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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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

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4.0
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ALERT ALERT

BLANK PAGE
Table 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

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Original Issue: July 29, 2010

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ALERT ALERT
FIGURE 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

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FIGURE 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

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FIGURE 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

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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.

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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.

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:

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
a. 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

Original Issue: July 29, 2010

Revision 1: March 26, 2012

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT

BLANK PAGE
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).

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11 of 434
ACTION (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:

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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:

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

the P5 overhead panel, make a change to the wire bundles W36, W368 and W386. Between the P6

disconnect panel and the fuel boost pump relays R54 and R55, make a change to the wire bundle W44.

Between the P6 disconnect panel and the fuel boost pump relays R146 and R147, make a change to the

wire bundle W44.

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

assembly, install the new wire bundles W1764 and W1774.

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

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

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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 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.

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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.

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.

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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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.

GROUP CONFIGURATION DESCRIPTION

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

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

SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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17 of 434
GROUP CONFIGURATION DESCRIPTION

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

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

SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
GROUP CONFIGURATION DESCRIPTION

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

wiring configurations at the P5 and P6 panels.

12 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

wiring configurations at the P5 and P6 panels.

15 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

Airplanes with Airstairs, delivered with wire provision for Auxiliary

Tank installation and have different wiring configurations at the P5

and P6 panels.

18 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
GROUP CONFIGURATION DESCRIPTION

Airplanes that have the auxiliary fuel tanks and have different wiring

configurations at the P5 and P6 panels.

19 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

Airplanes that have the auxiliary fuel tanks and have different wiring

configurations at the P5 and P6 panels.

20 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

with or without SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

with or without SB 737-28A1212 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 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

with or without SB 737-28A1212 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 -

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
GROUP CONFIGURATION DESCRIPTION

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

have different wiring configurations at the P5 and P6 panels.

28 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

have different wiring configurations at the P5 and P6 panels.

29 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

different wiring configurations at the P5 and P6 panels.

30 -

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

2 Airplanes with SB 737-28A1212 R0 or R1 incorporated.

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

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

with or without SB 737-28A1212 R0 or R1 incorporated.

31 -

Airplane Models:

737-300, 737-400, 737-500

Variable Number Group

PJ301 - PJ302 1

PJ551 - PJ561 1

PJ601 - PJ615 1

PJ811 19

PJ816 - PJ817 21

PM381 - PM399 22

PM401 - PM417 22

PM541 - PM550 22

PM551 - PM564 23

PP001 - PP054 6

PP101 29

PP102 - PP169 12

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Variable Number Group

PP181 - PP187 6

PP188 - PP199 7

PP201 - PP205 25

PP221 14

PP231 - PP243 6

PP281 - PP286 6

PP301 - PP305 6

PP351 - PP353 25

PP376 - PP384 25

PP391 - PP393 25

PP401 - PP440 6

PP471 - PP475 20

PP501 - PP520 18

PP521 - PP522 25

PP631 - PP634 6

PP651 - PP652 25

PP671 - PP689 6

PP690 - PP694 20

PP695 - PP699 6

PP701 - PP706 6

PP707 - PP716 20

PP717 - PP733 6

PP771 - PP779 6

PP801 - PP808 25

PP821 - PP827 25

PP831 - PP848 22

PP851 - PP852 28

PP861 - PP877 11

PP891 - PP899 28

PP901 - PP936 28

PP946 - PP948 28

PP951 - PP952 28

PP961 - PP965 11

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ALERT ALERT
Variable Number Group

PP966 - PP967 3

PP981 - PP982 11

PP983 - PP990 3

PP991 11

PP993 23

PQ001 - PQ016 11

PQ026 - PQ041 11

PQ051 - PQ092 11

PQ101 - PQ199 11

PQ201 - PQ202 11

PQ221 - PQ230 23

PQ231 - PQ232 11

PQ233 - PQ237 10

PQ241 - PQ242 28

PQ243 27

PQ251 - PQ267 27

PQ281 - PQ291 27

PQ292 - PQ297 10

PQ298 27

PQ299 10

PQ301 - PQ307 10

PQ331 - PQ332 10

PQ341 - PQ348 10

PQ361 - PQ373 27

PQ391 - PQ395 27

PQ401 - PQ418 27

PQ421 27

PQ431 - PQ438 10

PQ447 - PQ448 27

PQ451 10

PQ454 10

PQ471 10

PQ472 - PQ475 27

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ALERT ALERT
Variable Number Group

PQ479 - PQ481 10

PQ486 - PQ487 10

PQ491 - PQ493 10

PQ771 - PQ772 10

PQ791 - PQ793 10

PQ801 - PQ805 16

PQ931 - PQ935 16

PQ951 27

PQ971 - PQ997 27

PR001 - PR017 23

PR021 - PR030 23

PR031 - PR034 3

PR041 - PR045 3

PR061 - PR072 3

PR077 - PR080 3

PR081 - PR082 23

PR091 - PR092 23

PR096 23

PR101 23

PR121 - PR122 23

PR131 - PR132 23

PR141 - PR143 23

PR161 - PR172 23

PR181 16

PS601 - PS631 22

PS636 - PS638 22

PS641 - PS642 22

PS643 - PS644 2

PS651 - PS657 23

PS666 - PS669 10

PS691 - PS692 3

PS701 - PS706 11

PS751 - PS799 12

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ALERT ALERT
Variable Number Group

PS811 23

PS836 - PS837 23

PS841 - PS846 22

PS851 - PS852 22

PS856 22

PS861 - PS863 17

PS866 - PS868 17

PS871 - PS874 22

PS896 - PS897 22

PS901 - PS941 15

PS956 - PS957 17

PS961 - PS963 23

PS971 - PS978 23

PT001 - PT015 3

PT021 - PT031 3

PT041 - PT064 23

PT101 - PT105 3

PT121 - PT138 23

PT146 - PT148 23

PT161 - PT170 23

PT181 - PT185 31

PT186 - PT188 9

PT211 - PT220 23

PT295 23

PT301 - PT309 3

PT331 - PT360 10

PT381 - PT399 3

PT401 - PT438 3

PT501 - PT517 27

PT561 - PT565 3

PT581 - PT586 3

PT611 - PT621 10

PT641 - PT644 3

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ALERT ALERT
Variable Number Group

PT651 - PT656 3

PT671 - PT672 27

PT681 - PT685 3

PT701 - PT703 13

PT716 - PT717 3

PT721 - PT725 23

PT801 - PT834 10

PT851 - PT854 3

PT871 - PT886 23

PT901 - PT930 10

PT971 - PT973 10

PT981 - PT985 3

PT996 23

PU001 - PU025 10

PU301 23

PU311 - PU313 23

PV001 4

PV002 - PV055 5

PV201 - PV209 1

PV226 - PV229 1

PV231 - PV237 8

PV271 - PV272 1

PV281 - PV287 1

PV296 21

PV301 - PV302 21

PV351 1

PV356 - PV357 31

PW001 - PW054 21

PW061 21

PW062 - PW068 1

PW072 21

PW086 - PW088 21

PW091 - PW094 21

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ALERT ALERT
Variable Number Group

PW101 - PW102 21

PW106 21

PW111 - PW120 21

PW156 - PW157 21

PW161 - PW171 21

PW201 - PW252 1

PW261 - PW268 21

PW271 - PW276 21

PW278 21

PW281 - PW293 21

PW296 21

PW301 - PW327 26

PW401 - PW408 1

PW411 - PW418 1

PW421 - PW424 1

PW431 - PW435 1

PW441 - PW450 8

PW461 - PW467 1

PW501 - PW504 21

PW511 - PW522 19

PW524 19

PW525 - PW529 1

PW530 19

PW531 - PW550 5

PW556 - PW557 24

PW561 - PW564 1

PW571 - PW576 1

PW591 - PW596 21

PW611 - PW622 5

PW631 - PW637 5

PW661 - PW662 24

PW681 - PW683 5

PW701 - PW702 30

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ALERT ALERT
Variable Number Group

PW711 - PW717 1

PW741 - PW742 24

PW761 5

PW771 1

PW831 31

PW851 - PW856 31

2. Spares Affected

None.

B. Concurrent Requirements

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

Company Service Bulletin Description

Gives instruction to install a new printed

circuit assembly in the P5-2 fuel system

module assembly to supply Low fuel pressure master caution Annunciation.

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

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.

Boeing 737-28A1210, Revision 1

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.

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ALERT ALERT
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).

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.

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ALERT ALERT
The 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.

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ALERT ALERT
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:

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:

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BOEING SERVICE BULLETIN 737-28A1216

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

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

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

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

make a change to the wire bundle W44.

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

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

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

R3318 and R3321. At the J2802 box assembly, install the time delay relays R3327 and R3329.

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

correctly.

Group 14, 21-29, 31:

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

TANKS, AND AIRSTAIRS

1. Work Package 1:

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.

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
In the J2802 box assembly, install the wire bundles W1760 and W1770.

2. Work Package 2:

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

install the J2802 box assembly.

3. Work Package 3:

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

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

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

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

make a change to the wire bundle W44.

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

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

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

R3318 and R3321. At the J2802 box assembly, install the time delay relays R3327 and R3329.

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

correctly.```````

Group 14, 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 Zones

Model Zone

737-400 102, 205

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 2, 6-7, 11-12, 14-18, 20, 22, 25, 28-29:

Affected Maintenance Zones

Model Zone

737-300 102, 205

Group 3, 10:

Affected Maintenance Zones

Model Zone

737-300, 737-500 102, 205

Group 9, 13, 31:

Affected Maintenance Zones

Model Zone

737-500 102, 205

Group 23:

Affected Maintenance Zones

Model Zone

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

Group 27:

Affected Maintenance Zones

Model Zone

737-300 102, 105, 205

Group 27:

Affected Maintenance Zones

Model Zone

737-500 105, 205

Group 31:

Affected Maintenance Zones

Model Zone

737-400 105, 205

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
E. Compliance

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

related to this service bulletin.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this

service bulletin mandatory.

Boeing recommends that the change given in this service bulletin be done within 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:

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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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 21 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 45 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 2, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 46 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 2, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

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ALERT ALERT
Group 2, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 47 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 3:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 3:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 48 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 4, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 4, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 49 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 4, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 50 1 3.80 3.80

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 4, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 5:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 5:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 6, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 52 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 6, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

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

Group 6, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 53 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 7:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 59 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 8:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 8:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 25 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 85 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 9:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 9:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 26 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 54 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 10:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 10:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 55 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 11, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 62 1 3.80 3.80

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 11, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 11, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 63 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 11, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 12, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 56 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 12, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

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

Group 12, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 57 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 13:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 29 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 58 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 14, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 14, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 20 (a) 2 - -

FIGURE 30 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 60 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 96.75 54.00

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 14, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 30 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 61 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 96.75 54.00

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 15, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 31 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 64 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 15, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 15, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 31 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 65 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 16:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 1 1 0.15 0.15

FIGURE 3 (a) 2 - -

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 12 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 16 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 32 2 5.50 2.75

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 16:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 44 (a) 1 - -

FIGURE 48 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 83 2 16.40 8.20

FIGURE 85 2 15.20 7.60

FIGURE 88 1 1.50 1.50

FIGURE 90 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.60 48.85

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

Group 17, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 38 2 5.50 2.75

FIGURE 39 (b) 2 4.60 2.30

FIGURE 40 (b) 2 4.60 2.30

FIGURE 66 (a) 2 - -

FIGURE 67 1 3.80 3.80

FIGURE 69 (b) 2 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 17, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.75

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 154.90 84.75

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

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

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

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

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

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

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

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

Kits given in the original 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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 38 2 5.50 2.75

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 17, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 39 (b) 2 4.60 2.30

FIGURE 40 (b) 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 68 1 3.80 3.80

FIGURE 70 (b) 1 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.75

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 154.90 84.75

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

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

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

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

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

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

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

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

Kits given in the original 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.

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Revision 1: March 26, 2012 737-28A1216

58 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 18, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 (b) 2 4.60 2.30

FIGURE 43 (b) 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 71 1 3.80 3.80

FIGURE 73 (b) 1 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.75

Close Access 3 12.00 4.00

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 18, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 160.55 90.40

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

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

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

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

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

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

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

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

Kits given in the original 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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 (b) 2 4.60 2.30

FIGURE 43 (b) 2 4.60 2.30

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 18, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 66 (a) 1 - -

FIGURE 72 1 3.80 3.80

FIGURE 74 (b) 1 3.80 3.80

FIGURE 84 (c) 2 32.60 16.30

FIGURE 87 (d) 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

FIGURE 93 (e) 1 3.00 3.00

FIGURE 95 (e) 1 2.80 2.80

FIGURE 97 (f) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 105 (a) 1 - -

FIGURE 107 1 0.75 0.75

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 160.55 90.40

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

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

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

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

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

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

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

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

Kits given in the original 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.

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Copyright © Unpublished Work - See page 1 for details.

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Revision 1: March 26, 2012 737-28A1216

61 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 19, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 2 1 0.15 0.15

FIGURE 6 (a) 2 - -

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 76 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 19, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 2 1 0.15 0.15

FIGURE 6 (a) 2 - -

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 77 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 20, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 2 1 0.15 0.15

FIGURE 6 (a) 2 - -

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 2 4.60 2.30

FIGURE 43 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 78 1 3.80 3.80

FIGURE 80 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 20, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 2 1 0.15 0.15

FIGURE 6 (a) 2 - -

FIGURE 7 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 11 1 0.15 0.15

FIGURE 13 1 1.00 1.00

FIGURE 14 1 1.00 1.00

FIGURE 15 1 2.00 2.00

FIGURE 17 1 0.50 0.50

FIGURE 18 1 1.00 1.00

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 41 2 5.50 2.75

FIGURE 42 2 4.60 2.30

FIGURE 43 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 79 1 3.80 3.80

FIGURE 81 1 3.80 3.80

FIGURE 82 (a) 2 - -

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 89 1 3.00 3.00

FIGURE 91 1 1.50 1.50

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.70 81.55

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

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 21:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 21 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 45 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 22, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 46 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 22, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 47 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 92.30 49.55

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 22 2 5.50 2.75

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68 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 23:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 44 (a) 1 - -

FIGURE 48 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 23 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

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ALERT ALERT
Group 24:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) - - -

FIGURE 52 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

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ALERT ALERT
Group 25, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) - - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 24 2 5.50 2.75

FIGURE 44 (a) - - -

FIGURE 53 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

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ALERT ALERT
Group 25, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 25 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 51 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 85 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 26:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 (a) 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 55 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 27:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 27 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 62 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 28, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 21 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 63 1 3.80 3.80

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

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Revision 1: March 26, 2012 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 28, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 56 1 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.30 48.55

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Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 29, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

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

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 28 2 5.50 2.75

FIGURE 57 1 - -

FIGURE 83 2 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 91.30 48.55

(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.

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Revision 1: March 26, 2012 737-28A1216

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 29, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 76 1 3.80 3.80

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (b) 1 3.00 3.00

FIGURE 95 (b) 1 2.80 2.80

FIGURE 97 (c) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 105 1 - -

FIGURE 107 1 0.75 0.75

Close Access 3 12.00 4.00

Test 2 2.00 1.00

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 30, Configuration 1:

Number of Per- Task-Hours Elapsed Hours

sons

Task

TOTAL FOR EACH AIRPLANE 151.75 81.60

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 7 (b) 2 7.20 3.60

FIGURE 8 2 7.20 3.60

FIGURE 9 (b) 2 7.20 3.60

FIGURE 10 2 7.20 3.60

FIGURE 33 1 1.50 1.50

FIGURE 34 (a) 2 - -

FIGURE 35 2 5.50 2.75

FIGURE 36 2 4.60 2.30

FIGURE 37 2 4.60 2.30

FIGURE 66 (a) 1 - -

FIGURE 75 1 3.80 3.80

FIGURE 76 1 3.80 3.80

FIGURE 84 2 32.60 16.30

FIGURE 87 2 30.20 15.10

FIGURE 91 1 1.50 1.50

FIGURE 93 (b) 1 3.00 3.00

FIGURE 95 (b) 1 2.80 2.80

FIGURE 97 (c) 1 0.15 0.15

FIGURE 99 1 1.20 1.20

FIGURE 101 1 0.50 0.50

FIGURE 103 1 0.60 0.60

FIGURE 105 1 - -

FIGURE 107 1 0.75 0.75

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

79 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 30, Configuration 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Close Access 3 12.00 4.00

Test 2 2.00 1.00

TOTAL FOR EACH AIRPLANE 151.75 81.60

(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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 3 12.00 4.00

FIGURE 4 2 7.20 3.60

FIGURE 5 2 7.20 3.60

FIGURE 19 1 1.50 1.50

FIGURE 20 (a) 2 - -

FIGURE 26 2 5.50 2.75

FIGURE 44 (a) 1 - -

FIGURE 54 1 3.80 3.80

FIGURE 83 1 16.40 8.20

FIGURE 86 2 15.20 7.60

FIGURE 90 1 1.50 1.50

FIGURE 92 (b) 1 2.75 2.75

FIGURE 94 (b) 1 2.80 2.80

FIGURE 96 (c) 1 0.15 0.15

FIGURE 98 1 1.20 1.20

FIGURE 100 1 0.50 0.50

FIGURE 102 1 0.60 0.60

FIGURE 104 1 2.30 2.30

FIGURE 105 1 - -

FIGURE 106 1 0.65 0.65

Close Access 3 12.00 4.00

Test 2 2.00 1.00

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Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

80 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 31:

Number of Per- Task-Hours Elapsed Hours

sons

Task

TOTAL FOR EACH AIRPLANE 95.10 52.35

(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

Each 737-300 +6 +1,300

Each 737-400 +6 +900

Each 737-500 +6 +1,650

Group 14, 17-18, 21-31:

AIRPLANES WITHOUT AIRSTAIRS

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

Each 737-300 +6.4 +1,400

Each 737-400 +6.4 +950

Each 737-500 +6.4 +1,750

I. Electrical Load Data

1. Direct Current (DC) Loads

Group 1-16:

Circuit Breaker Amperes Bus

C3318 150 Milliampere 28V DC Bus 1

C3320 150 Milliampere 28V DC Bus 2

Group 17-20:

Circuit Breaker Amperes Bus

C3318 150 Milliampere 28V DC Bus 1

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 17-20:

Circuit Breaker Amperes Bus

C3320 150 Milliampere 28V DC Bus 2

C3327 150 Milliampere 28V DC Bus 1

C3329 150 Milliampere 28V DC Bus 2

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.

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Revision 1: March 26, 2012 737-28A1216

82 of 434

BOEING SERVICE BULLETIN 737-28A1216

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

Drawing Number Title

61-74478 Kit- Wire Installation, Auto Shut Off System

65-48315 Wire Bundle Installation- Flight Compartment

65-48322 Wire Bundle Installation- Flight Compartment

65-48325 Wire Bundle Installation- Flight Compartment

65-49731 Disconnect Panel Installation- Flight Compartment

65-63811 Support Post Installation- E2 and E3 Rack

65-78950 Moisture Shroud Instl - Elec/Elex Racks (E2 and E3)

65C38471 Top Kit- Fuel Boost Pump, Auto Shut Off System, Center Fuel Tank

65C38484 Kit- J2802 Box Installation, Auto Shut Off System,

These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications

Publication Chapter-Section

737 Airplane Flight Manual Section 1 and Section 3.1

737 Operations Manual 12, NP and NNC

737 Maintenance Manual 28-22

737 Wiring Diagram Manual 28-23, 28-43

737 System Schematic Manual 28-23

737 Illustrated Parts Catalog 28-22

737 Dispatch Deviation Guide 28

737 Minimum Equipment List 28

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.

L. Interchangeability and Intermixability of Parts

None.

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
BOEING PROPRIETARY -

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT

BLANK PAGE
2. 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)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost Available 200 - $9,869.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-7 (a)

08/16/2012 50 2

Supplemental Kit - New La- Available 105 - $227.00

bels For J2802 Relay Box

65C37854-16

03/30/2012 50 2

(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)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost Available 10 75 $9,758.00

Pump Auto Shut Off System, Center and Auxiliary

Fuel Tanks

65C38471-8 (a) (b)

Supplemental Kit - New Available 105 - $227.00

Labels For J2802 Relay

Box

65C37854-16

03/30/2012 50 2

(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

Revision 1: March 26, 2012 737-28A1216

85 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 14, 21-29, 31:

Unit Price thru

31-Dec-2012

ROLT

(Weeks)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost Available 250 - $10,358.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-11 (a)

08/16/2012 10 2

(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)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost Available 200 - $9,869.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-7 (a)

08/16/2012 50 2

Supplemental Kit - J2802 $2,106.00

Relay Box Modification For

Airplanes With Airstairs

65C37854-15 (a)

Supplemental Kit - New La- Available 105 - $227.00

bels For J2802 Relay Box

65C37854-16 (a)

03/30/2012 50 2

(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)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost Available 1 - $13,976.00

Pump 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

Revision 1: March 26, 2012 737-28A1216

86 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Group 30:

Unit Price thru

31-Dec-2012

ROLT

(Weeks)

Kit Number Name Date QTY

Top Kit- Fuel Tank Boost Available 10 75 $9,758.00

Pump Auto Shut Off System, Center Fuel Tank

65C38471-8 (a)

Supplemental Kit - J2802 $2,106.00

Relay Box Modification For

Airplanes With Airstairs

65C37854-15 (a)

Supplemental Kit - New La- Available 105 - $227.00

bels For J2802 Relay Box

65C37854-16 (a)

03/30/2012 50 2

(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

Revision 1: March 26, 2012 737-28A1216

87 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 65C38471

Existing Part Notes

Number

New Part Number QTY Name

-7 -8 -11 -12

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 OFF

SYSTEM, CENTER TANK 737-

300/-400/-500

65C38471-7 - . . .

TOP KIT-FUEL

BOOST PUMP,

AUTO SHUT OFF

SYSTEM, CTR &

AUX TANK 737-

300/-400/-500

65C38471-8 . - . .

61-74478-1 1 . 1 . WIRE KIT

61-74478-2 . 1 . 1 WIRE KIT

KIT - JBOX INSTALLATION FOR

AIRPLANES

WITHOUT Auxiliary

TANK

65C38484-22 . . 1 .

KIT - JBOX INSTALLATION FOR

AIRPLANES WITH

Auxiliary TANK

65C38484-23 . . . 1

KIT - JBOX INSTALLATION FOR

AIRPLANES

WITHOUT AUX

TANK

65C38484-8 1 . . .

KIT - JBOX INSTALLATION FOR

AIRPLANES WITH

AUX TANK

65C38484-9 . 1 . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

88 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 65C37854

Existing Part Notes

Number

New Part Number QTY Name

-15 -16

Supplemental Kit -

J2802 Relay Box

Modification For

Airplanes With

Airstairs

65C37854-15 - .

Supplemental Kit -

New Labels For

J2802 Relay Box

65C37854-16 . -

287T0011-1 2 . CLAMP OLYMPIC

65C38484-18 1 . BRACKET

65C38484-19 1 . BRACKET

J2802 PANEL

COVER

65C38484-20 1 .

J2802 Relay Box

Label - J2802

65C38484-30 . 1

J2802 Relay Box

Label - CTR-L

65C38484-31 . 1

J2802 Relay Box

Label - CTR-R

65C38484-32 . 1

J2802 Relay Box

Label - NOT-USED

65C38484-33 . 2

J2802 Relay Box

Label - AUX-FWD

65C38484-34 . 1

J2802 Relay Box

Label - AUX-AFT

65C38484-35 . 1

J2802 Relay Box

Label - TEST

SWITCHES

65C38484-36 . 1

J2802 Relay Box

Label - AUTO

SHUTOFF

65C38484-37 . 1

J2802 PANEL

COVER SEAL

65C38484-7 2 .

BACB30NX6K6 6 . BOLT

BACC30BH6 6 . COLLAR

BACF3F008E013NN 1 . FILLER

BACF3F013E043NN 1 . FILLER, FLAT

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

89 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 65C37854

Existing Part Notes

Number

New Part Number QTY Name

-15 -16

BACG20Z- 4 . GROMMET

B001275

BACJ40AB20-8 1 . JUMPER

NUT, SPACER

PLATE, LIGHT

DUTY

BACN10TL3A10 2 .

NUT SPACER

PLATE

BACN10TL3A14 2 .

BACN10YR3CD 12 . NUT

BACS12HN3-10 2 . BOLT

BACS12HN3-8 12 . BOLT

NAS1149D0316H 28 . WASHER

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-1 -2

61-74478-1 - . WIRE KIT

61-74478-2 . - WIRE KIT

61-74478-101 1 . ASSY - W036

61-74478-102 . 1 ASSY - W036

61-74478-103 1 . ASSY - W044

61-74478-104 . 1 ASSY - W044

61-74478-105 1 . ASSY - W1760

61-74478-106 . 1 ASSY - W1760

61-74478-107 1 . ASSY - W1770

61-74478-108 . 1 ASSY - W1770

ASSY - W368,

W1764

61-74478-109 1 .

ASSY - W368,

W1764

61-74478-110 . 1

ASSY - W386,

W1774

61-74478-111 1 .

ASSY - W386,

W1774

61-74478-112 . 1

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

90 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-1 -2

LACING TAPE -

WHITE

61-74478-2001 1 1

LACING TAPE -

RED

61-74478-2002 1 1

LACING TAPE -

YELLOW

61-74478-2003 1 1

THERMOFIT

SLEEVE - 0.125

I.D.

61-74478-2005 1 1

EXPANDABLE

SLEEVE, 0.5 IN.

I.D.

61-74478-2006 1 1

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

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

CONNECTOR I.D. (b)

TAPE - D04064P

61-74478-10101 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04076P

61-74478-10102 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04148P

61-74478-10103 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04180P

61-74478-10104 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04238P

61-74478-10105 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04240P

61-74478-10106 1 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM116

61-74478-10107 1 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM118

61-74478-10108 1 1 . . . .

61-74478-101W 1 . . . . . WIRE LIST

61-74478-102 . - . . . . ASSY - W036 (a)

CONNECTOR I.D. (b)

TAPE - D04026P

61-74478-10201 . 1 . . . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

91 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

CONNECTOR I.D. (b)

TAPE - D04132P

61-74478-10202 . 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04154P

61-74478-10203 . 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04156P

61-74478-10204 . 1 . . . .

CONNECTOR I.D. (b)

TAPE - D04212P

61-74478-10205 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM182

61-74478-10206 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM184

61-74478-10207 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM186

61-74478-10208 . 1 . . . .

SPLICE I.D. (c)

SLEEVE - SM188

61-74478-10209 . 1 . . . .

61-74478-10210 . 1 . . . . FILLER WIRE (a) (d)

61-74478-102W . 1 . . . . WIRE LIST

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

CONNECTOR I.D. (b)

TAPE - D01606

61-74478-10301 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D01608

61-74478-10302 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04076J

61-74478-10305 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04148J

61-74478-10306 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04238J

61-74478-10307 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04240J

61-74478-10308 . . 1 1 . .

61-74478-10309 . . 1 1 . . FILLER WIRE (d)

61-74478-103W . . 1 . . . WIRE LIST

61-74478-104 . . . - . . ASSY - W044 (a)

CONNECTOR I.D. (b)

TAPE - D01818

61-74478-10401 . . . 1 . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

92 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

CONNECTOR I.D. (b)

TAPE - D01820

61-74478-10402 . . . 1 . .

61-74478-104W . . . 1 . . WIRE LIST

61-74478-105 . . . . - . ASSY - W1760 (a)

WIRE BUNDLE (e)

I.D. TAPE - 61-

31760-001

61-74478-10501 . . . . 1 .

CONNECTOR I.D. (b)

TAPE - D05208J

61-74478-10502 . . . . 1 1

CONNECTOR I.D. (b)

TAPE - D10966

61-74478-10503 . . . . 1 1

61-74478-105W . . . . 1 . WIRE LIST

61-74478-106 . . . . . - ASSY - W1760 (a)

CONNECTOR I.D. (b)

TAPE - D10970

61-74478-10601 . . . . . 1

WIRE BUNDLE (e)

I.D. TAPE - 61-

31760-002

61-74478-10602 . . . . . 1

61-74478-106W . . . . . 1 WIRE LIST

316-1616-634 . . 3 3 . . CONTACT (a)

SPLICE, PARAL- (a)

LEL, SOLISTRAND

34137 3 7 . . . .

BACC47CN1S 7 18 . . 4 7 CONTACT, PIN (a)

BACC47CN2 . 5 . . . . CONTACT, PIN (a)

CONTACT, SOCK- (a)

ET

BACC47CP1S 3 3 3 5 . .

BACC47CP2T . . 3 5 . . CONTACT (a)

BACC47DE1A . . . . 5 9 CONTACT (a)

BACC47DE4A . . 3 5 . . CONTACT (a)

BACC47DE7A . . 3 5 . . CONTACT, PIN (a)

CONTACT, SOCK- (a)

ET

BACC47ER1 . . . . 5 9

BACT12AR202 . . . . 3 5 TERMINAL (a)

BACT12AR203 . . . . 3 5 TERMINAL (a)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

93 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101 -102 -103 -104 -105 -106

SLEEVE, SEALING, SPLICED-436-46 3 7 . . . .

CONTACT, PIN, (a)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 . . . . 4 7

MS27488-16-1 . . . . 22 22 PLUG (a)

MS27488-20-1 . . . . 27 28 PLUG (a)

(a) There are more parts in this kit than are necessary. Keep the part not used if there are other uses for it

or discard it.

(b) The identification (ID) tape is made from label BACT19( ). The ID tape is imprinted with the equipment

numbers.

(c) The identification (ID) sleeve is made from marker sleeve TMSSCE14-2-4. The ID sleeve is imprinted with

the equipment number.

(d) The filler wire is made from BMS13-48, Type 10, Class 1 and AWG 18. The total length is longer than

necessary. Cut to the final necessary length during the wiring installation.

(e) The identification (ID) tape is made from label BACT19E-T6 or BACT19ET6. The ID tape is imprinted with

the wire bundle number.

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107 -108 -109 -110 -111 -112

61-74478-107 - . . . . . ASSY - W1770

WIRE BUNDLE (a)

I.D. TAPE - 61-

31770-001

61-74478-10701 1 . . . . .

CONNECTOR I.D. (b)

TAPE - D05210J

61-74478-10702 1 1 . . . .

CONNECTOR I.D. (b)

TAPE - D10968

61-74478-10703 1 1 . . . .

61-74478-107W 1 . . . . . WIRE LIST

61-74478-108 . - . . . . ASSY - W1770

CONNECTOR I.D. (b)

TAPE - D10972

61-74478-10801 . 1 . . . .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31770-002

61-74478-10802 . 1 . . . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

94 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107 -108 -109 -110 -111 -112

61-74478-108W . 1 . . . . WIRE LIST

ASSY - W368,

W1764

61-74478-109 . . - . . .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31764-001

61-74478-10901 . . 2 . . .

CONNECTOR I.D. (b)

TAPE - D04180J

61-74478-10902 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D04202J

61-74478-10903 . . 1 1 . .

CONNECTOR I.D. (b)

TAPE - D05208P

61-74478-10904 . . 1 1 . .

SPLICE I.D. (c)

SLEEVE - SP4510

61-74478-10905 . . 1 1 . .

WIRE I.D. TAPE - (d)

W0368-031-20

61-74478-10906 . . 2 2 . .

61-74478-109W . . 1 . . . WIRE LIST

ASSY - W368,

W1764

61-74478-110 . . . - . .

CONNECTOR I.D. (b)

TAPE - D04026J

61-74478-11001 . . . 1 . .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31764-002

61-74478-11002 . . . 2 . .

61-74478-110W . . . 1 . . WIRE LIST

ASSY - W386,

W1774

61-74478-111 . . . . - .

WIRE BUNDLE (a)

I.D. TAPE - 61-

31774-001

61-74478-11101 . . . . 2 .

CONNECTOR I.D. (b)

TAPE - D04064J

61-74478-11102 . . . . 1 1

CONNECTOR I.D. (b)

TAPE - D04084J

61-74478-11103 . . . . 1 1

CONNECTOR I.D. (b)

TAPE - D05210P

61-74478-11104 . . . . 1 1

SPLICE I.D. (c)

SLEEVE - SP4512

61-74478-11105 . . . . 1 1

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

95 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107 -108 -109 -110 -111 -112

WIRE I.D. TAPE - (d)

W0386-032-20

61-74478-11106 . . . . 2 2

61-74478-111W . . . . 1 . WIRE LIST

ASSY - W386,

W1774

61-74478-112 . . . . . -

CONNECTOR I.D. (b)

TAPE - D04212J

61-74478-11201 . . . . . 1

WIRE BUNDLE (a)

I.D. TAPE - 61-

31774-002

61-74478-11202 . . . . . 2

61-74478-112W . . . . . 1 WIRE LIST

CONNECTOR,

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT24-43S . . 1 1 . .

CONNECTOR, (e)

ELECTRICAL,

PLUG, STRAIGHT,

BAYONET COUPLING

BACC45FT24- . . . . 1 1

43S6

BACC47CN1S 4 7 3 3 . . CONTACT, PIN (e)

CONTACT, SOCK- (e)

ET

BACC47CP1S . . 4 10 6 13

BACC47DE1A 5 9 . . . . CONTACT (e)

CONTACT, SOCK- (e)

ET

BACC47ER1 5 9 . . . .

BACT12AR202 3 5 . . . . TERMINAL (e)

BACT12AR203 3 5 . . . . TERMINAL (e)

D-436-37 . . 2 2 2 2 SPLICE (e)

CONTACT, PIN, (e)

CRIMP REMOVABLE, PER MIL-C39029/11

M39029/11-145 4 7 . . . .

MS27488-16-1 22 22 22 22 22 22 PLUG (e)

MS27488-20-1 27 28 22 19 22 19 PLUG (e)

(a) The identification (ID) tape is made from label BACT19E-T6 or BACT19ET6. The ID tape is imprinted with

the wire bundle number.

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

96 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107 -108 -109 -110 -111 -112

(b) The identification (ID) tape is made from label BACT19( ). The ID tape is imprinted with the equipment

numbers.

(c) The identification (ID) sleeve is made from marker sleeve TMSSCE14-2-4. The ID sleeve is imprinted with

the equipment number.

(d) The identification (ID) tape is made from label BACT19C-T or BACT19CT. The ID tape is imprinted with

the wire number.

(e) There are more parts in this kit than are necessary. Keep the part not used if there are other uses for it

or discard it.

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-2001 -2002 -2003 -2005 -2006 -10101

CONNECTOR I.D.

TAPE - D04064P

61-74478-10101 . . . . . -

LACING TAPE - (a)

WHITE

61-74478-2001 - . . . . .

LACING TAPE - (b)

RED

61-74478-2002 . - . . . .

LACING TAPE - (c)

YELLOW

61-74478-2003 . . - . . .

THERMOFIT (d)

SLEEVE - 0.125

I.D.

61-74478-2005 . . . - . .

EXPANDABLE (e)

SLEEVE, 0.5 IN.

I.D.

61-74478-2006 . . . . - .

CONNECTOR I.D.

TAPE - D04064P

61-74478-10101 . . . . . -

BACT19C-T . . . . . 1 TAPE, ID

POLYOLEFIN, (f)

HEAT SHRINKABLE SLEEVE,

SEE RM PL FOR

COMPLETE DEFINITION

M23053/5-104-4 . . . 1 . .

NA374H2 1 . . . . . BMS 13-54 (g)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

97 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-2001 -2002 -2003 -2005 -2006 -10101

OBSOLETE, INAC- (f)

TIVE FOR NEW

DESIGN, MAY BE

USED FOR

SPARES/MODIFICATIONS

NA728R99 . . . . 1 .

OBSOLETE, INAC- (g)

TIVE FOR NEW

DESIGN, MAY BE

USED FOR

SPARES/MODIFICATIONS

NE597X7 . 1 . . . .

NN048A9 . . 1 . . . BMS 13-54 TAPE (g)

(a) The total length supplied is a minimum of 4,500 inches or one spool and is longer than it is necessary.

(b) The total length supplied is a minimum of 1,020 inches or one spool and is longer than it is necessary.

(c) The total length supplied is a minimum of 1,800 inches or one spool and is longer than it is necessary.

(d) The total length of the sleeve is 9 inches and is longer than is necessary.

(e) The supplied total length is a minimum of 276 inches or one spool and is longer than it is necessary.

(f) Cut each sleeve to the final necessary length during the wiring installation.

(g) Cut each tape to the final necessary length during the wiring installation.

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10102 -10103 -10104 -10105 -10106 -10107

CONNECTOR I.D.

TAPE - D04076P

61-74478-10102 - . . . . .

CONNECTOR I.D.

TAPE - D04148P

61-74478-10103 . - . . . .

CONNECTOR I.D.

TAPE - D04180P

61-74478-10104 . . - . . .

CONNECTOR I.D.

TAPE - D04238P

61-74478-10105 . . . - . .

CONNECTOR I.D.

TAPE - D04240P

61-74478-10106 . . . . - .

SPLICE I.D.

SLEEVE - SM116

61-74478-10107 . . . . . -

BACT19C-T 1 1 1 1 1 . TAPE, ID

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Original Issue: July 29, 2010

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98 of 434

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ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10102 -10103 -10104 -10105 -10106 -10107

TMSSCE14-2-4 . . . . . 1 MARKER SLEEVE

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10108 -10201 -10202 -10203 -10204 -10205

SPLICE I.D.

SLEEVE - SM118

61-74478-10108 - . . . . .

CONNECTOR I.D.

TAPE - D04026P

61-74478-10201 . - . . . .

CONNECTOR I.D.

TAPE - D04132P

61-74478-10202 . . - . . .

CONNECTOR I.D.

TAPE - D04154P

61-74478-10203 . . . - . .

CONNECTOR I.D.

TAPE - D04156P

61-74478-10204 . . . . - .

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 . . . . . -

BACT19C-T . 1 1 1 1 1 TAPE, ID

TMSSCE14-2-4 1 . . . . . MARKER SLEEVE

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Original Issue: July 29, 2010

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99 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10206 -10207 -10208 -10209 -10210 -10301

SPLICE I.D.

SLEEVE - SM182

61-74478-10206 - . . . . .

SPLICE I.D.

SLEEVE - SM184

61-74478-10207 . - . . . .

SPLICE I.D.

SLEEVE - SM186

61-74478-10208 . . - . . .

SPLICE I.D.

SLEEVE - SM188

61-74478-10209 . . . - . .

61-74478-10210 . . . . - . FILLER WIRE

CONNECTOR I.D.

TAPE - D01606

61-74478-10301 . . . . . -

SPLICE I.D.

SLEEVE - SM182

61-74478-10206 - . . . . .

SPLICE I.D.

SLEEVE - SM184

61-74478-10207 . - . . . .

SPLICE I.D.

SLEEVE - SM186

61-74478-10208 . . - . . .

SPLICE I.D.

SLEEVE - SM188

61-74478-10209 . . . - . .

61-74478-10210 . . . . - . FILLER WIRE

CONNECTOR I.D.

TAPE - D01606

61-74478-10301 . . . . . -

BACT19C-T . . . . . 1 TAPE, ID

BMS13- . . . . 1 . WIRE

48T10C01G018

TMSSCE14-2-4 1 1 1 1 . . MARKER SLEEVE

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10302 -10303 -10304 -10305 -10306 -10307

CONNECTOR I.D.

TAPE - D01608

61-74478-10302 - . . . . .

CONNECTOR I.D.

TAPE - D01606

61-74478-10303 . - . . . .

CONNECTOR I.D.

TAPE - D01608

61-74478-10304 . . - . . .

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

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100 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10302 -10303 -10304 -10305 -10306 -10307

CONNECTOR I.D.

TAPE - D04076J

61-74478-10305 . . . - . .

CONNECTOR I.D.

TAPE - D04148J

61-74478-10306 . . . . - .

CONNECTOR I.D.

TAPE - D04238J

61-74478-10307 . . . . . -

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 . . . . . -

BACT19C-T 1 1 1 1 1 1 TAPE, ID

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10308 -10309 -10401 -10402 -10403 -10404

CONNECTOR I.D.

TAPE - D04240J

61-74478-10308 - . . . . .

61-74478-10309 . - . . . . FILLER WIRE

CONNECTOR I.D.

TAPE - D01818

61-74478-10401 . . - . . .

CONNECTOR I.D.

TAPE - D01820

61-74478-10402 . . . - . .

CONNECTOR I.D.

TAPE - D01818

61-74478-10403 . . . . - .

CONNECTOR I.D.

TAPE - D01820

61-74478-10404 . . . . . -

CONNECTOR I.D.

TAPE - D04240J

61-74478-10308 - . . . . .

61-74478-10309 . - . . . . FILLER WIRE

CONNECTOR I.D.

TAPE - D01818

61-74478-10401 . . - . . .

CONNECTOR I.D.

TAPE - D01820

61-74478-10402 . . . - . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

101 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10308 -10309 -10401 -10402 -10403 -10404

BACT19C-T 1 . 1 1 1 1 TAPE, ID

BMS13- . 1 . . . . WIRE

48T10C01G018

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10501 -10502 -10503 -10601 -10602 -10701

WIRE BUNDLE

I.D. TAPE - 61-

31760-001

61-74478-10501 - . . . . .

CONNECTOR I.D.

TAPE - D05208J

61-74478-10502 . - . . . .

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 . . . . . -

BACT19C-T . 1 1 1 . . TAPE, ID

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

102 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10501 -10502 -10503 -10601 -10602 -10701

BACT19E-T6 1 . . . 1 1 TAPE, ID

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10702 -10703 -10801 -10802 -10901 -10902

CONNECTOR I.D.

TAPE - D05210J

61-74478-10702 - . . . . .

CONNECTOR I.D.

TAPE - D10968

61-74478-10703 . - . . . .

CONNECTOR I.D.

TAPE - D10972

61-74478-10801 . . - . . .

WIRE BUNDLE

I.D. TAPE - 61-

31770-002

61-74478-10802 . . . - . .

WIRE BUNDLE

I.D. TAPE - 61-

31764-001

61-74478-10901 . . . . - .

CONNECTOR I.D.

TAPE - D04180J

61-74478-10902 . . . . . -

CONNECTOR I.D.

TAPE - D05210J

61-74478-10702 - . . . . .

CONNECTOR I.D.

TAPE - D10968

61-74478-10703 . - . . . .

CONNECTOR I.D.

TAPE - D10972

61-74478-10801 . . - . . .

WIRE BUNDLE

I.D. TAPE - 61-

31770-002

61-74478-10802 . . . - . .

WIRE BUNDLE

I.D. TAPE - 61-

31764-001

61-74478-10901 . . . . - .

CONNECTOR I.D.

TAPE - D04180J

61-74478-10902 . . . . . -

BACT19C-T 1 1 1 . . 1 TAPE, ID

BACT19E-T6 . . . 1 1 . TAPE, ID

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

103 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-10903 -10904 -10905 -10906 -11001 -11002

CONNECTOR I.D.

TAPE - D04202J

61-74478-10903 - . . . . .

CONNECTOR I.D.

TAPE - D05208P

61-74478-10904 . - . . . .

SPLICE I.D.

SLEEVE - SP4510

61-74478-10905 . . - . . .

WIRE I.D. TAPE -

W0368-031-20

61-74478-10906 . . . - . .

CONNECTOR I.D.

TAPE - D04026J

61-74478-11001 . . . . - .

WIRE BUNDLE

I.D. TAPE - 61-

31764-002

61-74478-11002 . . . . . -

CONNECTOR I.D.

TAPE - D04202J

61-74478-10903 - . . . . .

CONNECTOR I.D.

TAPE - D05208P

61-74478-10904 . - . . . .

SPLICE I.D.

SLEEVE - SP4510

61-74478-10905 . . - . . .

WIRE I.D. TAPE -

W0368-031-20

61-74478-10906 . . . - . .

CONNECTOR I.D.

TAPE - D04026J

61-74478-11001 . . . . - .

WIRE BUNDLE

I.D. TAPE - 61-

31764-002

61-74478-11002 . . . . . -

BACT19C-T 1 1 . 1 1 . TAPE, ID

BACT19E-T6 . . . . . 1 TAPE, ID

TMSSCE14-2-4 . . 1 . . . MARKER SLEEVE

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-11101 -11102 -11103 -11104 -11105 -11106

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

Revision 1: March 26, 2012 737-28A1216

104 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-11101 -11102 -11103 -11104 -11105 -11106

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 . . . . . -

BACT19C-T . 1 1 1 . 1 TAPE, ID

BACT19E-T6 1 . . . . . TAPE, ID

TMSSCE14-2-4 . . . . 1 . MARKER SLEEVE

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-11201 -11202

CONNECTOR I.D.

TAPE - D04212J

61-74478-11201 - .

WIRE BUNDLE

I.D. TAPE - 61-

31774-002

61-74478-11202 . -

CONNECTOR I.D.

TAPE - D04212J

61-74478-11201 - .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

105 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-11201 -11202

WIRE BUNDLE

I.D. TAPE - 61-

31774-002

61-74478-11202 . -

BACT19C-T 1 . TAPE, ID

BACT19E-T6 . 1 TAPE, ID

Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-101W -102W -103W -104W -105W -106W

61-74478-101W - . . . . . WIRE LIST

61-74478-102W . - . . . . WIRE LIST

61-74478-103W . . - . . . WIRE LIST

61-74478-104W . . . - . . WIRE LIST

61-74478-105W . . . . - . WIRE LIST

61-74478-106W . . . . . - WIRE LIST

61-74478-101W - . . . . . WIRE LIST

61-74478-102W . - . . . . WIRE LIST

61-74478-103W . . - . . . WIRE LIST

61-74478-104W . . . - . . WIRE LIST

61-74478-105W . . . . - . WIRE LIST

61-74478-106W . . . . . - WIRE LIST

BMS13- . . 1 1 . . WIRE (a) (d)

58T01C01G022

WIRE RMS (b) (d)

5454011752

BMS13- 1 1 . 1 1 1

58T1C1G20

WIRE RMS (c) (d)

5454011755

BMS13- 1 1 . . . .

58T5C1G24

(a) Made from the BMS13-58, Type 1, Class 1, AWG 22 wires.

(b) Made from the BMS13-58, Type 1, Class 1, Gage (AWG) 20 wires.

(c) Made from the BMS13-58, Type 5, Class 1, AWG 24 wires.

(d) Each cut and coded wire is longer than necessary. Cut the wire to the final necessary length during the

wiring installation. Some wiring installations possibly do not use this wire.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

106 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 61-74478

Existing Part Notes

Number

New Part Number QTY Name

-107W -108W -109W -110W -111W -112W

61-74478-107W - . . . . . WIRE LIST

61-74478-108W . - . . . . WIRE LIST

61-74478-109W . . - . . . WIRE LIST

61-74478-110W . . . - . . WIRE LIST

61-74478-111W . . . . - . WIRE LIST

61-74478-112W . . . . . - WIRE LIST

61-74478-107W - . . . . . WIRE LIST

61-74478-108W . - . . . . WIRE LIST

61-74478-109W . . - . . . WIRE LIST

61-74478-110W . . . - . . WIRE LIST

61-74478-111W . . . . - . WIRE LIST

61-74478-112W . . . . . - WIRE LIST

WIRE RMS (a) (b)

5454011752

BMS13- 1 1 1 1 1 1

58T1C1G20

(a) Made from the BMS13-58, Type 1, Class 1, Gage (AWG) 20 wires.

(b) Each cut and coded wire is longer than necessary. Cut the wire to the final necessary length during the

wiring installation. Some wiring installations possibly do not use this wire.

Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

KIT ASSY - J2802

JBOX

65C38484-10 1 . - . . .

KIT ASSY - J2802

JBOX

65C38484-11 . 1 . - . .

J2802 PANEL ASSY65C38484-12 . . 1 1 - .

65C38484-13 . . . . 1 - J2802 PANEL

65C38484-14 1 1 . . . . KIT - SLEEVING

KIT - JBOX INSTALLATION FOR

AIRPLANES

WITHOUT AUX

TANK

65C38484-8 - . . . . .

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

107 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

KIT - JBOX INSTALLATION FOR

AIRPLANES WITH

AUX TANK

65C38484-9 . - . . . .

287T0011-1 4 4 . . . . CLAMP OLYMPIC

DISCONNECT ANGLE (1

BACD2010-640,

NO PILOT HOLES)

287U0016-185 . . 2 2 . .

KIT ASSY - J2802

JBOX

65C38484-10 1 . - . . .

KIT ASSY - J2802

JBOX

65C38484-11 . 1 . - . .

J2802 PANEL ASSY65C38484-12 . . 1 1 - .

65C38484-13 . . . . 1 - J2802 PANEL

65C38484-14 1 1 . . . . KIT - SLEEVING

J2802 PANEL

COVER

65C38484-6 . . 1 1 . .

J2802 PANEL

COVER SEAL

65C38484-7 . . 2 2 . .

BOLT, PROTRUDING HD

BACB30NX5HK6 6 6 . . . .

CIRCUIT BREAKERBACC18Z1R . . 2 4 . .

COLLAR,

PRELOAD

BACC30BH5 6 6 . . . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24-43P . . 1 1 . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24- . . 1 1 . .

43P6

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

108 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

CLAMP ASSEMBLYBACC49A2 . . 4 4 . .

BACG20Z- . . 4 4 . . GROMMET

B000400

BONDING

JUMPER

BACJ40AB20-6 1 1 . . . .

BACM15C3E . . 2 4 . . TERMINAL BLOCK

BACN10JC06CD . . 4 4 . . NUT

BACN10JN08 . . . . 16 . NUT PLATE

NUTPLATE, SELFLOCKBACN10JY3R . . 6 6 . .

BACN10NX32D4 . . 3 3 . . STANDOFF

BACN10YR3CD 6 6 . . . . NUT

BACR15BA3AD4C . . . . 32 . RIVET

BACR15BA3D4C . . 12 12 . . RIVET, 100 DEG

BACR15BA4D4C . . 8 8 . . RIVET

BACR15BA4D5C . . 14 14 . . RIVET, 100 DEG

BACR15BB5D5C . . 4 4 . . RIVET

BACS12HN06-7 . . 4 4 . . BOLT

BACS12HN3-7 2 2 . . . . BOLT

BACS12HN3-8 4 4 6 6 . . BOLT

BACS16AH1 . . 2 4 . . RELAY SOCKET

RINGPOST, WIRE

HARNESS

MOUNTING SUPPORT

BACS31H2B . . 3 3 . .

BACS38W2I 10 10 . . . . STRAP

(BACS38W2 optional)

BACT19J2 . . 20 26 . . TAPE, ID

BACT19J3 . . 38 38 . . TAPE, ID

BACT19J4 . . 2 2 . . TAPE, ID

BACT44B0700U . . 2 2 . . TRACK, TB MDL

MS24524-27 . . 2 2 . . SWITCH, TOGGLE

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

109 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-8 -9 -10 -11 -12 -13

ALUMINUM ALLOY, CLAD

SHEET; SEE RM

PL REPORT FOR

COMPLETE DEFINITION

MX211F . . . . . 1

NAS1149D0316H 10 10 . . . . WASHER

NAS1149F0363P . . 6 6 . . WASHER, PLAIN

SPACERS FOR

RIVETS

NAS42DD6-16FC 6 6 . . . .

TIME DELAY RELAYTDH1852-1502 2 4 . . . .

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-33 . . 2 4 . .

YHLZG16-1 . . 2 2 . . GROUND BLOCK

Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-14 -15 -16 -17 -18 -19

65C38484-14 - . . . . . KIT - SLEEVING

KIT ASSY - J2802

JBOX

65C38484-15 . - . . . .

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

J2802 PANEL ASSY65C38484-17 . 1 . - . .

65C38484-18 . . . 1 - . BRACKET

65C38484-19 . . . 1 . - BRACKET

J2802 PANEL

COVER

65C38484-20 . 1 . . . .

287T0011-1 . 4 . . . . CLAMP OLYMPIC

DISCONNECT ANGLE (1

BACD2010-640,

NO PILOT HOLES)

287U0016-185 . 2 . . . .

65C38484-14 - . . . . . KIT - SLEEVING

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

110 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-14 -15 -16 -17 -18 -19

KIT ASSY - J2802

JBOX

65C38484-15 . - . . . .

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

J2802 PANEL ASSY65C38484-17 . 1 . - . .

65C38484-18 . . . 1 - . BRACKET

65C38484-19 . . . 1 . - BRACKET

J2802 PANEL

COVER

65C38484-20 . 1 . . . .

J2802 PANEL

COVER SEAL

65C38484-7 . 2 . . . .

CIRCUIT BREAKERBACC18Z1R . 4 . . . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24-43P . 1 . . . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24- . 1 . . . .

43P6

CLAMP ASSEMBLYBACC49A2 . 4 . . . .

BACG20Z- . 4 . . . . GROMMET

B000400

BACM15C3E . 4 . . . . TERMINAL BLOCK

BACN10JC06CD . 4 . . . . NUT

BACN10JN08 . . . 16 . . NUT PLATE

NUTPLATE, SELFLOCKBACN10JY3R . 6 . . . .

BACN10NX32D4 . 3 . . . . STANDOFF

NUT, SPACER

PLATE, LIGHT

DUTY

BACN10TL3A10 . 2 . . . .

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ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-14 -15 -16 -17 -18 -19

NUT SPACER

PLATE

BACN10TL3A14 . 2 . . . .

BACN10YR3CD . 4 . 8 . . NUT

BACR15BA3AD4C . . . 32 . . RIVET

BACR15BA3D4C . 12 . . . . RIVET, 100 DEG

BACR15BA4D3C . 8 . . . . RIVET, 100 DEG

BACR15BA4D4C . 8 . . . . RIVET

BACR15BA4D5C . 14 . . . . RIVET, 100 DEG

BACS12HN06-7 . 4 . . . . BOLT

BACS12HN3-10 . 3 . . . . BOLT

BACS12HN3-8 . 12 . 8 . . BOLT

BACS16AH1 . 4 . . . . RELAY SOCKET

RINGPOST, WIRE

HARNESS

MOUNTING SUPPORT

BACS31H2B . 3 . . . .

BACT19J2 . 26 . . . . TAPE, ID

BACT19J3 . 38 . . . . TAPE, ID

BACT19J4 . 2 . . . . TAPE, ID

BACT44B0700U . 2 . . . . TRACK, TB MDL

INSULATION

SLEEVING, HEAT

SHRINKABLE

PTFE.

M23053/12-514-C 1 . . . . .

MS24524-27 . 2 . . . . SWITCH, TOGGLE

ALUMINUM ALLOY, CLAD

SHEET; SEE RM

PL REPORT FOR

COMPLETE DEFINITION

MX211F . . 1 . 1 1

NAS1149D0316H . 12 . 16 . . WASHER

NAS1149F0363P . 6 . . . . WASHER, PLAIN

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-33 . 4 . . . .

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ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-14 -15 -16 -17 -18 -19

YHLZG16-1 . 2 . . . . GROUND BLOCK

Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

65C38484-14 . . 1 1 KIT - SLEEVING

KIT ASSY - J2802

JBOX

65C38484-15 . . . 1

J2802 PANEL ASSY65C38484-17 . 1 . .

J2802 PANEL

COVER

65C38484-20 - 1 . .

KIT ASSY - J2802

JBOX

65C38484-21 . - 1 .

KIT - JBOX INSTALLATION FOR

AIRPLANES

WITHOUT Auxiliary

TANK

65C38484-22 . . - .

KIT - JBOX INSTALLATION FOR

AIRPLANES WITH

Auxiliary TANK

65C38484-23 . . . -

287T0011-1 . 4 4 4 CLAMP OLYMPIC

DISCONNECT ANGLE (1

BACD2010-640,

NO PILOT HOLES)

287U0016-185 . 2 . .

65C38484-14 . . 1 1 KIT - SLEEVING

KIT ASSY - J2802

JBOX

65C38484-15 . . . 1

J2802 PANEL ASSY65C38484-17 . 1 . .

J2802 PANEL

COVER

65C38484-20 - 1 . .

KIT ASSY - J2802

JBOX

65C38484-21 . - 1 .

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ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

J2802 PANEL

COVER SEAL

65C38484-7 . 2 . .

BOLT, PROTRUDING HDBACB30NX5HK6 . . 6 6

BACB30NX6K6 . . 6 6 BOLT

CIRCUIT BREAKERBACC18Z1R . 2 . .

COLLAR,

PRELOAD

BACC30BH5 . . 6 6

BACC30BH6 . . 6 6 COLLAR

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24-43P . 1 . .

CONNECTOR,

ELECTRICAL, RECEPTACLE,

FLANGE MOUNT,

BAYONET COUPLING

BACC45FN24- . 1 . .

43P6

CLAMP ASSEMBLYBACC49A2 . 4 . .

BACF3F008E013NN . . 1 1 FILLER

BACF3F013E043NN . . 1 1 FILLER, FLAT

BACG20Z- . 4 . . GROMMET

B000400

BACJ40AB20-8 . . 1 1 JUMPER

BACM15C3E . 2 . . TERMINAL BLOCK

BACN10JC06CD . 4 . . NUT

NUTPLATE, SELFLOCKBACN10JY3R . 6 . .

BACN10NX32D4 . 3 . . STANDOFF

NUT, SPACER

PLATE, LIGHT

DUTY

BACN10TL3A10 . 2 . .

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ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

NUT SPACER

PLATE

BACN10TL3A14 . 2 . .

BACN10YR3CD . 4 6 6 NUT

BACR15BA3D4C . 12 . . RIVET, 100 DEG

BACR15BA4D3C . 8 . . RIVET, 100 DEG

BACR15BA4D4C . 8 . . RIVET

BACR15BA4D5C . 14 . . RIVET, 100 DEG

BACS12HN06-7 . 4 . . BOLT

BACS12HN3-10 . 3 . . BOLT

BACS12HN3-7 . . 2 2 BOLT

BACS12HN3-8 . 12 4 4 BOLT

BACS16AH1 . 2 . . RELAY SOCKET

RINGPOST, WIRE

HARNESS

MOUNTING SUPPORT

BACS31H2B . 3 . .

BACS38W2 . . 10 10 STRAP

BACT19J2 . 20 . . TAPE, ID

BACT19J3 . 38 . . TAPE, ID

BACT19J4 . 2 . . TAPE, ID

BACT44B0700U . 2 . . TRACK, TB MDL

MS24524-27 . 2 . . SWITCH, TOGGLE

ALUMINUM ALLOY, CLAD

SHEET; SEE RM

PL REPORT FOR

COMPLETE DEFINITION

MX211F 1 . . .

NAS1149D0316H . 12 10 10 WASHER

NAS1149F0363P . 6 . . WASHER, PLAIN

SPACERS FOR

RIVETS

NAS42DD6-16FC . . 6 6

TIME DELAY RELAYTDH1852-1502 . . 2 4

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ALERT ALERT
Kit 65C38484

Existing Part Notes

Number

New Part Number QTY Name

-20 -21 -22 -23

TERMINAL BLOCK

DIODE ASSEMBLY MODULE

YHLZD-33 . 2 . .

YHLZG16-1 . 2 . . GROUND BLOCK

2. Parts and Materials Supplied by the Operator:

Part Number / Specifi- QTY Name Notes

cation

CHEMICAL CONVERSION (a) (b)

COATING

ALODINE TYPE 2, 2 Ounce

CLASS A OR TYPE 5,

CLASS F

BACS38W2I or 12 TIE STRAP (a)

BACS38W2

BMS10-11, Type I 1 Ounce PRIMER FINISH (a) (c)

BMS10-11, Type II, 1 Ounce ENAMEL FINISH (a) (c)

White Gloss

BMS5-95 2 Ounce SEALANT (a)

BAC 5010 TYPE 82 1 Ounce ADHESIVE (a)

CLEAR SKYDROL RESIS- (a)

TANT TOPCOATING

BAC5710 TYPE 41 1 Ounce

TAPE, ELECTRICAL PAN- (a)

EL LABELING

BACT19J2 2

TAPE, ELECTRICAL PAN- (a)

EL LABELING

BACT19J4 6

(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:

Existing Part QTY Name New Part Number Notes

Number

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

65C38484-11 (a) - J-Box Assembly 65C38484-16 (c) (b) (d)

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ALERT ALERT
Existing Part QTY Name New Part Number Notes

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.

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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently or at the same time, except Work Package 3 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.

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Airplane Groups Part Do Work Packages

1 Through 13, 15, 1 1, 2, 3

and 16

17 Through 18 2 1, 2, 3

19 Through 20 3 1, 2, 3

14, 21 Through 29, 4 1, 2, 3

and 31

30 5 1, 2, 3

14, 17, 18, 21 6 -

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.

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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

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(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.

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6) Group 9:

In accordance with FIGURE 20 and FIGURE 26.

7) Group 10-11:

In accordance with FIGURE 20 and FIGURE 27.

8) Group 12:

In accordance with FIGURE 20 and FIGURE 28.

9) Group 13:

In accordance with FIGURE 20 and FIGURE 29.

10) Group 15:

In accordance with FIGURE 20 and FIGURE 31.

11) Group 16:

In accordance with FIGURE 20 and FIGURE 32.

(c) Between the P6 top disconnect panel and the P6 relay panel, change the wire bundle

W0044.

1) Group 1:

In accordance with FIGURE 44 and FIGURE 45.

2) Group 2, Configuration 1:

In accordance with FIGURE 44 and FIGURE 46.

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.

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12) Group 10:

In accordance with FIGURE 44 and FIGURE 55.

13) Group 11, Configuration 1:

In accordance with FIGURE 44 and FIGURE 62.

14) Group 11, Configuration 2:

In accordance with FIGURE 44 and FIGURE 63.

15) Group 12, Configuration 1:

In accordance with FIGURE 44 and FIGURE 56.

16) Group 12, Configuration 2:

In accordance with FIGURE 44 and FIGURE 57.

17) Group 13:

In accordance with FIGURE 44 and FIGURE 58.

18) Group 15, Configuration 1:

In accordance with FIGURE 44 and FIGURE 64.

19) Group 15, Configuration 2:

In accordance with FIGURE 44 and FIGURE 65.

(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.

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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.

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125 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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 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.

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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.

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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.

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but

with wire provisions for Auxiliary Tank installation. It is necessary to do

the change given in Figure 69 only if Auxiliary 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 -

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Revision 1: March 26, 2012 737-28A1216

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 -

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Original Issue: July 29, 2010

Revision 1: March 26, 2012 737-28A1216

130 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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

(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.

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Revision 1: March 26, 2012 737-28A1216

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 -

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Revision 1: March 26, 2012 737-28A1216

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

Revision 1: March 26, 2012 737-28A1216

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

Revision 1: March 26, 2012 737-28A1216

134 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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

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

Revision 1: March 26, 2012 737-28A1216

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.

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3) In the main equipment compartment, remove and keep the airstairs drain pan

if it is not already removed. Refer to 737-300/400/500 AMM 25-51-01 as an

accepted procedure.

(d) Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00

as an accepted procedure.

(e) In the main electronics compartment, disconnect the battery power cables from the

battery. Refer to 737-300/400/500 AMM 24-31-11 as an accepted procedure.

(f) Remove and keep the moisture shroud from above the E3 rack if it is not already

removed. Refer to the 737-300/400/500 AMM 25-51-01 as an accepted procedure.

(g) In the nose wheel well, remove and keep the right access panels, 3103R and 3105R.

Refer to 737-300/400/500 AMM 12-31-11 as an accepted procedure.

(h) In the flight compartment, move the first officer's seat to the forward position. Refer

to 737-300/400/500 AMM 25-10-00 as an accepted procedure.

(i) Remove and keep the ceiling linings adjacent and forward of the P6 load control

panel. Refer to 737-300/400/500 AMM 25-11-21 as an accepted procedure.

(j) Remove and keep the aft and mid center ceiling panels. Refer to 737-300/400/500

AMM 25-11-21 as an accepted procedure.

(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.

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8) Group 27-28:

In accordance with FIGURE 20 and FIGURE 27.

9) Group 29:

In accordance with FIGURE 20 and FIGURE 28.

(c) Between the P6 top disconnect panel and the P6 relay panel, change the wire bundle

W0044.

1) Group 14, Configuration 1:

In accordance with FIGURE 44 and FIGURE 60.

2) Group 14, Configuration 2:

In accordance with FIGURE 44 and FIGURE 61.

3) Group 21:

In accordance with FIGURE 44 and FIGURE 45.

4) Group 22, Configuration 1:

In accordance with FIGURE 44 and FIGURE 46.

5) Group 22, Configuration 2:

In accordance with FIGURE 44 and FIGURE 47.

6) Group 23:

In accordance with FIGURE 44 and FIGURE 48.

7) Group 24, 26:

In accordance with FIGURE 44 and FIGURE 51.

8) Group 25, Configuration 1:

In accordance with FIGURE 44 and FIGURE 52.

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.

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(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.

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(g) Close the access door to the main electronics compartment. Refer to 737-300/400/500

AMM 52-48-41 as an accepted procedure.

(5) Put the airplane back to a serviceable condition.

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.

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(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.

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(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.

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2) Group 30, Configuration 2:

In accordance with FIGURE 66, FIGURE 75 and FIGURE 77.

(d) Between the P5 overhead disconnect panel in the flight compartment and the J2802

box assembly in the main 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.

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(g) Close the access door to the main electronics compartment. Refer to 737-300/400/500

AMM 52-48-41 as an accepted procedure.

(5) Put the airplane back to a serviceable condition.

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.

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

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

given in Figure 7 of the Original 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.

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ALERT ALERT
This Figure applies only to: Group 1-13, 15-16.

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: The J-box assembly is available in the J-box installation kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

J2802 Box As- 65C38484-10 1

sembly

1 Disassemble

Remove / Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

2 Remove / Keep Cover 65C38484-6 1

FIGURE 1: REMOVAL OF THE J2802 BOX ASSEMBLY COVER

(SHEET 1 OF 1)

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ALERT ALERT
This Figure applies only to: Group 19-20.

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: The J-box assembly is available in the J-box installation kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

J2802 Box As- 65C38484-11 1

sembly

1 Disassemble

Remove / Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

2 Remove / Keep Cover 65C38484-6 1

FIGURE 2: REMOVAL OF THE J2802 BOX ASSEMBLY COVER

(SHEET 1 OF 1)

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ALERT ALERT
This Figure applies only to: Group 1-13, 15-16.

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

BOX ASSEMBLY

(SHEET 1 OF 3)

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

BOX ASSEMBLY

(SHEET 2 OF 3)

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ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each airplane.

NOTE: Parts are available in the supplemental kit 65C37854-16. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Install Label-CTR-L 65C38484-31 1 (a)

(New)

1

Apply Top Coat BAC5710, TYPE 41 -

Install Label-CTR-R 65C38484-32 1 (b)

(New)

2

Apply Top Coat BAC5710, TYPE 41 -

Install Label-NOT-USED 65C38484-33 1 (c)

(New)

3

Apply Top Coat BAC5710, TYPE 41 -

Label-TEST SWITCH- 65C38484-36 1 (d)

ES

Install

(New)

4

Label-AUTO SHUTOFF 65C38484-37 1 (e)

Apply Top Coat BAC5710, Type 41 -

Refer to SWPM 20-10-11 as an accepted procedure.5 Install Wires W1760, W1770 -

(a) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-L". Refer to SWPM 20-10-11 as an accepted procedure..

(b) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-R". Refer to SWPM 20-10-11 as an accepted procedure.

(c) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "NOT USED". Refer to SWPM 20-10-11 as an accepted procedure.

(d) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "TEST" and one with "SWITCHES". Refer to SWPM 20-10-11 as an accepted procedure.

(e) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "AUTO" and one with "SHUTOFF". Refer to SWPM 20-10-11 as an accepted procedure.

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

BOX ASSEMBLY

(SHEET 3 OF 3)

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ALERT ALERT
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 1 OF 3)

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151 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-105. The wire kits possibly has more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11and SWPM 20-10-

12 as accepted procedures.

BMS13-58 Type 1, Class 9

1, AWG 20

1 Wire

Use white color tie material. Refer to SWPM

20-10-11 as an accepted procedure.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an accepted

procedure.

2 Contact, Pin BACC47CN1S 3

Install less than 4 inches from the connector

to identify the wire bundle. Refer to SWPM

20-10-11 as an accepted procedure.

3 ID Tape 61-74478-10501 1

Install at less than 6 inches from the connector to identify the connector.61-74478-10502 1

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-61-11 as accepted procedures.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 20

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an accepted

procedure.

M39029/11-145 or 3

M39029-11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an accepted

procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on each wire

end. Refer to SWPM 20-10-14 and SWPM

20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an accepted

procedure.

8 Contact BACC47DE1A 2

FIGURE 4: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 2 OF 3)

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152 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-19 as an accepted

procedure.

Contact, Sock- BACC47ER1 4

et

9

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from the connector to identify the connector.ID Tape 61-74478-10503 1

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

Revision 1 March 26, 2012 737-28A1216

153 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

154 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-107. The wire kits possibly has more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-

12 as accepted procedures.

BMS13-58 Type 1, Class 9

1, AWG 20

1 Wire

Use white color tie material. Refer to SWPM

20-10-11 as an accepted procedure.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an accepted

procedure.

2 Contact, Pin BACC47CN1S 3

Install adjacent to the connector to identify the

wire bundle. Refer to SWPM 20-10-11 as an

accepted procedure.

3 ID Tape 61-74478-10701 1

Install at less than 6 inches from the connector

to identify the connector.

61-74478-10702 1

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-61-11 as accepted procedures.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 20

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an accepted

procedure.

M39029/11-145 or 3

M39029-11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an accepted

procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on each wire

end. Refer to SWPM 20-10-14 and SWPM

20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an accepted

procedure.

8 Contact BACC47DE1A 2

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 2 OF 3)

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155 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-19 as an accepted

procedure.

Contact, Sock- BACC47ER1 4

et

9

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from the connector

to identify the connector.

ID Tape 61-74478-10703 1

FIGURE 5: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 3 OF 3)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

156 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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 -

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157 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

158 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each airplane.

NOTE: Parts are available in the supplemental kit 65C37854-16. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Install Label-CTR-L 65C38484-31 1 (a)

(New)

1

Apply Top Coat BAC5710, TYPE 41 -

Install Label-CTR-R 65C38484-32 1 (b)

(New)

2

Apply Top Coat BAC5710, TYPE 41 -

Install Label-AUX-AFT 65C38484-33 1 (c)

(New)

3

Apply Top Coat BAC5710, TYPE 41 -

Install Label-AUX-FWD 65C38484-33 1 (d)

(New)

4

Apply Top Coat BAC5710, TYPE 41 -

Label-TEST SWITCH- 65C38484-36 1 (e)

ES

Install

(New)

5

Label-AUTO SHUTOFF 65C38484-37 1 (f)

Apply Top Coat BAC5710, TYPE 41 -

Refer to SWPM 20-10-11 as an accepted procedure.6 Install Wires W1760, W1770 -

(a) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-L". Refer to SWPM 20-10-11 as an accepted procedure..

(b) As an option operators can use BACT19J2 Tape, or other equivalent materials, to fabricate the label.

Identify with "CTR-R". Refer to SWPM 20-10-11 as an accepted procedure.

(c) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "AUX-AFT". Refer to SWPM 20-10-11 as an accepted procedure.

(d) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the label.

Identify with "AUX-FWD". Refer to SWPM 20-10-11 as an accepted procedure.

(e) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "TEST" and one with "SWITCHES". Refer to SWPM 20-10-11 as an accepted procedure.

(f) As an option operators can use BACT19J4 Tape, or other equivalent materials, to fabricate the labels.

Identify one label with "AUTO" and one with "SHUTOFF". Refer to SWPM 20-10-11 as an accepted procedure.

FIGURE 6: WIRE BUNDLES W1760/W1770 INSTALLATION IN THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

159 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

160 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

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

for Auxiliary Tank installation. 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.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-

10-12 as accepted procedures.

BMS13-58 Type 1, Class 9

1, AWG 20

1 Wire

Use white color tie material. Refer to

SWPM 20-10-11 as an accepted procedure.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an accepted

procedure.

2 Contact, Pin BACC47CN1S 3

Refer to SWPM 20-30-00 and SWPM 20-

30-11 as accepted procedures.

3 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an accepted

procedure.

M39029/11-145 or 3

M39029-11-145

4 Contact, Pin

Refer to SWPM 20-30-00 and SWPM 20-

30-11 as accepted procedures.

5 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an accepted

procedure.

6 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on each

wire end. Refer to SWPM 20-10-14 and

SWPM 20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an accepted

procedure.

7 Contact BACC47DE1A 2

Refer to SWPM 20-81-19 as an accepted

procedure.

Contact, Sock- BACC47ER1 4

et

8

Use one in each empty contact hole of

the connector. Refer to SWPM 20-60-08

and SWPM 20-81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from the

connector to identify the connector.

ID Tape 61-74478-10601 1

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

Revision 1 March 26, 2012 737-28A1216

161 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

162 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-106. The wire kit possibly has more parts

than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-

10-12 as accepted procedures.

BMS13-58 Type 1, Class 9

1, AWG 20

1 Wire

Use white color tie material. Refer to SWPM

20-10-11 as an accepted procedure.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an accepted

procedure.

2 Contact, Pin BACC47CN1S 3

Install adjacent to the connector to identify

the wire bundle. Refer to SWPM 20-10-11

as an accepted procedure.

3 ID Tape 61-74478-10602 1

Install at less than 6 inches from the connector to identify the connector.61-74478-10502 1

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-61-11 as accepted procedures.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Refer to SWPM 20-30-00 and SWPM 20-

30-11 as accepted procedures.

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an accepted

procedure.

M39029/11-145 or 3

M39029-11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and SWPM 20-

30-11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an accepted

procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on each wire

end. Refer to SWPM 20-10-14 and SWPM

20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an accepted

procedure.

8 Contact BACC47DE1A 2

FIGURE 8: CONNECTION OF THE WIRE BUNDLE W1760

(SHEET 2 OF 3)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

163 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-19 as an accepted

procedure.

Contact, Sock- BACC47ER1 4

et

9

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from the connector to identify the connector.ID Tape 61-74478-10503 1

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

Revision 1 March 26, 2012 737-28A1216

164 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

165 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

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

for Auxiliary Tank installation. 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.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-

10-12 as accepted procedures.

BMS13-58 Type 1, Class 9

1, AWG 20

1 Wire

Use white color tie material. Refer to

SWPM 20-10-11 as an accepted procedure.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an accepted

procedure.

2 Contact, Pin BACC47CN1S 3

Refer to SWPM 20-30-00 and SWPM 20-

30-11 as accepted procedures.

3 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an accepted

procedure.

M39029/11-145 or 3

M39029-11-145

4 Contact, Pin

Refer to SWPM 20-30-00 and SWPM 20-

30-11 as accepted procedures.

5 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an accepted

procedure.

6 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on each

wire end. Refer to SWPM 20-10-14 and

SWPM 20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an accepted

procedure.

7 Contact BACC47DE1A 2

Refer to SWPM 20-81-19 as an accepted

procedure.

Contact, Sock- BACC47ER1 4

et

8

Use one in each empty contact hole of

the connector. Refer to SWPM 20-60-08

and SWPM 20-81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from the

connector to identify the connector.

ID Tape 61-74478-10801 1

FIGURE 9: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 2 OF 2)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

166 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

167 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-108. The wire kit possibly has more parts

than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-

12 as accepted procedures.

BMS13-58 Type 1, Class 9

1, AWG 20

1 Wire

Use white color tie material. Refer to SWPM

20-10-11 as an accepted procedure.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Lacing Tape

Refer to SWPM 20-61-11 as an accepted

procedure.

2 Contact, Pin BACC47CN1S 3

Install adjacent to the connector to identify

the wire bundle. Refer to SWPM 20-10-11

as an accepted procedure.

3 ID Tape 61-74478-10802 1

Install at less than 6 inches from the connector to identify the connector.61-74478-10702 1

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-61-11 as accepted procedures.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.

4 Terminal Lug BACT12AR203 2

Refer to SWPM 20-90-11 as an accepted

procedure.

M39029/11-145 or 3

M39029-11-145

5 Contact, Pin

Refer to SWPM 20-30-00 and SWPM 20-30-

11 as accepted procedures.

6 Terminal Lug BACT12AR202 2

Refer to SWPM 20-90-11 as an accepted

procedure.

7 Contact BACC47DE1A 2

Use a minimum 0.5 inch long on each wire

end. Refer to SWPM 20-10-14 and SWPM

20-90-11 as accepted procedures.

61-74478-2005 (Supplier -

Part Number: M23053/5-

104-4)

Sleeve

Refer to SWPM 20-20-11 as an accepted

procedure.

8 Contact BACC47DE1A 2

FIGURE 10: CONNECTION OF THE WIRE BUNDLE W1770

(SHEET 2 OF 3)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

168 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-19 as an accepted

procedure.

Contact, Sock- BACC47ER1 4

et

9

Use one in each empty contact hole of the

connector. Refer to SWPM 20-60-08 and

SWPM 20-81-19 as accepted procedures.

Seal Plug MS27488-20-1 4

Install at less than 6 inches from the connector to identify the connector.ID Tape 61-74478-10703 1

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

Revision 1 March 26, 2012 737-28A1216

169 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-13, 15-16, 19-20.

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SWPM 20-10-04 as an

acceptable procedure.

1 Clean J-BOX ASSEMBLY 65C38484-( ) 1

2 Put COVER 65C38484-6 1 On the box assembly.

Install (Kept) BOLT BACS12HN3-8 6

Install (Kept) WASHER NAS1149F0363P 6

FIGURE 11: INSTALLATION OF THE J2802 BOX ASSEMBLY COVER

(SHEET 1 OF 1)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

170 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

171 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 2 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

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172 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Part is in the kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With clamps when the J-box is

level on the E2 and E3 support

posts.

KIT ASSY - J2802 65C38484-10 1

JBOX

1 Attach

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

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

FIGURE 12: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

173 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

174 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 2 OF 3)

BOEING PROPRIETARY -

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Part is in the kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

With clamps when the J-box is

level on the E2 and E3 support

posts.

KIT ASSY - J2802 65C38484-11 1

JBOX

1 Attach

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

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

FIGURE 13: ATTACHMENT OF THE J2802 BOX ASSEMBLY

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-13, 15-16, 19-20.

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

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

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

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Align J-BOX ASSEMBLY 65C38484-( ) 1 On the E3 support post.

2 Drill HOLE - 3 0.161-0.164 inch diameter.

3 Drill HOLE - 4 0.218-0.229 inch diameter.

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

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove J-BOX ASSEMBLY 65C38484-( ) 1 From the support posts.

Refer to SOPM 20-30-03 as an

accepted procedure.

2 Clean HOLE - 4

By abrasive cleaning for faying

surface bonding. (a)

3 Clean HOLE - 14

(a) Refer to SWPM 20-20-00 as an accepted procedure.

FIGURE 15: PREPARATION OF THE J2802 BOX ASSEMBLY, E2 AND E3 SUPPORT POSTS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-13, 15-16.

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

(SHEET 1 OF 2)

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182 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: Part is in the kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank and J-box

faying surface. Refer to SOPM

20-50-19 and SWPM 20-20-00

as an acceptable procedures.

1 Apply SEALANT BMS5-95 -

KIT ASSY - J2802 65C38484-10 1

JBOX

Install (New)

BOLT, PROTRUD- BACB30NX5HK6 6

ING HD

Install (New)

SPACERS FOR NAS42DD6-16FC 6

RIVETS

Install (New)

COLLAR, BACC30BH5 6

PRELOAD

Install (New)

COLLAR, BACC30BH5 6

PRELOAD

2 Tighten

On the bolt heads. Refer to

SOPM 20-50-19 as an acceptable procedure.

3 Apply SEALANT BMS5-95 -

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

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 19-20.

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

(SHEET 1 OF 2)

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184 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: Part is in the kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank and J-box faying

surface. Refer to SOPM 20-50-19

and SWPM 20-20-00 as an acceptable procedures.

1 Apply SEALANT BMS5-95 -

KIT ASSY - J2802 65C38484-11 1

JBOX

Install (New)

BOLT, PROTRUD- BACB30NX5HK6 6

ING HD

Install (New)

SPACERS FOR NAS42DD6-16FC 6

RIVETS

Install (New)

COLLAR, BACC30BH5 6

PRELOAD

Install (New)

COLLAR, BACC30BH5 6

PRELOAD

2 Tighten

On the bolt heads. Refer to SOPM

20-50-19 as an acceptable procedure.

3 Apply SEALANT BMS5-95 -

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

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-13, 15-16, 19-20.

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (New) CLAMP OLYMPIC 287T0011-1 4

Install (New) BOLT BACS12HN3-8 4

Install (New) WASHER NAS1149D0316H 4

Install (New) NUT BACN10YR3CD 4

Maximum resistance is 0.5 milliohms between J-box and support post faying surfaces. (a) (c)2 Measure J-BOX ASSEMBLY 65C38484-( ) 1

BONDING BACJ40AB20-6 1 (b)

JUMPER

3 Install (New)

Install (New) BOLT BACS12HN3-7 2

Install (New) WASHER NAS1149D0316H 6

Install (New) NUT BACN10YR3CD 2

4 Torque BOLT BACS12HN3-7 2 35 to 45 inch pound. (b)

Torque NUT BACN10YR3CD 2

Maximum resistance is 0.001

Ohms (1.0 milliohms) between

jumper faying surfaces. (a) (c)

ELECTRICAL BACJ40AB20-6 1

BONDING RESISTANCE

5 Measure

Maximum resistance is 3.5 milliohms between J2802 Box and

Stanchion. (a) (c)

ELECTRICAL - 1

BONDING RESISTANCE

6 Measure

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

7 Apply

Refer to SOPM 20-41-02 as an

accepted procedure.

BMS10-11, TYPE -

1

8 Apply PRIMER FINISH

On the support posts. Refer to

SOPM 20-41-02 as an accepted

procedure.

BMS10-11, TYPE -

2, COLOR WHITE

9 Apply ENAMEL FINISH

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) Refer to SWPM 20-20-10 as an accepted procedure.

(c) If the resistance measurement is greater than the maximum resistance shown, then disassemble parts,

clean faying surfaces, install parts and measure bonding resistance again. Refer to SWPM 20-20-00

as an accepted procedure.

FIGURE 18: INSTALLATION THE BONDING JUMPER AND CLAMPS

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep Cover 65-49815-( ) 1

2 Remove / Keep Closure Panel 69-41661-( ) 1

The panel has the captive

screws.

3 Remove / Keep Cover Panel 69-41661-( ) 1

4 Open P6-2 Panel 65C25704-( ) 1

5 Remove / Keep Bolt NAS514P1032-( ) 8

6 Remove / Keep Channel 65-49815-( ) 1 If necessary to get access.

7 Remove / Keep Screw NAS1801-3-8 5 If necessary to get access.

Washer AN960PD10L 5 If necessary to get access.

As necessary to get access

to the wires and connectors.

8 Move Relay Panel 69-73627-( ) 1

From the connectors that are

identified as R54 and R55 on

the panel.

9 Remove / Keep Relay KCD4N 2

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

FIGURE 19: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 20: INSTALLATION OF THE P5 PANEL WIRE BUNDLE W036

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1, 21.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on adjacent wires

to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13- -

54, Class 1, Grade D, Type

III, Finish C, White

Lacing Tape

61-74478-2002, BMS13- -

54, Class 1, Grade D, Type

III, Finish C, Red Color

61-74478-2003, BMS13- -

54, Class 1, Grade D, Type

III, Finish C, Yellow Color

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on adjacent wires

to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13- -

54, Class 1, Grade D, Type

III, Finish C, White

Lacing Tape

61-74478-2002, BMS13- -

54, Class 1, Grade D, Type

III, Finish C, Red

61-74478-2003, BMS13- -

54, Class 1, Grade D, Type

III, Finish C, Yellow

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on adjacent wires

to the connector. Refer to SWPM 20-10-11 and

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 21: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

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194 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 2-3, 22-23.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

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195 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Color

Lacing Tape

61-74478-2002, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, Red

Color

61-74478-2003, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, Yellow

Color)

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, White

Color

Lacing Tape

61-74478-2002, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, Red

Color

61-74478-2003, BMS13- -

54, Class 1, Grade D,

Type III, Finish C, Yellow

Color

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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196 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 22: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

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197 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 4-5, 24.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

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198 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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199 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 23: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

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200 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 6-7, 25.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

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201 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10103 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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202 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10106 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.7 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.8 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 24: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

203 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 8, 26.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

204 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

205 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 25: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

206 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

207 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10106 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

208 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.7 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

10 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 26: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

209 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 10-11, 27-28.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

210 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

211 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use white or red or yellow color tie material same

as the adjacent wires. Refer to SWPM 20-10-11

SWPM 20-10-19

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 27: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

212 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 12, 29.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

213 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

Wire

Lacing Tape

2

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10103 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

214 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10106 1 Install at less than 6 inches from the connector.

7 Contact, Socket BACC47CP1S 2 Refer to SWPM 20-61-11

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.8 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use white or red or yellow color tie material same

as the adjacent wires. Refer to SWPM 20-10-11

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 28: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

215 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 13.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

216 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

217 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use white or red or yellow color tie material same

as the adjacent wires. Refer to SWPM 20-10-11

SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 29: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

218 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

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219 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10103 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10106 1 Install at less than 6 inches from the connector.

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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220 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.7 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.8 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

11 Lacing Tape

61-74478-2002,BMS 13-54, -

CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 30: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

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221 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 15.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

222 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10103 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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223 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10106 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.Contact, Sock- BACC47CP1S 2

et

7

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.8 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 31: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

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224 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 16.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

225 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-101. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003 , BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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226 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 32: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

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227 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17-20, 30.

FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 1 OF 2)

BOEING PROPRIETARY -

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228 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep Cover 65-49815-( ) 1

2 Remove / Keep Closure Panel 69-41661-( ) 1

3 Remove / Keep Cover Panel 69-41661-( ) 1 The panel has the captive screws.

4 Open P6-2 Panel 65C25704-( ) 1

5 Remove / Keep Bolt NAS514P1032-( ) 8

6 Remove / Keep Channel 65-49815-( ) 1

7 Remove / Keep Screw NAS1801-3-8 5

Washer AN960PD10L 5

As necessary to get access to the

wires and connectors.

8 Move Relay Panel 69-73627-( ) 1

From the relay locations that are

identified as R54 and R55 on the

relay panel.

9 Remove / Keep Relay KCD4N 2

From the relay locations that are

identified as R146 and R147 on the

relay panel.

10 Remove / Keep Relay 10-60450-6 2

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

FIGURE 33: REMOVAL OF THE RELAYS FROM THE P6 PANEL

(SHEET 2 OF 2)

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229 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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.

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230 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

231 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

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

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232 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 35: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

233 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 19, 30.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

234 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN2 2

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10210 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

ID Tape 61-74478-10203 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 3

ID Tape 61-74478-10201 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

235 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-30-12 as an accepted procedure.6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10208 1

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10206 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 36: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

236 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 19, 30.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

237 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN2 2

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10210 or BMS13- -

48, Type 1, Class 1, AWG

18

Filler Wire

ID Tape 61-74478-10204 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 3

ID Tape 61-74478-10205 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

238 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10209 1

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10207 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 37: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

239 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

240 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

241 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-10104 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10101 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10107 1

Refer to SWPM 20-30-12 as an accepted procedure.8 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

9 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 38: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

242 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

243 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10202 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 3

ID Tape 61-74478-10201 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10105 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

244 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-30-12 as an accepted procedure.6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10208 1

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10206 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 39: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

245 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

246 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN2 2

61-74478-10210 or - Into the contact barrel.

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10204 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 3

ID Tape 61-74478-10205 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

247 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10209 1

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10207 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 40: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

248 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 18, 20.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

249 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-

12 as accepted procedures.

BMS13-58, Type 5, Class 2

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-

12 as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted

procedure.

3 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from the connector.ID Tape 61-74478-10105 1

Refer to SWPM 20-61-11 as an accepted

procedure.

4 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from the connector.ID Tape 61-74478-10103 1

FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

250 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted

procedure.

5 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from the connector.ID Tape 61-74478-10102 1

Refer to SWPM 20-61-11 as an accepted

procedure.

6 Contact, Pin BACC47CN1S 1

Install at less than 6 inches from the connector.ID Tape 61-74478-10106 1

Refer to SWPM 20-61-11 as an accepted

procedure.

7 Contact, Socket BACC47CP1S 2

Install at less than 6 inches from the connector.ID Tape 61-74478-10104 1

Refer to SWPM 20-61-11 as an accepted

procedure.

8 Contact, Pin BACC47CN1S 2

Install at less than 6 inches from the connector.ID Tape 61-74478-10101 1

Refer to SWPM 20-30-12 as an accepted

procedure.

9 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted

procedure.

ID Sleeve 61-74478-10106 1

Refer to SWPM 20-30-12 as an accepted

procedure.

10 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted

procedure.

ID Sleeve 61-74478-10108 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-

10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

11 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 41: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

251 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 18, 20.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

252 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10202 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 3

ID Tape 61-74478-10201 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10103 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

253 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-30-12 as an accepted procedure.6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10208 1

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10206 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 42: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

254 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 18, 20.

REFERENCE: 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM 28-43-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 1 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

255 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-102. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 5, Class 1

1, AWG 24

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 4

1, AWG 20

2 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

Refer to SWPM 20-61-11 as an accepted procedure.3 Contact, Pin BACC47CN2 2

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10210 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10204 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Pin BACC47CN1S 3

ID Tape 61-74478-10205 1 Install at less than 6 inches from the connector.

FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 2 OF 3)

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Original Issue: July 29, 2010

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256 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Pin BACC47CN1S 1

ID Tape 61-74478-10106 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.6 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10209 1

Refer to SWPM 20-30-12 as an accepted procedure.7 Splice 34137 1

Sleeve, Sealing D-436-46 or D436-46 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10207 1

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-11

and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

8 Lacing Tape

61-74478-2002, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, RED

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, YELLOW

FIGURE 43: CONNECTION OF THE WIRE BUNDLE W036

(SHEET 3 OF 3)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

257 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 44: INSTALLATION OF THE P6 PANEL WIRE BUNDLE W044

(SHEET 1 OF 1)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

258 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1, 21.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-

12 as accepted procedures.

BMS13-58, Type 1, 2

Class 1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

61-74478-2003 BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, YELLOW

FIGURE 45: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

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259 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an accepted

procedure.

2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-

00 as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1,

Class 1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted

procedure.

3 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-

00 as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1,

Class 1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted

procedure.

4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted

procedure.

5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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.

6 Contact, Pin BACC47DE4A or 2

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.

BACC47DE7A 2

Use the same tie color as the existing ties on

the wires. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

61-74478-2003, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, YELLOW

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

Revision 1 March 26, 2012 737-28A1216

260 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 2, 22, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

261 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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.

6 Contact, Pin BACC47DE4A or 2

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.

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 46: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

262 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 2, 22, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 47: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

263 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

264 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 3, 16, 23.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 48: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

265 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

266 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 4, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 49: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

267 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

268 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 4, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 50: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

269 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

270 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 5, 8, 24, 26.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

271 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 51: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

272 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 6, 25, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 52: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

273 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

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

Revision 1 March 26, 2012 737-28A1216

274 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 6, 25, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

275 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 53: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

276 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 9, 31.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

277 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 54: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

278 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 10, 27.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

279 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 55: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

280 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 12, 29, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

281 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 56: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

282 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 12, 29, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

283 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 57: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

284 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 13.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

285 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003 , BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 58: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

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286 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 7.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

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Original Issue: July 29, 2010

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287 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Socket 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Socket 316-1616-634 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 59: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

288 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 60: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

289 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

290 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 61: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

291 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

Use to increase the wire diameter in the contact

barrel. Refer to SWPM 20-60-00 as an accepted

procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

292 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 11, 28, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 62: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

293 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

294 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 11, 28, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 63: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

295 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

296 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 15, Configuration 1.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 64: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

297 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

298 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 15, Configuration 2.

REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-103. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

FIGURE 65: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

299 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

300 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

301 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

302 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Pin BACC47CP2T` 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

303 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

304 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

305 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C, BMS

13-54, CLASS 1, GRADE

D, TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

306 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

307 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

308 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

309 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

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

Revision 1 March 26, 2012 737-28A1216

310 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

311 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 17 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

312 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

313 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

314 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

315 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

316 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

317 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

318 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

319 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

320 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

321 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

322 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

323 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Airplanes in Group 18 have been delivered without Auxiliary Tanks but with wire provisions for Auxiliary

Tank installation. It is necessary to do the change given in this figure only if Auxiliary Tank with Fuel

Boost pumps are installed on the airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

324 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

325 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

326 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-17 as an accepted procedure.2 Contact, Pin 316-1616-634 1

in the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or 1

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-17 as an accepted procedure.3 Contact, Pin 316-1616-634 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

327 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

328 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

329 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

330 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

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

Revision 1 March 26, 2012 737-28A1216

331 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

332 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10307 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10305 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

333 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

334 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

335 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

336 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

337 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

338 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 22

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10302 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Pin BACC47CP2T 1

In the contact barrel. Refer to SWPM 20-60-00

as an accepted procedure.

61-74478-10309 or -

BMS13-48, Type 1, Class

1, AWG 18

Filler Wire

ID Tape 61-74478-10301 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

339 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

340 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

341 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

Refer to SWPM 20-81-11 as an accepted procedure.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

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

Revision 1 March 26, 2012 737-28A1216

342 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 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

Revision 1 March 26, 2012 737-28A1216

343 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

344 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-02

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-104. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, Class 2

1, AWG 20

1 Wire

Use the same color as the ties on the adjacent

wires to the connector. Refer to SWPM 20-10-

11 and SWPM 20-10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

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.2 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10402 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-81-11 as an accepted procedure.3 Contact, Socket BACC47CP2T 1

ID Tape 61-74478-10401 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.4 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10306 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.5 Contact, Socket BACC47CP1S 1

ID Tape 61-74478-10308 1 Install at less than 6 inches from the connector.

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 2 OF 3)

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345 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

6 Contact, Pin BACC47DE4A or 2

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)

BACC47DE7A 2

Use the same tie color as the existing ties on the

wires. Refer to SWPM 20-10-11 and SWPM 20-

10-19 as accepted procedures.

61-74478-2001, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

WHITE

Lacing Tape

61-74478-2003, BMS 13- -

54, CLASS 1, GRADE D,

TYPE III, FINISH C,

YELLOW

(a) Each deleted wire possibly connected with no other wire or one other existing wire.

FIGURE 81: CONNECTION OF THE WIRE BUNDLE W044

(SHEET 3 OF 3)

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346 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-16, 19-20.

FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 1 OF 4)

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347 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 2 OF 4)

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348 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 3 OF 4)

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349 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 82: INSTALLATION OF WIRE BUNDLE W368, W386, W1764 AND W1774

(SHEET 4 OF 4)

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350 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-16, 21-29, 31.

REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-109. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, 3

Class 1, AWG 20

1 Wire

On the wires at STA 259.5. Refer to SWPM 20-

10-18. (a)

61-74478-2006 or BMS 1

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)

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351 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.2 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10902 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change the existing

wire identification number. Refer to SWPM 20-

10-11 as an accepted procedure. (b)

ID Tape 61-74478-10906 2

ID Tape 61-74478-10903 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10905 1

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

Install at the wire bundle breakout adjacent to

the splice. Refer to SWPM 20-10-11 as an accepted procedure.

5 ID Tape 61-74478-10901 1

Refer to SWPM 20-61-11 as an accepted procedure.6 Connector BACC45FT24-43S 1

Refer to SWPM 20-61-11 as an accepted procedure.Contact, Socket BACC47CP1S 3

Use one in each empty contact hole at the

connector. Refer to SWPM 20-60-08 as an accepted procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 20

ID Tape 61-74478-10904 1 Install at less than 6 inches from the connector.

Install at less than 12 inches from the connector.

Refer to SWPM 20-10-11 as an accepted procedure.

61-74478-10901 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit 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)

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352 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

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)

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353 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

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354 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM

28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

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

for Auxiliary Tank installation. It is necessary to install wires W1764-004-20, W1764-005-20, and

W1764-006-20 given in this figure only if Auxiliary Tank with Fuel Boost pumps are installed on the

airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-110. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, 6

Class 1, AWG 20

1 Wire

On the wires at STA 259.5. Refer to SWPM 20-

10-18. (a)

61-74478-2006 or BMS 1

13-52, Type V or

NA728R99

Expando Sleeve

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

Refer to SWPM 20-61-11 as an accepted procedure.2 Contact, Pin BACC47CN1S 2

ID Tape 61-74478-10902 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change the existing wire

identification number. Refer to SWPM 20-10-11

as an accepted procedure. (b)

ID Tape 61-74478-10906 2

ID Tape 61-74478-10903 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-10905 1

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

FIGURE 84: CONNECTION OF WIRE BUNDLE W368 AND W1764

(SHEET 2 OF 3)

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Original Issue: July 29, 2010

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355 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Install at the wire bundle breakout adjacent to the

splice. Refer to SWPM 20-10-11 as an accepted

procedure.

5 ID Tape 61-74478-11002 1

Refer to SWPM 20-61-11 as an accepted procedure.6 Contact, Socket BACC47CP1S 3

ID Tape 61-74478-11001 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-61-11 as an accepted procedure.7 Connector BACC45FT24-43S 1

Refer to SWPM 20-61-11 as an accepted procedure.Contact, Socket BACC47CP1S 6

Use one in each empty contact hole at the connector. Refer to SWPM 20-60-08 as an accepted

procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

ID Tape 61-74478-10904 1 Install at less than 6 inches from the connector.

Install at less than 12 inches from the connector.

Refer to SWPM 20-10-11 as an accepted procedure.

61-74478-11002 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit 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)

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356 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 8, 16, 26.

REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-111. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-

12 as accepted procedures.

BMS13-58, Type 1, 3

Class 1, AWG 20

1 Wire

On the wires at STA 259.5. Refer to SWPM

20-10-18. (a)

61-74478-2006 or BMS 1

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)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

357 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.2 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-11102 1 Install at less than 6 inches from the connector.

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

3 Lacing Tape

Install at the two ends to change the existing

wire identification number. Refer to SWPM 20-

10-11 as an accepted procedure.

ID Tape 61-74478-11106 2

ID Tape 61-74478-11103 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-11105 1

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

Install at the wire bundle breakout adjacent to

the splice. Refer to SWPM 20-10-11 as an accepted procedure.

5 ID Tape 61-74478-11101 1

Refer to SWPM 20-61-11 as an accepted procedure.6 Connector BACC45FT24-43S6 1

Contact, Socket BACC47CP1S 3

Use one in each empty contact hole at the

connector. Refer to SWPM 20-60-08 as an

accepted procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

ID Tape 61-74478-11104 1 Install at less than 6 inches from the connector.

Install at less than 12 inches from the connector. Refer to SWPM 20-10-11 as an accepted

procedure.

61-74478-11101 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit 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)

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Original Issue: July 29, 2010

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358 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-7, 9-15, 21-25, 27-29, 31.

REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: Parts are available in the wire kits 61-74478-1 and 61-74478-111. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12

as accepted procedures.

BMS13-58, Type 1, 3

Class 1, AWG 20

1 Wire

On the wires at STA 259.5. Refer to SWPM 20-

10-18. (a)

61-74478-2006 or BMS -

13-52, Type V or

NA728R99

Expando Sleeve

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

FIGURE 86: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 1 OF 2)

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Original Issue: July 29, 2010

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359 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-61-11 as an accepted procedure.2 Contact, Socket BACC47CP1S 2

ID Tape 61-74478-11102 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change the existing

wire identification number. Refer to SWPM 20-

10-11 as an accepted procedure.

ID Tape 61-74478-11106 2

ID Tape 61-74478-11103 1 Install at less than 6 inches from the connector.

Refer to SWPM 20-30-12 as an accepted procedure.4 Splice D-436-37 or D436-37 1

Refer to SWPM 20-10-14 as an accepted procedure.ID Sleeve 61-74478-11105 1

Refer to SWPM 20-10-11 as an accepted procedure.61-74478-2001, BMS -

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

Install at the wire bundle breakout adjacent to

the splice. Refer to SWPM 20-10-11 as an accepted procedure.

5 ID Tape 61-74478-11101 1

Refer to SWPM 20-61-11 as an accepted procedure.6 Connector BACC45FT24-43S6 1

Contact, Socket BACC47CP1S 3

Use one in each empty contact hole at the connector. Refer to SWPM 20-60-08 as an accepted

procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

ID Tape 61-74478-11104 1 Install at less than 6 inches from the connector.

Install at less than 12 inches from the connector.

Refer to SWPM 20-10-11 as an accepted procedure.

61-74478-11101 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit 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

Revision 1 March 26, 2012 737-28A1216

360 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

361 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
REFERENCE: 737-300/400/500 WDM 28-23-01, 737-300/400/500 WDM 28-23-02, 737-300/400/500 WDM

28-43-01

The flag shown below agree with the numbers shown in the circle symbols in the figure.

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

for Auxiliary Tank installation. It is necessary to install wires W1774-004-20, W1774-005-20, and

W1774-006-20 given in this figure only if Auxiliary Tank with Fuel Boost pumps are installed on the

airplane.

NOTE: Parts are available in the wire kits 61-74478-2 and 61-74478-112. The wire kits possibly have more

parts than necessary.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-10-11 and SWPM 20-10-12 as

accepted procedures.

BMS13-58, Type 1, 6

Class 1, AWG 20

1 Wire

On the wires at STA 259.5. Refer to SWPM 20-10-18.

(a)

61-74478-2006 or -

BMS 13-52, Type V or

NA728R99

Expando Sleeve

61-74478-2001, BMS - Refer to SWPM 20-10-11 as an accepted procedure.

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

2 Contact, Socket BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure.

ID Tape 61-74478-11102 1 Install at less than 6 inches from the connector.

61-74478-2001, BMS - Refer to SWPM 20-10-11 as an accepted procedure.

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

3 Lacing Tape

Install at the two ends to change the existing wire

identification number. Refer to SWPM 20-10-11 as an

accepted procedure.

ID Tape 61-74478-11106 2

ID Tape 61-74478-11103 1 Install at less than 6 inches from the connector.

4 Splice D-436-37 or D436-37 1 Refer to SWPM 20-30-12 as an accepted procedure.

ID Sleeve 61-74478-11105 1 Refer to SWPM 20-10-14 as an accepted procedure.

61-74478-2001, BMS - Refer to SWPM 20-10-11 as an accepted procedure.

13-54, CLASS 1,

GRADE D, TYPE III,

FINISH C, WHITE

Lacing Tape

Install at the wire bundle breakout adjacent to the

splice. Refer to SWPM 20-10-11 as an accepted procedure.

5 ID Tape 61-74478-11202 1

FIGURE 87: CONNECTION OF WIRE BUNDLE W386 / W1774

(SHEET 2 OF 3)

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Original Issue: July 29, 2010

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362 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

6 Contact, Socket BACC47CP1S 3 Refer to SWPM 20-61-11 as an accepted procedure.

ID Tape 61-74478-11201 1 Install at less than 6 inches from the connector.

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

7 Connector BACC45FT24-43S6 1 Refer to SWPM 20-61-11 as an accepted procedure.

Contact, Socket BACC47CP1S 6

Use one in each empty contact hole at the connector.

Refer to SWPM 20-60-08 as an accepted procedure.

Seal Plug MS27488-16-1 or 20

MS27488-20-1 17

ID Tape 61-74478-11104 1 Install at less than 6 inches from the connector.

Install at less than 12 inches from the connector. Refer

to SWPM 20-10-11 as an accepted procedure.

61-74478-11101 1

(a) There is only one expando sleeve provided in the kit for both wire bundles W1764 and W1774. Wire

bundles W1764 and W1774 are sleeved together in the expando sleeve. The expando sleeve is installed

in the existing conduit 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 -

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Original Issue: July 29, 2010

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363 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

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364 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

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

(SHEET 2 OF 3)

BOEING PROPRIETARY -

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365 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are in the kit 65C38484-8.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

To make a drip loop below the

J2802 box assembly.

1 Adjust WIRE BUNDLE W1764 1

Adjust WIRE BUNDLE W1774 1

To close the clamps on the wire

bundles.

BACS38W2I 4

(BACS38W2 or

BACS38W2 optional)

2 Install (New) STRAP

Around the adjacent wire bundle

if installed. Refer to SWPM 20-

10-11, "Split Sleeve Installation",

as an accepted procedure.

65C38484-14 1

(M23053/12-514-C)

INSULATION

SLEEVING, HEAT

SHRINKABLE

PTFE.

3 Install (New)

Use quantity as necessary on

the sleeve and wire bundles.

BACS38W2I 6

(BACS38W2 or

BACS38W2 optional)

Install (New) STRAP

Refer to SWPM 20-81-22 as an

accepted procedure.

TDH-1852-1502 or 2

TDH1852-1502

4 Install Relay

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

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 19-20.

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

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

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

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts are in the kit 65C38484-9.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

To make a drip loop below the

J2802 box assembly.

1 Adjust WIRE BUNDLE W1764 1

Adjust WIRE BUNDLE W1774 1

To close the clamps on the wire

bundles.

BACS38W2I 4

(BACS38W2 or

BACS38W2 optional)

2 Install (New) STRAP

Around the adjacent wire bundle

if installed. Refer to SWPM 20-

10-11, "Split Sleeve Installation",

as an accepted procedure.

65C38484-14 1

(M23053/12-514-C)

INSULATION

SLEEVING, HEAT

SHRINKABLE

PTFE.

3 Install (New)

Use quantity as necessary on

the sleeve and wire bundles.

BACS38W2I 6

(BACS38W2 or

BACS38W2 optional)

Install (New) STRAP

Refer to SWPM 20-81-22 as an

accepted procedure.

TDH-1852-1502 or 4

TDH1852-1502

4 Install Relay

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

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 1-16, 21-29, 31.

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Close P6-1 Panel 65C25704-( ) 1

At the initial R54 and R55

relay locations.

2 Install (Kept) Relay KCD4N 2

3 Move Relay Panel 69-73627-( ) 1 To the initial location.

4 Install (Kept) Screw NAS1801-3-8 5

Washer AN960PD10L 5

At the initial location if removed.5 Install (Kept) Channel 65-49815-( ) 1

Through the channel if removed.6 Install (Kept) Bolt NAS514P1032-( ) 8

7 Close P6-2 Panel 65C25704-( ) 1

8 Install (Kept) Closure Panel 69-41661-( ) 1

9 Install (Kept) Cover 65-49815-( ) 1

The panel has the captive

screws.

10 Install (Kept) Cover Panel 69-41661-( ) 1

FIGURE 90: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17-20, 30.

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Close P6-1 Panel 65C25704-( ) 1

P6-3 Panel 65C25704-( ) 1

At the initial R54 and R55

relay locations.

2 Install (Kept) Relay KCD4N 2

At the initial R146 and R147

relay locations.

3 Install (Kept) Relay 10-60450-6 2

4 Move Relay Panel 69-73627-( ) 1 To the initial location.

5 Install (Kept) Screw NAS1801-3-8 5

Washer AN960PD10L 5

At the initial location if removed.6 Install (Kept) Channel 65-49815-( ) 1

Through the channel if removed.7 Install (Kept) Bolt NAS514P1032-( ) 8

8 Close P6-2 Panel 65C25704-( ) 1

9 Install (Kept) Closure Panel 69-41661-( ) 1

10 Install (Kept) Cover 65-49815-( ) 1

The panel has the captive

screws.

11 Install (Kept) Cover Panel 69-41661-( ) 1

FIGURE 91: INSTALLATION OF THE RELAYS IN THE P6 PANEL

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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. Parts to rework the J-Box

are available in the supplemental kit 65C37854-16. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Disassemble J-BOX ASSEMBLY 65C38484-10 1

Remove/ Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

2 Remove Cover 65C38484-6 1

3 Remove Rivets BACR15BB( )D( )C 4 (a)

4 Remove/Keep Disconnect Angle 287U0016-185 2

Trim the left and right flange of

the J2802 box assembly to accomodate the installation of the

repair bracket.

5 Cut Flange 65C38484-12 2

6 Deburr Edge 65C38484-12 1

Refer to SOPM 20-43-03 as an

accepted procedure.

TYPE 2, CLASS A, -

or TYPE 5 CLASS

F

Chemical Conversion Coating7 Apply

FIGURE 92: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SOPM 20-41-02 as an

accepted procedure.

8 Apply Primer BMS 10-11, Type 1 -

9 Clean J-BOX ASSEMBLY 65C38484-10 1 (b)

10 Install (New) Label-CTR-L 65C38484-31 1 (c)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

11 Install (New) Label-CTR-R 65C38484-32 1 (d)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

12 Install (New) Label-NOT-USED 65C38484-33 1 (e)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

Label-TEST 65C38484-36 1 (f)

SWITCHES

13 Install (New)

Label-AUTO 65C38484-37 1 (g)

SHUTOFF

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

Refer to SOPM 20-50-10 as an

accepted procedure. (h)

14 Identify J-BOX ASSEMBLY 65C38484-16

(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)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17-18, 30.

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 4)

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377 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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. Parts to rework the J-Box

are available in the supplemental kit 65C37854-16. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Disassemble J-BOX ASSEMBLY 65C38484-11 1

Remove/ Keep Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

2 Remove Cover 65C38484-6 1

3 Remove Rivets BACR15BB( )D( )C 4 (a)

4 Remove/Keep Disconnect Angle 287U0016-185 2

Trim the left and right flange of

the J2802 box assembly to accomodate the installation of the

repair bracket.

5 Cut Flange 65C38484-12 2

6 Deburr Edge 65C38484-12 1

Refer to SOPM 20-43-03 as an

accepted procedure.

TYPE 2, CLASS A, -

or TYPE 5 CLASS

F

Chemical Conversion Coating7 Apply

Refer to SOPM 20-41-02 as an

accepted procedure.

8 Apply Primer BMS 10-11, Type 1 -

FIGURE 93: CHANGE OF THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

9 Clean J-BOX ASSEMBLY 65C38484-10 1 (b)

10 Install (New) Label-CTR-L 65C38484-31 1 (c)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

11 Install (New) Label-CTR-R 65C38484-32 1 (d)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

12 Install (New) Label-AUX-AFT 65C38484-33 1 (e)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

13 Install (New) Label-AUX-FWD 65C38484-33 1 (f)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

Label-TEST 65C38484-36 1 (g)

SWITCHES

14 Install (New)

Label-AUTO 65C38484-37 1 (h)

SHUTOFF

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

Refer to SOPM 20-50-10 as an

accepted procedure. (i)

15 Identify J-BOX ASSEMBLY 65C38484-16

(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)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, 21-29, 31.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 6)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 6)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

383 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 6)

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384 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts to rework the J-Box are available in the supplemental kit 65C37854-15. The kit possibly has more

parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Make sure and maintain the

edge margin for the holes

1 Locate Bracket 65C38484-19 1

J2802 Panel Assy 65C38484-16 1

2 Put/Hold Disconnect Bracket 287U0016-185 2

Close Ream Holes in accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable

0.1905-0.1895 Inch 4

DIA

3 Drill Holes

4 Remove Disconnect Bracket 287U0016-185 1

Bracket 65C38484-19 1

5 Locate Bracket 65C38484-18 1

J2802 Panel Assy 65C38484-16 1

6 Put/Hold Disconnect Bracket 287U0016-185 2

Close Ream Holes in accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable

0.1905-0.1895 Inch 4

DIA

7 Drill Holes

In accordance with 737-300

SRM 51-40-05, 737-400 SRM

51-40-05, or 737-500 SRM 51-

40-05 as applicable

0.229-0.218 Inch 1

DIA

8 Drill Hole

9 Remove Disconnect Bracket 287U0016-185 1

Bracket 65C38484-19 1

10 Deburr Bracket 65C38484-19 1

Bracket 65C38484-18 1

Disconnect Angle 287U0016-185 2

J2802 Panel 65C38484-16 1

0.010 - 0.015 Inch deep on the

inner side.

11 Countersink J2802 Panel 65C38484-10 4

Shave the rivet flush on the inner side of the panel12 Install Rivet BACR15BB6AD

FIGURE 94: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

In accordance with 737-300

SRM 51-40-02, 737-400 SRM

51-40-02, or 737-500 SRM 51-

40-02 as applicable

13 Install Screw BACS12HN3-8 16

Washer NAS1149D0316H 16

Nut BACN10YR3CD 16

Trim Grommet on assembly as

necessary

BACG20Z- 4

B000400

14 Install Grommet

Trim Grommet on assembly as

necessary

Adhesive BAC 5010 Type 82

Locate approximately as shown.

(a)

J2802 Relay Box 65C38484-30 1

Label

15 Install (New)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

16 Install Cover 65C38484-20

Refer to SOPM 20-50-10 as an

accepted procedure.

17 Identify J-BOX ASSEMBLY 65C38484-21

(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)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17-18, 30.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 6)

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387 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 2 OF 6)

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388 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

389 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

390 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
NOTE: Parts to rework the J-Box are available in the supplemental kit 65C37854-15. The kit possibly has more

parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Make sure and maintain the

edge margin for the holes

1 Locate Bracket 65C38484-19 1

J2802 Panel Assy 65C38484-16 1

2 Put/Hold Disconnect Bracket 287U0016-185 2

Close Ream Holes in accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable

0.1905-0.1895 Inch 4

DIA

3 Drill Holes

4 Remove Disconnect Bracket 287U0016-185 1

Bracket 65C38484-19 1

5 Locate Bracket 65C38484-18 1

J2802 Panel Assy 65C38484-16 1

6 Put/Hold Disconnect Bracket 287U0016-185 2

Close Ream Holes in accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable

0.1905-0.1895 Inch 4

DIA

7 Drill Holes

In accordance with 737-300

SRM 51-40-05, 737-400 SRM

51-40-05, or 737-500 SRM 51-

40-05 as applicable

0.229-0.218 Inch 1

DIA

8 Drill Hole

9 Remove Disconnect Bracket 287U0016-185 1

Bracket 65C38484-19 1

10 Deburr Bracket 65C38484-19 1

Bracket 65C38484-18 1

Disconnect Angle 287U0016-185 2

J2802 Panel 65C38484-16 1

0.010 - 0.015 Inch deep on the

inner side.

11 Countersink J2802 Panel 65C38484-16 4

Shave the rivet flush on the inner side of the panel12 Install Rivet BACR15BB6AD

FIGURE 95: ASSEMBLE THE J2802 BOX ASSEMBLY FOR AIRPLANES WITH AIRSTAIRS

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

In accordance with 737-300

SRM 51-40-02, 737-400 SRM

51-40-02, or 737-500 SRM 51-

40-02 as applicable

13 Install Screw BACS12HN3-8 16

Washer NAS1149D0316H 16

Nut BACN10YR3CD 16

Trim Grommet on assembly as

necessary

BACG20Z- 4

B000400

14 Install Grommet

Trim Grommet on assembly as

necessary

Adhesive BAC 5010 Type 82

Locate approximately as shown.

(a)

J2802 Relay Box 65C38484-30 1

Label

15 Install (New)

Refer to SOPM 20-44-01 as an

accepted procedure.

BAC5710, TYPE -

41

Apply Top Coat

16 Install Cover 65C38484-20

Refer to SOPM 20-50-10 as an

accepted procedure.

17 Identify J-BOX ASSEMBLY 65C38484-15

(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)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

392 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, 21-29, 31.

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

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 4)

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Original Issue: July 29, 2010

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393 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

394 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

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

AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 4)

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395 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Remove / Bolt BACS12HN3-8 6

Keep

1

Washer NAS1149F0363P 6

Cover 65C38484-20 1

Refer to SWPM 20-10-11 as an

accepted procedure.

2 Install Wires W1760, W1770 -

3 Install / Kept Cover 65C38484-20 1

Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

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

AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 4)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

396 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17-18, 30.

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

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 4)

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Original Issue: July 29, 2010

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397 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

398 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

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

AIRPLANES WITH AIRSTAIRS

(SHEET 3 OF 4)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

399 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Remove / Bolt BACS12HN3-8 6

Keep

1

Washer NAS1149F0363P 6

Cover 65C38484-20 1

Refer to SWPM 20-10-11 as an

accepted procedure.

2 Install Wires W1760, W1770 -

3 Install / Kept Cover 65C38484-20 1

Bolt BACS12HN3-8 6

Washer NAS1149F0363P 6

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

AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 4)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

400 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

401 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

402 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

403 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

FIGURE 98: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND E3 SUPPORT POST FOR

AIRPLANES WITH AIRSTAIRS

(SHEET 4 OF 5)

BOEING PROPRIETARY -

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

404 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

from E2 and E3 Support Posts

from area where the J2802 Box

Assy will be in contact with the

stanchions

1 Remove RIVET - 4

With clamps when the J-box is

level on the E2 and E3 support

posts.

KIT ASSY - J2802 65C38484-21 1

JBOX

2 Locate

Interference fit holes In accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable

0.187 - 0.190 Inch 2

Dia

3 Drill HOLE

Interference fit holes In accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable. (a)

0.161 - 0.164 Inch 4

Dia

4 Drill HOLE

In accordance with 737-300

SRM 51-40-05, 737-400 SRM

51-40-05, or 737-500 SRM 51-

40-05 as applicable

0.218 - 0.229 Inch 3

Dia

5 Drill HOLE

In accordance with 737-300

SRM 51-40-05, 737-400 SRM

51-40-05, or 737-500 SRM 51-

40-05 as applicable

0.128 - 0.135 Inch 2

Dia

6 Drill HOLE

KIT ASSY - J2802 65C38484-21 1

JBOX

7 Trim

Deburr

Refer to SOPM 20-43-03 as an

accepted procedure.

CHEMICAL CON- Typ 2, Class A -

VERSION COATING

8 Apply

Refer to SOPM 20-41-02 as an

accepted procedure.

Apply PRIMER BMS 10-11, Type 1 -

BMS 5-95, CLASS - (b)

B

9 Apply SEALANT

(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)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

405 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

406 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

407 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

408 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

FIGURE 99: DRILLING OF HOLES ON THE J2802 BOX ASSEMBLY AND 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

Revision 1 March 26, 2012 737-28A1216

409 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

from E2 and E3 Support Posts

from area where the J2802 Box

Assy will be in contact with the

stanchions

1 Remove RIVET - 4

With clamps when the J-box is

level on the E2 and E3 support

posts.

KIT ASSY - J2802 65C38484-15 1

JBOX

2 Locate

Interference fit holes In accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable

0.187 - 0.190 Inch 2

Dia

3 Drill HOLE

Interference fit holes In accordance with 737-300 SRM 51-40-

05, 737-400 SRM 51-40-05, or

737-500 SRM 51-40-05 as applicable. (a)

0.161 - 0.164 Inch 4

Dia

4 Drill HOLE

In accordance with 737-300

SRM 51-40-05, 737-400 SRM

51-40-05, or 737-500 SRM 51-

40-05 as applicable

0.218 - 0.229 Inch 3

Dia

5 Drill HOLE

In accordance with 737-300

SRM 51-40-05, 737-400 SRM

51-40-05, or 737-500 SRM 51-

40-05 as applicable

0.128 - 0.135 Inch 2

Dia

6 Drill HOLE

KIT ASSY - J2802 65C38484-15 1

JBOX

7 Trim

Deburr

Refer to SOPM 20-43-03 as an

accepted procedure.

CHEMICAL CON- Type 2, Class A -

VERSION COATING

8 Apply

Refer to SOPM 20-41-02 as an

accepted procedure.

Apply PRIMER BMS 10-11, Type 1 -

BMS 5-95, CLASS - (b)

B

9 Apply SEALANT

(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)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

410 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, 21-29, 31.

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

AIRPLANE WITH AIRSTAIRS

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

411 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

KIT ASSY - J2802 65C38484-21 1 From the support posts.

JBOX

1 Remove

Refer to SOPM 20-30-03 as an

accepted procedure.

2 Clean HOLE - 18

By abrasive cleaning for faying

surface bonding. (a)

3 Clean HOLE - 1

(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)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

412 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 17-18, 30.

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

AIRPLANES WITH AIRSTAIRS

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

413 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove J-BOX ASSEMBLY 65C38484-15 1 From the support posts.

Refer to SOPM 20-30-03 as an

accepted procedure.

2 Clean HOLE - 18

By abrasive cleaning for faying

surface bonding. (a)

3 Clean HOLE - 1

(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

Revision 1 March 26, 2012 737-28A1216

414 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

415 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: Parts are available in the supplemental kit 65C37854-15 for J-Boxes that have been reworked, or in

the new J-Box installation kit 65C38484-22. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank and J-box

faying surface. Refer to SOPM

20-50-19 and SWPM 20-20-00

as an acceptable procedures.

1 Apply SEALANT BMS5-95 -

2 Put J2802 JBOX 65C38484-21 -

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)

BOLT, PROTRUD- BACB30NX5HK3 4

ING HD

3 Install (New)

COLLAR, BACC30BH5 4

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.

BOLT, PROTRUD- BACB30NX6K3 2

ING HD

4 Install (New)

COLLAR, BACC30BH6 2

PRELOAD

On the bolt heads and fillet seal

the collars. Refer to SOPM 20-

50-19 as an acceptable procedure.

5 Apply SEALANT BMS5-95 -

(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)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

416 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This 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

Revision 1 March 26, 2012 737-28A1216

417 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: Parts are available in the supplemental kit 65C37854-15 for J-Boxes that have been reworked, or in

the new J-Box installation kit 65C38484-23. The kit possibly has more parts than necessary.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the bolt shank and J-box

faying surface. Refer to SOPM

20-50-19 and SWPM 20-20-00

as an acceptable procedures.

1 Apply SEALANT BMS5-95 -

2 Put J2802 JBOX 65C38484-15 -

In accordance with 737-300

SRM 51-40-02, 737-400 SRM

51-40-02, or 737-500 SRM 51-

40-02 as applicable.

BOLT, PROTRUD- BACB30NX5HK3 4

ING HD

3 Install (New)

COLLAR, BACC30BH5 4

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.

BOLT, PROTRUD- BACB30NX6K3 2

ING HD

4 Install (New)

COLLAR, BACC30BH6 2

PRELOAD

On the bolt heads and fillet seal

the collars. Refer to SOPM 20-

50-19 as an acceptable procedure.

5 Apply SEALANT BMS5-95 -

(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)

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Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

418 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, 17-18, 21-31.

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

(SHEET 1 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

419 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

420 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
FIGURE 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

Revision 1 March 26, 2012 737-28A1216

421 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

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

(SHEET 4 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

422 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

use a CLICO to locate the

Spacer Nut Plate to the existing

hole

NUT, SPACER BACN10TL3A10 2

PLATE

1 Locate

use a CLICO to locate the

Spacer Nut Plate to the existing

hole

NUT, SPACER BACN10TL3A12 2

PLATE

2 Locate

In accordance with 737-300

SRM 51-40-05, 737-400 SRM

51-40-05, or 737-500 SRM 51-

40-05 as applicable

0.128-0.135 Inch 4

DIA

3 Drill Hole

4 Install Rivet BACR15BB4D( )C

5 Install (New) CLAMP 287T0011-1 4

BOLT BACS12HN3-8 4

WASHER NAS1149D0316H 4

6 Install (New) CLAMP 287T0011-1 4

BOLT BACS12HN3-8 4

WASHER NAS1149D0316H 4

NUT BACN10YR3CD 4

BONDING BACJ40AB20-8 1 (b)

JUMPER

7 Install (New)

BOLT BACS12HN3-7 2

WASHER NAS1149D0316H 6

NUT BACN10YR3CD 2

Maximum resistance is 0.001

Ohms (1.0 milliohms) between

jumper faying surfaces. (a) (c)

ELECTRICAL BACJ40AB20-6 1

BONDING RESISTANCE

8 Measure

Maximum resistance is 3.5 milliohms between J2802 Box and

Stanchion. (a) (c)

ELECTRICAL - 1

BONDING RESISTANCE

9 Measure

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

10 Apply

Refer to SOPM 20-41-02 as an

accepted procedure.

BMS10-11, TYPE -

1

11 Apply PRIMER FINISH

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

(SHEET 5 OF 6)

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Original Issue: July 29, 2010

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423 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

On the support posts. Refer to

SOPM 20-41-02 as an accepted

procedure.

BMS10-11, TYPE -

2, COLOR WHITE

12 Apply ENAMEL FINISH

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) Refer to SWPM 20-20-10 as an accepted procedure. 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

Revision 1 March 26, 2012 737-28A1216

424 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
This Figure applies only to: Group 14, 17-18, 21-31.

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

AIRSTAIRS

(SHEET 1 OF 6)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

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425 of 434

BOEING SERVICE BULLETIN 737-28A1216

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

AIRSTAIRS

(SHEET 2 OF 6)

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BOEING SERVICE BULLETIN 737-28A1216

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

AIRSTAIRS

(SHEET 3 OF 6)

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

AIRSTAIRS

(SHEET 4 OF 6)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

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BOEING SERVICE BULLETIN 737-28A1216

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

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

AIRSTAIRS

(SHEET 5 OF 6)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Loosen CLAMPS 287T0011-1 4

To make a drip loop below the

J2802 box assembly.

2 Adjust WIRE BUNDLE W1764 1

To make a drip loop below the

J2802 box assembly.

3 Adjust WIRE BUNDLE W1764 1

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

AIRSTAIRS

(SHEET 6 OF 6)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

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BOEING SERVICE BULLETIN 737-28A1216

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This Figure applies only to: Group 14, 21-29, 31.

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

AIRSTAIRS

(SHEET 1 OF 2)

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Original Issue: July 29, 2010

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431 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: Parts are in the kit 65C38484-8 if the J-Box has been reworked, or in 65C38484-22 if a new kit is used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Cover 65C38484-20 1

Refer to SWPM 20-81-22 as an

accepted procedure.

TDH-1852-1502 or 2

TDH1852-1502

2 Install Relay

3 Install Cover 65C38484-20 1

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

AIRSTAIRS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 737-28A1216

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This Figure applies only to: Group 17-18, 30.

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

AIRSTAIRS

(SHEET 1 OF 2)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

Revision 1 March 26, 2012 737-28A1216

433 of 434

BOEING SERVICE BULLETIN 737-28A1216

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for one airplane.

NOTE: Parts are in the kit 65C38484-9 if the J-Box has been reworked, or in 65C38484-23 if a new kit is used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove Cover 65C38484-20 1

Refer to SWPM 20-81-22 as an

accepted procedure.

TDH-1852-1502 or 4

TDH1852-1502

2 Install Relay

3 Install Cover 65C38484-20 1

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

AIRSTAIRS

(SHEET 2 OF 2)

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 29, 2010

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434 of 434

BOEING SERVICE BULLETIN 737-28A1216

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