### Commercial Airplanes 

# 737 Service Bulletin ALERT Number: 737-28A1216 Original Issue: July 29, 2010 Revision 1: March 26, 2012 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 730-774). 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. 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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 1 of 434 4.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 2 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT

BLANK PAGETable of Contents Revision Transmittal Sheet............................................ 7 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 82 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 83 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 83 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . 116 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 116 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 117 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . 117 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 119 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 119 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 120 FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16]. . . . . . . . 146 FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER [Group 19-20]. . . . . . . . . . . 147 FIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 1-13, 15-16]. . . . . . . . . . . . . . . . . . . . . . . . . . . . 148 FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 [Group 1-16, 21-29, 31]. . . . . . . . . 151 FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 [Group 1-16, 21-29, 31]. . . . . . . . . 154 FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY [Group 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 157 FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30]. . . . . . . . . . . . 160 FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 [Group 17-20, 30]. . . . . . . . . . . . 162 FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30]. . . . . . . . . . . . 165

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 3 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 [Group 17-20, 30]. . . . . . . . . . . . 167 FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER [Group 1-13, 15-16, 19-20] . 170 FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 1-13, 15-16]. . . . . . . . . . 171 FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY [Group 19-20]. . . . . . . . . . . . . 174 FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST [Group 1-13, 15-16, 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 177 FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS [Group 1-13, 15-16, 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group 1-13, 15-16] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 182 FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS [Group 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 184 FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS [Group 1-13, 15-16, 19-20] . . 186 FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 1-16, 21-29, 31]. . . . . . 189 FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 1-16, 21-29, 31] . . . 191 FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036 [Group 1, 21]. . . . . . . . . . . . . . . 192 FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036 [Group 2-3, 22-23]. . . . . . . . . . . . 195 FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036 [Group 4-5, 24]. . . . . . . . . . . . . . 198 FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036 [Group 6-7, 25]. . . . . . . . . . . . . . 201 FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036 [Group 8, 26]. . . . . . . . . . . . . . . 204 FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 [Group 9, 31]. . . . . . . . . . . . . . . 207 FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036 [Group 10-11, 27-28]. . . . . . . . . . . 210 FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036 [Group 12, 29]. . . . . . . . . . . . . . 213 FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036 [Group 13]. . . . . . . . . . . . . . . . 216 FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036 [Group 14]. . . . . . . . . . . . . . . . 219 FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036 [Group 15]. . . . . . . . . . . . . . . . 222 FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036 [Group 16]. . . . . . . . . . . . . . . . 225 FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL [Group 17-20, 30]. . . . . . . . . 228 FIGURE 34: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 [Group 17-20, 30]. . . . . . 230 FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30]. . . . . . . . . . . . . . 231 FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30]. . . . . . . . . . . . . . 234 FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036 [Group 19, 30]. . . . . . . . . . . . . . 237 FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036 [Group 17]. . . . . . . . . . . . . . . . 240 FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036 [Group 17]. . . . . . . . . . . . . . . . 243 FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036 [Group 17]. . . . . . . . . . . . . . . . 246 FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20]. . . . . . . . . . . . . . 249 FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20]. . . . . . . . . . . . . . 252 FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036 [Group 18, 20]. . . . . . . . . . . . . . 255 FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 1-16, 21-29, 31] . . . 258 FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044 [Group 1, 21]. . . . . . . . . . . . . . . 259 FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 1]. . . . . . 261 FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044 [Group 2, 22, Configuration 2]. . . . . . 263 FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044 [Group 3, 16, 23]. . . . . . . . . . . . . 265 FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 1]. . . . . . . . 267 FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044 [Group 4, Configuration 2]. . . . . . . . 269 FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 [Group 5, 8, 24, 26]. . . . . . . . . . . . 271 FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 1]. . . . . . 273

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 4 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 53: CONNECTION OF THE WIRE BUNDLE W044 [Group 6, 25, Configuration 2]. . . . . . 275 FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044 [Group 9, 31]. . . . . . . . . . . . . . . 277 FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044 [Group 10, 27]. . . . . . . . . . . . . . 279 FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 1]. . . . . 281 FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044 [Group 12, 29, Configuration 2]. . . . . 283 FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044 [Group 13]. . . . . . . . . . . . . . . . 285 FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044 [Group 7]. . . . . . . . . . . . . . . . . 287 FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 1]. . . . . . . 289 FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044 [Group 14, Configuration 2]. . . . . . . 291 FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 1]. . . . . 293 FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044 [Group 11, 28, Configuration 2]. . . . . 295 FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 1]. . . . . . . 297 FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044 [Group 15, Configuration 2]. . . . . . . 299 FIGURE 66: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 [Group 17-20, 30]. . . . . . 301 FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 1]. . . . . . . 302 FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2]. . . . . . . 305 FIGURE 69: CONNECTION OF WIRE BUNDLE W044 [Group 17, Configuration 1]. . . . . . . . . . 308 FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044 [Group 17, Configuration 2]. . . . . . . 311 FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1]. . . . . . . 314 FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2]. . . . . . . 317 FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 1]. . . . . . . 320 FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044 [Group 18, Configuration 2]. . . . . . . 323 FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30]. . . . . . . . . . . . . . 326 FIGURE 76: CONNECTION OF WIRE BUNDLE W044 [Group 19, 30, Configuration 1]. . . . . . . . 329 FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044 [Group 19, 30, Configuration 2]. . . . . 332 FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1]. . . . . . . 335 FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2]. . . . . . . 338 FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 1]. . . . . . . 341 FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044 [Group 20, Configuration 2]. . . . . . . 344 FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 [Group 1-16, 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 347 FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 1-16, 21-29, 31]. . . . . 351 FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 [Group 17-20, 30]. . . . . . . . 354 FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 8, 16, 26]. . . . . . . . . . . 357 FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 1-7, 9-15, 21-25, 27-29, 31] . 359 FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 [Group 17-20, 30]. . . . . . . . . . 361 FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group 1-16] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 364 FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY [Group 19-20] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 367 FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 1-16, 21-29, 31]. . . . . . 370 FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL [Group 17-20, 30]. . . . . . . . . 372 FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 374 FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 377

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 5 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 381 FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 387 FIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31]. . . . . . . . . . . . . . . . . . . 393 FIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30]. . . . . . . . . . . . . . . . . . . . . 397 FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31]. . . . . . . . . . . . . . . . . . . 401 FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30]. . . . . . . . . . . . . . . . . . . . . 406 FIGURE 100: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR AIRPLANE WITH AIRSTAIRS [Group 14, 21-29, 31]. . . . . . . . . . . . . . . . . . . . 411 FIGURE 101: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30]. . . . . . . . . . . . . . . . . . . . . 413 FIGURE 102: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31]. . . . . . . . . . . . . . . . . . . 415 FIGURE 103: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30]. . . . . . . . . . . . . . . . . . . . . 417 FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS [Group 14, 17-18, 21-31]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 419 FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS [Group 14, 17-18, 21-31]. . . . . . . . . . . . . . . . . . . . . . . . . . . . 425 FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 14, 21-29, 31]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 431 FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS [Group 17-18, 30]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 433

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 6 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT

### Commercial Airplanes 

# 737 Service Bulletin ALERT Revision Transmittal Sheet Number: 737-28A1216 Original Issue: July 29, 2010 Revision 1: March 26, 2012 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. More work is 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 relay 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. 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. 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. REASON FOR REVISION This revision is sent to tell the operators that for airplanes with Airstairs the J2802 Box provided in the original release 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 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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 7 of 434New steps are added to Figure 3 that instruct the operators to install markers on the J2802 Box 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 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" if necessary. These sections were changed: 1. Summary: a. Background: Updated PART 1 and PART 3. Changed PART 2 for airplanes with Airstairs. Added PART 4, PART 5, and PART 6 for airplanes with Airstairs. b. Material Information paragraph added Operator Supplied Parts/Materials. c. Summary Illustration updated to include airplanes with Airstairs. 2. Planning Information: a. Paragraph 1.A Effectivity: Changed the Group Configuration Table. Created new groups with airplane with Airstairs. b. Paragraph 1.C Reason: Added the reason for Revision 1. c. Paragraph 1.D. Description: Updated PART 1 and PART 3. Changed PART 2 for airplanes with Airstairs. Added PART 4, PART 5, and PART 6 for airplanes with Airstairs. d. Paragraph 1.G. Manpower: Changed Manpower Tables for Groups 14, 17, and 18. Added Manpower tables for Groups 21 through 31. e. Paragraph 1.H. Weight and Balance Changes: Added Groups 21 and 31 to Weight and Balance table. f. Paragraph 1.J.1. References, Existing Data: Updated the reference list. g. Paragraph 1.J.3. Installation Drawings Used in the Preparation of this Service Bulletin: Updated the Drawings list. h. Paragraph 1.K.1. Publications: Updated the publication list. 3. Material Information:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 8 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTa. Paragraph 2.A. Material - Price and Availability: Notes are added, kit pricing data is updated, and new top kits and supplemental kits are added. b. Paragraph 2.C.1. Parts Necessary For Each Airplane: Parts for the new top kits and supplemental kits and new footnotes are added. c. Paragraph 2.C.2. Part and Materials Supplied by the Operator: New materials are added. d. Paragraph 2.C.3. Parts Modified and Reidentified: New data is added for airplanes with airstairs. 4. Paragraph 3.B. Work Instructions: Updated PART 1 and PART 3. Changed PART 2 for airplanes with Airstairs. Added PART 4, PART 5, and PART 6 for airplanes with Airstairs 5. Changed Figures 3-10, 12-18, 82-84, 88-89: Group effectivities are updated. 6. Figures 92-107: Added these figures for airplane with airstairs. The data given in Information Notice 737-28A1216 IN 01, 737-28A1216 IN 02, and 737-28A1216 IN 03 are included in this revision. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. REVISION HISTORY July 29, 2010 Original Issue: March 26, 2012 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 9 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTBOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 10 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT

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### Commercial Airplanes 

# 737 Service Bulletin ALERT Summary Number: 737-28A1216 Original Issue: July 29, 2010 Revision 1: March 26, 2012 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 BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 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).

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 11 of 434ACTION (PRR 35442-RS) The work instructions are divided into 31 airplane groups, 6 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 release, and want to re-work the kit for airplanes with Airstairs. 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: 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. 2. Work Package 2:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 12 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGet 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. FAA may release an AD to require that all airplanes that have AUX tanks with Fuel Boost Pumps should 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 13 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 14, 21-29, 31: PART 4 - AIRPLANES WITH CENTER FUEL TANKS AND WITHOUT AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS 1. Work Package 1: Change J2802 Box Assy in accordance with PART 6 if necessary. 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 30: PART 5 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS 1. Work Package 1: Change J2802 Box Assy in accordance with PART 6 if necessary. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 14 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTIn 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 Assy for airplanes with Airstairs. NOTE:Operators that have airplanes with Airstairs that ordered and received the Top Kits given in the original release 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. EFFECTIVITY 737-300/400/500 airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. 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 36 months after the original issue 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 15 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTBOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 16 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT

### Commercial Airplanes 

# 737 Service Bulletin ALERT Number: 737-28A1216 Original Issue: July 29, 2010 Revision 1: March 26, 2012 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 BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 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. FAA may release an AD to require that all airplanes that have AUX tanks with Fuel Boost Pumps should 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 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 or R1 incorporated. 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 17 of 434DESCRIPTION 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 R0 or R1 incorporated. - 3

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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 R0 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 R0 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 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 or R1 incorporated. 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 18 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTDESCRIPTION CONFIGURATION GROUP 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 or R1 incorporated. 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 19 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTDESCRIPTION CONFIGURATION GROUP Airplanes that have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 19
Airplanes with SB 737-28A1212 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 or R1 incorporated. 2 Airplanes that have the auxiliary fuel tanks and have different wiring configurations at the P5 and P6 panels. - 20
Airplanes with SB 737-28A1212 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 R0 or R1 incorporated. - 27

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 20 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTDESCRIPTION CONFIGURATION GROUP 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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. - 29
Airplanes with SB 737-28A1212 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 or R1 not incorporated. 1 Airplanes with SB 737-28A1212 R0 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 R0 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 - PM564 6 PP001 - PP054 29 PP101 12 PP102 - PP169

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 21 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup Variable Number6 PP181 - PP187 7 PP188 - PP199 25 PP201 - PP205 14 PP221 6 PP231 - PP243 6 PP281 - PP286 6 PP301 - PP305 25 PP351 - PP353 25 PP376 - PP384 25 PP391 - PP393 6 PP401 - PP440 20 PP471 - PP475 18 PP501 - PP520 25 PP521 - PP522 6 PP631 - PP634 25 PP651 - PP652 6 PP671 - PP689 20 PP690 - PP694 6 PP695 - PP699 6 PP701 - PP706 20 PP707 - PP716 6 PP717 - PP733 6 PP771 - PP779 25 PP801 - PP808 25 PP821 - PP827 22 PP831 - PP848 28 PP851 - PP852 11 PP861 - PP877 28 PP891 - PP899 28 PP901 - PP936 28 PP946 - PP948 28 PP951 - PP952 11 PP961 - PP965

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 22 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup Variable Number3 PP966 - PP967 11 PP981 - PP982 3 PP983 - PP990 11 PP991 23 PP993 11 PQ001 - PQ016 11 PQ026 - PQ041 11 PQ051 - PQ092 11 PQ101 - PQ199 11 PQ201 - PQ202 23 PQ221 - PQ230 11 PQ231 - PQ232 10 PQ233 - PQ23728 PQ241 - PQ242 27 PQ243 27 PQ251 - PQ26727 PQ281 - PQ291 10 PQ292 - PQ29727 PQ298 10 PQ299 10 PQ301 - PQ307 10 PQ331 - PQ332 10 PQ341 - PQ34827 PQ361 - PQ37327 PQ391 - PQ39527 PQ401 - PQ41827 PQ421 10 PQ431 - PQ43827 PQ447 - PQ448 10 PQ451 10 PQ454 10 PQ471 27 PQ472 - PQ475

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 23 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup Variable Number10 PQ479 - PQ481 10 PQ486 - PQ487 10 PQ491 - PQ493 10 PQ771 - PQ772 10 PQ791 - PQ793 16 PQ801 - PQ805 16 PQ931 - PQ93527 PQ951 27 PQ971 - PQ99723 PR001 - PR017 23 PR021 - PR030 3 PR031 - PR034 3 PR041 - PR045 3 PR061 - PR072 3 PR077 - PR080 23 PR081 - PR082 23 PR091 - PR092 23 PR096 23 PR101 23 PR121 - PR122 23 PR131 - PR132 23 PR141 - PR143 23 PR161 - PR172 16 PR181 22 PS601 - PS631 22 PS636 - PS638 22 PS641 - PS642 2 PS643 - PS644 23 PS651 - PS657 10 PS666 - PS669 3 PS691 - PS692 11 PS701 - PS706 12 PS751 - PS799

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 24 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup Variable Number23 PS811 23 PS836 - PS837 22 PS841 - PS846 22 PS851 - PS852 22 PS856 17 PS861 - PS863 17 PS866 - PS868 22 PS871 - PS874 22 PS896 - PS897 15 PS901 - PS941 17 PS956 - PS957 23 PS961 - PS963 23 PS971 - PS978 3 PT001 - PT015 3 PT021 - PT031 23 PT041 - PT064 3 PT101 - PT105 23 PT121 - PT138 23 PT146 - PT148 23 PT161 - PT170 31 PT181 - PT185 9 PT186 - PT188 23 PT211 - PT220 23 PT295 3 PT301 - PT309 10 PT331 - PT360 3 PT381 - PT399 3 PT401 - PT438 27 PT501 - PT517 3 PT561 - PT565 3 PT581 - PT586 10 PT611 - PT621 3 PT641 - PT644

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 25 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup Variable Number3 PT651 - PT656 27 PT671 - PT672 3 PT681 - PT685 13 PT701 - PT703 3 PT716 - PT717 23 PT721 - PT725 10 PT801 - PT834 3 PT851 - PT854 23 PT871 - PT886 10 PT901 - PT930 10 PT971 - PT973 3 PT981 - PT985 23 PT996 10 PU001 - PU025 23 PU301 23 PU311 - PU313 4 PV001 5 PV002 - PV055 1 PV201 - PV209 1 PV226 - PV229 8 PV231 - PV237 1 PV271 - PV272 1 PV281 - PV287 21 PV296 21 PV301 - PV302 1 PV351 31 PV356 - PV357 21 PW001 - PW05421 PW061 1 PW062 - PW06821 PW072 21 PW086 - PW08821 PW091 - PW094

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 26 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup Variable Number21 PW101 - PW10221 PW106 21 PW111 - PW12021 PW156 - PW15721 PW161 - PW171 1 PW201 - PW25221 PW261 - PW26821 PW271 - PW27621 PW278 21 PW281 - PW29321 PW296 26 PW301 - PW327 1 PW401 - PW408 1 PW411 - PW418 1 PW421 - PW424 1 PW431 - PW4358 PW441 - PW450 1 PW461 - PW46721 PW501 - PW50419 PW511 - PW52219 PW524 1 PW525 - PW52919 PW530 5 PW531 - PW55024 PW556 - PW557 1 PW561 - PW564 1 PW571 - PW57621 PW591 - PW5965 PW611 - PW6225 PW631 - PW63724 PW661 - PW6625 PW681 - PW68330 PW701 - PW702

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 27 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup Variable Number1 PW711 - PW71724 PW741 - PW7425 PW761 1 PW771 31 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 2, dated Feb 10/2010 BAE

Gives instruction to replace the P5-2 fuel system module assembly to supply Low fuel pressure master caution Annunciation. 737-28A1210, Revision 1 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 28 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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). Other related airplane service bulletins are Service Bulletin 737-28A1228 for the 737-100/200 airplanes and Service Bulletin 737-28A1206 for the 737-600/700/800/900 airplanes. Revision 1: This revision is sent to tell the operators that for airplanes with Airstairs the J2802 Box provided in the original release 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 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 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 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 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" if necessary.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 29 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe data given in Information Notice 737-28A1216 IN 01, 737-28A1216 IN 02, and 737-28A1216 IN 03 are included in this revision. D. Description The work instructions are divided into 31 airplane groups and 6 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 release, and want to re-work the kit for airplanes with Airstairs. 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: 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 30 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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. 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. FAA may release an AD to require that all airplanes that have AUX tanks with Fuel Boost Pumps should 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 31 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTIn 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: Change J2802 Box Assy if/as necessary. 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 30: PART 5 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS 1. Work Package 1: Change J2802 Box Assy if/as necessary.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 32 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTIn 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, 17-18, 21-31: PART 6 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS, AND AIRSTAIRS 1. Change J2802 Box Assy for airplanes with Airstairs. NOTE:Operators that have airplanes with Airstairs that ordered and received the Top Kits given in the original release 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. Revision 1: More work is 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 relay 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. 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. 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 33 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 34 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTE. 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 36 months after the original issue 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 1, 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-20in 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 35 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT— 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 36 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 37 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 38 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 39 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 40 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 41 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 42 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 43 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 44 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 45 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 46 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 47 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 11, Configuration 1: 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 48 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 49 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 50 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 51 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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 88 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 54.00 96.75 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. Group 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 52 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 14, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
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 88 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 54.00 96.75 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 53 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 15, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
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. Group 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 54 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 15, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 55 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 16: Elapsed Hours Task-Hours Number of Per- sons Task

- - 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 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) 3.00 3.00 1 FIGURE 89 1.50 1.50 1 FIGURE 91 3.00 3.00 1 FIGURE 93 (e)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 56 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 17, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
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

- - 1 FIGURE 105 (a) 0.75 0.75 1 FIGURE 107 4.00 12.00 3 Close Access 1.00 2.00 2 Test 84.75 154.90 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 release of this service bulletin and they need to change the J2802 Box Assembly. (f) See related wire connection figure for wire routing task hours. 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 57 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 17, Configuration 2: 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)

- - 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) 3.00 3.00 1 FIGURE 89 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

- - 1 FIGURE 105 (a) 0.75 0.75 1 FIGURE 107 4.00 12.00 3 Close Access 1.00 2.00 2 Test 84.75 154.90 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 release of this service bulletin and they need to change the J2802 Box Assembly. (f) See related wire connection figure for wire routing task hours.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 58 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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 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 (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) 3.00 3.00 1 FIGURE 89 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

- - 1 FIGURE 105 (a) 0.75 0.75 1 FIGURE 107 4.00 12.00 3 Close Access

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 59 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 18, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
1.00 2.00 2 Test 90.40 160.55 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 release of this service bulletin and they need to change the J2802 Box Assembly. (f) See related wire connection figure for wire routing task hours. 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 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 (b) 2.30 4.60 2 FIGURE 43 (b)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 60 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 18, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task

- - 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) 3.00 3.00 1 FIGURE 89 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

- - 1 FIGURE 105 (a) 0.75 0.75 1 FIGURE 107 4.00 12.00 3 Close Access 1.00 2.00 2 Test 90.40 160.55 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 release of this service bulletin and they need to change the J2802 Box Assembly. (f) See related wire connection figure for wire routing task hours.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 61 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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) 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 62 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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

- - 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 63 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 20, 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) 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 64 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 65 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 66 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 22, 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 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 67 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 22, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task

- - 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 49.55 92.30 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 68 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 23: Elapsed Hours Task-Hours Number of Per- sons Task

- - 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) 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 69 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 70 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 25, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 71 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 25, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 72 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 26: 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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 0.50 0.50 1 FIGURE 100

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 73 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 27: Elapsed Hours Task-Hours Number of Per- sons Task
0.60 0.60 1 FIGURE 102 2.30 2.30 1 FIGURE 104

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 74 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 28, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task

- - 1 FIGURE 105 0.65 0.65 1 FIGURE 106 4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 75 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 28, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Close Access 1.00 2.00 2 Test 52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. Group 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 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.55 91.30 TOTAL FOR EACH AIRPLANE

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 76 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 29, 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. (b) The task hours for this figure to be used only if operators ordered and received the Top Kits given in the original release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test 48.55 91.30 TOTAL FOR EACH AIRPLANE (a) This figure shows wire routes only. See the related wire connection figure for task hours.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 77 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 29, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task (b) The task hours for this figure to be used only if operators ordered and received the Top Kits given in the original release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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 0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103

- - 1 FIGURE 105 0.75 0.75 1 FIGURE 107 4.00 12.00 3 Close Access 1.00 2.00 2 Test

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 78 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 30, Configuration 1: Elapsed Hours Task-Hours Number of Per- sons Task
81.60 151.75 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. 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 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 0.50 0.50 1 FIGURE 101 0.60 0.60 1 FIGURE 103

- - 1 FIGURE 105 0.75 0.75 1 FIGURE 107

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 79 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 30, Configuration 2: Elapsed Hours Task-Hours Number of Per- sons Task
4.00 12.00 3 Close Access 1.00 2.00 2 Test 81.60 151.75 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. Group 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 4.00 12.00 3 Close Access 1.00 2.00 2 Test

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 80 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 31: Elapsed Hours Task-Hours Number of Per- sons Task
52.35 95.10 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 release of this service bulletin and they need to change the J2802 Box Assembly. (c) See related wire connection figure for wire routing task hours. H. Weight and Balance Changes Group 1-13, 15-16, 19-20: AIRPLANES WITHOUT AIRSTAIRS Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane
+1,300 +6 Each 737-300 +900 +6 Each 737-400 +1,650 +6 Each 737-500 Group 14, 17-18, 21-31: AIRPLANES WITHOUT AIRSTAIRS Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane
+1,400 +6.4 Each 737-300 +950 +6.4 Each 737-400 +1,750 +6.4 Each 737-500
I. Electrical Load Data 1. Direct Current (DC) Loads Group 1-16: Bus Amperes Circuit Breaker 28V DC Bus 1 150 Milliampere C3318 28V DC Bus 2 150 Milliampere C3320 Group 17-20: Bus Amperes Circuit Breaker 28V DC Bus 1 150 Milliampere C3318

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 81 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 17-20: Bus Amperes Circuit Breaker 28V DC Bus 2 150 Milliampere C3320 28V DC Bus 1 150 Milliampere C3327 28V DC Bus 2 150 Milliampere C3329 2. Alternating Current (AC) Loads 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 d. Federal Aviation Administration (FAA) Notice of Proposed Rule Making (NPRM) 2010-NM-189-AD e. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-43-03, 20-44-01 , 20-50-10, 20-50-19 f. Standard Wiring Practices Manual (SWPM) 20-10-04, 20-10-11, 20-10-12, 20-10-14, 20-10-18, 20-10-19, 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, 25-51-01, 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 j. 737-400 Structural Repair Manual (SRM) 51-40-02, 51-40-05 k. 737-500 Structural Repair Manual (SRM) 51-40-02, 51-40-05 l. BAE Systems Service Bulletin 69-37335-28-04 2. Data supplied with this Service Bulletin: None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 82 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT3. 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 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, NP and NNC 737 Operations Manual 28-22 737 Maintenance Manual 28-23, 28-43 737 Wiring Diagram Manual 28-23 737 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. L. Interchangeability and Intermixability of Parts None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 83 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTBOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 84 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT

BLANK PAGE2. MATERIAL INFORMATION A. Material - Price and Availability 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 Boeing can supply the kits in Paragraph 2.C., Parts Necessary for Each Airplane as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. Group 1-13, 15-16: Unit Price thru 31-Dec-2012 ROLT (Weeks) QTY Date Name Kit Number $9,869.00

- 200 Available Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-7 (a) 2 50 08/16/2012 $227.00

- 105 Available Supplemental Kit - New La- bels For J2802 Relay Box 65C37854-16 2 50 03/30/2012 (a) One top kit is necessary for each airplane in Groups 1 through 16. Group 17-20: Unit Price thru 31-Dec-2012 ROLT (Weeks) QTY Date Name Kit Number $9,758.00 75 10 Available Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-8 (a) (b)

$227.00

- 105 Available Supplemental Kit - New Labels For J2802 Relay Box 65C37854-16 2 50 03/30/2012 (a) One top kit is necessary for each airplane in Groups 17 through 20. (b) Airplanes in Group 17 and Group 18 have been delivered with wire provisions for Auxiliary Tanks installation. If Auxiliary Tanks have been installed on these airplanes operators need to order this kit. If Auxiliary Tanks have not been installed on these airplanes there are more parts than necessary in this kit. Operators need to order only the necessary parts to incorporate the Auto Shutoff system for the Center Tanks. The necessary parts can be ordered as end item parts. Contact Boeing Spares for ordering the necessary end item parts from kit 65C38471-8.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 85 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 14, 21-29, 31: Unit Price thru 31-Dec-2012 ROLT (Weeks) QTY Date Name Kit Number $10,358.00

- 250 Available Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-11 (a)

2 10 08/16/2012 (a) One top kit is necessary for each airplane in Groups 21-29 and 31.
Or: NOTE:Operators that have airplanes with Airstairs that ordered and received the Top Kits given in the original release 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 14, 21-29, 31: Unit Price thru 31-Dec-2012 ROLT (Weeks) QTY Date Name Kit Number $9,869.00

- 200 Available Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-7 (a) 2 50 08/16/2012 $2,106.00 Supplemental Kit - J2802 Relay Box Modification For Airplanes With Airstairs 65C37854-15 (a)

$227.00

- 105 Available Supplemental Kit - New La- bels For J2802 Relay Box 65C37854-16 (a) 2 50 03/30/2012 (a) One top kit and the two supplemental kits are necessary for each airplane in Groups 21-29 and 31.
Group 30: Unit Price thru 31-Dec-2012 ROLT (Weeks) QTY Date Name Kit Number $13,976.00

- 1 Available Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center and Auxiliary Fuel Tanks 65C38471-12 (a)

18 (a) One top kit is necessary for each airplane in Group 30.
Or: NOTE:Operators that have airplanes with Airstairs that ordered and received the Top Kits given in the original release 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 86 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTGroup 30: Unit Price thru 31-Dec-2012 ROLT (Weeks) QTY Date Name Kit Number $9,758.00 75 10 Available Top Kit- Fuel Tank BoostPump Auto Shut Off System, Center Fuel Tank 65C38471-8 (a)

$2,106.00 Supplemental Kit - J2802 Relay Box Modification For Airplanes With Airstairs 65C37854-15 (a)

$227.00

- 105 Available Supplemental Kit - New La- bels For J2802 Relay Box 65C37854-16 (a)

2 50 03/30/2012 (a) One top kit and the two supplemental kits are necessary for each airplane in Group 30. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE:One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 87 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C38471 Notes Existing Part Number Name QTY New Part Number -12 -11 -8 -7 TOP KIT-BOOST PUMP, AUTO S/O, CTR TANK, AIRSTAIRS 737- 300/-400/-500 . - . . 65C38471-11

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

TOP KIT-FUEL BOOST PUMP, AUTO SHUT OFFSYSTEM, 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

KIT - JBOX INSTALLATION FOR AIRPLANES WITHOUT AUX TANK . . . 1 65C38484-8

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

. 65C38484-9

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 88 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C37854 Notes Existing Part Number Name QTY New Part Number -16 -15 Supplemental Kit - J2802 Relay Box Modification For Airplanes With Airstairs . - 65C37854-15

Supplemental Kit - New Labels For J2802 Relay Box - . 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 1

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

. 65C38484-31 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 89 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C37854 Notes Existing Part Number Name QTY New Part Number -16 -15 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
Kit 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 90 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -2 -1 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 (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 91 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 (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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 92 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 (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 (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 93 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -106 -105 -104 -103 -102 -101 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. (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 94 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -112 -111 -110 -109 -108 -107 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
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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 95 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -112 -111 -110 -109 -108 -107 (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

(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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 96 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -112 -111 -110 -109 -108 -107 (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 (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 97 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -10101 -2006 -2005 -2003 -2002 -2001 (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. (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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 98 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -10107 -10106 -10105 -10104 -10103 -10102 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
CONNECTOR I.D. TAPE - D04212P - . . . . . 61-74478-10205
SPLICE I.D. SLEEVE - SM118 . . . . . - 61-74478-10108
CONNECTOR I.D. TAPE - D04026P . . . . - . 61-74478-10201
CONNECTOR I.D. TAPE - D04132P . . . - . . 61-74478-10202
CONNECTOR I.D. TAPE - D04154P . . - . . . 61-74478-10203
CONNECTOR I.D. TAPE - D04156P . - . . . . 61-74478-10204
CONNECTOR I.D. TAPE - D04212P - . . . . . 61-74478-10205
TAPE, ID 1 1 1 1 1

. BACT19C-T MARKER SLEEVE

. . . . . 1 TMSSCE14-2-4

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 99 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 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
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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 100 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 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
CONNECTOR I.D. TAPE - D01608 . . . . . - 61-74478-10302
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
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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 101 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -10404 -10403 -10402 -10401 -10309 -10308 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
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

WIRE BUNDLE I.D. TAPE - 61- 31760-001 . . . . . - 61-74478-10501

CONNECTOR I.D. TAPE - D05208J . . . . - . 61-74478-10502
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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 102 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -10701 -10602 -10601 -10503 -10502 -10501 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
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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 103 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 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

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 104 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -11106 -11105 -11104 -11103 -11102 -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
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
Kit 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

CONNECTOR I.D. TAPE - D04212J . - 61-74478-11201

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 105 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 61-74478 Notes Existing Part Number Name QTY New Part Number -11202 -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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 106 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 107 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 108 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 109 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 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

KIT - SLEEVING

. . . . . - 65C38484-14

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 110 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C38484 Notes Existing Part Number Name QTY New Part Number -19 -18 -17 -16 -15 -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
J2802 PANEL COVER SEAL . . . . 2

. 65C38484-7
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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 111 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C38484 Notes Existing Part Number Name QTY New Part Number -19 -18 -17 -16 -15 -14 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 112 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C38484 Notes Existing Part Number Name QTY New Part Number -19 -18 -17 -16 -15 -14 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
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

KIT - SLEEVING 1 1

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

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

. 65C38484-17
J2802 PANEL COVER . . 1
- 65C38484-20
KIT ASSY - J2802 JBOX . 1
- . 65C38484-21

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 113 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C38484 Notes Existing Part Number Name QTY New Part Number -23 -22 -21 -20 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

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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 114 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C38484 Notes Existing Part Number Name QTY New Part Number -23 -22 -21 -20 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 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 115 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTKit 65C38484 Notes Existing Part Number Name QTY New Part Number -23 -22 -21 -20 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) CLEAR SKYDROL RESIS- TANT TOPCOATING 1 Ounce BAC5710 TYPE 41 (a) TAPE, ELECTRICAL PAN- EL LABELING 2 BACT19J2 (a) TAPE, ELECTRICAL PAN- EL LABELING 6 BACT19J4 (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Parker-Amchemm, Henkel Surface Technologies 32100 Stephens Highway Madison Heights, Michigan 48071 U.S.A. Supplier Code: V84063. (c) Essex Chemical Corp. Pro-seal Div. 19451 Susana Road Compton, CA 90221 U.S.A. Supplier Code: V83527.
3. Parts Modified and Reidentified:
Notes New Part Number Name QTY Existing Part Number (b) (d) 65C38484-16 (c) J-Box Assembly

- 65C38484-10 (a) (b) (d) 65C38484-16 (c) J-Box Assembly

- 65C38484-11 (a)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 116 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNotes New Part Number Name QTY Existing Part Number (a) Operators that have airplanes with Airstairs that ordered and received the Top Kits given in the original release 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. (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. 4. Parts Removed and Not Replaced: None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 117 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTBOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 118 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT

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 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 are in 737 SRM, Chapter 51 — Torque limits to tighten nuts and bolts are in 737 SRM, Chapter 51. 5. Use the approved fastener and process material substitutions in accordance with 737 SRM, Chapter 51. 6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures. 7. If the length of any fastener specified in this service bulletin does not meet the installation standards in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards in SRM Chapter 51 may be used. 8. These work instructions refer to procedures included on 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. 9. The work instructions are divided into 31 airplane groups, 6 "PARTS", (PART 1, PART 2, PART 3, PART 4, PART 5, PART 6), and 3 work packages in each "PART" because of the 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 119 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTDo 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
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 a new wire. 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. 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 as given in 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 120 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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 equipment compartment, attach the box assembly on the E2 and E3 support posts In accordance with FIGURE 12. (b) Drill holes through the box assembly and the E3 support post in accordance with FIGURE 14. (c) Prepare the open holes in the support and box assembly in accordance with FIGURE 15. (d) Install the box assembly on the support posts: 1)Group 1-13, 15-16: 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 to a serviceable condition.

c. WORK PACKAGE 3: INSTALLATION OF WIRES AND TEST OF THE CHANGED FUEL SYSTEM

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 121 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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. (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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 122 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT6)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. 3)Group 2, Configuration 2: In accordance with FIGURE 44 and FIGURE 47. 4)Group 3, 16: In accordance with FIGURE 44 and FIGURE 48. 5)Group 4, Configuration 1: In accordance with FIGURE 44 and FIGURE 49. 6)Group 4, Configuration 2: In accordance with FIGURE 44 and FIGURE 50. 7)Group 5, 8: In accordance with FIGURE 44 and FIGURE 51. 8)Group 6, Configuration 1: In accordance with FIGURE 44 and FIGURE 52. 9)Group 6, Configuration 2: In accordance with FIGURE 44 and FIGURE 53. 10)Group 7: In accordance with FIGURE 44 and FIGURE 59. 11)Group 9: In accordance with FIGURE 44 and FIGURE 54.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 123 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT12)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. (d) Between the flight and main equipment 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 equipment 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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 124 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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) 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. (b) 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. (c) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM 25-10-00 as an accepted procedure. (d) 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. (e) 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. (f) 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. FAA may release an AD to require that all airplanes that have AUX tanks with Fuel Boost Pumps should 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. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 125 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFor 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 as given in 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 release of this service bulletin can use the J2802 Box assembly received in the kit but they need to change the J2802 Box 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 in accordance with PART 6. (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 Tank 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 Tank 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 if necessary. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 126 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(d) In the main equipment compartment, remove and keep the drain pan if/as necessary. 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 equipment compartment, attach the box assembly on the E2 and E3 support posts in accordance with FIGURE 99 . (b) Drill holes on the box assembly and the E3 support post in accordance with FIGURE 99 . (c) Prepare the open holes and box assembly in accordance with FIGURE 101 . (d) Install the box assembly on the support posts in accordance with FIGURE 103 . (e) Install the clamps and a bonding jumper wire in accordance with FIGURE 104 . (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 equipment compartment, install the kept drain pan 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 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 equipment compartment, remove and keep the airstairs drain pan if/as necessary. Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 127 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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. (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. NOTE:Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary Tank installation. It is necessary to do the change given in Figure 39 and Figure 40 only if Auxiliary Tank 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 Tank 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 128 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 Tank 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 Tank 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 Tank 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 Tank 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. NOTE:It is necessary to install wires W1764-004-20, W1764-005-20, and W1764-006-20 shown in Figure 84 only if an 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:It is necessary to install wires W1774-004-20, W1774-005-20, and W1774-006-20 shown in Figure 87 only if an AUX tanks with Fuel Boost Pumps are installed on these airplanes. (f) In the main equipment 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 129 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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. 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) 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. (b) 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. (c) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM 25-10-00 as an accepted procedure. (d) 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. (e) 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. (f) Install the kept drain pan if removed. 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. 3.Group 19-20: PART 3 - AIRPLANES WITH CENTER AND AUXILIARY (AUX) FUEL TANKS

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 130 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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. 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. 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 as given in 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 (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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 131 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(a) In the main equipment compartment, attach the box assembly on the E2 and E3 support posts in accordance with FIGURE 13. (b) Drill holes on the box assembly and the E3 support post in accordance with FIGURE 14. (c) Prepare the open holes and box assembly in accordance with FIGURE 15. (d) Install the box assembly on the 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 equipment compartment, 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 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) 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 132 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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. (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. (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 equipment 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 equipment 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 133 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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) 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. (b) 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. (c) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM 25-10-00 as an accepted procedure. (d) 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. (e) 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. (f) Install the kept drain pan if removed. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 134 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTAirplane 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. 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. 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 as given in 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 NOTE:Operators that have airplanes with Airstairs that ordered and received the Top Kits given in the original release of this service bulletin can use the J2802 Box assembly received in the kit but they need to change the J2802 Box 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 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 if necessary. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 135 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(d) In the main equipment compartment, remove and keep the drain pan if/as necessary. 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 equipment compartment, attach the box assembly on the E2 and E3 support posts In accordance with FIGURE 98. (b) Drill holes through the box assembly and the E3 support posts in accordance with FIGURE 98. (c) Prepare the open holes in the support and box assembly in accordance with FIGURE 100. (d) Install the box assembly on the support posts in accordance with FIGURE 102. (e) Install the clamps and a bonding jumper in accordance with FIGURE 104. (f) 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. 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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 136 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT3) 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. (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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 137 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT8)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. 9)Group 25, Configuration 2: In accordance with FIGURE 44 and FIGURE 53. 10)Group 31: In accordance with FIGURE 44 and FIGURE 54. 11)Group 27: In accordance with FIGURE 44 and FIGURE 55. 12)Group 28, Configuration 1: In accordance with FIGURE 44 and FIGURE 62. 13)Group 28, Configuration 2: In accordance with FIGURE 44 and FIGURE 63. 14)Group 29, Configuration 1: In accordance with FIGURE 44 and FIGURE 56. 15)Group 29, Configuration 2: In accordance with FIGURE 44 and FIGURE 57.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 138 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(d) Between the flight and main equipment 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 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) 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) 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. (b) 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. (c) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM 25-10-00 as an accepted procedure. (d) 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. (e) 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. (f) Install the kept drain pan if removed. Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 139 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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.
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 a new wire. 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. 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 as given in 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 release of this service bulletin can use the J2802 Box assembly received in the kit but they need to change the J2802 Box 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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 140 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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 if necessary. 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 equipment compartment, remove and keep the drain pan as necessary. 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 equipment compartment, attach the box assembly on the E2 and E3 support posts in accordance with FIGURE 99. (b) Drill holes on the box assembly and the E3 support post in accordance with FIGURE 99. (c) Prepare the open holes and box assembly in accordance with FIGURE 101. (d) Install the box assembly on the support posts in accordance with FIGURE 103. (e) Install the clamps and a bonding jumper wire in accordance with FIGURE 104. (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 airstairs drain pan. 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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 141 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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. 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. (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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 142 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT2)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 equipment 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 equipment 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) 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. (b) 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. (c) Move the first officer's seat to the initial position. Refer to 737-300/400/500 AMM 25-10-00 as an accepted procedure. (d) 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. (e) 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. (f) Install the kept drain pan if removed. Refer to 737-300/400/500 AMM 25-51-01 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 143 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT(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. 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 release of this service bulletin can use the J2802 Box assembly received in the kit but they need to change the J2802 Box. a. Change the J2802 box: (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: PART 7- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE ORIGINAL RELEASE OF THE SERVICE BULLETIN NOTE:Only airplanes that were in Group 1 through 16 of the Original Release of this service bulletin and incorporated the changes provided in the Original Release of the service bulletin have to do the work provided in PART 7. a. Install the Labels in accordance with FIGURE 3. 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 in accordance with FIGURE 82 and FIGURE 83. e. 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 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE ORIGINAL RELEASE OF THE SERVICE BULLETIN NOTE:Only airplanes that were in Group 17 and 18 of the Original Release of this service bulletin and incorporated the changes provided in the Original Release of the service bulletin have to do the work provided in PART 8. a. Install the Labels in accordance with FIGURE 6. b. Change wire W1760 termination at switch S3318 in accordance with FIGURE 7 and FIGURE 8.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 144 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 Release 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 Release 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. d. Inspect the imprinted text on the ID tape of wire W368-031-20 installed in accordance with FIGURE 82 and FIGURE 84. e. 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. 9.Group 19-20: PART 9- CHANGE OF THE J2802 RELAY BOX FOR AIRPLANES THAT INCORPORATED THE ORIGINAL RELEASE OF THE SERVICE BULLETIN NOTE:Only airplanes that were in Group 19 through 20 of the Original Release of this service bulletin and incorporated the changes provided in the Original Release of the service bulletin have to do the work provided in PART 9. a. Install the Labels in accordance with FIGURE 6. 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 in accordance with FIGURE 82 and FIGURE 84. e. 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. 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1: March 26, 2012 145 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 J-box assembly is available in the J-box installation kit 65C38484-8.
MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-10 J2802 Box As- sembly 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 146 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 J-box assembly is available in the J-box installation kit 65C38484-9.
MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-11 J2802 Box As- sembly 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 147 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 148 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 3: LABELS INSTALLATION, AND WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 149 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 65C38484-33 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 150 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 151 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 the connector 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 from the 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 and SWPM 20-30- 11 as accepted procedures. 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 4: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 152 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 61-74478-10503 ID Tape

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 153 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 154 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 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 61-74478-10701 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. 20 MS27488-16-1 or Seal Plug 20 MS27488-20-1 Refer to SWPM 20-30-00 and SWPM 20-30- 11 as accepted procedures. 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 5: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 155 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 156 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 19-20.

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 157 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 158 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 65C38484-33 Label-AUX-AFT Install (New) 3

- BAC5710, TYPE 41 Top Coat Apply (d) 1 65C38484-33 Label-AUX-FWD Install (New) 4

- BAC5710, TYPE 41 Top Coat Apply (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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 159 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 160 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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. 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 61-74478-106. The wire kits 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 toSWPM 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 and SWPM 20- 30-11 as accepted procedures. 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 and SWPM 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 Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Sock- et 8 Use one in each empty contact hole of the connector. Refer to SWPM 20-60-08and 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 61-74478-10601 ID Tape

FIGURE 7: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 161 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 162 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 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 61-74478-10602 ID Tape 3

Install at less than 6 inches from the 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 17 MS27488-20-1 Refer to SWPM 20-30-00 and SWPM 20- 30-11 as accepted procedures. 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 8: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 163 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 61-74478-10503 ID Tape

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 164 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 165 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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. It is necessary to do the 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 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 toSWPM 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 and SWPM 20- 30-11 as accepted procedures. 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 and SWPM 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 Refer to SWPM 20-81-19 as an accepted procedure. 4 BACC47ER1 Contact, Sock- et 8 Use one in each empty contact hole of the connector. Refer to SWPM 20-60-08and 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 61-74478-10801 ID Tape

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 166 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 167 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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. 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. 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 168 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 169 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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-( ) J-BOX ASSEMBLY Clean 1 On the 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 170 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-13, 15-16.

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 171 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 172 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Part is in the kit 65C38484-8.
MORE DATA QTY IDENTIFICATION NAME TASK STEP With clamps when the J-box is level on the E2 and E3 support posts. 1 65C38484-10 KIT ASSY - J2802 JBOX Attach 1

With 0.161-0.164 inch diameter. 3
- HOLE Drill 2 With 0.218-0.229 inch diameter. 2
- HOLE Drill 3

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 173 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 19-20.

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 174 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 175 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Part is in the kit 65C38484-9.
MORE DATA QTY IDENTIFICATION NAME TASK STEP With clamps when the J-box is level on the E2 and E3 support posts. 1 65C38484-11 KIT ASSY - J2802 JBOX Attach 1

With 0.161-0.164 inch diameter. 3
- HOLE Drill 2 With 0.218-0.229 inch diameter. 2
- HOLE Drill 3

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 176 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 177 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 178 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP On the E3 support post. 1 65C38484-( ) J-BOX ASSEMBLY Align 1 0.161-0.164 inch diameter. 3
- HOLE Drill 2 0.218-0.229 inch diameter. 4
- HOLE Drill 3

FIGURE 14: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 179 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 180 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 support posts. 1 65C38484-( ) J-BOX ASSEMBLY 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 181 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 182 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 shank and J-box faying surface. Refer to SOPM 20-50-19 and SWPM 20-20-00 as an acceptable procedures. - BMS5-95 SEALANT Apply 1

1 65C38484-10 KIT ASSY - J2802 JBOX Install (New)

6 BACB30NX5HK6 BOLT, PROTRUD- ING HD Install (New)

6 NAS42DD6-16FC SPACERS FOR RIVETS Install (New)

6 BACC30BH5 COLLAR, PRELOAD Install (New)

6 BACC30BH5 COLLAR, PRELOAD Tighten 2
On the bolt heads. Refer toSOPM 20-50-19 as an acceptable procedure. - BMS5-95 SEALANT Apply 3

FIGURE 16: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 183 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 184 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 shank and J-box faying surface. Refer to SOPM 20-50-19and SWPM 20-20-00 as an acceptable procedures. - BMS5-95 SEALANT Apply 1

1 65C38484-11 KIT ASSY - J2802 JBOX Install (New)

6 BACB30NX5HK6 BOLT, PROTRUD- ING HD Install (New)

6 NAS42DD6-16FC SPACERS FOR RIVETS Install (New)

6 BACC30BH5 COLLAR, PRELOAD Install (New)

6 BACC30BH5 COLLAR, PRELOAD Tighten 2
On the bolt heads. Refer to SOPM20-50-19 as an acceptable procedure. - BMS5-95 SEALANT Apply 3

FIGURE 17: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 185 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 186 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 187 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 resistance is 0.5 milliohms between J-box and support post faying surfaces. (a) (c) 1 65C38484-( ) J-BOX ASSEMBLY 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) between jumper faying surfaces. (a) (c) 1 BACJ40AB20-6 ELECTRICALBONDING RESISTANCE Measure 5

Maximum resistance is 3.5 milliohms between J2802 Box and Stanchion. (a) (c) 1
- ELECTRICALBONDING RESISTANCE Measure 6

On any bare metal surface at the J-box and support posts. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE, TYPE 2, CLASS A OR TYPE 5, CLASS F CONVERSION COATING Apply 7

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

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 188 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 189 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 If necessary to get access. 1 65-49815-( ) Channel Remove / Keep 6 If necessary to get access. 5 NAS1801-3-8 Screw Remove / Keep 7 If necessary to get access. 5 AN960PD10L Washer As necessary to get 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 190 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 (SHEET 1 OF 1)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 191 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 192 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE Refer to SWPM 20-10-11 and SWPM 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 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS13- 54, Class 1, Grade D, Type III, Finish C, White Lacing Tape

- 61-74478-2002, BMS13- 54, Class 1, Grade D, Type III, Finish C, Red Color

- 61-74478-2003, BMS13- 54, Class 1, Grade D, Type III, Finish C, Yellow Color Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 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 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS13- 54, Class 1, Grade D, Type III, Finish C, White Lacing Tape

- 61-74478-2002, BMS13- 54, Class 1, Grade D, Type III, Finish C, Red

- 61-74478-2003, BMS13- 54, Class 1, Grade D, Type III, Finish C, Yellow Refer to SWPM 20-61-11 as an accepted procedure. 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 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

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 193 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 194 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 195 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10- 11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS13- 54, Class 1, Grade D, Type III, Finish C, White Color Lacing Tape

- 61-74478-2002, BMS13- 54, Class 1, Grade D, Type III, Finish C, Red Color

- 61-74478-2003, BMS13- 54, Class 1, Grade D, Type III, Finish C, Yellow Color) Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10- 11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 196 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 197 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 198 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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 23: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 199 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 200 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 201 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 202 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 203 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 204 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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 25: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 205 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 206 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 9, 31.

FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 207 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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

FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 208 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 209 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 210 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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 27: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 211 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 212 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 213 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire Lacing Tape 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-61-11 as an accepted procedure. 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 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

FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 214 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 20-10-11 SWPM 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 215 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 216 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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 29: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 217 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 white or red or yellow color tie material same as the adjacent wires. Refer to SWPM 20-10-11 SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 218 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 219 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 220 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 221 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 222 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10- 11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10- 11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 223 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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, Sock- et 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 224 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 225 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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 32: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 226 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 227 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 228 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 As necessary to get access to the 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 229 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 34: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036 (SHEET 1 OF 1)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 230 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 19, 30.

FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 231 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 232 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 233 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 234 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 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

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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

FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 235 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 236 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 237 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 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

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 37: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 238 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 239 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17.

FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 240 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 38: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 241 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 242 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 243 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 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

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10- 11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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

FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 244 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 245 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 246 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 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

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 247 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 248 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 249 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 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 the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE Lacing Tape

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10- 12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 250 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 251 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 252 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 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

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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 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

FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 253 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 254 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 255 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE: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 and SWPM 20-10-12 as accepted procedures. 1 BMS13-58, Type 5, Class 1, AWG 24 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

- 61-74478-2002, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, RED

- 61-74478-2003, BMS 13- 54, CLASS 1, GRADE D,TYPE III, FINISH C, YELLOW Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures. 4 BMS13-58, Type 1, Class 1, AWG 20 Wire 2 Use the same color as the ties on the adjacent wires to the connector. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. - 61-74478-2001, BMS 13- 54, CLASS 1, GRADE D, TYPE III, FINISH C, WHITE 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 256 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 257 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 (SHEET 1 OF 1)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 258 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 45: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 259 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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. Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire. Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE7A

Use the same tie color as the existing ties onthe 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

FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 260 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 46: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 261 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. 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

FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 262 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 47: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 263 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 264 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 48: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 265 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 266 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 49: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 267 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 268 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 50: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 269 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 270 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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, WHITE

FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 271 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 272 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 52: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 273 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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, WHITEr 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 274 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 53: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 275 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 276 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 54: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 277 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 61-74478-10307 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 278 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 55: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 279 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 61-74478-10307 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 280 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 56: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 281 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 282 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 57: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 283 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 284 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 58: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 285 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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 61-74478-10307 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 286 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 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 59: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 287 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) 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 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 288 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 289 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 290 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 291 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 292 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 293 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 294 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 295 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 296 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 297 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 298 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 299 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 300 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 66: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044 (SHEET 1 OF 1)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 301 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17, Configuration 1.

FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 302 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 303 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 67: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 304 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17, Configuration 2.

FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 305 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 306 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 68: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 307 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17, Configuration 1.

FIGURE 69: CONNECTION OF WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 308 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 309 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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, WHITEr 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 69: CONNECTION OF WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 310 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17, Configuration 2.

FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 311 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 312 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 70: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 313 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 18, Configuration 1.

FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 314 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 315 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 71: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 316 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 18, Configuration 2.

FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 317 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 318 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 72: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 319 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 18, Configuration 1.

FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 320 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 321 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 73: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 322 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 18, Configuration 2.

FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 323 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 324 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 74: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 325 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 19, 30.

FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 326 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 327 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 75: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 328 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 19, 30, Configuration 1.

FIGURE 76: CONNECTION OF WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 329 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 330 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (b) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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, WHITEr 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 76: CONNECTION OF WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 331 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 19, 30, Configuration 2.

FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 332 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 333 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 77: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 334 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 20, Configuration 1.

FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 335 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 336 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 78: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 337 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 20, Configuration 2.

FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 338 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 339 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 79: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 340 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 20, Configuration 1.

FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 341 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 342 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 80: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 343 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 20, Configuration 2.

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 344 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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, WHITEr 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 345 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE To connect each existing wire if that deleted wire was connected with an existing AWG 22 wire.Refer to SWPM 20-20-11 as an accepted procedure. (a) 2 BACC47DE4A or Contact, Pin 6

To connect each existing wire if that deleted wire was connected with an existing AWG 20 wire.Refer to SWPM 20-20-11 as an accepted procedure. (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) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 346 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16, 19-20.

FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 (SHEET 1 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 347 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 (SHEET 2 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 348 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 (SHEET 3 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 349 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 (SHEET 4 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 350 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 and SWPM 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 351 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 tothe 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 theconnector. 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

(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 shown in Figure 82 at STA 259.5. The expando sleeve should extend 2 to 3 inches beyond the both ends of the conduit.

FIGURE 83: CONNECTION OF WIRE BUNDLE W368 AND W1764 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 352 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE (b) Some wires W368-031-20 have been identified incorrectly as "W036-031-20". Before installation inspect 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 353 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 354 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 and SWPM 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 355 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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. 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 shown in Figure 82 at STA 259.5. The expando sleeve should extend 2 to 3 inches beyond the both ends of the conduit. (b) Some wires W368-031-20 have been identified incorrectly as "W036-031-20". Before installation inspect 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 84: CONNECTION OF WIRE BUNDLE W368 AND W1764 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 356 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 and SWPM 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 357 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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, WHITEr 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 tothe 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 shown in Figure 82 at STA 259.5. The expando sleeve should extend 2 to 3 inches beyond the both ends of the conduit.

FIGURE 85: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 358 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 and SWPM 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 359 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 tothe 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 shown in Figure 82 at STA 259.5. The expando sleeve should extend 2 to 3 inches beyond the both ends of the conduit.

FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 360 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 361 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTREFERENCE: 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 and SWPM 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

Install at the wire bundle breakout adjacent to thesplice. Refer to SWPM 20-10-11 as an accepted procedure. 1 61-74478-11202 ID Tape 5

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 362 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME FLAG NOTE 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. 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 shown in Figure 82 at STA 259.5. The expando sleeve should extend 2 to 3 inches beyond the both ends of the conduit.

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774 (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 363 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16.

FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 364 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 365 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Parts are in the kit 65C38484-8.
MORE DATA QTY IDENTIFICATION NAME TASK STEP To make a drip loop below the J2802 box assembly. 1 W1764 WIRE BUNDLE Adjust 1 1 W1774 WIRE BUNDLE Adjust To close the clamps on the wire bundles. 4 BACS38W2I (BACS38W2 orBACS38W2 optional) STRAP Install (New) 2

Around the adjacent wire bundle if installed. Refer to SWPM 20- 10-11, "Split Sleeve Installation", as an accepted procedure. 1 65C38484-14 (M23053/12-514-C) INSULATION SLEEVING, HEAT SHRINKABLE PTFE. Install (New) 3

Use quantity as necessary on the sleeve and wire bundles. 6 BACS38W2I (BACS38W2 orBACS38W2 optional) STRAP Install (New)

Refer to SWPM 20-81-22 as an accepted procedure. 2 TDH-1852-1502 or TDH1852-1502 Relay Install 4

FIGURE 88: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 366 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 19-20.

FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 367 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 368 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Parts are in the kit 65C38484-9.
MORE DATA QTY IDENTIFICATION NAME TASK STEP To make a drip loop below the J2802 box assembly. 1 W1764 WIRE BUNDLE Adjust 1 1 W1774 WIRE BUNDLE Adjust To close the clamps on the wire bundles. 4 BACS38W2I (BACS38W2 orBACS38W2 optional) STRAP Install (New) 2

Around the adjacent wire bundle if installed. Refer to SWPM 20- 10-11, "Split Sleeve Installation", as an accepted procedure. 1 65C38484-14 (M23053/12-514-C) INSULATION SLEEVING, HEAT SHRINKABLE PTFE. Install (New) 3

Use quantity as necessary on the sleeve and wire bundles. 6 BACS38W2I (BACS38W2 orBACS38W2 optional) STRAP Install (New)

Refer to SWPM 20-81-22 as an accepted procedure. 4 TDH-1852-1502 or TDH1852-1502 Relay Install 4

FIGURE 89: INSTALLATION OF THE RELAYS AND STRAPS ON THE J2802 BOX ASSEMBLY (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 369 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 370 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 371 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-20, 30.

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 372 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 R146 and 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 373 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 14, 21-29, 31.

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 374 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 J-Box assembly is available in the J-Box Installation Kit 65C38484-8. Parts to rework the J-Box 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 J-BOX ASSEMBLY Disassemble 1 6 BACS12HN3-8 Bolt Remove/ Keep 6 NAS1149F0363P Washer 1 65C38484-6 Cover Remove 2 (a) 4 BACR15BB( )D( )C Rivets Remove 3 2 287U0016-185 Disconnect Angle Remove/Keep 4 Trim the left and right flange ofthe J2802 box assembly to accomodate the installation of the repair bracket. 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 FChemical Conversion Coating Apply 7

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 375 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 Primer Apply 8 (b) 1 65C38484-10 J-BOX ASSEMBLY 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 (e) 1 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 SWITCHES 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
Refer to SOPM 20-50-10 as an accepted procedure. (h) 65C38484-16 J-BOX ASSEMBLY 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. (b) Remove the protective material applied in step 3 and clean any debris and/or metal shaving. (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. (h) On the Top flange.

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 3)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 376 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-18, 30.

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 377 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 J-Box assembly is available in the J-Box Installation Kit 65C38484-9. Parts to rework the J-Box 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 J-BOX ASSEMBLY Disassemble 1 6 BACS12HN3-8 Bolt Remove/ Keep 6 NAS1149F0363P Washer 1 65C38484-6 Cover Remove 2 (a) 4 BACR15BB( )D( )C Rivets Remove 3 2 287U0016-185 Disconnect Angle Remove/Keep 4 Trim the left and right flange ofthe J2802 box assembly to accomodate the installation of the repair bracket. 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 FChemical Conversion Coating Apply 7

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

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 378 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP (b) 1 65C38484-10 J-BOX ASSEMBLY 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 (e) 1 65C38484-33 Label-AUX-AFT Install (New) 12 Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply (f) 1 65C38484-33 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 SWITCHES 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
Refer to SOPM 20-50-10 as an accepted procedure. (i) 65C38484-16 J-BOX ASSEMBLY 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. (b) Remove the protective material applied in step 3 and clean any debris and/or metal shaving. (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.

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 379 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP (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. (i) On the Top flange.

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 4 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 380 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 14, 21-29, 31.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 381 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 382 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 383 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 384 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Parts to rework the J-Box are available in the supplemental kit 65C37854-15. The kit possibly has more parts than necessary.
MORE DATA QTY IDENTIFICATION NAME TASK STEP Make sure and maintain the edge margin for the holes 1 65C38484-19 Bracket Locate 1

1 65C38484-16 J2802 Panel Assy 2 287U0016-185 Disconnect Bracket Put/Hold 2 Close Ream Holes in accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable 4 0.1905-0.1895 Inch DIA Holes Drill 3

1 287U0016-185 Disconnect Bracket Remove 4 1 65C38484-19 Bracket 1 65C38484-18 Bracket Locate 5 1 65C38484-16 J2802 Panel Assy 2 287U0016-185 Disconnect Bracket Put/Hold 6 Close Ream Holes in accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable 4 0.1905-0.1895 Inch DIA Holes Drill 7

In accordance with 737-300 SRM 51-40-05, 737-400 SRM 51-40-05, or 737-500 SRM 51- 40-05 as applicable 1 0.229-0.218 Inch DIA Hole Drill 8

1 287U0016-185 Disconnect Bracket Remove 9 1 65C38484-19 Bracket 1 65C38484-19 Bracket Deburr 10 1 65C38484-18 Bracket 2 287U0016-185 Disconnect Angle 1 65C38484-16 J2802 Panel 0.010 - 0.015 Inch deep on the inner side. 4 65C38484-10 J2802 Panel Countersink 11
Shave the rivet flush on the inner side of the panel BACR15BB6AD Rivet Install 12

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 385 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 as applicable 16 BACS12HN3-8 Screw Install 13 16 NAS1149D0316H Washer 16 BACN10YR3CD Nut Trim Grommet on assembly as necessary 4 BACG20Z- B000400 Grommet Install 14 Trim Grommet on assembly as necessary BAC 5010 Type 82 Adhesive Locate approximately as shown. (a) 1 65C38484-30 J2802 Relay Box Label Install (New) 15
Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
65C38484-20 Cover Install 16 Refer to SOPM 20-50-10 as an accepted procedure. 65C38484-21 J-BOX ASSEMBLY Identify 17 (a) 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.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 6 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 386 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-18, 30.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 387 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 388 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 389 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 390 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Parts to rework the J-Box are available in the supplemental kit 65C37854-15. The kit possibly has more parts than necessary.
MORE DATA QTY IDENTIFICATION NAME TASK STEP Make sure and maintain the edge margin for the holes 1 65C38484-19 Bracket Locate 1

1 65C38484-16 J2802 Panel Assy 2 287U0016-185 Disconnect Bracket Put/Hold 2 Close Ream Holes in accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable 4 0.1905-0.1895 Inch DIA Holes Drill 3

1 287U0016-185 Disconnect Bracket Remove 4 1 65C38484-19 Bracket 1 65C38484-18 Bracket Locate 5 1 65C38484-16 J2802 Panel Assy 2 287U0016-185 Disconnect Bracket Put/Hold 6 Close Ream Holes in accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable 4 0.1905-0.1895 Inch DIA Holes Drill 7

In accordance with 737-300 SRM 51-40-05, 737-400 SRM 51-40-05, or 737-500 SRM 51- 40-05 as applicable 1 0.229-0.218 Inch DIA Hole Drill 8

1 287U0016-185 Disconnect Bracket Remove 9 1 65C38484-19 Bracket 1 65C38484-19 Bracket Deburr 10 1 65C38484-18 Bracket 2 287U0016-185 Disconnect Angle 1 65C38484-16 J2802 Panel 0.010 - 0.015 Inch deep on the inner side. 4 65C38484-16 J2802 Panel Countersink 11
Shave the rivet flush on the inner side of the panel BACR15BB6AD Rivet Install 12

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 391 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE 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 as applicable 16 BACS12HN3-8 Screw Install 13 16 NAS1149D0316H Washer 16 BACN10YR3CD Nut Trim Grommet on assembly as necessary 4 BACG20Z- B000400 Grommet Install 14 Trim Grommet on assembly as necessary BAC 5010 Type 82 Adhesive Locate approximately as shown. (a) 1 65C38484-30 J2802 Relay Box Label Install (New) 15
Refer to SOPM 20-44-01 as an accepted procedure. - BAC5710, TYPE 41 Top Coat Apply
65C38484-20 Cover Install 16 Refer to SOPM 20-50-10 as an accepted procedure. 65C38484-15 J-BOX ASSEMBLY Identify 17 (a) 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.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 6 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 392 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 393 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 96: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 394 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 395 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP 6 BACS12HN3-8 Bolt Remove / Keep 1 6 NAS1149F0363P Washer 1 65C38484-20 Cover Refer to SWPM 20-10-11 as an accepted procedure. - W1760, W1770 Wires Install 2

1 65C38484-20 Cover Install / Kept 3 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 396 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 397 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 97: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 4)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 398 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 399 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP 6 BACS12HN3-8 Bolt Remove / Keep 1 6 NAS1149F0363P Washer 1 65C38484-20 Cover Refer to SWPM 20-10-11 as an accepted procedure. - W1760, W1770 Wires Install 2

1 65C38484-20 Cover Install / Kept 3 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 400 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 14, 21-29, 31.

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 401 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 402 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 403 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 4 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 404 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Parts are available in the supplemental kit 65C37854-15 for J-Boxes that have been reworked, or in the new J-Box installation kit 65C38484-22. The kit possibly has more parts than necessary.
MORE DATA QTY IDENTIFICATION NAME TASK STEP from E2 and E3 Support Posts from area where the J2802 Box Assy will be in contact with the stanchions 4
- RIVET Remove 1

With clamps when the J-box is level on the E2 and E3 support posts. 1 65C38484-21 KIT ASSY - J2802 JBOX Locate 2

Interference fit holes In accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable 2 0.187 - 0.190 Inch Dia HOLE Drill 3

Interference fit holes In accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable. (a) 4 0.161 - 0.164 Inch Dia HOLE Drill 4

In accordance with 737-300 SRM 51-40-05, 737-400 SRM 51-40-05, or 737-500 SRM 51- 40-05 as applicable 3 0.218 - 0.229 Inch Dia HOLE Drill 5

In accordance with 737-300 SRM 51-40-05, 737-400 SRM 51-40-05, or 737-500 SRM 51- 40-05 as applicable 2 0.128 - 0.135 Inch Dia HOLE Drill 6

1 65C38484-21 KIT ASSY - J2802 JBOX Trim 7Deburr Refer to SOPM 20-43-03 as an accepted procedure. - Typ 2, Class A CHEMICAL CON-VERSION COATING Apply 8

Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 PRIMER Apply (b)

- BMS 5-95, CLASS B SEALANT Apply 9 (a) If it is necessary Operators can oversize the holes to 0.187-0.190 Inch DIA. (b) Inject Sealant between Moisture Shroud Angle and Web. Apply a Fillet Seal on top to prevent moisture to enter between the Moisture Shroud Angle and Web.

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 405 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-18, 30.

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 406 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 407 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 408 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 4 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 409 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Parts are available in the supplemental kit 65C37854-15 for J-Boxes that have been reworked, or in the new J-Box installation kit 65C38484-23. The kit possibly has more parts than necessary.
MORE DATA QTY IDENTIFICATION NAME TASK STEP from E2 and E3 Support Posts from area where the J2802 Box Assy will be in contact with the stanchions 4
- RIVET Remove 1

With clamps when the J-box is level on the E2 and E3 support posts. 1 65C38484-15 KIT ASSY - J2802 JBOX Locate 2

Interference fit holes In accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable 2 0.187 - 0.190 Inch Dia HOLE Drill 3

Interference fit holes In accordance with 737-300 SRM 51-40- 05, 737-400 SRM 51-40-05, or737-500 SRM 51-40-05 as applicable. (a) 4 0.161 - 0.164 Inch Dia HOLE Drill 4

In accordance with 737-300 SRM 51-40-05, 737-400 SRM 51-40-05, or 737-500 SRM 51- 40-05 as applicable 3 0.218 - 0.229 Inch Dia HOLE Drill 5

In accordance with 737-300 SRM 51-40-05, 737-400 SRM 51-40-05, or 737-500 SRM 51- 40-05 as applicable 2 0.128 - 0.135 Inch Dia HOLE Drill 6

1 65C38484-15 KIT ASSY - J2802 JBOX Trim 7Deburr Refer to SOPM 20-43-03 as an accepted procedure. - Type 2, Class A CHEMICAL CON-VERSION COATING Apply 8

Refer to SOPM 20-41-02 as an accepted procedure. - BMS 10-11, Type 1 PRIMER Apply (b)

- BMS 5-95, CLASS B SEALANT Apply 9 (a) If it is necessary Operators can oversize the holes to 0.187-0.190 Inch DIA. (b) Inject Sealant between Moisture Shroud Angle and Web. Form a Fillet Seal on top to prevent moisture to enter between the Moisture Shroud Angle and Web.

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 5)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 410 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 411 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 support posts. 1 65C38484-21 KIT ASSY - J2802 JBOX Remove 1
Refer to SOPM 20-30-03 as an accepted procedure. 18
- HOLE Clean 2 By abrasive cleaning for faying surface bonding. (a) 1
- HOLE Clean 3 (a) Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 100: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR AIRPLANE WITH AIRSTAIRS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 412 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 413 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 support posts. 1 65C38484-15 J-BOX ASSEMBLY Remove 1 Refer to SOPM 20-30-03 as an accepted procedure. 18
- HOLE Clean 2 By abrasive cleaning for faying surface bonding. (a) 1
- HOLE Clean 3 (a) Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 101: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 414 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 14, 21-29, 31.

FIGURE 102: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 415 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 J-Boxes that have been reworked, or in the new J-Box installation kit 65C38484-22. The kit possibly has more parts than necessary.
MORE DATA QTY IDENTIFICATION NAME TASK STEP On the bolt shank and J-box faying surface. Refer to SOPM 20-50-19 and SWPM 20-20-00 as an acceptable procedures. - BMS5-95 SEALANT Apply 1

- 65C38484-21 J2802 JBOX Put 2 In accordance with 737-300 SRM 51-40-02, 737-400 SRM 51-40-02, or 737-500 SRM 51- 40-02 as applicable.(a) 4 BACB30NX5HK3 BOLT, PROTRUD- ING 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 as applicable. 2 BACB30NX6K3 BOLT, PROTRUD- ING HD Install (New) 4

2 BACC30BH6 COLLAR, PRELOAD On the bolt heads and fillet seal the collars. Refer to SOPM 20-50-19 as an acceptable procedure. - BMS5-95 SEALANT Apply 5

(a) If holes were oversized It is acceptable to install a BACB30NX6K3 bolt with BACC30BH6 Collar.

FIGURE 102: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 416 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis Figure applies only to: Group 17-18, 30.

FIGURE 103: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS (SHEET 1 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 417 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 J-Boxes that have been reworked, or in the new J-Box installation kit 65C38484-23. The kit possibly has more parts than necessary.
MORE DATA QTY IDENTIFICATION NAME TASK STEP On the bolt shank and J-box faying surface. Refer to SOPM 20-50-19 and SWPM 20-20-00 as an acceptable procedures. - BMS5-95 SEALANT Apply 1

- 65C38484-15 J2802 JBOX Put 2 In accordance with 737-300 SRM 51-40-02, 737-400 SRM 51-40-02, or 737-500 SRM 51- 40-02 as applicable. 4 BACB30NX5HK3 BOLT, PROTRUD- ING 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 as applicable. 2 BACB30NX6K3 BOLT, PROTRUD- ING HD Install (New) 4

2 BACC30BH6 COLLAR, PRELOAD On the bolt heads and fillet seal the collars. Refer to SOPM 20-50-19 as an acceptable procedure. - BMS5-95 SEALANT Apply 5

(a) holes were oversized It is acceptable to install a BACB30NX6K3 bolt with BACC30BH6 Collar.

FIGURE 103: INSTALLATION THE J2802 BOX ASSEMBLY ON THE E2 AND E3 SUPPORT POSTS FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 418 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 419 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 420 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 421 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 422 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTNOTE:Parts are available in the supplemental kit 65C37854-15 for J-Boxes that have been reworked, or in the new J-Box installation kit 65C38484-23. 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 2 BACN10TL3A10 NUT, SPACER PLATE Locate 1

use a CLICO to locate the Spacer Nut Plate to the existing hole 2 BACN10TL3A12 NUT, SPACER PLATE Locate 2

In accordance with 737-300 SRM 51-40-05, 737-400 SRM 51-40-05, or 737-500 SRM 51- 40-05 as applicable 4 0.128-0.135 Inch DIA Hole Drill 3

BACR15BB4D( )C Rivet Install 4 4 287T0011-1 CLAMP Install (New) 5 4 BACS12HN3-8 BOLT 4 NAS1149D0316H WASHER 4 287T0011-1 CLAMP Install (New) 6 4 BACS12HN3-8 BOLT 4 NAS1149D0316H WASHER 4 BACN10YR3CD NUT (b) 1 BACJ40AB20-8 BONDING JUMPER Install (New) 7

2 BACS12HN3-7 BOLT 6 NAS1149D0316H WASHER 2 BACN10YR3CD NUT Maximum resistance is 0.001 Ohms (1.0 milliohms) between jumper faying surfaces. (a) (c) 1 BACJ40AB20-6 ELECTRICALBONDING RESISTANCE Measure 8

Maximum resistance is 3.5 milliohms between J2802 Box and Stanchion. (a) (c) 1
- ELECTRICALBONDING RESISTANCE Measure 9

On any bare metal surface at the J-box and support posts. Refer to SOPM 20-43-03 as an accepted procedure. - ALODINE, TYPE 2, CLASS A OR TYPE 5, CLASS F CONVERSION COATING Apply 10

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

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 423 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP On the support posts. Refer to SOPM 20-41-02 as an accepted procedure. - BMS10-11, TYPE 2, COLOR WHITE ENAMEL FINISH Apply 12

(a) Refer to SWPM 20-20-00 as an accepted procedure. (b) Refer to SWPM 20-20-10 as an accepted procedure. Torque bolt 35 to 45 inch pound. (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.

FIGURE 104: INSTALLATION THE BONDING JUMPER AND CLAMPS FOR AIRPLANES WITH AIRSTAIRS (SHEET 6 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 424 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 425 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 426 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 3 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 427 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTFIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 4 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 428 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 5 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 429 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTMORE DATA QTY IDENTIFICATION NAME TASK STEP 4 287T0011-1 CLAMPS Loosen 1 To make a drip loop below the J2802 box assembly. 1 W1764 WIRE BUNDLE Adjust 2 To make a drip loop below the J2802 box assembly. 1 W1764 WIRE BUNDLE Adjust 3

FIGURE 105: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774 FOR AIRPLANES WITH AIRSTAIRS (SHEET 6 OF 6)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 430 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 431 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 J-Box has been reworked, or in 65C38484-22 if a new kit is used.
MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-20 Cover Remove 1 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 3

FIGURE 106: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 432 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThis 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)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 433 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERTThe 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 J-Box has been reworked, or in 65C38484-23 if a new kit is used.
MORE DATA QTY IDENTIFICATION NAME TASK STEP 1 65C38484-20 Cover Remove 1 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 3

FIGURE 107: INSTALLATION OF THE RELAYS ON THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS (SHEET 2 OF 2)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 29, 2010 737-28A1216 Revision 1 March 26, 2012 434 of 434 BOEING SERVICE BULLETIN 737-28A1216 ALERT ALERT