted procedure.

(c) Install the kept ceiling linings adjacent and forward of the P6 load control panel. Refer

to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(d) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM

25-10-00 as an accepted procedure.

(e) In the nose wheel well, install the kept right access panels, 3103R and 3105R. Refer

to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(f) In the main electronics compartment, install the kept moisture shrouds if removed.

Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) Install the kept drain pan if removed. Refer to 737-300/400/500 AMM 25-51-01 as

an accepted procedure.

NOTE: To complete this step, supply electrical power to the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure. When

completed, remove electrical power from the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure.

(h) Close the access door to the main electronics compartment. Refer to 737-300/400/500

AMM 52-48-41 as an accepted procedure.

(5) Put the airplane back to a serviceable condition.

5. Group 30:

PART 5 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND WITH

AIRSTAIRS

NOTE: The production delivered fuel boost pump power relays were not polarity sensitive. The

fuel boost pump power control wire has not been connected on the same relay contact

on all 737 classic airplanes. Some airplanes have the power wire connected to contact

X1 of the relay, and the ground connected to contact X2 of the relay. Other airplanes

have the power wire connected to contact X2 of the relay, and the ground connected to

contact X1 of the relay. The Ground Fault Interrupter (GFI) relays are polarity sensitive

relays and requires power to be connected to contact X1 of the relays.

Airplane Groups that had the fuel boost pump power wire connected in production to

contact X2 and the ground wire connected to contact X1 are divided in two configurations.

Airplanes without the GFI service bulletin 737-28A1212 incorporated do not have the fuel

boost pump power wire moved from contact X2 to X1 and are placed in Configuration 1

airplanes. These airplanes need to replace the ground wire connected to contact X1 with

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BOEING SERVICE BULLETIN 737-28A1216
a new wire in accordance with this service bulletin. The airplanes with GFI service bulletin

737-28A1212 incorporated have the fuel boost pump power wire moved from contact X2

to X1 and are placed in Configuration 2 airplanes. These airplanes need to replace the

ground wire connected to contact X2 with a new wire in accordance with this service

bulletin.

For Airplane Groups that had the fuel boost pump power wire connected in production

to contact X1 and ground wire connected to contact X2 it is not necessary to swap the

wires between contact X1 and X2 when service bulletin 737-28A1212 is incorporated.

For these Airplane Groups it is only necessary to remove the ground wire from contact

X2 and install a new wire in accordance with this service bulletin. These airplanes have

only one configuration regardless if the GFI service bulletin 737-28A1212 has been

incorporated or not.

a. WORK PACKAGE 1: INSTALLATION OF WIRING IN THE J2802 BOX ASSEMBLY

NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits

given in the Original Issue of this service bulletin can use the J2802 Box Assembly

received in the kit but they need to change the J2802 Box Assembly in accordance

with PART 6.

(1) If Top Kits given in the Original Issue of this service bulletin have been ordered and

received change the J2802 Box Assembly in accordance with PART 6.

(2) Remove and keep the cover from the J2802 Box Assembly in accordance with FIGURE

97.

(3) Install the labels on the face of the J2802 Box Assembly, and the wire bundle, W1760 in

the J2802 Box Assembly in accordance with FIGURE 97, FIGURE 7 and FIGURE 8.

(4) Install the wire bundle W1770 in the J2802 Box Assembly in accordance with FIGURE

97, FIGURE 9 and FIGURE 10.

(5) Install the kept cover on the J2802 Box Assembly in accordance with FIGURE 97.

b. WORK PACKAGE 2: INSTALLATION OF THE J2802 BOX ASSEMBLY IN THE AIRPLANE

(1) Do these steps to get access.

(a) At the lower forward fuselage, below the main electronics compartment, open the

access door. Refer to 737-300/400/500 AMM 52-48-41 as an accepted procedure.

(b) Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the forward airstairs extension if the airstairs are retracted. Refer to

737-300/400/500 AMM 52-61-00 or 737-300/400/500 AMM 52-61-10 as an accepted

procedure.

(d) In the main electronics compartment, remove and keep the drain pan. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

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(e) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(2) Do these steps to prepare for and to install the J2802 box assembly.

(a) In the main electronics compartment do a General Visual Inspection on the forward

face of the E2 Support Post to find the location of Ground stud GD00422A, in

accordance with FIGURE 108.

1) If Ground Stud GD00422A location meets or exceeds the minimum dimension

shown, no change of the E2 Support Post is necessary.

2) If Ground Stud GD00422A location does not meet the minimum dimension

shown, change the E2 Support Post in accordance with FIGURE 110.

(b) In the main electronics compartment do a General Visual Inspection on the forward

face of the E3 Support Post to determine if the Moisture Shroud Angle and Strap

protrude in front of the Leading Edge Test Switch Bracket or E3 Support Post, in

accordance with FIGURE 109.

1) If the Moisture Shroud Angle and Strap do not protrude in front of the Leading

Edge Test Switch Bracket or E3 Support Post, no change will be necessary.

2) If the Moisture Shroud Angle and Strap do protrude in front of the Leading Edge

Test Switch Bracket or E3 Support Post, change in accordance with FIGURE

111.

NOTE: Only change the Moisture Shroud Angle and Strap. Do not change the

Shroud as this is required to protect the Avionics racks from water

incursion.

(c) Attach the J2802 Box Assembly on the E2 and E3 Support Posts and drill holes on

the J2802 Box Assembly and the E2 and E3 Support Posts in accordance with

FIGURE 99.

(d) Prepare the open holes in the E2 and E3 Support Posts and J2802 Box Assembly

in accordance with FIGURE 101.

(e) Install the J2802 Box Assembly on the E2 and E3 Support Posts in accordance with

FIGURE 103.

(f) Install the clamps and a bonding jumper wire in accordance with FIGURE 104.

(g) If the airplane is to be put in a serviceable condition before Work Package 3, do

these steps to close access.

1) In the main electronics compartment, install the kept airstairs drain pan. Refer

to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

NOTE: To complete this step, supply electrical power to the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure. When

completed, remove electrical power from the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure.

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2) Close the access door to the main electronics compartment. Refer to

737-300/400/500 AMM 52-48-41 as an accepted procedure.

3) Put the airplane back to a serviceable condition.

c. WORK PACKAGE 3: INSTALLATION OF WIRES AND TEST OF THE CHANGED FUEL

SYSTEM

(1) Do these steps to get access.

(a) At the nose landing gear, install the down lock pin. Refer to 737-300/400/500 AMM

32-00-01 as an accepted procedure.

(b) At the lower forward fuselage, below the main electronics compartment, open the

access door if it is closed. Refer to 737-300/400/500 AMM 52-48-41 as an accepted

procedure.

(c) If the Airstairs are retracted, do these steps to get access to the work area.

1) Supply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

2) Do the forward airstairs extension. Refer to 737-300/400/500 AMM 52-61-00 or

737-300/400/500 AMM 52-61-10 as an accepted procedure.

3) In the main electronics compartment, remove and keep the airstairs drain pan

if it is not already removed. Refer to 737-300/400/500 AMM 25-51-01 as an

accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(e) In the main electronics compartment, disconnect the battery power cables from the

battery. Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(f) Remove and keep the moisture shroud from above the E3 rack. Refer to

737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) In the nose wheel well, remove and keep the right access panels, 3103R and 3105R.

Refer to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(h) In the flight compartment, move the first officer's seat to the forward position. Refer

to 737-300/400/500 AMM 25-10-00 as an accepted procedure.

(i) Remove and keep the ceiling linings adjacent and forward of the P6 load control

panel. Refer to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(j) Remove and keep the aft and mid center ceiling panels. Refer to 737-300/400/500

AMM 25-11-21 as an accepted procedure.

NOTE: As an optional procedure to get improved access to the P6 Top Disconnect

Panel, Galley No.1 can be removed. Refer to 737-300/400/500 AMM 25-31-11

as an accepted procedure.

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(2) Do these steps to change the wiring in the airplane.

(a) In the flight compartment, at the P6 load control panel, loosen the relay panel, remove

and keep the covers, panels and relays in accordance with FIGURE 33.

(b) Between the P5 overhead and P6 top disconnect panels, change the wire bundle

W0036 In accordance with FIGURE 34, FIGURE 35, FIGURE 36 and FIGURE 37.

(c) Between the P6 top disconnect panel and the P6 relay panel, change the wire bundle

W0044.

1) Group 30, Configuration 1:

In accordance with FIGURE 66, FIGURE 75 and FIGURE 76.

2) Group 30, Configuration 2:

In accordance with FIGURE 66, FIGURE 75 and FIGURE 77.

(d) Between the P5 overhead disconnect panel in the flight compartment and the J2802

Box Assembly in the main electronics compartment, change the wire bundle W0368

and install the wire bundle W1764 in accordance with FIGURE 105 and FIGURE 84.

(e) Change the wire bundle W0386 and install the wire bundle W1774 in accordance

with FIGURE 105 and FIGURE 87.

(f) In the main electronics compartment, at the J2802 Box Assembly, install the relays

R3318, R3321, R3327, R3329, sleeve, grommets and tie straps in accordance with

FIGURE 107.

(g) In the flight compartment, at the P6 load control panel, install the kept relays, covers,

panels and the loosened relay panel in accordance with FIGURE 91.

(3) Do these steps to make sure the changed fuel control system operates correctly.

(a) In the main equipment compartment, connect the battery power cables to the battery.

Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(b) Apply electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as

an accepted procedure.

(c) Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

(d) Do the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test. Refer to

737-300/400/500 AMM 28-22-00 as an accepted procedure.

(e) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(4) Do these steps to close access.

(a) If removed, install Galley No.1. Refer to 737-300/400/500 AMM 25-31-11 as an

accepted procedure.

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(b) In the flight compartment, install the kept aft and mid center ceiling panels. Refer to

737-300/400/500 AMM 25-11-21 as an accepted procedure.

(c) Install the kept ceiling linings adjacent and forward of the P6 load control panel. Refer

to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(d) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM

25-10-00 as an accepted procedure.

(e) In the nose wheel well, install the kept right access panels, 3103R and 3105R. Refer

to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(f) In the main electronics compartment, install the kept moisture shrouds if removed.

Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) Install the kept drain pan. Refer to 737-300/400/500 AMM 25-51-01 as an accepted

procedure.

NOTE: To complete this step, supply electrical power to the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure. When

completed, remove electrical power from the airplane. Refer to

737-300/400/500 AMM 24-22-00 as an accepted procedure.

(h) Close the access door to the main electronics compartment. Refer to 737-300/400/500

AMM 52-48-41 as an accepted procedure.

(5) Put the airplane back to a serviceable condition.

6. Group 14, 17-18, 21-31:

PART 6 - CHANGE THE J2802 BOX ASSEMBLY TO FIT AIRPLANES WITH AIRSTAIRS

NOTE: Operators that have airplanes with Airstairs that ordered and received the Top Kits given

in the Original Issue of this service bulletin can use the J2802 Box Assembly received in

the kit but they need to change the J2802 Box Assembly.

a. Change the J2802 Box Assembly:

(1) Group 14, 21-29, 31:

In accordance with FIGURE 92 and FIGURE 94.

(2) Group 17-18, 30:

In accordance with FIGURE 93 and FIGURE 95.

7. Group 1-16, 21-29, 31:

PART 7- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED

THE ORIGINAL ISSUE OF THE SERVICE BULLETIN

NOTE: Only airplanes that were in Group 1 through 16 of the Original Issue of this service bulletin

and incorporated the changes provided in the Original Issue of the service bulletin have

to do the work provided in PART 7.

a. Install Labels on rear of J2802 Box Assembly.

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(1) Group 1-13, 15-16:

In accordance with FIGURE 3.

(2) Group 14, 21-29, 31:

In accordance with FIGURE 92.

b. Change wire W1760 termination at switch S3318 in accordance with FIGURE 4.

c. Change wire W1770 termination at switch S3321 in accordance with FIGURE 5.

d. Inspect the imprinted text on the ID tape of wire W368-031-20 installed as specified in the

applicable figures that follow. Correct any incorrectly identified wires in accordance with

FIGURE 83.

(1) Group 1-13, 15-16:

Installed in accordance with FIGURE 82 and FIGURE 83.

(2) Group 14, 21-29, 31:

Installed in accordance with FIGURE 105 and FIGURE 83.

e. Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to 737-300/400/500 AMM

28-22-00 as an accepted procedure.

8. Group 17-18:

PART 8- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED

THE ORIGINAL ISSUE OF THE SERVICE BULLETIN

NOTE: Only airplanes that were in Group 17 and 18 of the Original Issue of this service bulletin

and incorporated the changes provided in the Original Issue of the service bulletin have

to do the work provided in PART 8.

a. Install Labels on rear of J2802 Box Assembly in accordance with FIGURE 93.

b. Change wire W1760 termination at switch S3318 in accordance with FIGURE 7 and FIGURE

8.

NOTE: Airplanes in Group 17 and 18 have been delivered without Auxiliary Tanks but with

wire provisions for Auxiliary Tank Installation. It was necessary to do the change

given in FIGURE 7 of the Original Issue of the service bulletin only if Auxiliary Tank

with Fuel Boost Pumps were installed on the airplane. If Auxiliary Tank is not installed,

it is not necessary to do the changes of wire W1760 in accordance with FIGURE 7

of this revision.

c. Change wire W1770 termination at switch S3321 in accordance with FIGURE 9 and FIGURE

10.

NOTE: Airplanes in Group 17 and 18 have been delivered without Auxiliary Tanks but with

wire provisions for Auxiliary Tank Installation. It was necessary to do the change

given in FIGURE 9 of the Original Issue of the service bulletin only if Auxiliary Tank

with Fuel Boost Pumps were installed on the airplane. If Auxiliary Tank is not installed,

it is not necessary to do the changes of wire W1770 in accordance with FIGURE 9

of this revision.

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d. Inspect the imprinted text on the ID tape of wire W368-031-20 installed in accordance with

FIGURE 105 and FIGURE 84. Correct any incorrectly identified wires in accordance with

FIGURE 84.

e. Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to 737-300/400/500 AMM

28-22-00 as an accepted procedure.

f. Do the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test for airplanes that have an

Auxiliary Tank Installed. Refer to 737-300/400/500 AMM 28-22-00 as an accepted procedure.

9. Group 19-20, 30:

PART 9- CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES THAT INCORPORATED

THE ORIGINAL ISSUE OF THE SERVICE BULLETIN

NOTE: Only airplanes that were in Group 19 through 20 of the Original Issue of this service

bulletin and incorporated the changes provided in the Original Issue of the service bulletin

have to do the work provided in PART 9.

a. Install Labels on rear of J2802 Box Assembly.

(1) Group 19-20:

In accordance with FIGURE 6.

(2) Group 30:

In accordance with FIGURE 93.

b. Change wire W1760 termination at switch S3318 in accordance with FIGURE 7 and FIGURE

8.

c. Change wire W1770 termination at switch S3321 in accordance with FIGURE 9 and FIGURE

10.

d. Inspect the imprinted text on the ID tape of wire W368-031-20 installed as specified in the

applicable figures that follow. Correct any incorrectly identified wires in accordance with

FIGURE 84.

(1) Group 19-20:

Installed in accordance with FIGURE 82 and FIGURE 84.

(2) Group 30:

Installed in accordance with FIGURE 105 and FIGURE 84.

e. Do the Center Fuel Boost Pump Auto Shutoff Functional Test. Refer to 737-300/400/500 AMM

28-22-00 as an accepted procedure.

f. Do the Auxiliary Fuel Boost Pump Auto Shutoff Functional Test. Refer to 737-300/400/500

AMM 28-22-00 as an accepted procedure.

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This Figure applies only to: Group 1-13, 15-16.

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 airplane.

NOTE: The J2802 Box Assembly is available in the J2802 Box Installation Kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Disassemble J2802 Box Assembly 65C38484-10 1

Remove / Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

2 Remove / Keep Cover 65C38484-6 1

FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19-20.

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 airplane.

NOTE: The J2802 Box Assembly is available in the J2802 Box Installation Kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Disassemble J2802 Box Assembly 65C38484-11 1

Remove / Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

2 Remove / Keep Cover 65C38484-6 1

FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER

(SHEET 1 OF 1)

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This Figure applies only to: Group 1-13, 15-16.

FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802

BOX ASSEMBLY

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
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 each airplane.

NOTE: Parts are available in the supplemental kit 65C37854-16. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (New) Label-CTR-L 65C38484-31 1 (a)

Apply Top Coat BAC5710, TYPE 41 -

2 Install (New) Label-CTR-R 65C38484-32 1 (b)

Apply Top Coat BAC5710, TYPE 41 -

3 Install (New) Label-NOT-USED 65C38484-33 2 (c)

Apply Top Coat BAC5710, TYPE 41 -

Label-TEST SWITCH- 65C38484-36 1 (d)

ES

4 Install (New)

Label-AUTO SHUTOFF 65C38484-37 1 (e)

Apply Top Coat BAC5710, Type 41 -

FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802

BOX ASSEMBLY

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SWPM 20-

10-11 as an accepted procedure.

5 Install Wires W1760, W1770 -

(a) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-L". Refer to SWPM 20-10-11 as an accepted procedure..

(b) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-R". Refer to SWPM 20-10-11 as an accepted procedure.

(c) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "NOT USED". Refer to SWPM 20-10-11 as an accepted procedure.

(d) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "TEST" and one with "SWITCHES". Refer to SWPM 20-10-11 as an accepted

procedure.

(e) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "AUTO" and one with "SHUTOFF". Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802

BOX ASSEMBLY

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-105. The wire kits possibly has more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11and SWPM 20-10-12 as accepted procedures.

BMS13-58 Type 1, Class 1, 9

AWG 20

1 Wire

Use white color tie material. Refer

to SWPM 20-10-11 as an accepted

procedure.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Pin BACC47CN1S 3

Install less than 4 inches from the

connector to identify the wire bundle. Refer to SWPM 20-10-11 as

an accepted procedure.

3 ID Tape 61-74478-10501 1

Install at less than 6 inches from

the connector to identify the connector.

61-74478-10502 1

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

61-11 as accepted procedures.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 20

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.(a)

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an

accepted procedure.

M39029/11-145 or M39029- 3

11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an

accepted procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on

each wire end. Refer to SWPM 20-

10-14 and SWPM 20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 2 OF 3)

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FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-20-11 as an

accepted procedure.

8 Contact BACC47DE1A 2

Refer to SWPM 20-81-19 as an

accepted procedure.

9 Contact, Socket BACC47ER1 4

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from

the connector to identify the connector.

ID Tape 61-74478-10503 1

(a) Connect wire, W1760-001-20, '=B', to one of the two terminals of Circuit Breaker C3318, marked '1' or '2'.

Connect wire, W1760-002-20, '=L', to the other terminal of Circuit Breaker C3318.

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 3 OF 3)

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This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 1 OF 3)

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REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-107. The wire kits possibly has more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58 Type 1, Class 1, 9

AWG 20

1 Wire

Use white color tie material. Refer

to SWPM 20-10-11 as an accepted

procedure.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Pin BACC47CN1S 3

Install adjacent to the connector to

identify the wire bundle. Refer to

SWPM 20-10-11 as an accepted

procedure.

3 ID Tape 61-74478-10701 1

Install at less than 6 inches from

the connector to identify the connector.

61-74478-10702 1

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

61-11 as accepted procedures.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 20

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.(a)

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an

accepted procedure.

M39029/11-145 or M39029- 3

11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an

accepted procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on

each wire end. Refer to SWPM 20-

10-14 and SWPM 20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 2 OF 3)

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FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-20-11 as an

accepted procedure.

8 Contact BACC47DE1A 2

Refer to SWPM 20-81-19 as an

accepted procedure.

9 Contact, Socket BACC47ER1 4

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from

the connector to identify the connector.

ID Tape 61-74478-10703 1

(a) Connect wire, W1770-001-20, '=B', to one of the two terminals of Circuit Breaker C3320, marked '1' or '2'.

Connect wire, W1770-002-20, '=L', to the other terminal of Circuit Breaker C3320.

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 3 OF 3)

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This Figure applies only to: Group 19-20.

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
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 each airplane.

NOTE: Parts are available in the supplemental kit 65C37854-16. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (New) Label-CTR-L 65C38484-31 1 (a)

Apply Top Coat BAC5710, TYPE 41 -

2 Install (New) Label-CTR-R 65C38484-32 1 (b)

Apply Top Coat BAC5710, TYPE 41 -

3 Install (New) Label-AUX-AFT 65C38484-35 1 (c)

Apply Top Coat BAC5710, TYPE 41 -

4 Install (New) Label-AUX-FWD 65C38484-34 1 (d)

Apply Top Coat BAC5710, TYPE 41 -

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY

(SHEET 2 OF 3)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

Label-TEST SWITCH- 65C38484-36 1 (e)

ES

5 Install (New)

Label-AUTO SHUTOFF 65C38484-37 1 (f)

Apply Top Coat BAC5710, TYPE 41 -

Refer to SWPM 20-

10-11 as an accepted procedure.

6 Install Wires W1760, W1770 -

(a) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-L". Refer to SWPM 20-10-11 as an accepted procedure..

(b) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-R". Refer to SWPM 20-10-11 as an accepted procedure.

(c) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "AUX-AFT". Refer to SWPM 20-10-11 as an accepted procedure.

(d) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "AUX-FWD". Refer to SWPM 20-10-11 as an accepted procedure.

(e) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "TEST" and one with "SWITCHES". Refer to SWPM 20-10-11 as an accepted

procedure.

(f) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "AUTO" and one with "SHUTOFF". Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

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This Figure applies only to: Group 17-20, 30.

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 and Group 18 have been delivered without Auxiliary Tanks but with wire provisions

for Auxiliary Tank installation. Accomplish change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-106. The wire kits possibly has more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58 Type 1, Class 1, 9

AWG 20

1 Wire

Use white color tie material. Refer

to SWPM 20-10-11 as an accepted

procedure.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Pin BACC47CN1S 3

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.(a)

3 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an

accepted procedure.

M39029/11-145 or M39029- 3

11-145

4 Contact, Pin

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.

5 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an

accepted procedure.

6 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on

each wire end. Refer to SWPM 20-

10-14 and SWPM 20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an

accepted procedure.

7 Contact BACC47DE1A 2

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-19 as an

accepted procedure.

8 Contact, Socket BACC47ER1 4

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from

the connector to identify the connector.

ID Tape 61-74478-10601 1

(a) Connect wire, W1760-011-20, '=B', to one of the two terminals of Circuit Breaker C3318, marked '1' or '2'.

Connect wire, W1760-012-20, '=L', to the other terminal of Circuit Breaker C3318.

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-106. The wire kit possibly has more parts

than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58 Type 1, Class 1, 9

AWG 20

1 Wire

Use white color tie material. Refer

to SWPM 20-10-11 as an accepted

procedure.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Pin BACC47CN1S 3

Install adjacent to the connector to

identify the wire bundle. Refer to

SWPM 20-10-11 as an accepted

procedure.

3 ID Tape 61-74478-10602 1

Install at less than 6 inches from

the connector to identify the connector.

61-74478-10502 1

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

61-11 as accepted procedures.(a)

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.(b)

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an

accepted procedure.

M39029/11-145 or M39029- 3

11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an

accepted procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on

each wire end. Refer to SWPM 20-

10-14 and SWPM 20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-20-11 as an

accepted procedure.

8 Contact BACC47DE1A 2

Refer to SWPM 20-81-19 as an

accepted procedure.

9 Contact, Socket BACC47ER1 4

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from

the connector to identify the connector.

ID Tape 61-74478-10503 1

(a) For airplanes with wire provisions for AUX Tank, and with no AUX tank installed, use Qty (20) MS27488-

20-1 seal plugs for connector D5208J.

(b) Connect wire, W1760-001-20, '=B', to one of the two terminals of Circuit Breaker C3318, marked '1' or '2'.

Connect wire, W1760-002-20, '=L', to the other terminal of Circuit Breaker C3318.

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

NOTE: Airplanes in Group 17 and Group 18 have been delivered without Auxiliary Tanks but with wire provisions

for Auxiliary Tank installation. Accomplish change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-108. The wire kit possibly has more parts

than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58 Type 1, Class 1, 9

AWG 20

1 Wire

Use white color tie material. Refer

to SWPM 20-10-11 as an accepted

procedure.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Pin BACC47CN1S 3

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.(a)

3 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an

accepted procedure.

M39029/11-145 or M39029- 3

11-145

4 Contact, Pin

Refer to SWPM 20-30-00 and

SWPM 20-30-11 as accepted procedures.

5 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an

accepted procedure.

6 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on

each wire end. Refer to SWPM 20-

10-14 and SWPM 20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an

accepted procedure.

7 Contact BACC47DE1A 2

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-19 as an

accepted procedure.

8 Contact, Socket BACC47ER1 4

Use one in each empty contact

hole of the connector. Refer to

SWPM 20-60-08 and SWPM 20-

81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from

the connector to identify the connector.

ID Tape 61-74478-10801 1

(a) Connect wire, W1770-011-20, '=B', to one of the two terminals of Circuit Breaker C3320, marked '1' or '2'.

Connect wire, W1770-012-20, '=L', to the other terminal of Circuit Breaker C3320.

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-108. The wire kit possibly has more parts

than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-

12 as accepted procedures.

BMS13-58 Type 1, Class 9

1, AWG 20

1 Wire

Use white color tie material. Refer to SWPM

20-10-11 as an accepted procedure.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an accepted

procedure.

2 Contact, Pin BACC47CN1S 3

Install adjacent to the connector to identify

the wire bundle. Refer to SWPM 20-10-11

as an accepted procedure.

3 ID Tape 61-74478-10802 1

Install at less than 6 inches from the connector to identify the connector.61-74478-10702 1

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-61-11 as accepted procedures.(a)

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.(b)

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an accepted

procedure.

M39029/11-145 or 3

M39029-11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an accepted

procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on each wire

end. Refer to SWPM 20-10-14 and SWPM

20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an accepted

procedure.

8 Contact BACC47DE1A 2

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-19 as an accepted

procedure.

Contact, Sock- BACC47ER1 4

et

9

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from the connector to identify the connector.ID Tape 61-74478-10703 1

(a) For airplanes with wire provisions for AUX Tank, and with no AUX tank installed, use Qty (20) MS27488-

20-1 seal plugs for connector D5210J.

(b) Connect wire, W1770-001-20, '=B', to one of the two terminals of Circuit Breaker C3320, marked '1'

or '2'. Connect wire, W1770-002-20, '=L', to the other terminal of Circuit Breaker C3320.

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-13, 15-16, 19-20.

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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SWPM 20-

10-04 as an acceptable procedure.

J2802 BOX ASSEM- 65C38484-( ) 1

BLY

1 Clean

On the J2802 Box

Assembly.

2 Put COVER 65C38484-6 1

Install (Kept) BOLT BACS12HN3-8 6

Install (Kept) WASHER NAS1149F0363P 6

FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER

(SHEET 1 OF 1)

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This Figure applies only to: Group 1-13, 15-16.

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Part is in the kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With clamps when

the J2802 Box Assembly is level on

the E2 and E3 Support Posts.

1 Attach KIT ASSY - J2802 BOX 65C38484-10 1

0.161-0.164 inch

dia. interference fit

holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

2 Drill HOLE - 3

0.218-0.229 inch

dia. holes in accordance with 737-300

SRM 51-40-05, 737-

400 SRM 51-40-05,

or 737-500 SRM 51-

40-05.

3 Drill HOLE - 2

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19-20.

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Part is in the kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With clamps when

the J2802 Box Assembly is level on

the E2 and E3 Support Posts.

1 Attach KIT ASSY - J2802 BOX 65C38484-11 1

0.161-0.164 inch

dia. interference fit

holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

2 Drill HOLE - 3

0.218-0.229 inch

dia. holes in accordance with 737-300

SRM 51-40-05, 737-

400 SRM 51-40-05,

or 737-500 SRM 51-

40-05.

3 Drill HOLE - 2

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the E3 Support

Post.

J2802 BOX ASSEM- 65C38484-( ) 1

BLY

1 Align

0.161-0.164 inch

dia. interference fit

holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

2 Drill HOLE - 3

0.218-0.229 inch

dia. holes in accordance with 737-300

SRM 51-40-05, 737-

400 SRM 51-40-05,

or 737-500 SRM 51-

40-05.

3 Drill HOLE - 4

FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

From the E2 and E3

Support Posts.

J2802 BOX ASSEM- 65C38484-( ) 1

BLY

1 Remove

Refer to SOPM 20-

30-03 as an accepted procedure.

2 Clean HOLE - 4

By abrasive cleaning

for faying surface

bonding. (a)

3 Clean HOLE - 14

(a) Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-13, 15-16.

FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: Part is in the kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank

and J2802 Box faying surface. (a)

1 Apply SEALANT BMS5-95 -

Install (New) KIT ASSY - J2802 BOX 65C38484-10 1

BOLT, PROTRUDING BACB30NX5HK6 6

HD

Install (New)

SPACERS FOR RIV- NAS42DD6-16FC 6

ETS

Install (New)

Install (New) COLLAR, PRELOAD BACC30BH5 6

2 Tighten COLLAR, PRELOAD BACC30BH5 6

On the bolt heads.

Refer to SOPM 20-

50-19 as an acceptable procedure.

3 Apply SEALANT BMS5-95 -

(a) Refer to SOPM 20-50-19 and SWPM 20-20-00 as an acceptable procedures.

FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19-20.

FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: Part is in the kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank

and J2802 Box faying surface. (a)

1 Apply SEALANT BMS5-95 -

Install (New) KIT ASSY - J2802 BOX 65C38484-11 1

BOLT, PROTRUDING BACB30NX5HK6 6

HD

Install (New)

SPACERS FOR RIV- NAS42DD6-16FC 6

ETS

Install (New)

Install (New) COLLAR, PRELOAD BACC30BH5 6

2 Tighten COLLAR, PRELOAD BACC30BH5 6

On the bolt heads.

Refer to SOPM 20-

50-19 as an acceptable procedure.

3 Apply SEALANT BMS5-95 -

(a) Refer to SOPM 20-50-19 and SWPM 20-20-00 as an acceptable procedures.

FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (New) CLAMP OLYMPIC 287T0011-1 4

Install (New) BOLT BACS12HN3-8 4

Install (New) WASHER NAS1149D0316H 4

Install (New) NUT BACN10YR3CD 4

Maximum resistance

is 0.5 milliohms between J2802 Box

Assembly and E3

Support Post faying

surfaces. (a) (c)

J2802 BOX ASSEM- 65C38484-( ) 1

BLY

2 Measure

3 Install (New) BONDING JUMPER BACJ40AB20-6 1 (b)

Install (New) BOLT BACS12HN3-7 2

Install (New) WASHER NAS1149D0316H 6

Install (New) NUT BACN10YR3CD 2

35 to 45 inch pound.

(b)

4 Torque BOLT BACS12HN3-7 2

Torque NUT BACN10YR3CD 2

Maximum resistance

is 0.001 Ohms (1.0

milliohms) between

jumper faying surfaces. (a) (c)

ELECTRICAL BOND- BACJ40AB20-6 1

ING RESISTANCE

5 Measure

Maximum resistance

is 3.5 milliohms between J2802 Box

Assembly and E3

Support Post. (a) (c)

ELECTRICAL BOND- - 1

ING RESISTANCE

6 Measure

On any bare metal

surface at the J2802

Box Assembly and

E2 and E3 Support

Posts. (d)

ALODINE, TYPE 2, -

CLASS A OR TYPE 5,

CLASS F

CONVERSION COATING7 Apply

Refer to SOPM 20-

41-02 as an accepted procedure.

8 Apply PRIMER FINISH BMS10-11, TYPE 1 -

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the Support

Posts. Refer to

SOPM 20-41-02 as

an accepted procedure. (e)

BMS10-11, TYPE 2, -

COLOR WHITE

9 Apply ENAMEL FINISH

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) Refer to SWPM 20-20-10 as an accepted procedure.

(c) If the resistance measurement is greater than the maximum resistance shown, then disassemble parts,

clean faying surfaces, install parts and measure bonding resistance again. Refer to SWPM 20-20-00 as

an accepted procedure.

(d) Refer to SOPM 20-43-03 as an accepted procedure.

(e) Only if the Support Posts have been painted before with white enamel.

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep Cover 65-49815-( ) 1

2 Remove / Keep Closure Panel 69-41661-( ) 1

The panel has the

captive screws.

3 Remove / Keep Cover Panel 69-41661-( ) 1

4 Open P6-2 Panel 65C25704-( ) 1

5 Remove / Keep Bolt NAS514P1032-( ) 8

To get better access.6 Remove / Keep Channel 65-49815-( ) 1

To get better access.7 Remove / Keep Screw NAS1801-3-8 5

To get better access.Washer AN960PD10L 5

To get better access

to the wires and

connectors.

8 Move Relay Panel 69-73627-( ) 1

From the connectors

that are identified as

R54 and R55 on the

panel.

9 Remove / Keep Relay KCD4N 2

10 Open P6-1 Panel 65C25704-( ) 1

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1, 21.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

adjacent wires to the connector.

Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White

Lacing Tape

61-74478-2002, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Red Color

61-74478-2003, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Yellow Color

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

adjacent wires to the connector.

Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White

Lacing Tape

61-74478-2002, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Red

61-74478-2003, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Yellow

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

adjacent wires to the connector.

Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 2-3, 22-23.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White Color

Lacing Tape

61-74478-2002, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Red Color

61-74478-2003, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Yellow Color)

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, White Color

Lacing Tape

61-74478-2002, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Red Color

61-74478-2003, BMS13-54, -

Class 1, Grade D, Type III,

Finish C, Yellow Color

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 4-5, 24.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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220 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 6-7, 25.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

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221 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10103 1

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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222 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10106 1

Refer to SWPM 20-61-11 as an

accepted procedure.

7 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

8 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

223 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 8, 26.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

224 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

225 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

226 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 9, 31.

FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

227 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

228 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10106 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

7 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

10 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

229 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 10-11, 27-28.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

230 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

231 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use white or red or yellow color tie

material same as the adjacent

wires. Refer to SWPM 20-10-11

SWPM 20-10-19

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

232 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 12, 29.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

233 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

Wire

Lacing Tape

2

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10103 1

FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

234 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10106 1

7 Contact, Socket BACC47CP1S 2 Refer to SWPM 20-61-11

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

8 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use white or red or yellow color tie

material same as the adjacent

wires. Refer to SWPM 20-10-11

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

235 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 13.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

236 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

237 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use white or red or yellow color tie

material same as the adjacent

wires. Refer to SWPM 20-10-11

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

238 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

239 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10103 1

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10106 1

Refer to SWPM 20-61-11 as an

accepted procedure.

7 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

8 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

11 Lacing Tape

61-74478-2002,BMS 13-54, -

CLASS 1, GRADE D, TYPE

III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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241 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 15.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Revision 3 July 16, 2014 737-28A1216

242 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10103 1

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

243 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10106 1

Refer to SWPM 20-61-11 as an

accepted procedure.

7 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

8 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

244 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 16.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

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245 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003 , BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

246 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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247 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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248 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep Cover 65-49815-( ) 1

2 Remove / Keep Closure Panel 69-41661-( ) 1

The panel has the

captive screws.

3 Remove / Keep Cover Panel 69-41661-( ) 1

4 Open P6-2 Panel 65C25704-( ) 1

5 Remove / Keep Bolt NAS514P1032-( ) 8

6 Remove / Keep Channel 65-49815-( ) 1

7 Remove / Keep Screw NAS1801-3-8 5

Washer AN960PD10L 5

To gain access to

the wires and connectors.

8 Move Relay Panel 69-73627-( ) 1

From the relay locations that are identified as R54 and R55

on the relay panel.

9 Remove / Keep Relay KCD4N 2

From the relay locations that are identified as R146 and

R147 on the relay

panel.

10 Remove / Keep Relay 10-60450-6 2

11 Open P6-1 Panel 65C25704-( ) 1

FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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249 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 34: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036

(SHEET 1 OF 1)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

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250 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19, 30.

FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

251 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

252 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

253 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19, 30.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

254 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN2 2

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10210 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10203 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10201 1

FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

255 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-30-12 as an

accepted procedure.

6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10208 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10206 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

256 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19, 30.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

257 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN2 2

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10210 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10204 1

FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

258 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10205 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-30-12 as an

accepted procedure.

6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10209 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10207 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

259 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17.

FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

260 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

261 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an

accepted procedure.

8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

262 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

263 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10202 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10201 1

FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

264 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-30-12 as an

accepted procedure.

6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10208 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10206 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

265 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

266 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN2 2

61-74478-10210 or BMS13- - Into the contact barrel.

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10204 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10205 1

FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

267 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-30-12 as an

accepted procedure.

6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10209 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10207 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

268 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 18, 20.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

269 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10103 1

FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

270 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10106 1

Refer to SWPM 20-61-11 as an

accepted procedure.

7 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an

accepted procedure.

8 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an

accepted procedure.

9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10106 1

Refer to SWPM 20-30-12 as an

accepted procedure.

10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

271 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 18, 20.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

272 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10202 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10201 1

FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

273 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10103 1

Refer to SWPM 20-30-12 as an

accepted procedure.

6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10208 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10206 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

274 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 18, 20.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

275 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an

accepted procedure.

3 Contact, Pin BACC47CN2 2

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10210 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10204 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Pin BACC47CN1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10205 1

FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

276 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10106 1

Refer to SWPM 20-30-12 as an

accepted procedure.

6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10209 1

Refer to SWPM 20-30-12 as an

accepted procedure.

7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10207 1

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

277 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044

(SHEET 1 OF 1)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

278 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1, 21.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003 BMS 13-54, -

CLASS 1, GRADE D, TYPE

III, FINISH C, YELLOW

FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

279 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an

accepted procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an

accepted procedure.

3 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

280 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 2, 22, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

281 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

282 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 2, 22, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

283 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

284 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 3, 16, 23.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

285 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an

accepted procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an

accepted procedure.

3 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

286 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 4, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

287 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

288 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 4, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

289 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

290 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 5, 8, 24, 26.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

291 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an

accepted procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an

accepted procedure.

3 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

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292 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 6, 25, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

293 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10308 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

294 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

295 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 6, 25, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

296 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10308 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: July 29, 2010

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297 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

298 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 9, 31.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

299 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an

accepted procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an

accepted procedure.

3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10308 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

300 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

301 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 10, 27.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

302 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an

accepted procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an

accepted procedure.

3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

303 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

304 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 12, 29, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

305 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10308 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

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306 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

307 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 12, 29, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

308 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an

accepted procedure.

2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an

accepted procedure.

3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10308 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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309 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Revision 3 July 16, 2014 737-28A1216

310 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 13.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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311 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an

accepted procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an

accepted procedure.

3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10305 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003 , BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

312 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

313 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 7.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on

the adjacent wires to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

314 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an

accepted procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an

accepted procedure.

3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter

in the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an

accepted procedure.

4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an

accepted procedure.

5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10308 1

To connect each existing wire if

that deleted wire was connected

with an existing AWG 22 wire. (a)

(b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if

that deleted wire was connected

with an existing AWG 20 wire. (a)

(b)

BACC47DE7A 2

Use the same tie color as the existing ties on the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19

as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

315 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

316 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

317 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in

the contact barrel. Refer to SWPM 20-

60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

318 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

319 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in

the contact barrel. Refer to SWPM 20-

60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

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320 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 11, 28, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

321 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

322 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 11, 28, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

323 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

324 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 15, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

325 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

326 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 15, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

327 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

328 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 66: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044

(SHEET 1 OF 1)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

329 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17, Configuration 1.

FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

330 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Pin BACC47CP2T` 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

331 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

332 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17, Configuration 2.

FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

333 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, BMS

13-54, CLASS 1, GRADE

D, TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

334 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

335 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17, Configuration 1.

FIGURE 69: CONNECTION OF WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

336 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

FIGURE 69: CONNECTION OF WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

337 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 69: CONNECTION OF WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

338 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17, Configuration 2.

FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

339 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

340 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

341 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 18, Configuration 1.

FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

342 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

343 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

344 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 18, Configuration 2.

FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

345 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

346 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

347 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 18, Configuration 1.

FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

348 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

349 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

350 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 18, Configuration 2.

FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

351 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

352 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

353 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19, 30.

FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

354 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Pin 316-1616-634 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- 1

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Pin 316-1616-634 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

355 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

356 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19, 30, Configuration 1.

FIGURE 76: CONNECTION OF WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

357 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

FIGURE 76: CONNECTION OF WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

358 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 76: CONNECTION OF WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

359 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19, 30, Configuration 2.

FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

360 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10307 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10305 1

FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

361 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

362 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 20, Configuration 1.

FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

363 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

364 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

365 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 20, Configuration 2.

FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

366 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10302 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM

20-60-00 as an accepted procedure.

61-74478-10309 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10301 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

367 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 20, Configuration 1.

FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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369 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

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370 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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371 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 20, Configuration 2.

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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372 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM

20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the

adjacent wires to the connector. Refer

to SWPM 20-10-11 and SWPM 20-10-

19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10402 1

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10401 1

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10306 1

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

Install at less than 6 inches from the

connector.

ID Tape 61-74478-10308 1

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

373 of 490

BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

To connect each existing wire if that

deleted wire was connected with an

existing AWG 22 wire. (a) (b)

6 Contact, Pin BACC47DE4A or 2

To connect each existing wire if that

deleted wire was connected with an

existing AWG 20 wire. (a) (b)

BACC47DE7A 2

Use the same tie color as the existing

ties on the wires. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

(b) Refer to SWPM 20-20-11 as an accepted procedure.

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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374 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 1 OF 4)

Export Controlled ECCN: 9E991 - BOEING

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375 of 490

BOEING SERVICE BULLETIN 737-28A1216
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 3 OF 4)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 4 OF 4)

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378 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-16, 21-29, 31.

REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-109. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 3

1, AWG 20

1 Wire

On the wires at STA 259.5. Refer

to SWPM 20-10-18. (a)

61-74478-2006 or BMS 13- 1

52, Type V or NA728R99

Expando Sleeve

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10902 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change

the existing wire identification

number. Refer to SWPM 20-10-11

as an accepted procedure. (b)

ID Tape 61-74478-10906 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10903 1

Refer to SWPM 20-30-12 as an

accepted procedure.

4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10905 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

Install at the wire bundle breakout

adjacent to the splice. Refer to

SWPM 20-10-11 as an accepted

procedure.

5 ID Tape 61-74478-10901 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Connector BACC45FT24-43S 1

Refer to SWPM 20-61-11 as an

accepted procedure.

Contact, Socket BACC47CP1S 3

Use one in each empty contact

hole at the connector. Refer to

SWPM 20-60-08 as an accepted

procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 20

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10904 1

Install at less than 12 inches from

the connector. Refer to SWPM 20-

10-11 as an accepted procedure.

61-74478-10901 1

FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit at STA 259.5, and should extend 2 to 3 inches beyond both ends of the conduit.

(b) Some wires W368-031-20 have been identified incorrectly as "W036-031-20". Before installation, do a

General Visual Inspection of the imprinted text on Wire I.D. tape(s). If they are imprinted as "W036-031-

20", then correct that text to "W0368-031-20" using a permanent marker.

FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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382 of 490

BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM

28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Airplanes in Group 17 and Group 18 have been delivered without Auxiliary Tanks but with wire provisions

for Auxiliary Tank installation. It is necessary to install wires W1764-004-20, W1764-005-20, and

W1764-006-20 given in this figure only if Auxiliary Tank with Fuel Boost pumps are installed on the

airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-110. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 6

1, AWG 20

1 Wire

On the wires at STA 259.5. Refer

to SWPM 20-10-18. (a)

61-74478-2006 or BMS 13- 1

52, Type V or NA728R99

Expando Sleeve

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10902 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change

the existing wire identification

number. Refer to SWPM 20-10-11

as an accepted procedure. (b)

ID Tape 61-74478-10906 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10903 1

Refer to SWPM 20-30-12 as an

accepted procedure.

4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-10905 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Install at the wire bundle breakout

adjacent to the splice. Refer to

SWPM 20-10-11 as an accepted

procedure.

5 ID Tape 61-74478-11002 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Socket BACC47CP1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11001 1

Refer to SWPM 20-61-11 as an

accepted procedure.

7 Connector BACC45FT24-43S 1

Refer to SWPM 20-61-11 as an

accepted procedure.

Contact, Socket BACC47CP1S 6

Use one in each empty contact

hole at the connector. Refer to

SWPM 20-60-08 as an accepted

procedure.(c)

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Install at less than 6 inches from

the connector.

ID Tape 61-74478-10904 1

Install at less than 12 inches from

the connector. Refer to SWPM 20-

10-11 as an accepted procedure.

61-74478-11002 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit at STA 259.5 and should extend 2 to 3 inches beyond both ends of the conduit.

(b) Some wires W368-031-20 have been identified incorrectly as "W036-031-20". Before installation, do a

General Visual Inspection of the imprinted text on Wire I.D. tape(s). If they are imprinted as "W036-031-

20", then correct that text to "W0368-031-20" using a permanent marker.

(c) For airplanes with wire provisions for AUX Tank, and with no AUX tank installed, use Qty (20) MS27488-

20-1 seal plugs for connector D5208P.

FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764

(SHEET 3 OF 3)

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384 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 8, 16, 26.

REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-111. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 3

1, AWG 20

1 Wire

On the wires at STA 259.5. Refer

to SWPM 20-10-18. (a)

61-74478-2006 or BMS 13- 1

52, Type V or NA728R99

Expando Sleeve

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11102 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change

the existing wire identification

number. Refer to SWPM 20-10-11

as an accepted procedure.

ID Tape 61-74478-11106 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11103 1

Refer to SWPM 20-30-12 as an

accepted procedure.

4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-11105 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

Install at the wire bundle breakout

adjacent to the splice. Refer to

SWPM 20-10-11 as an accepted

procedure.

5 ID Tape 61-74478-11101 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Connector BACC45FT24-43S6 1

Contact, Socket BACC47CP1S 3

Use one in each empty contact

hole at the connector. Refer to

SWPM 20-60-08 as an accepted

procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11104 1

Install at less than 12 inches from

the connector. Refer to SWPM 20-

10-11 as an accepted procedure.

61-74478-11101 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit at STA 259.5 and should extend 2 to 3 inches beyond both ends of the conduit.

FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-7, 9-15, 21-25, 27-29, 31.

REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-111. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 3

1, AWG 20

1 Wire

On the wires at STA 259.5. Refer

to SWPM 20-10-18. (a)

61-74478-2006 or BMS 13- -

52, Type V or NA728R99

Expando Sleeve

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11102 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change

the existing wire identification

number. Refer to SWPM 20-10-11

as an accepted procedure.

ID Tape 61-74478-11106 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11103 1

Refer to SWPM 20-30-12 as an

accepted procedure.

4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-11105 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

Install at the wire bundle breakout

adjacent to the splice. Refer to

SWPM 20-10-11 as an accepted

procedure.

5 ID Tape 61-74478-11101 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Connector BACC45FT24-43S6 1

Contact, Socket BACC47CP1S 3

Use one in each empty contact

hole at the connector. Refer to

SWPM 20-60-08 as an accepted

procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11104 1

Install at less than 12 inches from

the connector. Refer to SWPM 20-

10-11 as an accepted procedure.

61-74478-11101 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit at STA 259.5 and should extend 2 to 3 inches beyond both ends of the conduit.

FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 2 OF 2)

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This Figure applies only to: Group 17-20, 30.

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM

28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Airplanes in Group 17 and Group 18 have been delivered without Auxiliary Tanks but with wire provisions

for Auxiliary Tank installation. It is necessary to install wires W1774-004-20, W1774-005-20, and

W1774-006-20 given in this figure only if Auxiliary Tank with Fuel Boost pumps are installed on the

airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-112. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and

SWPM 20-10-12 as accepted procedures.

BMS13-58, Type 1, Class 6

1, AWG 20

1 Wire

On the wires at STA 259.5. Refer

to SWPM 20-10-18. (a)

61-74478-2006 or BMS 13- -

52, Type V or NA728R99

Expando Sleeve

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

2 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11102 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change

the existing wire identification

number. Refer to SWPM 20-10-11

as an accepted procedure.

ID Tape 61-74478-11106 2

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11103 1

Refer to SWPM 20-30-12 as an

accepted procedure.

4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an

accepted procedure.

ID Sleeve 61-74478-11105 1

Refer to SWPM 20-10-11 as an

accepted procedure.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Install at the wire bundle breakout

adjacent to the splice. Refer to

SWPM 20-10-11 as an accepted

procedure.

5 ID Tape 61-74478-11202 1

Refer to SWPM 20-61-11 as an

accepted procedure.

6 Contact, Socket BACC47CP1S 3

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11201 1

Use the same color tie as the adjacent wires to the connector. Refer

to SWPM 20-10-11and SWPM 20-

10-19 as accepted procedures.

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Lacing Tape

Refer to SWPM 20-61-11 as an

accepted procedure.

7 Connector BACC45FT24-43S6 1

Contact, Socket BACC47CP1S 6

Use one in each empty contact

hole at the connector. Refer to

SWPM 20-60-08 as an accepted

procedure.(b)

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Install at less than 6 inches from

the connector.

ID Tape 61-74478-11104 1

Install at less than 12 inches from

the connector. Refer to SWPM 20-

10-11 as an accepted procedure.

61-74478-11101 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit at STA 259.5 and should extend 2 to 3 inches beyond both ends of the conduit.

(b) For airplanes with wire provisions for AUX Tank, and with no AUX tank installed, use Qty (20) MS27488-

20-1 seal plugs for connector D5210P.

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 3 OF 3)

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This Figure applies only to: Group 1-13, 15-16.

FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are in the kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

To make a drip loop

below the J2802 Box

Assembly. (a)

1 Adjust WIRE BUNDLE W1764 1

Adjust WIRE BUNDLE W1774 1

Tighten to close the

clamps on the wire

bundles. (a)

BACS38W2I 4

(BACS38W2 or

BACS38W2 optional)

2 Install (New) STRAP

Around the adjacent

wire bundle if installed. (b)

65C38484-14 1

(M23053/12-514-C)

INSULATION SLEEVING, HEAT SHRINKABLE PTFE.3 Install (New)

Use sufficient quantity on the sleeve and

wire bundles.

BACS38W2I 6

(BACS38W2 or

BACS38W2 optional)

Install (New) STRAP

Refer to SWPM 20-

81-22 as an accepted procedure.

TDH-1852-1502 or 2

TDH1852-1502

4 Install Relay

(a) Refer to SWPM 20-10-11 as an accepted procedure.

(b) Refer to SWPM 20-10-11, "Split Sleeve Installation", as an accepted procedure.

FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 19-20.

FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are in the kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

To make a drip loop

below the J2802 Box

Assembly. (a)

1 Adjust WIRE BUNDLE W1764 1

Adjust WIRE BUNDLE W1774 1

Tighten to close the

clamps on the wire

bundles. (a)

BACS38W2I 4

(BACS38W2 or

BACS38W2 optional)

2 Install (New) STRAP

Around the adjacent

wire bundle if installed. (b)

65C38484-14 1

(M23053/12-514-C)

INSULATION SLEEVING, HEAT SHRINKABLE PTFE.3 Install (New)

Use sufficient quantity on the sleeve and

wire bundles.

BACS38W2I 6

(BACS38W2 or

BACS38W2 optional)

Install (New) STRAP

Refer to SWPM 20-

81-22 as an accepted procedure.

TDH-1852-1502 or 4

TDH1852-1502

4 Install Relay

(a) Refer to SWPM 20-10-11 as an accepted procedure.

(b) Refer to SWPM 20-10-11, "Split Sleeve Installation", as an accepted procedure.

FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Close P6-1 Panel 65C25704-( ) 1

At the initial R54 and

R55 relay locations.

2 Install (Kept) Relay KCD4N 2

To the initial location.3 Move Relay Panel 69-73627-( ) 1

4 Install (Kept) Screw NAS1801-3-8 5

Washer AN960PD10L 5

At the initial location

if removed.

5 Install (Kept) Channel 65-49815-( ) 1

Through the channel

if removed.

6 Install (Kept) Bolt NAS514P1032-( ) 8

7 Close P6-2 Panel 65C25704-( ) 1

8 Install (Kept) Closure Panel 69-41661-( ) 1

9 Install (Kept) Cover 65-49815-( ) 1

The panel has the

captive screws.

10 Install (Kept) Cover Panel 69-41661-( ) 1

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-20, 30.

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 1 OF 2)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Close P6-1 Panel 65C25704-( ) 1

P6-3 Panel 65C25704-( ) 1

At the initial R54 and

R55 relay locations.

2 Install (Kept) Relay KCD4N 2

At the initial R146

and R147 relay locations.

3 Install (Kept) Relay 10-60450-6 2

To the initial location.4 Move Relay Panel 69-73627-( ) 1

5 Install (Kept) Screw NAS1801-3-8 5

Washer AN960PD10L 5

At the initial location

if removed.

6 Install (Kept) Channel 65-49815-( ) 1

Through the channel

if removed.

7 Install (Kept) Bolt NAS514P1032-( ) 8

8 Close P6-2 Panel 65C25704-( ) 1

9 Install (Kept) Closure Panel 69-41661-( ) 1

10 Install (Kept) Cover 65-49815-( ) 1

The panel has the

captive screws.

11 Install (Kept) Cover Panel 69-41661-( ) 1

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: The J2802 Box Assembly is available in the J2802 Box Installation Kit, 65C38484-8. Parts to rework

the J2802 Box Assembly are available in the supplemental kit, 65C37854-16. The kit possibly has more

parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

J2802 BOX ASSEM- 65C38484-10 1

BLY

1 Disassemble

Remove/Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

Remove Cover 65C38484-6 1

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

From Disconnect

Angle.

2 Remove/Keep Nut BACN10JC06CD 2

Bolt BACS12HN06-7 2

Connector (D5208J) BACC45FN24-43P 1

From GDY0001. Refer to SWPM 20-10-

11 as an accepted

procedure.

Disconnect Wires W1760 -

From Disconnect

Angle.

3 Remove/Keep Nut BACN10JC06CD 2

Bolt BACS12HN06-7 2

Connector (D5210J) BACC45FN24-43P6 1

From GDY0002. Refer to SWPM 20-10-

11 as an accepted

procedure.

Disconnect Wires W1770 -

4 Remove Rivets BACR15BB( )D( )C 4 (a)

Remove/Keep Disconnect Angle 287U0016-185 2

From J2802 Box Assembly for new

brackets to be fitted.

5 Cut Flange 65C38484-12 2

6 Deburr Edge 65C38484-12 1

Refer to SOPM 20-

43-03 as an accepted procedure.

TYPE 2, CLASS A, or -

TYPE 5 CLASS F

Chemical Conversion

Coating

7 Apply

Refer to SOPM 20-

41-02 as an accepted procedure.

8 Apply Primer BMS 10-11, Type 1 -

Remove and clean

any debris and/or

metal shaving. (b)

J2802 BOX ASSEM- 65C38484-10 1

BLY

9 Clean

10 Install (New) Label-CTR-L 65C38484-31 1 (c)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

11 Install (New) Label-CTR-R 65C38484-32 1 (d)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

12 Install (New) Label-NOT-USED 65C38484-33 2 (e)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

Label-TEST SWITCH- 65C38484-36 1 (f)

ES

13 Install (New)

Label-AUTO SHUTOFF 65C38484-37 1 (g)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

On the Top flange.

Refer to SOPM 20-

50-10 as an accepted procedure.

J2802 BOX ASSEM- 65C38484-16 1

BLY

14 Identify

(a) Protect the wires and the electrical equipment with plastic foil or other equivalent material to prevent

contamination with debris and/or metal shaving. Refer to SWPM 20-00-08 as an accepted procedure.

(b) Refer to SOPM 20-30-03 as an accepted procedure.

(c) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-L". Refer to SWPM 20-10-11 as an accepted procedure.

(d) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-R". Refer to SWPM 20-10-11 as an accepted procedure.

(e) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "NOT USED". Refer to SWPM 20-10-11 as an accepted procedure.

(f) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "TEST" and one with "SWITCHES". Refer to SWPM 20-10-11 as an accepted

procedure.

(g) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "AUTO" and one with "SHUTOFF". Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-18, 30.

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: The J2802 Box Assembly is available in the J2802 Box Installation Kit, 65C38484-9. Parts to rework

the J2802 Box Assembly are available in the supplemental kit, 65C37854-16. The kit possibly has more

parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

J2802 BOX ASSEM- 65C38484-11 1

BLY

1 Disassemble

Remove/Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

Remove Cover 65C38484-6 1

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

From Disconnect

Angle.

2 Remove/Keep Nut BACN10JC06CD 2

Bolt BACS12HN06-7 2

Connector (D5208J) BACC45FN24-43P 1

From GDY0001. Refer to SWPM 20-10-

11 as an accepted

procedure.

Disconnect Wires -

From Disconnect

Angle.

3 Remove/Keep Nut BACN10JC06CD 2

Bolt BACS12HN06-7 2

Connector (D5210J) BACC45FN24-43P6 1

From GDY0002. Refer to SWPM 20-10-

11 as an accepted

procedure.

Disconnect Wires -

4 Remove Rivets BACR15BB( )D( )C 4 (a)

Remove/Keep Disconnect Angle 287U0016-185 2

From left and right of

J2802 Box Assembly for new brackets

to be fitted.

5 Cut Flange 65C38484-12 2

6 Deburr Edge 65C38484-12 1

Refer to SOPM 20-

43-03 as an accepted procedure.

TYPE 2, CLASS A, or -

TYPE 5 CLASS F

Chemical Conversion

Coating

7 Apply

Refer to SOPM 20-

41-02 as an accepted procedure.

8 Apply Primer BMS 10-11, Type 1 -

Remove and clean

any debris and/or

metal shaving. (b)

J2802 BOX ASSEM- 65C38484-11 1

BLY

9 Clean

10 Install (New) Label-CTR-L 65C38484-31 1 (c)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

11 Install (New) Label-CTR-R 65C38484-32 1 (d)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

12 Install (New) Label-AUX-AFT 65C38484-35 1 (e)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

13 Install (New) Label-AUX-FWD 65C38484-34 1 (f)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

Label-TEST SWITCH- 65C38484-36 1 (g)

ES

14 Install (New)

Label-AUTO SHUTOFF 65C38484-37 1 (h)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply Top Coat BAC5710, TYPE 41 -

On the Top flange.

Refer to SOPM 20-

50-10 as an accepted procedure.

J2802 BOX ASSEM- 65C38484-16 1

BLY

15 Identify

(a) Protect the wires and the electrical equipment with plastic foil or other equivalent material to prevent

contamination with debris and/or metal shaving. Refer to SWPM 20-00-08 as an accepted procedure.

(b) Refer to SOPM 20-30-03 as an accepted procedure.

(c) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-L". Refer to SWPM 20-10-11 as an accepted procedure.

(d) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-R". Refer to SWPM 20-10-11 as an accepted procedure.

(e) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "AUX-AFT". Refer to SWPM 20-10-11 as an accepted procedure.

(f) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "AUX-FWD". Refer to SWPM 20-10-11 as an accepted procedure.

(g) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "TEST" and one with "SWITCHES". Refer to SWPM 20-10-11 as an accepted

procedure.

(h) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "AUTO" and one with "SHUTOFF". Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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412 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts to rework the J2802 Box Assembly are available in the supplemental kit, 65C37854-15. The kit

possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the J2802 Box

Assembly. (a)

1 Put/Hold BRACKET 65C38484-19 1

On Bracket as

shown.

2 Put/Hold DISCONNECT ANGLE 287U0016-185 1

0.1905-0.1895 Inch

DIA. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

3 Drill HOLE - 4

0.1905-0.1895 Inch

DIA. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (b)

4 Drill HOLE - 2

5 Remove/Keep DISCONNECT ANGLE 287U0016-185 1

BRACKET 65C38384-19 1

On the J2802 Box

Assembly. (a)

6 Put/Hold BRACKET 65C38484-18 1

On Bracket as

shown.

7 Put/Hold DISCONNECT ANGLE 287U0016-185 1

0.1905-0.1895 Inch

dia. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

8 Drill HOLE - 4

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 5 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

0.1905-0.1895 Inch

dia. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (b)

9 Drill HOLE - 2

0.229-0.218 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

10 Drill HOLE - 1

11 Remove/Keep DISCONNECT ANGLE 287U0016-185 1

BRACKET 65C38484-18 1

12 Deburr BRACKET 65C38484-19 1

BRACKET 65C38484-18 1

DISCONNECT ANGLE 287U0016-185 2

J2802 BOX ASSEM- 65C38484-16 1

BLY

0.010 - 0.015 Inch

deep on both sides

of the panel.

J2802 BOX ASSEM- 65C38484-16 2

BLY

13 Countersink

Shave the rivet flush

on both sides of the

panel. (c)

14 Install (New) RIVET BACR15BA6AD5C 2

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

15 Install (New) SCREW BACS12HN3-8 12

WASHER NAS1149D0316H 12

NUT BACN10YR3CD 12

Install (Kept) BRACKET 65C38484-19 1

BRACKET 65C38484-18 1

DISCONNECT ANGLE 287U0016-185 2

Cut sufficient Grommet on assembly.

(d)

16 Install (New) GROMMET BACG20Z-B000400 4

Apply ADHESIVE BAC 5010 Type 82 -

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 6 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Put in approximate

position as shown.

(e)

J2802 RELAY BOX 65C38484-30 2

LABEL

17 Install (New)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply TOP COAT BAC5710, TYPE 41 -

J2802 BOX ASSEM- 65C38484-16 1 (f)

BLY

18 Clean

To J2802 Box Assembly Cover. (g)J2802 PANEL COVER 65C38484-7 2

SEAL

19 Install (New)

Refer to SOPM 20-

50-12 as an accepted procedure.

Apply ADHESIVE BAC 5010 Type 77 -

0.245-0.255 Inch

dia. Match drill existing holes in Cover

through Cover Seal.

20 Drill HOLE - 6

21 Install (New) COVER 65C38484-20 1

Install (Kept) BOLT BACS12HN3-8 6

WASHER NAS1149F0363P 6

By abrasive cleaning

for faying surface

bonding. (h)

22 Clean HOLE - 1

On the top flange.

Refer to SOPM 20-

50-10 as an accepted procedure.

J2802 BOX ASSEM- 65C38484-43 1

BLY

23 Identify

(a) Make sure the edge margin for the holes are in accordance with 737-300 SRM 51-40-06, 737-400 SRM

51-40-06, or 737-500 SRM 51-40-06.

(b) Match drill using existing hole in Disconnect Bracket or J2802 Box.

(c) If possible, operators can use BACR15BA5AD5C Rivet if the existing hole has not been enlarged when

the original fastener was removed.

(d) Bond to Bracket. Refer to SOPM 20-50-09 as an approved procedure.

(e) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "J2802". Refer to SWPM 20-10-11 as an accepted procedure.

(f) Clean away any debris and/or metal shavings. Refer to SOPM 20-30-03 as an accepted procedure. Remove

protective material applied to components and wire bundles. Refer to SWPM 20-10-04 as an accepted

procedure.

(g) Align Cover Seal with leading edge of inside face of J2802 Box Assembly Cover.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 7 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(h) Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 8 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-18, 30.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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418 of 490

BOEING SERVICE BULLETIN 737-28A1216
FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

420 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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Revision 3 July 16, 2014 737-28A1216

421 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts to rework the J2802 Box Assembly are available in the supplemental kit, 65C37854-15. The kit

possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the J2802 Box

Assembly. (a)

1 Put/Hold BRACKET 65C38484-19 1

On Bracket as

shown.

2 Put/Hold DISCONNECT ANGLE 287U0016-185 1

0.1905-0.1895 Inch

dia. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

3 Drill HOLE - 4

0.1905-0.1895 Inch

dia. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (b)

4 Drill HOLE - 2

5 Remove/Keep DISCONNECT ANGLE 287U0016-185 1

BRACKET 65C38384-19 1

On the J2802 Box

Assembly. (a)

6 Put/Hold BRACKET 65C38484-18 1

On Bracket as

shown.

7 Put/Hold DISCONNECT ANGLE 287U0016-185 1

0.1905-0.1895 Inch

dia. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

8 Drill HOLE - 4

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 5 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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422 of 490

BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

0.1905-0.1895 Inch

dia. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (b)

9 Drill HOLE - 2

0.229-0.218 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

10 Drill HOLE - 1

11 Remove/Keep DISCONNECT ANGLE 287U0016-185 1

BRACKET 65C38484-19 1

12 Deburr BRACKET 65C38484-19 1

BRACKET 65C38484-18 1

DISCONNECT ANGLE 287U0016-185 2

J2802 BOX ASSEM- 65C38484-16 1

BLY

0.010 - 0.015 Inch

deep on both sides

of the panel.

J2802 BOX ASSEM- 65C38484-16 2

BLY

13 Countersink

Shave the rivet flush

on both sides of the

panel. (c)

14 Install (New) RIVET BACR15BA6AD5C 2

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

15 Install (New) SCREW BACS12HN3-8 12

WASHER NAS1149D0316H 12

NUT BACN10YR3CD 12

Install (Kept) BRACKET 65C38484-19 1

BRACKET 65C38484-18 1

DISCONNECT ANGLE 287U0016-185 2

Cut sufficient Grommet on assembly.

(d)

16 Install (New) GROMMET BACG20Z-B000400 4

Apply ADHESIVE BAC 5010 Type 82 -

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 6 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Put in approximate

position as shown.

(e)

J2802 RELAY BOX 65C38484-30 2

LABEL

17 Install (New)

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply TOP COAT BAC5710, TYPE 41 -

J2802 BOX ASSEM- 65C38484-16 1 (f)

BLY

18 Clean

To J2802 Box Assembly Cover. (g)J2802 PANEL COVER 65C38484-7 2

SEAL

19 Install (New)

Refer to SOPM 20-

50-12 as an accepted procedure.

Apply ADHESIVE BAC 5010 Type 77 -

0.245-0.255 Inch

dia. Match drill existing Cover holes

through Cover Seal.

20 Drill HOLE - 6

21 Install (New) COVER 65C38484-20 1

Install (Kept) BOLT BACS12HN3-8 6

WASHER NAS1149F0363P 6

By abrasive cleaning

for faying surface

bonding. (h)

22 Clean HOLE - 1

On the top flange.

Refer to SOPM 20-

50-10 as an accepted procedure.

J2802 BOX ASSEM- 65C38484-40 1

BLY

23 Identify

(a) Make sure the edge margin for the holes are in accordance with 737-300 SRM 51-40-06, 737-400 SRM

51-40-06, or 737-500 SRM 51-40-06.

(b) Match drill using existing hole in Disconnect Angle or J2802 Panel Assy.

(c) If possible, operators can use BACR15BA5AD5C Rivet if the existing hole has not been enlarged when

the original fastener was removed.

(d) Bond to Bracket. Refer to SOPM 20-50-09 as an approved procedure.

(e) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "J2802". Refer to SWPM 20-10-11 as an accepted procedure.

(f) Clean away any debris and/or metal shavings. Refer to SOPM 20-30-03 as an accepted procedure. Remove

protective material applied to components and wire bundles. Refer to SWPM 20-10-04 as an accepted

procedure.

(g) Align Cover Seal with leading edge of inside face of J2802 Box Assembly Cover.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 7 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(h) Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 8 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 4)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

427 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

COVER 65C38484-20 1

Part of wire bundle

W1770.

CONNECTOR BACC45FN24-43P6 1

(D5210J)

2 Install (Kept)

BOLT BACS12HN06-7 2

NUT BACN10JC06CD 2

To GDY0002. Refer

to SWPM 20-10-11

as an accepted procedure.

Install WIRES W1770 -

Part of wire bundle

W1760.

CONNECTOR BACC45FN24-43P 1

(D5208J)

3 Install (Kept)

BOLT BACS12HN06-7 2

NUT BACN10JC06CD 2

To GDY0001. Refer

to SWPM 20-10-11

as an accepted procedure.

Install WIRES W1760 -

4 Install (Kept) COVER 65C38484-20 1

Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-18, 30.

FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 4)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

431 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 4)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

COVER 65C38484-20 1

Part of wire bundle

W1770.

CONNECTOR BACC45FN24-43P6 1

(D5210J)

2 Install (Kept)

BOLT BACS12HN06-7 2

NUT BACN10JC06CD 2

To GDY0002. Refer

to SWPM 20-10-11

as an accepted procedure.

Install WIRES W1770 -

Part of wire bundle

W1760.

CONNECTOR BACC45FN24-43P 1

(D5208J)

3 Install (Kept)

BOLT BACS12HN06-7 2

NUT BACN10JC06CD 2

To GDY0001. Refer

to SWPM 20-10-11

as an accepted procedure.

Install WIRES W1760 -

4 Install / Kept COVER 65C38484-20 1

Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 8)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

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437 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 5 OF 8)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the supplemental kit, 65C37854-15, for J2802 Box Assemblies that have been

reworked, or in the new Top Kit, 65C38471-13. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove RIVET - 4 (a) (b) (j)

From E2 Support

Post.

2 Remove CLAMP SUPPORT BACN10DZ3-( ) 1

BOLT BACS12HN-( ) 1

WASHER NAS1149F0363P 1

Remove/Keep CLAMP - 1

0.128 - 0.135 Inch

dia. in the E2 Support Post in accordance with 737-300

SRM 51-40-05, 737-

400 SRM 51-40-05,

or 737-500 SRM 51-

40-05.

3 Drill HOLE - 1

On the E2 and E3

Support Posts. (c)

65C38484-21 or 1

65C38484-43

J2802 BOX ASSEMBLY4 Put/Hold

On the J2802 Box

Assembly Brackets.

(d)

5 Apply MARK - -

65C38484-21 or

65C38484-43

J2802 BOX ASSEMBLY6 Remove/Keep

65C38484-21 or 1 On marked lines.

65C38484-43

J2802 BOX ASSEMBLY7 Cut

Deburr

To cut edges. Refer

to SOPM 20-43-03

as an accepted procedure.

ALODINE, TYPE 2, -

CLASS A OR TYPE 5,

CLASS F

CHEMICAL CONVERSION COATING8 Apply

To cut edges. Refer

to SOPM 20-41-02

as an accepted procedure.

PRIMER BMS 10-11, Type 1 -

On the E2 and E3

Support Posts and

against the LE Test

switch Bracket. (e)

65C38484-21 or 1

65C38484-43

J2802 BOX ASSEMBLY9 Put/Hold

FILLER BACF3F008E013NN 1

FILLER BACF3F013E043NN 1

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 6 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

439 of 490

BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

0.187 - 0.190 Inch

dia. Interference fit

holes In accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.(f)

10 Drill HOLE - 2

0.161 - 0.164 Inch

dia. Interference fit

holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (f) (g)

11 Drill HOLE - 4

0.218 - 0.229 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

12 Drill HOLE - 3

0.128 - 0.135 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (h)

13 Drill HOLE - 4

14 Apply SEALANT BMS 5-95, CLASS B - (i)

(a) From area where the J2802 Box Assembly will be in contact with the E2 and E3 Support Posts and to

remove existing Cable Clamp Support.

(b) Before drilling holes and removing fasteners in the E3 Support Post, remove the test switches, S784 and

S785, from the Leading Edge Test Switch Bracket. Do not remove wires from the test switches.

(c) Make sure the J2802 Box Assembly is level and put against the E2 and E3 Support Posts in a location

where it does not touch the Moisture Shroud structure. Align the vertical centerline of the J2802 Box Assembly with vertical centerline between E2 and E3 Support Posts. This is only a temporary position to

give location of vertical cut lines on J2802 Box Assembly Brackets.

(d) On Left Hand side of J2802 Box Assembly, use a pencil to make a cut line on Bracket that agrees with

the vertical edge of Web on E3 Support Post at RBL20.5. On Right Hand side of J2802 Box Assembly

make a cut line on Bracket that agrees with vertical outboard face of E2 Support Post at LBL 12.

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 7 OF 8)

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Original Issue: July 29, 2010

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(e) Make sure the J2802 Box Assembly is level and against the E2 and E3 Support Posts. Align the vertical

centerline of the J2802 Box Assembly with vertical centerline between E2 and E3 Support Posts.

(f) Drill hole at the location shown, even if the installation of the Moisture Shroud is different from that shown.

If new drilled hole does not keep the necessary edge margin with an existing hole, do not drill the new

hole. It is acceptable to match drill using the existing hole position, but only if this hole is not a drilled out

Ground Stud hole. If a drilled out Ground Stud hole is present, position the new hole as close as possible

to the required location shown, maintaining edge margin dimensions. If the new drilled hole does keep

the necessary edge margin with the existing hole, it is acceptable to leave the existing hole as it is. Edge

margin dimensions are in accordance with 737-300 SRM 51-40-06, 737-400 SRM 51-40-06, or 737-500

SRM 51-40-06.

(g) Operators can increase the diameter of this hole to 0.187-0.190 Inch DIA.

(h) For a new J2802 Box Assembly, with part number 65C38484-21, this step is not required.

(i) Inject Sealant between Moisture Shroud Angle and Web. Apply a Fillet Seal on top to prevent moisture

to enter between the Moisture Shroud Angle and Web. Refer to SOPM 20-50-19 as an acceptable procedure.

(j) If alternate Location 2 is found, rivet quantity to be removed is 5.

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 8 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

441 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-18, 30.

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

442 of 490

BOEING SERVICE BULLETIN 737-28A1216
FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

443 of 490

BOEING SERVICE BULLETIN 737-28A1216
FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

444 of 490

BOEING SERVICE BULLETIN 737-28A1216
FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

445 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 5 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

446 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the supplemental kit, 65C37854-15, for J2802 Box Assemblies that have been

reworked, or in the new Top Kit, 65C38471-14. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove RIVET - 4 (a) (b) (j)

From E2 Support

Post.

2 Remove CLAMP SUPPORT BACN10DZ3-( ) 1

BOLT BACS12HN-( ) 1

WASHER NAS1149F0363P 1

Remove/Keep CLAMP - 1

0.128 - 0.135 Inch

dia. in the E2 Support Post in accordance with 737-300

SRM 51-40-05, 737-

400 SRM 51-40-05,

or 737-500 SRM 51-

40-05.

3 Drill HOLE - 1

On the E2 and E3

Support Posts. (c)

65C38484-15 or 1

65C38484-40

J2802 BOX ASSEMBLY4 Put/Hold

On the J2802 Box

Assembly Brackets.

(d)

5 Apply MARK - -

65C38484-15 or

65C38484-40

J2802 BOX ASSEMBLY6 Remove/Keep

65C38484-15 or 1 On marked lines.

65C38484-40

J2802 BOX ASSEMBLY7 Cut

Deburr

To cut edges. Refer

to SOPM 20-43-03

as an accepted procedure.

ALODINE, TYPE 2, -

CLASS A OR TYPE 5,

CLASS F

CHEMICAL CONVERSION COATING8 Apply

To cut edges. Refer

to SOPM 20-41-02

as an accepted procedure.

PRIMER BMS 10-11, Type 1 -

On the E2 and E3

Support Posts and

against the LE Test

switch Bracket. (e)

65C38484-15 or 1

65C38484-40

J2802 BOX ASSEMBLY9 Put/Hold

FILLER BACF3F008E013NN 1

FILLER BACF3F013E043NN 1

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 6 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

447 of 490

BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

0.187 - 0.190 Inch

dia. Interference fit

holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.(f)

10 Drill HOLE - 2

0.161 - 0.164 Inch

dia. Interference fit

holes In accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (f) (g)

11 Drill HOLE - 4

0.218 - 0.229 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

12 Drill HOLE - 3

0.128 - 0.135 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (h)

13 Drill HOLE - 4

14 Apply SEALANT BMS 5-95, CLASS B - (i)

(a) From area where the J2802 Box Assembly will be in contact with the E2 and E3 Support Posts and to

remove existing Cable Clamp Support.

(b) Before drilling holes and removing fasteners in the E3 Support Post, remove the test switches, S784 and

S785, from the Leading Edge Test Switch Bracket. Do not remove wires from the test switches.

(c) Make sure the J2802 Box Assembly is level and put against the E2 and E3 Support Posts in a location

where it does not touch the Moisture Shroud structure. Align the vertical centerline of the J2802 Box Assembly with vertical centerline between E2 and E3 Support Posts. This is only a temporary position to

give location of vertical cut lines on J2802 Box Assembly Brackets.

(d) On Left Hand side of J2802 Box Assembly, use a pencil to make a cut line that agrees with the vertical

edge of Web on E3 Support Post at RBL20.5. On Right Hand side of J2802 Box Assembly make a cut

line that agrees with vertical outboard face of E2 Support Post at LBL 12.

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 7 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(e) Make sure the J2802 Box Assembly is level and against the E2 and E3 Support Posts. Align the vertical

centerline of the J2802 Box Assembly with vertical centerline between E2 and E3 Support Posts.

(f) Drill hole at the location shown, even if the installation of the Moisture Shroud is different from that shown.

If new drilled hole does not keep the necessary edge margin with an existing hole, do not drill the new

hole. It is acceptable to match drill using the existing hole position, but only if this hole is not a drilled out

Ground Stud hole. If a drilled out Ground Stud hole is present, position the new hole as close as possible

to the required location shown, maintaining edge margin dimensions. If the new drilled hole does keep

the necessary edge margin with the existing hole, it is acceptable to leave the existing hole as it is. Edge

margin dimensions are in accordance with 737-300 SRM 51-40-06, 737-400 SRM 51-40-06, or 737-500

SRM 51-40-06.

(g) Operators can increase the diameter of this hole to 0.187-0.190 Inch DIA.

(h) For a new J2802 Box Assembly, with part number 65C38484-21, this step is not required.

(i) Inject Sealant between Moisture Shroud Angle and Web. Apply a Fillet Seal on top to prevent moisture

to enter between the Moisture Shroud Angle and Web. Refer to SOPM 20-50-19 as an acceptable procedure.

(j) If alternate Location 2 is found, rivet quantity to be removed is 5.

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND IN THE E2 AND E3 SUPPORT

POSTS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 8 OF 8)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

449 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 100: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR

AIRPLANE WITH AIRSTAIRS

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

450 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

From the E2 and E3

Support Posts.

65C38484-21 or 1

65C38484-43

J2802 BOX ASSEMBLY1 Remove/Keep

FILLER BACF3F008E013NN 1

FILLER BACF3F013E043NN 1

Refer to SOPM 20-

30-03 as an accepted procedure.

2 Clean HOLE - 19

By abrasive cleaning

for faying surface

bonding. (a)

3 Clean HOLE - 1

Refer to SOPM 20-

30-03 as an accepted procedure. (b)

4 Clean HOLE - 4

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) For a new J2802 Box Assembly, with part number 65C38484-21, this step is not required.

FIGURE 100: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR

AIRPLANE WITH AIRSTAIRS

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-18, 30.

FIGURE 101: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

452 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

From the E2 and E3

Support Posts.

65C38484-15 or 1

65C38484-40

J2802 BOX ASSEMBLY1 Remove/Keep

FILLER BACF3F008E013NN 1

FILLER BACF3F013E043NN 1

Refer to SOPM 20-

30-03 as an accepted procedure.

2 Clean HOLE - 19

By abrasive cleaning

for faying surface

bonding. (a)

3 Clean HOLE - 1

Refer to SOPM 20-

30-03 as an accepted procedure. (b)

4 Clean HOLE - 4

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) For a new J2802 Box Assembly, with part number 65C38484-15, this step is not required.

FIGURE 101: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

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453 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 102: INSTALLATION OF THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

454 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: Parts are available in the supplemental kit 65C37854-15 for J2802 Box Assemblies that have been

reworked, or in the new Top Kit 65C38471-13. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank,

fillers and J2802 Box

Assembly faying

surface. (a)

1 Apply SEALANT BMS5-95 -

Against E2 and E3

Support Posts.

65C38484-21 or 1

65C38484-43

J2802 BOX ASSEMBLY2 Put/Hold

Between J2802 Box

Assembly and structure as shown.

FILTER BACF3F008E013NN 1

FILTER BACF3F013E043NN 1

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

(b)

BOLT, PROTRUDING BACB30NX5HK3 4

HD

3 Install (New)

COLLAR, PRELOAD BACC30BH5 4

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

BOLT, PROTRUDING BACB30NX6K3 2

HD

4 Install (New)

COLLAR, PRELOAD BACC30BH6 2

On the bolt heads

and fillet seal the

collars. (c)

5 Apply SEALANT BMS5-95 -

(a) Refer to SOPM 20-50-19 and SWPM 20-20-00 as an acceptable procedures.

(b) It is permitted to install a BACB30NX6K3 Bolt with a BACC30BH6 Collar where hole was increased in

size.

(c) Refer to SOPM 20-50-19 as an acceptable procedure.

FIGURE 102: INSTALLATION OF THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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455 of 490

BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 17-18, 30.

FIGURE 103: INSTALLATION OF THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

456 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: Parts are available in the supplemental kit 65C37854-15 for J2802 Box Assemblies that have been

reworked, or in the new Top Kit 65C38471-14. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank,

fillers and J2802 Box

Assembly faying

surface. (a)

1 Apply SEALANT BMS5-95 -

Against E2 and E3

Support Posts.

65C38484-15 or 1

65C38484-40

J2802 BOX ASSEMBLY2 Put/Hold

Between J2802 Box

Assembly and structure as shown.

FILLER BACF3F008E013NN 1

FILLER BACF3F013E043NN 1

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

(b)

BOLT, PROTRUDING BACB30NX5HK3 4

HD

3 Install (New)

COLLAR, PRELOAD BACC30BH5 4

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

BOLT, PROTRUDING BACB30NX6K3 2

HD

4 Install (New)

COLLAR, PRELOAD BACC30BH6 2

On the bolt heads

and fillet seal the

collars. (c)

5 Apply SEALANT BMS5-95 -

(a) Refer to SOPM 20-50-19 and SWPM 20-20-00 as an acceptable procedures.

(b) It is permitted to install a BACB30NX6K3 Bolt with a BACC30BH6 Collar where hole was increased in

size.

(c) Refer to SOPM 20-50-19 as an acceptable procedure.

FIGURE 103: INSTALLATION OF THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
This Figure applies only to: Group 14, 17-18, 21-31.

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 7)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 7)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 7)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

460 of 490

BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 7)

Export Controlled ECCN: 9E991 - BOEING

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461 of 490

BOEING SERVICE BULLETIN 737-28A1216
NOTE: Parts are available in the supplemental kits 65C37854-15 and 65C38471-15 for J2802 Box Assemblies

that have been reworked, or in the new Top Kits, 65C38471-13 or 65C38471-14. The kit possibly has

more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Use a CLICO to locate the Spacer Nut

Plate to the existing

hole on J2802 Box

Assembly. (a)

1 Put/Hold NUT, SPACER PLATE BACN10TL3A10 2

Use a CLICO to locate the Spacer Nut

Plate to the existing

hole on J2802 Box

Assembly. (a) (b)

2 Put/Hold NUT, SPACER PLATE BACN10TL3A14 2

0.128-0.135 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (a)

3 Drill HOLE - 4

4 Install (New) NUT, SPACER PLATE BACN10TL3A10 2 (a)

NUT, SPACER PLATE BACN10TL3A14 2 (a) (b)

RIVET BACR15BB4D( )C 8 (a)

5 Install (New) CLAMP 287T0011-1 4 (a)

BOLT BACS12HN3-8 4

WASHER NAS1149D0316H 4

6 Install (New) CLAMP 287T0011-1 2

BOLT BACS12HN3-8 2

WASHER NAS1149D0316H 4

NUT BACN10YR3CD 2

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 5 OF 7)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

7 Install (New) BONDING JUMPER BACJ40AB20-8 1 (c)

BOLT BACS12HN3-7 2

WASHER NAS1149D0316H 6

NUT BACN10YR3CD 2

Between the bonding jumper and faying surfaces. The

maximum resistance

allowed is 0.001

Ohms (1.0 milliohms). (d) (e)

ELECTRICAL BOND- BACJ40AB20-8 1

ING RESISTANCE

8 Measure

Between the J2802

Box Assembly and

the E2 Support post.

The maximum resistance allowed is 3.5

Ohms. (d) (e)

ELECTRICAL BOND- - 1

ING RESISTANCE

9 Measure

On bare metal surfaces of the J2802

Box Assembly and

E2 and E3 Support

Posts. (f)

ALODINE, TYPE 2, -

CLASS A OR TYPE 5,

CLASS F

CONVERSION COATING10 Apply

Refer to SOPM 20-

41-02 as an accepted procedure.

11 Apply PRIMER FINISH BMS10-11, TYPE 1 -

Refer to SOPM 20-

41-02 as an accepted procedure. (g)

BMS10-11, TYPE 2, -

COLOR WHITE

12 Apply ENAMEL FINISH

Use a CLICO to locate the Spacer Nut

Plate to the existing

hole on E2 Support

Post.

13 Put/Hold NUT, SPACER PLATE BACN10TL3A10 1

0.128-0.135 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05.

14 Drill HOLE - 1

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 6 OF 7)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

15 Install (New) NUT, SPACER PLATE BACN10TL3A10 1

RIVET BACR15BB4D( )C 2

To attach existing

cable bundle to E2

Support Post.

16 Install (Kept) CLAMP - 1

Install (New) BOLT BACS12HN3-8 1

WASHER NAS1149D0316H 1

(a) For new J2802 Box Assemblies, with part numbers 65C38484-15 or 65C38484-21, this step is not required.

(b) For installations where this Spacer Plate Nut touches airplane structure, operators can install alternative

item, BACN10TL3A4.

(c) Refer to SWPM 20-20-10 as an accepted procedure. Torque bolt 35 to 45 inch pound.

(d) Refer to SWPM 20-20-00 as an accepted procedure.

(e) If the resistance measurement is greater than the maximum resistance shown, then disassemble parts,

clean faying surfaces, install parts and measure bonding resistance again. Refer to SWPM 20-20-00 as

an accepted procedure.

(f) Refer to SOPM 20-43-03 as an accepted procedure.

(g) Only if the Support Posts have been painted before with white enamel.

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS

(SHEET 7 OF 7)

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This Figure applies only to: Group 14, 17-18, 21-31.

FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 1 OF 6)

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FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 2 OF 6)

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FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 3 OF 6)

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FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 4 OF 6)

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FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 5 OF 6)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install WIRE BUNDLE W1764 1 (a)

To make a drip loop

below the J2802 Box

Assembly. (a)

2 Adjust WIRE BUNDLE W1764 1

3 Install WIRE BUNDLE W1774 1 (a)

To make a drip loop

below the J2802 Box

Assembly. (a)

4 Adjust WIRE BUNDLE W1774 1

5 Tighten CLAMPS 287T0011-1 4 (a)

TIE STRAP BACS38W2 4

(a) Refer to SWPM 20-10-11 as an acceptable procedure.

FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 6 OF 6)

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This Figure applies only to: Group 14, 21-29, 31.

FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: Parts are in the kit 65C38484-8 if the J2802 Box Assembly has been reworked, or in 65C38471-13 if

a new Top Kit is used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep COVER 65C38484-20 1

BOLT BACS12HN3-8 6

WASHER NAS1149F0363P 6

Refer to SWPM 20-

81-22 as an accepted procedure.

TDH-1852-1502 or 2

TDH1852-1502

2 Install RELAY

3 Install (Kept) COVER 65C38484-20 1

BOLT BACS12HN3-8 6

WASHER NAS1149F0363P 6

FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 2 OF 2)

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This Figure applies only to: Group 17-18, 30.

FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216
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 airplane.

NOTE: Parts are in the kit 65C38484-9 if the J2802 Box Assembly has been reworked, or in 65C38471-14 if

a new Top Kit is used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep COVER 65C38484-20 1

BOLT BACS12HN3-8 6

WASHER NAS1149F0363P 6

Refer to SWPM 20-

81-22 as an accepted procedure.

TDH-1852-1502 or 4

TDH1852-1502

2 Install RELAY

3 Install (Kept) COVER 65C38484-20 1

BOLT BACS12HN3-8 6

WASHER NAS1149F0363P 6

FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH

AIRSTAIRS

(SHEET 2 OF 2)

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This Figure applies only to: Group 14, 17-18, 21-31.

FIGURE 108: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION -

INSPECTION

(SHEET 1 OF 2)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Inspect GROUND STUD GD00422A 1 (a) (b)

(a) Do a General Visual Inspection of the Ground Stud location on the E2 Support Post to verify it meets the

minimum dimension shown.

(b) Measure dimension from top edge of inboard side of E2 Support Post to center of GD00422A Ground

Stud.

FIGURE 108: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION -

INSPECTION

(SHEET 2 OF 2)

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This Figure applies only to: Group 14, 17-18, 21-31.

FIGURE 109: ELECTRONICS COMPARTMENT - MOISTURE SHROUD ANGLE AND STRAP - INSPECTION

(SHEET 1 OF 2)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

MOISTURE SHROUD 65-78254-19 1 (a) (b)

ANGLE

1 Inspect

MOISTURE SHROUD 65-78254-15 1 (a) (b)

STRAP

(a) Do a General Visual Inspection of the Moisture Shroud Angle and Strap to see if they protrude in front of

the LE Test Switch Bracket beyond edge of web on the E3 Support Post.

(b) The view shown is an example of a Moisture Shroud Angle and Strap location. The height relative to the

LE Test Switch Bracket can be different on some airplanes.

FIGURE 109: ELECTRONICS COMPARTMENT - MOISTURE SHROUD ANGLE AND STRAP - INSPECTION

(SHEET 2 OF 2)

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This Figure applies only to: Group 14, 17-18, 21-31.

FIGURE 110: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION CHANGE

(SHEET 1 OF 3)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: Any new parts required will be Operator supplied.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

From Ground Stud,

GD00422A.

1 Disconnect WIRE W0346-115-22 1

From E2 Support

Post. (a)

2 Remove STUD, GROUND GD00422A 1

From E2 Support

Post.

GD00422A LABEL - 1

Refer to SOPM 20-

30-03 as an accepted procedure.

3 Clean HOLE - 1

ALODINE, TYPE 2, - To edges of hole. (b)

CLASS A OR TYPE 5,

CLASS F

CHEMICAL CONVERSION COATING4 Apply

PRIMER BMS 10-11, Type 1 - To edges of hole. (c)

0.160 - 0.164 Inch

dia. Close Ream

Holes in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (d)

5 Drill HOLE - 1

By abrasive cleaning

for faying surface

bonding. (e)

6 Clean HOLE - 1

Do not tighten nut at

this stage. (a)

7 Install (New) SCREW BACS12GU3K10 1

WASHER, LOCK BACW10EC3S 1

WASHER, PROTEC- NAS1149D0316H 2

TIVE

NUT MS35650-305T 1

Apply SEALANT BMS 5-95, CLASS B -

Locate below new

Ground Stud. (e)

8 Install (New) GD00422A LABEL BACT19J4 Tape 1

Refer to SOPM 20-

44-01 as an accepted procedure.

Apply TOP COAT BAC5710, TYPE 41 -

FIGURE 110: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION CHANGE

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Between Ground

Stud and E2 Support

Post. The maximum

resistance allowed

is 0.0005 Ohms (0.5

milliohms). (e) (g)

ELECTRICAL BOND- GD00422A 1

ING RESISTANCE

9 Measure

To Ground Stud,

GD00422A. (a)

10 Connect WIRE W0346-115-22 1

Tighten nut to specified torque. (a)Tighten NUT MS35650-305T 1

Between Ground

Stud and W0346-

115-22 Terminal

Lug. The maximum

resistance allowed

is 0.0005 Ohms (0.5

milliohms). (e) (g)

ELECTRICAL BOND- GD00422A 1

ING RESISTANCE

11 Measure

(a) Refer to SWPM 20-20-10 as an accepted procedure.

(b) Refer to SOPM 20-40-03 as an accepted procedure.

(c) Refer to SOPM 20-41-02 as an accepted procedure.

(d) Measure dimension from top edge of inboard side of E2 Support Post to center of new position for

GD00422A Ground Stud.

(e) Refer to SWPM 20-20-00 as an accepted procedure.

(f) Operators can use other equivalent materials to fabricate the label. Identify with "GD00422A". Refer to

SWPM 20-10-11 as an accepted procedure.

(g) If the resistance measurement is greater than the maximum resistance shown, then disassemble parts,clean

faying surfaces, install parts and measure bonding resistance again. Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 110: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION CHANGE

(SHEET 3 OF 3)

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This Figure applies only to: Group 14, 17-18, 21-31.

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE

(SHEET 1 OF 7)

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FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE

(SHEET 2 OF 7)

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BOEING SERVICE BULLETIN 737-28A1216
FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE

(SHEET 3 OF 7)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE

(SHEET 4 OF 7)

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NOTE: Any new parts required will be Operator supplied.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

From Moisture

Shroud Angle on E3

Support Post.

1 Remove/Keep NUT BACN10JC08CD 3

WASHER NAS1149DN832J 6

SCREW BACS12CK08-10 3

MOISTURE SHROUD 65-78950-12 1

MOISTURE SHROUD 65-78254-15 1

STRAP

On Moisture Shroud

Angle. (a)

2 Apply MARK - -

On top of Moisture

Shroud Angle. (b)

MOISTURE SHROUD 65-78254-15 1

STRAP

3 Put/Hold

On Moisture Shroud

Strap. (a)

4 Apply MARK - -

MOISTURE SHROUD 65-78254-15 1

STRAP

5 Remove/Keep

From the inboard

and outboard end of

Moisture Shroud Angle. (c) (d) (e)

6 Remove RIVET - 2

MOISTURE SHROUD 65-78254-19 1

ANGLE

7 Remove/Keep

On marked line. Do

not change the

Moisture Shroud.

MOISTURE SHROUD 65-78254-19 1

ANGLE

8 Cut

Deburr

On marked line. Do

not change the

Moisture Shroud.

MOISTURE SHROUD 65-78254-15 1

STRAP

9 Cut

Deburr

To cut edges. Refer

to SOPM 20-43-03

as an accepted procedure.

ALODINE, TYPE 2, -

CLASS A OR TYPE

5,CLASS F

CHEMICAL CONVERSION COATING10 Apply

To cut edges. Refer

to SOPM 20-41-02

as an accepted procedure.

PRIMER BMS10-11, TYPE 1 -

Cut sufficient Grommet on assembly. (f)

11 Install GROMMET BACG20Z- 4B000400 1

Apply ADHESIVE BAC 5010 Type 82 -

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE

(SHEET 5 OF 7)

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BOEING SERVICE BULLETIN 737-28A1216
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Align holes in Moisture Shroud, Angle

and Strap. (g)

MOISTURE SHROUD 65-78254-19 1

ANGLE

12 Locate

MOISTURE SHROUD 65-78950-12 1

MOISTURE SHROUD 65-78254-15 1

STRAP

0.169 - 0.177 Inch

dia. In accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (h)

13 Drill HOLE - 1

MOISTURE SHROUD 65-78254-19 1

ANGLE

14 Assemble

MOISTURE SHROUD 65-78950-12 1

MOISTURE SHROUD 65-78254-15 1

STRAP

SCREW BACS12CK08-10 3

WASHER NAS1149DN832J 6

NUT BACN10JC08CD 3

In the horizontal position on the E3

Support Post.

MOISTURE SHROUD 65-78254-19 1

ANGLE

15 Put/Hold

MOISTURE SHROUD 65-78950-12 1

MOISTURE SHROUD 65-78254-15 1

STRAP

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

(i)

16 Install (New) RIVET NAS1398D5AB4 1

0.160 - 0.164 Inch

dia. in accordance

with 737-300 SRM

51-40-05, 737-400

SRM 51-40-05, or

737-500 SRM 51-

40-05. (j)

17 Drill HOLE - 1

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE

(SHEET 6 OF 7)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

In accordance with

737-300 SRM 51-

40-02, 737-400 SRM

51-40-02, or 737-

500 SRM 51-40-02.

(k)

18 Install (New) RIVET NAS1398D5AB4 1

(a) Use a pencil to make a cut line that agrees with vertical edge of Web at RBL20.5. Keep a minimum 0.25

Inch radius on lower inboard corner.

(b) Align Moisture Shroud Strap fixing holes with fixing holes on Moisture Shroud Angle.

(c) Before drilling holes and removing fasteners, remove the test switches, S784 and S785, from the Leading

Edge Test Switch Bracket. Do not remove the wires from the Test switches.

(d) Hole position should obey locations shown, even if the installation of the Moisture Shroud is different from

those shown.

(e) It is permitted to leave the inboard drilled hole on the E3 Support Post and/or LE Test Switch Bracket as

it is.

(f) Bond to Moisture Shroud Angle. Refer to SOPM 20-50-09 as an approved procedure.

(g) Clamp Moisture Shroud between Moisture Shroud Angle and Moisture Shroud Strap.

(h) Through Moisture Shroud Angle, Strap and Shroud. Keep edge margin in accordance with 737-300 SRM

51-40-06, 737-400 SRM 51-40-06, or 737-500 SRM 51-40-06.

(i) In the outboard hole position to secure the Moisture Shroud Angle.

(j) Through Moisture Shroud Angle, Web and E3 Support Post. Use Web to E3 Support Post rivet centerline

to set hole location.

(k) This task completes the installation of the Moisture Shroud, Angle and Strap on to the E3 Support Post.

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND

STRAP CHANGE

(SHEET 7 OF 7)

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BOEING SERVICE BULLETIN 737-28A1216
APPENDIX A: KIT ORDERING FLOW CHART

(SHEET 1 OF 2)

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489 of 490

BOEING SERVICE BULLETIN 737-28A1216
APPENDIX A: KIT ORDERING FLOW CHART

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: July 29, 2010

Revision 3 July 16, 2014 737-28A1216

490 of 490

BOEING SERVICE BULLETIN 737-28A1216