August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 204

ALERT ALERT

Commercial

Airplane

Group 737

ALERT ALERT

Service Bulletin

Number: 737-28A1227

Date: August 02, 2010

ATA System: 2822

SUBJECT: FUEL - Distribution - Center and Auxiliary Tank Boost Pumps Fuel Control System UnCommanded On Relay Installation and Related Wiring Changes

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2010 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable 

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third 

parties. Treatment of the document and the information it contains is governed by contract with Boeing. For 

more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

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 Table of Contents

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Table of Contents

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 55

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 56

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 56

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 56

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 66

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 67

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

FIGURE 1: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION . . . . . . . . . . 102

FIGURE 2: WIRE BUNDLE W1760 AND W1770 IN THE J2802 BOX ASSEMBLY - INSTALLATION . 104

FIGURE 3: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION . . . . . . . . . . 105

FIGURE 4: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION . . . . . . . . . . 108

FIGURE 5: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION . . . . . . . . . . 111

FIGURE 6: WIRE BUNDLE W1760 AND W1770 IN THE J2802 BOX ASSEMBLY - INSTALLATION . 113

FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION . . . . . . . . . . 114

FIGURE 8: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION . . . . . . . . . . 118

FIGURE 9: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO

J2802 BOX ASSEMBLY - ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . . 122

FIGURE 10: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANELS TO J2802 BOX

ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 127
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FIGURE 11: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX

ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 129

FIGURE 12: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO

J2802 BOX ASSEMBLY - ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . 131

FIGURE 13: WIRE BUNDLE W0368 AND W1764 FROM DISCONNECT PANEL A TO J2802 BOX

ASSEMBLY - WIRING CHANGES . . . . . . . . . . . . . . . . . . . . . . . . . . . 136

FIGURE 14: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX

ASSEMBLY - WIRING CHANGES . . . . . . . . . . . . . . . . . . . . . . . . . . . 138

FIGURE 15: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO

J2802 BOX ASSEMBLY - ROUTING . . . . . . . . . . . . . . . . . . . . . . . . . . 140

FIGURE 16: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX

ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 145

FIGURE 17: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX

ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . 147

FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6

DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING . . . . . . . . . . . 149

FIGURE 19: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 154

FIGURE 20: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 158

FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6

DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING . . . . . . . . . . . 162

FIGURE 22: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 170

FIGURE 23: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 174

FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6

DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING . . . . . . . . . . . 178

FIGURE 25: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 183

FIGURE 26: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 187

FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6

DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING . . . . . . . . . . . 191

FIGURE 28: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 196

FIGURE 29: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802

BOX ASSEMBLY - WIRING CHANGE . . . . . . . . . . . . . . . . . . . . . . . . . 200

FIGURE 30: J2802 BOX ASSEMBLY - CLOSE ACCESS . . . . . . . . . . . . . . . . . . . . . . . 204
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ALERT ALERT

Commercial

Airplanes 737

ALERT ALERT

Service Bulletin

Number: 737-28A1227 Summary

Original Issue: August 02, 2010

ATA System: 2822

SUBJECT: FUEL - Distribution - Center and Auxiliary Tank Boost Pumps Fuel Control System UnCommanded On Relay Installation and Related Wiring Changes

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 affects the 737-200/-200C/-300/-400/-500 airplanes with line numbers 292 thru 3132 that 

have center and auxiliary fuel tanks. Operators with 737-100/-200/-200C airplanes with line numbers 1 thru 291 

that have center and auxiliary fuel tanks should contact Boeing to obtain engineering and accomplishment 

instructions for this modification. This service bulletin is sent to give ’un-commanded on’ protection for the fuel 

pump control system. Instructions are given to add one more relay, as a fail safe, for each fuel pump in the center 

and auxiliary fuel tanks. If this service bulletin is not done, the fuel pumps could run dry, which increases the 

pumps temperature and could cause an ignition source for fuel vapor in the fuel tank. Ignition of the flammable 

fuel vapors in the fuel tanks, could cause a fire or explosion which will put the airplane in an unsafe condition.

The Boeing system safety assessment necessary for Special Federal Aviation Regulation (SFAR) 88, showed 

that electrical faults within the fuel tank pump system can cause a fuel pump to operate when the fuel pump 

switch is in the ’OFF’ position. Boeing has developed a new system to prevent extended operation of the fuel 

tank boost pumps in this condition. This new system has a second relay to prevent the operation of a pump when 

its switch is in the ’OFF’ position. The auto shutdown relay currently installed for each pump gives the same 

solution as the new additional relay, but is known to have caused in-service problems because its contacts have 

’welded’ closed and continued to let power be supplied. This condition is referred to as ’un-commanded on’ 

(UCO) pump operation. This new second relay added to the existing fuel control circuit and interfaced with the 

P5-2 fuel control module, prevents UCO operation of the fuel boost pumps. The system senses if there is a 

voltage remaining in the fuel boost pump circuit and activates the UCO relay to remove the power. In the flight 

deck, the pump low pressure light in the P5-2 fuel systems module, and master caution light come on when the 

fuel pump is at low pressure. No additional indication is provided for dry running pumps.
 

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Accomplishment of this service bulletin installs new UCO relays and toggle switches in the J2802 box assembly 

located in the Electronic Equipment Bay (E/E bay). This service bulletin also changes and adds new wire 

bundles that route from the J2802 box assembly to the P5 Forward Overhead Panel and the P6 Disconnect 

Panels. Installation of the new UCO relays for each pump will prevent "dry running" of the fuel pumps and reduce 

the risk of fuel tank fire or explosion.

New Airworthiness Limitations (AWL) 28-AWL-24 (Center Tank) and 28-AWL-25 (Auxiliary Fuel Tank) for 737-

200 airplanes and AWL 28-AWL-23 (Center Tank) and 28-AWL-24 (Auxiliary Fuel Tank) for 737-300/-400/-500 

airplanes will be added to section 9 of the Maintenance Planning Data (MPD) to include a functional check of 

the center fuel pumps and (auxiliary tank pumps for applicable airplanes) primary and secondary control relays.

Boeing Fleet Team Digest (FTD) 737 FTD 28-04004 is related to this service bulletin.

ACTION (PRR 35443-RS)

Remove equipment as necessary to get access the J2802 box assembly on the E2 and E3 support posts in the 

E/E bay, P6 Load Control Center in the flight compartment/control cabin, and P6 disconnect panels. Remove 

the cover from the J2802 box assembly and install wire bundles W1760 and W1770 and relays. Change wire 

bundles W036, W368, W386, W1034, W1046, W1764 and W1774, as applicable, between the P6 disconnect 

panels and J2802 box assembly. Check the continuity of all the new and changed wires and do a functional test 

to make sure the changed fuel control system operates correctly.

Operators with Group 1 airplanes should contact Boeing to obtain engineering and accomplishment instructions 

for this modification. 

EFFECTIVITY

737-100/200/200C/300/400/500 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

COMPLIANCE

Boeing recommends that the change given in this service bulletin be done within 60 months after the original 

issue date of 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.

Operators with Group 1 airplanes should contact Boeing to obtain engineering and accomplishment instructions 

for this modification. 

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.
 

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

CHANGE WIRE BUNDLES

W1764/W1774

CHANGE WIRE BUNDLES

W0368/W0386

INSTALL NEW TOGGLE

SWITCHES, RELAYS AND WIRE

BUNDLES W1760 AND W1770 IN

THE J2802 BOX ASSEMBLY

CHANGE WIRE BUNDLES

W0386/W1034/W1046/W1764/W1774

1308568
 

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ALERT ALERT

Commercial

Airplanes 737

ALERT ALERT

Service Bulletin

Number: 737-28A1227

Original Issue: August 02, 2010

ATA System: 2822

SUBJECT: FUEL - Distribution - Center and Auxiliary Tank Boost Pumps Fuel Control System 

Un-Commanded On Relay Installation and Related Wiring Changes

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

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

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. Refer to PRR 35443-RS for data about this 

change

GROUP CONFIGURATION DESCRIPTION

1 - 737-100/200/200C airplanes, that have a center 

tank but do not have a auxiliary tank, with a 

unique wiring configuration.

2 - 737-200/200C airplanes, that have a center tank 

but do not have an auxiliary tank, with a unique 

wiring configuration.

3 - 737-300/400/500 airplanes, that have a center 

tank but do not have an auxiliary tank.

4 - 737-200/200C airplanes, that have a center tank 

but do not have an auxiliary tank, with a unique 

wiring configuration.

5 - 737-300 airplanes, that have a center tank and 

an auxiliary tank (or provisions for an auxiliary 

tank).
 

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Airplane models:

737-100 737-200 737-200C 737-300

737-400 737-500

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

A.P.S. TRADING SERV S.R.L (PSV)

2 PL019

AAR A/C ENG. SALES & LEASING (AFD)

3 PQ116

ADC AIRLINES (ADN)

2 PK462 PN034

4 PJ118–PJ119

AEGEAN AIRLINES S.A. (CRM)

3 PS608 PW002 PW046 PW053

PW157 PW261 PW276 PW289

PW502 PW564

AERCAP B.V. (DEA)

3 PW249

AERGO CAPITAL LIMITED (CLJ)

2 PK528 PK802 PK901 PK903

PK915 PK922 PK974

3 PP935

AERO CONTRACTORS OF NIGERIA (NCC)

3 PQ194 PQ196 PT396 PT401

PT420–PT421 PT430–PT431 PT433 PV031

PV041

AERO CONTROLS (AEO)

1 PG312 PG629

AEROFLOT - CARGO (CGB)

3 PP825–PP826

6 - 737-400 airplanes, that have a center tank and 

an auxiliary tank (or provisions for an auxiliary 

tank).

7 - 737-200 airplanes, that have a center tank and 

an auxiliary tank (or provisions for an auxiliary 

tank), with a unique wiring configuration.

8 - 737-200 airplanes, that have a center tank and 

an auxiliary tank (or provisions for an auxiliary 

tank), with a unique wiring configuration.

GROUP CONFIGURATION DESCRIPTION
 

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AEROFLOT-DON (DAU)

3 PT507–PT508 PT513–PT514 PT701–PT703

AEROFLOT-NORD (CJS)

3 PR044 PT022 PT050–PT051 PT054

PT056–PT057 PT147–PT148 PT182–PT184

AEROGAL/GALAPAGOS AIRLINES (ERG)

2 PK715 PL102 PL110 PL171

PL624–PL625 PN030 PN405

3 PP946 PQ226 PQ243

4 PK827

AEROLINEAS ARGENTINAS (ARG)

1 PH705–PH708 PH742

2 PG584–PG585 PK102–PK103 PK735–PK737 PK740

PK747 PK750–PK751 PK755 PK757

PK761 PK765 PN104 PN110

PN112–PN113

3 PT023 PT042 PT044–PT045 PT047

PT101–PT102 PT212 PT214 PT220

PT303–PT306 PT309 PT509–PT510

AEROLINEAS AUSTRAL CHILE S.A. (LUT)

2 PK745 PL405 PN103

7 PM141–PM142

AEROSERVICE (SRI)

2 PL742–PL743

AEROSUCRE (SUS)

1 PY341

2 PY201 PY451

AEROSUR (REO)

2 PK594 PK713–PK714 PK716

AEROSVIT (UKA)

2 PK564

3 PP924 PQ284 PQ286 PT138

PT614–PT615 PW039 PW265 PW268

PW591–PW592 PW595–PW596

AEROVISTA GULF EXPRESS (GXP)

2 PK861–PK863 PY621

AIR ALGERIE (ALG)

2 PK633–PK634 PL722 PL724 PY051

PY053

AIR AUSTRAL (AUX)

3 PS621 PT215
 

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AIR CANADA (ACN)

2 PK679–PK680

AIR CARRIER ACCESSORY SERVICE (RCY)

2 PN085

AIR CHINA (BEJ)

3 PQ345–PQ346 PQ361–PQ364 PQ373 PQ438

PQ447 PQ971 PQ975

5 PS957

AIR CHINA INNER MONGOLIAN (IML)

3 PQ365–PQ366 PQ370 PQ372 PQ988

PQ990 PS614–PS617

AIR CHINA SOUTHWEST BRANCH (XIN)

3 PP632–PP633 PQ401–PQ406 PQ408–PQ410 PS811

AIR CHINA TIANJIN BRANCH (TJA)

3 PQ367–PQ369 PQ371

AIR CORRIDOR (KRD)

2 PK468 PK749

AIR DO (HIA)

3 PT874

AIR DOMINICANA (DMA)

3 PP894

AIR GUINEE (GNE)

2 PN456 PY651

AIR HORIZONS (AHZ)

1 PY004

AIR INDIA (IND)

2 PK237–PK240 PM001–PM006 PY631

AIR INUIT (AIU)

2 PY243

AIR ITALY (RIT)

3 PP393 PP903

AIR MADAGASCAR (MAD)

3 PP852 PQ297 PQ299

AIR MALAWI (AML)

3 PS602 PT397

AIR MEDITERRANEE (AMV)

1 PG028–PG029 PY301
 

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AIR NAMIBIA (NAM)

3 PT503–PT504

AIR NEW ZEALAND (ANZ)

3 PQ997 PR041 PR062–PR066 PR077–PR080

PS873–PS874

5 PS866–PS868

AIR NIPPON (ANK)

3 PJ817 PT053 PT060 PT063–PT064

PT126 PT128–PT131 PT871–PT873 PT875–PT886

AIR NORTH YUKON'S AIRLINE (AND)

2 PK596 PK599 PY592

AIR ONE (ADH)

2 PK432 PK933 PK938

3 PQ228–PQ229 PR021–PR022 PV228 PV232–PV234

PV236–PV237 PV301 PW041 PW043

PW052 PW054 PW287 PW290

AIR PHILIPPINES (PHP)

1 PG001 PG039 PG061–PG062 PG066

2 PK099 PK541–PK542 PN021–PN022 PN025

PN029 PN031 PN038 PN417–PN418

AIR SLOVAKIA (SLO)

2 PK936

3 PP851 PP866 PP869

AIR TANZANIA (TNZ)

2 PN411 PN413 PY611

AIR ZIMBABWE (ZMB)

2 PN431–PN433

AIRASIA BERHAD (ASW)

3 PM385 PM388 PM390 PM397

PP002 PP021 PP406–PP409 PP848

PP920 PQ184 PQ332 PQ448

5 PP471 PP516–PP517

AIRBALTIC CORPORATION (BCB)

3 PR015–PR017 PR162 PR164 PS624

PT005 PT161–PT163 PT424–PT425 PT428–PT429

PU311 PU313

AIRCRAFT MAINTENANCE CORP. (AMF)

2 PK254

AIRFAST INDONESIA (PTF)

2 PN481
 

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ALERT ALERT

AIRLINE CAPITAL LEASING, INC. (VTI)

7 PJ009

AIRTRAN AIRWAYS (CQT)

2 PK697

AIRWORK NZ (ANX)

2 PY741

3 PP028 PP039–PP040 PQ242

ALASKA AIRLINES (ASA)

3 PJ301–PJ302 PJ601–PJ615 PW116 PW231–PW248

PW250–PW252

ALOHA AIR CARGO (HLH)

2 PY131 PY463 PY593–PY594 PY721

ALTER BAIL AVIATION (ABH)

2 PK215

7 PK359

AMERICA WEST AIRLINES (AMW)

3 PP199 PS666–PS667

AMERICAN FALCON AIR (FAK)

2 PL026

AMERISTAR AIR CARGO (CGG)

1 PY345–PY346

2 PK221 PK560 PM051

APOLLO AVIATION GROUP LLC (APV)

3 PP234 PP419 PP421

ARIK AIR (AKD)

3 PQ154 PQ161

ASIA AIRLINES (YDO)

1 PY005

2 PL020 PY135

ASIANA AIRLINES (AAR)

3 PT851–PT853 PV204–PV206 PV208 PV227

PW283 PW286

ASTRAEUS, LTD. (AUA)

3 PP929 PS605

ATA ATLANTICO TRANSPORTE AEREO (AUI)

1 PY322 PY361

ATLANT-SOYUZ (AYZ)

3 PP233 PP239
 

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ALERT ALERT

ATLANTIC AIRLINES (LNL)

2 PK673 PL008 PL622–PL623

ATLANTIC AIRLINES LTD (YDG)

3 PP724

ATLAS BLUE (ABT)

3 PT581 PW631–PW636

AURELA (URE)

3 PQ233 PQ307

AURORA AVIATION (AGX)

3 PP420 PQ287

AUSTRAL - CIELOS DEL SUR (ALA)

2 PN111 PN114–PN115 PN117

AUTOMATIC LLC (AUM)

2 PK759–PK760 PK764

AVE.COM (PHX)

1 PG579

2 PK213 PM252

3 PP892

4 PK823 PK826

AVIACSA AEROEXO (AEJ)

2 PK211 PK216–PK219 PK598 PK625–PK626

PM181 PN154–PN155 PN401–PN404

3 PP422–PP423 PP425

7 PK609 PM101–PM102 PM104–PM107 PM114–PM119

AVIATION CAPITAL GROUP (CGP)

3 PP381 PW020

AVIATION CONSULTANTS (ACT)

1 PG037 PY001

AVIATION TECHNOLOGIES, INC. (VTT)

2 PL626

AVIOGENEX (AVG)

2 PN501

AVIOR (AWD)

2 PK549 PK591 PM052 PM058

PN133–PN134 PN137 PN139 PN144

PN147–PN148 PN153 PN159

AVOLAR (AOL)

3 PP231–PP232 PP679 PP682
 

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ALERT ALERT

AVSTAR (VSV)

2 PK355 PL111

AWAS (AWW)

3 PT213 PT216

BAHAMASAIR (BAH)

2 PK672

8 PL501 PL506

BASIC CAPITAL MANAGEMENT (BCM)

2 PN455

BATAVIA AIR (BTV)

2 PK252 PK283–PK284 PK305 PK514–PK515

PK563 PK617 PK622 PK635

PK711–PK712 PL413

3 PJ558 PP003–PP004 PP006 PP008

PP017–PP020 PP917 PP921 PS631

PW005 PW015 PW032 PW156

PW575

4 PJ107 PJ112 PK825

7 PK360

BAVARIA (BAV)

3 PP981–PP982 PP984

BAYU INDONESIA AIR (BAY)

2 PK561

BCI AIRCRAFT LEASING (BLI)

2 PN131 PN136 PN138 PN142–PN143

PY112 PY134 PY462

3 PP237–PP238

BELAVIA (ITU)

3 PQ472 PT722 PT971–PT973

BELLVIEW AIRLINES (BEB)

2 PK203 PK612 PL028

7 PK872

BLUE AIR (BTR)

3 PQ026 PQ160 PS618 PW741

PW831

BLUE DART AVIATION (BDA)

2 PK231–PK232 PL451 PM281

7 PN521

BLUE PANORAMA AIRLINES (BPA)

3 PR025–PR026 PW284

6 PW518–PW519
 

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ALERT ALERT

BLUEBIRD CARGO (BLS)

3 PM383 PQ342–PQ344

6 PW524 PW530

BMI BRITISH MIDLAND (BMA)

3 PQ291–PQ292 PQ431 PQ433–PQ435 PQ454

PQ974 PQ992 PQ996 PR012

PR043 PS625 PS971 PT186–PT188

5 PP520 PS861 PS956

BOA (BOV)

3 PS604

BOEING (TBC)

1 PG051 PG215

BOEING CAPITAL CORPORATION (ZMF)

3 PP162 PQ792

BOURAQ AIRLINES (PTB)

2 PK501 PK913 PK918–PK920 PK931

BRANSON AIR (PTY) LTD (BSL)

2 PL025

7 PK874

BRITISH AIRWAYS (BAB)

3 PM399 PP841–PP842 PQ283 PQ305

PT009 PT021 PT185 PT295

PT307–PT308 PT515–PT516 PW301–PW302 PW305–PW308

PW312 PW314–PW315 PW317–PW327

BRUSSELS AIRLINES (EBA)

3 PQ984 PQ989 PQ993 PS656

PS972 PW013 PW264 PW271

PW275 PW571–PW572

BULGARIA AIR (BLD)

3 PQ086–PQ087 PQ190 PQ262 PT170

PT211 PT427 PT437

5 PP503

BURAQ AIR (BQA)

2 PL723 PL725

C.I.T. LEASING CORPORATION (TCI)

3 PP043 PP836 PP965 PW562

CANADIAN NORTH (ANP)

2 PK681 PL415 PN132 PN492

PY152–PY154 PY422 PY441
 

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ALERT ALERT

CANJET (CNJ)

3 PQ231

CAPITAL AIRCRAFT (CPT)

2 PK464

CAPITAL AIRWAYS LLC (CPY)

3 PP404

CARDIG AIR (CGD)

1 PY343

3 PP241–PP242

CARGO AIR (CGE)

3 PP410

CASBAH AG AVIATION DIVISION (BHV)

2 PL581

CAYMAN AIRWAYS (CAY)

2 PK753 PY244

3 PQ293 PQ347–PQ348 PQ481

CENTRALWINGS (CLW)

3 PW106 PW267

CHANCHANGI AIRLINES (CGI)

2 PL416–PL417 PN083–PN084 PN086

7 PL412

CHARTER AIR (FIH)

3 PS630 PS871

CHILEAN AIR FORCE (CHF)

3 PQ053 PT996

CHINA EASTERN AIRLINES (CEA)

3 PQ263 PQ411–PQ412 PQ414–PQ418 PQ977

PQ979 PQ981 PR141–PR143 PS622–PS623

PS628

CHINA EASTERN AIRLINES WUHAN (WUH)

3 PQ491–PQ492 PR081–PR082 PR131

CHINA POSTAL AIRLINES (YIH)

3 PM407–PM409 PQ295–PQ296 PQ471 PQ493

CHINA SOUTHERN AIRLINES (GUN)

3 PM412 PM541–PM544 PM547 PM549

PQ252–PQ255 PQ407 PQ479–PQ480 PR121–PR122

PS836–PS837 PS841–PS846 PT061–PT062
 

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CHINA UNITED AIRLINES (CUL)

3 PP728–PP729 PS609–PS610 PS896–PS897

CHINA XINHUA AIRLINES (XIH)

3 PM546 PQ264 PQ804–PQ805 PR001

PS856 PW852–PW854

CHINA XINJIANG AIRLINES (XIJ)

3 PM545 PM548

CIRRUS ME S.A.L (CMU)

7 PM103

CIS AIR HOLDINGS (CIS)

1 PG217

CITYLINE HUNGARY LTD. (CTZ)

2 PY101

COMAIR LIMITED (CML)

2 PK734 PK738 PK744 PK748

PK754 PK758

3 PP915 PP923 PQ001 PQ003–PQ006

PQ008 PQ010 PW111–PW112 PW115

PW118 PW216 PW303 PW310–PW311

PW556

CONOCOPHILLIPS ALASKA, INC. (ATR)

2 PN452–PN453

CONTINENTAL AIRLINES (CAL)

3 PP671–PP675 PP678 PP680–PP681 PP683

PP688–PP689 PP695–PP699 PP701 PP703–PP706

PP717–PP723 PP725–PP726 PP730 PP732–PP733

PT801–PT824 PT826–PT834 PT901–PT905 PT907–PT918

PT921 PT924 PT926 PT929–PT930

5 PP690–PP694 PP707–PP710 PP712–PP716

CONVIASA S.A. (VSS)

2 PL005 PL010

3 PQ117

CORENDON AIRLINES (HVA)

3 PQ451 PW282 PW285

CSA (CSA)

3 PJ816 PT617–PT621 PT981–PT985 PV302

PW304 PW309 PW431–PW435

6 PW517

CSC TRANSPORT (CTC)

3 PW007
 

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ALERT ALERT

DAIMLERCHRYSLER AVIATION (DCY)

3 PP119–PP120

DBA (DBA)

3 PP961 PS655

5 PP511 PP515

DELTA AIR LINES (DAL)

2 PN149 PN161 PN415

3 PP240 PP243

DELTA CONNECTION (DTC)

2 PY272

DNIPROAVIA (DNE)

3 PT041 PT133–PT134 PW031

5 PP510

DODSON AVIATION (DOO)

1 PJ032

DOLPHIN AIR (FDN)

2 PL151 PY241

DONGHAI AIRLINES (JWC)

3 PM396 PM405 PP651–PP652

EARTH AIRLINES (ETL)

1 PG352

EAST AFRICAN AIRLINES (EAB)

2 PL023

EASTOK AVIA (ETK)

2 PK632 PN407–PN408 PN410 PN416

PN493

3 PP034 PP440 PV023 PW011

EDREES AVIATION (SME)

8 PL505

EG&G TECHNICAL SERVICES (EGN)

2 PL763

7 PJ205 PJ207–PJ210

EGYPTAIR (EGP)

1 PG026

3 PT561 PT563–PT565

ESEN AIR LTD. (ESN)

2 PK317 PL729
 

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ALERT ALERT

ESTAFETA (EST)

2 PY275

3 PP833 PP846 PQ224–PQ225

ESTONIAN AIR (ENA)

3 PQ994 PR045 PT136 PT716–PT717

PU312

ETHIOPIAN AIRLINES (ETH)

2 PN512

EUROPE AIRPOST (EUE)

3 PP392 PP832 PP925 PP947

PP951–PP952 PQ421 PQ771–PQ772 PR096

PR163 PR166 PS607 PS641–PS644

EUROPEAN AVIATION AIR CHARTER (EUL)

2 PK041 PK044 PK046 PK048–PK049

PY273

7 PN001

EUROPEAN CAPITAL HOLDINGS (ECC)

1 PY003 PY321

2 PJ006 PK524–PK525 PK641–PK642

EXECUTIVE JET AIRCRAFT COMPANY (EXF)

2 PL441

EXPORT RESTRICTED AIRPLANES (YWV)

1 PA002 PG021 PG041 PG074

PG218–PG219 PG224 PG305 PG308

PG310–PG311 PG574 PH731 PJ002

PJ102 PY021

2 PJ003 PK214 PK391 PL758

PY022 PY141–PY142

3 PQ288–PQ289

EXPRESSAIR (PTX)

2 PK304 PM022

FAA (FAA)

2 PL768

FACTS AIR (FAD)

1 PX701

FASCO AIRWAYS (EAO)

1 PG228

FEDERATIVE REPUBLIC OF BRAZIL (BRZ)

7 PK068–PK069
 

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ALERT ALERT

FIRST AIR (BRS)

2 PL407 PY133 PY281 PY410

PY421

7 PK358

FLAIR AIRLINES (FLR)

3 PW503

FLANA (FLQ)

2 PY270

FLYGLOBESPAN.COM (FGS)

3 PS962–PS963

FLYING CARPET (FYC)

2 PM064 PN140

FRESH AIR LTD. (FRR)

2 PN024 PN035

FUTURA (FUA)

3 PP430 PP432 PP899 PV032

PW034 PW047–PW048 PW101 PW266

PW561

GA TELESIS, LLC (GTG)

2 PK739

GARUDA INDONESIA (GIA)

3 PM404 PQ285 PQ487 PQ986–PQ987

PR061 PR068–PR072 PR091–PR092 PS653

PT681–PT685 PV271 PW067 PW119

PW443–PW450 PW461–PW467 PW525 PW712

PW851

5 PP508 PP514

GARY AIRCRAFT (GRH)

2 PL745

GE AVIATION MATERIALS (GML)

3 PP001

GECAS (GEF)

1 PG220–PG221 PG651–PG652

2 PK026–PK027 PK256 PK466–PK467

3 PM398 PM410–PM411 PP235–PP236 PP840

PW001 PW009 PW012 PW018–PW019

PW021
 

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ALERT ALERT

GENERIC CUSTOMER/SUPPLIER (XXX)

1 PG307 PG375

2 PH743 PJ005 PK029 PK253

PK274 PK286 PK318 PK495

PK519 PK801 PK803–PK804 PK934

PL107 PL112 PL740–PL741 PL793

PM253 PY411

3 PP031 PP046 PP431 PP436–PP438

PP905 PP936 PW526

4 PJ110–PJ111 PK821

7 PK503

GEORGIAN AIRWAYS (GEI)

3 PP044 PT181 PT611 PW262

GERMANIA (GER)

3 PP838 PQ119 PQ152 PQ230

PQ234–PQ235

5 PP507

GLOBAL AIR (YCH)

2 PJ004 PK145 PK548 PK595

PL013

GOL AIRLINES (GOT)

3 PP922 PP988–PP990 PQ120 PQ143–PQ145

PQ158 PQ162–PQ163 PQ191 PQ193

PQ195 PQ227 PQ303

HAINAN AIRLINES (HNA)

3 PQ088–PQ091 PQ156–PQ157 PQ473–PQ475 PR005

PR010 PS611 PS613 PS976–PS978

PV203 PV356–PV357 PW086–PW088 PW093

HAMBURG INTERNATIONAL (HAU)

3 PP904

HEMUS AIR (HEU)

3 PQ331

HEWA BORA AIRWAYS (EXD)

1 PG274

HOLA AIRLINES (HLB)

3 PP911–PP912 PQ304 PW006

ICARO (IKA)

2 PK742 PK771 PY461

IDM CAS (IDN)

2 PK552
 

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ALERT ALERT

INDIAN AIR FORCE (IDF)

1 PH712–PH713

2 PM016–PM017

INTAL AIR (IRT)

2 PK312 PY242 PY274

INTERAIR (ITI)

2 PK546 PL108 PL113 PY046–PY047

INTERLINK AIRLINES (ILK)

2 PK743 PK904 PK907 PL103

INTERNATIONAL AIR LEASES (IAL)

1 PL803

INTERNATIONAL AIR PARTS (IAO)

1 PG580

INTERNATIONAL TRANSPORT (YIT)

1 PG304

ION TIRIAC AIR (ION)

5 PS862

ISRAEL AEROSPACE INDUSTRIES (IAI)

1 PG575

2 PK692

JAL INTERNATIONAL (JAL)

3 PW411–PW418

JANCO AIRCRAFT AND ENGINES (JNC)

2 PM282–PM283

JAPAN TRANSOCEAN AIR (SWL)

3 PW401–PW408 PW681–PW683

6 PW515–PW516 PW520–PW521

JAT YUGOSLAV AIRLINES (JAT)

3 PP771–PP779 PQ241 PV024

JATAYU AIR (JAJ)

1 PG068

2 PK511 PK937

4 PJ117

7 PK257

JET AIRWAYS (JPL)

3 PW215 PW421–PW424

JET LITE (JPQ)

3 PQ306 PW064 PW066 PW273
 

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ALERT ALERT

JET MIDWEST (JMI)

2 PK558 PM057 PM066

JET TIME (JME)

3 PM384 PM391 PP897

5 PP504

JET2.COM LTD (CEX)

3 PP908–PP909 PP913–PP914 PQ027 PQ030–PQ039

PQ051–PQ052 PQ054–PQ055 PQ058–PQ059

JET4YOU.COM (JFU)

3 PW661–PW662

6 PW511

JETAIRFLY (TLB)

3 PT103

6 PJ811 PW522

JETCONNECT LIMITED (JCL)

3 PQ012–PQ016 PW540 PW542–PW543

JETLEASE (JLI)

2 PY595

JETRAN INTERNATIONAL, LTD. (JTI)

2 PK593

4 PK601 PK605

JETSCAPE LEASING (IAN)

3 PQ281 PW008 PW091

JETSTAR AIRCRAFT SALES (JTS)

1 PG306

JETSTAR PACIFIC AIRLINES (PAH)

3 PJ556 PJ559 PW102 PW272

PW316

JORDAN AVIATION (JOR)

3 PP896 PQ123–PQ124 PQ187 PT671

PW528

JSC "AIRCOMPANY SCAT" (DVW)

3 PT435

JSC STARLINE.KZ (MZK)

2 PK911 PL556

KARTHAGO AIRLINES (KAG)

3 PP926 PP928 PP930 PQ180

PQ432 PR029
 

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ALERT ALERT

KARTIKA AIRLINES (KRK)

2 PK309–PK310

KD AVIA (JSK)

3 PP016 PP196 PP305 PP383

PP418 PP424 PP426 PP429

PP801 PP837 PP843–PP844 PP867

PP870 PP916 PQ232 PQ302

PS652

5 PP475

KENYA AIRWAYS (KEN)

3 PR031–PR034

KLM - ROYAL DUTCH AIRLINES (KLM)

3 PP861 PP863–PP864 PP868 PP871–PP877

PW014 PW017 PW611–PW619 PW621–PW622

KRASAIR (ZXD)

3 PP962 PP967

LAC (CQC)

2 PY113

LAM (LAM)

2 PL455–PL456 PN451 PN454

LAN AIRLINES (LAN)

1 PJ104

2 PK431 PK775 PK909–PK910 PK912

PK914 PK916

LAPA ARGENTINA (LAZ)

2 PK051

LAS VEGAS SANDS, CORP. (LVS)

3 PQ236

5 PP506

LIBYAN AIRLINES (LAA)

2 PK361

LINEAS AEREAS AZTECA (AZX)

3 PP983 PP986

LION AIR (MLI)

3 PP181–PP182 PW016 PW022–PW023 PW025

PW029 PW037–PW038 PW042 PW501

LITHUANIAN AIRLINES (LIJ)

3 PQ189 PQ192 PQ237 PT169

PT426 PT434 PT438 PT721
 

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ALERT ALERT

LJH AVIATION MANAGEMENT (WAT)

2 PL006

LOBAYE AIRWAYS (LBY)

2 PN409

LOCALEASE (LLA)

2 PK282

LOCKHEED MARTIN (LMA)

3 PQ057

LOGISTIC AIR, INC. (LGA)

1 PY303–PY304

LORENA AIR (LRN)

3 PQ951

LOT POLISH AIRLINES (LOT)

3 PQ978 PQ980 PS973 PT651–PT656

PV281–PV287 PW065

LUFTHANSA GERMAN AIRLINES (DLH)

3 PQ060–PQ085 PQ092 PS701–PS706 PT331–PT360

LUXAIR (LUX)

3 PT672

MACEDONIAN AIRLINES, MACEDONIA (MCC)

3 PT612–PT613

MACQUARIE AIR FINANCE (ZGT)

3 PP022 PW504

MAGNICHARTERS (MAM)

2 PK143 PL454 PL554 PL558

3 PP405 PQ028 PQ168

MALAYSIA AIRLINES (MAS)

3 PJ551–PJ553 PJ555 PJ557 PJ560–PJ561

PW044 PW201–PW214 PW217–PW230 PW529

MANDALA AIRLINES (MND)

2 PK255 PK636 PL027 PL744

3 PW004 PW010

7 PL421 PN002

MANGAL AIRLINES (MGG)

2 PL785

MARANATHA LEASING CORPORATION (MNT)

1 PG436

2 PK201–PK202 PL011
 

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ALERT ALERT

MAX AVIA (MXY)

2 PK222 PK315 PK671 PL732

4 PK830

MERPATI NUSANTARA AIRLINES (PNM)

2 PK354 PK614–PK615 PK623–PK624 PK917

PK929–PK930 PL408 PL411 PN105–PN106

PN108

3 PP434–PP435 PP898 PW035

4 PK819

7 PL409–PL410

MEXICAN AIR FORCE (MXA)

2 PN041

MEXICO'S PRESIDENTIAL AIRCRAFT (MXG)

3 PP919 PQ155

MIAMI AIR (MIB)

3 PV226 PV229

MIDAMERICAN AEROSPACE, LTD (MML)

2 PL557 PY231

MIRAGE AVIATION LTD (MLE)

3 PP991

MISTRAL AIR (MSX)

3 PQ222 PQ341 PS638

MNG AIRLINES (MHK)

3 PW593

6 PW512 PW514

NAT AVIATION U.S.A. (NTV)

2 PK258 PK551 PK557 PK732

NATIONAL CITY (NTJ)

2 PL471

NATIONWIDE AIRLINES (NWR)

2 PK741 PK906 PK928 PK932

PN107 PN109

7 PJ007–PJ008 PK357 PK871 PL631–PL632

NEW AXIS AIRWAYS (NXA)

3 PQ301 PW033

NEWJET (NES)

2 PL172 PL562

NICON AIRWAYS LTD. (EAV)

2 PL453 PN032
 

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ALERT ALERT

NIGERIA AIRWAYS (NIA)

2 PL788

NOK AIR (OWL)

3 PJ554 PM553 PW045

NOLINOR AVIATION (NLO)

2 PY671–PY672

NORDESTE (NDT)

3 PP987

NORTHERN AIR CARGO (NAC)

2 PN150–PN152

7 PK610

NORTHROP GRUMMAN CORPORATION (GRU)

1 PG208

NORTHSTAR PRESIDIO MANAGEMENT (INH)

2 PK094–PK095

NORWEGIAN AIR SHUTTLE AS (NSB)

3 PM381 PM389 PM401–PM402 PP805–PP808

PP918 PP985 PQ791 PQ793

PQ983 PQ985 PR002 PR028

PR030 PR101 PR132 PR169

PS601 PS620 PS627 PS654

PS872 PS961

5 PP518–PP519

NOVA AIR (PDM)

2 PL007 PL406 PN412 PN414

OKAY AIRWAYS COMPANY LIMITED (OKY)

3 PP631 PP634 PQ290 PT725

OLYMPIC AIRLINES (OLY)

3 PQ298 PS657 PV201–PV202 PV231

PW063 PW068 PW072 PW291

PW711 PW713–PW717 PW771

OLYMPIC AIRWAY SERVICES (OLS)

3 PW062

ORENBURG AIRLINES (ORG)

3 PT010 PT029 PT301–PT302 PW028

PW036

OUR AIRLINE (NAU)

3 PP831 PP902
 

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ALERT ALERT

OZJET AIRLINES (OZJ)

2 PK045 PK050 PK052–PK053

PACE AIRLINES (PIE)

1 PG075 PG203

2 PL001 PN102 PN116

3 PP835

8 PL502–PL503

PACIFIC PEARL AIRWAYS (PPA)

2 PN146

PACIFIC SKY AVIATION INC. (SEF)

3 PT219

PAI AVIATION, INC. (PSS)

2 PK043 PK233 PK235 PK752

PK756

3 PP802

PAKISTAN INT'L AIRLINES (PIA)

3 PP281–PP286 PS612

PAMIR AIRWAYS (PMY)

2 PN135

PEGASUS AIRLINES (PGS)

3 PT137 PT724 PT854 PW030

PW263

PERUVIAN AIR FORCE (PRF)

1 PG251 PG253 PG351

2 PN082

3 PT517

PHILIPPINE AIRLINES (PAL)

3 PQ803

PHUKET AIRLINES (PHK)

1 PG581–PG582

2 PN037 PN039

PLATINUM AIRWAYS (PLW)

3 PP189

PLM INTERNATIONAL (PLI)

2 PK675

PLUNA (PLU)

2 PK923 PL201–PL203

PRECISIONAIR (PCR)

3 PM395
 

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ALERT ALERT

Q AVIATION (QAV)

2 PK288

4 PK603–PK604

QANTAS (QAN)

3 PQ002 PQ007 PQ009 PQ011

PW531–PW539 PW541 PW544–PW550 PW557

QUIKJET (QKJ)

3 PQ221 PQ223

QWEST AIR PARTS (QWE)

1 PG438

REGIONALCARGO (RGC)

2 PY057

REPEX AIRLINES (REX)

2 PY102–PY103

REPUBLIC FINANCIAL CORPORATION (RFC)

1 PA011 PG199 PG225 PG433

PG502–PG503 PG622 PG704

REPUBLIC OF INDONESIA (IDO)

7 PL601–PL603

REPUBLIC OF KOREA AIR FORCE (KAF)

3 PP221

REPUBLIC OF NIGER (NIR)

2 PY166

REPUBLIC OF VENEZUELA (VNZ)

7 PK070

REPUBLICAIR (RPB)

2 PL553 PL555

RICO (RLA)

2 PK119–PK120

ROSSIYA RUSSIAN AIRLINES (STG)

3 PT164–PT168

ROYAL AIR MAROC (RAM)

2 PK271–PK272

3 PT582–PT586

ROYAL KHMER AIRLINES (KHM)

2 PN163
 

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ALERT ALERT

RUTACA AIRLINES (ZRU)

2 PK281 PK611 PK613 PM062

RUTAS AEREAS VENEZOLANAS S.A. (RTV)

2 PL402 PL414 PN145 PN157

4 PK822

RYAN INTERNATIONAL AIRLINES (RYN)

2 PK097 PK543

3 PQ197

4 PK606

RYM AIRLINES (RYM)

2 PL017–PL018

S7 AIRLINES (SBR)

3 PM556 PT381 PT388–PT389 PT501–PT502

PT505–PT506 PW051 PW094

SAFAIR (SFA)

1 PY002

2 PK731 PK733 PK746 PL061

4 PK820 PK824

SAFI AIRWAYS (FFI)

3 PP521–PP522

SAGA AIRLINES (SGV)

3 PV207 PV209

SAMA AIRLINES (AWM)

3 PM393–PM394 PQ982 PS606 PS651

5 PP509

SAS NORWAY (BRT)

3 PT002–PT004 PT006–PT008 PT011–PT015 PT024–PT025

PV351 PW573–PW574 PW576

SAT AIRLINES (SKH)

2 PL221 PN158

SAUDI ARABIAN AIRLINES (SVA)

2 PK316 PL727–PL728 PL730–PL731 PL733

PY036

SEAGLE AIR (SGQ)

3 PP964

SHAHEEN INTERNATIONAL (SHK)

2 PK592 PL003 PL551 PL561

PN036

4 PK602

7 PK608
 

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ALERT ALERT

SHANDONG AIRLINES (SHG)

3 PQ391–PQ395 PR006–PR009 PR013–PR014 PR161

SHANTOU AIRLINES (SHT)

3 PM415–PM417

SHENZHEN AIRLINES (SHZ)

3 PQ486 PQ972 PQ976 PQ995

PS629 PS691–PS692 PS851–PS852

SIERRA PACIFIC AIRLINES (SRP)

2 PK627 PL621

SILVER AIR (SARL) (SVT)

2 PK313–PK314 PL726 PL734

3 PP865

SILVER SKY (SLZ)

2 PN419

SKY AIRLINES (SYC)

3 PV235 PW278 PW281 PW293

PW296

SKY EXPRESS (SXR)

3 PQ056 PQ258–PQ259 PT058 PT123–PT124

PT146 PT217–PT218 PT616

SKY HOLDING COMPANY (PSH)

2 PL401 PL403 PN491

SKY KING (SKN)

2 PK351–PK353 PK696 PL002 PN156

PN162

SKY SERVICE (SSV)

2 PK526–PK527 PK628–PK629 PK772 PK881

PK884 PK902 PK908 PK927

PK971 PK973 PL736

SKYNET ASIA AIRWAYS (SNU)

3 PM555 PW026 PW274 PW441–PW442

PW855–PW856

SLOK AIR (SRO)

7 PM108–PM113

SOUTH AFRICAN AIRWAYS (SAA)

2 PL104–PL106

3 PM413–PM414

SOUTHERN WINDS (SOW)

2 PK047 PK616
 

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ALERT ALERT

SOUTHWEST AIRLINES (SWA)

2 PM065

3 PP101–PP118 PP121–PP161 PP163–PP169 PP188

PP190–PP193 PP202–PP205 PP301–PP304 PP351

PP353 PP376–PP380 PP382 PP402–PP403

PP727 PP731 PP803–PP804 PP821–PP824

PP827 PS751–PS799 PS901–PS941 PU001–PU025

5 PP501–PP502

SPACE WORLD AIRLINE/SWA (WIN)

2 PL021–PL022

SRIWIJAYA AIR (SJA)

2 PK302–PK303 PK307–PK308 PK777 PM021

PM254 PN023 PN026–PN027 PN040

PN042–PN043

3 PP910 PP927 PW061

4 PJ114

5 PS863

STA SUPPLIES PTE. LTD. (SSP)

3 PQ040–PQ041

STAR AIR (SGY)

2 PN033

STAR UP S.A. (SRU)

2 PK921 PL611

4 PJ115

STERLING AIRLINES A/S (STR)

3 PT121 PT125 PT127 PT132

STEWART INDUSTRIES INT'L (SDT)

2 PK905 PK926 PK935 PM251

PN473

SUNDOWNER OKLAHOMA CITY LLC (SDO)

3 PW313

SWIFT AIR (SWF)

3 PM392 PP352 PP847 PP862

PP948

SWIFT AIR LLC (SFW)

3 PV042–PV043 PW563

TAAG (ANGOLA AIRLINES) (ANG)

2 PK664–PK666 PY162

7 PK661

TAC (TGB)

1 PY031
 

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ALERT ALERT

TACA INTERNATIONAL AIRLINES (TAC)

2 PL737 PN420

TAF LINHAS AEREAS (TFL)

1 PY323 PY342

2 PK118 PL404 PN160

TAROM - ROMANIAN AIR TRANSPORT (TRM)

3 PQ931–PQ935

TEEBAH AIRLINES (EBH)

2 PN028

THAI AIRASIA (THA)

3 PP411–PP412 PP676–PP677 PP684 PP686–PP687

THAI AIRWAYS INTERNATIONAL (TII)

3 PV296 PW161–PW162 PW164–PW171 PW594

THE MOURITZEN FAMILY TRUST (MRZ)

2 PY191

THE PEGASUS AVIATION COMPANY (PEG)

2 PK285

THOMSON AIRWAYS (BRI)

3 PQ436–PQ437 PR003–PR004 PR011 PR023–PR024

PR067 PR165 PS974–PS975

TITAN AIRWAYS (TIU)

3 PM387 PS636–PS637

5 PP505

TNT AIRWAYS (TNB)

3 PP384 PP391 PP413–PP414 PP433

PP702 PP845

5 PP472 PP474 PP711

TOR AIR (TOB)

3 PW288

TRAFIC (TFI)

2 PY056

TRANS AIR CONGO (TSC)

2 PK562 PK763

TRANSAERO AIRLINES (TRX)

2 PK451 PK773 PK779

3 PP963 PP966 PT046 PT049

PT052 PT104–PT105 PT723 PT923

PT925 PW024 PW040 PW113–PW114

PW120
 

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ALERT ALERT

TRANSMILE AIR SERVICES (TML)

1 PY381

2 PN472 PN474 PY151

TRAVEL SERVICE (TSF)

3 PT432 PT436

TRAVIRA AIR (TVR)

3 PT135

TRIGANA AIR (TGN)

8 PL504

TRITON AVIATION SERVICES (TIA)

1 PJ101 PJ103

2 PK677 PL770 PN101

TUIFLY (HAP)

6 PW513

TUNISAIR (TUN)

3 PT641–PT644

TURKISH AIRLINES (THY)

3 PM552 PM557 PM559–PM560 PM562–PM564

PW049–PW050

TURKMENISTAN AIRLINES (TUE)

3 PQ265 PQ801–PQ802

UKRAINE INTERNATIONAL AIRLINES (UKR)

3 PM382 PM551 PM554 PM561

PQ251 PQ991 PR042 PR181

PT043 PT048 PT055 PT059

PT511–PT512 PW742

6 PW701–PW702

UNITED AIR LINES (UAL)

1 PG024 PG052 PG054–PG055 PG057

PG067 PG069–PG071

2 PL004 PL009 PL012 PL014–PL016

3 PQ101–PQ115 PQ118 PQ121–PQ122 PQ125–PQ142

PQ146–PQ151 PQ164–PQ167 PQ169–PQ179 PQ181–PQ183

PQ185–PQ186 PQ198–PQ199 PQ201–PQ202 PT382–PT387

PT390–PT395 PT398–PT399 PT402–PT419 PT422–PT423

UNIVERSAL ASSET MANAGEMENT (UAM)

2 PM054 PM056 PM059–PM061

US AIR FORCE (USF)

7 PJ202 PJ206 PJ211 PJ213–PJ219
 

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ALERT ALERT

US AIRWAYS (USA)

2 PL081 PL560

3 PP005 PP007 PP014–PP015 PP024–PP027

PP029–PP030 PP032 PP036–PP038 PP047–PP054

PP183–PP187 PP194–PP195 PP197–PP198 PP401

PP417 PP428 PP439 PP834

PP891 PP893 PP895 PP901

PP931–PP934 PS668–PS669 PV001–PV010 PV012–PV022

PV025–PV030 PV033–PV040 PV044–PV055

UT FINANCE CORPORATION (ZZJ)

3 PQ153

UTAIR (UTR)

3 PT825 PT919–PT920 PT922 PT927–PT928

VARIG AIRLINES (VAR)

2 PK111–PK112 PK114 PK144

VASP AIRLINES (VSP)

1 PG472

2 PK581

5 PP512

VIRGIN NIGERIA (VNA)

3 PR167–PR168 PR170–PR172

VISION AIR (VEG)

3 PP685 PS626

VIVA AEROBUS (VIV)

3 PP009–PP010 PP013 PP023 PP041

PP427

5 PP473

WAHA LEASING (OSI)

3 PW527

WEBJET LINHAS AEREAS LTDA. (WJL)

3 PP839 PP906–PP907 PQ159 PQ188

PQ256–PQ257 PQ260–PQ261 PQ266–PQ267 PS603

WELLS FARGO (FSB)

5 PP513

WEST DOVER LLC (WDR)

3 PP415

WESTAIR CARGO AIRLINES (WCO)

2 PY037

WESTSTAR AVIATION (WSE)

2 PK565
 

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ALERT ALERT

WILMINGTON TRUST COMPANY (WBT)

3 PP035 PP042 PP045

WINGS OF LEBANON S.A.L. (WGL)

2 PN141

XIAMEN AIRLINES (XIA)

3 PT027–PT028 PT030–PT031

XSTRATA CANADA CORPORATION (NAD)

2 PY612

XTRA AIRWAYS (CIN)

1 PG279

3 PW117 PW761

YAMAL AIRLINES (YMA)

3 PU301

ZAMBIAN AIRWAYS (MBA)

2 PK220 PL109

ZASA (CZA)

2 PL735

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

PA001–PA022 1

PA099 1

PA231–PA232 1

PC001–PC005 1

PG001–PG075 1

PG199 1

PG201–PG230 1

PG251–PG255 1

PG271–PG279 1

PG301–PG314 1

PG331–PG332 1

PG351–PG356 1

PG375 1

PG401–PG403 1

PG431–PG442 1

PG471–PG475 1

PG501–PG505 1

PG571–PG583 1
 

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ALERT ALERT

PG584–PG586 2

PG621–PG630 1

PG651–PG652 1

PG701–PG705 1

PH001 2

PH011–PH013 2

PH021–PH024 2

PH701–PH715 1

PH731–PH732 1

PH741–PH742 1

PH743 2

PJ001–PJ002 1

PJ003–PJ006 2

PJ007–PJ009 7

PJ031–PJ032 1

PJ071–PJ072 1

PJ101–PJ104 1

PJ105–PJ119 4

PJ201–PJ219 7

PJ301–PJ302 3

PJ551–PJ561 3

PJ601–PJ615 3

PJ811 6

PJ816–PJ817 3

PK026–PK029 2

PK041–PK053 2

PK061–PK067 2

PK068–PK070 7

PK081–PK082 2

PK091–PK099 2

PK101–PK103 2

PK111–PK120 2

PK141–PK146 2

PK201–PK204 2

PK211–PK223 2

PK231–PK241 2

PK251–PK256 2

PK257 7

PK258 2

Variable Group
 

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ALERT ALERT

PK271–PK274 2

PK281–PK289 2

PK291 2

PK301–PK318 2

PK341 2

PK351–PK355 2

PK356–PK360 7

PK361 2

PK391 2

PK431–PK433 2

PK451–PK452 2

PK461–PK469 2

PK495 2

PK501 2

PK502–PK504 7

PK511–PK515 2

PK519 2

PK521–PK528 2

PK541–PK565 2

PK581 2

PK591–PK599 2

PK601–PK606 4

PK607–PK610 7

PK611–PK617 2

PK621–PK637 2

PK641–PK642 2

PK661 7

PK662–PK666 2

PK671–PK681 2

PK691–PK697 2

PK711–PK716 2

PK731–PK765 2

PK771–PK779 2

PK801–PK804 2

PK819–PK827 4

PK830 4

PK861–PK863 2

PK871–PK874 7

PK881–PK884 2

Variable Group
 

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ALERT ALERT

PK901–PK938 2

PK971–PK974 2

PL001–PL028 2

PL061 2

PL081 2

PL101–PL113 2

PL151 2

PL171–PL172 2

PL201–PL203 2

PL221 2

PL401–PL408 2

PL409–PL410 7

PL411 2

PL412 7

PL413–PL417 2

PL421 7

PL441 2

PL451–PL456 2

PL471 2

PL491 2

PL501–PL506 8

PL551–PL562 2

PL581 2

PL601–PL603 7

PL611 2

PL621–PL626 2

PL631–PL632 7

PL711–PL712 1

PL716 1

PL717–PL747 2

PL756 2

PL758 2

PL761–PL770 2

PL781–PL788 2

PL793 2

PL801–PL803 1

PM001–PM006 2

PM016–PM017 2

PM021–PM023 2

Variable Group
 

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ALERT ALERT

PM051–PM066 2

PM101–PM119 7

PM141–PM142 7

PM171 2

PM181 2

PM251–PM255 2

PM281–PM283 2

PM381–PM399 3

PM401–PM417 3

PM541–PM564 3

PN001–PN002 7

PN021–PN043 2

PN081–PN086 2

PN101–PN117 2

PN131–PN163 2

PN401–PN420 2

PN431–PN433 2

PN451–PN456 2

PN471–PN474 2

PN481 2

PN491–PN493 2

PN501–PN502 2

PN511–PN512 2

PN521 7

PP001–PP054 3

PP101–PP169 3

PP181–PP199 3

PP201–PP205 3

PP221 3

PP231–PP243 3

PP281–PP286 3

PP301–PP305 3

PP351–PP353 3

PP376–PP384 3

PP391–PP393 3

PP401–PP440 3

PP471–PP475 5

PP501–PP520 5

PP521–PP522 3

Variable Group
 

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ALERT ALERT

PP631–PP634 3

PP651–PP652 3

PP671–PP689 3

PP690–PP694 5

PP695–PP699 3

PP701–PP706 3

PP707–PP716 5

PP717–PP733 3

PP771–PP779 3

PP801–PP808 3

PP821–PP827 3

PP831–PP848 3

PP851–PP852 3

PP861–PP877 3

PP891–PP899 3

PP901–PP936 3

PP946–PP948 3

PP951–PP952 3

PP961–PP967 3

PP981–PP991 3

PP993 3

PQ001–PQ016 3

PQ026–PQ041 3

PQ051–PQ092 3

PQ101–PQ199 3

PQ201–PQ202 3

PQ221–PQ237 3

PQ241–PQ243 3

PQ251–PQ267 3

PQ281–PQ299 3

PQ301–PQ307 3

PQ331–PQ332 3

PQ341–PQ348 3

PQ361–PQ373 3

PQ391–PQ395 3

PQ401–PQ418 3

PQ421 3

PQ431–PQ438 3

PQ447–PQ448 3

Variable Group
 

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ALERT ALERT

PQ451 3

PQ454 3

PQ471–PQ475 3

PQ479–PQ481 3

PQ486–PQ487 3

PQ491–PQ493 3

PQ771–PQ772 3

PQ791–PQ793 3

PQ801–PQ805 3

PQ931–PQ935 3

PQ951 3

PQ971–PQ997 3

PR001–PR017 3

PR021–PR034 3

PR041–PR045 3

PR061–PR072 3

PR077–PR082 3

PR091–PR092 3

PR096 3

PR101 3

PR121–PR122 3

PR131–PR132 3

PR141–PR143 3

PR161–PR172 3

PR181 3

PS601–PS631 3

PS636–PS638 3

PS641–PS644 3

PS651–PS657 3

PS666–PS669 3

PS691–PS692 3

PS701–PS706 3

PS751–PS799 3

PS811 3

PS836–PS837 3

PS841–PS846 3

PS851–PS852 3

PS856 3

PS861–PS863 5

Variable Group
 

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ALERT ALERT

PS866–PS868 5

PS871–PS874 3

PS896–PS897 3

PS901–PS941 3

PS956–PS957 5

PS961–PS963 3

PS971–PS978 3

PT001–PT015 3

PT021–PT031 3

PT041–PT064 3

PT101–PT105 3

PT121–PT138 3

PT146–PT148 3

PT161–PT170 3

PT181–PT188 3

PT211–PT220 3

PT295 3

PT301–PT309 3

PT331–PT360 3

PT381–PT399 3

PT401–PT438 3

PT501–PT517 3

PT561–PT565 3

PT581–PT586 3

PT611–PT621 3

PT641–PT644 3

PT651–PT656 3

PT671–PT672 3

PT681–PT685 3

PT701–PT703 3

PT716–PT717 3

PT721–PT725 3

PT801–PT834 3

PT851–PT854 3

PT871–PT886 3

PT901–PT930 3

PT971–PT973 3

PT981–PT985 3

PT996 3

Variable Group
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

PU001–PU025 3

PU301 3

PU311–PU313 3

PV001–PV055 3

PV201–PV209 3

PV226–PV229 3

PV231–PV237 3

PV271–PV272 3

PV281–PV287 3

PV296 3

PV301–PV302 3

PV351 3

PV356–PV357 3

PW001–PW054 3

PW061–PW068 3

PW072 3

PW086–PW088 3

PW091–PW094 3

PW101–PW102 3

PW106 3

PW111–PW120 3

PW156–PW157 3

PW161–PW171 3

PW201–PW252 3

PW261–PW268 3

PW271–PW276 3

PW278 3

PW281–PW293 3

PW296 3

PW301–PW327 3

PW401–PW408 3

PW411–PW418 3

PW421–PW424 3

PW431–PW435 3

PW441–PW450 3

PW461–PW467 3

PW501–PW504 3

PW511–PW522 6

PW524 6

Variable Group
 

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ALERT ALERT

PW525–PW529 3

PW530 6

PW531–PW550 3

PW556–PW557 3

PW561–PW564 3

PW571–PW576 3

PW591–PW596 3

PW611–PW622 3

PW631–PW637 3

PW661–PW662 3

PW681–PW683 3

PW701–PW702 6

PW711–PW717 3

PW741–PW742 3

PW761 3

PW771 3

PW831 3

PW851–PW856 3

PX071 1

PX701 1

PY001–PY008 1

PY021 1

PY022 2

PY031 1

PY036–PY037 2

PY046–PY048 2

PY051–PY053 2

PY056–PY057 2

PY101–PY103 2

PY111–PY113 2

PY131–PY135 2

PY141–PY143 2

PY151–PY154 2

PY156–PY157 2

PY161–PY162 2

PY166 2

PY191 2

PY201 2

PY221–PY222 2

Variable Group
 

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ALERT ALERT

2. Spares Affected

None.

PY231 2

PY241–PY244 2

PY270–PY275 2

PY281 2

PY286 2

PY301–PY304 1

PY321–PY323 1

PY341–PY346 1

PY361–PY362 1

PY381 1

PY401 2

PY409–PY411 2

PY421–PY422 2

PY441 2

PY451 2

PY461–PY463 2

PY591–PY595 2

PY611–PY612 2

PY621 2

PY631 2

PY651 2

PY671–PY672 2

PY721 2

PY741 2

Variable Group
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

B. Concurrent Requirements

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

Group 1: Operators should contact Boeing to obtain engineering and accomplishment instructions for 

this modification. 

C. Reason

This service bulletin affects the 737-200/-200C/-300/-400/-500 airplanes with line numbers 292 thru 

3132 that have center and auxiliary fuel tanks. Operators with 737-100/-200/-200C airplanes with line 

numbers 1 thru 291 that have center and auxiliary fuel tanks should contact Boeing to obtain 

engineering and accomplishment instructions for this modification. This service bulletin is sent to give 

’un-commanded on’ protection for the fuel pump control system. Instructions are given to add one 

more relay, as a fail safe, for each fuel pump in the center and auxiliary fuel tanks. If this service 

bulletin is not done, the fuel pumps could run dry, which increases the pumps temperature and could 

cause an ignition source for fuel vapor in the fuel tank. Ignition of the flammable fuel vapors in the fuel 

tanks, could cause a fire or explosion which will put the airplane in an unsafe condition.

The Boeing system safety assessment necessary for Special Federal Aviation Regulation (SFAR) 88, 

showed that electrical faults within the fuel tank pump system can cause a fuel pump to operate when 

the fuel pump switch is in the ’OFF’ position. Boeing has developed a new system to prevent extended 

operation of the fuel tank boost pumps in this condition. This new system has a second relay to 

prevent the operation of a pump when its switch is in the ’OFF’ position. The auto shutdown relay 

currently installed for each pump gives the same solution as the new additional relay, but is known to 

have caused in-service problems because its contacts have ’welded’ closed and continued to let 

power be supplied. This condition is referred to as ’un-commanded on’ (UCO) pump operation. This 

new second relay added to the existing fuel control circuit and interfaced with the P5-2 fuel control 

module, prevents UCO operation of the fuel boost pumps. The system senses if there is a voltage 

remaining in the fuel boost pump circuit and activates the UCO relay to remove the power. In the flight 

deck the pump low pressure light in the P5-2 fuel control systems module, and master caution light 

come on when the fuel pump is at low pressure. No additional indication is provided for dry running 

pumps.

Group 2-8: 

Company Service Bulletin Description

Boeing 737-28A1210 Original Issue Replacement of the P5-2 Fuel System 

Module to Supply Low Fuel Pressure 

Master Caution Annunciation.

Group 3, 5-6: 

Company Service Bulletin Description

Boeing 737-28A1216 Original Issue Installation of the Auto Shutoff Protection 

for the Center and Auxiliary Fuel Tank 

Boost Pumps.

Group 2, 4, 7-8: 

Company Service Bulletin Description

Boeing 737-28A1228 Original Issue Installation of the Auto Shutoff Protection 

for the Center and Auxiliary Fuel Tank 

Boost Pumps.
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

Accomplishment of this service bulletin installs new UCO relays and toggle switches in the J2802 box 

assembly located in the Electronic Equipment Bay (E/E bay). This service bulletin also changes and 

adds new wire bundles that route from the J2802 box assembly to the P5 Forward Overhead Panel 

and the P6 Disconnect Panels. Installation of the new UCO relays for each pump will prevent "dry 

running" of the fuel pumps and reduce the risk of fuel tank fire or explosion.

New Airworthiness Limitations (AWL) 28-AWL-24 (Center Tank) and 28-AWL-25 (Auxiliary Fuel Tank) 

for 737-200 airplanes and AWL 28-AWL-23 (Center Tank) and 28-AWL-24 (Auxiliary Fuel Tank) for 

737-300/-400/-500 airplanes will be added to section 9 of the Maintenance Planning Data (MPD) to 

include a functional check of the center fuel pumps and (auxiliary tank pumps for applicable airplanes) 

primary and secondary control relays.

Boeing Fleet Team Digest (FTD) 737 FTD 28-04004 is related to this service bulletin.

D. Description

Remove equipment as necessary to get access the J2802 box assembly on the E2 and E3 support 

posts in the E/E bay, P6 Load Control Center in the flight compartment/control cabin, and P6 

disconnect panels. Remove the cover from the J2802 box assembly and install wire bundles W1760 

and W1770 and relays. Change wire bundles W036, W368, W386, W1034, W1046, W1764 and 

W1774, as applicable, between the P6 disconnect panels and J2802 box assembly. Check the 

continuity of all the new and changed wires and do a functional test to make sure the changed fuel 

control system operates correctly.

Operators with Group 1 airplanes should contact Boeing to obtain engineering and accomplishment 

instructions for this modification. 

E. Compliance

Boeing recommends that the change given in this service bulletin be done within 60 months after the 

original issue date of 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.

Operators with Group 1 airplanes should contact Boeing to obtain engineering and accomplishment 

instructions for this modification. 

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.
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

G. Manpower

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

— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Group 1: Operators should contact Boeing to obtain engineering and accomplishment instructions for 

this modification. 

Group 2: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 3.00 1.50

Figure 1 1 0.75 0.75

Figure 2 (Wire 

Routing only)

---

Figure 3 2 8.00 4.00

Figure 4 2 8.00 4.00

Figure 9 (Wire 

Routing only)

---

Figure 10 2 6.80 3.40

Figure 11 2 6.80 3.40

Figure 30 1 0.25 0.25

Test 1 0.50 0.50

Close Access 2 3.00 1.50

TOTAL FOR EACH AIRPLANE 37.10 19.30

Group 3: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 3.00 1.50

Figure 1 1 0.75 0.75

Figure 2 (Wire 

Routing only)

---

Figure 3 2 8.00 4.00

Figure 4 2 8.00 4.00

Figure 12 (Wire 

Routing only)

---

Figure 13 2 6.80 3.40
 

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ALERT ALERT

Figure 14 2 6.80 3.40

Figure 30 1 0.25 0.25

Test 1 0.50 0.50

Close Access 2 3.00 1.50

TOTAL FOR EACH AIRPLANE 37.10 19.30

Group 4: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 3.00 1.50

Figure 1 1 0.75 0.75

Figure 2 (Wire 

Routing only)

---

Figure 3 2 8.00 4.00

Figure 4 2 8.00 4.00

Figure 15 (Wire 

Routing only)

---

Figure 16 2 6.80 3.40

Figure 17 2 6.80 3.40

Figure 30 1 0.25 0.25

Test 1 0.50 0.50

Close Access 2 3.00 1.50

TOTAL FOR EACH AIRPLANE 37.10 19.30

Group 5: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 3.00 1.50

Figure 5 1 1.00 1.00

Figure 6 (Wire 

Routing only)

---

Figure 7 2 16.00 8.00

Figure 8 2 16.00 8.00

Figure 18 (Wire 

Routing only)

---

Figure 19 2 11.00 5.50

Figure 20 2 11.00 5.50

Figure 30 1 0.25 0.25

Group 3: 

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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ALERT ALERT

Test 1 1.00 1.00

Close Access 2 3.00 1.50

TOTAL FOR EACH AIRPLANE 62.25 32.25

Group 6: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 3.00 1.50

Figure 5 1 1.00 1.00

Figure 6 (Wire 

Routing only)

---

Figure 7 2 16.00 8.00

Figure 8 2 16.00 8.00

Figure 21 (Wire 

Routing only)

---

Figure 22 2 11.00 5.50

Figure 23 2 11.00 5.50

Figure 30 1 0.25 0.25

Test 1 1.10 1.10

Open Access 2 3.00 1.50

TOTAL FOR EACH AIRPLANE 62.35 32.35

Group 7: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 3.00 1.50

Figure 5 1 1.00 1.00

Figure 6 (Wire 

Routing only)

---

Figure 7 2 16.00 8.00

Figure 8 2 16.00 8.00

Figure 24 (Wire 

Routing only)

---

Figure 25 2 11.00 5.50

Figure 26 2 11.00 5.50

Figure 30 1 0.25 0.25

Test 1 1.10 1.10

Close Access 2 3.00 1.50

TOTAL FOR EACH AIRPLANE 62.35 32.35

Group 5: 

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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ALERT ALERT

H. Weight and Balance Changes

Group 1: Operators should contact Boeing to obtain engineering and accomplishment instructions for 

this modification. 

I. Electrical Load Data

1. Direct Current (DC) Loads

Group 8: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 3.00 1.50

Figure 5 1 1.00 1.00

Figure 6 (Wire 

Routing only) 

---

Figure 7 2 16.00 8.00

Figure 8 2 16.00 8.00

Figure 27 (Wire 

Routing only)

---

Figure 28 2 11.00 5.50

Figure 29 2 11.00 5.50

Figure 30 1 0.25 0.25

Test 1 0.50 0.50

Close Access 2 3.00 1.50

TOTAL FOR EACH AIRPLANE 61.75 31.75

Group 2-4: 

Airplane

Change in Weight 

(Pounds)

Change in Moment 

(Pound-Inches)

737-100 +7 +2,100

737-200 +7 +1,850

737-300 +7 +1,540

737-400 +7 +1,040

737-500 +7 +1,920

Group 5-8: 

Airplane

Change in Weight 

(Pounds)

Change in Moment 

(Pound-Inches)

737-200 +10 +2,640

737-300 +10 +2,200

737-400 +10 +1,480
 

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ALERT ALERT

Group 1: Operators should contact Boeing to obtain engineering and accomplishment 

instructions for this modification. 

2. Alternating Current (AC) Loads

No Change.

3. Type

Continuous.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 35443-RS.

b. 737-100/200 Aircraft Maintenance Manual (AMM) 12-31-11, 24-22-0, 24-31-11, 25-11-0, 

25-16-11, 25-31-11, 25-31-51, 25-51-01, 32-00-01, 52-48-41, 52-61-0, 52-61-100.

c. 737-300/400/500 Aircraft Maintenance Manual (AMM) 12-31-11, 24-22-00, 24-31-11, 

25-10-00, 25-11-21, 25-31-11, 25-51-01, 32-00-01, 52-48-41, 52-61-00, 52-61-10.

d. 737 Fleet Team Digest (FTD) 28-04004.

e. 737-100/200 Wiring Diagram 28-23-01, 28-23-02.

f. 737-300/400/500 Wiring Diagram 28-23-01, 28-23-02.

g. Boeing Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-15, 

20-10-18, 20-10-19, 20-20-11, 20-30-11, 20-30-12, 20-30-17, 20-30-22, 20-60-08, 

20-60-09, 20-60-11, 20-61-11, 20-81-19.

h. 737 Maintenance Planning Document (MPD) Section 9.

i. Boeing Drawing 65-88700.

j. Boeing Parts Standards Document D-590.

k. Boeing Service Bulletin 737-28A1210, 737-28A1216, 737-28A1228.

Group 2-4: 

Circuit Breaker Amperes Bus

C64 +0.25 28V DC Bus 1

C65 +0.25 28V DC Bus 2

Group 5-8: 

Circuit Breaker Amperes Bus

C64 +0.50 28V DC Bus 1

C65 +0.50 28V DC Bus 2
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

2. Data supplied with this Service Bulletin:

None.

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

This drawing was used to prepare this service bulletin. This drawing is not necessary to make the 

specified changes, and is not supplied with this service bulletin. This drawing may not be 

applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

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

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

Drawing Number Title

65C38484 KIT - EQUIPMENT / WIRE INSTALLATION, J2802 PANEL

Publication Chapter-Section

737 Aircraft Maintenance Manual 28-22

737 Wiring Diagram Manual 28-23

737 Illustrated Parts Catalog 28-23

737 Schematic Diagram Manual 28-23

737 Maintenance Planning Document Section 9
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown 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.

Kit Number Name Date QTY

ROLT 

(Weeks)

Unit Price thru

MAR 31/07

65C38537-1 (a) BOOST PUMP, FUEL 

UNCOMMANDED ON - 

TOP KIT, CENTER 

TANK 737/100/200/

300/400/500

06/04/07 10 33 $3,440.00

06/18/07 10

07/02/07 25

07/17/07 25

07/31/07 25

08/14/07 25

08/28/07 25

09/12/07 25

09/26/07 25

10/10/07 25

10/24/07 25

11/07/07 25

11/21/07 25

12/07/07 25

12/21/07 25

01/15/08 25

01/29/08 25

02/12/08 25

02/26/08 25

03/11/08 25

03/25/08 25

04/08/08 25

04/22/08 25

05/06/08 25

05/20/08 25

06/04/08 25

06/18/08 25

07/02/08 25

07/17/08 25

07/31/08 5
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

Operators with Group 1 airplanes should contact Boeing to obtain engineering and accomplishment 

instructions for this modification.

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.

65C38537-2 (b) BOOST PUMP, FUEL 

UNCOMMANDED ON - 

TOP KIT, CENTER & 

AUXILIARY TANKS

07/05/07 5 33 $5,699.00

07/19/07 5

65C38537-3 (c) 07/05/07 10 33 $5,646.00

06/19/07 10

(a) This kit is applicable to Group 2 thru 4.

(b) This kit is applicable to Group 5 and 6.

(c) This kit is applicable to Group 7 and 8.

Kit Number Name Date QTY

ROLT 

(Weeks)

Unit Price thru

MAR 31/07
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

Kit 65C38510 

New Part 

Number

QTY

-2 -1 Name Notes

65C38510-1 . - WIRE BUNDLE INSTALLATION 

FOR AIRPLANES WITHOUT AUX 

TANK - PUMP UNCOMMANDED ON

65C38510-2 - . WIRE BUNDLE INSTALLATION 

FOR AIRPLANES WITH AUX TANK 

- PUMP UNCOMMANDED ON

64AT23-7E 2 2 TOGGLE SWITCH - LOCKED IN 

CENTER POSITION

9324-7424 

(MS27418-2B 

optional)

4 2 RELAY

Kit 65C38537 

New Part 

Number

QTY

-3 -2 -1 Name Notes

65C38537-1 . . - BOOST PUMP, FUEL UNCOMMANDED ON - 

TOP KIT, CENTER TANK 737/200/300/400/500

65C38537-2 . - . BOOST PUMP, FUEL UNCOMMANDED ON - 

TOP KIT, CENTER & AUXILIARY TANKS

65C38537-3 - . . BOOST PUMP, FUEL UNCOMMANDED ON - 

TOP KIT, CENTER & AUXILIARY TANKS

61-74482-1 . . 1 WIRE KIT - UNCOMMANDED ON RELAYS - 

NO AUX TANK CONFIGURATION

61-74482-2 . 1 . WIRE KIT - UNCOMMANDED ON RELAYS - 

AUX TANK CONFIGURATION - 737-300/-400/-

500

61-74482-3 1 . . WIRE KIT - UNCOMMANDED ON RELAYS - 

AUX TANK CONFIGURATION - 737-200

65C38510-1 . . 1 WIRE BUNDLE INSTALLATION FOR 

AIRPLANES WITHOUT AUX TANK - PUMP 

UNCOMMANDED ON

65C38510-2 1 1 . WIRE BUNDLE INSTALLATION FOR 

AIRPLANES WITH AUX TANK - PUMP 

UNCOMMANDED ON
 

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ALERT ALERT

Kit 61-74482 

New Part 

Number

QTY

-1 Name Notes

61-74482-1 - WIRE KIT - UNCOMMANDED ON RELAYS - NO AUX 

TANK CONFIGURATION

61-74482-103 1 ASSY - W1760

61-74482-105 1 ASSY - W1770

61-74482-107 1 ASSY - W368, W1764

61-74482-110 1 ASSY - W386, W1774

61-74482-2001 1 LACING TAPE - WHITE

61-74482-2006 1 THERMOFIT SLEEVE - 0.093 IN. I.D.

61-74482-2009 1 THERMOFIT SLEEVE - YELLOW, .375 IN I.D.

61-74482-2010 1 EXPANDABLE SLEEVE - 0.25 IN. I.D.

61-74482-2014 1 THERMOFIT SLEEVE - YELLOW, .125 IN I.D.

61-74482-2015 1 THERMOFIT SLEEVE - YELLOW, .187 IN I.D.

Kit 61-74482 

New Part 

Number

QTY

-2 Name Notes

61-74482-2 - WIRE KIT - UNCOMMANDED ON RELAYS - AUX 

TANK CONFIGURATION - 737-300/-400/-500

61-74482-104 1 ASSY - W1760

61-74482-106 1 ASSY - W1770

61-74482-108 1 ASSY - W368, W1046, W1764

61-74482-111 1 ASSY - W386, W1034, W1774

61-74482-2001 1 LACING TAPE - WHITE

61-74482-2007 1 THERMOFIT SLEEVE - 0.093 IN. I.D.

61-74482-2008 1 THERMOFIT SLEEVE - 0.25 IN. I.D.

61-74482-2009 1 THERMOFIT SLEEVE - YELLOW, .375 IN I.D.

61-74482-2011 1 EXPANDABLE SLEEVE - 0.25 IN. I.D.

61-74482-2012 1 EXPANDABLE SLEEVE - 0.5 IN. I.D.

61-74482-2014 1 THERMOFIT SLEEVE - YELLOW, .125 IN I.D.

61-74482-2015 1 THERMOFIT SLEEVE - YELLOW, .187 IN I.D.

Kit 61-74482 

New Part 

Number

QTY

-3 Name Notes

61-74482-3 - WIRE KIT - UNCOMMANDED ON RELAYS - AUX 

TANK CONFIGURATION - 737-200

61-74482-104 1 ASSY - W1760

61-74482-106 1 ASSY - W1770
 

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ALERT ALERT

61-74482-109 1 ASSY - W368, W1046, W1764

61-74482-112 1 ASSY - W386, W1034, W1774

61-74482-2001 1 LACING TAPE - WHITE

61-74482-2007 1 THERMOFIT SLEEVE - 0.093 IN. I.D.

61-74482-2009 1 THERMOFIT SLEEVE - YELLOW, .375 IN I.D.

61-74482-2011 1 EXPANDABLE SLEEVE - 0.25 IN. I.D.

61-74482-2013 1 EXPANDABLE SLEEVE - 0.5 IN. I.D.

61-74482-2014 1 THERMOFIT SLEEVE - YELLOW, .125 IN I.D.

61-74482-2015 1 THERMOFIT SLEEVE - YELLOW, .187 IN I.D.

Kit 61-74482 

New Part Number

QTY

-108 -107 -106 -105 -104 -103 Name Notes

61-74482-103 . . . . . - ASSY - W1760

61-74482-104 . . . . - . ASSY - W1760

61-74482-105 . . . - . . ASSY - W1770

61-74482-106 . . - . . . ASSY - W1770

61-74482-107 . - . . . . ASSY - W368, 

W1764

61-74482-108 - . . . . . ASSY - W368, 

W1046, W1764

60789-2 (640024-

1 optional)

. . 5 3 5 3 CONTACTS (a)

61-74482-103W . . . . . 1 WIRE LIST

61-74482-104W . . . . 1 . WIRE LIST

61-74482-105W . . . 1 . . WIRE LIST

61-74482-106W . . 1 . . . WIRE LIST

61-74482-107W . 1 . . . . WIRE LIST

61-74482-108W 1 . . . . . WIRE LIST

61-74478-10502 . . . . 1 1 CONNECTOR I.D. 

TAPE - D05208J

61-74478-10503 . . . . 1 1 CONNECTOR I.D. 

TAPE - D10966

61-74478-10601 . . . . 1 . CONNECTOR I.D. 

TAPE - D10970

61-74478-10702 . . 1 1 . . CONNECTOR I.D. 

TAPE - D05210J

61-74478-10703 . . 1 1 . . CONNECTOR I.D. 

TAPE - D10968

Kit 61-74482 

New Part 

Number

QTY

-3 Name Notes
 

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ALERT ALERT

61-74478-10801 . . 1 . . . CONNECTOR I.D. 

TAPE - D10972

61-74478-10904 1 1 . . . . CONNECTOR I.D. 

TAPE - D05208P

61-74482-10701 . 1 . . . . CONNECTOR I.D. 

TAPE - D04202J

61-74482-10702 1 1 . . . . CONNECTOR I.D. 

TAPE - D04202J

61-74482-10703 1 1 . . . . SPLICE I.D. 

SLEEVE - SP4514

61-74482-10704 1 1 . . . . SPLICE I.D. 

SLEEVE - SP4516

61-74482-10705 1 1 . . . . SPLICE I.D. 

SLEEVE - SP4522

61-74482-10801 1 . . . . . CONNECTOR I.D. 

TAPE - D04900P

61-74482-10802 1 . . . . . CONNECTOR I.D. 

TAPE - D04900P

61-74482-10803 1 . . . . . SPLICE I.D. 

SLEEVE - SP4536

61-74482-10804 1 . . . . . SPLICE I.D. 

SLEEVE - SP4538

61-74482-10805 1 . . . . . SPLICE I.D. 

SLEEVE - SP4540

61-74482-10806 2 . . . . . WIRE I.D. TAPE - 

W1764-

301B,2R,3Y-18

61-74482-10807 2 . . . . . WIRE I.D. TAPE - 

W1764-

304B,5R,6Y-18

BACC47CN2 4 . 14 7 14 7 CONTACT, PIN (a)

BACC47CP2T 17 10 . . . . CONTACT (a)

BACC47DE7A . . 3 2 3 2 CONTACT (a)

BACC47ER1 . . 5 3 5 3 CONTACT, 

SOCKET

(a)

BACS38K5 2 . . . . . STRAP (a)

BACT12AC2 . . 5 3 5 3 TERMINAL, LUG (a)

BACT12AC49 . . 14 7 14 7 TERMINAL, LUG (a)

BACT12AC53 . . 3 2 3 2 TERMINAL, LUG (a)

D-436-37 7 4 . . . . SPLICE (a)

(a) There are more parts than are necessary.

Kit 61-74482 

New Part Number

QTY

-108 -107 -106 -105 -104 -103 Name Notes
 

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ALERT ALERT

Kit 61-74482 

New Part 

Number

QTY

Name Notes

-

2006

-

2001 -112 -111 -110 -109

61-74482-109 . . . . . - ASSY - W368, W1046, 

W1764

61-74482-110 . . . . - . ASSY - W386, W1774

61-74482-111 . . . - . . ASSY - W386, W1034, 

W1774

61-74482-112 . . - . . . ASSY - W386, W1034, 

W1774

61-74482-2001 . - . . . . LACING TAPE - WHITE

61-74482-2006 - . . . . . THERMOFIT SLEEVE - 

0.093 IN. I.D.

61-74482-109W . . . . . 1 WIRE LIST

61-74482-110W . . . . 1 . WIRE LIST

61-74482-111W . . . 1 . . WIRE LIST

61-74482-112W . . 1 . . . WIRE LIST

61-74478-10904 . . . . . 1 CONNECTOR I.D. 

TAPE - D05208P

61-74478-11104 . . 1 1 1 . CONNECTOR I.D. 

TAPE - D05210P

61-74482-10701 . . . . . 1 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10703 . . . . . 1 SPLICE I.D. SLEEVE - 

SP4514

61-74482-10704 . . . . . 1 SPLICE I.D. SLEEVE - 

SP4516

61-74482-10705 . . . . . 1 SPLICE I.D. SLEEVE - 

SP4522

61-74482-10803 . . . . . 1 SPLICE I.D. SLEEVE - 

SP4536

61-74482-10804 . . . . . 1 SPLICE I.D. SLEEVE - 

SP4538

61-74482-10805 . . . . . 1 SPLICE I.D. SLEEVE - 

SP4540

61-74482-10901 . . . . . 1 CONNECTOR I.D. 

TAPE - D04900P

61-74482-11002 . . . . 1 . CONNECTOR I.D. 

TAPE - D04084J

61-74482-11003 . . 1 . 1 . CONNECTOR I.D. 

TAPE - D04208P

61-74482-11004 . . . 1 1 . CONNECTOR I.D. 

TAPE - D04208P
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

61-74482-11005 . . 1 1 1 . SPLICE I.D. SLEEVE - 

SP4524

61-74482-11006 . . 1 1 1 . SPLICE I.D. SLEEVE - 

SP4526

61-74482-11007 . . 1 1 1 . SPLICE I.D. SLEEVE - 

SP4528

61-74482-11101 . . . 1 . . CONNECTOR I.D. 

TAPE - D04898P

61-74482-11102 . . . 1 . . CONNECTOR I.D. 

TAPE - D04898P

61-74482-11103 . . 1 1 . . SPLICE I.D. SLEEVE - 

SP4530

61-74482-11104 . . 1 1 . . SPLICE I.D. SLEEVE - 

SP4532

61-74482-11105 . . 1 1 . . SPLICE I.D. SLEEVE - 

SP4534

61-74482-11106 . . . 2 . . WIRE I.D. TAPE - 

W1774-301B,2R,3Y-18

61-74482-11107 . . . 2 . . WIRE I.D. TAPE - 

W1774-304B,5R,6Y-18

61-74482-11201 . . 1 . . . CONNECTOR I.D. 

TAPE - D04898P

BACC47CN2 . . 4 7 4 4 CONTACT, PIN (a)

BACC47CP2T . . 17 14 10 17 CONTACT (a)

BACS38K5 . . 2 2 . 2 STRAP (a)

D-436-37 . . 7 7 4 7 SPLICE (a)

M23053/5-103-4 1 . . . . . INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LINKED

NA374H2 . 1 . . . . BMS 13-54

(a) There are more parts than are necessary.

Kit 61-74482 

New Part 

Number

QTY

Name Notes

-

2006

-

2001 -112 -111 -110 -109
 

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ALERT ALERT

Kit 61-74482 

New Part 

Number

QTY

Name Notes

-

2012

-

2011

-

2010

-

2009

-

2008

-

2007

61-74482-2007 . . . . . - THERMOFIT SLEEVE - 

0.093 IN. I.D.

61-74482-2008 . . . . - . THERMOFIT SLEEVE - 

0.25 IN. I.D.

61-74482-2009 . . . - . . THERMOFIT SLEEVE - 

YELLOW, .375 IN I.D.

61-74482-2010 . . - . . . EXPANDABLE SLEEVE - 

0.25 IN. I.D.

61-74482-2011 . - . . . . EXPANDABLE SLEEVE - 

0.25 IN. I.D.

61-74482-2012 - . . . . . EXPANDABLE SLEEVE - 

0.5 IN. I.D.

M23053/5-103-4 . . . . . 1 INSULATION SLEEVING, 

HEAT SHRINKABLE, 

POLYOLEFIN, FLEXIBLE, 

X-LINKED

M23053/5-106-4 . . . . 1 . POLYOLEFIN HEAT 

SHRINKABLE SLEEVE 

RAW MATERIAL

M23053/5-107-4 . . . 1 . . INSULATION SLEEVING, 

HEAT SHRINKABLE, 

POLYOLEFIN, FLEXIBLE, 

X-LINKED

NA728R99 1 1 1 . . . BMS 13-52 

EXPANDABLE S

Kit 61-74482 

New Part 

Number

QTY

Name Notes

-

2015

-

2014

-

2013

61-74482-2013 . . - EXPANDABLE SLEEVE - 0.5 IN. I.D.

61-74482-2014 . - . THERMOFIT SLEEVE - YELLOW, .125 IN I.D.

61-74482-2015 - . . THERMOFIT SLEEVE - YELLOW, .187 IN I.D.

M23053/5-104-4 . 1 . INSULATION SLEEVING, HEAT 

SHRINKABLE, POLYOLEFIN, FLEXIBLE, XLINKED

M23053/5-105-4 1 . . INSULATION SLEEVING, HEAT 

SHRINKABLE, POLYOLEFIN, FLEXIBLE, XLINKED

NA728R99 . . 1 BMS 13-52 EXPANDABLE S
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

None.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

Kit 64AT23-7 

New Part 

Number

QTY

- Name Notes

64AT23-7 - COM$TOGGLE SWITCH - LOCKED IN CENTER 

POSITION

Kit 9324-7424 

New Part 

Number

QTY

- Name Notes

9324-7424 - COM$RELAY

Kit 65C38639 

New Part 

Number

QTY

-115 Name Notes

65C38639-115 - THREAD LOCK COMPOUND

NK442N 1 LOCTITE;222 KIT

Part Number / 

Specification QTY Name Notes

61-74482-2004 

(Permacel P421) 

1 TAPE - 0.5 INCH WIDTH (a) (b)

(a) Permacel (99742)

 One Tower Center BLVD. 14th Floor

 New Brunswick NJ 08903

(b) Required for Groups 5 thru 8.
 

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ALERT ALERT

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
 

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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. The instructions identified in Paragraph 3.B., Work Instructions and the Figures(s) give 

the recommended sequence of steps. The sequence of steps to do this service bulletin 

can be changed.

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

definition of the acronyms.

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

4. Refer to SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures.

5. Unless shown differently, these dimensions and tolerances are used:

— Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or 

minus 0.03 inch.

— Torque limits to tighten nuts and bolts are in 737 SRM, Chapter 51.

6. 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.

7. It is necessary to use a low input impedance voltmeter to check voltages at all relay 

contact terminals. A recommended low input impedance voltmeter is a Simpson 260 

VOM (Volt-Ohm meter) or an alternative is a Megger Model 8 mK7 analogue multimeter.

B. WORK INSTRUCTIONS

Group 1: 

1. Operators should contact Boeing to obtain engineering and accomplishment instructions for this 

modification. 

Group 2: 

1. At the lower forward fuselage, below the E/E bay, open the access door to get access to the work 

area. Refer to 737-100/200 AMM 52-48-41 as an accepted procedure.

2. Do the steps below as applicable:
 

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a. For airplanes with airstairs, do the forward airstairs extension to give better access to the 

work area. Refer to 737-100/200 AMM 52-61-0 or 737-100/200 AMM 52-61-100 as an 

accepted procedure.

b. For airplanes with airstairs, in the E/E bay, remove and keep the drip pan to get better 

access to the work area. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes without airstairs, in the E/E bay, remove and keep the moisture shroud from 

above the access door to get better access to the work area. Refer to 737-100/200 AMM 

25-51-01 as an accepted procedure.

3. Remove electrical power from the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

4. In the E/E bay, remove and keep the moisture shroud from above the E3 rack to get access to 

the work area. Refer 737-100/200 AMM 25-51-01 as an accepted procedure.

5. In the E/E bay, disconnect the battery power cables from the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

6. Install the Nose Landing Gear (NLG) ground lock. Refer to 737-100/200 AMM 32-00-01 as an 

accepted procedure.

7. In the NLG wheel well, remove and keep the right side access panels, 3103R and 3105R to get 

access to the work area. Refer to 737-100/200 AMM 12-31-11 for panel locations.

8. In the flight compartment, move the first officer’s seat to the forward position to get better access 

to the work area. Refer to 737-100/200 AMM 25-11-0 as an accepted procedure.

9. In the flight compartment, remove and keep aft and mid center ceiling linings and the ceiling 

linings adjacent and forward of the P6 Load Control Center to get access to the work area. Refer 

to 737-100/200 AMM 25-16-11 as an accepted procedure.

10. In the passenger compartment, as applicable, loosen and move the forward galley (galley no.1) 

in an aft direction to get access to the wire routing of the P6 Load Control Center. Refer to 

737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted procedure.

11. At the E2 and E3 support post in the E/E bay, remove the cover from the J2802 box assembly 

and install new toggle switches and relays in accordance with Figure 1.

12. Install and connect the W1760 and W1770 wire bundles in the J2802 box assembly in 

accordance with Figure 2 thru Figure 4.

13. Between the P6 disconnect panels and the J2802 box assembly, make changes to wire bundles 

W0368, W0386, W1764 and W1774 in accordance with Figures 9 thru 11.

14. Do a continuity check between the P6 disconnect panel ’E’, ’A’ and the J2802 box assembly to 

make sure that the wiring connections are made correctly.

15. At the E2 and E3 support post in the E/E bay, install the cover on the J2802 box assembly in 

accordance with Figure 30.
 

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ALERT ALERT

16. In the passenger compartment, as applicable, move the forward galley (galley no.1) back to its 

position. Refer to 737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted 

procedure.

17. In the flight compartment, install the kept aft and mid center ceiling linings and the ceiling linings 

adjacent and forward of the P6 Load Control Center. Refer to 737-100/200 AMM 25-16-11 as an 

accepted procedure.

18. In the flight compartment, put the first officer’s seat back to its usual position. Refer to 737-100/

200 AMM 25-11-0 as an accepted procedure.

19. In the NLG wheel well, install the kept right side access panels, 3103R and 3105R. Refer to 

737-100/200 AMM 12-31-11 for panel locations.

20. In the E/E bay, install the kept moisture shroud above the E3 rack. Refer 737-100/200 AMM 

25-51-01 as an accepted procedure.

21. Do the steps below as applicable:

a. For airplanes with airstairs, in the E/E bay, install the kept drip pan. Refer to 737-100/200 

AMM 25-51-01 as an accepted procedure.

b. For airplanes without airstairs, in the E/E bay, install the kept moisture shroud above the 

access door. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes with airstairs, do the forward airstairs retraction. Refer to 737-100/200 AMM 

52-61-0 or 737-100/200 AMM 52-61-100 as an accepted procedure.

22. In the E/E bay, connect the battery power cables to the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

23. Restore electrical power to the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

24. Do the Fuel Control System Functional Test that follows to make sure the changed fuel control 

system operates correctly:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (CENTER TANKS)

a. Make sure the center fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 kilograms) 

of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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ALERT ALERT

c. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Center-Left position.

f. At the P5-2 panel, make sure that the Center Left Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Center Left Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Center-Right position.

j. At the P5-2 panel, make sure that the Center Right Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Center Right Low Pressure Light goes out.

m. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the 

OFF position.

n. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

Relay Position Voltage

R3334 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3336 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3334 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm
 

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q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

25. At the lower forward fuselage, below the E/E bay, close the access door. Refer to 737-100/200 

AMM 52-48-41 as an accepted procedure.

26. Put the airplane back to a serviceable condition.

Group 3: 

1. At the lower forward fuselage, below the E/E bay, open the access door to get access to the work 

area. Refer to 737-300/400/500 AMM 52-48-41 as an accepted procedure.

2. Do the steps below as applicable:

a. For airplanes with airstairs, do the forward airstairs extension to give better access to the 

work area. Refer to 737-300/400/500 AMM 52-61-10 as an accepted procedure.

b. For airplanes with airstairs, in the E/E bay, remove and keep the drip pan to get better 

access to the work area. Refer to 737-300/400/500 AMM 25-51-01 as an accepted 

procedure.

c. For airplanes without airstairs, in the E/E bay, remove and keep the moisture shroud from 

above the access door to get better access to the work area. Refer to 737-300/400/500 

AMM 25-51-01 as an accepted procedure.

3. Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an 

accepted procedure.

4. In the E/E bay, remove and keep the moisture shroud from above the E3 rack to get access to 

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

5. In the E/E bay, disconnect the battery power cables from the battery. Refer to 737-300/400/500 

AMM 24-31-11 as an accepted procedure.

6. Install the Nose Landing Gear (NLG) ground lock. Refer to 737-300/400/500 AMM 32-00-01 as 

an accepted procedure.

R3336 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320

Relay Position Resistance
 

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ALERT ALERT

7. In the NLG wheel well, remove and keep the right side access panels, 3103R and 3105R to get 

access to the work area. Refer to 737-300/400/500 AMM 12-31-11 for panel locations.

8. In the flight compartment, move the first officer’s seat to the forward position to get better access 

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

9. In the flight compartment, remove and keep aft and mid center ceiling linings and the ceiling 

linings adjacent and forward of the P6 Load Control Center to get access to the work area. Refer 

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

10. In the passenger compartment, as applicable, loosen and move the forward galley (galley no.1) 

in an aft direction to get access to the wire routing of the P6 Load Control Center. Refer to 

737-300/400/500 AMM 25-31-11 as an accepted procedure.

11. At the E2 and E3 support post in the E/E bay, remove the cover from the J2802 box assembly 

and install new toggle switches and relays in accordance with Figure 1.

12. Install and connect the W1760 and W1770 wire bundles in the J2802 box assembly in 

accordance with Figure 2 thru Figure 4.

13. Between the P6 disconnect panels and the J2802 box assembly, make changes to wire bundles 

W0368, W0386, W1764 and W1774 in accordance with Figures 12 thru 14.

14. Do a continuity check between the P6 disconnect panels ’AP0600B’, ’AP1800A’ and the J2802 

box assembly to make sure that the wiring connections are made correctly.

15. At the E2 and E3 support post in the E/E bay, install the cover on the J2802 box assembly in 

accordance with Figure 30.

16. In the passenger compartment, as applicable, move the forward galley (galley no.1) back to its 

position. Refer to 737-300/400/500 AMM 25-31-11 as an accepted procedure.

17. In the flight compartment, install the kept aft and mid center ceiling linings and the ceiling linings 

adjacent and forward of the P6 Load Control Center. Refer to 737-300/400/500 AMM 25-11-21 

as an accepted procedure.

18. In the flight compartment, put the first officer’s seat back to its usual position. Refer to 737-300/

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

19. In the NLG wheel well, install the kept right side access panels, 3103R and 3105R. Refer to 

737-300/400/500 AMM 12-31-11 for panel locations.

20. In the E/E bay, install the kept moisture shroud above the E3 rack. Refer 737-300/400/500 AMM 

25-51-01 as an accepted procedure.

21. Do the steps below as applicable:

a. For airplanes with airstairs, in the E/E bay, install the kept drip pan. Refer to 737-300/400/

500 AMM 25-51-01 as an accepted procedure.

b. For airplanes without airstairs, in the E/E bay, install the kept moisture shroud above the 

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

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ALERT ALERT

c. For airplanes with airstairs, do the forward airstairs retraction. Refer to 737-300/400/500 

AMM 52-61-10 as an accepted procedure.

22. In the E/E bay, connect the battery power cables to the battery. Refer to 737-300/400/500 AMM 

24-31-11 as an accepted procedure.

23. Restore electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an 

accepted procedure.

24. Do the Fuel Control System Functional Test that follows to make sure the changed fuel control 

system operates correctly:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (CENTER TANKS)

a. Make sure the center fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 kilograms) 

of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Center-Left position.

f. At the P5-2 panel, make sure that the Center Left Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Center Left Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Center-Right position.

j. At the P5-2 panel, make sure that the Center Right Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Center Right Low Pressure Light goes out.

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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ALERT ALERT

m. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the 

OFF position.

n. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

25. At the lower forward fuselage, below the E/E bay, close the access door. Refer to 737-300/400/

500 AMM 52-48-41 as an accepted procedure.

26. Put the airplane back to a serviceable condition.

Group 4: 

1. At the lower forward fuselage, below the E/E bay, open the access door to get access to the work 

area. Refer to 737-100/200 AMM 52-48-41 as an accepted procedure.

Relay Position Voltage

R3334 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3336 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3334 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3336 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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2. Do the steps below as applicable:

a. For airplanes with airstairs, do the forward airstairs extension to give better access to the 

work area. Refer to 737-100/200 AMM 52-61-0 or 737-100/200 AMM 52-61-100 as an 

accepted procedure.

b. For airplanes with airstairs, in the E/E bay, remove and keep the drip pan to get better 

access to the work area. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes without airstairs, in the E/E bay, remove and keep the moisture shroud from 

above the access door to get better access to the work area. Refer to 737-100/200 AMM 

25-51-01 as an accepted procedure.

3. Remove electrical power from the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

4. In the E/E bay, remove and keep the moisture shroud from above the E3 rack to get access to 

the work area. Refer 737-100/200 AMM 25-51-01 as an accepted procedure.

5. In the E/E bay, disconnect the battery power cables from the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

6. Install the Nose Landing Gear (NLG) ground lock. Refer to 737-100/200 AMM 32-00-01 as an 

accepted procedure.

7. In the NLG wheel well, remove and keep the right side access panels, 3103R and 3105R to get 

access to the work area. Refer to 737-100/200 AMM 12-31-11 for panel locations.

8. In the flight compartment, move the first officer’s seat to the forward position to get better access 

to the work area. Refer to 737-100/200 AMM 25-11-0 as an accepted procedure.

9. In the flight compartment, remove and keep aft and mid center ceiling linings and the ceiling 

linings adjacent and forward of the P6 Load Control Center to get access to the work area. Refer 

to 737-100/200 AMM 25-16-11 as an accepted procedure.

10. In the passenger compartment, as applicable, loosen and move the forward galley (galley no.1) 

in an aft direction to get access to the wire routing of the P6 Load Control Center. Refer to 

737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted procedure.

11. At the E2 and E3 support post in the E/E bay, remove the cover from the J2802 box assembly 

and install new toggle switches and relays in accordance with Figure 1.

12. Install and connect the W1760 and W1770 wire bundles in the J2802 box assembly in 

accordance with Figure 2 thru Figure 4.

13. Between the P6 disconnect panels and the J2802 box assembly, make changes to wire bundles 

W0368, W0386, W1764 and W1774 in accordance with Figures 15 thru 17.

14. Do a continuity check between the P6 disconnect panels panel ’E’, ’A’ and the J2802 box 

assembly to make sure that the wiring connections are made correctly. 

15. At the E2 and E3 support post in the E/E bay, install the cover on the J2802 box assembly in 

accordance with Figure 30.
 

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16. In the passenger compartment, as applicable, move the forward galley (galley no.1) back to its 

position. Refer to 737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted 

procedure.

17. In the flight compartment, install the kept aft and mid center ceiling linings and the ceiling linings 

adjacent and forward of the P6 Load Control Center. Refer to 737-100/200 AMM 25-16-11 as an 

accepted procedure.

18. In the flight compartment, put the first officer’s seat back to its usual position. Refer to 737-100/

200 AMM 25-11-0 as an accepted procedure.

19. In the NLG wheel well, install the kept right side access panels, 3103R and 3105R. Refer to 

737-100/200 AMM 12-31-11 for panel locations.

20. In the E/E bay, install the kept moisture shroud above the E3 rack. Refer 737-100/200 AMM 

25-51-01 as an accepted procedure.

21. Do the steps below as applicable:

a. For airplanes with airstairs, in the E/E bay, install the kept drip pan. Refer to 737-100/200 

AMM 25-51-01 as an accepted procedure.

b. For airplanes without airstairs, in the E/E bay, install the kept moisture shroud above the 

access door. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes with airstairs, do the forward airstairs retraction. Refer to 737-100/200 AMM 

52-61-0 or 737-100/200 AMM 52-61-100 as an accepted procedure.

22. In the E/E bay, connect the battery power cables to the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

23. Restore electrical power to the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

24. Do the Fuel Control System Functional Test that follows to make sure the changed fuel control 

system operates correctly:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (CENTER TANKS)

a. Make sure the center fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 kilograms) 

of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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ALERT ALERT

c. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Center-Left position.

f. At the P5-2 panel, make sure that the Center Left Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Center Left Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Center-Right position.

j. At the P5-2 panel, make sure that the Center Right Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Center Right Low Pressure Light goes out.

m. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the 

OFF position.

n. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

Relay Position Voltage

R3334 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3336 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3334 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm
 

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q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

25. At the lower forward fuselage, below the E/E bay, close the access door. Refer to 737-100/200 

AMM 52-48-41 as an accepted procedure.

26. Put the airplane back to a serviceable condition.

Group 5: 

1. At the lower forward fuselage, below the E/E bay, open the access door to get access to the work 

area. Refer to 737-300/400/500 AMM 52-48-41 as an accepted procedure.

2. Do the steps below as applicable:

a. For airplanes with airstairs, do the forward airstairs extension to give better access to the 

work area. Refer to 737-300/400/500 AMM 52-61-00 or 737-300/400/500 AMM 52-61-10 as 

an accepted procedure.

b. For airplanes with airstairs, in the E/E bay, remove and keep the drip pan to get better 

access to the work area. Refer to 737-300/400/500 AMM 25-51-01 as an accepted 

procedure.

c. For airplanes without airstairs, in the E/E bay, remove and keep the moisture shroud from 

above the access door to get better access to the work area. Refer to 737-300/400/500 

AMM 25-51-01 as an accepted procedure.

3. Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an 

accepted procedure.

4. In the E/E bay, remove and keep the moisture shroud from above the E3 rack to get access to 

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

5. In the E/E bay, disconnect the battery power cables from the battery. Refer to 737-300/400/500 

AMM 24-31-11 as an accepted procedure.

6. Install the Nose Landing Gear (NLG) ground lock. Refer to 737-300/400/500 AMM 32-00-01 as 

an accepted procedure.

R3336 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320

Relay Position Resistance
 

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7. In the NLG wheel well, remove and keep the right side access panels, 3103R and 3105R to get 

access to the work area. Refer to 737-300/400/500 AMM 12-31-11 for panel locations.

8. In the flight compartment, move the first officer’s seat to the forward position to get better access 

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

9. In the flight compartment, remove and keep aft and mid center ceiling linings and the ceiling 

linings adjacent and forward of the P6 Load Control Center to get access to the work area. Refer 

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

10. In the passenger compartment, as applicable, loosen and move the forward galley (galley no.1) 

in an aft direction to get access to the wire routing of the P6 Load Control Center. Refer to 

737-300/400/500 AMM 25-31-11 as an accepted procedure.

11. At the E2 and E3 support post in the E/E bay, remove the cover from the J2802 box assembly 

and install new toggle switches and relays in accordance with Figure 5.

12. Install and connect the W1760 and W1770 wire bundles in the J2802 box assembly in 

accordance with Figure 6 thru 8.

13. Between the P6 disconnect panels and the J2802 box assembly, make changes to wire bundles 

W0368, W0386, W1034, W1046, W1764 and W1774 in accordance with Figures 18 thru 20.

14. Do a continuity check between the P6 disconnect panels ’AP0600B’, ’AP1800A’ and the J2802 

box assembly to make sure that the wiring connections are made correctly. 

15. At the E2 and E3 support post in the E/E bay, install the cover on the J2802 box assembly in 

accordance with Figure 30.

16. In the passenger compartment, as applicable, move the forward galley (galley no.1) back to its 

position. Refer to 737-300/400/500 AMM 25-31-11 as an accepted procedure.

17. In the flight compartment, install the kept aft and mid center ceiling linings and the ceiling linings 

adjacent and forward of the P6 Load Control Center. Refer to 737-300/400/500 AMM 25-11-21 

as an accepted procedure.

18. In the flight compartment, put the first officer’s seat back to its usual position. Refer to 737-300/

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

19. In the NLG wheel well, install the kept right side access panels, 3103R and 3105R. Refer to 

737-300/400/500 AMM 12-31-11 for panel locations.

20. In the E/E bay, install the kept moisture shroud above the E3 rack. Refer 737-300/400/500 AMM 

25-51-01 as an accepted procedure.

21. Do the steps below as applicable:

a. For airplanes with airstairs, in the E/E bay, install the kept drip pan. Refer to 737-300/400/

500 AMM 25-51-01 as an accepted procedure.

b. For airplanes without airstairs, in the E/E bay, install the kept moisture shroud above the 

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

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c. For airplanes with airstairs, do the forward airstairs retraction. Refer to 737-300/400/500 

AMM 52-61-10 as an accepted procedure.

22. In the E/E bay, connect the battery power cables to the battery. Refer to 737-300/400/500 AMM 

24-31-11 as an accepted procedure.

23. Restore electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an 

accepted procedure.

24. Do the Fuel Control System Functional Tests that follow to make sure the changed fuel control 

system operates correctly:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (CENTER TANKS)

a. Make sure the center fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 kilograms) 

of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Center-Left position.

f. At the P5-2 panel, make sure that the Center Left Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Center Left Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Center-Right position.

j. At the P5-2 panel, make sure that the Center Right Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Center Right Low Pressure Light goes out.

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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ALERT ALERT

m. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the 

OFF position.

n. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (AUXILIARY TANKS)

a. Make sure the auxiliary fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 

kilograms) of fuel.

Relay Position Voltage

R3334 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3336 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3334 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3336 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Aux-Aft position.

f. At the P5-2 panel, make sure that the Auxiliary Aft Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324)

h. At the P5-2 panel, make sure that the Auxiliary Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Aux-Fwd position.

j. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326)

l. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light goes out.

m. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the OFF 

position.

n. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329

Relay Position Voltage

R3340 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC
 

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p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

25. At the lower forward fuselage, below the E/E bay, close the access door. Refer to 737-300/400/

500 AMM 52-48-41 as an accepted procedure.

26. Put the airplane back to a serviceable condition.

Group 6: 

1. At the lower forward fuselage, below the E/E bay, open the access door to get access to the work 

area. Refer to 737-300/400/500 AMM 52-48-41 as an accepted procedure.

2. Do the steps below as applicable:

a. For airplanes with airstairs, do the forward airstairs extension to give better access to the 

work area. Refer to 737-300/400/500 AMM 52-61-00 or 737-300/400/500 AMM 52-61-10 as 

an accepted procedure.

b. For airplanes with airstairs, in the E/E bay, remove and keep the drip pan to get better 

access to the work area. Refer to 737-300/400/500 AMM 25-51-01 as an accepted 

procedure.

R3338 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3340 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3338 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329

Relay Position Voltage
 

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c. For airplanes without airstairs, in the E/E bay, remove and keep the moisture shroud from 

above the access door to get better access to the work area. Refer to 737-300/400/500 

AMM 25-51-01 as an accepted procedure.

3. Remove electrical power from the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an 

accepted procedure.

4. In the E/E bay, remove and keep the moisture shroud from above the E3 rack to get access to 

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

5. In the E/E bay, disconnect the battery power cables from the battery. Refer to 737-300/400/500 

AMM 24-31-11 as an accepted procedure.

6. Install the Nose Landing Gear (NLG) ground lock. Refer to 737-300/400/500 AMM 32-00-01 as 

an accepted procedure.

7. In the NLG wheel well, remove and keep the right side access panels, 3103R and 3105R to get 

access to the work area. Refer to 737-300/400/500 AMM 12-31-11 for panel locations.

8. In the flight compartment, move the first officer’s seat to the forward position to get better access 

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

9. In the flight compartment, remove and keep aft and mid center ceiling linings and the ceiling 

linings adjacent and forward of the P6 Load Control Center to get access to the work area. Refer 

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

10. In the passenger compartment, as applicable, loosen and move the forward galley (galley no.1) 

in an aft direction to get access to the wire routing of the P6 Load Control Center. Refer to 

737-300/400/500 AMM 25-31-11 as an accepted procedure.

11. At the E2 and E3 support post in the E/E bay, remove the cover from the J2802 box assembly 

and install new toggle switches and relays in accordance with Figure 5.

12. Install and connect the W1760 and W1770 wire bundles in the J2802 box assembly in 

accordance with Figure 6 thru 8.

13. Between the P6 disconnect panels and the J2802 box assembly, make changes to wire bundles 

W0368, W0386, W1034, W1046, W1764 and W1774 in accordance with Figures 21 thru 23.

14. Do a continuity check between the P6 disconnect panels ’AP0600B’, ’AP0600D’, ’AP1800A’ and 

the J2802 box assembly to make sure that the wiring connections are made correctly. 

15. At the E2 and E3 support post in the E/E bay, install the cover on the J2802 box assembly in 

accordance with Figure 30.

16. In the passenger compartment, as applicable, move the forward galley (galley no.1) back to its 

position. Refer to 737-300/400/500 AMM 25-31-11 as an accepted procedure.

17. In the flight compartment, install the kept aft and mid center ceiling linings and the ceiling linings 

adjacent and forward of the P6 Load Control Center. Refer to 737-300/400/500 AMM 25-11-21 

as an accepted procedure.
 

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18. In the flight compartment, put the first officer’s seat back to its usual position. Refer to 737-300/

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

19. In the NLG wheel well, install the kept right side access panels, 3103R and 3105R. Refer to 

737-300/400/500 AMM 12-31-11 for panel locations.

20. In the E/E bay, install the kept moisture shroud above the E3 rack. Refer to 737-300/400/500 

AMM 25-51-01 as an accepted procedure.

21. Do the steps below as applicable:

a. For airplanes with airstairs, in the E/E bay, install the kept drip pan. Refer to 737-300/400/

500 AMM 25-51-01 as an accepted procedure.

b. For airplanes without airstairs, in the E/E bay, install the kept moisture shroud above the 

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

c. For airplanes with airstairs, do the forward airstairs retraction. Refer to 737-300/400/500 

AMM 52-61-10 as an accepted procedure.

22. In the E/E bay, connect the battery power cables to the battery. Refer to 737-300/400/500 AMM 

24-31-11 as an accepted procedure.

23. Restore electrical power to the airplane. Refer to 737-300/400/500 AMM 24-22-00 as an 

accepted procedure.

24. Do the Fuel Control System Functional Tests that follow to make sure the changed fuel control 

system operates correctly:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (CENTER TANKS)

a. Make sure the center fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 kilograms) 

of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Center-Left position.

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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ALERT ALERT

f. At the P5-2 panel, make sure that the Center Left Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Center Left Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Center-Right position.

j. At the P5-2 panel, make sure that the Center Right Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Center Right Low Pressure Light goes out.

m. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the 

OFF position.

n. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

Relay Position Voltage

R3334 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3336 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3334 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3336 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm
 

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q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (AUXILIARY TANKS)

a. Make sure the auxiliary fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 

kilograms) of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Aux-Aft position.

f. At the P5-2 panel, make sure that the Auxiliary Aft Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324)

h. At the P5-2 panel, make sure that the Auxiliary Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Aux-Fwd position.

j. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326)

l. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light goes out.

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329
 

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m. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the OFF 

position.

n. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

25. At the lower forward fuselage, below the E/E bay, close the access door. Refer to 737-300/400/

500 AMM 52-48-41 as an accepted procedure.

26. Put the airplane back to a serviceable condition.

Group 7: 

1. At the lower forward fuselage, below the E/E bay, open the access door to get access to the work 

area. Refer to 737-100/200 AMM 52-48-41 as an accepted procedure.

Relay Position Voltage

R3340 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3338 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3340 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3338 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329
 

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2. Do the steps below as applicable:

a. For airplanes with airstairs, do the forward airstairs extension to give better access to the 

work area. Refer to 737-100/200 AMM 52-61-0 or 737-100/200 AMM 52-61-100 as an 

accepted procedure.

b. For airplanes with airstairs, in the E/E bay, remove and keep the drip pan to get better 

access to the work area. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes without airstairs, in the E/E bay, remove and keep the moisture shroud from 

above the access door to get better access to the work area. Refer to 737-100/200 AMM 

25-51-01 as an accepted procedure.

3. Remove electrical power from the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

4. In the E/E bay, remove and keep the moisture shroud from above the E3 rack to get access to 

the work area. Refer 737-100/200 AMM 25-51-01 as an accepted procedure.

5. In the E/E bay, disconnect the battery power cables from the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

6. Install the Nose Landing Gear (NLG) ground lock. Refer to 737-100/200 AMM 32-00-01 as an 

accepted procedure.

7. In the NLG wheel well, remove and keep the right side access panels, 3103R and 3105R to get 

access to the work area. Refer to 737-100/200 AMM 12-31-11 for panel locations.

8. In the flight compartment, move the first officer’s seat to the forward position to get better access 

to the work area. Refer to 737-100/200 AMM 25-11-0 as an accepted procedure.

9. In the flight compartment, remove and keep aft and mid center ceiling linings and the ceiling 

linings adjacent and forward of the P6 Load Control Center to get access to the work area. Refer 

to 737-100/200 AMM 25-16-11 as an accepted procedure.

10. In the passenger compartment, as applicable, loosen and move the forward galley (galley no.1) 

in an aft direction to get access to the wire routing of the P6 Load Control Center. Refer to 

737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted procedure.

11. At the E2 and E3 support post in the E/E bay, remove the cover from the J2802 box assembly 

and install new toggle switches and relays in accordance with Figure 5.

12. Install and connect the W1760 and W1770 wire bundles in the J2802 box assembly in 

accordance with Figure 6 thru 8.

13. Between the P6 disconnect panels and the J2802 box assembly, make changes to wire bundles 

W0368, W0386, W1034, W1046, W1764 and W1774 in accordance with Figures 24 thru 26.

14. Do a continuity check between the P6 disconnect panels ’E’, ’A’ and the J2802 box assembly to 

make sure that the wiring connections are made correctly. 

15. At the E2 and E3 support post in the E/E bay, install the cover on the J2802 box assembly in 

accordance with Figure 30.
 

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16. In the passenger compartment, as applicable, move the forward galley (galley no.1) back to its 

position. Refer to 737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted 

procedure.

17. In the flight compartment, install the kept aft and mid center ceiling linings and the ceiling linings 

adjacent and forward of the P6 Load Control Center. Refer to 737-100/200 AMM 25-16-11 as an 

accepted procedure.

18. In the flight compartment, put the first officer’s seat back to its usual position. Refer to 737-100/

200 AMM 25-11-0 as an accepted procedure.

19. In the NLG wheel well, install the kept right side access panels, 3103R and 3105R. Refer to 

737-100/200 AMM 12-31-11 for panel locations.

20. In the E/E bay, install the kept moisture shroud above the E3 rack. Refer 737-100/200 AMM 

25-51-01 as an accepted procedure.

21. Do the steps below as applicable:

a. For airplanes with airstairs, in the E/E bay, install the kept drip pan. Refer to 737-100/200 

AMM 25-51-01 as an accepted procedure.

b. For airplanes without airstairs, in the E/E bay, install the kept moisture shroud above the 

access door. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes with airstairs, do the forward airstairs retraction. Refer to 737-100/200 AMM 

52-61-0 or 737-100/200 AMM 52-61-100 as an accepted procedure.

22. In the E/E bay, connect the battery power cables to the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

23. Restore electrical power to the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

24. Do the Fuel Control System Functional Tests that follow to make sure the changed fuel control 

system operates correctly:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (CENTER TANKS)

a. Make sure the center fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 kilograms) 

of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320
 

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c. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Center-Left position.

f. At the P5-2 panel, make sure that the Center Left Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324)

h. At the P5-2 panel, make sure that the Center Left Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Center-Right position.

j. At the P5-2 panel, make sure that the Center Right Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326)

l. At the P5-2 panel, make sure that the Center Right Low Pressure Light goes out.

m. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the 

OFF position.

n. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

Relay Position Voltage

R3334 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3336 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3334 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm
 

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q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (AUXILIARY TANKS)

a. Make sure the auxiliary fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 

kilograms) of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Aux-Aft position.

f. At the P5-2 panel, make sure that the Auxiliary Aft Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Auxiliary Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Aux-Fwd position.

j. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light comes on.

R3336 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329

Relay Position Resistance
 

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k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light goes out.

m. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the OFF 

position.

n. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

25. At the lower forward fuselage, below the E/E bay, close the access door. Refer to 737-100/200 

AMM 52-48-41 as an accepted procedure.

26. Put the airplane back to a serviceable condition.

Relay Position Voltage

R3340 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3338 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3340 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3338 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329
 

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Group 8: 

1. At the lower forward fuselage, below the E/E bay, open the access door to get access to the work 

area. Refer to 737-100/200 AMM 52-48-41 as an accepted procedure.

2. Do the steps below as applicable:

a. For airplanes with airstairs, do the forward airstairs extension to give better access to the 

work area. Refer to 737-100/200 AMM 52-61-0 or 737-100/200 AMM 52-61-100 as an 

accepted procedure.

b. For airplanes with airstairs, in the E/E bay, remove and keep the drip pan to get better 

access to the work area. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes without airstairs, in the E/E bay, remove and keep the moisture shroud from 

above the access door to get better access to the work area. Refer to 737-100/200 AMM 

25-51-01 as an accepted procedure.

3. Remove electrical power from the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

4. In the E/E bay, remove and keep the moisture shroud from above the E3 rack to get access to 

the work area. Refer 737-100/200 AMM 25-51-01 as an accepted procedure.

5. In the E/E bay, disconnect the battery power cables from the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

6. Install the Nose Landing Gear (NLG) ground lock. Refer to 737-100/200 AMM 32-00-01 as an 

accepted procedure.

7. In the NLG wheel well, remove and keep the right side access panels, 3103R and 3105R to get 

access to the work area. Refer to 737-100/200 AMM 12-31-11 for panel locations.

8. In the flight compartment, move the first officer’s seat to the forward position to get better access 

to the work area. Refer to 737-100/200 AMM 25-11-0 as an accepted procedure.

9. In the flight compartment, remove and keep aft and mid center ceiling linings and the ceiling 

linings adjacent and forward of the P6 Load Control Center to get access to the work area. Refer 

to 737-100/200 AMM 25-16-11 as an accepted procedure.

10. In the passenger compartment, as applicable, loosen and move the forward galley (galley no.1) 

in an aft direction to get access to the wire routing of the P6 Load Control Center. Refer to 

737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted procedure.

11. At the E2 and E3 support post in the E/E bay, remove the cover from the J2802 box assembly 

and install new toggle switches and relays in accordance with Figure 5.

12. Install and connect the W1760 and W1770 wire bundles in the J2802 box assembly in 

accordance with Figure 6 thru 8.

13. Between the P6 disconnect panels and the J2802 box assembly, make changes to wire bundles 

W0368, W0386, W1034, W1046, W1764 and W1774 in accordance with Figures 27 thru 29.
 

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14. Do a continuity check between the P6 disconnect panels ’E’, ’A’ and the J2802 box assembly to 

make sure that the wiring connections are made correctly. 

15. At the E2 and E3 support post in the E/E bay, install the cover on the J2802 box assembly in 

accordance with Figure 30.

16. In the passenger compartment, as applicable, move the forward galley (galley no.1) back to its 

position. Refer to 737-100/200 AMM 25-31-11 or 737-100/200 AMM 25-31-51 as an accepted 

procedure.

17. In the flight compartment, install the kept aft and mid center ceiling linings and the ceiling linings 

adjacent and forward of the P6 Load Control Center. Refer to 737-100/200 AMM 25-16-11 as an 

accepted procedure.

18. In the flight compartment, put the first officer’s seat back to its usual position. Refer to 737-100/

200 AMM 25-11-0 as an accepted procedure.

19. In the NLG wheel well, install the kept right side access panels, 3103R and 3105R. Refer to 

737-100/200 AMM 12-31-11 for panel locations.

20. In the E/E bay, install the kept moisture shroud above the E3 rack. Refer 737-100/200 AMM 

25-51-01 as an accepted procedure.

21. Do the steps below as applicable:

a. For airplanes with airstairs, in the E/E bay, install the kept drip pan. Refer to 737-100/200 

AMM 25-51-01 as an accepted procedure.

b. For airplanes without airstairs, in the E/E bay, install the kept moisture shroud above the 

access door. Refer to 737-100/200 AMM 25-51-01 as an accepted procedure.

c. For airplanes with airstairs, do the forward airstairs retraction. Refer to 737-100/200 AMM 

52-61-0 or 737-100/200 AMM 52-61-100 as an accepted procedure.

22. In the E/E bay, connect the battery power cables to the battery. Refer to 737-100/200 AMM 

24-31-11 as an accepted procedure.

23. Restore electrical power to the airplane. Refer to 737-100/200 AMM 24-22-0 as an accepted 

procedure.

24. Do the Fuel Control System Functional Tests that follow to make sure the changed fuel control 

system operates correctly:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (CENTER TANKS)

a. Make sure the center fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 kilograms) 

of fuel.
 

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b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights come on and then go out.

e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Center-Left position.

f. At the P5-2 panel, make sure that the Center Left Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Center Left Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Center-Right position.

j. At the P5-2 panel, make sure that the Center Right Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Center Right Low Pressure Light goes out.

m. At the P5-2 panel, put the Center Tank Left and Center Tank Right pump switches to the 

OFF position.

n. At the P5-2 panel, make sure that the Center Tank Left and Center Tank Right pump Low 

Pressure Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320

Relay Position Voltage

R3334 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC
 

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p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and open the 

circuit breakers that follow:

FUEL CONTROL SYSTEM FUNCTIONAL TEST (AUXILIARY TANKS)

a. Make sure the auxiliary fuel tank has a minimum of 1000 - 1200 pounds (450 - 540 

kilograms) of fuel.

b. At the J2802 junction box in the E/E bay, open the circuit breakers that follow and attach 

DO-NOT-CLOSE tags:

c. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the ON 

position.

d. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights come on and then go out.

R3336 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3334 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3336 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK LEFT

C3318

J2802 FUEL CONTROL AUTO SHUTOFF CENTER 

TANK RIGHT

C3320

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329

Relay Position Voltage
 

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e. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3324) to the Aux-Aft position.

f. At the P5-2 panel, make sure that the Auxiliary Aft Low Pressure Light comes on.

g. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3324).

h. At the P5-2 panel, make sure that the Auxiliary Low Pressure Light goes out.

i. At the J2802 junction box in the E/E bay, push and hold the Pump Un-Commanded On Test 

Switch (S3326) to the Aux-Fwd position.

j. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light comes on.

k. At the J2802 junction box in the E/E bay, release the Pump Un-Commanded On Test Switch 

(S3326).

l. At the P5-2 panel, make sure that the Auxiliary Fwd Low Pressure Light goes out.

m. At the P5-2 panel, put the Aux Tank Aft and Aux Tank Fwd pump switches to the OFF 

position.

n. At the P5-2 panel, make sure that the Aux Tank Aft and Aux Tank Fwd pump Low Pressure 

Lights are off.

o. At the J2802 junction box in the E/E bay, check the voltage at the relay terminals that follow:

p. At the J2802 junction box in the E/E bay, check the resistance between the relay terminals 

that follow:

Relay Position Voltage

R3340 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

R3338 A2 to ground Less than 10 Volts AC

B2 to ground Less than 10 Volts AC

C2 to ground Less than 10 Volts AC

Relay Position Resistance

R3340 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm

R3338 A2 to A1 Greater than 1 megohm

B2 to B1 Greater than 1 megohm

C2 to C1 Greater than 1 megohm
 

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

q. At the J2802 junction box in the E/E bay, remove the DO-NOT-CLOSE tags and close the 

circuit breakers that follow:

25. At the lower forward fuselage, below the E/E bay, close the access door. Refer to 737-100/200 

AMM 52-48-41 as an accepted procedure.

26. Put the airplane back to a serviceable condition.

Panel Location/

Position

Name Circuit Breaker

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

AFT

C3327

J2802 FUEL CONTROL AUTO SHUTOFF AUX TANK 

FWD

C3329
 FIGURE 1: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 1: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION

E3 SUPPORT POST

E2 SUPPORT POST

FWD

3

350

STA

1 2

6 LOCATIONS

U81319

(SHEET 1 OF 2)
 FIGURE 1: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 103 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 2-4: 

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: Get the parts given below from kit 65C38510-1.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep BOLT BACS12HN3-8 6 from the 65C38484-10 

J2802 box assembly. 2 Remove/Keep WASHER NAS1149F0363P 6

3 Remove/Keep COVER 65C38484-5 1

4

Install (New) TOGGLE SWITCH - 

LOCKED IN CENTER 

POSITION

64AT23-7E 2 -

5

Install (New) RELAY 9324-7424 

(MS27418-2B 

optional)

2 -

5

4

5

4

J2802 BOX ASSEMBLY (COVER REMOVED)

1308185

(SHEET 2 OF 2)
 FIGURE 2: WIRE BUNDLE W1760 AND W1770 IN THE J2802 BOX ASSEMBLY - INSTALLATION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 104 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 2: WIRE BUNDLE W1760 AND W1770 IN THE J2802 BOX ASSEMBLY - INSTALLATION

This Figure applies to Group 2-4: 

U81322

J2802 GDY001

D5210J

TB0054

TB0052

GDY002

D5208J

W1770

C3320

S3321

D10968

D10966

S3318

C3318

W1760

TYPICAL

R3336 R3334

S3326 S3324

(SHEET 1 OF 1)
 FIGURE 3: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 3: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

This Figure applies to Group 2-4: 

2 LOCATIONS

3

7

1 2 3

28-23-01

P D5208J

021-18

022-18

023-18

026-18

024-18

025-18

027-20

R3334

C2

B1

B2

RELAY

PUMP UCO

CTR-LEFT

028-20

=B

CTR-LEFT

C3318 FUEL CONT ASO

=L

1

30

32

31

28

(28V DC)

28-23-01

A2

C1

A1

X2

001-20

27

29

X1

10 9

13

13

13

13

3 5

2 LOCATIONS

14

14

14

14

14

14

12 11

6 LOCATIONS

3 4

6 8

6 LOCATIONS

REFERENCE: 737 WIRING DIAGRAM 28-23-01

15

029-20

NOT USED

1NO

SWITCH CTR-L

PUMP UCO TEST

15 SEC

TD

NOT USED

4NO

4NC

OFF

S3324

1C

4C

W1760

28-23-01 3

6

1

8

7

R3318

ASO RELAY

CTR-LEFT

030-20

1NC

CTR-LEFT

GDY1-S

D10966

J2802

STA 349, WL 195, BL 0

MISCELLANEOUS RELAY BOX

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

2 LOCATIONS

U81335

(SHEET 1 OF 3)
 FIGURE 3: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 106 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-103 and 61-74482-103W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, PIN BACC47CN2 6 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D05208J

61-74478-10502 1 Install within 6 inches of equipment. 

3 THERMOFIT 

SLEEVE - 0.093 IN. 

I.D.

61-74482-2006 - Use to terminate wire to contact or 

lug. Refer to SWPM 20-30-17, 

SWPM 20-30-22, and SWPM 

20-60-08 as accepted procedures.

4 TERMINAL, LUG BACT12AC49 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL, LUG BACT12AC2 2 Refer to SWPM 20-30-11 and SWPM 

20-30-22 as accepted procedures.

6 CONTACTS 60789-2 

(640024-1)

2 Refer to SWPM 20-30-17 as an 

accepted procedure.

7 THERMOFIT 

SLEEVE - YELLOW, 

0.125 IN I.D.

61-74482-2014 - Use smallest diameter sleeve over 

wire and contact. Refer to SWPM 

20-30-17 as an accepted procedure.

THERMOFIT 

SLEEVE - YELLOW, 

0.187 IN I.D.

61-74482-2015 -

8 CONTACT BACC47DE7A 1 Refer to SWPM 20-20-11 as an 

acceped procedure.

9 CONTACT, SOCKET BACC47ER1 2 Refer to SWPM 20-81-19 as an 

accepted procedure.

10 CONNECTOR I.D. 

TAPE - D10966

61-74478-10503 1 Install within 6 inches of equipment. 

11 TERMINAL, LUG BACT12AC53 1 Terminate with existing wire. Refer to 

SWPM 20-30-11 and SWPM 

20-30-22 as accepted procedures.

12 THERMOFIT 

SLEEVE - YELLOW, 

0.375 IN I.D.

61-74482-2009 - Use sleeving to insulate wire 

termination to the lug. Refer to 

SWPM 20-30-22 as an accepted 

procedure.

13 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 20

4 Identified as shown. Cut to the 

necessary lengths.

14 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

15 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle 

lengths. Refer to SWPM 20-10-11 as 

an accepted procedure.

(SHEET 2 OF 3)
 FIGURE 3: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 107 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1760 027 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 028 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 029 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 030 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 021 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 022 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 023 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 024 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 025 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 026 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

(SHEET 3 OF 3)
 FIGURE 4: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 108 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 4: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

This Figure applies to Group 2-4: 

6 8

1 3 4

28-23-01

029-20

NOT USED

1NO

SWITCH CTR-R

PUMP UCO TEST

15 SEC

TD

NOT USED

4NO

4NC

OFF

S3326

1C

4C

P D5210J

W1770

28-23-01

021-18

022-18

023-18

3

6

1

8

026-18

024-18

7

R3321

ASO RELAY

CTR-RIGHT

025-18

027-20

R3336

C2

B1

B2

RELAY

PUMP UCO

CTR-RIGHT

028-20

030-20

=B

CTR-RIGHT

C3320 FUEL CONT ASO

=L

1

30

32

31

28

(28V DC)

28-23-01

1NC

CTR-RIGHT

A2

C1

A1

X2

GDY2-S

001-20

27

29

D10968

X1

J2802

STA 349, WL 195, BL 0

MISCELLANEOUS RELAY BOX

6 LOCATIONS

2 3

6 LOCATIONS

14

14

14

14

14

14

12 11

13

13

7

3

2 LOCATIONS

13

13

3 5

2 LOCATIONS

10 9

2 LOCATIONS

15

REFERENCE: 737 WIRING DIAGRAM 28-23-01

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

U81364

(SHEET 1 OF 3)
 FIGURE 4: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 109 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-105 and 61-74482-105W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, PIN BACC47CN2 6 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D05210J

61-74478-10702 1 Install within 6 inches of equipment. 

3 THERMOFIT SLEEVE - 

0.093 IN. I.D.

61-74482-2006 - Use to terminate wire to contact or 

lug. Refer SWPM 20-30-17, SWPM 

20-30-22, and SWPM 20-60-08 as 

accepted procedures.

4 TERMINAL, LUG BACT12AC49 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL, LUG BACT12AC2 2 Refer to SWPM 20-30-11 and 

SWPM 20-30-22 as accepted 

procedures.

6 CONTACTS 60789-2 

(640024-1)

2 Refer to SWPM 20-30-17 as an 

accepted procedure.

7 THERMOFIT SLEEVE - 

YELLOW, 0.125 IN I.D.

61-74482-2014 - Use smallest diameter sleeve over 

wire and contact. Refer to SWPM 

20-30-17 as an accepted 

procedure.

THERMOFIT SLEEVE - 

YELLOW, 0.187 IN I.D.

61-74482-2015 -

8 CONTACT BACC47DE7A 1 Refer to SWPM 20-20-11 as an 

accepted procedure.

9 CONTACT, SOCKET BACC47ER1 2 Refer to SWPM 20-81-19 as an 

accepted procedure. 

10 CONNECTOR I.D. 

TAPE - D10968

61-74478-10703 1 Install within 6 inches of equipment. 

11 TERMINAL, LUG BACT12AC53 1 Terminate with existing wire. Refer 

to SWPM 20-30-11 and SWPM 

20-30-22 as accepted procedures.

12 THERMOFIT SLEEVE - 

YELLOW, 0.375 IN I.D.

61-74482-2009 - Use sleeving to insulate wire 

termination to the lug. Refer to 

SWPM 20-30-22 as an accepted 

procedure.

13 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 20

4 Identified as shown. Cut to the 

necessary lengths.

14 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

15 LACING TAPE - WHITE 61-74482-2001 - Use to tie affected wire bundle 

lengths. Refer to SWPM 20-10-11 

as an accepted procedure.

(SHEET 2 OF 3)
 FIGURE 4: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1770 027 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 028 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 029 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 030 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 021 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 022 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 023 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 024 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 025 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 026 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

(SHEET 3 OF 3)
 FIGURE 5: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 5: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION

E3 SUPPORT POST

E2 SUPPORT POST

FWD

3

350

STA

1 2

6 LOCATIONS

U81348

(SHEET 1 OF 2)
 FIGURE 5: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 112 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 5-8: 

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: Get the parts given below from kit 65C38510-2.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove/Keep BOLT BACS12HN3-8 6 from the 65C38484-11 

J2802 box assembly. 2 Remove/Keep WASHER NAS1149F0363P 6

3 Remove/Keep COVER 65C38484-5 1

4

Install (New) TOGGLE SWITCH - 

LOCKED IN 

CENTER POSITION

64AT23-7E 2 -

5

Install (New) Relay 9324-7424 

(MS27418-2B 

optional)

4 -

5

4

5

4

J2802 BOX ASSEMBLY (COVER REMOVED)

1308184

(SHEET 2 OF 2)
 FIGURE 6: WIRE BUNDLE W1760 AND W1770 IN THE J2802 BOX ASSEMBLY - INSTALLATION

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 6: WIRE BUNDLE W1760 AND W1770 IN THE J2802 BOX ASSEMBLY - INSTALLATION

This Figure applies to Group 5-8: 

J2802 GDY001

D5210J

TB0054

TB0052

GDY002

D5208J

W1770

C3320

S3321

D10968 D10966

S3318

C3318

W1760

D10970

D10972

C3329

R3336 R3338 C3327 R3334

R3340

S3326 S3324

TYPICAL

U81351

(SHEET 1 OF 1)
 FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

28-23-01

029-20

NOT USED

1NO

SWITCH CTR-L

PUMP UCO TEST

15 SEC

TD

AUX-AFT

4NO

4NC

OFF

S3324

1C

4C

P D5208J

W1760

021-18

022-18

023-18

3

6

1

8

026-18

024-18

7

R3318

ASO RELAY

CTR-LEFT

025-18

28-23-01

027-20

R3334

C2

B1

B2

RELAY

PUMP UCO

CTR-LEFT

028-20

030-20

=B

CTR-LEFT

C3318 FUEL CONT ASO

=L

1

30

32

31

28

(28V DC)

28-23-01

1NC

CTR-LEFT

A2

C1

A1

X2

GDY1-S

001-20

27

29

D10966

X1

J2802

STA 349, WL 195, BL 0

MISCELLANEOUS RELAY BOX

1 2 3

6 LOCATIONS

3 4

6 LOCATIONS

15

15

15

15

15

15

12 11

2 LOCATIONS

3

7

6

14

14

3 5

2 LOCATIONS

8

14

14

10 9

2 LOCATIONS

16

REFERENCE: 737 WIRING DIAGRAM 28-23-01

U81357

(SHEET 1 OF 4)
 FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 115 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 5-8: 

REFERENCE: 737 WIRING DIAGRAM 28-23-02

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

28-23-02

38

NOT USED

SWITCH CTR-L

PUMP UCO TEST

15 SEC

TD

AUX-AFT

1NC

OFF

S3324 4NO

4NC

P D5208J

W1760

036-18

35

34

3

6

1

8

034-18

035-18

7

4C

R3327

D10970

031-18

28-23-02

36

R3340

C2

B1

B2

RELAY

PUMP UCO

AUX-AFT

33

37

=B

AUX-AFT

C3327 FUEL CONT ASO

=L

1

037-20

039-20

040-20

033-18

(28V DC)

28-23-02

1NO

CTR-LEFT

A2

C1

A1

X2

GDY1-S

011-20

038-20

032-18

ASO RELAY

AUX-AFT

X1

J2802

STA 349, WL 195, BL 0

MISCELLANEOUS RELAY BOX

1C

1 2 3

6 LOCATIONS

3 4

6 LOCATIONS

15

15

15

15

15

15

12 11

14

14

2 LOCATIONS

3

7

6 8

14

14

3 5

2 LOCATIONS

13 9

2 LOCATIONS

16

U81359

(SHEET 2 OF 4)
 FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 116 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-2, 61-74482-3, 61-74482-104 and 61-74482-104W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, PIN BACC47CN2 12 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D05208J

61-74478-10502 1 Install within 6 inches of equipment. 

3 THERMOFIT 

SLEEVE - 0.093 IN. 

I.D.

61-74485-2008 - Use to terminate wire to contact or lug. 

Refer to SWPM 20-30-17, SWPM 

20-30-22, and SWPM 20-60-08 as 

accepted procedures.

4 TERMINAL, LUG BACT12AC49 12 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL, LUG BACT12AC2 4 Refer to SWPM 20-30-11 and SWPM 

20-30-22 as accepted procedures.

6 CONTACTS 60789-2 

(640024-1)

4 Refer to SWPM 20-30-17 as an 

accepted procedure.

7 THERMOFIT 

SLEEVE - YELLOW, 

0.125 IN I.D.

61-74482-2014 - Use smallest diameter sleeve over 

wire and contact. Refer to SWPM 

20-30-17 as an accepted procedure.

THERMOFIT 

SLEEVE - YELLOW 

0.187 IN I.D.

61-74482-2015 -

8 CONTACT BACC47DE7A 2 Refer to SWPM 20-20-11 as an 

accepted procedure.

9 CONTACT, SOCKET BACC47ER1 4 Refer to SWPM 20-81-19 as an 

accepted procedure.

10 CONNECTOR I.D. 

TAPE - D10966

61-74478-10503 1 Install within 6 inches of equipment. 

11 TERMINAL, LUG BACT12AC53 2 Terminate with existing wire. Refer to 

SWPM 20-30-11 and SWPM 20-30-22 

as accepted procedures.

12 THERMOFIT 

SLEEVE - YELLOW, 

0.375 IN I.D.

61-74482-2009 - Use sleeving to insulate wire 

termination to the lug. Refer to SWPM 

20-30-22 as an accepted procedure.

13 CONNECTOR I.D. 

TAPE - D10970

61-74478-10601 1 Install within 6 inches of equipment. 

14 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 20

8 Identified as shown. Cut to the 

necessary lengths.

15 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

12 Identified as shown. Cut to the 

necessary lengths.

16 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 117 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1760 027 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 028 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 029 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 030 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 037 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 038 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 039 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 040 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1760 021 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 022 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 023 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 024 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 025 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 026 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 031 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 032 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 033 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 034 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 035 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1760 036 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

(SHEET 4 OF 4)
 FIGURE 8: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 118 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 8: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

28-23-01

029-20

NOT USED

1NO

SWITCH CTR-R

PUMP UCO TEST

15 SEC

TD

AUX-FWD

4NO

4NC

OFF

S3326

1C

4C

P D5210J

W1770

28-23-01

021-18

022-18

023-18

3

6

1

8

026-18

024-18

7

R3321

ASO RELAY

CTR-RIGHT

025-18

027-20

R3336

C2

B1

B2

RELAY

PUMP UCO

CTR-RIGHT

028-20

030-20

=B

CTR-RIGHT

C3320 FUEL CONT ASO

=L

1

30

32

31

28

(28V DC)

28-23-01

1NC

CTR-RIGHT

A2

C1

A1

X2

GDY2-S

001-20

27

29

D10968

X1

J2802

STA 349, WL 195, BL 0

MISCELLANEOUS RELAY BOX

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-01

1 2 3

6 LOCATIONS

3 4

6 LOCATIONS

15

15

15

15

15

15

12 11

14

14

3 5

2 LOCATIONS

8

14

14

2 LOCATIONS

3

7

6

10 9

2 LOCATIONS

16

U81611

(SHEET 1 OF 4)
 FIGURE 8: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 119 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 5-8: 

REFERENCE: 737 WIRING DIAGRAM 28-23-02

28-23-02

039-20

NOT USED

4NO

SWITCH CTR-R

PUMP UCO TEST

15 SEC

TD

CTR-RIGHT

1NO

1NC

OFF

S3326

4C

1C

P D5210J

W1770

28-23-02

031-18

032-18

033-18

3

6

1

8

036-18

034-18

7

R3329

ASO RELAY

AUX-FWD

035-18

037-20

R3338

C2

B1

B2

RELAY

PUMP UCO

AUX-FWD

038-20

040-20

=B

AUX-FWD

C3329 FUEL CONT ASO

=L

1

36

38

37

34

(28V DC)

28-23-02

4NC

AUX-FWD

A2

C1

A1

X2

GDY2-S

011-20

33

35

D10972

X1

J2802

STA 349, WL 195, BL 0

MISCELLANEOUS RELAY BOX

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1 2 3

6 LOCATIONS

3 4

6 LOCATIONS

15

15

15

15

15

15

12 11

14

14

3 5

2 LOCATIONS

8

14

14

2 LOCATIONS

3

7

6

13 9

2 LOCATIONS

16

U81612

(SHEET 2 OF 4)
 FIGURE 8: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 120 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-2, 61-74482-3, 61-74482-106 and 61-74482-106W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, PIN BACC47CN2 12 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D05210J

61-74478-10702 1 Install within 6 inches of equipment. 

3 THERMOFIT 

SLEEVE - 0.093 IN. 

I.D.

61-74482-2007 - Use to terminate wire to contact or lug. 

Refer to SWPM 20-30-17, SWPM 

20-30-22, and SWPM 20-60-08 as 

accepted procedures.

4 TERMINAL, LUG BACT12AC49 12 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL, LUG BACT12AC2 4 Refer to SWPM 20-30-11 and SWPM 

20-30-22 as accepted procedures.

6 CONTACTS 60789-2 

(640024-1)

4 Refer to SWPM 20-30-17 as an 

accepted procedure.

7 THERMOFIT 

SLLEVE - YELLOW, 

0.125 IN I.D.

61-74482-2014 - Use smallest diameter sleeve over wire 

and contact. Refer to SWPM 20-30-17 

as an accepted procedure.

THERMOFIT 

SLLEVE - YELLOW, 

0.187 IN I.D.

61-74482-2015 -

8 CONTACT BACC47DE7A 2 Refer to SWPM 20-20-11 as an 

accepted procedure.

9 CONTACT, SOCKET BACC47ER1 4 Refer to SWPM 20-81-19 as an 

accepted procedure.

10 CONNECTOR I.D. 

TAPE - D10968

61-74478-10703 1 Install within 6 inches of equipment. 

11 TERMINAL, LUG BACT12AC53 2 Terminate with existing wire. Refer to 

SWPM 20-30-11 and SWPM 20-30-22 

as accepted procedures.

12 THERMOFIT 

SLEEVE - YELLOW, 

0.375 IN I.D.

61-74482-2009 - Use sleeving to insulate wire 

termination to the lug. Refer to SWPM 

20-30-22 as an accepted procedure.

13 CONNECTOR I.D. 

TAPE - D10972

61-74478-10801 1 Install within 6 inches of equipment. 

14 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 20

8 Identified as shown. Cut to the 

necessary lengths.

15 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

12 Identified as shown. Cut to the 

necessary lengths.

16 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 8: WIRE BUNDLE W1770 THE J2802 BOX ASSEMBLY - CONNECTION

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 121 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1770 027 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 028 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 029 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 030 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 037 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 038 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 039 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 040 20 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 20

W1770 021 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 022 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 023 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 024 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 025 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 026 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 031 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 032 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 033 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 034 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 035 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1770 036 18 PA 48 BMS 13-48, TYPE 10, CLASS 1, AWG 18

(SHEET 4 OF 4)
 FIGURE 9: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 122 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 9: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

A

FWD

TYPICAL

U81668

PANEL C-3

DISCONNECT

DISCONNECT PANEL

P6 UPPER

W1764

W0368,

PANEL A

DISCONNECT

259.5

STA

294.5

STA

S-3R

S-2R

POS 13

D4202J

(SHEET 1 OF 5)
 FIGURE 9: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

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BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

UPPER RIGHT CAB

FWD

STA 178-277

STA

178

STA

196.5

W1774

W1764,

W1774

U82028

S-2

S-3

S-1

W1764

STA

277

259.5

STA

A

B

D

(SHEET 2 OF 5)
 FIGURE 9: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 124 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

STA

259.5

B

C

U82029

W1774

W1764,

(SHEET 3 OF 5)
 FIGURE 9: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 125 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

C CONNECTOR

D5210P

W1764,

W1774

RBL

20.20

J2802 BOX

ASSEMBLY

W1774

W1764

LBL

12.00

W1764

CONNECTOR

D5208P

U82030

(SHEET 4 OF 5)
 FIGURE 9: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 126 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 2: 

D

DISCONNECT

PANEL E

D4208J

POS 10

W0386,

W1774

P6 LOAD CONTROL CENTER

FWD

U81672

(SHEET 5 OF 5)
 FIGURE 10: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANELS TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 127 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 10: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANELS TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

This Figure applies to Group 2: 

3 LOCATIONS

6 LOCATIONS

3 LOCATIONS

REFERENCE: 737 WIRING DIAGRAM 28-23-01

007-18

008-18

009-18

27

28

29

31

POS 13

D4202P

SP4522

SP4516

4

13

STA 270

DISC

PNL "A"

SP4514

30

32

2

M234

6

D802

W368-

TANK BP

CTR-L

W368-

018-18

016-18

SP880

SP878

017-18

J

14

D5208P

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1764

J2802

SP882

P5

012-18

PANEL

OVHD

J

15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

W368-

10

5

6

1

8

2

3

1

7

4

11

9

9

9

9

9

9

3

U82034

(SHEET 1 OF 2)
 FIGURE 10: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANELS TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 128 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-107 and 61-74482-107W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 9 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10701 1 Install within 6 inches of equipment. 

3 THERMOFIT SLEEVE 

- 0.093 IN. I.D.

61-74482-2006 - Use to build up outer diameter of 

wire. Refer to SWPM 20-60-08 as an 

accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05208P

61-74478-10904 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 3 Locate splices near connector 

D4202J. Refer to SWPM 20-30-12 

as an accepted procedure.

6 SPLICE I.D. SLEEVE - 

SP4514

61-74482-10703 1 -

7 SPLICE I.D. SLEEVE - 

SP4516

61-74482-10704 1 -

8 SPLICE I.D. SLEEVE - 

SP4522

61-74482-10705 1 -

9 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

10 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle 

lengths. Refer to SWPM 20-10-11 as 

an accepted procedure.

11 EXPANDABLE 

SLEEVE - 0.25 IN. I.D.

61-74482-2010 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie each end 

of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1764 007 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 008 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 009 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 010 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 011 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 012 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

(SHEET 2 OF 2)
 FIGURE 11: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 129 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 11: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

This Figure applies to Group 2: 

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

10

SP884

SP888

6

4

9

D5210P

4

007-18

008-18

009-18

023-18 SP886

CTR-R

CNTRL

LOAD

STA 260

DISC

PNL "E"

W386-

27

28

29

31

5

P6

024-18

022-18

POS 10

D4208J P

4

7

5

30

32

2

M235

6

D804

SP4526

TANK BP

CTR-R

SP4528

SP4524

W386-

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1774

J2802

012-18

J

6

W386-

REFERENCE: 737 WIRING DIAGRAM 28-23-01

8

8

8

3 LOCATIONS

8

8

8

6 LOCATIONS

3 1

3 LOCATIONS

2

1

U82036

(SHEET 1 OF 2)
 FIGURE 11: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 130 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-110 and 61-74482-110W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 9 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04208P

61-74482-11003 1 Install within 6 inches of equipment. 

3 CONNECTOR I.D. 

TAPE - D05210P

61-74478-11104 1 Install within 6 inches of equipment. 

4 SPLICE D-436-37 3 Locate splices near connector D4208P. 

Refer to SWPM 20-30-12 as an 

accepted procedure.

5 SPLICE I.D. 

SLEEVE - SP4524

61-74482-11005 1 -

6 SPLICE I.D. 

SLEEVE - SP4526

61-74482-11006 1 -

7 SPLICE I.D. 

SLEEVE - SP4528

61-74482-11007 1 -

8 WIRE BMS 13-58, TYPE 1, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

9 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

10 EXPANDABLE 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2010 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1774 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each end of the 

sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1774 007 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 008 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 009 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 010 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 011 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 012 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

(SHEET 2 OF 2)
 FIGURE 12: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 131 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 12: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

A

FWD

TYPICAL

U82037

PANEL AP0600A

DISCONNECT

DISCONNECT PANEL

P6 UPPER

W1764

W0368,

PANEL AP1800A

DISCONNECT

259.5

STA

294.5

STA

S-3R

S-2R

POS 13

D4202J

(SHEET 1 OF 5)
 FIGURE 12: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 132 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

UPPER RIGHT CAB

FWD

STA 178-277

STA

178

STA

196.5

W1774

W1764, W1774

U82039

S-2

S-3

S-1

W1764

STA

277

259.5

STA

A

B D

(SHEET 2 OF 5)
 FIGURE 12: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 133 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

STA

259.5

B

C

U82040

W1774

W1764,

(SHEET 3 OF 5)
 FIGURE 12: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 134 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

C CONNECTOR

D5210P

W1764,

W1774

RBL

20.20

J2802 BOX

ASSEMBLY

W1774

W1764

LBL

12.00

W1764

CONNECTOR

D5208P

U82041

(SHEET 4 OF 5)
 FIGURE 12: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 135 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 3: 

D

DISCONNECT

PANEL

AP0600B

D4208J

POS 06

W0386,

W1774

P6 LOAD CONTROL CENTER

FWD

U82038

(SHEET 5 OF 5)
 FIGURE 13: WIRE BUNDLE W0368 AND W1764 FROM DISCONNECT PANEL A TO J2802 BOX 

ASSEMBLY - WIRING CHANGES

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 136 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 13: WIRE BUNDLE W0368 AND W1764 FROM DISCONNECT PANEL A TO J2802 BOX 

ASSEMBLY - WIRING CHANGES

This Figure applies to Group 3: 

007-18

008-18

009-18

27

28

29

31

POS 13

D4202P

SP4522

SP4516

4

13

AP1800A

STA 270

DISC

SP4514

30

32

2

M234

6

D802

W368-

TANK BP

CTR-L

W368-

018-18

016-18

SP880

SP878

017-18

J

14

D5208P

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1764

J2802

SP882

P5

012-18

PANEL

OVHD

J

15

W368-

9

9

9

9

9

9

5

6

8

7

3 LOCATIONS

6 LOCATIONS

4 3 1

10 11

3 LOCATIONS

2

1

3

REFERENCE: 737 WIRING DIAGRAM 28-23-01

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

U82042

(SHEET 1 OF 2)
 FIGURE 13: WIRE BUNDLE W0368 AND W1764 FROM DISCONNECT PANEL A TO J2802 BOX 

ASSEMBLY - WIRING CHANGES

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 137 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-107 and 61-74482-107W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 9 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10702 1 Install within 6 inches of equipment. 

3 THERMOFIT SLEEVE 

- 0.093 IN. I.D.

61-74482-2006 - Use to build up outer diameter of 

wire. Refer to SWPM 20-60-08 as 

an accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05208P

61-74478-10904 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 3 Locate splices near connector 

D4202J. Refer to SWPM 20-30-12 

as an accepted procedure.

6 SPLICE I.D. SLEEVE - 

SP4514

61-74482-10703 1 -

7 SPLICE I.D. SLEEVE - 

SP4516

61-74482-10704 1 -

8 SPLICE I.D. SLEEVE - 

SP4522

61-74482-10705 1 -

9 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

10 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle 

lengths. Refer to SWPM 20-10-11 

as an accepted procedure.

11 EXPANDABLE 

SLEEVE - 0.25 IN. I.D.

61-74482-2010 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie each 

end of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1764 007 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 008 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 009 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 010 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 011 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 012 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

(SHEET 2 OF 2)
 FIGURE 14: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGES

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 138 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 14: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGES

This Figure applies to Group 3: 

SP884

SP888

6

4

D5210P

007-18

008-18

009-18

023-18 SP886

CTR-R

CNTRL

LOAD

AP0600B

STA 260

DISC

W386-

27

28

29

31

P6

024-18

022-18

POS 06

D4208J P

4

5

30

32

2

M235

6

D804

SP4526

TANK BP

CTR-R

SP4528

SP4524

W386-

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1774

J2802

012-18

J

W386-

6 LOCATIONS

4 3

9

9

9

9

9

9

5

6

8

7

3 LOCATIONS

3 LOCATIONS

2

1

10 11

REFERENCE: 737 WIRING DIAGRAM 28-23-01

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

U82044

(SHEET 1 OF 2)
 FIGURE 14: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGES

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 139 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-110 and 61-74482-110W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, PIN BACC47CN2 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04208P

61-74482-11004 1 Install within 6 inches of equipment. 

3 CONTACT BACC47CP2T 6 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05210P

61-74478-11104 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 3 Locate splices near connector 

D4208P. Refer to SWPM 20-30-12 

as an accepted procedure.

6 SPLICE I.D. SLEEVE - 

SP4524

61-74482-11005 1 -

7 SPLICE I.D. SLEEVE - 

SP4526

61-74482-11006 1 -

8 SPLICE I.D. SLEEVE - 

SP4528

61-74482-11007 1 -

9 WIRE BMS 13-58, TYPE 1, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

10 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundles 

lengths. Refer to SWPM 20-10-11 

as an accepted procedure.

11 EXPANDABLE 

SLEEVE - 0.25 IN. I.D.

61-74482-2010 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1774 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each end of the 

sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1774 007 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 008 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 009 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 010 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 011 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 012 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

(SHEET 2 OF 2)
 FIGURE 15: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 140 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 15: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

A

FWD

TYPICAL

DISCONNECT

PANEL C-3

P6 UPPER

DISCONNECT PANEL

W0368,

W1764

DISCONNECT

PANEL A

259.5

STA

294.5

STA

S-3R

S-2L

D4202J

POS 12

U82059

(SHEET 1 OF 5)
 FIGURE 15: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 141 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

UPPER RIGHT CAB

FWD

STA 178-277

STA

178

STA

196.5

U82392

S-2

S-3

S-1

W1764

STA

277

259.5

STA

A

B

D

W1774

W1764, W1774

(SHEET 2 OF 5)
 FIGURE 15: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 142 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

STA

259.5

B

C

U82061

W1774

W1764,

(SHEET 3 OF 5)
 FIGURE 15: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 143 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

C CONNECTOR

D5210P

W1764,

W1774

RBL

20.20

J2802 BOX

ASSEMBLY

W1774

W1764

LBL

12.00

W1764

CONNECTOR

D5208P

U82065

(SHEET 4 OF 5)
 FIGURE 15: WIRE BUNDLE W0368, W0386, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO 

J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 144 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 4: 

D

PANEL E

DISCONNECT

POS 10

D4208J

W1774

P6 LOAD CONTROL CENTER

U82060

FWD

(SHEET 5 OF 5)
 FIGURE 16: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 145 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 16: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

This Figure applies to Group 4: 

REFERENCE: 737 WIRING DIAGRAM 28-23-01

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

007-18

008-18

009-18

27

28

29

31

POS 12

D4202P

SP4522

SP4516

4

13

STA 270

DISC

PNL "A"

SP4514

30

32

2

M234

6

D802

W368-

TANK BP

CTR-L

W368-

018-18

016-18

SP880

SP878

017-18

J

14

D5208P

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1764

J2802

SP882

P5

012-18

PANEL

OVHD

J

15

W368-

6 LOCATIONS

4 3 1

9

9

9

9

9

9

5

6

8

7

3 LOCATIONS

3 LOCATIONS

2

1

3

10 11

U82066

(SHEET 1 OF 2)
 FIGURE 16: WIRE BUNDLE W0368 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 146 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-107 and 61-74482-107W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 9 Refer to SWPM 20-61-11as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10701 1 Install within 6 inches of equipment. 

3 THERMOFIT SLEEVE 

- 0.093 IN. I.D.

61-74482-2006 - Use to build up outer diameter of 

wire. Refer to SWPM 20-60-08 as an 

accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05208P

61-74478-10904 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 3 Locate splices near connector 

D4202J. Refer to SWPM 20-30-12 

as an accepted procedure.

6 SPLICE I.D. SLEEVE 

- SP4514

61-74482-10703 1 -

7 SPLICE I.D. SLEEVE 

- SP4516

61-74482-10704 1 -

8 SPLICE I.D. SLEEVE 

- SP4522

61-74482-10705 1 -

9 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

10 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle 

lengths. Refer to SWPM 20-10-11 as 

an accepted procedure.

11 EXPANDABLE 

SLEEVE - 0.25 IN. I.D.

61-74482-2010 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie each end 

of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1764 007 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 008 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 009 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 010 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 011 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 012 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

(SHEET 2 OF 2)
 FIGURE 17: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 147 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 17: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

This Figure applies to Group 4: 

SP884

SP888

6

4

D5210P

007-18

008-18

009-18

023-18 SP886

CTR-R

CNTRL

LOAD

STA 260

DISC

PNL "E"

W386-

27

28

29

31

P6

024-18

022-18

POS 10

D4208J P

4

5

30

32

2

M235

6

D804

SP4526

TANK BP

CTR-R

SP4528

SP4524

W386-

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1774

J2802

012-18

J

W386-

6 LOCATIONS

3 1

8

8

8

8

8

8

4

5

7

6

3 LOCATIONS

3 LOCATIONS

2

1

9 10

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-01

U82067

(SHEET 1 OF 2)
 FIGURE 17: WIRE BUNDLE W0386 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 148 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-1, 61-74482-110 and 61-74482-110W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 9 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04208P

61-74482-11003 1 Install within 6 inches of equipment. 

3 CONNECTOR I.D. 

TAPE - D05210P

61-74478-11104 1 Install within 6 inches of equipment. 

4 SPLICE D-436-37 3 Locate splices near connector D4208P. 

Refer to SWPM 20-30-12 as an 

accepted procedure.

5 SPLICE I.D. SLEEVE - 

SP4524

61-74482-11005 1 -

6 SPLICE I.D. SLEEVE - 

SP4526

61-74482-11006 1 -

7 SPLICE I.D. SLEEVE - 

SP4528

61-74482-11007 1 -

8 WIRE BMS 13-58, TYPE 1, 

CLASS, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

9 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

10 EXPANDABLE 

SLEEVE - 0.25 IN. I.D.

61-74482-2010 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1774 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each end of the 

sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1774 007 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 008 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 009 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 010 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 011 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 012 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

(SHEET 2 OF 2)
 FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 149 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT 

PANELS TO J2802 BOX ASSEMBLY - ROUTING

A

FWD

TYPICAL

U82068

PANEL AP0600A

DISCONNECT

DISCONNECT PANEL

P6 UPPER

W1764

W0368,

PANEL AP1800A

DISCONNECT

259.5

STA

294.5

STA

S-3R

S-2L

POS 13

D4202J

(SHEET 1 OF 5)
 FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 150 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

UPPER RIGHT CAB

FWD

STA 178-277

STA

178

STA

196.5

S-2

S-3

S-1

W1764

STA

277

259.5

STA

A

B

D

W1764

W1774

U82391

(SHEET 2 OF 5)
 FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 151 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

STA

259.5

B

C

U82073

W1774

W1764,

(SHEET 3 OF 5)
 FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 152 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

C CONNECTOR

D5210P

W1764,

W1774

RBL

20.20

J2802 BOX

ASSEMBLY

W1774

W1764

LBL

12.00

W1764

CONNECTOR

D5208P

U82071

(SHEET 4 OF 5)
 FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 153 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 5: 

D

DISCONNECT

PANEL

AP0600B

D4898P

POS 05

W1034,

W1046

W1764,

W1774

D4900J

POS 07

D4208P

POS 06

P6 LOAD CONTROL CENTER

FWD

U82070

(SHEET 5 OF 5)
 FIGURE 19: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 154 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 19: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

007-18

008-18

009-18

27

28

29

31

POS 13

D4202P

SP4522

SP4516

4

13

AP1800A

STA 270

DISC

SP4514

30

32

2

M234

6

D802

W368-

TANK BP

CTR-L

W368-

018-18

016-18

SP880

SP878

017-18

J

14

D5208P

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1764

J2802

SP882

P5

012-18

PANEL

OVHD

J

15

W368-

6 LOCATIONS

3 1

20

20

20

20

20

20

5

6

8

7

3 LOCATIONS

3 LOCATIONS

2

1

3

22 23

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-01

4

U82076

(SHEET 1 OF 4)
 FIGURE 19: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 155 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 5: 

22

37

306-18Y

304-18B

305-18R

POS 07

D4900J

P6

CTR-R

CNTRL

LOAD

D4904J

303-18Y

302-18R

301-18B

SP4540

SP4538

4

1

AP0600B

STA 260

DISC

33

35

SP4536

34

36

38

24

2

M645

6

D1816

W1046-

TANK BP

AUX AFT

W1046-

301-18B

302-18R

303-18Y

P

2

D5208P

W1764

2

BL 0

WL 195,

STA 349,

BOX

J2802 MISC RELAY

3

1

J

P

3

W1046-

REFERENCE: 737 WIRING DIAGRAM 28-23-02

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

6 LOCATIONS

4 3 1

12 17

19

21

5

9

11

10

3 LOCATIONS

3 LOCATIONS

3

13

14

15

16

17

18

12 19

21

U82077

(SHEET 2 OF 4)
 FIGURE 19: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 156 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-2, 61-74482-108 and 61-74482-108W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 15 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10702 1 Install within 6 inches of equipment. 

3 THERMOFIT 

SLEEVE - 0.093 

IN. I.D.

61-74482-2007 - Use to build up outer diameter of wire. 

Refer SWPM 20-60-08 as an accepted 

procedure.

4 CONNECTOR I.D. 

TAPE - D05208P

61-74478-10904 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 6 Locate splices near connector D4202J 

and/or connector D4900P. Refer to 

SWPM 20-30-12 as an accepted 

procedure.

6 SPLICE I.D. 

SLEEVE - SP4514

61-74482-10703 1 -

7 SPLICE I.D. 

SLEEVE - SP4516

61-74482-10704 1 -

8 SPLICE I.D. 

SLEEVE - SP4522

61-74482-10705 1 -

9 SPLICE I.D. 

SLEEVE - SP4536

61-74482-10803 1 -

10 SPLICE I.D. 

SLEEVE - SP4538

61-74482-10804 1 -

11 SPLICE I.D. 

SLEEVE - SP4540

61-74482-10805 1 -

12 WIRE I.D. TAPE - 

W1764-301B, 2R, 

3Y-18

61-74482-10806 2 Install as required on end of wire. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

13 CONTACT, PIN BACC47CN2 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

14 CONNECTOR I.D. 

TAPE - D04900P

61-74482-10801 1 Install within 6 inches of equipment. 

15 ADHESIVE TAPE 

- 0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09 as an 

accepted procedure.

16 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

17 WIRE I.D. TAPE - 

W1764-304B, 5R, 

6Y-18

61-74482-10807 2 Install as required on end of wire. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

18 THREAD LOCK 

COMPOUND

65C38639-115 

(Loctite 222)

- Refer to SWPM 20-60-09 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 19: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 157 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

19 THERMOFIT 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2008 - Use to assemble a shield dead-end. 

Refer to SWPM 20-10-15 as an 

accepted procedure.

20 WIRE BMS 13-48, TYPE 

10, CLASS 1, 

AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

21 WIRE BMS 13-48, TYPE 

12, CLASS 3, 

AWG 18

2 Identified as shown. Cut to the 

necessary lengths.

22 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

23 EXPANDABLE 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2011 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

24 EXPANDABLE 

SLEEVE - 0.5 IN. 

I.D.

61-74482-2012 - Refer to SWPM 20-10-18 as an 

accepted procedure. (b)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in 

the W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie 

each end of the sleeve with white lacing tape.

(b) Install expandable sleeve over wires 301-18B, 302-18R, 303-18Y, 304-18B, 305-18R, and 306-

18Y in the W1764 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each 

end of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1764 007 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 008 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 009 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 010 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 011 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 012 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 301 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1764 302 18R

W1764 303 18Y

W1764 304 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1764 305 18R

W1764 306 18Y

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 20: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 158 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 20: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

SP884

SP888

6

4

22 23

D5210P

007-18

008-18

009-18

023-18 SP886

CTR-R

CNTRL

LOAD

AP0600B

STA 260

DISC

W386-

27

28

29

31

P6

024-18

022-18

POS 06

D4208J P

4

5

30

32

2

M235

6

D804

SP4526

TANK BP

CTR-R

SP4528

SP4524

W386-

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1774

J2802

012-18

J

W386-

REFERENCE: 737 WIRING DIAGRAM 28-23-01

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

6 LOCATIONS

4 3

20

20

20

20

20

20

5

6

8

7

3 LOCATIONS

3 LOCATIONS

2

1

U82079

(SHEET 1 OF 4)
 FIGURE 20: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 159 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 5: 

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-02

22

37

306-18Y

304-18B

305-18R

POS 05

D4898J

P6

CTR-R

CNTRL

LOAD

D4902J

303-18Y

302-18R

SP4530 301-18B

SP4532

4

1

AP0600B

STA 260

DISC

33

SP4534 35

34

36

38

23

2

M644

6

D1814

W1034-

TANK BP

AUX FWD

W1034-301-18B

302-18R

303-18Y

P

2

D5210P

W1774

2

BL 0

WL 195,

STA 349,

BOX

J2802 MISC RELAY

3

1

J

P

3

W1034-

3 LOCATIONS

13

1

14

15

16

17

18

5

9

11

10

3 LOCATIONS

12

21

21

19

19

6 LOCATIONS

12 4 3

16 17

U82078

(SHEET 2 OF 4)
 FIGURE 20: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 160 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-2, 61-74482-111 and 61-74482-111W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, PIN BACC47CN2 6 Refer to SWPM 20-61-11 as an accepted 

procedure.

2 CONNECTOR I.D. 

TAPE - D04208P

61-74482-11004 1 Install within 6 inches of equipment.

3 CONTACT BACC47CP2T 12 Refer to SWPM 20-61-11 as an accepted 

procedure.

4 CONNECTOR I.D. 

TAPE - D05210P

61-74478-11104 1 Install within 6 inches of equipment.

5 SPLICE D-436-37 6 Locate splices near connector D4208P 

and/or connector D4898P. Refer to 

SWPM 20-30-12 as an accepted 

procedure.

6 SPLICE I.D. 

SLEEVE - SP4524

61-74482-11005 1 -

7 SPLICE I.D. 

SLEEVE - SP4526

61-74482-11006 1 -

8 SPLICE I.D. 

SLEEVE - SP4528

61-74482-11007 1 -

9 SPLICE I.D. 

SLEEVE - SP4530

61-74482-11103 1 -

10 SPLICE I.D. 

SLEEVE - SP4532

61-74482-11104 1 -

11 SPLICE I.D. 

SLEEVE - SP4534

61-74482-11105 1 -

12 WIRE I.D. TAPE - 

W1774-301B, 2R, 

3Y-18

61-74482-11106 2 Install as required on end of wire. Refer 

to SWPM 20-10-11 as an accepted 

procedure.

13 CONNECTOR I.D. 

TAPE - D04898P

61-74482-11101 1 Install within 6 inches of equipment.

14 ADHESIVE TAPE 

- 0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09

15 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

16 THERMOFIT 

SLEEVE - 0.093 

IN. I.D.

61-74482-2007 - Use to build up wire diameter. Refer 

SWPM 20-60-08 as an accepted 

procedure.

17 WIRE I.D. TAPE - 

W1774-304B, 5R, 

6Y-18

61-74482-11107 2 Install as required on end of wire. Refer 

to SWPM 20-10-11 as an accepted 

procedure.

18 THREAD LOCK 

COMPOUND

65C38639-115 (Loctite 

222)

- Refer to SWPM 20-60-09 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 20: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 161 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

19 THERMOFIT 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2008 - Use to assemble a shield dead-end. 

Refer to SWPM 20-10-15 as an 

accepted procedure.

20 WIRE BMS-13-58, TYPE 1, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

21 WIRE BMS-13-48, TYPE 12, 

CLASS 3, AWG 18

2 Identified as shown. Cut to the 

necessary lengths.

22 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an accepted 

procedure.

23 EXPANDABLE 

SLEEVE - 0.5 IN. 

I.D.

61-74482-2012 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, 012-18, 301-18B, 302-

18R, 303-18Y, 304-18B, 305-18R, and 306-18Y in the W1774 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each end of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1774 007 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 008 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 009 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 010 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 011 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 012 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 301 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1774 302 18R

W1774 303 18Y

W1774 304 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1774 305 18R

W1774 306 18Y

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 162 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT 

PANELS TO J2802 BOX ASSEMBLY - ROUTING

A

FWD

TYPICAL

U82080

PANEL AP0600A

DISCONNECT

DISCONNECT PANEL

P6 UPPER

W1764

W0368,

PANEL AP1800A

DISCONNECT

259.5

STA

294.5

STA

S-3R

S-2R

POS 13

D4202J

(SHEET 1 OF 8)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 163 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

UPPER RIGHT CAB

FWD

STA 178-277

STA

178

STA

196.5

S-2

S-3

S-1

W1764

STA

277

259.5

STA

A

B

D

W1764,

W1774

U82089

(SHEET 2 OF 8)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 164 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

STA

259.5

B

C

G

U82091

W1774

W1764,

(SHEET 3 OF 8)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 165 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

C CONNECTOR

D5210P

W1764,

W1774

RBL

20.20

J2802 BOX

ASSEMBLY

W1774

W1764

LBL

12.00

W1764

CONNECTOR

D5208P

U82092

(SHEET 4 OF 8)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 166 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

D

DISCONNECT

PANEL

AP0600B

W1774

D4208P

POS 06

P6 LOAD CONTROL CENTER

FWD

U82084

(SHEET 5 OF 8)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 167 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

E

LOWER RIGHT SIDE

FWD

S-25

S-23

S-21

STA

259.5

STA

227B

STA

211B

W1764

W1046,

W1774,

W1034,

PANEL AP0600D

DISCONNECT

POS 01

D4898J

POS 02

D4900J

U82101

(SHEET 6 OF 8)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 168 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

F

E

FWD

W1764

W1774

STA

259.5

U82120

(SHEET 7 OF 8)
 FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 169 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 6: 

G

F

STA

259.5

CONTINUED

ON SHEET 3

W1774,

W1764

FWD

U82122

(SHEET 8 OF 8)
 FIGURE 22: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 170 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 22: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

007-18

008-18

009-18

27

28

29

31

POS 13

D4202P

SP4522

SP4516

4

13

AP1800A

STA 270

DISC

SP4514

30

32

2

M234

6

D802

W368-

TANK BP

CTR-L

W368-

018-18

016-18

SP880

SP878

017-18

J

14

D5208P

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1764

J2802

SP882

P5

012-18

PANEL

OVHD

J

15

W368-

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-01

22 23

20

20

20

20

20

20

5

6

8

7

3 LOCATIONS

6 LOCATIONS

4 3 1

3 LOCATIONS

2

1

3

U82126

(SHEET 1 OF 4)
 FIGURE 22: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 171 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 6: 

37

306-18Y

304-18B

305-18R

POS 02

D4900J

P6

CTR-R

CNTRL

LOAD

D4904J

303-18Y

302-18R

301-18B

SP4540

SP4538

4

1

AP0600D

STA 250

DISC

33

35

SP4536

34

36

38

2

M645

6

D1816

W1046-

TANK BP

AUX AFT

W1046-

301-18B

302-18R

303-18Y

P

2

D5208P

W1764

2

BL 0

WL 195,

STA 349,

BOX

J2802 MISC RELAY

3

1

J

P

3

W1046-

22 24

3 LOCATIONS

3

13

14

15

16

17

18

21

21

19

6 LOCATIONS

4 3 1

12 16

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-02

5

9

11

10

3 LOCATIONS

12 19

U82129

(SHEET 2 OF 4)
 FIGURE 22: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 172 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-2, 61-74482-108 and 61-74482-108W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 15 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10702 1 Install within 6 inches of equipment. 

3 THERMOFIT 

SLEEVE - 0.093 IN. 

I.D.

61-74482-2007 - Use to build up outer diameter of 

wire. Refer to SWPM 20-60-08 as 

an accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05208P

61-74478-10904 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 6 Locate splices near connector 

D4202J and/or connector D4900P. 

Refer to SWPM 20-30-12 as an 

accepted procedure.

6 SPLICE I.D. SLEEVE 

- SP4514

61-74482-10703 1 -

7 SPLICE I.D. SLEEVE 

- SP4516

61-74482-10704 1 -

8 SPLICE I.D. SLEEVE 

- SP4522

61-74482-10705 1 -

9 SPLICE I.D. SLEEVE 

- SP4536

61-74482-10803 1 -

10 SPLICE I.D. SLEEVE 

- SP4538

61-74482-10804 1 -

11 SPLICE I.D. SLEEVE 

- SP4540

61-74482-10805 1 -

12 WIRE I.D. TAPE - 

W1764-301B, 2R, 3Y18

61-74482-10806 2 Install as required on end of wire. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

13 CONTACT, PIN BACC47CN2 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

14 CONNECTOR I.D. 

TAPE - D04900P

61-74482-10802 1 Install within 6 inches of equipment. 

15 ADHESIVE TAPE - 

0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09 as an 

accepted procedure.

16 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

17 WIRE I.D. TAPE - 

W1764-304B, 5R, 6Y18

61-74482-10807 2 Install as required on end of wire. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

18 THREAD LOCK 

COMPOUND

65C38639-115 

(Loctite 222)

- Refer to SWPM 20-60-09 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 22: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 173 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

19 THERMOFIT 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2008 - Use to assemble a shield deadend. Refer to SWPM 20-10-15 as 

an accepted procedure.

20 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

21 WIRE BMS 13-48, TYPE 12, 

CLASS 3, AWG 18

2 Identified as shown. Cut to the 

necessary lengths.

22 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle 

lengths. Refer to SWPM 20-10-11 

as an accepted procedure.

23 EXPANDABLE 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2011 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

24 EXPANDABLE 

SLEEVE - 0.5 IN. I.D.

61-74482-2012 - Refer to SWPM 20-10-18 as an 

accepted procedure. (b)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie each 

end with lacing tape.

(b) Install expandable sleeve over wires 301-18B, 302-18R, 303-18Y, 304-18B, 305-18R, and 306-

18Y in the W1764 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each 

end of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1764 007 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 008 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 009 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 010 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 011 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 012 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 301 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1764 302 18R

W1764 303 18Y

W1764 304 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1764 305 18R

W1764 306 18Y

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 23: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 174 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 23: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

SP884

SP888

6

4

D5210P

007-18

008-18

009-18

023-18 SP886

CTR-R

CNTRL

LOAD

AP0600B

STA 260

DISC

W386-

27

28

29

31

P6

024-18

022-18

POS 06

D4208J P

4

5

30

32

2

M235

6

D804

SP4526

TANK BP

CTR-R

SP4528

SP4524

W386-

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1774

J2802

012-18

J

W386-

22 23

3 LOCATIONS

2

1

5

6

8

7

3 LOCATIONS

20

20

20

20

20

20

6 LOCATIONS

4 3

REFERENCE: 737 WIRING DIAGRAM 28-23-01

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

U82149

(SHEET 1 OF 4)
 FIGURE 23: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 175 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 6: 

37

306-18Y

304-18B

305-18R

POS 01

D4898J

P6

CTR-R

CNTRL

LOAD

D4902J

303-18Y

302-18R

SP4530 301-18B

SP4532

4

1

AP0600D

STA 250

DISC

33

SP4534 35

34

36

38

2

M644

6

D1814

W1034-

TANK BP

AUX FWD

W1034-301-18B

302-18R

303-18Y

P

2

D5210P

W1774

2

BL 0

WL 195,

STA 349,

BOX

J2802 MISC RELAY

3

1

J

P

3

W1034-

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-02

22 24

21

21 19

19

6 LOCATIONS

12 4 3

16 17

5

9

11

10

3 LOCATIONS

12

3 LOCATIONS

13

1

14

15

16

17

18

U82139

(SHEET 2 OF 4)
 FIGURE 23: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 176 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-2, 61-74482-111 and 61-74482-111W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, PIN BACC47CN2 6 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04208P

61-74482-11004 1 Install within 6 inches of equipment. 

3 CONTACT BACC47CP2T 12 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05210P

61-74478-11104 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 6 Locate splices near connector D4208P 

and/or connector D4898P. Refer to 

SWPM 20-30-12 as an accepted 

procedure.

6 SPLICE I.D. 

SLEEVE - SP4524

61-74482-11005 1 -

7 SPLICE I.D. 

SLEEVE - SP4526

61-74482-11006 1 -

8 SPLICE I.D. 

SLEEVE - SP4528

61-74482-11007 1 -

9 SPLICE I.D. 

SLEEVE - SP4530

61-74482-11103 1 -

10 SPLICE I.D. 

SLEEVE - SP4532

61-74482-11104 1 -

11 SPLICE I.D. 

SLEEVE - SP4534

61-74482-11105 1 -

12 WIRE I.D. TAPE - 

W1774-301B, 2R, 

3Y-18 

61-74482-11106 2 Install as required on end of wire. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

13 CONNECTOR I.D. 

TAPE - D04898P

61-74482-11102 1 Install within 6 inches of equipment. 

14 ADHESIVE TAPE 

- 0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09 as an 

accepted procedure.

15 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

16 THERMOFIT 

SLEEVE - 0.093 

IN. I.D.

61-74482-2007 - Use to build up outer diameter of the 

wire. Refer to SWPM 20-60-08 as an 

accepted procedure.

17 WIRE I.D. TAPE - 

W1774-304B, 5R, 

6Y-18

61-74482-11107 2 Install as required on end of wire. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 23: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 177 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

18 THREAD LOCK 

COMPOUND

65C38639-115 (Loctite 

222)

- Refer to SWPM 20-60-09 as an 

accepted procedure. 

19 THERMOFIT 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2008 - Use to assemble a shield dead-end. 

Refer to SWPM 20-10-15 as an 

accepted procedure.

20 WIRE BMS 13-58, TYPE 1, 

CLASS 1, AWG 18

6 Identified as shown. Cut to the 

necessary lengths.

21 WIRE BMS 13-48, TYPE 12, 

CLASS 3, AWG 18

2 Identified as shown. Cut to the 

necessary lengths.

22 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

23 EXPANDABLE 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2011 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

24 EXPANDABLE 

SLEEVE - 0.5 IN. 

I.D.

61-74482-2012 - Refer to SWPM 20-10-18 as an 

accepted procedure. (b)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1774 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each end of the 

sleeve with white lacing tape.

(b) Install expandable sleeve over wires 301-18B, 302-18R, 303-18Y, 304-18B, 305-18R, and 306-18Y 

in the W1774 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each end of 

the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1774 007 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 008 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 009 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 010 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 011 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 012 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 301 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1774 302 18R

W1774 303 18Y

W1774 304 18B VH 636 BMS 13-48, TYPE 12, CLASS 3, AWG 18

W1774 305 18R

W1774 306 18Y

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 178 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT 

PANELS TO J2802 BOX ASSEMBLY - ROUTING

A

FWD

TYPICAL

DISCONNECT

PANEL C-3

P6 UPPER

DISCONNECT PANEL

W0368,

W1764

DISCONNECT

PANEL A

259.5

STA

294.5

STA

S-3R

S-2L

D4202J

POS 13

U82156

(SHEET 1 OF 5)
 FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 179 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

UPPER RIGHT CAB

FWD

STA 178-277

STA

178

STA

196.5

S-2

S-3

S-1

W1764

STA

277

259.5

STA

A

B

D

W1764,

W1774

U82166

(SHEET 2 OF 5)
 FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 180 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

STA

259.5

B

C

U82167

W1774

W1764,

(SHEET 3 OF 5)
 FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 181 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

C CONNECTOR

D5210P

W1764,

W1774

RBL

20.20

J2802 BOX

ASSEMBLY

W1774

W1764

LBL

12.00

W1764

CONNECTOR

D5208P

U82172

(SHEET 4 OF 5)
 FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 182 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 7: 

D

DISCONNECT

PANEL E

D4898P

POS 19

D4900P

POS 26

D4208P

POS 10

W1034,

W1046,

W1764,

W1774

P6 LOAD CONTROL CENTER

FWD

U82164

(SHEET 5 OF 5)
 FIGURE 25: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 183 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 25: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

19

007-18

008-18

009-18

27

28

29

31

POS 13

D4202P

18

SP4522

SP4516

4

13

STA 270

DISC

PNL "A"

SP4514

30

32

2

M234

6

D802

W368-

TANK BP

CTR-L

W368-

018-18

-016-18

SP880

SP878

017-18

J

14

D5208P

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1764

J2802

SP882

P5

012-18

PANEL

OVHD

J

15

REFERENCE: 737 WIRING DIAGRAM 28-23-01

3 LOCATIONS

2

1

3

D5208P

6 LOCATIONS

4 3 1

17

17

17

17

17

17

5

6

8

7

3 LOCATIONS

U82381

(SHEET 1 OF 4)
 FIGURE 25: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 184 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 7: 

34

STA 260

DISC

PNL "E"

37

POS 26

D4900J

P6

CTR-R

CNTRL

LOAD

D4904J

SP4540

SP4538

4

1

33

35

SP4536

36

38

2

M645

6

D1816

W1046-

TANK BP

AUX AFT

W1046-003-18

-002-18

001-18

P

2

D5208P

015-18

W1764

016-18

017-18

2

018-18

BL 0

WL 195,

STA 349,

BOX

RELAY

J2802 MISC

3

1

J

P

3

020-18

019-18

REFERENCE: 737 WIRING DIAGRAM 28-23-02

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

18 19

3 LOCATIONS

3

12

13

14

15

16

6 LOCATIONS

4 3 1

17

17

17

17

17

17

5

9

11

10

3 LOCATIONS

U82183

(SHEET 2 OF 4)
 FIGURE 25: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 185 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-3, 61-74482-109 and 61-74482-109W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 15 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10701 1 Install within 6 inches of equipment. 

3 THERMOFIT 

SLEEVE - 0.093 

IN. I.D.

61-74482-2007 - Use to build up outer diameter of wire. 

Refer to SWPM 20-60-08 as an 

accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05208P

61-74478-10904 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 6 Locate splices near connector D4202J 

and/or connector D4900P. Refer to 

SWPM 20-30-12 as an accepted 

procedure.

6 SPLICE I.D. 

SLEEVE - SP4514

61-74482-10703 1 -

7 SPLICE I.D. 

SLEEVE - SP4516

61-74482-10704 1 -

8 SPLICE I.D. 

SLEEVE - SP4522

61-74482-10705 1 -

9 SPLICE I.D. 

SLEEVE - SP4536

61-74482-10803 1 -

10 SPLICE I.D. 

SLEEVE - SP4538

61-74482-10804 1 -

11 SPLICE I.D. 

SLEEVE - SP4540

61-74482-10805 1 -

12 CONTACT, PIN BACC47CN2 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

13 CONNECTOR I.D. 

TAPE - D04900P

61-74482-10901 1 Install within 6 inches of equipment. 

14 ADHESIVE TAPE 

- 0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09 as an 

accepted procedure.

15 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

16 THREAD LOCK 

COMPOUND

65C38639-115 

(Loctite 222)

- Refer to SWPM 20-60-09 as an 

accepted procedure.

17 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

12 Identified as shown. Cut to the 

necessary lengths.

18 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 25: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 186 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

19 EXPANDABLE 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2011 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a) (b)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie each 

end of the sleeve with white lacing tape.

(b) Install expandable sleeve over wires 015-18, 016-18, 017-18, 018-18, 019-18, and 020-18 in the 

W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie each 

end of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1764 007 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 008 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 009 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 010 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 011 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 012 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 015 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 016 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 017 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 018 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 019 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 020 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 26: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 187 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 26: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

SP884

SP888

6

4

D5210P

007-18

008-18

009-18

023-18 SP886

CTR-R

CNTRL

LOAD

STA 260

DISC

PNL "E"

W386-

27

28

29

31

P6

024-18

-022-18

POS 10

D4208J P

4

5

30

32

2

M235

6

D804

SP4526

TANK BP

CTR-R

SP4528

SP4524

W386-

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1774

J2802

012-18

J

3 LOCATIONS

2

1

17 18

16

16

16

16

16

16

6 LOCATIONS

3 1

4

5

7

6

3 LOCATIONS

REFERENCE: 737 WIRING DIAGRAM 28-23-01

U82383

(SHEET 1 OF 4)
 FIGURE 26: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 188 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 7: 

34

STA 260

DISC

PNL "E"

37

POS 19

D4898J

P6

CTR-R

CNTRL

LOAD

D4902J

SP4530

SP4532

4

1

33

SP4534 35

36

38

2

M644

6

D1814

W1034-

TANK BP

AUX FWD

W1034- 003-18

-002-18

001-18

P

2

D5210P

015-18

W1774

016-18

017-18

2

018-18

BL 0

WL 195,

STA 349,

BOX

RELAY

J2802 MISC

3

1

J

P

3

020-18

019-18

REFERENCE: 737 WIRING DIAGRAM 28-23-02

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

17 18

3 LOCATIONS

12

11

13

14

15

16

16

16

16

16

16

4

8

10

9

3 LOCATIONS

6 LOCATIONS

3 1

U82384

(SHEET 2 OF 4)
 FIGURE 26: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 189 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-3, 61-74482-112 and 61-74482-112W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 15 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04208P

61-74482-11003 1 Install within 6 inches of equipment. 

3 CONNECTOR I.D. 

TAPE - D05210P

61-74478-11104 1 Install within 6 inches of equipment. 

4 SPLICE D-436-37 6 Locate splices near connector 

D4208P and/or connector D4898P. 

Refer to SWPM 20-30-12 as an 

accepted procedure.

5 SPLICE I.D. 

SLEEVE - SP4524

61-74482-11005 1 -

6 SPLICE I.D. 

SLEEVE - SP4526

61-74482-11006 1 -

7 SPLICE I.D. 

SLEEVE - SP4528

61-74482-11007 1 -

8 SPLICE I.D. 

SLEEVE - SP4530

61-74482-11103 1 -

9 SPLICE I.D. 

SLEEVE - SP4532

61-74482-11104 1 -

10 SPLICE I.D. 

SLEEVE - SP4534

61-74482-11105 1 -

11 CONTACT, PIN BACC47CN2 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

12 CONNECTOR I.D. 

TAPE - D04898P

61-74482-11201 1 Install within 6 inches of equipment. 

13 ADHESIVE TAPE 

- 0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09 as an 

accepted procedure.

14 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

15 THREAD LOCK 

COMPOUND

65C38639-115 (Loctite 

222)

- Refer to SWPM 20-60-09 as an 

accepted procedure.

16 WIRE BMS 13-58, TYPE 1, 

CLASS 1, AWG 18

12 Identified as shown. Cut to the 

necessary lengths.

(SHEET 3 OF 4)
 FIGURE 26: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 190 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

17 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle 

lengths. Refer to SWPM 20-10-11 

as an accepted procedure.

18 EXPANDABLE 

SLEEVE - 0.5 IN. 

I.D.

61-74482-2013 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a) 

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, 012-18, 015-18, 

016-18, 017-18, 018-18, 019-18, and 020-18 in the W1774 wire bundle. Install sleeve along wire 

routing outboard of the P6 Panel. Tie each end of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1774 007 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 008 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 009 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 010 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 011 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 012 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 015 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 016 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 017 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 018 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 019 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 020 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 191 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT 

PANELS TO J2802 BOX ASSEMBLY - ROUTING

A

FWD

TYPICAL

U90792

PANEL C-3

DISCONNECT

DISCONNECT PANEL

P6 UPPER

W1764

W0368,

PANEL A

DISCONNECT

259.5

STA

294.5

STA

S-3R

S-2L

POS 13

D4202J

(SHEET 1 OF 5)
 FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 192 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

UPPER RIGHT CAB

FWD

STA 178-277

STA

178

STA

196.5

S-2

S-3

S-1

W1764

STA

277

259.5

STA

A

B

D

W1764,

W1774

U90793

(SHEET 2 OF 5)
 FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 193 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

STA

259.5

B

C

U90794

W1774

W1764,

FLOOR BEAMS

(SHEET 3 OF 5)
 FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 194 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FWD

C CONNECTOR

D5210P

W1764,

W1774

RBL

20.20

J2802 BOX

ASSEMBLY

W1774

W1764

LBL

12.00

W1764

CONNECTOR

D5208P

U81321

(SHEET 4 OF 5)
 FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCONNECT PANELS TO J2802 BOX ASSEMBLY - ROUTING

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 195 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 8: 

D

DISCONNECT

PANEL E W1034,

W1046,

W1764,

W1774 D4208P

POS 10

D4900P

POS 9

D4898P

POS 5

P6 LOAD CONTROL CENTER

FWD

U90799

(SHEET 5 OF 5)
 FIGURE 28: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 196 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 28: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

REFERENCE: 737 WIRING DIAGRAM 28-23-01

19

007-18

008-18

009-18

27

28

29

31

POS 13

D4202P

18

SP4522

SP4516

4

13

STA 270

DISC

PNL "A"

SP4514

30

32

2

M234

6

D802

W368-

TANK BP

CTR-L

W368-

018-18

-016-18

SP880

SP878

017-18

J

14

D5208P

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1764

J2802

SP882

P5

012-18

PANEL

OVHD

J

15

3 LOCATIONS

2

1

3

17

17

17

17

17

17

6 LOCATIONS

4 3 1

5

6

8

7

3 LOCATIONS

U90800

(SHEET 1 OF 4)
 FIGURE 28: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 197 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 8: 

34

STA 260

DISC

PNL "E"

37

19

POS 9

D4900J

P6

CTR-R

CNTRL

LOAD

D4904J

SP4540

SP4538

18

4

1

33

35

SP4536

36

38

2

M645

6

D1816

W1046-

TANK BP

AUX AFT

W1046-003-18

-002-18

001-18

P

2

D5208P

015-18

W1764

016-18

017-18

2

018-18

BL 0

WL 195,

STA 349,

BOX

RELAY

J2802 MISC

3

1

J

P

3

020-18

019-18

REFERENCE: 737 WIRING DIAGRAM 28-23-02

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

6 LOCATIONS

4 3 1

17

17

17

17

17

17

5

9

11

10

3 LOCATIONS

3 LOCATIONS

3

12

13

14

15

16

U90802

(SHEET 2 OF 4)
 FIGURE 28: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 198 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-3, 61-74482-109 and 61-74482-109W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 15 Refer to SWPM 20-61-11as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04202J

61-74482-10701 1 Install within 6 inches of equipment. 

3 THERMOFIT 

SLEEVE - 0.093 

IN. I.D.

61-74482-2007 - Use to build up outer diameter of wire. 

Refer to SWPM 20-60-08 as an 

accepted procedure.

4 CONNECTOR I.D. 

TAPE - D05208P

61-74478-10904 1 Install within 6 inches of equipment. 

5 SPLICE D-436-37 6 Locate splices near connector D4202J 

and/or connector D4900P. Refer to 

SWPM 20-30-12 as an accepted 

procedure.

6 SPLICE I.D. 

SLEEVE - SP4514

61-74482-10703 1 -

7 SPLICE I.D. 

SLEEVE - SP4516

61-74482-10704 1 -

8 SPLICE I.D. 

SLEEVE - SP4522

61-74482-10705 1 -

9 SPLICE I.D. 

SLEEVE - SP4536

61-74482-10803 1 -

10 SPLICE I.D. 

SLEEVE - SP4538

61-74482-10804 1 -

11 SPLICE I.D. 

SLEEVE - SP4540

61-74482-10805 1 -

12 CONTACT, PIN BACC47CN2 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

13 CONNECTOR I.D. 

TAPE - D04900P

61-74482-10901 1 Install within 6 inches of equipment. 

14 ADHESIVE TAPE 

- 0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09 as an 

accepted procedure.

15 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

16 THREAD LOCK 

COMPOUND

65C38639-115 

(Loctite 222)

- Refer to SWPM 20-60-09 as an 

accepted procedure.

17 WIRE BMS 13-48, TYPE 10, 

CLASS 1, AWG 18

12 Identified as shown. Cut to the 

necessary length.

18 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 3 OF 4)
 FIGURE 28: WIRE BUNDLE W0368, W1046 AND W1764 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 199 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

19 EXPANDABLE 

SLEEVE - 0.25 IN. 

I.D.

61-74482-2011 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a) (b)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, and 012-18 in the 

W1764 wire bundle. Install sleeve along wire routing above and outboard of the P6 Panel. Tie each end 

of the sleeve with white lacing tape.

(b) Install an expandable sleeve over wires 015-18, 016-18, 017-18, 018-18, 019-18, and 020-18 in the 

W1764 wire bundle. Install sleeve along wire routing outboard of the P6 Panel. Tie each end of the 

sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1764 007 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 008 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 009 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 010 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 011 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 012 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 015 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 016 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 017 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 018 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 019 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

W1764 020 18 PA 636 BMS 13-48, TYPE 10, CLASS 1, AWG 18

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 29: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 200 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 29: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 BOX 

ASSEMBLY - WIRING CHANGE

REFERENCE: 737 WIRING DIAGRAM 28-23-01

SP884

SP888

6

4

17

D5210P

18

007-18

008-18

009-18

023-18 SP886

CTR-R

CNTRL

LOAD

STA 260

DISC

PNL "E"

W386-

27

28

29

31

P6

024-18

-022-18

POS 10

D4208J P

4

5

30

32

2

M235

6

D804

SP4526

TANK BP

CTR-R

SP4528

SP4524

W386-

010-18

011-18

BL 0

WL 195,

STA 349,

BOX

RELAY

MISC

W1774

J2802

012-18

J

3 LOCATIONS

2

1

6 LOCATIONS

3 1

16

16

16

16

16

16

4

5

7

6

3 LOCATIONS

U90803

(SHEET 1 OF 4)
 FIGURE 29: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 201 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

This Figure applies to Group 8: 

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

REFERENCE: 737 WIRING DIAGRAM 28-23-02

34

STA 260

DISC

PNL "E"

37

POS 5

D4898J

P6

CTR-R

CNTRL

LOAD

D4902J

SP4530

SP4532

4

1

33

SP4534 35

36

38

2

M644

6

D1814

W1034-

TANK BP

AUX FWD

W1034- 003-18

-002-18

001-18

P

2

D5210P

015-18

W1774

016-18

017-18

2

018-18

BL 0

WL 195,

STA 349,

BOX

RELAY

J2802 MISC

3

1

J

P

3

020-18

019-18

4

8

10

9

3 LOCATIONS

16

16

16

16

16

16

6 LOCATIONS

3 1

3 LOCATIONS

12

11

13

14

15

17 18

U90804

(SHEET 2 OF 4)
 FIGURE 29: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 202 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

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

NOTE: Get the parts given below from kits 61-74482-3, 61-74482-112 and 61-74482-112W.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT BACC47CP2T 15 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 CONNECTOR I.D. 

TAPE - D04208P

61-74482-11003 1 Install within 6 inches of equipment. 

3 CONNECTOR I.D. 

TAPE - D05210P

61-74478-11104 1 Install within 6 inches of equipment. 

4 SPLICE D-436-37 6 Locate splices near connector D4208P 

and/or connector D4898P. Refer to 

SWPM 20-30-12 as an accepted 

procedure.

5 SPLICE I.D. 

SLEEVE - SP4524

61-74482-11005 1 -

6 SPLICE I.D. 

SLEEVE - SP4526

61-74482-11006 1 -

7 SPLICE I.D. 

SLEEVE - SP4528

61-74482-11007 1 -

8 SPLICE I.D. 

SLEEVE - SP4530

61-74482-11103 1 -

9 SPLICE I.D. 

SLEEVE - SP4532

61-74482-11104 1 -

10 SPLICE I.D. 

SLEEVE - SP4534

61-74482-11105 1 -

11 CONTACT, PIN BACC47CN2 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

12 CONNECTOR I.D. 

TAPE - D04898P

61-74482-11201 1 Install within 6 inches of equipment. 

13 ADHESIVE TAPE 

- 0.5 IN

61-74482-2004 - Refer to SWPM 20-60-09 as an 

accepted procedure.

14 STRAP BACS38K5 1 Refer to SWPM 20-60-09 as an 

accepted procedure.

15 THREAD LOCK 

COMPOUND

65C38639-115 

(Loctite 222)

- Refer to SWPM 20-60-09 as an 

accepted procedure.

16 WIRE BMS 13-58. TYPE 1, 

CLASS 1, AWG 18

12 Identified as shown. Cut to the 

necessary length.

(SHEET 3 OF 4)
 FIGURE 29: WIRE BUNDLE W0386, W1034 AND W1774 FROM P6 DISCONNECT PANEL TO J2802 

BOX ASSEMBLY - WIRING CHANGE

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 203 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

17 LACING TAPE - 

WHITE

61-74482-2001 - Use to tie affected wire bundle lengths. 

Refer to SWPM 20-10-11 as an 

accepted procedure.

18 EXPANDABLE 

SLEEVE - 0.5 IN. 

I.D.

61-74482-2013 - Refer to SWPM 20-10-18 as an 

accepted procedure. (a)

(a) Install expandable sleeve over wires 007-18, 008-18, 009-18, 010-18, 011-18, 012-18, 015-18, 

016-18, 017-18, 018-18, 019-18, and 020-18 in the W1774 wire bundle. Install sleeve along wire 

routing above and outboard of the P6 Panel. Tie each end of the sleeve with white lacing tape.

CUT AND CODE AS NECESSARY

WBA# WIRE# GAGE 

COLOR

TYPE 

CODE

LENGTH 

(INCHES)

MATERIAL SPECIFICATION

W1774 007 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 008 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 009 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 010 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 011 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 012 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 015 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 016 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 017 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 018 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 019 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

W1774 020 18 CQ 636 BMS 13-58, TYPE 1, CLASS 1, AWG 18

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 30: J2802 BOX ASSEMBLY - CLOSE ACCESS

Original Issue: August 02, 2010

737-28A1227

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 204 of 204

BOEING SERVICE BULLETIN 737-28A1227

ALERT ALERT

FIGURE 30: J2802 BOX ASSEMBLY - CLOSE ACCESS

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 the airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install (Kept) COVER 65C38484-5 1 -

2 Install (Kept) WASHER NAS1149F0363P 6 -

3 Install (Kept) BOLT BACS12HN3-8 6 -

E3 SUPPORT POST

E2 SUPPORT POST

FWD

1

350

STA

2 3

6 LOCATIONS

U81349

(SHEET 1 OF 1)