### 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.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2010 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 1 of 490 3.0Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 2 of 490 BOEING SERVICE BULLETIN 737-28A1216

BLANK PAGETable 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 737-28A1216 Revision 3: July 16, 2014 3 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 4 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3: July 16, 2014 5 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 7 of 4905. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 8 of 490 BOEING SERVICE BULLETIN 737-28A121628. 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 July 29, 2010 Original Issue: March 26, 2012 Revision 1: November 12, 2012 Revision 2: July 16, 2014 Revision 3:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 9 of 490 BOEING SERVICE BULLETIN 737-28A1216Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 10 of 490 BOEING SERVICE BULLETIN 737-28A1216

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### 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. Reference Affected Planning Data Paragraph 1.A.2., Spares Affected No Spares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval Yes AD Related

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 11 of 490Reference Affected Planning Data Paragraph 1.H., Weight and Balance Changes Yes Weight and Balance Change Paragraph 1.I., Electrical Load Data Yes Electrical Load Changed Paragraph 1.K., Publications Affected Yes Publications Affected Paragraph 1.K., Publications Affected Yes Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Paragraph 2.C.1., Kits/Parts Yes Kits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin No Special Tooling Required
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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 12 of 490 BOEING SERVICE BULLETIN 737-28A1216In 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 13 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 14 of 490 BOEING SERVICE BULLETIN 737-28A1216In 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 15 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 16 of 490 BOEING SERVICE BULLETIN 737-28A1216COMPLIANCE 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 17 of 490 BOEING SERVICE BULLETIN 737-28A1216Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 18 of 490 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. DESCRIPTION CONFIGURATION GROUP 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
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 19 of 490DESCRIPTION CONFIGURATION GROUP Airplanes that do not have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 4
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 Airplanes that do not have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 12
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 20 of 490 BOEING SERVICE BULLETIN 737-28A1216DESCRIPTION CONFIGURATION GROUP 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
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 Airplanes that do not have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 15
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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

Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 Airplanes with Airstairs, delivered with wire provision for Auxiliary Tank installation and have different wiring configurations at the P5 and P6 panels. - 18

Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 Airplanes that have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 19
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 21 of 490 BOEING SERVICE BULLETIN 737-28A1216DESCRIPTION CONFIGURATION GROUP Airplanes that have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 20
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 22 of 490 BOEING SERVICE BULLETIN 737-28A1216DESCRIPTION CONFIGURATION GROUP Airplanes with Airstairs, that do not have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 29
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 Airplanes with Airstairs, that have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 30
Airplanes with SB 737-28A1212 Original Issue or R1 not incorporated. 1 Airplanes with SB 737-28A1212 Original Issue or R1 incorporated. 2 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 Group Variable Number1 PJ301 - PJ302 1 PJ551 - PJ561 1 PJ601 - PJ615 19 PJ811 21 PJ816 - PJ817 22 PM381 - PM39922 PM401 - PM41722 PM541 - PM55023 PM551 - PM5646 PP001 - PP05429 PP101 12 PP102 - PP169 6 PP181 - PP187 7 PP188 - PP19925 PP201 - PP20514 PP221

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 23 of 490 BOEING SERVICE BULLETIN 737-28A1216Group Variable Number6 PP231 - PP243 6 PP281 - PP286 6 PP301 - PP30525 PP351 - PP35325 PP376 - PP38425 PP391 - PP393 6 PP401 - PP44020 PP471 - PP47518 PP501 - PP52025 PP521 - PP522 6 PP631 - PP63425 PP651 - PP652 6 PP671 - PP68920 PP690 - PP694 6 PP695 - PP699 6 PP701 - PP70620 PP707 - PP716 6 PP717 - PP733 6 PP771 - PP77925 PP801 - PP80825 PP821 - PP82722 PP831 - PP84828 PP851 - PP85211 PP861 - PP87728 PP891 - PP89928 PP901 - PP93628 PP946 - PP94828 PP951 - PP95211 PP961 - PP965 3 PP966 - PP96711 PP981 - PP982 3 PP983 - PP99011 PP991

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 24 of 490 BOEING SERVICE BULLETIN 737-28A1216Group Variable Number23 PP993 11 PQ001 - PQ01611 PQ026 - PQ04111 PQ051 - PQ09211 PQ101 - PQ19911 PQ201 - PQ20223 PQ221 - PQ23011 PQ231 - PQ23210 PQ233 - PQ23728 PQ241 - PQ24227 PQ243 27 PQ251 - PQ26727 PQ281 - PQ29110 PQ292 - PQ29727 PQ298 10 PQ299 10 PQ301 - PQ30710 PQ331 - PQ33210 PQ341 - PQ34827 PQ361 - PQ37327 PQ391 - PQ39527 PQ401 - PQ41827 PQ421 10 PQ431 - PQ43827 PQ447 - PQ44810 PQ451 10 PQ454 10 PQ471 27 PQ472 - PQ47510 PQ479 - PQ48110 PQ486 - PQ48710 PQ491 - PQ49310 PQ771 - PQ772

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 25 of 490 BOEING SERVICE BULLETIN 737-28A1216Group Variable Number10 PQ791 - PQ79316 PQ801 - PQ80516 PQ931 - PQ93527 PQ951 27 PQ971 - PQ99723 PR001 - PR01723 PR021 - PR0303 PR031 - PR0343 PR041 - PR0453 PR061 - PR0723 PR077 - PR08023 PR081 - PR08223 PR091 - PR09223 PR096 23 PR101 23 PR121 - PR12223 PR131 - PR13223 PR141 - PR14323 PR161 - PR17216 PR181 22 PS601 - PS63122 PS636 - PS63822 PS641 - PS642 2 PS643 - PS64423 PS651 - PS65710 PS666 - PS669 3 PS691 - PS69211 PS701 - PS70612 PS751 - PS79923 PS811 23 PS836 - PS83722 PS841 - PS84622 PS851 - PS852

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 26 of 490 BOEING SERVICE BULLETIN 737-28A1216Group Variable Number22 PS856 17 PS861 - PS86317 PS866 - PS86822 PS871 - PS87422 PS896 - PS89715 PS901 - PS941 17 PS956 - PS95723 PS961 - PS96323 PS971 - PS978 3 PT001 - PT015 3 PT021 - PT031 23 PT041 - PT064 3 PT101 - PT10523 PT121 - PT13823 PT146 - PT14823 PT161 - PT17031 PT181 - PT185 9 PT186 - PT18823 PT211 - PT22023 PT295 3 PT301 - PT30910 PT331 - PT360 3 PT381 - PT399 3 PT401 - PT43827 PT501 - PT517 3 PT561 - PT565 3 PT581 - PT58610 PT611 - PT621 3 PT641 - PT644 3 PT651 - PT65627 PT671 - PT672 3 PT681 - PT68513 PT701 - PT703

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 27 of 490 BOEING SERVICE BULLETIN 737-28A1216Group Variable Number3 PT716 - PT71723 PT721 - PT72510 PT801 - PT834 3 PT851 - PT85423 PT871 - PT88610 PT901 - PT93010 PT971 - PT973 3 PT981 - PT98523 PT996 10 PU001 - PU02523 PU301 23 PU311 - PU3134 PV001 5 PV002 - PV055 1 PV201 - PV209 1 PV226 - PV229 8 PV231 - PV237 1 PV271 - PV272 1 PV281 - PV28721 PV296 21 PV301 - PV302 1 PV351 31 PV356 - PV35721 PW001 - PW05421 PW061 1 PW062 - PW06821 PW072 21 PW086 - PW08821 PW091 - PW09421 PW101 - PW10221 PW106 21 PW111 - PW12021 PW156 - PW157

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 28 of 490 BOEING SERVICE BULLETIN 737-28A1216Group Variable Number21 PW161 - PW1711 PW201 - PW25221 PW261 - PW26821 PW271 - PW27621 PW278 21 PW281 - PW29321 PW296 26 PW301 - PW3271 PW401 - PW4081 PW411 - PW4181 PW421 - PW4241 PW431 - PW4358 PW441 - PW4501 PW461 - PW46721 PW501 - PW50419 PW511 - PW52219 PW524 1 PW525 - PW52919 PW530 5 PW531 - PW55024 PW556 - PW5571 PW561 - PW5641 PW571 - PW57621 PW591 - PW5965 PW611 - PW6225 PW631 - PW63724 PW661 - PW6625 PW681 - PW68330 PW701 - PW7021 PW711 - PW71724 PW741 - PW7425 PW761 1 PW771

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 29 of 490 BOEING SERVICE BULLETIN 737-28A1216Group Variable Number31 PW831 31 PW851 - PW856 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: Description Service Bulletin Company Gives instruction to install a new printed circuit assembly in the P5-2 fuel systemmodule 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).

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 30 of 490 BOEING SERVICE BULLETIN 737-28A1216Other 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 31 of 490 BOEING SERVICE BULLETIN 737-28A1216Revision 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 32 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 33 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 34 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 35 of 490 BOEING SERVICE BULLETIN 737-28A1216In 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 36 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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 ZonesZone Model 102, 205 737-400

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 37 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 2, 6-7, 11-12, 14-18, 20, 22, 25, 28-29: Affected Maintenance ZonesZone Model 102, 205 737-300 Group 3, 10: Affected Maintenance ZonesZone Model 102, 205 737-300, 737-500 Group 9, 13, 31: Affected Maintenance ZonesZone Model 102, 205 737-500 Group 23: Affected Maintenance ZonesZone Model 102, 205 737-300, 737-400, 737-500 Group 27: Affected Maintenance ZonesZone Model 102, 105, 205 737-300 Group 27: Affected Maintenance ZonesZone Model 105, 205 737-500 Group 31: Affected Maintenance ZonesZone Model 105, 205 737-400

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 38 of 490 BOEING SERVICE BULLETIN 737-28A1216E. 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:

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 39 of 490 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 21

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 45

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 40 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 2, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 22

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 46

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 2, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 41 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 2, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 22

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 47

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 3: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 42 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 3: Elapsed Hours Task-Hours Number of Per- sons Task
2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 22

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 48

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 4, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 43 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 4, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 23

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 49

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 4, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 23

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 50

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 44 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 4, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 5: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 23

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 51

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 45 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 5: Elapsed Hours Task-Hours Number of Per- sons Task
1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 6, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 24

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 52

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 46 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 6, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 6, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 24

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 53

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 47 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 7: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 24

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 59

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 8: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 48 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 8: Elapsed Hours Task-Hours Number of Per- sons Task
3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 25

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 51

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 85 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 9: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 49 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 9: Elapsed Hours Task-Hours Number of Per- sons Task
2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 26

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 54

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 10: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 50 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 10: Elapsed Hours Task-Hours Number of Per- sons Task

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 27

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 55

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 11, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 27

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 62

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- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 11, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 27

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 63

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 52 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 11, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 12, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 28

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 56

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 53 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 12, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 12, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 28

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 57

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 54 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 13: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 29

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 58

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 14, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 55 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 14, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 30

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 60 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 56 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 14, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 30

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 61 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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 737-28A1216 Revision 3: July 16, 2014 57 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 14, Configuration 2: Elapsed Hours Task-Hours Number of Per- 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 31

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 64

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 58 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 15, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 31

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 65

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 16: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 1

- - 2 FIGURE 3 (a) 3.60 7.20 2 FIGURE 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 59 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 16: Elapsed Hours Task-Hours Number of Per- sons Task
3.60 7.20 2 FIGURE 5 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 12 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 16 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 32

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 48

- - 2 FIGURE 82 (a) 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 85 1.50 1.50 1 FIGURE 88 1.50 1.50 1 FIGURE 90 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.85 91.60 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 17, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 7 (b) 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 (b) 3.60 7.20 2 FIGURE 10 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 38

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 60 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 17, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
2.30 4.60 2 FIGURE 39 (b) 2.30 4.60 2 FIGURE 40 (b)

- - 2 FIGURE 66 (a) 3.80 3.80 1 FIGURE 67 3.80 3.80 2 FIGURE 69 (b) 16.30 32.60 2 FIGURE 84 (c) 15.10 30.20 2 FIGURE 87 (d) 1.50 1.50 1 FIGURE 91 3.00 3.00 1 FIGURE 93 (e) 2.80 2.80 1 FIGURE 95 (e) 0.15 0.15 1 FIGURE 97 (f) 1.20 1.20 1 FIGURE 99 0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.60 0.75 1 FIGURE 107 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (g) 3.00 3.00 1 FIGURE 111 (h) 4.00 12.00 3 Close Access 1.00 2.00 Test 72.40 130.75 TOTAL FOR EACH AIRPLANE (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 givenin 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 givenin this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 61 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 17, Configuration 1: Elapsed Hours Task-Hours Number of Per- 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 7 (b) 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 (b) 3.60 7.20 2 FIGURE 10 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 38 2.30 4.60 2 FIGURE 39 (b) 2.30 4.60 2 FIGURE 40 (b)

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 68 3.80 3.80 1 FIGURE 70 (b) 16.30 32.60 2 FIGURE 84 (c) 15.10 30.20 2 FIGURE 87 (d) 1.50 1.50 1 FIGURE 91 3.00 3.00 1 FIGURE 93 (e) 2.80 2.80 1 FIGURE 95 (e) 0.15 0.15 1 FIGURE 97 (f) 1.20 1.20 1 FIGURE 99 0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 62 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 17, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.75 0.75 1 FIGURE 107 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (g) 3.00 3.00 1 FIGURE 111 (h) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 72.40 130.75 TOTAL FOR EACH AIRPLANE (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 givenin 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 givenin 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 7 (b) 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 (b) 3.60 7.20 2 FIGURE 10

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 63 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 18, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 41 2.30 4.60 2 FIGURE 42 (b) 2.30 4.60 2 FIGURE 43 (b)

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 71 3.80 3.80 1 FIGURE 73 (b) 16.30 32.60 2 FIGURE 84 (c) 15.10 30.20 2 FIGURE 87 (d) 1.50 1.50 1 FIGURE 91 3.00 3.00 1 FIGURE 93 (e) 2.80 2.80 1 FIGURE 95 (e) 0.15 0.15 1 FIGURE 97 (f) 1.20 1.20 1 FIGURE 99 0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.75 0.75 1 FIGURE 107 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (g) 3.00 3.00 1 FIGURE 111 (h) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 72.40 130.75 TOTAL FOR EACH AIRPLANE (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 givenin this figure only if Auxiliary Fuel Tanks with Fuel Boost Pumps are installed on the airplane.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 64 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 18, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task (d) It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 givenin 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 7 (b) 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 (b) 3.60 7.20 2 FIGURE 10 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 41 2.30 4.60 2 FIGURE 42 (b) 2.30 4.60 2 FIGURE 43 (b)

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 72 3.80 3.80 1 FIGURE 74 (b) 16.30 32.60 2 FIGURE 84 (c) 15.10 30.20 2 FIGURE 87 (d) 1.50 1.50 1 FIGURE 91 3.00 3.00 1 FIGURE 93 (e) 2.80 2.80 1 FIGURE 95 (e) 0.15 0.15 1 FIGURE 97 (f) 1.20 1.20 1 FIGURE 99

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 65 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 18, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.75 0.75 1 FIGURE 107 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (g) 3.00 3.00 1 FIGURE 111 (h) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 72.40 130.75 TOTAL FOR EACH AIRPLANE (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 givenin 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 givenin 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 2

- - 2 FIGURE 6 (a)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 66 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 19, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
3.60 7.20 2 FIGURE 7 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 3.60 7.20 2 FIGURE 10 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 13 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 17 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 35 2.30 4.60 2 FIGURE 36 2.30 4.60 2 FIGURE 37

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 75 3.80 3.80 1 FIGURE 76

- - 2 FIGURE 82 (a) 16.30 32.60 2 FIGURE 84 15.10 30.20 2 FIGURE 87 3.00 3.00 1 FIGURE 89 1.50 1.50 1 FIGURE 91 4.00 12.00 3 Close Access 1.00 2.00 2 Test 81.55 151.70 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 19, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 2

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 67 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 19, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task

- - 2 FIGURE 6 (a) 3.60 7.20 2 FIGURE 7 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 3.60 7.20 2 FIGURE 10 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 13 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 17 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 35 2.30 4.60 2 FIGURE 36 2.30 4.60 2 FIGURE 37

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 75 3.80 3.80 1 FIGURE 77

- - 2 FIGURE 82 (a) 16.30 32.60 2 FIGURE 84 15.10 30.20 2 FIGURE 87 3.00 3.00 1 FIGURE 89 1.50 1.50 1 FIGURE 91 4.00 12.00 3 Close Access 1.00 2.00 2 Test 81.55 151.70 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours. Group 20, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 68 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 20, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
0.15 0.15 1 FIGURE 2

- - 2 FIGURE 6 (a) 3.60 7.20 2 FIGURE 7 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 3.60 7.20 2 FIGURE 10 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 13 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 17 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 41 2.30 4.60 2 FIGURE 42 2.30 4.60 2 FIGURE 43

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 78 3.80 3.80 1 FIGURE 80

- - 2 FIGURE 82 (a) 16.30 32.60 2 FIGURE 84 15.10 30.20 2 FIGURE 87 3.00 3.00 1 FIGURE 89 1.50 1.50 1 FIGURE 91 4.00 12.00 3 Close Access 1.00 2.00 2 Test 81.55 151.70 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 69 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 20, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 0.15 0.15 1 FIGURE 2

- - 2 FIGURE 6 (a) 3.60 7.20 2 FIGURE 7 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 3.60 7.20 2 FIGURE 10 0.15 0.15 1 FIGURE 11 1.00 1.00 1 FIGURE 13 1.00 1.00 1 FIGURE 14 2.00 2.00 1 FIGURE 15 0.50 0.50 1 FIGURE 17 1.00 1.00 1 FIGURE 18 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 41 2.30 4.60 2 FIGURE 42 2.30 4.60 2 FIGURE 43

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 79 3.80 3.80 1 FIGURE 81

- - 2 FIGURE 82 (a) 16.30 32.60 2 FIGURE 84 15.10 30.20 2 FIGURE 87 3.00 3.00 1 FIGURE 89 1.50 1.50 1 FIGURE 91 4.00 12.00 3 Close Access 1.00 2.00 2 Test 81.55 151.70 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 70 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 21: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 21

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 45 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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 737-28A1216 Revision 3: July 16, 2014 71 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 21: Elapsed Hours Task-Hours Number of Per- 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 22

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 46 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 72 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 22, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
56.45 99.20 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 22

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 47 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 73 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 22, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 22

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 48 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 74 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 23: Elapsed Hours Task-Hours Number of Per- sons Task
1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 23

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 51

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 75 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 24: Elapsed Hours Task-Hours Number of Per- sons Task
8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 76 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 25, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 24

- - - FIGURE 44 (a) 3.80 3.80 1 FIGURE 52 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - - FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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 737-28A1216 Revision 3: July 16, 2014 77 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 25, Configuration 1: Elapsed Hours Task-Hours Number of Per- 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 24

- - - FIGURE 44 (a) 3.80 3.80 1 FIGURE 53 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 78 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 25, Configuration 2: Elapsed Hours Task-Hours Number of Per- 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 25

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 51 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 85 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 (a) 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 79 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 26: Elapsed Hours Task-Hours Number of Per- sons Task
0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 27

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 55 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 80 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 27: Elapsed Hours Task-Hours Number of Per- sons Task
0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 27

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 62 8.20 16.40 2 FIGURE 83

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 81 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 28, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 82 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 28, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 27

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 63 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 83 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 29, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 28

- - 1 FIGURE 44 (a)

- - 1 FIGURE 56 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.65 95.40 TOTAL FOR EACH AIRPLANE (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 737-28A1216 Revision 3: July 16, 2014 84 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 29, Configuration 1: Elapsed Hours Task-Hours Number of Per- 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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 28

- - 1 FIGURE 44 (a)

- - 1 FIGURE 57 8.20 16.40 2 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 85 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 29, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
52.65 95.40 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 7 (b) 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 (b) 3.60 7.20 2 FIGURE 10 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 35 2.30 4.60 2 FIGURE 36 2.30 4.60 2 FIGURE 37

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 75 3.80 3.80 1 FIGURE 76 16.30 32.60 2 FIGURE 84 15.10 30.20 2 FIGURE 87 1.50 1.50 1 FIGURE 91 3.00 3.00 1 FIGURE 93 (b) 2.80 2.80 1 FIGURE 95 (b) 0.15 0.15 1 FIGURE 97 (c) 1.20 1.20 1 FIGURE 99

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 86 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 30, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.75 0.75 1 FIGURE 107 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 75.4 133.75 TOTAL FOR EACH AIRPLANE (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: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 7 (b) 3.60 7.20 2 FIGURE 8 3.60 7.20 2 FIGURE 9 (b) 3.60 7.20 2 FIGURE 10 1.50 1.50 1 FIGURE 33

- - 2 FIGURE 34 (a) 2.75 5.50 2 FIGURE 35 2.30 4.60 2 FIGURE 36

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 87 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 30, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
2.30 4.60 2 FIGURE 37

- - 1 FIGURE 66 (a) 3.80 3.80 1 FIGURE 75 3.80 3.80 1 FIGURE 77 16.30 32.60 2 FIGURE 84 15.10 30.20 2 FIGURE 87 1.50 1.50 1 FIGURE 91 3.00 3.00 1 FIGURE 93 (b) 2.80 2.80 1 FIGURE 95 (b) 0.15 0.15 1 FIGURE 97 (c) 1.20 1.20 1 FIGURE 99 0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.75 0.75 1 FIGURE 107 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 72.40 130.75 TOTAL FOR EACH AIRPLANE (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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 88 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 31: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Open Access 3.60 7.20 2 FIGURE 4 3.60 7.20 2 FIGURE 5 1.50 1.50 1 FIGURE 19

- - 2 FIGURE 20 (a) 2.75 5.50 2 FIGURE 26

- - 1 FIGURE 44 (a) 3.80 3.80 1 FIGURE 54 8.20 16.40 1 FIGURE 83 7.60 15.20 2 FIGURE 86 1.50 1.50 1 FIGURE 90 2.75 2.75 1 FIGURE 92 (b) 2.80 2.80 1 FIGURE 94 (b) 0.15 0.15 1 FIGURE 96 (c) 1.20 1.20 1 FIGURE 98 0.50 0.50 1 FIGURE 100 0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 0.10 0.10 1 FIGURE 108 0.10 0.10 1 FIGURE 109 0.75 0.75 1 FIGURE 110 (d) 3.00 3.00 1 FIGURE 111 (e) 4.00 12.00 3 Close Access 1.00 2.00 2 Test 56.45 99.20 TOTAL FOR EACH AIRPLANE (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 737-28A1216 Revision 3: July 16, 2014 89 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 31: Elapsed Hours Task-Hours Number of Per- 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 +1,300 +6.0 Each 737-300 (a) +900 +6.0 Each 737-400 +1,650 +6.0 Each 737-500 (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 +2,200 +10.0 Each 737-300 (a) +1,500 +10.0 Each 737-400 +2,750 +10.0 Each 737-500 (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 AMPS Duty Cycle Load Data Action Bus Nomenclature Circuit Breaker +150 Milliampere Intermittent ON/OFF Connected 100% Cruise,Hold and Land Add 28V DC Bus 1 Fuel Cont Auto Shut Off CTR-L C3318

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 90 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 1-16, 21-29, 31: AIRPLANES WITH NO AUX TANK AMPS Duty Cycle Load Data Action Bus Nomenclature Circuit Breaker +150 Milliampere Intermittent ON/OFF Connected 100% Cruise,Hold and Land Add 28V DC Bus 2 Fuel Cont Auto Shut Off CTR-R C3320

Group 17-20, 30: AIRPLANES WITH AUX TANK AMPS Duty Cycle Load Data Action Bus Nomenclature Circuit Breaker +150 Milliampere Intermittent ON/OFF Connected 100% Cruise,Hold and Land Add 28V DC Bus 1 Fuel Cont Auto Shut Off CTR-L C3318

+150 Milliampere Intermittent ON/OFF Connected 100% Cruise,Hold and Land Add 28V DC Bus 2 Fuel Cont Auto Shut Off CTR-R C3320

+150 Milliampere Intermittent ON/OFF Connected 100% Cruise,Hold and Land Add 28V DC Bus 1 Fuel Cont Auto Shut Off AUX AFT C3327

+150 Milliampere Intermittent ON/OFF Connected 100% Cruise,Hold and Land Add 28V DC Bus 2 Fuel Cont Auto Shut Off AUX FWD C3329

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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 91 of 490 BOEING SERVICE BULLETIN 737-28A1216d. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 92 of 490 BOEING SERVICE BULLETIN 737-28A12163. Installation Drawings Used in the Preparation of this Service Bulletin: Title Drawing NumberKit- Wire Installation, Auto Shut Off System 61-74478 Wire Bundle Installation- Flight Compartment 65-48315 Wire Bundle Installation- Flight Compartment 65-48322 Wire Bundle Installation- Flight Compartment 65-48325 Disconnect Panel Installation- Flight Compartment 65-49731 Support Post Installation- E2 and E3 Rack 65-63811 Moisture Shroud Instl - Elec/Elex Racks (E2 and E3) 65-78950 Top Kit- Fuel Boost Pump, Auto Shut Off System, Center Fuel Tank 65C38471 Kit- J2802 Box Installation, Auto Shut Off System, 65C38484 Wire Bundle attach Point Loc. - Electronics Equipment Bay, Section 51 and 53 65-49791 Switch Instl - Test, L.E. Warning 69-71787 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 Chapter-Section Publication Section 1 and Section 3.1 737 Airplane Flight Manual 12 and NP 737 Operations Manual 28-22 737 Maintenance Manual 28-23, 28-43, Equipment List 737 Wiring Diagram Manual 28-23, 28-43 737 System Schematic Manual 28-22 737 Illustrated Parts Catalog 28 737 Dispatch Deviation Guide 28 737 Minimum Equipment List 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 93 of 490 BOEING SERVICE BULLETIN 737-28A1216L. Interchangeability and Intermixability of Parts None. M. Software Accomplishment Summary Not affected.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 94 of 490 BOEING SERVICE BULLETIN 737-28A12162. 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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$9,869.00 539 200 05/05/10 Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-7 (a) (c) 100 05/12/10 13 05/19/10 50 08/16/12 50 08/30/12 50 09/14/12 50 09/28/12 $239.00 139 105 07/17/12 Supplemental Kit - New 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 95 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$10,719.00 539 10 05/05/10 Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-8 (a) (b)
Not Available for procurement Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-12 (c) (e)
$16,236.00 539
- - Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-14 (d) (h)
$1,059.00 203 25 07/19/12 Supplemental Kit - J2802 Relay Box Modification For Airplanes With Airstairs 65C37854-15 (f)

$239.00 139 105 07/17/12 Supplemental Kit - New Labels For J2802 Relay Box 65C37854-16 (f)

$59.00 147
- - Supplemental Kit-Boost 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 installedon 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 96 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

(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 installedon 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 installedon 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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$10,719.00 539 10 05/05/10 Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-8 (a) (c)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 97 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$239.00 139 105 07/17/12 Supplemental Kit - New 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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$9,869.00 539 200 05/05/10 Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-7 (a) 100 05/12/10 13 05/19/10 50 08/16/12 50 08/30/12 50 09/14/12 50 09/28/12 Not Available for procurement Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-11 (b)
$22,414.00 539
- - Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-13 (c)

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 98 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$1,059.00 203 25 07/19/12 Supplemental Kit - J2802 Relay Box Modification For Airplanes With Airstairs 65C37854-15 (d)

$239.00 139 105 03/09/12 Supplemental Kit - New Labels For J2802 Relay Box 65C37854-16 (d)

$59.00 147
- - Supplemental Kit-Boost 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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 99 of 490 BOEING SERVICE BULLETIN 737-28A1216Group 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 03date of this Service Bulletin (US Dollars) ROLT as of the Revision 03 date of this Service Bulletin (Calendar Days) QTY Date Name Kit Number

$10,719.00 539 10 05/05/10 Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-8 (a)
Not Available for procurement Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-12 (b)

$16,236.00 539
- - Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-14 (c)

$1,059.00 203 25 07/19/12 Supplemental Kit - J2802 Relay Box Modification For Airplanes With Airstairs 65C37854-15 (d)

$239.00 139 105 07/17/12 Supplemental Kit - New Labels For J2802 Relay Box 65C37854-16 (d)

$59.00 147
- - Supplemental Kit-Boost 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 100 of 490 BOEING SERVICE BULLETIN 737-28A1216B. 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 Notes Existing Part Number Name QTY New Part Number -12 -11 -8 -7 (a) TOP KIT-BOOST PUMP, AUTO S/O, CTR TANK, AIRSTAIRS 737-300/- 400/-500 . - . . 65C38471-11

(a) TOP KIT-BOOST PUMP, AUTO S/O, CTR & AUX TANK, AIRSTAIRS 737-3/-4/- 5 - . . . 65C38471-12

TOP KIT-FUEL BOOST PUMP, AUTO SHUTOFF 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

WIRE KIT

. 1

. 1 61-74478-1 WIRE KIT 1

. 1

. 61-74478-2 KIT - JBOX INSTALLATION FOR AIRPLANES WITHOUT Auxiliary TANK . 1

. . 65C38484-22

KIT - JBOX INSTALLATION FOR AIRPLANES WITH Auxiliary TANK 1

. . . 65C38484-23

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 101 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38471 Notes Existing Part Number Name QTY New Part Number -12 -11 -8 -7 KIT - JBOX INSTALLATION FOR AIRPLANES WITHOUT AUX TANK . . . 1 65C38484-8

KIT - JBOX INSTALLATION FOR AIRPLANES WITH AUX TANK . . 1

. 65C38484-9

(a) Kit no longer available for purchase.
Kit 65C38471 Notes Existing Part Number Name QTY New Part Number -15 -14 -13 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

CLAMP OLYMPIC 4 4 4 287T0011-1 WIRE KIT

. . 1 61-74478-1 WIRE KIT

. 1

. 61-74478-2 KIT - JBOX INSTALLATION FOR AIRPLANESWITHOUT AUXILIARY TANK . . 1 65C38484-22

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 102 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38471 Notes Existing Part Number Name QTY New Part Number -15 -14 -13 KIT - JBOX INSTALLATION FOR AIRPLANES WITH AUXILIARY TANK . 1

. 65C38484-23

NUT, SPACER PLATE, LIGHT DUTY 3 3 3 BACN10TL3A10

NUT SPACER PLATE 2 2 2 BACN10TL3A14 NUT, SPACER PLATE 2 2 2 BACN10TL3A4 RIVET, UNIVERSAL HD 8 8 8 BACR15BB4D3C
RIVET 2 2 2 BACR15BB4D4C BOLT 5 5 5 BACS12HN3-8 WASHER 5 5 5 NAS1149D0316H
Kit 65C37854 Notes Existing Part Number Name QTY New Part Number -16 -15 Supplemental Kit -J2802 Box Assembly Modification For Airplanes With Airstairs . - 65C37854-15

Supplemental Kit - New Labels ForJ2802 Box Assembly - . 65C37854-16

CLAMP OLYMPIC

. 2 287T0011-1 BRACKET

. 1 65C38484-18 BRACKET

. 1 65C38484-19 J2802 PANEL COVER . 1 65C38484-20 J2802 Relay Box Label - J2802 2

. 65C38484-30 J2802 Relay Box Label - CTR-L 1

. 65C38484-31

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 103 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C37854 Notes Existing Part Number Name QTY New Part Number -16 -15 J2802 Relay Box Label - CTR-R 1

. 65C38484-32 J2802 Relay Box Label - NOT-USED 2

. 65C38484-33 J2802 Relay Box Label - AUX-FWD 1

. 65C38484-34 J2802 Relay Box Label - AUX-AFT 1

. 65C38484-35 J2802 Relay Box Label - TEST SWITCHES 1

. 65C38484-36
J2802 Relay Box Label - AUTO SHUTOFF 1

. 65C38484-37

J2802 PANEL COVER SEAL . 2 65C38484-7
BOLT

. 6 BACB30NX6K6 COLLAR

. 6 BACC30BH6 FILLER

. 1 BACF3F008E013NN FILLER, FLAT

. 1 BACF3F013E043NN GROMMET

. 4 BACG20Z- B001275 JUMPER

. 1 BACJ40AB20-8 NUT, SPACER PLATE, LIGHT DUTY . 2 BACN10TL3A10

NUT SPACER PLATE . 2 BACN10TL3A14
NUT

. 12 BACN10YR3CD BOLT

. 2 BACS12HN3-10 BOLT

. 12 BACS12HN3-8 WASHER

. 28 NAS1149D0316H

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 104 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -2 -1 WIRE KIT

. - 61-74478-1 WIRE KIT
- . 61-74478-2 ASSY - W036

. 1 61-74478-101 ASSY - W036 1

. 61-74478-102 ASSY - W044

. 1 61-74478-103 ASSY - W044 1

. 61-74478-104 ASSY - W1760

. 1 61-74478-105 ASSY - W1760 1

. 61-74478-106 ASSY - W1770

. 1 61-74478-107 ASSY - W1770 1

. 61-74478-108 ASSY - W368, W1764 . 1 61-74478-109 ASSY - W368, W1764 1

. 61-74478-110 ASSY - W386, W1774 . 1 61-74478-111 ASSY - W386, W1774 1

. 61-74478-112
LACING TAPE - WHITE 1 1 61-74478-2001
LACING TAPE - RED 1 1 61-74478-2002
LACING TAPE - YELLOW 1 1 61-74478-2003
THERMOFIT SLEEVE - 0.125 I.D. 1 1 61-74478-2005

EXPANDABLE SLEEVE, 0.5 IN. I.D. 1 1 61-74478-2006

Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 (a) ASSY - W036

. . . . . - 61-74478-101

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 105 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 (b) CONNECTOR I.D. TAPE - D04064P . . . . 1 1 61-74478-10101 (b) CONNECTOR I.D. TAPE - D04076P . . . . 1 1 61-74478-10102 (b) CONNECTOR I.D. TAPE - D04148P . . . . 1 1 61-74478-10103 (b) CONNECTOR I.D. TAPE - D04180P . . . . 1 1 61-74478-10104 (b) CONNECTOR I.D. TAPE - D04238P . . . . 1 1 61-74478-10105 (b) CONNECTOR I.D. TAPE - D04240P . . . . 1 1 61-74478-10106 (c) SPLICE I.D. SLEEVE - SM116 . . . . 1 1 61-74478-10107 (c) SPLICE I.D. SLEEVE - SM118 . . . . 1 1 61-74478-10108
WIRE LIST

. . . . . 1 61-74478-101W (a) ASSY - W036

. . . . - . 61-74478-102 (b) CONNECTOR I.D. TAPE - D04026P . . . . 1

. 61-74478-10201 (b) CONNECTOR I.D. TAPE - D04132P . . . . 1

. 61-74478-10202 (b) CONNECTOR I.D. TAPE - D04154P . . . . 1

. 61-74478-10203 (b) CONNECTOR I.D. TAPE - D04156P . . . . 1

. 61-74478-10204 (b) CONNECTOR I.D. TAPE - D04212P . . . . 1

. 61-74478-10205 (c) SPLICE I.D. SLEEVE - SM182 . . . . 1

. 61-74478-10206 (c) SPLICE I.D. SLEEVE - SM184 . . . . 1

. 61-74478-10207 (c) SPLICE I.D. SLEEVE - SM186 . . . . 1

. 61-74478-10208 (c) SPLICE I.D. SLEEVE - SM188 . . . . 1

. 61-74478-10209 (a) (d) FILLER WIRE

. . . . 1

. 61-74478-10210

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 106 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 WIRE LIST

. . . . 1

. 61-74478-102W (a) ASSY - W044

. . . - . . 61-74478-103 (b) CONNECTOR I.D. TAPE - D01606 . . 1 1

. . 61-74478-10301 (b) CONNECTOR I.D. TAPE - D01608 . . 1 1

. . 61-74478-10302 (b) CONNECTOR I.D. TAPE - D04076J . . 1 1

. . 61-74478-10305 (b) CONNECTOR I.D. TAPE - D04148J . . 1 1

. . 61-74478-10306 (b) CONNECTOR I.D. TAPE - D04238J . . 1 1

. . 61-74478-10307 (b) CONNECTOR I.D. TAPE - D04240J . . 1 1

. . 61-74478-10308 (d) FILLER WIRE

. . 1 1

. . 61-74478-10309 WIRE LIST

. . . 1

. . 61-74478-103W (a) ASSY - W044

. . - . . . 61-74478-104 (b) CONNECTOR I.D. TAPE - D01818 . . 1

. . . 61-74478-10401 (b) CONNECTOR I.D. TAPE - D01820 . . 1

. . . 61-74478-10402
WIRE LIST

. . 1

. . . 61-74478-104W (a) ASSY - W1760

. - . . . . 61-74478-105 (e) WIRE BUNDLE I.D. TAPE - 61- 31760-001 . 1

. . . . 61-74478-10501
(b) CONNECTOR I.D. TAPE - D05208J 1 1

. . . . 61-74478-10502 (b) CONNECTOR I.D. TAPE - D10966 1 1

. . . . 61-74478-10503
WIRE LIST

. 1

. . . . 61-74478-105W (a) ASSY - W1760
- . . . . . 61-74478-106 (b) CONNECTOR I.D. TAPE - D10970 1

. . . . . 61-74478-10601

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 107 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 (e) WIRE BUNDLE I.D. TAPE - 61- 31760-002 1

. . . . . 61-74478-10602

WIRE LIST 1

. . . . . 61-74478-106W (a) CONTACT

. . 3 3

. . 316-1616-634 (a) SPLICE, PARAL- LEL, SOLISTRAND . . . . 7 3 34137 (a) CONTACT, PIN 7 4

. . 18 7 BACC47CN1S (a) CONTACT, PIN

. . . . 5

. BACC47CN2 (a) CONTACT, SOCK- ET . . 5 3 3 3 BACC47CP1S (a) CONTACT

. . 5 3

. . BACC47CP2T (a) CONTACT 9 5

. . . . BACC47DE1A (a) CONTACT

. . 5 3

. . BACC47DE4A (a) CONTACT, PIN

. . 5 3

. . BACC47DE7A (a) CONTACT, SOCK- ET 9 5

. . . . BACC47ER1 (a) TERMINAL 5 3

. . . . BACT12AR202 (a) TERMINAL 5 3

. . . . BACT12AR203 SLEEVE, SEALING, SPLICE . . . . 7 3 D-436-46 (a) CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 7 4

. . . . M39029/11-145

(a) PLUG 22 22

. . . . MS27488-16-1 (a) PLUG 28 27

. . . . MS27488-20-1 (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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 108 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 (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 Notes Existing Part Number Name QTY New Part Number -112 -111 -110 -109 -108 -107 ASSY - W1770

. . . . . - 61-74478-107 (a) WIRE BUNDLE I.D. TAPE - 61- 31770-001 . . . . . 1 61-74478-10701
(b) CONNECTOR I.D. TAPE - D05210J . . . . 1 1 61-74478-10702 (b) CONNECTOR I.D. TAPE - D10968 . . . . 1 1 61-74478-10703
WIRE LIST

. . . . . 1 61-74478-107W ASSY - W1770

. . . . - . 61-74478-108 (b) CONNECTOR I.D. TAPE - D10972 . . . . 1

. 61-74478-10801 (a) WIRE BUNDLE I.D. TAPE - 61- 31770-002 . . . . 1

. 61-74478-10802

WIRE LIST

. . . . 1

. 61-74478-108W ASSY - W368, W1764 . . . - . . 61-74478-109 (a) WIRE BUNDLE I.D. TAPE - 61- 31764-001 . . . 2

. . 61-74478-10901
(b) CONNECTOR I.D. TAPE - D04180J . . 1 1

. . 61-74478-10902 (b) CONNECTOR I.D. TAPE - D04202J . . 1 1

. . 61-74478-10903 (b) CONNECTOR I.D. TAPE - D05208P . . 1 1

. . 61-74478-10904 (c) SPLICE I.D. SLEEVE - SP4510 . . 1 1

. . 61-74478-10905 (d) WIRE I.D. TAPE - W0368-031-20 . . 2 2

. . 61-74478-10906

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 109 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -112 -111 -110 -109 -108 -107 WIRE LIST

. . . 1

. . 61-74478-109W ASSY - W368, W1764 . . - . . . 61-74478-110 (b) CONNECTOR I.D. TAPE - D04026J . . 1

. . . 61-74478-11001 (a) WIRE BUNDLE I.D. TAPE - 61- 31764-002 . . 2

. . . 61-74478-11002

WIRE LIST

. . 1

. . . 61-74478-110W ASSY - W386, W1774 . - . . . . 61-74478-111 (a) WIRE BUNDLE I.D. TAPE - 61- 31774-001 . 2

. . . . 61-74478-11101
(b) CONNECTOR I.D. TAPE - D04064J 1 1

. . . . 61-74478-11102 (b) CONNECTOR I.D. TAPE - D04084J 1 1

. . . . 61-74478-11103 (b) CONNECTOR I.D. TAPE - D05210P 1 1

. . . . 61-74478-11104 (c) SPLICE I.D. SLEEVE - SP4512 1 1

. . . . 61-74478-11105 (d) WIRE I.D. TAPE - W0386-032-20 2 2

. . . . 61-74478-11106
WIRE LIST

. 1

. . . . 61-74478-111W ASSY - W386, W1774 - . . . . . 61-74478-112 (b) CONNECTOR I.D. TAPE - D04212J 1

. . . . . 61-74478-11201 (a) WIRE BUNDLE I.D. TAPE - 61- 31774-002 2

. . . . . 61-74478-11202

WIRE LIST 1

. . . . . 61-74478-112W CONNECTOR, ELECTRICAL, PLUG, STRAIGHT,BAYONET COUPLING . . 1 1

. . BACC45FT24-43S

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 110 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -112 -111 -110 -109 -108 -107 (e) CONNECTOR, ELECTRICAL, PLUG, STRAIGHT,BAYONET COUPLING 1 1

. . . . BACC45FT24- 43S6

(e) CONTACT, PIN

. . 3 3 7 4 BACC47CN1S (e) CONTACT, SOCK- ET 13 6 10 4

. . BACC47CP1S (e) CONTACT

. . . . 9 5 BACC47DE1A (e) CONTACT, SOCK- ET . . . . 9 5 BACC47ER1 (e) TERMINAL

. . . . 5 3 BACT12AR202 (e) TERMINAL

. . . . 5 3 BACT12AR203 (e) SPLICE 2 2 2 2

. . D-436-37 (e) CONTACT, PIN,CRIMP REMOVABLE, PER MIL-C39029/11 . . . . 7 4 M39029/11-145

(e) PLUG 22 22 22 22 22 22 MS27488-16-1 (e) PLUG 19 22 19 22 28 27 MS27488-20-1 (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 Notes Existing Part Number Name QTY New Part Number -10101 -2006 -2005 -2003 -2002 -2001 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 737-28A1216 Revision 3: July 16, 2014 111 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10101 -2006 -2005 -2003 -2002 -2001 (a) LACING TAPE - WHITE . . . . . - 61-74478-2001 (b) LACING TAPE - RED . . . . - . 61-74478-2002 (c) LACING TAPE - YELLOW . . . - . . 61-74478-2003 (d) THERMOFIT SLEEVE - 0.125 I.D. . . - . . . 61-74478-2005
(e) EXPANDABLE SLEEVE, 0.5 IN. I.D. . - . . . . 61-74478-2006

CONNECTOR I.D. TAPE - D04064P - . . . . . 61-74478-10101 TAPE, ID 1

. . . . . BACT19C-T (f) POLYOLEFIN,HEAT SHRINKABLE SLEEVE, SEE RM PL FORCOMPLETE DEFINITION . . 1

. . . M23053/5-104-4

(g) BMS 13-54

. . . . . 1 NA374H2 (f) OBSOLETE, INAC- TIVE FOR NEW DESIGN, MAY BE USED FORSPARES/MODIFICATIONS . 1

. . . . NA728R99

(g) OBSOLETE, INAC- TIVE FOR NEW DESIGN, MAY BE USED FORSPARES/MODIFICATIONS . . . . 1

. NE597X7

(g) BMS 13-54 TAPE

. . . 1

. . NN048A9 (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 737-28A1216 Revision 3: July 16, 2014 112 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10101 -2006 -2005 -2003 -2002 -2001 (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 Notes Existing Part Number Name QTY New Part Number -10107 -10106 -10105 -10104 -10103 -10102 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 TAPE, ID

. 1 1 1 1 1 BACT19C-T MARKER SLEEVE 1

. . . . . TMSSCE14-2-4
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10205 -10204 -10203 -10202 -10201 -10108 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 737-28A1216 Revision 3: July 16, 2014 113 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10205 -10204 -10203 -10202 -10201 -10108 CONNECTOR I.D. TAPE - D04212P - . . . . . 61-74478-10205
SPLICE I.D. SLEEVE - SM118 . . . . . - 61-74478-10108 TAPE, ID 1 1 1 1 1

. BACT19C-T MARKER SLEEVE

. . . . . 1 TMSSCE14-2-4
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10301 -10210 -10209 -10208 -10207 -10206 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
FILLER WIRE

. - . . . . 61-74478-10210 CONNECTOR I.D. TAPE - D01606 - . . . . . 61-74478-10301 TAPE, ID 1

. . . . . BACT19C-T WIRE

. 1

. . . . BMS13- 48T10C01G018 MARKER SLEEVE

. . 1 1 1 1 TMSSCE14-2-4
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10307 -10306 -10305 -10304 -10303 -10302 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 737-28A1216 Revision 3: July 16, 2014 114 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10307 -10306 -10305 -10304 -10303 -10302 CONNECTOR I.D. TAPE - D04076J . . - . . . 61-74478-10305
CONNECTOR I.D. TAPE - D04148J . - . . . . 61-74478-10306
CONNECTOR I.D. TAPE - D04238J - . . . . . 61-74478-10307 TAPE, ID 1 1 1 1 1 1 BACT19C-T
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10404 -10403 -10402 -10401 -10309 -10308 CONNECTOR I.D. TAPE - D04240J . . . . . - 61-74478-10308
FILLER WIRE

. . . . - . 61-74478-10309 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 TAPE, ID 1 1 1 1

. 1 BACT19C-T WIRE

. . . . 1

. BMS13- 48T10C01G018
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10701 -10602 -10601 -10503 -10502 -10501 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 737-28A1216 Revision 3: July 16, 2014 115 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10701 -10602 -10601 -10503 -10502 -10501 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

TAPE, ID

. . 1 1 1

. BACT19C-T TAPE, ID 1 1

. . . 1 BACT19E-T6
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -10902 -10901 -10802 -10801 -10703 -10702 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 TAPE, ID 1

. . 1 1 1 BACT19C-T TAPE, ID

. 1 1

. . . BACT19E-T6

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 116 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -11002 -11001 -10906 -10905 -10904 -10903 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

TAPE, ID

. 1 1

. 1 1 BACT19C-T TAPE, ID 1

. . . . . BACT19E-T6 MARKER SLEEVE

. . . 1

. . TMSSCE14-2-4
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -11106 -11105 -11104 -11103 -11102 -11101 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 TAPE, ID 1

. 1 1 1

. BACT19C-T TAPE, ID

. . . . . 1 BACT19E-T6 MARKER SLEEVE

. 1

. . . . TMSSCE14-2-4

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 117 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -11202 -11201 CONNECTOR I.D. TAPE - D04212J . - 61-74478-11201
WIRE BUNDLE I.D. TAPE - 61- 31774-002 - . 61-74478-11202

TAPE, ID

. 1 BACT19C-T TAPE, ID 1

. BACT19E-T6
Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -106W -105W -104W -103W -102W -101W 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

. . . . . - 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 (a) (d) WIRE

. . 1 1

. . BMS13- 58T01C01G022 (b) (d) WIRE RMS 5454011752 1 1 1

. 1 1 BMS13- 58T1C1G20 (c) (d) WIRE RMS 5454011755 . . . . 1 1 BMS13- 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 737-28A1216 Revision 3: July 16, 2014 118 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 61-74478 Notes Existing Part Number Name QTY New Part Number -112W -111W -110W -109W -108W -107W 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

. . . . . - 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 (a) (b) WIRE RMS 5454011752 1 1 1 1 1 1 BMS13- 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 Notes Existing Part Number Name QTY New Part Number -13 -12 -11 -10 -9 -8 KIT ASSY - J2802 JBOX . . . - . 1 65C38484-10
KIT ASSY - J2802 JBOX . . - . 1

. 65C38484-11
J2802 PANEL ASSY . - 1 1

. . 65C38484-12
J2802 PANEL
- 1

. . . . 65C38484-13 KIT - SLEEVING

. . . . 1 1 65C38484-14 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 737-28A1216 Revision 3: July 16, 2014 119 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -13 -12 -11 -10 -9 -8 KIT - JBOX INSTALLATION FOR AIRPLANES WITH AUX TANK . . . . - . 65C38484-9

CLAMP OLYMPIC

. . . . 4 4 287T0011-1 DISCONNECT ANGLE (1 BACD2010-640, NO PILOT HOLES) . . 2 2

. . 287U0016-185

KIT ASSY - J2802 JBOX . . . - . 1 65C38484-10
KIT ASSY - J2802 JBOX . . - . 1

. 65C38484-11
J2802 PANEL ASSY . - 1 1

. . 65C38484-12
J2802 PANEL
- 1

. . . . 65C38484-13 KIT - SLEEVING

. . . . 1 1 65C38484-14 J2802 PANEL COVER . . 1 1

. . 65C38484-6
J2802 PANEL COVER SEAL . . 2 2

. . 65C38484-7 BOLT, PROTRUDING HD . . . . 6 6 BACB30NX5HK6
CIRCUIT BREAKER . . 4 2

. . BACC18Z1R COLLAR, PRELOAD . . . . 6 6 BACC30BH5 CONNECTOR,ELECTRICAL, RECEPTACLE, FLANGE MOUNT,BAYONET COUPLING . . 1 1

. . BACC45FN24-43P

CONNECTOR,ELECTRICAL, RECEPTACLE, FLANGE MOUNT,BAYONET COUPLING . . 1 1

. . BACC45FN24- 43P6

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 120 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -13 -12 -11 -10 -9 -8 CLAMP ASSEMBLY . . 4 4

. . BACC49A2
GROMMET

. . 4 4

. . BACG20Z- B000400 BONDING JUMPER . . . . 1 1 BACJ40AB20-6
TERMINAL BLOCK

. . 4 2

. . BACM15C3E NUT

. . 4 4

. . BACN10JC06CD NUT PLATE

. 16

. . . . BACN10JN08 NUTPLATE, SELFLOCK . . 6 6

. . BACN10JY3R
STANDOFF

. . 3 3

. . BACN10NX32D4 NUT

. . . . 6 6 BACN10YR3CD RIVET

. 32

. . . . BACR15BA3AD4C RIVET, 100 DEG

. . 12 12

. . BACR15BA3D4C RIVET

. . 8 8

. . BACR15BA4D4C RIVET, 100 DEG

. . 14 14

. . BACR15BA4D5C RIVET

. . 4 4

. . BACR15BB5D5C BOLT

. . 4 4

. . BACS12HN06-7 BOLT

. . . . 2 2 BACS12HN3-7 BOLT

. . 6 6 4 4 BACS12HN3-8 RELAY SOCKET

. . 4 2

. . BACS16AH1 RINGPOST, WIRE HARNESSMOUNTING SUPPORT . . 3 3

. . BACS31H2B

STRAP

. . . . 10 10 BACS38W2I(BACS38W2 optional) TAPE, ID

. . 26 20

. . BACT19J2 TAPE, ID

. . 38 38

. . BACT19J3 TAPE, ID

. . 2 2

. . BACT19J4 TRACK, TB MDL

. . 2 2

. . BACT44B0700U SWITCH, TOGGLE

. . 2 2

. . MS24524-27

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 121 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -13 -12 -11 -10 -9 -8 ALUMINUM ALLOY, CLAD SHEET; SEE RM PL REPORT FORCOMPLETE DEFINITION 1

. . . . . MX211F

WASHER

. . . . 10 10 NAS1149D0316H WASHER, PLAIN

. . 6 6

. . NAS1149F0363P SPACERS FOR RIVETS . . . . 6 6 NAS42DD6-16FC
TIME DELAY RELAY . . . . 4 2 TDH1852-1502
TERMINAL BLOCKDIODE ASSEMBLY MODULE . . 4 2

. . YHLZD-33

GROUND BLOCK

. . 2 2

. . YHLZG16-1
Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -19 -18 -17 -16 -15 -14 KIT - SLEEVING

. . . . . - 65C38484-14 KIT ASSY - J2802 JBOX . . . . - . 65C38484-15
J2802 PANEL

. . 1
- . . 65C38484-16 J2802 PANEL ASSY . . - . 1

. 65C38484-17
BRACKET

. - 1

. . . 65C38484-18 BRACKET
- . 1

. . . 65C38484-19 J2802 PANEL COVER . . . . 1

. 65C38484-20
CLAMP OLYMPIC

. . . . 4

. 287T0011-1 DISCONNECT ANGLE (1 BACD2010-640, NO PILOT HOLES) . . . . 2

. 287U0016-185

J2802 PANEL COVER SEAL . . . . 2

. 65C38484-7

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 122 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -19 -18 -17 -16 -15 -14 CIRCUIT BREAKER . . . . 4

. BACC18Z1R CONNECTOR,ELECTRICAL, RECEPTACLE, FLANGE MOUNT,BAYONET COUPLING . . . . 1

. BACC45FN24-43P

CONNECTOR,ELECTRICAL, RECEPTACLE, FLANGE MOUNT,BAYONET COUPLING . . . . 1

. BACC45FN24- 43P6

CLAMP ASSEMBLY . . . . 4

. BACC49A2
GROMMET

. . . . 4

. BACG20Z- B000400 TERMINAL BLOCK

. . . . 4

. BACM15C3E NUT

. . . . 4

. BACN10JC06CD NUT PLATE

. . 16

. . . BACN10JN08 NUTPLATE, SELFLOCK . . . . 6

. BACN10JY3R
STANDOFF

. . . . 3

. BACN10NX32D4 NUT, SPACER PLATE, LIGHT DUTY . . . . 2

. BACN10TL3A10

NUT SPACER PLATE . . . . 2

. BACN10TL3A14
NUT

. . 8

. 4

. BACN10YR3CD RIVET

. . 32

. . . BACR15BA3AD4C RIVET, 100 DEG

. . . . 12

. BACR15BA3D4C RIVET, 100 DEG

. . . . 8

. BACR15BA4D3C RIVET

. . . . 8

. BACR15BA4D4C RIVET, 100 DEG

. . . . 14

. BACR15BA4D5C BOLT

. . . . 4

. BACS12HN06-7 BOLT

. . . . 3

. BACS12HN3-10

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 123 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -19 -18 -17 -16 -15 -14 BOLT

. . 8

. 12

. BACS12HN3-8 RELAY SOCKET

. . . . 4

. BACS16AH1 RINGPOST, WIRE HARNESSMOUNTING SUPPORT . . . . 3

. BACS31H2B

TAPE, ID

. . . . 26

. BACT19J2 TAPE, ID

. . . . 38

. BACT19J3 TAPE, ID

. . . . 2

. BACT19J4 TRACK, TB MDL

. . . . 2

. BACT44B0700U INSULATION SLEEVING, HEAT SHRINKABLE PTFE. . . . . . 1 M23053/12-514-C

SWITCH, TOGGLE

. . . . 2

. MS24524-27 ALUMINUM ALLOY, CLAD SHEET; SEE RM PL REPORT FORCOMPLETE DEFINITION 1 1

. 1

. . MX211F

WASHER

. . 16

. 12

. NAS1149D0316H WASHER, PLAIN

. . . . 6

. NAS1149F0363P TERMINAL BLOCKDIODE ASSEMBLY MODULE . . . . 4

. YHLZD-33

GROUND BLOCK

. . . . 2

. YHLZG16-1
Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -23 -22 -21 -20 KIT - SLEEVING 1 1

. . 65C38484-14 KIT ASSY - J2802 JBOX 1

. . . 65C38484-15
J2802 PANEL ASSY . . 1

. 65C38484-17

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 124 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -23 -22 -21 -20 J2802 PANEL COVER . . 1
- 65C38484-20
KIT ASSY - J2802 JBOX . 1
- . 65C38484-21
KIT - JBOX INSTALLATION FOR AIRPLANES WITHOUT Auxiliary TANK . - . . 65C38484-22

KIT - JBOX INSTALLATION FOR AIRPLANES WITH Auxiliary TANK - . . . 65C38484-23

CLAMP OLYMPIC 4 4 4

. 287T0011-1 DISCONNECT ANGLE (1 BACD2010-640, NO PILOT HOLES) . . 2

. 287U0016-185

J2802 PANEL COVER SEAL . . 2

. 65C38484-7 BOLT, PROTRUDING HD 6 6

. . BACB30NX5HK6
BOLT 6 6

. . BACB30NX6K6 CIRCUIT BREAKER . . 2

. BACC18Z1R COLLAR, PRELOAD 6 6

. . BACC30BH5
COLLAR 6 6

. . BACC30BH6 CONNECTOR,ELECTRICAL, RECEPTACLE, FLANGE MOUNT,BAYONET COUPLING . . 1

. BACC45FN24-43P

CONNECTOR,ELECTRICAL, RECEPTACLE, FLANGE MOUNT,BAYONET COUPLING . . 1

. BACC45FN24- 43P6

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 125 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -23 -22 -21 -20 CLAMP ASSEMBLY . . 4

. BACC49A2
FILLER 1 1

. . BACF3F008E013NN FILLER, FLAT 1 1

. . BACF3F013E043NN GROMMET

. . 4

. BACG20Z- B000400 JUMPER 1 1

. . BACJ40AB20-8 TERMINAL BLOCK

. . 2

. BACM15C3E NUT

. . 4

. BACN10JC06CD NUTPLATE, SELFLOCK . . 6

. BACN10JY3R
STANDOFF

. . 3

. BACN10NX32D4 NUT, SPACER PLATE, LIGHT DUTY . . 2

. BACN10TL3A10

NUT SPACER PLATE . . 2

. BACN10TL3A14
NUT 6 6 4

. BACN10YR3CD RIVET, 100 DEG

. . 12

. BACR15BA3D4C RIVET, 100 DEG

. . 8

. BACR15BA4D3C RIVET

. . 8

. BACR15BA4D4C RIVET, 100 DEG

. . 14

. BACR15BA4D5C BOLT

. . 4

. BACS12HN06-7 BOLT

. . 3

. BACS12HN3-10 BOLT 2 2

. . BACS12HN3-7 BOLT 4 4 12

. BACS12HN3-8 RELAY SOCKET

. . 2

. BACS16AH1 RINGPOST, WIRE HARNESSMOUNTING SUPPORT . . 3

. BACS31H2B

STRAP 10 10

. . BACS38W2 TAPE, ID

. . 20

. BACT19J2 TAPE, ID

. . 38

. BACT19J3

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 126 of 490 BOEING SERVICE BULLETIN 737-28A1216Kit 65C38484 Notes Existing Part Number Name QTY New Part Number -23 -22 -21 -20 TAPE, ID

. . 2

. BACT19J4 TRACK, TB MDL

. . 2

. BACT44B0700U SWITCH, TOGGLE

. . 2

. MS24524-27 ALUMINUM ALLOY, CLAD SHEET; SEE RM PL REPORT FORCOMPLETE DEFINITION . . . 1 MX211F

WASHER 10 10 12

. NAS1149D0316H WASHER, PLAIN

. . 6

. NAS1149F0363P SPACERS FOR RIVETS 6 6

. . NAS42DD6-16FC
TIME DELAY RELAY 4 2

. . TDH1852-1502
TERMINAL BLOCKDIODE ASSEMBLY MODULE . . 2

. YHLZD-33

GROUND BLOCK

. . 2

. YHLZG16-1

2. Parts and Materials Supplied by the Operator: Notes Name QTY Part Number / Specifi- cation (a) (b) CHEMICAL CONVERSION COATING 2 Ounce ALODINE TYPE 2, CLASS A OR TYPE 5, CLASS F (a) TIE STRAP 12 BACS38W2I or BACS38W2 (a) (c) PRIMER FINISH 1 Ounce BMS10-11, Type I (a) (c) ENAMEL FINISH 1 Ounce BMS10-11, Type II, White Gloss (a) SEALANT 2 Ounce BMS5-95 (a) ADHESIVE 1 Ounce BAC 5010 TYPE 82 (a) ADHESIVE 1 Ounce BAC 5010 TYPE 77 (a) CLEAR SKYDROL RESIS- TANT TOPCOATING 1 Ounce BAC5710 TYPE 41

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 127 of 490 BOEING SERVICE BULLETIN 737-28A1216Notes Name QTY Part Number / Specifi- cation (a) TAPE, ELECTRICAL PAN- EL LABELING 2 BACT19J2 (a) TAPE, ELECTRICAL PAN- EL LABELING 6 BACT19J4 (d) PLUG 12 MS27488-20-1 (a) RIVET, BLIND 1 NAS1398D5AB4 (a) RIVET 1 BACR15BB10D6C (a) SCREW 1 BACS12GU3K10 (a) WASHER, LOCK 1 BACW10EC3S (a) WASHER, PROTECTIVE 2 NAS1149D0316H (a) NUT, HEX 1 MS35650-305T (a) GROMMET 1 BACG20Z-B001275 (a) RIVET 2 BACR15BA6AD5C (a) RIVET 2 BACR15BA5AD5C (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: Notes New Part Number Name QTY Existing Part Number (b) (d) 65C38484-16 (c) J2802 Box Assembly
- 65C38484-10 (a) (b) (d) 65C38484-16 (c) J2802 Box Assembly
- 65C38484-11 (a) (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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 128 of 490 BOEING SERVICE BULLETIN 737-28A12164. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 129 of 490 BOEING SERVICE BULLETIN 737-28A1216Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 130 of 490 BOEING SERVICE BULLETIN 737-28A1216

BLANK PAGE3. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 131 of 490 BOEING SERVICE BULLETIN 737-28A12168. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 132 of 490 BOEING SERVICE BULLETIN 737-28A1216PART 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. Do Work Packages Part Airplane Groups 1, 2, 3 1 1 Through 13, 15 and 16 1, 2, 3 2 17 Through 18 1, 2, 3 3 19 Through 20 1, 2, 3 4 14, 21 Through 29 and 31 1, 2, 3 5 30

- 6 14, 17, 18, 21 Through 31

- 7 1-16, 21-29, 31

- 8 17-18

- 9 19-20, 30 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 133 of 490 BOEING SERVICE BULLETIN 737-28A1216a 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 134 of 490 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 135 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 136 of 490 BOEING SERVICE BULLETIN 737-28A12163)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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 137 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 138 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 139 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 140 of 490 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, 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 141 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 142 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 143 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 144 of 490 BOEING SERVICE BULLETIN 737-28A1216(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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 145 of 490 BOEING SERVICE BULLETIN 737-28A1216(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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 146 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 147 of 490 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 148 of 490 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 149 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 150 of 490 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 151 of 490 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 152 of 490 BOEING SERVICE BULLETIN 737-28A12161)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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 153 of 490 BOEING SERVICE BULLETIN 737-28A12169)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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 154 of 490 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

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 155 of 490 BOEING SERVICE BULLETIN 737-28A1216a 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 156 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 157 of 490 BOEING SERVICE BULLETIN 737-28A12162) 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 158 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 159 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 160 of 490 BOEING SERVICE BULLETIN 737-28A1216(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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 161 of 490 BOEING SERVICE BULLETIN 737-28A1216d. 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.

Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3: July 16, 2014 162 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-10 J2802 Box Assembly Disassemble 1 6 BACS12HN3-8 Bolt Remove / Keep 6 NAS1149F0363P Washer 1 65C38484-6 Cover Remove / Keep 2

FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 163 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-11 J2802 Box Assembly Disassemble 1 6 BACS12HN3-8 Bolt Remove / Keep 6 NAS1149F0363P Washer 1 65C38484-6 Cover Remove / Keep 2

FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 164 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 165 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP (a) 1 65C38484-31 Label-CTR-L Install (New) 1

- BAC5710, TYPE 41 Top Coat Apply (b) 1 65C38484-32 Label-CTR-R Install (New) 2

- BAC5710, TYPE 41 Top Coat Apply (c) 2 65C38484-33 Label-NOT-USED Install (New) 3

- BAC5710, TYPE 41 Top Coat Apply (d) 1 65C38484-36 Label-TEST SWITCH- ES Install (New) 4 (e) 1 65C38484-37 Label-AUTO SHUTOFF

- BAC5710, Type 41 Top Coat Apply

FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 166 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP Refer to SWPM 20-10-11 as an accepted procedure. - W1760, W1770 Wires Install 5
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 167 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 168 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11and SWPM 20-10-12 as accepted procedures. 9 BMS13-58 Type 1, Class 1, AWG 20 Wire 1

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. 3 BACC47CN1S Contact, Pin 2
Install less than 4 inches from theconnector to identify the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-10501 ID Tape 3

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10502
Use one in each empty contact hole of the connector. Refer to SWPM 20-60-08 and SWPM 20- 61-11 as accepted procedures. 20 MS27488-16-1 or Seal Plug 20 MS27488-20-1

Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures.(a) 2 BACT12AR203 Terminal Lug 4

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 or M39029- 11-145 Contact, Pin 5
Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures. 2 BACT12AR202 Terminal Lug 6

Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE1A Contact 7 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 169 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE1A Contact 8
Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Socket 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. 4 MS27488-20-1 Seal Plug

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10503 ID Tape
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 170 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 171 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 9 BMS13-58 Type 1, Class 1, AWG 20 Wire 1

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. 3 BACC47CN1S Contact, Pin 2 Install adjacent to the connector to identify the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-10701 ID Tape 3

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10702
Use one in each empty contact hole of the connector. Refer to SWPM 20-60-08 and SWPM 20- 61-11 as accepted procedures. 20 MS27488-16-1 or Seal Plug 20 MS27488-20-1

Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures.(a) 2 BACT12AR203 Terminal Lug 4

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 or M39029- 11-145 Contact, Pin 5
Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures. 2 BACT12AR202 Terminal Lug 6

Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE1A Contact 7 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 172 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE1A Contact 8
Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Socket 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. 4 MS27488-20-1 Seal Plug

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10703 ID Tape
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 173 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 19-20.

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 174 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP (a) 1 65C38484-31 Label-CTR-L Install (New) 1

- BAC5710, TYPE 41 Top Coat Apply (b) 1 65C38484-32 Label-CTR-R Install (New) 2

- BAC5710, TYPE 41 Top Coat Apply (c) 1 65C38484-35 Label-AUX-AFT Install (New) 3

- BAC5710, TYPE 41 Top Coat Apply (d) 1 65C38484-34 Label-AUX-FWD Install (New) 4

- BAC5710, TYPE 41 Top Coat Apply

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 175 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (e) 1 65C38484-36 Label-TEST SWITCH- ES Install (New) 5 (f) 1 65C38484-37 Label-AUTO SHUTOFF

- BAC5710, TYPE 41 Top Coat Apply Refer to SWPM 20-10-11 as an accepted procedure. - W1760, W1770 Wires Install 6
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 176 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 17-20, 30.

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 177 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 9 BMS13-58 Type 1, Class 1, AWG 20 Wire 1

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. 3 BACC47CN1S Contact, Pin 2
Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures.(a) 2 BACT12AR203 Terminal Lug 3

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 or M39029- 11-145 Contact, Pin 4
Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures. 2 BACT12AR202 Terminal Lug 5

Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE1A Contact 6 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. 2 BACC47DE1A Contact 7

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 178 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Socket 8 Use one in each empty contact hole of the connector. Refer to SWPM 20-60-08 and SWPM 20- 81-19 as accepted procedures. 4 MS27488-20-1 Seal Plug

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10601 ID Tape
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 179 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 17-20, 30.

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 180 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 9 BMS13-58 Type 1, Class 1, AWG 20 Wire 1

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. 3 BACC47CN1S Contact, Pin 2 Install adjacent to the connector to identify the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-10602 ID Tape 3

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10502
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) 20 MS27488-16-1 or Seal Plug 17 MS27488-20-1

Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures.(b) 2 BACT12AR203 Terminal Lug 4

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 or M39029- 11-145 Contact, Pin 5
Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures. 2 BACT12AR202 Terminal Lug 6

Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE1A Contact 7 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 181 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE1A Contact 8
Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Socket 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. 4 MS27488-20-1 Seal Plug

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10503 ID Tape
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 182 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 17-20, 30.

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 183 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 9 BMS13-58 Type 1, Class 1, AWG 20 Wire 1

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. 3 BACC47CN1S Contact, Pin 2
Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures.(a) 2 BACT12AR203 Terminal Lug 3

Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 or M39029- 11-145 Contact, Pin 4
Refer to SWPM 20-30-00 andSWPM 20-30-11 as accepted procedures. 2 BACT12AR202 Terminal Lug 5

Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE1A Contact 6 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. 2 BACC47DE1A Contact 7

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 184 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Socket 8 Use one in each empty contact hole of the connector. Refer to SWPM 20-60-08 and SWPM 20- 81-19 as accepted procedures. 4 MS27488-20-1 Seal Plug

Install at less than 6 inches fromthe connector to identify the connector. 1 61-74478-10801 ID Tape
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 185 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 17-20, 30.

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 186 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10- 12 as accepted procedures. 9 BMS13-58 Type 1, Class 1, AWG 20 Wire 1
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. 3 BACC47CN1S Contact, Pin 2 Install adjacent to the connector to identify the wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-10802 ID Tape 3

Install at less than 6 inches from the connector to identify the connector. 1 61-74478-10702 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) 20 MS27488-16-1 or Seal Plug 17 MS27488-20-1 Refer to SWPM 20-30-00 and SWPM 20-30- 11 as accepted procedures.(b) 2 BACT12AR203 Terminal Lug 4 Refer to SWPM 20-90-11 as an accepted procedure. 3 M39029/11-145 or M39029-11-145 Contact, Pin 5
Refer to SWPM 20-30-00 and SWPM 20-30- 11 as accepted procedures. 2 BACT12AR202 Terminal Lug 6 Refer to SWPM 20-90-11 as an accepted procedure. 2 BACC47DE1A Contact 7 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. 2 BACC47DE1A Contact 8

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 187 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Sock- 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. 4 MS27488-20-1 Seal Plug

Install at less than 6 inches from the connector to identify the connector. 1 61-74478-10703 ID Tape (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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 188 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP Refer to SWPM 20-10-04 as an acceptable procedure. 1 65C38484-( ) J2802 BOX ASSEM- BLY Clean 1

On the J2802 Box Assembly. 1 65C38484-6 COVER Put 2
6 BACS12HN3-8 BOLT Install (Kept) 6 NAS1149F0363P WASHER Install (Kept)

FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 189 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 1-13, 15-16.

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 190 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 191 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Part is in the kit 65C38484-8. MORE DATA QTY IDENTIFICATION NAME TASK STEP With clamps whenthe J2802 Box Assembly is level onthe E2 and E3 Support Posts. 1 65C38484-10 KIT ASSY - J2802 BOX Attach 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. 3
- HOLE Drill 2

0.218-0.229 inchdia. holes in accordance with 737-300 SRM 51-40-05, 737- 400 SRM 51-40-05, or 737-500 SRM 51- 40-05. 2
- HOLE Drill 3

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 192 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 19-20.

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 193 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 194 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Part is in the kit 65C38484-9. MORE DATA QTY IDENTIFICATION NAME TASK STEP With clamps whenthe J2802 Box Assembly is level onthe E2 and E3 Support Posts. 1 65C38484-11 KIT ASSY - J2802 BOX Attach 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. 3
- HOLE Drill 2

0.218-0.229 inchdia. holes in accordance with 737-300 SRM 51-40-05, 737- 400 SRM 51-40-05, or 737-500 SRM 51- 40-05. 2
- HOLE Drill 3

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 195 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 196 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 197 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP On the E3 Support Post. 1 65C38484-( ) J2802 BOX ASSEM- BLY Align 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. 3
- HOLE Drill 2

0.218-0.229 inchdia. holes in accordance with 737-300 SRM 51-40-05, 737- 400 SRM 51-40-05, or 737-500 SRM 51- 40-05. 4
- HOLE Drill 3

FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 198 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 199 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP From the E2 and E3 Support Posts. 1 65C38484-( ) J2802 BOX ASSEM- BLY Remove 1
Refer to SOPM 20-30-03 as an accepted procedure. 4
- HOLE Clean 2
By abrasive cleaning for faying surface bonding. (a) 14
- HOLE Clean 3
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 200 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 201 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP On the bolt shankand J2802 Box faying surface. (a) - BMS5-95 SEALANT Apply 1

1 65C38484-10 KIT ASSY - J2802 BOX Install (New) 6 BACB30NX5HK6 BOLT, PROTRUDING HD Install (New)
6 NAS42DD6-16FC SPACERS FOR RIV- ETS Install (New)
6 BACC30BH5 COLLAR, PRELOAD Install (New) 6 BACC30BH5 COLLAR, PRELOAD Tighten 2 On the bolt heads. Refer to SOPM 20-50-19 as an acceptable procedure. - BMS5-95 SEALANT Apply 3

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 202 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 203 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP On the bolt shankand J2802 Box faying surface. (a) - BMS5-95 SEALANT Apply 1

1 65C38484-11 KIT ASSY - J2802 BOX Install (New) 6 BACB30NX5HK6 BOLT, PROTRUDING HD Install (New)
6 NAS42DD6-16FC SPACERS FOR RIV- ETS Install (New)
6 BACC30BH5 COLLAR, PRELOAD Install (New) 6 BACC30BH5 COLLAR, PRELOAD Tighten 2 On the bolt heads. Refer to SOPM 20-50-19 as an acceptable procedure. - BMS5-95 SEALANT Apply 3

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 204 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 205 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 206 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 4 287T0011-1 CLAMP OLYMPIC Install (New) 1 4 BACS12HN3-8 BOLT Install (New) 4 NAS1149D0316H WASHER Install (New) 4 BACN10YR3CD NUT Install (New) Maximum resistanceis 0.5 milliohms between J2802 Box Assembly and E3 Support Post faying surfaces. (a) (c) 1 65C38484-( ) J2802 BOX ASSEM- BLY Measure 2

(b) 1 BACJ40AB20-6 BONDING JUMPER Install (New) 3 2 BACS12HN3-7 BOLT Install (New) 6 NAS1149D0316H WASHER Install (New) 2 BACN10YR3CD NUT Install (New) 35 to 45 inch pound. (b) 2 BACS12HN3-7 BOLT Torque 4
2 BACN10YR3CD NUT Torque Maximum resistance is 0.001 Ohms (1.0 milliohms) betweenjumper faying surfaces. (a) (c) 1 BACJ40AB20-6 ELECTRICAL BOND- ING RESISTANCE Measure 5

Maximum resistanceis 3.5 milliohms between J2802 Box Assembly and E3 Support Post. (a) (c) 1
- ELECTRICAL BOND- ING RESISTANCE Measure 6

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 FCONVERSION COATING Apply 7

Refer to SOPM 20-41-02 as an accepted procedure. - BMS10-11, TYPE 1 PRIMER FINISH Apply 8

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 207 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP On the Support Posts. Refer to SOPM 20-41-02 asan accepted procedure. (e) - BMS10-11, TYPE 2, COLOR WHITE ENAMEL FINISH Apply 9

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 208 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 209 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65-49815-( ) Cover Remove / Keep 1 1 69-41661-( ) Closure Panel Remove / Keep 2 The panel has the captive screws. 1 69-41661-( ) Cover Panel Remove / Keep 3
1 65C25704-( ) P6-2 Panel Open 4 8 NAS514P1032-( ) Bolt Remove / Keep 5 To get better access. 1 65-49815-( ) Channel Remove / Keep 6 To get better access. 5 NAS1801-3-8 Screw Remove / Keep 7 To get better access. 5 AN960PD10L Washer To get better access to the wires and connectors. 1 69-73627-( ) Relay Panel Move 8

From the connectors that are identified as R54 and R55 on the panel. 2 KCD4N Relay Remove / Keep 9

1 65C25704-( ) P6-1 Panel Open 10

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 210 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 (SHEET 1 OF 1) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 211 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 212 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties on adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties on adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape

FIGURE 21: 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 737-28A1216 Revision 3 July 16, 2014 213 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties on adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 214 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 215 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape

FIGURE 22: 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 737-28A1216 Revision 3 July 16, 2014 216 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 217 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 218 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape

FIGURE 23: 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 737-28A1216 Revision 3 July 16, 2014 219 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 220 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 221 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 1 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10103 ID Tape

FIGURE 24: 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 737-28A1216 Revision 3 July 16, 2014 222 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10106 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 7
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 8
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 9 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 10 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 11

- 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 737-28A1216 Revision 3 July 16, 2014 223 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 224 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 225 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 737-28A1216 Revision 3 July 16, 2014 226 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 227 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 228 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10106 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 6
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 7
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 9 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 10

- 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 737-28A1216 Revision 3 July 16, 2014 229 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 230 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 231 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve 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 Lacing Tape 9

- 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 737-28A1216 Revision 3 July 16, 2014 232 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 233 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire Lacing Tape 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 1 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10103 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 234 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10106 ID Tape
Refer to SWPM 20-61-11 2 BACC47CP1S Contact, Socket 7 Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 8
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 9 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 10 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve Use white or red or yellow color tie material same as the adjacent wires. Refer to SWPM 20-10-11SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 11

- 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 737-28A1216 Revision 3 July 16, 2014 235 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 236 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 237 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve Use white or red or yellow color tie material same as the adjacent wires. Refer to SWPM 20-10-11SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 737-28A1216 Revision 3 July 16, 2014 238 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 239 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 1 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10103 ID Tape

FIGURE 30: 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 737-28A1216 Revision 3 July 16, 2014 240 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10106 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 7
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 8
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 9 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 10 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 11

- 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 241 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 242 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 1 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10103 ID Tape

FIGURE 31: 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 737-28A1216 Revision 3 July 16, 2014 243 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10106 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 7
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 8
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 9 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 10 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 11

- 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 244 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 245 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape

FIGURE 32: 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 737-28A1216 Revision 3 July 16, 2014 246 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 247 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 248 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65-49815-( ) Cover Remove / Keep 1 1 69-41661-( ) Closure Panel Remove / Keep 2 The panel has the captive screws. 1 69-41661-( ) Cover Panel Remove / Keep 3
1 65C25704-( ) P6-2 Panel Open 4 8 NAS514P1032-( ) Bolt Remove / Keep 5 1 65-49815-( ) Channel Remove / Keep 6 5 NAS1801-3-8 Screw Remove / Keep 7 5 AN960PD10L Washer To gain access tothe wires and connectors. 1 69-73627-( ) Relay Panel Move 8
From the relay locations that are identified as R54 and R55 on the relay panel. 2 KCD4N Relay Remove / Keep 9

From the relay locations that are identified as R146 and R147 on the relay panel. 2 10-60450-6 Relay Remove / Keep 10

1 65C25704-( ) P6-1 Panel Open 11

FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 249 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 250 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 251 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 252 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 737-28A1216 Revision 3 July 16, 2014 253 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 254 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN2 Contact, Pin 3
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. 1 61-74478-10203 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10201 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 255 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 6 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10208 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10206 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 8

- 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 737-28A1216 Revision 3 July 16, 2014 256 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 257 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more parts than necessary.

MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN2 Contact, Pin 3
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. 1 61-74478-10204 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 258 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10205 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 6 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10209 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10207 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 8

- 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 737-28A1216 Revision 3 July 16, 2014 259 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 260 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 261 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10107 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 8 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 9

- 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 737-28A1216 Revision 3 July 16, 2014 262 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 263 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10202 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10201 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 264 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 6 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10208 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10206 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 8

- 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 737-28A1216 Revision 3 July 16, 2014 265 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 266 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN2 Contact, Pin 3
Into the contact barrel.
- 61-74478-10210 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10204 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10205 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 267 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 6 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10209 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10207 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 8

- 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 737-28A1216 Revision 3 July 16, 2014 268 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 269 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 1 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10105 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10103 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 270 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10102 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 6
Install at less than 6 inches from the connector. 1 61-74478-10106 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 7
Install at less than 6 inches from the connector. 1 61-74478-10104 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 8
Install at less than 6 inches from the connector. 1 61-74478-10101 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 9 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10106 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 10 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10108 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 11

- 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 737-28A1216 Revision 3 July 16, 2014 271 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 272 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN1S Contact, Pin 3
Install at less than 6 inches from the connector. 1 61-74478-10202 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10201 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 273 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10103 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 6 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10208 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10206 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 8

- 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 737-28A1216 Revision 3 July 16, 2014 274 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 275 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more parts than necessary. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 andSWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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. 2 BACC47CN2 Contact, Pin 3
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. 1 61-74478-10204 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CN1S Contact, Pin 4
Install at less than 6 inches from the connector. 1 61-74478-10205 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 276 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CN1S Contact, Pin 5
Install at less than 6 inches from the connector. 1 61-74478-10106 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 6 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10209 ID Sleeve
Refer to SWPM 20-30-12 as an accepted procedure. 1 34137 Splice 7 1 D-436-46 or D436-46 Sleeve, Sealing Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10207 ID Sleeve
Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape 8

- 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 737-28A1216 Revision 3 July 16, 2014 277 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 278 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 279 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 3
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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 280 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 281 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 282 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 283 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 284 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 285 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 2
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 3
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 286 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 287 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 288 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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.

MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 289 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 290 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 291 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 3
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 292 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 293 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 294 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 737-28A1216 Revision 3 July 16, 2014 295 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 296 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 297 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 298 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 299 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 300 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 737-28A1216 Revision 3 July 16, 2014 301 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 302 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 303 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 304 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 305 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 306 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 737-28A1216 Revision 3 July 16, 2014 307 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 737-28A1216 Revision 3 July 16, 2014 308 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 309 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 310 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 311 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 312 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 737-28A1216 Revision 3 July 16, 2014 313 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 1

Use the same color as the ties onthe adjacent wires to the connector. Refer to SWPM 20-10-11 andSWPM 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 314 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 2
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. 1 61-74478-10302 ID Tape
Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Socket 3
Use to increase the wire diameterin 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. 1 61-74478-10301 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A

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 737-28A1216 Revision 3 July 16, 2014 315 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 316 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 317 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 318 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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 737-28A1216 Revision 3 July 16, 2014 319 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 320 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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 737-28A1216 Revision 3 July 16, 2014 321 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 322 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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 737-28A1216 Revision 3 July 16, 2014 323 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 324 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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 737-28A1216 Revision 3 July 16, 2014 325 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 326 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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 737-28A1216 Revision 3 July 16, 2014 327 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 328 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 329 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 330 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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. 1 BACC47CP2T` Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-17 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 331 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 332 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 333 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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. 1 BACC47CP2T Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-17 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 334 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 335 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 336 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 337 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 338 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 339 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 340 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 341 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 342 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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.

MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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. 1 BACC47CP2T Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 343 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 344 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 345 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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. 1 BACC47CP2T Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 346 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 347 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 348 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 349 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 350 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 351 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 352 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 353 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 354 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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. 1 316-1616-634 Contact, Pin 2
In the contact barrel. Refer to SWPM 20-60-00 as an accepted procedure. 1 61-74478-10309 or BMS13- 48, Type 1, Class 1, AWG 18 Filler Wire

Install at less than 6 inches from the connector. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-17 as an accepted procedure. 1 316-1616-634 Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 355 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 356 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 357 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 358 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 359 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 360 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10307 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10305 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 361 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 362 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 363 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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. 1 BACC47CP2T Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 364 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 737-28A1216 Revision 3 July 16, 2014 365 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 366 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 22 Wire 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 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. 1 BACC47CP2T Contact, Pin 2
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. 1 61-74478-10302 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Pin 3
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. 1 61-74478-10301 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

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 737-28A1216 Revision 3 July 16, 2014 367 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 368 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 369 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

FIGURE 80: 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 737-28A1216 Revision 3 July 16, 2014 370 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 371 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 372 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 2 BMS13-58, Type 1, Class 1, AWG 20 Wire 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 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. 1 BACC47CP2T Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-10402 ID Tape Refer to SWPM 20-81-11 as an accepted procedure. 1 BACC47CP2T Contact, Socket 3
Install at less than 6 inches from the connector. 1 61-74478-10401 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 4
Install at less than 6 inches from the connector. 1 61-74478-10306 ID Tape Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC47CP1S Contact, Socket 5
Install at less than 6 inches from the connector. 1 61-74478-10308 ID Tape

FIGURE 81: 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 737-28A1216 Revision 3 July 16, 2014 373 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire. (a) (b) 2 BACC47DE4A or Contact, Pin 6
To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. (a) (b) 2 BACC47DE7A
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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 374 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 375 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 (SHEET 2 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 376 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 377 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 378 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 3 BMS13-58, Type 1, Class 1, AWG 20 Wire 1

On the wires at STA 259.5. Refer to SWPM 20-10-18. (a) 1 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 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 379 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CN1S Contact, Pin 2
Install at less than 6 inches from the connector. 1 61-74478-10902 ID Tape
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 3
Install at the two ends to change the existing wire identification number. Refer to SWPM 20-10-11 as an accepted procedure. (b) 2 61-74478-10906 ID Tape

Install at less than 6 inches from the connector. 1 61-74478-10903 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 D-436-37 or D436-37 Splice 4
Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10905 ID 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

Install at the wire bundle breakout adjacent to the splice. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-10901 ID Tape 5

Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT24-43S Connector 6
Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CP1S Contact, Socket Use one in each empty contact hole at the connector. Refer to SWPM 20-60-08 as an accepted procedure. 20 MS27488-16-1 or Seal Plug 20 MS27488-20-1

Install at less than 6 inches from the connector. 1 61-74478-10904 ID Tape
Install at less than 12 inches from the connector. Refer to SWPM 20- 10-11 as an accepted procedure. 1 61-74478-10901

FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 380 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 381 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 382 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 6 BMS13-58, Type 1, Class 1, AWG 20 Wire 1

On the wires at STA 259.5. Refer to SWPM 20-10-18. (a) 1 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 BACC47CN1S Contact, Pin 2
Install at less than 6 inches from the connector. 1 61-74478-10902 ID Tape
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 3
Install at the two ends to change the existing wire identification number. Refer to SWPM 20-10-11 as an accepted procedure. (b) 2 61-74478-10906 ID Tape

Install at less than 6 inches from the connector. 1 61-74478-10903 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 D-436-37 or D436-37 Splice 4
Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-10905 ID 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 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 383 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Install at the wire bundle breakout adjacent to the splice. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-11002 ID Tape 5

Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CP1S Contact, Socket 6
Install at less than 6 inches from the connector. 1 61-74478-11001 ID Tape
Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT24-43S Connector 7
Refer to SWPM 20-61-11 as an accepted procedure. 6 BACC47CP1S Contact, Socket Use one in each empty contact hole at the connector. Refer to SWPM 20-60-08 as an accepted procedure.(c) 20 MS27488-16-1 or Seal Plug 17 MS27488-20-1

Install at less than 6 inches from the connector. 1 61-74478-10904 ID Tape
Install at less than 12 inches from the connector. Refer to SWPM 20- 10-11 as an accepted procedure. 1 61-74478-11002
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 384 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 3 BMS13-58, Type 1, Class 1, AWG 20 Wire 1

On the wires at STA 259.5. Refer to SWPM 20-10-18. (a) 1 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 85: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 385 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-11102 ID Tape
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 3
Install at the two ends to change the existing wire identification number. Refer to SWPM 20-10-11 as an accepted procedure. 2 61-74478-11106 ID Tape

Install at less than 6 inches from the connector. 1 61-74478-11103 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 D-436-37 or D436-37 Splice 4
Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-11105 ID 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

Install at the wire bundle breakout adjacent to the splice. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-11101 ID Tape 5

Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT24-43S6 Connector 6 3 BACC47CP1S Contact, Socket Use one in each empty contact hole at the connector. Refer to SWPM 20-60-08 as an accepted procedure. 20 MS27488-16-1 or Seal Plug 17 MS27488-20-1

Install at less than 6 inches from the connector. 1 61-74478-11104 ID Tape
Install at less than 12 inches from the connector. Refer to SWPM 20- 10-11 as an accepted procedure. 1 61-74478-11101
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 386 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 3 BMS13-58, Type 1, Class 1, AWG 20 Wire 1

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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 387 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-11102 ID Tape
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 3
Install at the two ends to change the existing wire identification number. Refer to SWPM 20-10-11 as an accepted procedure. 2 61-74478-11106 ID Tape

Install at less than 6 inches from the connector. 1 61-74478-11103 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 D-436-37 or D436-37 Splice 4
Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-11105 ID 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

Install at the wire bundle breakout adjacent to the splice. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-11101 ID Tape 5

Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC45FT24-43S6 Connector 6 3 BACC47CP1S Contact, Socket Use one in each empty contact hole at the connector. Refer to SWPM 20-60-08 as an accepted procedure. 20 MS27488-16-1 or Seal Plug 17 MS27488-20-1

Install at less than 6 inches from the connector. 1 61-74478-11104 ID Tape
Install at less than 12 inches from the connector. Refer to SWPM 20- 10-11 as an accepted procedure. 1 61-74478-11101
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 388 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 17-20, 30.

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 389 of 490 BOEING SERVICE BULLETIN 737-28A1216REFERENCE: 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. MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 andSWPM 20-10-12 as accepted procedures. 6 BMS13-58, Type 1, Class 1, AWG 20 Wire 1

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 BACC47CP1S Contact, Socket 2
Install at less than 6 inches from the connector. 1 61-74478-11102 ID Tape
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 3
Install at the two ends to change the existing wire identification number. Refer to SWPM 20-10-11 as an accepted procedure. 2 61-74478-11106 ID Tape

Install at less than 6 inches from the connector. 1 61-74478-11103 ID Tape
Refer to SWPM 20-30-12 as an accepted procedure. 1 D-436-37 or D436-37 Splice 4
Refer to SWPM 20-10-14 as an accepted procedure. 1 61-74478-11105 ID 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 87: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 390 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME FLAG NOTE Install at the wire bundle breakout adjacent to the splice. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-11202 ID Tape 5

Refer to SWPM 20-61-11 as an accepted procedure. 3 BACC47CP1S Contact, Socket 6
Install at less than 6 inches from the connector. 1 61-74478-11201 ID Tape 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. 1 BACC45FT24-43S6 Connector 7 6 BACC47CP1S Contact, Socket Use one in each empty contact hole at the connector. Refer to SWPM 20-60-08 as an accepted procedure.(b) 20 MS27488-16-1 or Seal Plug 17 MS27488-20-1

Install at less than 6 inches from the connector. 1 61-74478-11104 ID Tape
Install at less than 12 inches from the connector. Refer to SWPM 20- 10-11 as an accepted procedure. 1 61-74478-11101
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 391 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 392 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 393 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are in the kit 65C38484-8. MORE DATA QTY IDENTIFICATION NAME TASK STEP To make a drip loop below the J2802 Box Assembly. (a) 1 W1764 WIRE BUNDLE Adjust 1 1 W1774 WIRE BUNDLE Adjust Tighten to close the clamps on the wire bundles. (a) 4 BACS38W2I (BACS38W2 or BACS38W2 optional) STRAP Install (New) 2
Around the adjacentwire bundle if installed. (b) 1 65C38484-14 (M23053/12-514-C)INSULATION SLEEVING, HEAT SHRINKABLE PTFE. Install (New) 3
Use sufficient quantity on the sleeve and wire bundles. 6 BACS38W2I (BACS38W2 or BACS38W2 optional) STRAP Install (New)

Refer to SWPM 20-81-22 as an accepted procedure. 2 TDH-1852-1502 or TDH1852-1502 Relay Install 4
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 394 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 19-20.

FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY (SHEET 1 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 395 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 396 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts are in the kit 65C38484-9. MORE DATA QTY IDENTIFICATION NAME TASK STEP To make a drip loop below the J2802 Box Assembly. (a) 1 W1764 WIRE BUNDLE Adjust 1 1 W1774 WIRE BUNDLE Adjust Tighten to close the clamps on the wire bundles. (a) 4 BACS38W2I (BACS38W2 or BACS38W2 optional) STRAP Install (New) 2
Around the adjacentwire bundle if installed. (b) 1 65C38484-14 (M23053/12-514-C)INSULATION SLEEVING, HEAT SHRINKABLE PTFE. Install (New) 3
Use sufficient quantity on the sleeve and wire bundles. 6 BACS38W2I (BACS38W2 or BACS38W2 optional) STRAP Install (New)

Refer to SWPM 20-81-22 as an accepted procedure. 4 TDH-1852-1502 or TDH1852-1502 Relay Install 4
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 397 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 398 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C25704-( ) P6-1 Panel Close 1 At the initial R54 and R55 relay locations. 2 KCD4N Relay Install (Kept) 2
To the initial location. 1 69-73627-( ) Relay Panel Move 3
5 NAS1801-3-8 Screw Install (Kept) 4 5 AN960PD10L Washer At the initial location if removed. 1 65-49815-( ) Channel Install (Kept) 5 Through the channel if removed. 8 NAS514P1032-( ) Bolt Install (Kept) 6
1 65C25704-( ) P6-2 Panel Close 7 1 69-41661-( ) Closure Panel Install (Kept) 8 1 65-49815-( ) Cover Install (Kept) 9 The panel has the captive screws. 1 69-41661-( ) Cover Panel Install (Kept) 10

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 399 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 17-20, 30.

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 400 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C25704-( ) P6-1 Panel Close 1 1 65C25704-( ) P6-3 Panel At the initial R54 and R55 relay locations. 2 KCD4N Relay Install (Kept) 2
At the initial R146and R147 relay locations. 2 10-60450-6 Relay Install (Kept) 3

To the initial location. 1 69-73627-( ) Relay Panel Move 4
5 NAS1801-3-8 Screw Install (Kept) 5 5 AN960PD10L Washer At the initial location if removed. 1 65-49815-( ) Channel Install (Kept) 6 Through the channel if removed. 8 NAS514P1032-( ) Bolt Install (Kept) 7
1 65C25704-( ) P6-2 Panel Close 8 1 69-41661-( ) Closure Panel Install (Kept) 9 1 65-49815-( ) Cover Install (Kept) 10 The panel has the captive screws. 1 69-41661-( ) Cover Panel Install (Kept) 11

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 401 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 402 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-10 J2802 BOX ASSEM- BLY Disassemble 1
6 BACS12HN3-8 Bolt Remove/Keep 6 NAS1149F0363P Washer 1 65C38484-6 Cover Remove

FIGURE 92: CHANGE OF 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 737-28A1216 Revision 3 July 16, 2014 403 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP From Disconnect Angle. 2 BACN10JC06CD Nut Remove/Keep 2 2 BACS12HN06-7 Bolt 1 BACC45FN24-43P Connector (D5208J) From GDY0001. Refer to SWPM 20-10- 11 as an accepted procedure. - W1760 Wires Disconnect

From Disconnect Angle. 2 BACN10JC06CD Nut Remove/Keep 3 2 BACS12HN06-7 Bolt 1 BACC45FN24-43P6 Connector (D5210J) From GDY0002. Refer to SWPM 20-10- 11 as an accepted procedure. - W1770 Wires Disconnect

(a) 4 BACR15BB( )D( )C Rivets Remove 4 2 287U0016-185 Disconnect Angle Remove/Keep From J2802 Box Assembly for new brackets to be fitted. 2 65C38484-12 Flange Cut 5

1 65C38484-12 Edge Deburr 6 Refer to SOPM 20-43-03 as an accepted procedure. - TYPE 2, CLASS A, or TYPE 5 CLASS F Chemical Conversion Coating Apply 7

Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 Primer Apply 8

Remove and clean any debris and/or metal shaving. (b) 1 65C38484-10 J2802 BOX ASSEM- BLY Clean 9
(c) 1 65C38484-31 Label-CTR-L Install (New) 10 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
(d) 1 65C38484-32 Label-CTR-R Install (New) 11 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 404 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (e) 2 65C38484-33 Label-NOT-USED Install (New) 12 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
(f) 1 65C38484-36 Label-TEST SWITCH- ES Install (New) 13 (g) 1 65C38484-37 Label-AUTO SHUTOFF Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
On the Top flange. Refer to SOPM 20-50-10 as an accepted procedure. 1 65C38484-16 J2802 BOX ASSEM- BLY Identify 14

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 405 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 17-18, 30.

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 406 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-11 J2802 BOX ASSEM- BLY Disassemble 1
6 BACS12HN3-8 Bolt Remove/Keep 6 NAS1149F0363P Washer 1 65C38484-6 Cover Remove

FIGURE 93: CHANGE OF 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 737-28A1216 Revision 3 July 16, 2014 407 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP From Disconnect Angle. 2 BACN10JC06CD Nut Remove/Keep 2 2 BACS12HN06-7 Bolt 1 BACC45FN24-43P Connector (D5208J) From GDY0001. Refer to SWPM 20-10- 11 as an accepted procedure. - Wires Disconnect

From Disconnect Angle. 2 BACN10JC06CD Nut Remove/Keep 3 2 BACS12HN06-7 Bolt 1 BACC45FN24-43P6 Connector (D5210J) From GDY0002. Refer to SWPM 20-10- 11 as an accepted procedure. - Wires Disconnect

(a) 4 BACR15BB( )D( )C Rivets Remove 4 2 287U0016-185 Disconnect Angle Remove/Keep From left and right ofJ2802 Box Assembly for new brackets to be fitted. 2 65C38484-12 Flange Cut 5

1 65C38484-12 Edge Deburr 6 Refer to SOPM 20-43-03 as an accepted procedure. - TYPE 2, CLASS A, or TYPE 5 CLASS F Chemical Conversion Coating Apply 7

Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 Primer Apply 8

Remove and clean any debris and/or metal shaving. (b) 1 65C38484-11 J2802 BOX ASSEM- BLY Clean 9
(c) 1 65C38484-31 Label-CTR-L Install (New) 10 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
(d) 1 65C38484-32 Label-CTR-R Install (New) 11 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 408 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (e) 1 65C38484-35 Label-AUX-AFT Install (New) 12 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
(f) 1 65C38484-34 Label-AUX-FWD Install (New) 13 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
(g) 1 65C38484-36 Label-TEST SWITCH- ES Install (New) 14 (h) 1 65C38484-37 Label-AUTO SHUTOFF Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
On the Top flange. Refer to SOPM 20-50-10 as an accepted procedure. 1 65C38484-16 J2802 BOX ASSEM- BLY Identify 15

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 409 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 14, 21-29, 31.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY 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 737-28A1216 Revision 3 July 16, 2014 410 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY 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 737-28A1216 Revision 3 July 16, 2014 411 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 94: 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 737-28A1216 Revision 3 July 16, 2014 412 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 413 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts to rework the J2802 Box Assembly are available in the supplemental kit, 65C37854-15. The kit possibly has more parts than necessary. MORE DATA QTY IDENTIFICATION NAME TASK STEP On the J2802 Box Assembly. (a) 1 65C38484-19 BRACKET Put/Hold 1
On Bracket as shown. 1 287U0016-185 DISCONNECT ANGLE Put/Hold 2
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. 4
- HOLE Drill 3

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) 2
- HOLE Drill 4

1 287U0016-185 DISCONNECT ANGLE Remove/Keep 5 1 65C38384-19 BRACKET On the J2802 Box Assembly. (a) 1 65C38484-18 BRACKET Put/Hold 6
On Bracket as shown. 1 287U0016-185 DISCONNECT ANGLE Put/Hold 7
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. 4
- HOLE Drill 8

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY 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 737-28A1216 Revision 3 July 16, 2014 414 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP 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) 2
- HOLE Drill 9

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. 1
- HOLE Drill 10

1 287U0016-185 DISCONNECT ANGLE Remove/Keep 11 1 65C38484-18 BRACKET 1 65C38484-19 BRACKET Deburr 12 1 65C38484-18 BRACKET 2 287U0016-185 DISCONNECT ANGLE 1 65C38484-16 J2802 BOX ASSEM- BLY 0.010 - 0.015 Inch deep on both sides of the panel. 2 65C38484-16 J2802 BOX ASSEM- BLY Countersink 13

Shave the rivet flush on both sides of the panel. (c) 2 BACR15BA6AD5C RIVET Install (New) 14

In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. 12 BACS12HN3-8 SCREW Install (New) 15 12 NAS1149D0316H WASHER 12 BACN10YR3CD NUT
1 65C38484-19 BRACKET Install (Kept) 1 65C38484-18 BRACKET 2 287U0016-185 DISCONNECT ANGLE Cut sufficient Grommet on assembly. (d) 4 BACG20Z-B000400 GROMMET Install (New) 16

- BAC 5010 Type 82 ADHESIVE Apply

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY 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 737-28A1216 Revision 3 July 16, 2014 415 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP Put in approximate position as shown. (e) 2 65C38484-30 J2802 RELAY BOX LABEL Install (New) 17

Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 TOP COAT Apply
(f) 1 65C38484-16 J2802 BOX ASSEM- BLY Clean 18
To J2802 Box Assembly Cover. (g) 2 65C38484-7 J2802 PANEL COVER SEAL Install (New) 19
Refer to SOPM 20-50-12 as an accepted procedure. - BAC 5010 Type 77 ADHESIVE Apply

0.245-0.255 Inchdia. Match drill existing holes in Cover through Cover Seal. 6
- HOLE Drill 20

1 65C38484-20 COVER Install (New) 21 6 BACS12HN3-8 BOLT Install (Kept) 6 NAS1149F0363P WASHER By abrasive cleaning for faying surface bonding. (h) 1
- HOLE Clean 22
On the top flange. Refer to SOPM 20-50-10 as an accepted procedure. 1 65C38484-43 J2802 BOX ASSEM- BLY Identify 23

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 416 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 417 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 418 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY 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 737-28A1216 Revision 3 July 16, 2014 419 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3 July 16, 2014 420 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 421 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Parts to rework the J2802 Box Assembly are available in the supplemental kit, 65C37854-15. The kit possibly has more parts than necessary. MORE DATA QTY IDENTIFICATION NAME TASK STEP On the J2802 Box Assembly. (a) 1 65C38484-19 BRACKET Put/Hold 1
On Bracket as shown. 1 287U0016-185 DISCONNECT ANGLE Put/Hold 2
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. 4
- HOLE Drill 3

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) 2
- HOLE Drill 4

1 287U0016-185 DISCONNECT ANGLE Remove/Keep 5 1 65C38384-19 BRACKET On the J2802 Box Assembly. (a) 1 65C38484-18 BRACKET Put/Hold 6
On Bracket as shown. 1 287U0016-185 DISCONNECT ANGLE Put/Hold 7
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. 4
- HOLE Drill 8

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY 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 737-28A1216 Revision 3 July 16, 2014 422 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP 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) 2
- HOLE Drill 9

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. 1
- HOLE Drill 10

1 287U0016-185 DISCONNECT ANGLE Remove/Keep 11 1 65C38484-19 BRACKET 1 65C38484-19 BRACKET Deburr 12 1 65C38484-18 BRACKET 2 287U0016-185 DISCONNECT ANGLE 1 65C38484-16 J2802 BOX ASSEM- BLY 0.010 - 0.015 Inch deep on both sides of the panel. 2 65C38484-16 J2802 BOX ASSEM- BLY Countersink 13

Shave the rivet flush on both sides of the panel. (c) 2 BACR15BA6AD5C RIVET Install (New) 14

In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. 12 BACS12HN3-8 SCREW Install (New) 15 12 NAS1149D0316H WASHER 12 BACN10YR3CD NUT
1 65C38484-19 BRACKET Install (Kept) 1 65C38484-18 BRACKET 2 287U0016-185 DISCONNECT ANGLE Cut sufficient Grommet on assembly. (d) 4 BACG20Z-B000400 GROMMET Install (New) 16

- BAC 5010 Type 82 ADHESIVE Apply

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY 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 737-28A1216 Revision 3 July 16, 2014 423 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP Put in approximate position as shown. (e) 2 65C38484-30 J2802 RELAY BOX LABEL Install (New) 17

Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 TOP COAT Apply
(f) 1 65C38484-16 J2802 BOX ASSEM- BLY Clean 18
To J2802 Box Assembly Cover. (g) 2 65C38484-7 J2802 PANEL COVER SEAL Install (New) 19
Refer to SOPM 20-50-12 as an accepted procedure. - BAC 5010 Type 77 ADHESIVE Apply

0.245-0.255 Inchdia. Match drill existing Cover holes through Cover Seal. 6
- HOLE Drill 20

1 65C38484-20 COVER Install (New) 21 6 BACS12HN3-8 BOLT Install (Kept) 6 NAS1149F0363P WASHER By abrasive cleaning for faying surface bonding. (h) 1
- HOLE Clean 22
On the top flange. Refer to SOPM 20-50-10 as an accepted procedure. 1 65C38484-40 J2802 BOX ASSEM- BLY Identify 23

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 424 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 425 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 426 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3 July 16, 2014 427 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 428 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP 6 BACS12HN3-8 Bolt Remove/Keep 1 6 NAS1149F0363P Washer 1 65C38484-20 COVER Part of wire bundle W1770. 1 BACC45FN24-43P6 CONNECTOR (D5210J) Install (Kept) 2
2 BACS12HN06-7 BOLT 2 BACN10JC06CD NUT To GDY0002. Refer to SWPM 20-10-11as an accepted procedure. - W1770 WIRES Install

Part of wire bundle W1760. 1 BACC45FN24-43P CONNECTOR (D5208J) Install (Kept) 3
2 BACS12HN06-7 BOLT 2 BACN10JC06CD NUT To GDY0001. Refer to SWPM 20-10-11as an accepted procedure. - W1760 WIRES Install

1 65C38484-20 COVER Install (Kept) 4 6 BACS12HN3-8 Bolt 6 NAS1149F0363P Washer

FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 429 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 430 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3 July 16, 2014 431 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 432 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP 6 BACS12HN3-8 Bolt Remove/Keep 1 6 NAS1149F0363P Washer 1 65C38484-20 COVER Part of wire bundle W1770. 1 BACC45FN24-43P6 CONNECTOR (D5210J) Install (Kept) 2
2 BACS12HN06-7 BOLT 2 BACN10JC06CD NUT To GDY0002. Refer to SWPM 20-10-11as an accepted procedure. - W1770 WIRES Install

Part of wire bundle W1760. 1 BACC45FN24-43P CONNECTOR (D5208J) Install (Kept) 3
2 BACS12HN06-7 BOLT 2 BACN10JC06CD NUT To GDY0001. Refer to SWPM 20-10-11as an accepted procedure. - W1760 WIRES Install

1 65C38484-20 COVER Install / Kept 4 6 BACS12HN3-8 Bolt 6 NAS1149F0363P Washer

FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 433 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 434 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 435 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 436 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 437 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 438 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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. MORE DATA QTY IDENTIFICATION NAME TASK STEP (a) (b) (j) 4
- RIVET Remove 1 From E2 Support Post. 1 BACN10DZ3-( ) CLAMP SUPPORT Remove 2 1 BACS12HN-( ) BOLT 1 NAS1149F0363P WASHER 1
- CLAMP Remove/Keep 0.128 - 0.135 Inchdia. 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. 1
- HOLE Drill 3

On the E2 and E3 Support Posts. (c) 1 65C38484-21 or 65C38484-43J2802 BOX ASSEMBLY Put/Hold 4
On the J2802 Box Assembly Brackets. (d) - - MARK Apply 5

65C38484-21 or 65C38484-43J2802 BOX ASSEMBLY Remove/Keep 6
On marked lines. 1 65C38484-21 or 65C38484-43J2802 BOX ASSEMBLY Cut 7Deburr To cut edges. Refer to SOPM 20-43-03as an accepted procedure. - ALODINE, TYPE 2, CLASS A OR TYPE 5, CLASS FCHEMICAL CONVERSION COATING Apply 8

To cut edges. Refer to SOPM 20-41-02as an accepted procedure. - BMS 10-11, Type 1 PRIMER

On the E2 and E3 Support Posts and against the LE Test switch Bracket. (e) 1 65C38484-21 or 65C38484-43J2802 BOX ASSEMBLY Put/Hold 9
1 BACF3F008E013NN FILLER 1 BACF3F013E043NN FILLER

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 737-28A1216 Revision 3 July 16, 2014 439 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP 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) 2
- HOLE Drill 10

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) 4
- HOLE Drill 11

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. 3
- HOLE Drill 12

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) 4
- HOLE Drill 13

(i)
- BMS 5-95, CLASS B SEALANT Apply 14 (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 locationwhere 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 440 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (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 moistureto 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 737-28A1216 Revision 3 July 16, 2014 441 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 442 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3 July 16, 2014 443 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3 July 16, 2014 444 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3 July 16, 2014 445 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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 737-28A1216 Revision 3 July 16, 2014 446 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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. MORE DATA QTY IDENTIFICATION NAME TASK STEP (a) (b) (j) 4
- RIVET Remove 1 From E2 Support Post. 1 BACN10DZ3-( ) CLAMP SUPPORT Remove 2 1 BACS12HN-( ) BOLT 1 NAS1149F0363P WASHER 1
- CLAMP Remove/Keep 0.128 - 0.135 Inchdia. 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. 1
- HOLE Drill 3

On the E2 and E3 Support Posts. (c) 1 65C38484-15 or 65C38484-40J2802 BOX ASSEMBLY Put/Hold 4
On the J2802 Box Assembly Brackets. (d) - - MARK Apply 5

65C38484-15 or 65C38484-40J2802 BOX ASSEMBLY Remove/Keep 6
On marked lines. 1 65C38484-15 or 65C38484-40J2802 BOX ASSEMBLY Cut 7Deburr To cut edges. Refer to SOPM 20-43-03as an accepted procedure. - ALODINE, TYPE 2, CLASS A OR TYPE 5, CLASS FCHEMICAL CONVERSION COATING Apply 8

To cut edges. Refer to SOPM 20-41-02as an accepted procedure. - BMS 10-11, Type 1 PRIMER

On the E2 and E3 Support Posts and against the LE Test switch Bracket. (e) 1 65C38484-15 or 65C38484-40J2802 BOX ASSEMBLY Put/Hold 9
1 BACF3F008E013NN FILLER 1 BACF3F013E043NN FILLER

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 737-28A1216 Revision 3 July 16, 2014 447 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP 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) 2
- HOLE Drill 10

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) 4
- HOLE Drill 11

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. 3
- HOLE Drill 12

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) 4
- HOLE Drill 13

(i)
- BMS 5-95, CLASS B SEALANT Apply 14 (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 locationwhere 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 737-28A1216 Revision 3 July 16, 2014 448 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (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 moistureto 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 737-28A1216 Revision 3 July 16, 2014 449 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 450 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP From the E2 and E3 Support Posts. 1 65C38484-21 or 65C38484-43J2802 BOX ASSEMBLY Remove/Keep 1
1 BACF3F008E013NN FILLER 1 BACF3F013E043NN FILLER Refer to SOPM 20-30-03 as an accepted procedure. 19
- HOLE Clean 2
By abrasive cleaning for faying surface bonding. (a) 1
- HOLE Clean 3

Refer to SOPM 20-30-03 as an accepted procedure. (b) 4
- HOLE Clean 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 451 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 452 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP From the E2 and E3 Support Posts. 1 65C38484-15 or 65C38484-40J2802 BOX ASSEMBLY Remove/Keep 1
1 BACF3F008E013NN FILLER 1 BACF3F013E043NN FILLER Refer to SOPM 20-30-03 as an accepted procedure. 19
- HOLE Clean 2
By abrasive cleaning for faying surface bonding. (a) 1
- HOLE Clean 3

Refer to SOPM 20-30-03 as an accepted procedure. (b) 4
- HOLE Clean 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 453 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 454 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP On the bolt shank, fillers and J2802 Box Assembly faying surface. (a) - BMS5-95 SEALANT Apply 1

Against E2 and E3 Support Posts. 1 65C38484-21 or 65C38484-43J2802 BOX ASSEMBLY Put/Hold 2
Between J2802 BoxAssembly and structure as shown. 1 BACF3F008E013NN FILTER 1 BACF3F013E043NN FILTER In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. (b) 4 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New) 3
4 BACC30BH5 COLLAR, PRELOAD

In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. 2 BACB30NX6K3 BOLT, PROTRUDING HD Install (New) 4
2 BACC30BH6 COLLAR, PRELOAD

On the bolt heads and fillet seal the collars. (c) - BMS5-95 SEALANT Apply 5
(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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 455 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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 737-28A1216 Revision 3 July 16, 2014 456 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP On the bolt shank, fillers and J2802 Box Assembly faying surface. (a) - BMS5-95 SEALANT Apply 1

Against E2 and E3 Support Posts. 1 65C38484-15 or 65C38484-40J2802 BOX ASSEMBLY Put/Hold 2
Between J2802 BoxAssembly and structure as shown. 1 BACF3F008E013NN FILLER 1 BACF3F013E043NN FILLER In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. (b) 4 BACB30NX5HK3 BOLT, PROTRUDING HD Install (New) 3
4 BACC30BH5 COLLAR, PRELOAD

In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. 2 BACB30NX6K3 BOLT, PROTRUDING HD Install (New) 4
2 BACC30BH6 COLLAR, PRELOAD

On the bolt heads and fillet seal the collars. (c) - BMS5-95 SEALANT Apply 5
(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 457 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 458 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 459 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 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 737-28A1216 Revision 3 July 16, 2014 460 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 461 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE: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. MORE DATA QTY IDENTIFICATION NAME TASK STEP Use a CLICO to locate the Spacer Nut Plate to the existing hole on J2802 Box Assembly. (a) 2 BACN10TL3A10 NUT, SPACER PLATE Put/Hold 1

Use a CLICO to locate the Spacer Nut Plate to the existing hole on J2802 Box Assembly. (a) (b) 2 BACN10TL3A14 NUT, SPACER PLATE Put/Hold 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) 4
- HOLE Drill 3

(a) 2 BACN10TL3A10 NUT, SPACER PLATE Install (New) 4 (a) (b) 2 BACN10TL3A14 NUT, SPACER PLATE (a) 8 BACR15BB4D( )C RIVET (a) 4 287T0011-1 CLAMP Install (New) 5 4 BACS12HN3-8 BOLT 4 NAS1149D0316H WASHER 2 287T0011-1 CLAMP Install (New) 6 2 BACS12HN3-8 BOLT 4 NAS1149D0316H WASHER 2 BACN10YR3CD NUT

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 462 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP (c) 1 BACJ40AB20-8 BONDING JUMPER Install (New) 7 2 BACS12HN3-7 BOLT 6 NAS1149D0316H WASHER 2 BACN10YR3CD NUT Between the bonding jumper and faying surfaces. The maximum resistance allowed is 0.001Ohms (1.0 milliohms). (d) (e) 1 BACJ40AB20-8 ELECTRICAL BOND- ING RESISTANCE Measure 8

Between the J2802 Box Assembly and the E2 Support post.The maximum resistance allowed is 3.5 Ohms. (d) (e) 1
- ELECTRICAL BOND- ING RESISTANCE Measure 9

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 FCONVERSION COATING Apply 10

Refer to SOPM 20-41-02 as an accepted procedure. - BMS10-11, TYPE 1 PRIMER FINISH Apply 11

Refer to SOPM 20-41-02 as an accepted procedure. (g) - BMS10-11, TYPE 2, COLOR WHITE ENAMEL FINISH Apply 12

Use a CLICO to locate the Spacer Nut Plate to the existing hole on E2 Support Post. 1 BACN10TL3A10 NUT, SPACER PLATE Put/Hold 13

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. 1
- HOLE Drill 14

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 463 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 BACN10TL3A10 NUT, SPACER PLATE Install (New) 15 2 BACR15BB4D( )C RIVET To attach existing cable bundle to E2 Support Post. 1
- CLAMP Install (Kept) 16

1 BACS12HN3-8 BOLT Install (New) 1 NAS1149D0316H WASHER (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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 464 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 465 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 466 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 467 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 4 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 468 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 469 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP (a) 1 W1764 WIRE BUNDLE Install 1 To make a drip loop below the J2802 Box Assembly. (a) 1 W1764 WIRE BUNDLE Adjust 2
(a) 1 W1774 WIRE BUNDLE Install 3 To make a drip loop below the J2802 Box Assembly. (a) 1 W1774 WIRE BUNDLE Adjust 4
(a) 4 287T0011-1 CLAMPS Tighten 5 4 BACS38W2 TIE STRAP (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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 470 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 471 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-20 COVER Remove/Keep 1 6 BACS12HN3-8 BOLT 6 NAS1149F0363P WASHER Refer to SWPM 20-81-22 as an accepted procedure. 2 TDH-1852-1502 or TDH1852-1502 RELAY Install 2

1 65C38484-20 COVER Install (Kept) 3 6 BACS12HN3-8 BOLT 6 NAS1149F0363P WASHER

FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 472 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 473 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-20 COVER Remove/Keep 1 6 BACS12HN3-8 BOLT 6 NAS1149F0363P WASHER Refer to SWPM 20-81-22 as an accepted procedure. 4 TDH-1852-1502 or TDH1852-1502 RELAY Install 2

1 65C38484-20 COVER Install (Kept) 3 6 BACS12HN3-8 BOLT 6 NAS1149F0363P WASHER

FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 474 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 475 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP (a) (b) 1 GD00422A GROUND STUD Inspect 1 (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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 476 of 490 BOEING SERVICE BULLETIN 737-28A1216This Figure applies only to: Group 14, 17-18, 21-31.

FIGURE 109: ELECTRONICS COMPARTMENT - MOISTURE SHROUD ANGLE AND STRAP - INSPECTION (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 477 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP (a) (b) 1 65-78254-19 MOISTURE SHROUD ANGLE Inspect 1 (a) (b) 1 65-78254-15 MOISTURE SHROUD 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 478 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 479 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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. MORE DATA QTY IDENTIFICATION NAME TASK STEP From Ground Stud, GD00422A. 1 W0346-115-22 WIRE Disconnect 1 From E2 Support Post. (a) 1 GD00422A STUD, GROUND Remove 2 From E2 Support Post. 1
- GD00422A LABEL
Refer to SOPM 20-30-03 as an accepted procedure. 1
- HOLE Clean 3
To edges of hole. (b)
- ALODINE, TYPE 2, CLASS A OR TYPE 5, CLASS FCHEMICAL CONVERSION COATING Apply 4
To edges of hole. (c)
- BMS 10-11, Type 1 PRIMER 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) 1
- HOLE Drill 5

By abrasive cleaning for faying surface bonding. (e) 1
- HOLE Clean 6
Do not tighten nut at this stage. (a) 1 BACS12GU3K10 SCREW Install (New) 7 1 BACW10EC3S WASHER, LOCK 2 NAS1149D0316H WASHER, PROTEC- TIVE 1 MS35650-305T NUT

- BMS 5-95, CLASS B SEALANT Apply Locate below new Ground Stud. (e) 1 BACT19J4 Tape GD00422A LABEL Install (New) 8
Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 TOP COAT Apply

FIGURE 110: ELECTRONICS COMPARTMENT - E2 SUPPORT POST - GROUND STUD LOCATION CHANGE (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 480 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP Between Ground Stud and E2 Support Post. The maximum resistance allowed is 0.0005 Ohms (0.5 milliohms). (e) (g) 1 GD00422A ELECTRICAL BOND- ING RESISTANCE Measure 9

To Ground Stud, GD00422A. (a) 1 W0346-115-22 WIRE Connect 10 Tighten nut to specified torque. (a) 1 MS35650-305T NUT Tighten
Between Ground Stud and W0346- 115-22 Terminal Lug. The maximum resistance allowed is 0.0005 Ohms (0.5 milliohms). (e) (g) 1 GD00422A ELECTRICAL BOND- ING RESISTANCE Measure 11

(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,cleanfaying 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 481 of 490 BOEING SERVICE BULLETIN 737-28A1216This 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 482 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND STRAP CHANGE (SHEET 2 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 483 of 490 BOEING SERVICE BULLETIN 737-28A1216FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND STRAP CHANGE (SHEET 3 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 484 of 490 BOEING SERVICE BULLETIN 737-28A1216The 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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 485 of 490 BOEING SERVICE BULLETIN 737-28A1216NOTE:Any new parts required will be Operator supplied. MORE DATA QTY IDENTIFICATION NAME TASK STEP From Moisture Shroud Angle on E3 Support Post. 3 BACN10JC08CD NUT Remove/Keep 1 6 NAS1149DN832J WASHER 3 BACS12CK08-10 SCREW 1 65-78950-12 MOISTURE SHROUD 1 65-78254-15 MOISTURE SHROUD STRAP On Moisture Shroud Angle. (a) - - MARK Apply 2 On top of Moisture Shroud Angle. (b) 1 65-78254-15 MOISTURE SHROUD STRAP Put/Hold 3
On Moisture Shroud Strap. (a) - - MARK Apply 4
1 65-78254-15 MOISTURE SHROUD STRAP Remove/Keep 5
From the inboard and outboard end ofMoisture Shroud Angle. (c) (d) (e) 2
- RIVET Remove 6

1 65-78254-19 MOISTURE SHROUD ANGLE Remove/Keep 7
On marked line. Do not change the Moisture Shroud. 1 65-78254-19 MOISTURE SHROUD ANGLE Cut 8Deburr On marked line. Do not change the Moisture Shroud. 1 65-78254-15 MOISTURE SHROUD STRAP Cut 9Deburr To cut edges. Refer to SOPM 20-43-03as an accepted procedure. - ALODINE, TYPE 2, CLASS A OR TYPE 5,CLASS FCHEMICAL CONVERSION COATING Apply 10

To cut edges. Refer to SOPM 20-41-02as an accepted procedure. - BMS10-11, TYPE 1 PRIMER

Cut sufficient Grommet on assembly. (f) 1 BACG20Z- 4B000400 GROMMET Install 11

- BAC 5010 Type 82 ADHESIVE Apply

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND STRAP CHANGE (SHEET 5 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 486 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP Align holes in Moisture Shroud, Angle and Strap. (g) 1 65-78254-19 MOISTURE SHROUD ANGLE Locate 12
1 65-78950-12 MOISTURE SHROUD 1 65-78254-15 MOISTURE SHROUD 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) 1
- HOLE Drill 13

1 65-78254-19 MOISTURE SHROUD ANGLE Assemble 14
1 65-78950-12 MOISTURE SHROUD 1 65-78254-15 MOISTURE SHROUD STRAP 3 BACS12CK08-10 SCREW 6 NAS1149DN832J WASHER 3 BACN10JC08CD NUT In the horizontal position on the E3 Support Post. 1 65-78254-19 MOISTURE SHROUD ANGLE Put/Hold 15
1 65-78950-12 MOISTURE SHROUD 1 65-78254-15 MOISTURE SHROUD STRAP In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. (i) 1 NAS1398D5AB4 RIVET Install (New) 16

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) 1
- HOLE Drill 17

FIGURE 111: ELECTRONICS COMPARTMENT - E3 SUPPORT POST - MOISTURE SHROUD ANGLE AND STRAP CHANGE (SHEET 6 OF 7) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 487 of 490 BOEING SERVICE BULLETIN 737-28A1216MORE DATA QTY IDENTIFICATION NAME TASK STEP In accordance with 737-300 SRM 51- 40-02, 737-400 SRM 51-40-02, or 737- 500 SRM 51-40-02. (k) 1 NAS1398D5AB4 RIVET Install (New) 18

(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) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 488 of 490 BOEING SERVICE BULLETIN 737-28A1216APPENDIX A: KIT ORDERING FLOW CHART (SHEET 1 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 489 of 490 BOEING SERVICE BULLETIN 737-28A1216APPENDIX A: KIT ORDERING FLOW CHART (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 3 July 16, 2014 490 of 490 BOEING SERVICE BULLETIN 737-28A1216