### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-33-1146**  Original Issue: November 02, 2011 ATA System: 3340 **SUBJECT:**LIGHTS - Strobe Position Lights - Lightning Protection of the Tail Strobe Light system wiring Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2011 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 1 of 78 5.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 2 of 78 **BOEING SERVICE BULLETIN 737-33-1146**

BLANK PAGE**Table of Contents** Summary...................................................... 5 1. PLANNING INFORMATION........................................ 9 A. Effectivity................................................ 9 1. Airplanes............................................. 9 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 1. Existing Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 2. Data supplied with this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 3. Installation Drawings Used in the Preparation of this Service Bulletin. . . . . . . . . . . . 28 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 29 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 1. Kits/Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 2. Parts and Materials Supplied by the Operator. . . . . . . . . . . . . . . . . . . . . . . . 36 3. Parts Modified and Reidentified. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36 4. Parts Removed and Not Replaced. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 37 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 FIGURE 1: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY [Group 1, 3]. . . . . . . . . . 42 FIGURE 2: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY [Group 2]. . . . . . . . . . . 44 FIGURE 3: INSTALLATION OF NEW DISCONNECT BRACKET AT THE STA 1156 BULKHEAD [Group 1, Configuration 1; Group 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 FIGURE 4: INSTALLATION OF NEW DISCONNECT BRACKET AT THE STA 1156 BULKHEAD [Group 1, Configuration 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 FIGURE 5: REMOVAL OF SGLA DISCONNECT BRACKET AT STA 1156 BULKHEAD [Group 2] . . 50 FIGURE 6: INSTALLATION OF NEW DISCONNECT BRACKET AT STA 1156 BULKHEAD [Group 2] . 52 FIGURE 7: WIRE ROUTING FOR WIRE BUNDLE W4724 AND INSTALLATION OF CLAMP [Group 1-2] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 FIGURE 8: WIRE CHANGE FOR WIRE BUNDLE W4724 [Group 1-2]. . . . . . . . . . . . . . . . . 56 FIGURE 9: WIRE ROUTING FOR WIRE BUNDLE W5726 AND INSTALLATION OF CLAMP [Group 3] . 58

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 3 of 78 **BOEING SERVICE BULLETIN 737-33-1146**FIGURE 10: WIRE CHANGE FOR WIRE BUNDLE W5726 [Group 3]. . . . . . . . . . . . . . . . . . . 60 FIGURE 11: WIRE ROUTING FOR WIRE BUNDLE W7150. . . . . . . . . . . . . . . . . . . . . . . . 63 FIGURE 12: WIRE CHANGE FOR WIRE BUNDLE W7150. . . . . . . . . . . . . . . . . . . . . . . . 64 FIGURE 13: WIRE ROUTING FOR WIRE BUNDLE W7152 AND INSTALLATION OF POTTED INSERT AND SPACERS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65 FIGURE 14: WIRE CHANGE FOR WIRE BUNDLE W7152. . . . . . . . . . . . . . . . . . . . . . . . 68 FIGURE 15: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG [Group 1, 3]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69 FIGURE 16: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG [Group 2]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 4 of 78 **BOEING SERVICE BULLETIN 737-33-1146**

### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Summary**  **Number: 737-33-1146** Original Issue: November 02, 2011 ATA System: 3340 **SUBJECT:**LIGHTS - Strobe Position Lights - Lightning Protection of the Tail Strobe Light system wiring BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **CONCURRENT REQUIREMENTS** None. **BACKGROUND** The tail strobe light, located at the aft end of section 48, is not electrically bonded to a primary structure in the airplane. In case of a direct lightning strike to the tail strobe light, electromagnetic coupling and large transient voltages can be transmitted into the pressure vessel and couple to wires of the airplane systems that are routed with the light wires. Those large transient voltages can possibly cause damage to the operation of the airplane's electrical systems and avionics equipment. In addition to electromagnetic coupling, electrical current on the tail strobe light system wiring could create an ignition source. This service bulletin will add lightning protection to the tail strobe light system wiring and minimize potential fire hazard created by induced electrical current. This is done by adding 2 electrical ground paths. The primary ground path passes through the APU exhaust system to the airplane metal structure. The secondary ground path passes through the added wire bundle shields to ground any transient voltages. The electrical bonding will prevent the effects of lightning strikes to the airplane system. If the change in this service bulletin is not done, a direct lightning strike to the tail strobe light can cause damage to the operation of the airplane's systems. This service bulletin gives the instructions and a kit of parts to change the tail strobe light installation and wiring. Boeing Service Related Problem (SRP) 737NG-SRP-33-0052 is related to this service bulletin. **ACTION (PRR 38275-138S)** At the aft end of the airplane, remove the tail strobe light L46 and replace the light housing. Drill holes on the new light housing. Install the light housing and tail strobe light L46. In the tail cone area, install a new STA 1156 bulkhead disconnect bracket. Install the new wire bundle W7152 that runs from the tail strobe light to the new disconnect bracket and install a potted insert and spacers on the tail cone wall to hold the new wire bundle. Make wiring changes to wire bundles W4724, W5726, and W7150 to remove the tail strobe light wires. Measure the electrical bonding of the new STA 1156 bulkhead disconnect bracket and the new connector D44582.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 5 of 78Measure the electrical bonding of the tail strobe light, the light housing and aft fairing to make sure of the correct resistance. Do an operational test of tail strobe light L46 to make sure the light operates correctly. **EFFECTIVITY** All 737-600/-700/-700C/-800/-900/-900ER Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s). **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the change given in this service bulletin be done within 72 months after the original issue date of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are available for airplanes in warranty as of November 6, 2007. Please refer to Paragraph 2.B., Industry Support Information. **MANPOWER Elapsed Hours**  **Total Task Hours Airplanes**  16.55 19.05 Group 1 Configu- ration 1 16.55 19.05 Group 1 Configu- ration 2 17.80 18.55 Group 2 15.85 18.35 Group 3
**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 6 of 78 **BOEING SERVICE BULLETIN 737-33-1146**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 7 of 78 **BOEING SERVICE BULLETIN 737-33-1146**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 8 of 78 **BOEING SERVICE BULLETIN 737-33-1146**

BLANK PAGE

### Commercial **Airplanes** 

# 737 Service Bulletin **SPECIAL ATTENTION Number: 737-33-1146**  Original Issue: November 02, 2011 ATA System: 3340 **SUBJECT:**LIGHTS - Strobe Position Lights - Lightning Protection of the Tail Strobe Light system wiring BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY. **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index D6-19567 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplane(s) shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 38275-138S for data about this change.

**DESCRIPTION CONFIGURATION**  **GROUP** All 737-600/-700/-700C/-800/-900/-900ER airplanes from line number 1 through 3060 except airplanes with effectivities YA001-YA013, YA201-YA203, YA231-YA240, YA251-YA252, YA271-YA271, YA301-YA302, YA311-YA312, YA501-YA508, YC001-YC007, YC051-YC052, YC071-YC072, YC101-YC101, YC301-YC301, YC321-YC322 and YE001-YE003. - 1

Airplanes with a non-integrated bulkhead installed at STA 1156. 1 Airplanes with an integrated bulkhead installed at STA 1156. 2 All 737-700/-700C/-800/-900ER airplanes from line numbers 3061 through 3469. - 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 9 of 78**DESCRIPTION CONFIGURATION**  **GROUP** 737-600/-700/-800 airplanes with effectivities YA001-YA013, YA201-YA203, YA231-YA240, YA251-YA252, YA271-YA271, YA301-YA302, YA311-YA312, YA501-YA508, YC001-YC007, YC051-YC052, YC071-YC072, YC101-YC101, YC301-YC301, YC321-YC322 and YE001-YE003. - 3

Airplane Models: 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **Group Variable Number** 3 YA001 - YA013 1 YA014 - YA099 1 YA101 - YA199 3 YA201 - YA203 1 YA204 - YA211 1 YA221 3 YA231 - YA240 1 YA241 - YA242 3 YA251 - YA252 1 YA253 - YA256 3 YA271 1 YA272 1 YA291 3 YA301 - YA302 3 YA311 - YA312 1 YA313 - YA314 1 YA321 - YA323 1 YA336 - YA345 1 YA351 1 YA356 - YA357 1 YA366 - YA367 1 YA371 - YA377 3 YA501 - YA508 1 YA509 - YA536

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 10 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YA541 - YA552 1 YA571 - YA578 1 YA601 - YA615 1 YA621 - YA622 1 YA626 - YA631 1 YA635 - YA636 1 YA641 - YA642 1 YA645 - YA650 1 YA656 - YA659 1 YA666 - YA667 1 YA671 - YA672 1 YA681 - YA691 1 YA701 - YA710 1 YA721 - YA722 1 YA731 - YA734 1 YA751 - YA756 1 YA801 - YA803 1 YA809 1 YA811 - YA814 1 YA831 - YA835 1 YA841 - YA862 1 YA881 - YA882 1 YA891 - YA892 1 YA961 - YA978 1 YB001 - YB006 1 YB101 - YB132 1 YB151 - YB153 1 YB156 - YB158 1 YB161 - YB164 1 YB171 - YB172 1 YB181 - YB184 1 YB201 - YB208 1 YB271

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 11 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YB276 1 YB301 - YB310 1 YB371 - YB392 1 YB501 - YB502 1 YB521 - YB526 1 YB541 - YB544 1 YB551 1 YB561 - YB598 1 YB601 - YB633 2 YB634 - YB635 1 YB651 1 YB656 1 YB671 - YB672 1 YB851 - YB863 1 YB871 - YB874 1 YB881 - YB893 1 YB901 - YB903 1 YB911 1 YB961 - YB974 1 YB986 - YB989 2 YB990 - YB996 3 YC001 - YC007 1 YC008 - YC030 3 YC051 - YC052 1 YC053 - YC070 3 YC071 - YC072 1 YC073 - YC084 1 YC091 - YC095 3 YC101 1 YC102 - YC104 1 YC111 - YC113 1 YC121 1 YC126 - YC127

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 12 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YC136 - YC141 1 YC146 - YC147 1 YC151 - YC156 1 YC166 - YC171 1 YC176 - YC179 1 YC186 - YC190 1 YC201 - YC203 1 YC206 - YC207 3 YC301 1 YC302 - YC305 3 YC321 - YC322 1 YC323 - YC387 1 YC391 - YC394 1 YC396 1 YC401 - YC417 1 YC421 - YC422 1 YC426 - YC428 1 YC436 - YC439 1 YC441 - YC448 1 YC451 - YC455 1 YC459 1 YC461 - YC467 1 YC471 - YC499 1 YC501 - YC526 1 YC571 - YC583 1 YC587 - YC589 1 YC591 - YC593 1 YC601 - YC655 1 YC681 - YC696 1 YC701 - YC715 1 YC720 - YC725 1 YC727 - YC752 1 YC761 - YC770

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 13 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YC781 - YC793 1 YC801 - YC892 1 YC901 - YC907 1 YC921 - YC922 1 YC931 - YC932 1 YC941 - YC951 1 YC971 - YC978 1 YC981 - YC983 1 YD001 - YD007 1 YD021 - YD025 1 YD041 - YD057 1 YD081 - YD084 1 YD101 - YD110 2 YD111 - YD112 1 YD121 - YD126 1 YD151 - YD159 1 YD171 - YD172 1 YD201 - YD203 1 YD206 - YD209 1 YD216 - YD219 1 YD251 - YD254 1 YD256 - YD257 1 YD261 1 YD301 - YD334 1 YD391 1 YD401 - YD410 1 YD412 - YD416 2 YD417 1 YD481 - YD485 1 YD491 - YD499 1 YD501 - YD512 1 YD531 - YD535 1 YD541 - YD547

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 14 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YD561 - YD564 1 YD571 - YD572 1 YD591 - YD595 1 YD601 - YD612 1 YD651 - YD655 3 YE001 - YE003 1 YE004 - YE020 1 YE051 1 YE101 - YE109 1 YE151 - YE157 1 YE171 - YE172 1 YE201 - YE206 1 YE301 - YE305 1 YE321 - YE326 1 YE371 - YE383 1 YF001 - YF006 2 YF007 - YF011 1 YF021 - YF035 2 YF036 - YF049 1 YF051 - YF058 2 YF059 - YF063 1 YF086 1 YF106 - YF107 1 YF111 - YF114 1 YF116 2 YF117 - YF118 2 YF121 - YF127 1 YF176 - YF178 1 YF191 2 YF192 1 YF201 - YF221 2 YF222 - YF271 1 YF401 - YF402

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 15 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**2 YF431 - YF432 2 YF441 - YF442 1 YF451 - YF452 2 YF453 - YF460 1 YF501 - YF541 2 YF542 - YF596 1 YF701 - YF703 2 YF704 - YF707 1 YF801 2 YF802 - YF803 1 YF831 2 YF832 2 YF836 - YF838 2 YF901 - YF905 2 YF921 - YF927 2 YF951 1 YG001 - YG044 1 YG061 - YG064 1 YG066 - YG089 1 YG091 - YG099 1 YG101 - YG103 1 YG111 - YG114 1 YG116 - YG123 2 YG124 - YG128 1 YG201 - YG205 1 YG211 - YG214 1 YG221 2 YG222 - YG224 1 YG251 - YG252 1 YG501 - YG509 2 YG510 - YG511 1 YG601 - YG602 1 YG701

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 16 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YG711 1 YH001 - YH012 1 YH031 - YH040 2 YH041 - YH050 1 YH051 - YH055 2 YH071 - YH077 1 YH101 - YH130 2 YH131 - YH132 1 YH201 - YH202 1 YH206 - YH207 1 YH301 - YH304 2 YH305 - YH306 1 YH321 - YH322 1 YJ001 - YJ013 1 YJ021 1 YJ471 - YJ480 1 YJ501 - YJ517 1 YJ531 - YJ570 2 YJ571 - YJ579 1 YJ591 - YJ599 1 YJ631 - YJ632 1 YJ671 - YJ694 1 YJ801 - YJ867 1 YJ871 - YJ879 2 YJ880 1 YJ901 - YJ904 1 YJ908 - YJ929 1 YJ931 - YJ937 1 YJ941 - YJ956 2 YJ961 1 YJ976 - YJ977 1 YK001 - YK007 1 YK101 - YK104

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 17 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YK111 - YK112 1 YK121 - YK122 1 YK131 - YK133 1 YK136 - YK139 1 YK141 - YK142 1 YK146 - YK148 1 YK151 - YK154 1 YK161 - YK167 1 YK171 1 YK176 - YK177 1 YK186 1 YK191 1 YK196 1 YK201 - YK202 1 YK301 - YK312 2 YK313 - YK314 1 YK321 - YK340 1 YK361 - YK378 1 YK401 - YK406 1 YK426 - YK427 1 YK431 - YK450 1 YK456 - YK463 2 YK464 - YK467 2 YK471 - YK473 1 YK476 1 YK480 - YK487 2 YK491 1 YK495 - YK496 2 YK497 - YK498 1 YK511 - YK516 1 YK521 - YK529 2 YK530 1 YK551 - YK571

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 18 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YK576 - YK577 1 YK580 - YK585 1 YK601 - YK602 1 YK606 - YK607 1 YK611 - YK616 1 YK621 - YK634 1 YK641 - YK644 1 YK651 - YK663 2 YK664 - YK665 1 YK671 - YK672 1 YK676 - YK677 1 YK681 - YK686 1 YK691 1 YK701 - YK713 1 YK716 - YK719 1 YK721 - YK741 1 YK751 - YK769 2 YK770 2 YK776 - YK778 2 YK781 - YK783 1 YK791 - YK792 1 YK796 - YK797 1 YK801 - YK899 1 YK901 - YK912 1 YK918 - YK919 1 YK921 - YK927 1 YK941 - YK955 2 YK956 - YK958 1 YK961 - YK974 2 YK975 - YK980 1 YK981 - YK991 2 YK992 - YK994 1 YL001 - YL005

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 19 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YL011 - YL016 1 YL021 - YL024 1 YL051 - YL052 1 YL056 - YL057 1 YL061 1 YL066 - YL069 1 YL076 - YL077 1 YL101 - YL130 2 YL131 - YL134 1 YL201 - YL214 2 YL215 - YL224 1 YL271 - YL272 1 YL281 - YL284 1 YL301 - YL303 1 YL311 - YL312 2 YL313 - YL314 1 YL316 - YL320 2 YL321 1 YL351 - YL353 1 YL371 - YL374 1 YL401 1 YL421 - YL429 1 YL431 - YL441 2 YL442 - YL444 1 YL461 - YL477 2 YL478 1 YL501 - YL509 1 YL531 - YL534 1 YL541 - YL544 1 YL561 - YL568 1 YL591 - YL592 2 YL593 - YL598 1 YL601 - YL606

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 20 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YL611 - YL612 1 YL616 - YL617 1 YL621 1 YL626 1 YL631 - YL632 2 YL633 - YL634 2 YL636 - YL637 1 YL661 - YL664 1 YL676 - YL681 1 YL691 2 YL701 - YL706 1 YL731 2 YL751 - YL752 2 YL756 1 YL761 2 YL762 - YL779 2 YL796 2 YL801 - YL813 1 YL901 - YL910 1 YL921 - YL925 2 YL926 - YL930 1 YL931 - YL936 2 YL937 - YL940 1 YL951 - YL955 2 YL956 - YL968 1 YM101 - YM103 1 YM201 - YM242 1 YM251 - YM299 1 YM301 - YM3872 YM388 - YM396 1 YM471 1 YM481 - YM4841 YM501 - YM515

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 21 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**1 YM521 - YM522 1 YM541 1 YM551 - YM553 1 YM571 - YM572 1 YM581 - YM582 1 YM591 - YM5982 YM599 1 YM631 - YM6341 YM641 - YM652 1 YM671 - YM6722 YM673 - YM6741 YM691 - YM6942 YM695 - YM698 1 YM701 - YM7102 YM761 - YM765 1 YN001 - YN016 1 YN021 - YN024 1 YN061 1 YN071 - YN082 1 YN091 - YN092 1 YN101 - YN112 1 YN121 1 YN201 - YN202 1 YN211 - YN219 1 YN231 - YN235 1 YN261 1 YQ001 2 YQ002 - YQ003 2 YQ011 - YQ014 2 YQ026 - YQ027 2 YQ036 - YQ041 2 YQ201 2 YQ231

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 22 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group**  **Variable Number**2 YQ241 2 YQ291 - YQ293 2 YQ401 - YQ402 2 YR001 - YR003 2 YR051 - YR052 2 YR101 2 YR201 2. Spares Affected None. **B. Concurrent Requirements** None. **C. Reason** The tail strobe light, located at the aft end of section 48, is not electrically bonded to a primary structure in the airplane. In case of a direct lightning strike to the tail strobe light, electromagnetic coupling and large transient voltages can be transmitted into the pressure vessel and couple to wires of the airplane systems that are routed with the light wires. Those large transient voltages can possibly cause damage to the operation of the airplane's electrical systems and avionics equipment. In addition to electromagnetic coupling, electrical current on the tail strobe light system wiring could create an ignition source. This service bulletin will add lightning protection to the tail strobe light system wiring and minimize potential fire hazard created by induced electrical current. This is done by adding 2 electrical ground paths. The primary ground path passes through the APU exhaust system to the airplane metal structure. The secondary ground path passes through the added wire bundle shields to ground any transient voltages. The electrical bonding will prevent the effects of lightning strikes to the airplane system. If the change in this service bulletin is not done, a direct lightning strike to the tail strobe light can cause damage to the operation of the airplane's systems. This service bulletin gives the instructions and a kit of parts to change the tail strobe light installation and wiring. Boeing Service Related Problem (SRP) 737NG-SRP-33-0052 is related to this service bulletin. **D. Description** At the aft end of the airplane, remove the tail strobe light L46 and replace the light housing. Drill holes on the new light housing. Install the light housing and tail strobe light L46. In the tail cone area, install a new STA 1156 bulkhead disconnect bracket. Install the new wire bundle W7152 that runs from the tail strobe light to the new disconnect bracket and install a potted insert and spacers on the tail cone wall to hold the new wire bundle. Make wiring changes to wire bundles W4724, W5726, and W7150 to remove the tail strobe light wires.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 23 of 78 **BOEING SERVICE BULLETIN 737-33-1146**Measure the electrical bonding of the new STA 1156 bulkhead disconnect bracket and the new connector D44582. Measure the electrical bonding of the tail strobe light, the light housing and aft fairing to make sure of the correct resistance. Do an operational test of tail strobe light L46 to make sure the light operates correctly. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1:**
**Affected Maintenance Zones Zone**  **Model** 211, 317, 318 737-600, 737-700, 737-700C, 737-800, 737-900, 737-900ER **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 211, 317, 318 737-700, 737-700C, 737-800, 737-900ER **Group 3:**
**Affected Maintenance Zones Zone**  **Model** 211, 317, 318 737-600, 737-700, 737-800 **E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that the change given in this service bulletin be done within 72 months after the original issue date of this service bulletin. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 24 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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. **G. Manpower** The table below shows an estimate of the task hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task hour data if necessary. The estimate does not include lost time. These are some examples of lost time: • Time to adjust to the workplace • Time to schedule the work • Time to inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools. **Group 1, Configuration 1: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.50 2.50 1 Open Access 1.00 1 1 Figure 1 1.00 1 1 Figure 3 Only Route Shows Figure 7 2.40 2.40 1 Figure 8 Only Route Shows Figure 11 0.50 0.50 1 Figure 12 0.55 0.55 1 Figure 13 2.60 2.60 1 Figure 14 2.75 4.50 2 Figure 15 2.50 2.50 1 Close Access 0.75 1.50 2 Test 16.55 19.05 TOTAL FOR EACH AIRPLANE **Group 1, Configuration 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.50 2.50 1 Open Access 1.00 1 1 Figure 1 1.00 1 1 Figure 4 Only Route Shows Figure 7

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 25 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group 1, Configuration 2:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  2.40 2.40 1 Figure 8 Only Route Shows Figure 11 0.50 0.50 1 Figure 12 0.55 0.55 1 Figure 13 2.60 2.60 1 Figure 14 2.75 4.50 2 Figure 15 2.50 2.50 1 Close Access 0.75 1.50 2 Test 16.55 19.05 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.50 2.50 1 Open Access 1.00 1.00 1 Figure 2 0.50 0.50 1 Figure 5 0.75 0.75 1 Figure 6 Only Route Shows Figure 7 2.40 2.40 1 Figure 8 Only Route Shows Figure 11 0.50 0.50 1 Figure 12 0.55 0.55 1 Figure 13 2.60 2.60 1 Figure 14 3.75 3.75 1 Figure 16 2.50 2.50 1 Close Access 0.75 1.50 2 Test 17.80 18.55 TOTAL FOR EACH AIRPLANE **Group 3: Elapsed Hours**  **Task Hours Number of Persons**  **Task** 2.50 2.50 1 Open Access 1.00 1.00 1 Figure 1 1.00 1.00 1 Figure 3

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 26 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group 3:**  **Elapsed Hours Task Hours**  **Number of Persons Task**  Only Route Shows Figure 9 1.70 1.70 1 Figure 10 Only Route Shows Figure 11 0.50 0.50 1 Figure 12 0.55 0.55 1 Figure 13 2.60 2.60 1 Figure 14 2.75 4.50 2 Figure 15 2.50 2.50 1 Close Access 0.75 1.50 2 Test 15.85 18.35 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Group 1:**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane** + 1,216.0 + 1 737-600 + 1,256.0 + 1 737-700/-700C + 1,368.0 + 1 737-800 + 1,410.0 + 1 737-900/-900ER **Group 2: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  + 1,256.0 + 1 737-700/-700C + 1,368.0 + 1 737-800 + 1,410.0 + 1 737-900ER **Group 3: Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane**  + 1,216.0 + 1 737-600 + 1,256.0 + 1 737-700 + 1,368.0 + 1 737-800

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 27 of 78 **BOEING SERVICE BULLETIN 737-33-1146 I. Electrical Load Data**  Not changed. **J. References** 1. Existing Data a. Engineering Change Memo PRR 38275-138S b. Boeing Service Related Problem (SRP) 737NG-SRP-33-0052 c. Service Bulletin Index D6-19567 d. Standard Overhaul Practices Manual (SOPM) 20-50-19 e. 737-600/700/800/900 Aircraft Maintenance Manual (AMM) 24-22-00, 27-31-00, 33-44-04, 49-81-31. f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-14-12, 20-20-00, 20-23-17, 20-25-11, 20-25-12, 20-30-11, 20-30-12, 20-61-11, 20-74-12 g. 737-600/700/800/900 Wiring Diagram Manual (WDM) 33-44-12 h. Structural Repair Manual Chapter 51 2. Data supplied with this Service Bulletin None. 3. Installation Drawings Used in the Preparation of this Service Bulletin
**Title Drawing Number** Bracket Installation 148A2605 Tailcone Integration Instl 148A7100 Wire Bundle Inst - Right Sidewall, Section 48 288A4808 Duct Instl - Eductor Inlet, APU 355A1000 Duct Instl - Exhaust, APU 354A0000 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 28 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Chapter-Section**  **Publication** 33-44 737 Aircraft Maintenance Manual 33-44 737 Wiring Diagram Manual 33-44 737 Illustrated Parts Catalog 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 29 of 78 **BOEING SERVICE BULLETIN 737-33-1146**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 30 of 78 **BOEING SERVICE BULLETIN 737-33-1146**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 **Group 1: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER**  **AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the origi**  **nal issue date of this Service Bulletin (US Dol**  **lars) Date**  **Name Kit Number** 

4,422.00 February 28, 2012 Top Kit, Retrofit - TailStrobe Light System Protection 002A0006-69

**Group 2: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER**  **AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the origi**  **nal issue date of this Service Bulletin (US Dol**  **lars) Date**  **Name Kit Number** 

2,818.00 February 28, 2012 Top Kit, Retrofit - TailStrobe Light System Protection 002A0006-90

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 31 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Group 3:**  **REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION** **Unit Price as of the origi nal issue date of this** **Service Bulletin (US Dol lars)**  **Date Name**  **Kit Number**

4,478.00 February 28, 2012 Top Kit, Retrofit - TailStrobe Light System Protection 002A0006-93

**B. Industry Support Information** Boeing warranty remedies are available for 737 airplanes in warranty as of November 6, 2007. For task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. The kits/parts for airplanes in warranty as of that date will be supplied at no charge. Send a purchase order for the kits/parts to Boeing Spares. Please refer to this service bulletin number and reference the airplane variable number in your purchase order. **C. Parts Necessary For Each Airplane** 1. Kits/Parts
**Kit 002A0006 Notes**  **Name QTY**  **New Part Number -93**  **-90 -69**  Top Kit, Retrofit - Tail Strobe Light System Protection . . - 002A0006-69

Top Kit, Retrofit - Tail Strobe Light System Protection . - . 002A0006-90

Top Kit, Retrofit - Tail Strobe Light System Protection - . . 002A0006-93

WIRE KIT-LIGHTNING PROTECTION OF TAIL STROBE LIGHTSYSTEM WIRING1 . 1 1 280A3160-1

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 32 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Kit 002A0006**  **Notes Name**  **QTY New Part Number**  **-93 -90**  **-69** WIRE KIT-LIGHTNING PROTECTION OF TAIL STROBE LIGHTSYSTEM WIRING2 1

. . 280A3160-2

(a) HOUSING ASSY - RETROFIT 1

. 1 284A3162Y6
DISCONNECT BRACKET 1 1 1 287A4811Y119 (b) BOLT, PROTRUD- ING HD 3 3 3 BACB30NX6K4 (b) BOLT, PROTRUD- ING HD . 3

. BACB30NX6K4X CLAMP, WIRE BUNDLE 3 3 3 BACC10GU102 CLAMP, WIRE BUNDLE 3 3 3 BACC10GU103 CLAMP, WIRE BUNDLE 3 3 3 BACC10GU104
COLLAR 3 3 3 BACC30BH6 INSERT, BLIND 1 1 1 BACI12AD3CM14 NUT, SELF-LOCK, HEX 4 4 4 BACN10JC04CD
SCREW 5

. 5 BACS12CK3U8 SCREW, CAP 1 1 1 BACS12GU3K17 SCREW, CAP 1 1 1 BACS12GU3K23 SCREW, CAP 3 3 3 BACS12GU3K6 WASHER 5

. 5 NAS1149C0332R WASHER 8 8 8 NAS1149DN432J (b) SCREW 4 4 4 NAS1801-04-7 SPACERS FOR RIVETS 1 1 1 NAS42DD6-40FC
SPACERS FOR RIVETS 1 1 1 NAS42DD6-64FC (a) Discard the existing part.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 33 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Kit 002A0006**  **Notes Name**  **QTY New Part Number**  **-93 -90**  **-69** (b) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if anyfasteners part numbers listed are not available or have been superseded, substitute fasteners may be supplied in kits. SRM Chapter 51 and Boeing Document D-590 are used to determine the part numbers used as substitutes.
**Kit 280A3160 Notes**  **Name QTY**  **New Part Number -104**  **-103 -102**  **-101 -2**  **-1** WIRE KIT-LIGHTNING PROTECTION OF TAIL STROBE LIGHTSYSTEM WIRING1 . . . . . - 280A3160-1

ASSY - W4724

. . . - . 1 280A3160-101 ASSY - W5726

. . - . 1

. 280A3160-102 ASSY - W7150

. - . . 1 1 280A3160-103 ASSY - W7152

- . . . 1 1 280A3160-104 WIRE KIT-LIGHTNING PROTECTION OF TAIL STROBE LIGHTSYSTEM WIRING2 . . . . - . 280A3160-2

LACING TAPE

. . . . 1 1 280A2001-1 ASSY - W4724

. . . - . 1 280A3160-101 ID - CONNECTOR

. . 1 1

. . 280A3160-10101 ID - WIRE

. . . 1

. . 280A3160-10102 ID - WIRE

. . . 1

. . 280A3160-10103 ID - SPLICE

. . . 1

. . 280A3160-10104 ID - SPLICE

. . . 1

. . 280A3160-10105 WIRE LIST

. . . 1

. . 280A3160-101W ASSY - W5726

. . - . 1

. 280A3160-102 ID - WIRE

. . 1

. . . 280A3160-10201 ID - WIRE

. . 1

. . . 280A3160-10202

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 34 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Kit 280A3160**  **Notes Name**  **QTY New Part Number**  **-104 -103**  **-102 -101**  **-2 -1**  ID - SPLICE

. . 1

. . . 280A3160-10203 ID - SPLICE

. . 1

. . . 280A3160-10204 OVERSHIELD - TUBULAR WIRE BRAID . . 1

. . . 280A3160-10205

SLEEVE - PROTECTIVE . . 1

. . . 280A3160-10206
WIRE - PIGTAIL

. . 1

. . . 280A3160-10207 WIRE LIST

. . 1

. . . 280A3160-102W ASSY - W7150

. - . . 1 1 280A3160-103 ASSY - W7152

- . . . 1 1 280A3160-104 WIRE BUNDLE - TAIL STROBE DISC. TO TAIL NAV LIGHT 1

. . . . . 286A7152-003

(a) INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 1/8", CLASS 1 . 3 3 3

. . 829A9003-180

(a) INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 3/16", CLASS 1 . . 3

. . . 829A9003-360

(a) INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 3/8", CLASS 1 . . 2

. . . 829A9003-380

TFE TAPE, PERMACEL P-440 . . . . 1 1 829A9007-075 CLAMP, LOOP

. . 1 1

. . BACC10KE10 (a) CONTACT, SOCK- ET . . 3 3

. . BACC47CP1S CONNECTOR, PLUG . . 1 1

. . BACC63BP10C5SN

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 35 of 78 **BOEING SERVICE BULLETIN 737-33-1146 Kit 280A3160**  **Notes Name**  **QTY New Part Number**  **-104 -103**  **-102 -101**  **-2 -1**  (a) SLEEVE, SOL- DER, HEAT SHRINKABLE WITH 20 AWG SHIELD WIRE . . . 7

. . BACS13CT3C

(a) SLEEVE

. . 2

. . . BACS13S232BNP (a) SLEEVE

. . 2

. . . BACS13S312CNP (a) TERMINAL, LUG

. . 2 3

. . BACT12AC3 (a) TERMINAL

. . 3

. . . BACT12C20 (a) SPLICE

. . . 3

. . D-150-0168 PLUG

. . 4 4

. . MS27488-20-1 (a) There are more parts than are necessary
**Kit 280A2001 Notes**  **Name QTY**  **New Part Number -1** LACING TAPE

- 280A2001-1 BMS13-54, TYPE I, CLASS 1, GRADE B, FINISH C, COLOR WHITE 1 N0001947

2. Parts and Materials Supplied by the Operator
**Notes Name**  **QTY Part Number /**  **Specification** (a) (b) SEALANT, BMS5-95

- A00247 (b) ALCOHOL - ISOPROPYL, TT-I-735

- B00130 (a) (b) COTTON WIPER, BMS15-5

- G00034 (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) It is permissible to use an equivalent.
3. Parts Modified and Reidentified None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 36 of 78 **BOEING SERVICE BULLETIN 737-33-1146**4. Parts Removed and Not Replaced
**Notes QTY**  **Name Existing Part**  **Number** 1 PLUG MS3126F16-8S 1 HOUSING ASSEM- BLY 65-58288-( )

1 BRACKET ASSYSPARK GAP ARRESTER 284A3862-( )

1 MARKER BAC27DEX7380 **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 37 of 78 **BOEING SERVICE BULLETIN 737-33-1146**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 38 of 78 **BOEING SERVICE BULLETIN 737-33-1146**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CAUTION:**KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:**1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. The work instructions are divided into work packages. Task Hours and Elapsed Hours for each package are given in Paragraph 1.G., Manpower. You can do each work package independently. 4. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 5. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 7. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly. 8. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 39 of 78 **BOEING SERVICE BULLETIN 737-33-1146**9. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 10. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 11. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 12. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. The removed part can be discarded if a new or serviceable part is installed. 13. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 14. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-' (dash) part number. Boeing Drawing 005W0900 contains more data. **B. WORK INSTRUCTIONS** 1. Remove electrical power from the airplane. Refer to 737-600/700/800/900 AMM 24-22-00 as an accepted procedure. 2. At the area aft of the tail cone, remove and keep the aft fairing assembly and the tail cone access door 318BR. Refer to 737-600/700/800/900 AMM 49-81-31 as an accepted procedure. 3.**Group 1, 3:** Make changes to the tail cone light assembly in accordance with FIGURE 1. 4.**Group 2:** Make changes to the tail cone light assembly in accordance with FIGURE 2. 5.**Group 1, Configuration 1; Group 3:** In the tail cone, install the new STA 1156 disconnect bracket in accordance with FIGURE 3. 6.**Group 1, Configuration 2:** In the tail cone, install the new STA 1156 disconnect bracket in accordance with FIGURE 4.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 40 of 78 **BOEING SERVICE BULLETIN 737-33-1146**7.**Group 2:** Remove the old Spark Gap Lightning Arrestor (SGLA) STA 1156 disconnect bracket and the marker and install the new disconnect bracket in accordance with FIGURE 5 and FIGURE 6. 8.**Group 1-2:** In the tail cone, remove the wire support clamps and make changes to the wire bundle W4724 in accordance with FIGURE 7 and FIGURE 8. 9.**Group 3:** In the tail cone, remove the wire support clamps and make changes to the wire bundle W5726 in accordance with FIGURE 9 and FIGURE 10. 10. In the tail cone, make wiring changes for wire bundle W7150 in accordance with FIGURE 11 and FIGURE 12. 11. In the tail cone, install the wire bundle W7152 in accordance with FIGURE 13 and FIGURE 14. 12.**Group 1, 3:** At the aft area of the tail cone, install and bond the housing assembly and aft fairing assembly in accordance with FIGURE 15. 13.**Group 2:** At the aft area of the tail cone, install and bond the housing assembly and aft fairing assembly in accordance with FIGURE 16. 14. To make sure the elevator system is free from binding or interference, do a general visual inspection of wiring around the upper & lower torque tubes and input quadrants. Make sure the wiring is secure and has appropriate clearance through full range of elevator travel. 15. Apply electrical power to the airplane. Refer to 737-600/-700/-800/-900 AMM 24-22-00 as an accepted procedure. 16. Do the Light Test for the tailcone anti-collision light assembly. Refer to 737-600/-700/-800/-900 AMM 33-44-04 as an accepted procedure. 17. Accomplish the Elevator Travel Limit test. Refer to 737-600/700/800/900 AMM 27-31-00 as an accepted procedure. 18. At the aft area of the tail cone, install the tail cone access door 318BR. Refer to 737-600/700/800/900 AMM 49-81-31 as an accepted procedure. 19. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 41 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 1, 3.** 

**FIGURE 1: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 42 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  8 BACB30NT3K2 BOLT Remove / Keep 1 8 BACN10JR3CFD NUT Remove / Keep 1 MS3126F16-8S PLUG Remove 2 8 BACS12HN3-6 BOLT Remove / Keep 3 1 30-0909-( ) LIGHT ASSEMBLY Remove / Keep 4 1 65-58288-( ) HOUSING ASSEMBLY Remove 5

**FIGURE 1: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 43 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 2.** 

**FIGURE 2: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 44 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  8 BACB30NT3K2 BOLT Remove / Keep 1 8 BACN10JR3CFD NUT Remove / Keep 5 BACS12CK3U8 SCREW Remove / Keep 5 NAS1149C0332R WASHER Remove / Keep 1 MS3126F16-8S PLUG Remove 2 8 BACS12HN3-6 BOLT Remove / Keep 3 1 30-0909-( ) LIGHT ASSEMBLY Remove / Keep 4 1 284A3162-6 STROBE HOUSING ASSEMBLY Remove / Keep 5

**FIGURE 2: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 45 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 1, Configuration 1; Group 3.** 

**FIGURE 3: INSTALLATION OF NEW DISCONNECT BRACKET AT THE STA 1156 BULKHEAD (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 46 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) (b)

- - SURFACE Clean 1 Measure to the given dimensions. Refer to view B-B. 1 287A4811-119 DISCONNECT BRACKET Put / Hold 2

(c) 1 287A4811-119 DISCONNECT BRACKET Measure
Drill three 0.187- 0.190 inch holes. 3
- HOLE Drill 3
1 287A4811-119 DISCONNECT BRACKET Install (New) 4
3 BACB30NX6K4 BOLT, PROTRUDING HD Install (New) 5
3 BACC30BH6 COLLAR Install (New) (d)

- - SURFACE Measure 6 (a) Clean and prepare the STA 1156 disconnect bracket surface for bonding in accordance with cleaning procedure 5. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure. (b) Clean and prepare the stiffener surface for bonding in accordance with cleaning procedure 1 and cleaning procedure 5. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure. (c) Maintain 0.02 minimum clearances between the upper forward edge of the 287A4811-119 disconnect bracket and the adjacent 1156 bulkhead chord. Maintain a minimum of 1.7 Dimensions fastener edge margin on the disconnect bracket and the stiffener. (d) Maximum resistance 0.5 Milliohms. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure.

**FIGURE 3: INSTALLATION OF NEW DISCONNECT BRACKET AT THE STA 1156 BULKHEAD (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 47 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 1, Configuration 2.** 

**FIGURE 4: INSTALLATION OF NEW DISCONNECT BRACKET AT THE STA 1156 BULKHEAD (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 48 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) (b)

- - SURFACE Clean 1 Measure to the given dimensions. Refer to view B-B. 1 287A4811-119 DISCONNECT BRACKET Put / Hold 2

1 287A4811-119 DISCONNECT BRACKET Measure
Drill three 0.187- 0.190 inch holes. 3
- HOLE Drill 3
1 287A4811-119 DISCONNECT BRACKET Install (New) 4
3 BACB30NX6K4 BOLT, PROTRUDING HD Install (New) 5
3 BACC30BH6 COLLAR Install (New) (c)

- - SURFACE Measure 6 (a) Clean and prepare the STA 1156 disconnect bracket surface for bonding in accordance with cleaning procedure 5. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure. (b) Clean and prepare the stiffener surface for bonding in accordance with cleaning procedure 1 and cleaning procedure 5. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure. (c) Maximum resistance 0.5 Milliohms. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure.

**FIGURE 4: INSTALLATION OF NEW DISCONNECT BRACKET AT THE STA 1156 BULKHEAD (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 49 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 2.** 

**FIGURE 5: REMOVAL OF SGLA DISCONNECT BRACKET AT STA 1156 BULKHEAD (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 50 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  3 BACB30NX6K4 BOLT, PROTRUDING HD Remove 1
3 BACC30BH6 COLLAR Remove 1 284A3862-( ) BRACKET ASSY -SPARK GAP ARRESTER Remove 2

1 BAC27DEX7380 Marker Remove 3

**FIGURE 5: REMOVAL OF SGLA DISCONNECT BRACKET AT STA 1156 BULKHEAD (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 51 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 2.** 

**FIGURE 6: INSTALLATION OF NEW DISCONNECT BRACKET AT STA 1156 BULKHEAD (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 52 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) (b)

- - SURFACE Clean 1 1 287A4811-119 DISCONNECT BRACKET Attach 2 (c) 3 BACB30NX6K4X BOLT, PROTRUDING HD Install (New) 3
3 BACC30BH6 COLLAR Install (New) (d)

- - SURFACE Measure 4 (a) Clean and prepare the STA 1156 disconnect bracket surface for bonding in accordance with cleaning procedure 5. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure. (b) Clean and prepare the stiffener surface for bonding in accordance with cleaning procedure 1 and cleaning procedure 5. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure. (c) Make sure to oversize the hole by increasing the dimensions to 0.200-0.203 inch holes in accordance with 737-600/-700/-800/-900/-900ER SRM 51-40-05. (d) Maximum resistance 0.5 Milliohms. Refer to SWPM 20-20-00 electrical fay surface bond, category 2 as an accepted procedure.

**FIGURE 6: INSTALLATION OF NEW DISCONNECT BRACKET AT STA 1156 BULKHEAD (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 53 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 1-2.** 

**FIGURE 7: WIRE ROUTING FOR WIRE BUNDLE W4724 AND INSTALLATION OF CLAMP (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 54 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Use existing fasteners. 1 BACC10GU102 CLAMP, WIRE BUN- DLE Install (New) 1

**FIGURE 7: WIRE ROUTING FOR WIRE BUNDLE W4724 AND INSTALLATION OF CLAMP (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 55 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 1-2.** 

REFER TO: 737-600/700/800/900 WDM 33-44-12

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS13-48, TYPE 12, CLASS 1, AWG 20 WIRE 1
Use to retie wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. - 280A2001-1 LACING TAPE

(a)

- 829A9007-075 TFE TAPE, PERMACEL P- 440 Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S CONTACT, SOCKET 2

**FIGURE 8: WIRE CHANGE FOR WIRE BUNDLE W4724 (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 56 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-74-12 as an accepted procedure. 6 BACS13CT3C SLEEVE, SOLDER, HEAT SHRINKABLE WITH 20 AWG SHIELD WIRE 3

Refer to SWPM 20-30-11 as an accepted procedure. 2 BACT12AC3 TERMINAL, LUG 4
Refer to SWPM 20-14-12 as an accepted procedure. 2 829A9003-180 INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 1/8", CLASS 1 5

Clock the backshell on connector D44582P to 10:00. Refer to SWPM20-61-11 as an accepted procedure. 1 BACC63BP10C5SN CONNECTOR, PLUG 6

Refer to SWPM 20-25-12 as an accepted procedure. 1 BACC10KE10 CLAMP, LOOP Imprinted "D44582P". Install ID tape within 6 inches of connector. 1 280A3160-10101 ID - CONNECTOR
Seal unused connector cavities as required. 3 MS27488-20-1 PLUG (b) 1 280A3160-10102 ID - WIRE 7 (b) 1 280A3160-10103 ID - WIRE 8 Refer to SWPM 20-30-12 as an accepted procedure. 2 D-150-0168 SPLICE 9 Imprinted "SM34". 1 280A3160-10105 ID - SPLICE 10 Imprinted "SM33". 1 280A3160-10104 ID - SPLICE 11(a) Apply Teflon tape at the strain relief clamp as necessary. Refer to SWPM 20-25-11 as an accepted procedure. (b) Re-identify the cap and stow segment of the wire from W4724-1003-20 to W4724-1013-20 and from W4724-1004-20 to W4724-1014-20. Cap and stow wires.

**FIGURE 8: WIRE CHANGE FOR WIRE BUNDLE W4724 (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 57 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 3.** 

**FIGURE 9: WIRE ROUTING FOR WIRE BUNDLE W5726 AND INSTALLATION OF CLAMP (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 58 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Use existing fasteners. 1 BACC10GU104 CLAMP, WIRE BUN- DLE Install (New) 1

**FIGURE 9: WIRE ROUTING FOR WIRE BUNDLE W5726 AND INSTALLATION OF CLAMP (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 59 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 3.** 

REFER TO: 737-600/700/800/900 WDM 33-44-12 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  2 BMS13-48, TYPE 10, CLASS 1, AWG 20 WIRE 1
Use to retie wire bundle. Refer to SWPM 20-10-11 as an accepted procedure. - 280A2001-1 LACING TAPE

(a)

- 829A9007-075 TFE TAPE, PERMACEL P- 440

**FIGURE 10: WIRE CHANGE FOR WIRE BUNDLE W5726 (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 60 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-61-11 as an accepted procedure. 2 BACC47CP1S CONTACT, SOCKET 2
Refer to SWPM 20-23-17 as an accepted procedure. 1 BACS13S232BNP SLEEVE 3
Refer to SWPM 20-23-17 as an accepted procedure. 1 BACS13S312CNP SLEEVE
Refer to SWPM 20-14-12 as an accepted procedure. 1 829A9003-380 INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 3/8'', CLASS 1 Refer to SWPM 20-30-11 as an accepted procedure. 1 BACT12AC3 TERMINAL, LUG 4
Refer to SWPM 20-14-12 as an accepted procedure. 2 829A9003-180 INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 1/8", CLASS 1 5

(b) 1 280A3160-10201 ID - WIRE 6 (b) 1 280A3160-10202 ID - WIRE 7 Refer to SWPM 20-61-11 as an accepted procedure. 1 BACC63BP10C5SN CONNECTOR, PLUG 8
Refer to SWPM 20-25-12 as an accepted procedure. 1 BACC10KE10 CLAMP, LOOP Imprinted "D44582P". Install ID tape within 6 inches of connector. 1 280A3160-10101 ID - CONNECTOR
Seal unused connector cavities as required. 3 MS27488-20-1 PLUG
Refer to SWPM 20-30-12 as an accepted procedure. 2 BACT12C20 TERMINAL 9 Imprinted "SM24". 1 280A3160-10204 ID - SPLICE 10 Imprinted "SM23". 1 280A3160-10203 ID - SPLICE 11 Refer to SWPM 20-14-12 as an accepted procedure. 2 829A9003-360 INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 3/16'', CLASS 1 12

(c) 1 280A3160-10206 SLEEVE - PROTECTIVE 13 (d) (e) (f) 1 280A3160-10205 OVERSHIELD - TUBULAR WIRE BRAID 14

**FIGURE 10: WIRE CHANGE FOR WIRE BUNDLE W5726 (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 61 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** 1 280A3160-10207 WIRE - PIGTAIL 15(a) Apply Teflon tape at the strain relief clamp as necessary. Refer to SWPM 20-25-11 as an accepted procedure. (b) Re-identify the cap and stow segment of the wire from W5726-0003-20 to W5726-0043-20 and from W5726-0004-20 to W5726-0044-20. Cap and stow wires under the overbraids. (c) Cut the expando sleeve to the required length that is needed to install the expando sleeve over the wires starting at the connector D44582P to the point where wires W5726-0003-20 and W5726-0004-20 break out of the wire bundle. (d) Install the overbraids over the wires starting at the connector to the point where wires W5726-0003-20 and W5726-0004-20 break out of the wire bundle. (e) Install the remaining expando sleeve over the same length after the installation of the overbraid. (f) Connect between the existing wire bundle overbraid shields and the new wire bundle overbraid shields. Refer to SWPM 20-25-11 as an accepted procedure.

**FIGURE 10: WIRE CHANGE FOR WIRE BUNDLE W5726 (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 62 of 78 **BOEING SERVICE BULLETIN 737-33-1146 FIGURE 11: WIRE ROUTING FOR WIRE BUNDLE W7150**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 63 of 78 **BOEING SERVICE BULLETIN 737-33-1146**REFER TO: 737-600/700/800/900 WDM 33-44-12 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  (a) 2 829A9003-180 INSULATION SLEEVING, HEAT SHRINKABLE, BLACK, IN DIA 1/8", CLASS 1 1

(a) Cap and stow the wires near the wire bundle W7150 breakout. Remove the wire segment from the tail strobe connector to the breakout.

**FIGURE 12: WIRE CHANGE FOR WIRE BUNDLE W7150 (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 64 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.

**FIGURE 13: WIRE ROUTING FOR WIRE BUNDLE W7152 AND INSTALLATION OF POTTED INSERT AND SPACERS**  **(SHEET 1 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 65 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a) 1 BACI12AD3CM14 INSERT, BLIND Insert 1 1 BACC10GU103 CLAMP, WIRE BUN- DLE Install (New)

1 BACS12GU3K6 SCREW, CAP Install (New) 1 BACC10GU102 CLAMP, WIRE BUN- DLE Install (New) 2
2 NAS42DD6-40FC SPACERS FOR RIV- ETS Install (New) 3
1 BACC10GU103 CLAMP, WIRE BUN- DLE Install (New)

1 BACS12GU3K17 SCREW, CAP Install (New) 1 BACC10GU102 CLAMP, WIRE BUN- DLE Install (New) 4
1 NAS42DD6-64FC SPACERS FOR RIV- ETS Install (New) 5
1 BACC10GU104 CLAMP, WIRE BUN- DLE Install (New)

1 BACS12GU3K23 SCREW, CAP Install (New) 1 BACC10GU104 CLAMP, WIRE BUN- DLE Install (New) 6
1 BACS12GU3K6 SCREW, CAP Install (New) 1 BACC10GU103 CLAMP, WIRE BUN- DLE Install (New) 7
1 BACS12GU3K6 SCREW, CAP Install (New) (b) (c)

- - SURFACE Clean 8 (d) 1 280A3160-104 ASSY - W7152 Install (New) 9 1 BACC63BV10F5S CONNECTOR Install (New) 10 4 NAS1149DN432J WASHER Install (New) 4 NAS1801-04-7 SCREW Install (New) 4 BACN10JC04CD NUT Install (New) 4 NAS1149DN432J WASHER Install (New) 1 BACC63BP10C5SL PLUG Connect 11 (e)

- - SURFACE Measure 12 (a) Install at STA 1169.33, BL 15.91, and WL 287.

**FIGURE 13: WIRE ROUTING FOR WIRE BUNDLE W7152 AND INSTALLATION OF POTTED INSERT AND SPACERS**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 66 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (b) Clean and prepare the STA 1156 disconnect bracket surface for bonding in accordance with cleaning procedure 5. Refer to SWPM 20-20-00 bonding of receptacle connectors as an accepted procedure. (c) Clean and prepare the connector's surface for bonding in accordance with cleaning procedure 5. Refer to SWPM 20-20-00 bonding of receptacle connectors as an accepted procedure.(d) Wire bundle W7152 is a prefabricated wire bundle, including connectors. You may want to hold the installation of the plug for the connector D148 after the installation of the strobe light housing in figure 14. (e) Maximum resistance of 1.5 Milliohms, Refer to SWPM 20-20-00 bonding of receptacle connectors as an accepted procedure.

**FIGURE 13: WIRE ROUTING FOR WIRE BUNDLE W7152 AND INSTALLATION OF POTTED INSERT AND SPACERS**  **(SHEET 3 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 67 of 78 **BOEING SERVICE BULLETIN 737-33-1146**REFER TO: 737-600/700/800/900 WDM 33-44-12 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

**MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  (a) (b) 1 286A7152-003 WIRE BUNDLE - TAIL STROBE DISC. TO TAIL NAV LIGHT 1

(a) Make sure to bond both ends of the wire bundle. Refer to SWPM 20-20-00 bonding of receptacle connectors as an accepted procedure.(b) Apply Teflon tape at the strain relief clamp as necessary. Refer to SWPM 20-25-11 as an accepted procedure.

**FIGURE 14: WIRE CHANGE FOR WIRE BUNDLE W7152 (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 68 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 1, 3.** 

**FIGURE 15: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 69 of 78 **BOEING SERVICE BULLETIN 737-33-1146 FIGURE 15: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT**  **HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG (SHEET 2 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 70 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.

**FIGURE 15: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 71 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a)

- - SURFACE Clean 1 (b)

- - SURFACE Prepare 2 (c) 1 355A1010-( ) DUCT ASSY - EDUC- TOR INLET, APU Put 3
1 354A4000-( ) FAIRING ASSY, UP- PER Install (Kept) 4 (d) 6 BACS12CK3U8 SCREW Install (Kept) 5 6 NAS1149C0332R WASHER Install (Kept) (e) 1 354A3000-( ) MUFFLER ASSY-EXH, APU Put 6 (f) 1 354A4000-( ) FAIRING ASSY - LOWER Install (Kept) 7 (g) 39 BACS12CK3U8 SCREW Install (Kept) 8 39 NAS1523C3R WASHER Install (Kept) 9 BACS12CK3U7 SCREW Install (Kept) 9 9 NAS1523C3R WASHER Install (Kept) (h)

- - SURFACE Measure 10 (k)

- - SURFACE Prepare 11 (l) 1 30-0909-( ) LIGHT ASSEMBLY Attach 12 8 BACS12HN3-6 BOLT Install (Kept) (m)

- - SURFACE Measure 13 Connect the newplug to the light assembly. 1 MS3126F16-8S PLUG Connect 14

(n)

- - SURFACE Measure 15 1 284A3162Y6 HOUSING ASSY - RETROFIT Align 16 (i) 5
- HOLE Drill (j) 8
- HOLE Drill Refer to 737- 600/700/800/900 AMM 33-44-04 asan accepted procedure. 1 284A3162Y6 HOUSING ASSY - RETROFIT Install (New) 17

**FIGURE 15: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 4 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 72 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** 8 BACB30NT3K2 BOLT Install (Kept) 18 8 BACN10JR3CFD NUT Install (Kept) (o)

- - SURFACE Prepare 19 5 BACS12CK3U8 SCREW Install (New) 20 5 NAS1149C0332R WASHER Install (New) (p)

- - SURFACE Measure 21 (a) Refer to 737-600/700/800/900 AMM 49-81-31 as an accepted procedure. (b) Prepare lower fairing surface and upper fairing surface for bonding per solvent cleaning method CM3. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. (c) Remove the temporary materials (cord or equivalent), if installed, from the eductor inlet duct. (d) Install (6) BACS12CK3U8 screws and (6) NAS1149CD332R washers to hold the upper aft fairing assembly. (e) Remove the temporary materials (cord, foam pad or equivalent), if installed, from the exhaust duct muffler. (f) The screws for the lower aft fairing must be tightened in the correct sequence. The correct sequence is to start at the bottom screw location, then the left adjacent side and then the right adjacent side until all the screws are tightened at the top of the lower aft fairing. (g) Apply BMS5-95 fillet seal to the edge periphery of the lower fairing after fasteners are secured. Refer to SOPM 20-50-19 as an accepted procedure. (h) Use maximum resistance of 1 Milliohm. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. (i) Match the (5) holes located on the lower side of the upper fairing assembly with the new housing assembly and drill (5) holes 0.279-0.0291 on the lower edge of the housing assembly. Remove the unwanted sealant from the lower aft fairing with a cotton wiper, G00034, or an equivalent. (j) Match the existing (8) holes located on the tail cone wall with the new housing assembly and drill (8) holes 0.218-0.229 on the upper side of the housing assembly. (k) Prepare the light assembly surface and the housing assembly surface for bonding per solvent cleaning method CM3. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. To hold the light assembly to the housing assembly. (l) Attach the light assembly to the new housing assembly using the (8) bolts. (m) Use maximum resistance of 2.5 Milliohms. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. Apply BMS5-95 sealant or equivalent around the edge surfaces of the lower aft fairing. (n) Make sure that the plug is tightened. Measure and record the resistance between the tail strobe light and the new connector. The resistance measured must not exceed 3.0 Milliohms. (o) Prepare the new housing assembly surface and eductor fairing surface per solvent cleaning method CM3. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. (p) Use maximum resistance of 1 Milliohm. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure.

**FIGURE 15: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 5 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 73 of 78 **BOEING SERVICE BULLETIN 737-33-1146 This Figure applies only to: Group 2.** 

**FIGURE 16: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 74 of 78 **BOEING SERVICE BULLETIN 737-33-1146 FIGURE 16: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT**  **HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG (SHEET 2 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 75 of 78 **BOEING SERVICE BULLETIN 737-33-1146**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 this figure.

**FIGURE 16: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 3 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 76 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a)

- - SURFACE Clean 1 (b)

- - SURFACE Prepare 2 (c) 1 355A1010-( ) DUCT ASSY - EDUC- TOR INLET, APU Put 3
1 354A4000-( ) FAIRING ASSY, UP- PER Install (Kept) 4 (d) 6 BACS12CK3U8 SCREW Install (Kept) 5 6 NAS1149C0332R WASHER Install (Kept) (e) 1 354A3000-( ) MUFFLER ASSY-EXH, APU Put 6 (f) 1 354A4000-( ) FAIRING ASSY - LOWER Install (Kept) 7 (g) 39 BACS12CK3U8 SCREW Install (Kept) 8 39 NAS1523C3R WASHER Install (Kept) 9 BACS12CK3U7 SCREW Install (Kept) 9 9 NAS1523C3R WASHER Install (Kept) (h)

- - SURFACE Measure 10 (i)

- - SURFACE Prepare 11 (j) 1 30-0909-( ) LIGHT ASSEMBLY Attach 12 8 BACS12HN3-6 BOLT Install (Kept) (k)

- - SURFACE Measure 13 Connect the newplug to the light assembly. 1 MS3126F16-8S PLUG Connect 14

(l)

- - SURFACE Measure 15 Refer to 737- 600/700/800/900 AMM 33-44-04 asan accepted procedure. 1 284A3162-6 STROBE HOUSING ASSEMBLY Install (Kept) 16

8 BACB30NT3K2 BOLT Install (Kept) 17 8 BACN10JR3CFD NUT Install (Kept) (m)

- - SURFACE Prepare 18 5 BACS12CK3U8 SCREW Install (Kept) 19 5 NAS1149C0332R WASHER Install (Kept)

**FIGURE 16: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 4 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 77 of 78 **BOEING SERVICE BULLETIN 737-33-1146 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (n)

- - SURFACE Measure 20 (a) Refer to 737-600/700/800/900 AMM 49-81-31 as an accepted procedure. (b) Prepare lower fairing surface and upper fairing surface for bonding per solvent cleaning method CM3. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. (c) Remove the temporary materials (cord or equivalent), if installed, from the eductor inlet duct. (d) Install (6) BACS12CK3U8 screws and (6) NAS1149CD332R washers to hold the upper aft fairing assembly. (e) Remove the temporary materials (cord, foam pad or equivalent), if installed, from the exhaust duct muffler. (f) The screws for the lower aft fairing must be tightened in the correct sequence. The correct sequence is to start at the bottom screw location, then the left adjacent side and then the right adjacent side until all the screws are tightened at the top of the lower aft fairing. (g) Apply BMS5-95 fillet seal to the edge periphery of the lower fairing after fasteners are secured. Refer to SOPM 20-50-19 as an accepted procedure. (h) Use maximum resistance of 1 Milliohm. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. (i) Prepare the light assembly surface and the housing assembly surface for bonding per solvent cleaning method CM3. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. To hold the light assembly to the housing assembly. (j) Attach the light assembly to the new housing assembly using the (8) bolts. (k) Use maximum resistance of 2.5 Milliohms. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. Apply BMS5-95 sealant or equivalent around the edge surfaces of the lower aft fairing. (l) Make sure that the plug is tightened. Measure and record the resistance between the tail strobe light and the new connector. The resistance measured must not exceed 3.0 Milliohms. (m) Prepare the new housing assembly surface and eductor fairing surface per solvent cleaning method CM3. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure. (n) Use maximum resistance of 1 Milliohm. Refer to SWPM 20-20-00 electrical fay surface bond, category 1 as an accepted procedure.

**FIGURE 16: INSTALLATION AND BONDING RESISTANCE CHECK FOR THE TAIL STROBE LIGHT HOUSING ASSEMBLY, THE TAIL CONE FAIRING ASSEMBLIES, AND THE L46 LIGHT CONNECTOR PLUG**  **(SHEET 5 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: November 02, 2011 737-33-1146 78 of 78 **BOEING SERVICE BULLETIN 737-33-1146**