August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 204 ALERT ALERT 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2010 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document or otherwise.**BLANK PAGE** August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

BLANK PAGE**Table of Contents** August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT 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**Table of Contents** August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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 . . . . . . . . . . . . . . . . . . . . . . . 204Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 204 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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 204 

### 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. **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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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/W17741308568Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

BLANK PAGEOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 204 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).Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 PT215Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 PY301Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 PN481Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PP239Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PP682Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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–PW519Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PY441Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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–PT062Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 PW007Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PL729Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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–PK069Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PW021Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PK552Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PW273Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PR029Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PT721Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PL011Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PN032Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PP902Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PM395Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PN163Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PK608Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PK616Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PY031Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PW120Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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–PJ219Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 PK565Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 1Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 204 

### 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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 204 

### 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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 204 

### 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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 204 

### 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 3.40Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 +1,480Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 2Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 204 

### 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 9Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 204 

### 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 5Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 204 

### 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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 204 

### 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**  **Name Notes -2 -1**  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 Name Notes**  **-3 -2 -1** 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 ONOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

**Kit 61-74482 New Part**  **Number QTY**  **Name Notes -1**  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**  **Name Notes -2**  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**  **Name Notes -3**  61-74482-3 - WIRE KIT - UNCOMMANDED ON RELAYS - AUX TANK CONFIGURATION - 737-200 61-74482-104 1 ASSY - W1760 61-74482-106 1 ASSY - W1770Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 61 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**  **Name Notes -108 -107 -106 -105 -104 -103**  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**  **Name Notes -3** Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 62 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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**  **Name Notes -108 -107 -106 -105 -104 -103** Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 63 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 - D04208POriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 64 of 204 

### 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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 65 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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, HEATSHRINKABLE, POLYOLEFIN, FLEXIBLE, XLINKED M23053/5-105-4 1 . . INSULATION SLEEVING, HEATSHRINKABLE, POLYOLEFIN, FLEXIBLE, XLINKED NA728R99 . . 1 BMS 13-52 EXPANDABLE SOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 66 of 204 

### 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**  **Name Notes -115**  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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 67 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 68 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

BLANK PAGEOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 69 of 204 

### 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:Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 70 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 71 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 72 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 megohmOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 73 of 204 

### 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. **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 74 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 75 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 76 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 77 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 78 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 79 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 megohmOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 80 of 204 

### 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. **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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 81 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 82 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 83 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 84 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 ACOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 85 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 86 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 87 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 88 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 megohmOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 89 of 204 

### 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:

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 C3329Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 90 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 C3329Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 91 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 92 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 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 C3320Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 93 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **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 megohmOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 94 of 204 

### 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:

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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 95 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 C3329Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 96 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

**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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 97 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

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.Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 98 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 ACOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 99 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

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**Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 100 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT** 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 megohmOriginal Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 101 of 204 

### 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 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 102 of 204 

### 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 LOCATIONSU81319

**(SHEET 1 OF 2) FIGURE 1: J2802 BOX ASSEMBLY - RELAYS AND SWITCHES INSTALLATION**  Original Issue: August 02, 2010 737-28A1227 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 737-28A1227 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 TH**  **E J2802 BOX ASSEMBLY - CONNECTION** Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 105 of 204 

### 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

D5208J P 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 FUEL CONT ASO C3318 =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 5 3 2 LOCATIONS

14

14

14

14

14 14 12 11

6 LOCATIONS 3 4 8 6

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 LOCATIONSU81335

**(SHEET 1 OF 3) FIGURE 3: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION**  Original Issue: August 02, 2010 737-28A1227 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 TH**  **E J2802 BOX ASSEMBLY - CONNECTION** Original Issue: August 02, 2010 737-28A1227 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 737-28A1227 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: 8 6

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

D5210J P 

## 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 FUEL CONT ASO C3320 =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 11 12 13 13 7
3 2 LOCATIONS 13 13

5 3 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 ROUTINGU81364

**(SHEET 1 OF 3) FIGURE 4: WIRE BUNDLE W1770 TH**  **E J2802 BOX ASSEMBLY - CONNECTION** Original Issue: August 02, 2010 737-28A1227 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 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 110 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 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 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 111 of 204 

### 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 LOCATIONSU81348

**(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 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 113 of 204 

### 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
C3327 R3336 R3338 R3334 R3340 S3326 S3324

TYPICALU81351

**(SHEET 1 OF 1) FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION**  Original Issue: August 02, 2010 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 114 of 204 

### 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

D5208J P 

## 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 FUEL CONT ASO C3318 =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 5 3 2 LOCATIONS 8 14

14 10 9 2 LOCATIONS 16

REFERENCE: 737 WIRING DIAGRAM 28-23-01U81357

**(SHEET 1 OF 4) FIGURE 7: WIRE BUNDLE W1760 TH**  **E J2802 BOX ASSEMBLY - CONNECTION** Original Issue: August 02, 2010 737-28A1227 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

D5208J P 

## 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 FUEL CONT ASO C3327 =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

5 3 2 LOCATIONS 13 9 2 LOCATIONS 16U81359

**(SHEET 2 OF 4) FIGURE 7: WIRE BUNDLE W1760 THE J2802 BOX ASSEMBLY - CONNECTION**  Original Issue: August 02, 2010 737-28A1227 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 TH**  **E J2802 BOX ASSEMBLY - CONNECTION** Original Issue: August 02, 2010 737-28A1227 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 737-28A1227 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

D5210J P 

## 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 FUEL CONT ASO C3320 =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 5 3 2 LOCATIONS 8 14

14 2 LOCATIONS

3 7 6 10 9 2 LOCATIONS 16U81611

**(SHEET 1 OF 4) FIGURE 8: WIRE BUNDLE W1770 TH**  **E 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

D5210J P 

## 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 FUEL CONT ASO C3329 =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 5 3 2 LOCATIONS 8 14

14 2 LOCATIONS

3 7 6 13 9 2 LOCATIONS 16U81612

**(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 TH**  **E 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

TYPICALU81668 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 737-28A1227 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 123 of 204 

### BOEING SERVICE BULLETIN 737-28A1227 **ALERT ALERT**

UPPER RIGHT CAB FWD
STA 178-277 STA 178 STA 196.5 W1774 W1764, W1774U82028 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 737-28A1227 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

CU82029 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 737-28A1227 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 D5208PU82030

**(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 737-28A1227 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 FWDU81672

**(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 737-28A1227 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 3U82034

**(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 1 3 3 LOCATIONS 2 1U82036

**(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

TYPICALU82037 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 737-28A1227 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, W1774U82039

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

CU82040 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 D5208PU82041

**(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 FWDU82038

**(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 1 3 4 11 10

3 LOCATIONS 2 1

3

REFERENCE: 737 WIRING DIAGRAM 28-23-01
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTINGU82042

**(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 3 4 9

9

9 9

9

9 5 6
8 7

3 LOCATIONS 3 LOCATIONS 2 1 11 10

REFERENCE: 737 WIRING DIAGRAM 28-23-01
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTINGU82044

**(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 12U82059

**(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 196.5U82392 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

CU82061 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 D5208PU82065

**(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 CENTERU82060
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 1 3 4 9

9

9 9

9

9 5 6
8 7

3 LOCATIONS 3 LOCATIONS 2 1

3 11 10U82066

**(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 1 3 8

8

8 8

8

8 4 5
7 6

3 LOCATIONS 3 LOCATIONS 2 1 10 9

ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING REFERENCE: 737 WIRING DIAGRAM 28-23-01U82067

**(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 DISCON**  **NECT 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

TYPICALU82068 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 DISCON**  **NECT 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

W1774U82391

**(SHEET 2 OF 5) FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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

CU82073 W1774 W1764,

**(SHEET 3 OF 5) FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 D5208PU82071

**(SHEET 4 OF 5) FIGURE 18: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 FWDU82070

**(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 1 3 20

20

20 20

20

20 5 6
8 7

3 LOCATIONS 3 LOCATIONS 2 1

3 23 22

ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING REFERENCE: 737 WIRING DIAGRAM 28-23-01 4U82076

**(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 MISC RELAY J2802 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 1 3 4
17 12 19 21 5 9
11 10

3 LOCATIONS 3 LOCATIONS 3 13

14
15
16
17
18 19 12

21U82077

**(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 23 22

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 3 4 20

20

20 20

20

20 5 6
8 7

3 LOCATIONS 3 LOCATIONS 2 1U82079

**(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
301-18B SP4530 SP4532 4 1 AP0600B STA 260 DISC

33 35 SP4534
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 MISC RELAY J2802 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 3 4 12 17 16U82078

**(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 DISCON**  **NECT 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

TYPICALU82080 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 DISCON**  **NECT 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, W1774U82089

**(SHEET 2 OF 8) FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 GU82091 W1774 W1764,

**(SHEET 3 OF 8) FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 D5208PU82092

**(SHEET 4 OF 8) FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 FWDU82084

**(SHEET 5 OF 8) FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 D4900JU82101

**(SHEET 6 OF 8) FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 259.5U82120

**(SHEET 7 OF 8) FIGURE 21: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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

FWDU82122

**(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 23 22

20

20

20 20

20

20 5 6
8 7

3 LOCATIONS

6 LOCATIONS 1 3 4 3 LOCATIONS 2 1

3U82126

**(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 MISC RELAY J2802 3 1

J P 3 W1046- 22 24

3 LOCATIONS 3 13

14
15
16
17
18

21 21

19
6 LOCATIONS 1 3 4 16 12

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 19U82129

**(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- 23 22

3 LOCATIONS 2 1

5 6
8 7

3 LOCATIONS

20

20

20 20

20

20

6 LOCATIONS 3 4

REFERENCE: 737 WIRING DIAGRAM 28-23-01 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTINGU82149

**(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
301-18B SP4530 SP4532 4 1 AP0600D

STA 250 DISC

33 35 SP4534

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 MISC RELAY J2802 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 3 4 12
17 16 5 9
11 10

3 LOCATIONS 12 3 LOCATIONS 13 1

14
15
16
17
18U82139

**(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 DISCON**  **NECT 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 13U82156

**(SHEET 1 OF 5) FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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,

W1774U82166

**(SHEET 2 OF 5) FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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

CU82167 W1774 W1764,

**(SHEET 3 OF 5) FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 D5208PU82172

**(SHEET 4 OF 5) FIGURE 24: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 FWDU82164

**(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 1 3 4 17

17

17 17

17

17 5 6
8 7

3 LOCATIONSU82381

**(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 MISC J2802 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

19 18

3 LOCATIONS 3 12

13
14
15
16

6 LOCATIONS 1 3 4 17

17

17 17

17

17 5 9
11 10

3 LOCATIONSU82183

**(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 18 17

16

16

16 16

16

16

6 LOCATIONS 1 3 4 5
7 6

3 LOCATIONS

REFERENCE: 737 WIRING DIAGRAM 28-23-01U82383

**(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 35 SP4534

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 MISC J2802 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 17

3 LOCATIONS 12 11

13
14
15

16

16

16 16

16

16 4 8
10 9

3 LOCATIONS

6 LOCATIONS 1 3U82384

**(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 DISCON**  **NECT 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

TYPICALU90792 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 DISCON**  **NECT 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,

W1774U90793

**(SHEET 2 OF 5) FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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

CU90794 W1774 W1764,



### FLOOR BEAMS

**(SHEET 3 OF 5) FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 D5208PU81321

**(SHEET 4 OF 5) FIGURE 27: WIRE BUNDLE W0368, W0386, W1034, W1046, W1764 AND W1774 FROM P6 DISCON**  **NECT 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 FWDU90799

**(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 1 3 4 5 6
8 7

3 LOCATIONSU90800

**(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 MISC J2802 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 1 3 4 17

17

17 17

17

17 5 9
11 10

3 LOCATIONS 3 LOCATIONS 3 12

13
14
15
16U90802

**(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 1 3 16

16

16 16

16

16 4 5
7 6

3 LOCATIONSU90803

**(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 35 SP4534

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 MISC J2802 3 1

J P 3

020-18 019-18 4 8
10 9

3 LOCATIONS

16

16

16 16

16

16

6 LOCATIONS 1 3 3 LOCATIONS 12 11

13
14
15 17 18U90804

**(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 LOCATIONSU81349

**(SHEET 1 OF 1)**