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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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

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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

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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

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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.

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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.

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

Airplanes Total Task Hours Elapsed Hours

Group 1 Configu- 19.05 16.55

ration 1

Group 1 Configu- 19.05 16.55

ration 2

Group 2 18.55 17.80

Group 3 18.35 15.85

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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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.

GROUP CONFIGURATION DESCRIPTION

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 -

1 Airplanes with a non-integrated bulkhead installed at STA 1156.

2 Airplanes with an integrated bulkhead installed at STA 1156.

All 737-700/-700C/-800/-900ER airplanes from line numbers 3061

through 3469.

2 -

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GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

YA001 - YA013 3

YA014 - YA099 1

YA101 - YA199 1

YA201 - YA203 3

YA204 - YA211 1

YA221 1

YA231 - YA240 3

YA241 - YA242 1

YA251 - YA252 3

YA253 - YA256 1

YA271 3

YA272 1

YA291 1

YA301 - YA302 3

YA311 - YA312 3

YA313 - YA314 1

YA321 - YA323 1

YA336 - YA345 1

YA351 1

YA356 - YA357 1

YA366 - YA367 1

YA371 - YA377 1

YA501 - YA508 3

YA509 - YA536 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

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 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

YB276 1

YB301 - YB310 1

YB371 - YB392 1

YB501 - YB502 1

YB521 - YB526 1

YB541 - YB544 1

YB551 1

YB561 - YB598 1

YB601 - YB633 1

YB634 - YB635 2

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 1

YB990 - YB996 2

YC001 - YC007 3

YC008 - YC030 1

YC051 - YC052 3

YC053 - YC070 1

YC071 - YC072 3

YC073 - YC084 1

YC091 - YC095 1

YC101 3

YC102 - YC104 1

YC111 - YC113 1

YC121 1

YC126 - YC127 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

YC136 - YC141 1

YC146 - YC147 1

YC151 - YC156 1

YC166 - YC171 1

YC176 - YC179 1

YC186 - YC190 1

YC201 - YC203 1

YC206 - YC207 1

YC301 3

YC302 - YC305 1

YC321 - YC322 3

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 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

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 1

YD111 - YD112 2

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 1

YD417 2

YD481 - YD485 1

YD491 - YD499 1

YD501 - YD512 1

YD531 - YD535 1

YD541 - YD547 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

YD561 - YD564 1

YD571 - YD572 1

YD591 - YD595 1

YD601 - YD612 1

YD651 - YD655 1

YE001 - YE003 3

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 1

YF007 - YF011 2

YF021 - YF035 1

YF036 - YF049 2

YF051 - YF058 1

YF059 - YF063 2

YF086 1

YF106 - YF107 1

YF111 - YF114 1

YF116 1

YF117 - YF118 2

YF121 - YF127 2

YF176 - YF178 1

YF191 1

YF192 2

YF201 - YF221 1

YF222 - YF271 2

YF401 - YF402 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

YF431 - YF432 2

YF441 - YF442 2

YF451 - YF452 1

YF453 - YF460 2

YF501 - YF541 1

YF542 - YF596 2

YF701 - YF703 1

YF704 - YF707 2

YF801 1

YF802 - YF803 2

YF831 1

YF832 2

YF836 - YF838 2

YF901 - YF905 2

YF921 - YF927 2

YF951 2

YG001 - YG044 1

YG061 - YG064 1

YG066 - YG089 1

YG091 - YG099 1

YG101 - YG103 1

YG111 - YG114 1

YG116 - YG123 1

YG124 - YG128 2

YG201 - YG205 1

YG211 - YG214 1

YG221 1

YG222 - YG224 2

YG251 - YG252 1

YG501 - YG509 1

YG510 - YG511 2

YG601 - YG602 1

YG701 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

YG711 1

YH001 - YH012 1

YH031 - YH040 1

YH041 - YH050 2

YH051 - YH055 1

YH071 - YH077 2

YH101 - YH130 1

YH131 - YH132 2

YH201 - YH202 1

YH206 - YH207 1

YH301 - YH304 1

YH305 - YH306 2

YH321 - YH322 1

YJ001 - YJ013 1

YJ021 1

YJ471 - YJ480 1

YJ501 - YJ517 1

YJ531 - YJ570 1

YJ571 - YJ579 2

YJ591 - YJ599 1

YJ631 - YJ632 1

YJ671 - YJ694 1

YJ801 - YJ867 1

YJ871 - YJ879 1

YJ880 2

YJ901 - YJ904 1

YJ908 - YJ929 1

YJ931 - YJ937 1

YJ941 - YJ956 1

YJ961 2

YJ976 - YJ977 1

YK001 - YK007 1

YK101 - YK104 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

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 1

YK313 - YK314 2

YK321 - YK340 1

YK361 - YK378 1

YK401 - YK406 1

YK426 - YK427 1

YK431 - YK450 1

YK456 - YK463 1

YK464 - YK467 2

YK471 - YK473 2

YK476 1

YK480 - YK487 1

YK491 2

YK495 - YK496 1

YK497 - YK498 2

YK511 - YK516 1

YK521 - YK529 1

YK530 2

YK551 - YK571 1

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Variable Number Group

YK576 - YK577 1

YK580 - YK585 1

YK601 - YK602 1

YK606 - YK607 1

YK611 - YK616 1

YK621 - YK634 1

YK641 - YK644 1

YK651 - YK663 1

YK664 - YK665 2

YK671 - YK672 1

YK676 - YK677 1

YK681 - YK686 1

YK691 1

YK701 - YK713 1

YK716 - YK719 1

YK721 - YK741 1

YK751 - YK769 1

YK770 2

YK776 - YK778 2

YK781 - YK783 2

YK791 - YK792 1

YK796 - YK797 1

YK801 - YK899 1

YK901 - YK912 1

YK918 - YK919 1

YK921 - YK927 1

YK941 - YK955 1

YK956 - YK958 2

YK961 - YK974 1

YK975 - YK980 2

YK981 - YK991 1

YK992 - YK994 2

YL001 - YL005 1

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BOEING SERVICE BULLETIN 737-33-1146
Variable Number Group

YL011 - YL016 1

YL021 - YL024 1

YL051 - YL052 1

YL056 - YL057 1

YL061 1

YL066 - YL069 1

YL076 - YL077 1

YL101 - YL130 1

YL131 - YL134 2

YL201 - YL214 1

YL215 - YL224 2

YL271 - YL272 1

YL281 - YL284 1

YL301 - YL303 1

YL311 - YL312 1

YL313 - YL314 2

YL316 - YL320 1

YL321 2

YL351 - YL353 1

YL371 - YL374 1

YL401 1

YL421 - YL429 1

YL431 - YL441 1

YL442 - YL444 2

YL461 - YL477 1

YL478 2

YL501 - YL509 1

YL531 - YL534 1

YL541 - YL544 1

YL561 - YL568 1

YL591 - YL592 1

YL593 - YL598 2

YL601 - YL606 1

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Variable Number Group

YL611 - YL612 1

YL616 - YL617 1

YL621 1

YL626 1

YL631 - YL632 1

YL633 - YL634 2

YL636 - YL637 2

YL661 - YL664 1

YL676 - YL681 1

YL691 1

YL701 - YL706 2

YL731 1

YL751 - YL752 2

YL756 2

YL761 1

YL762 - YL779 2

YL796 2

YL801 - YL813 2

YL901 - YL910 1

YL921 - YL925 1

YL926 - YL930 2

YL931 - YL936 1

YL937 - YL940 2

YL951 - YL955 1

YL956 - YL968 2

YM101 - YM103 1

YM201 - YM242 1

YM251 - YM299 1

YM301 - YM387 1

YM388 - YM396 2

YM471 1

YM481 - YM484 1

YM501 - YM515 1

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Variable Number Group

YM521 - YM522 1

YM541 1

YM551 - YM553 1

YM571 - YM572 1

YM581 - YM582 1

YM591 - YM598 1

YM599 2

YM631 - YM634 1

YM641 - YM652 1

YM671 - YM672 1

YM673 - YM674 2

YM691 - YM694 1

YM695 - YM698 2

YM701 - YM710 1

YM761 - YM765 2

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 1

YQ002 - YQ003 2

YQ011 - YQ014 2

YQ026 - YQ027 2

YQ036 - YQ041 2

YQ201 2

YQ231 2

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Variable Number Group

YQ241 2

YQ291 - YQ293 2

YQ401 - YQ402 2

YR001 - YR003 2

YR051 - YR052 2

YR101 2

YR201 2

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.

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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

Model Zone

737-600, 737-700, 737-700C, 211, 317, 318

737-800, 737-900, 737-900ER

Group 2:

Affected Maintenance Zones

Model Zone

737-700, 737-700C, 737-800, 211, 317, 318

737-900ER

Group 3:

Affected Maintenance Zones

Model Zone

737-600, 737-700, 737-800 211, 317, 318

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.

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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:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.50 2.50

Figure 1 1 1 1.00

Figure 3 1 1 1.00

Figure 7 Shows Route Only

Figure 8 1 2.40 2.40

Figure 11 Shows Route Only

Figure 12 1 0.50 0.50

Figure 13 1 0.55 0.55

Figure 14 1 2.60 2.60

Figure 15 2 4.50 2.75

Close Access 1 2.50 2.50

Test 2 1.50 0.75

TOTAL FOR EACH AIRPLANE 19.05 16.55

Group 1, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.50 2.50

Figure 1 1 1 1.00

Figure 4 1 1 1.00

Figure 7 Shows Route Only

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Group 1, Configuration 2:

Task Number of Persons Task Hours Elapsed Hours

Figure 8 1 2.40 2.40

Figure 11 Shows Route Only

Figure 12 1 0.50 0.50

Figure 13 1 0.55 0.55

Figure 14 1 2.60 2.60

Figure 15 2 4.50 2.75

Close Access 1 2.50 2.50

Test 2 1.50 0.75

TOTAL FOR EACH AIRPLANE 19.05 16.55

Group 2:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.50 2.50

Figure 2 1 1.00 1.00

Figure 5 1 0.50 0.50

Figure 6 1 0.75 0.75

Figure 7 Shows Route Only

Figure 8 1 2.40 2.40

Figure 11 Shows Route Only

Figure 12 1 0.50 0.50

Figure 13 1 0.55 0.55

Figure 14 1 2.60 2.60

Figure 16 1 3.75 3.75

Close Access 1 2.50 2.50

Test 2 1.50 0.75

TOTAL FOR EACH AIRPLANE 18.55 17.80

Group 3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 2.50 2.50

Figure 1 1 1.00 1.00

Figure 3 1 1.00 1.00

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Group 3:

Task Number of Persons Task Hours Elapsed Hours

Figure 9 Shows Route Only

Figure 10 1 1.70 1.70

Figure 11 Shows Route Only

Figure 12 1 0.50 0.50

Figure 13 1 0.55 0.55

Figure 14 1 2.60 2.60

Figure 15 2 4.50 2.75

Close Access 1 2.50 2.50

Test 2 1.50 0.75

TOTAL FOR EACH AIRPLANE 18.35 15.85

H. Weight and Balance Changes

Group 1:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

737-600 + 1 + 1,216.0

737-700/-700C + 1 + 1,256.0

737-800 + 1 + 1,368.0

737-900/-900ER + 1 + 1,410.0

Group 2:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

737-700/-700C + 1 + 1,256.0

737-800 + 1 + 1,368.0

737-900ER + 1 + 1,410.0

Group 3:

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

737-600 + 1 + 1,216.0

737-700 + 1 + 1,256.0

737-800 + 1 + 1,368.0

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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

Drawing Number Title

148A2605 Bracket Installation

148A7100 Tailcone Integration Instl

288A4808 Wire Bundle Inst - Right Sidewall, Section 48

355A1000 Duct Instl - Eductor Inlet, APU

354A0000 Duct Instl - Exhaust, APU

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:

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BOEING SERVICE BULLETIN 737-33-1146
Publication Chapter-Section

737 Aircraft Maintenance Manual 33-44

737 Wiring Diagram Manual 33-44

737 Illustrated Parts Catalog 33-44

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.

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BOEING SERVICE BULLETIN 737-33-1146
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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 original issue date of this

Service Bulletin (US Dollars)

Kit Number Name Date

Top Kit, Retrofit - Tail February 28, 2012 4,422.00

Strobe 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 original issue date of this

Service Bulletin (US Dollars)

Kit Number Name Date

Top Kit, Retrofit - Tail February 28, 2012 2,818.00

Strobe Light System Protection

002A0006-90

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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 original issue date of this

Service Bulletin (US Dollars)

Kit Number Name Date

Top Kit, Retrofit - Tail February 28, 2012 4,478.00

Strobe 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

New Part Number QTY Name Notes

-69 -90 -93

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 LIGHT

SYSTEM WIRING1

280A3160-1 1 1 .

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BOEING SERVICE BULLETIN 737-33-1146
Kit 002A0006

New Part Number QTY Name Notes

-69 -90 -93

WIRE KIT-LIGHTNING PROTECTION OF TAIL

STROBE LIGHT

SYSTEM WIRING2

280A3160-2 . . 1

HOUSING ASSY - (a)

RETROFIT

284A3162Y6 1 . 1

DISCONNECT

BRACKET

287A4811Y119 1 1 1

BOLT, PROTRUD- (b)

ING HD

BACB30NX6K4 3 3 3

BOLT, PROTRUD- (b)

ING HD

BACB30NX6K4X . 3 .

CLAMP, WIRE

BUNDLE

BACC10GU102 3 3 3

CLAMP, WIRE

BUNDLE

BACC10GU103 3 3 3

CLAMP, WIRE

BUNDLE

BACC10GU104 3 3 3

BACC30BH6 3 3 3 COLLAR

BACI12AD3CM14 1 1 1 INSERT, BLIND

NUT, SELF-LOCK,

HEX

BACN10JC04CD 4 4 4

BACS12CK3U8 5 . 5 SCREW

BACS12GU3K17 1 1 1 SCREW, CAP

BACS12GU3K23 1 1 1 SCREW, CAP

BACS12GU3K6 3 3 3 SCREW, CAP

NAS1149C0332R 5 . 5 WASHER

NAS1149DN432J 8 8 8 WASHER

NAS1801-04-7 4 4 4 SCREW (b)

SPACERS FOR

RIVETS

NAS42DD6-40FC 1 1 1

SPACERS FOR

RIVETS

NAS42DD6-64FC 1 1 1

(a) Discard the existing part.

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BOEING SERVICE BULLETIN 737-33-1146
Kit 002A0006

New Part Number QTY Name Notes

-69 -90 -93

(b) If grip length shown is not available at Boeing, fasteners supplied

in kits may be one grip length longer than indicated. Also, if any

fasteners 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

New Part Number QTY Name Notes

-1 -2 -101 -102 -103 -104

WIRE KIT-LIGHTNING PROTECTION OF TAIL

STROBE LIGHT

SYSTEM WIRING1

280A3160-1 - . . . . .

280A3160-101 1 . - . . . ASSY - W4724

280A3160-102 . 1 . - . . ASSY - W5726

280A3160-103 1 1 . . - . ASSY - W7150

280A3160-104 1 1 . . . - ASSY - W7152

WIRE KIT-LIGHTNING PROTECTION OF TAIL

STROBE LIGHT

SYSTEM WIRING2

280A3160-2 . - . . . .

280A2001-1 1 1 . . . . LACING TAPE

280A3160-101 1 . - . . . ASSY - W4724

280A3160-10101 . . 1 1 . . ID - CONNECTOR

280A3160-10102 . . 1 . . . ID - WIRE

280A3160-10103 . . 1 . . . ID - WIRE

280A3160-10104 . . 1 . . . ID - SPLICE

280A3160-10105 . . 1 . . . ID - SPLICE

280A3160-101W . . 1 . . . WIRE LIST

280A3160-102 . 1 . - . . ASSY - W5726

280A3160-10201 . . . 1 . . ID - WIRE

280A3160-10202 . . . 1 . . ID - WIRE

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BOEING SERVICE BULLETIN 737-33-1146
Kit 280A3160

New Part Number QTY Name Notes

-1 -2 -101 -102 -103 -104

280A3160-10203 . . . 1 . . ID - SPLICE

280A3160-10204 . . . 1 . . ID - SPLICE

OVERSHIELD -

TUBULAR WIRE

BRAID

280A3160-10205 . . . 1 . .

SLEEVE - PROTECTIVE280A3160-10206 . . . 1 . .

280A3160-10207 . . . 1 . . WIRE - PIGTAIL

280A3160-102W . . . 1 . . WIRE LIST

280A3160-103 1 1 . . - . ASSY - W7150

280A3160-104 1 1 . . . - ASSY - W7152

WIRE BUNDLE -

TAIL STROBE

DISC. TO TAIL

NAV LIGHT

286A7152-003 . . . . . 1

INSULATION (a)

SLEEVING, HEAT

SHRINKABLE,

BLACK, IN DIA

1/8", CLASS 1

829A9003-180 . . 3 3 3 .

INSULATION (a)

SLEEVING, HEAT

SHRINKABLE,

BLACK, IN DIA

3/16", CLASS 1

829A9003-360 . . . 3 . .

INSULATION (a)

SLEEVING, HEAT

SHRINKABLE,

BLACK, IN DIA

3/8", CLASS 1

829A9003-380 . . . 2 . .

TFE TAPE, PERMACEL P-440829A9007-075 1 1 . . . .

BACC10KE10 . . 1 1 . . CLAMP, LOOP

CONTACT, SOCK- (a)

ET

BACC47CP1S . . 3 3 . .

CONNECTOR,

PLUG

BACC63BP10C5SN . . 1 1 . .

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BOEING SERVICE BULLETIN 737-33-1146
Kit 280A3160

New Part Number QTY Name Notes

-1 -2 -101 -102 -103 -104

SLEEVE, SOL- (a)

DER, HEAT

SHRINKABLE

WITH 20 AWG

SHIELD WIRE

BACS13CT3C . . 7 . . .

BACS13S232BNP . . . 2 . . SLEEVE (a)

BACS13S312CNP . . . 2 . . SLEEVE (a)

BACT12AC3 . . 3 2 . . TERMINAL, LUG (a)

BACT12C20 . . . 3 . . TERMINAL (a)

D-150-0168 . . 3 . . . SPLICE (a)

MS27488-20-1 . . 4 4 . . PLUG

(a) There are more parts than are necessary

Kit 280A2001

New Part Number QTY Name Notes

-1

280A2001-1 - LACING TAPE

BMS13-54, TYPE

I, CLASS 1,

GRADE B, FINISH

C, COLOR WHITE

N0001947 1

2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

A00247 - SEALANT, BMS5-95 (a) (b)

B00130 - ALCOHOL - ISOPROPYL, TT-I-735 (b)

G00034 - COTTON WIPER, BMS15-5 (a) (b)

(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.

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BOEING SERVICE BULLETIN 737-33-1146
4. Parts Removed and Not Replaced

Existing Part Name QTY Notes

Number

MS3126F16-8S PLUG 1

HOUSING ASSEM- 1

BLY

65-58288-( )

BRACKET ASSY 1

SPARK GAP ARRESTER

284A3862-( )

BAC27DEX7380 MARKER 1

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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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.

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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.

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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.

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep BOLT BACB30NT3K2 8

Remove / Keep NUT BACN10JR3CFD 8

2 Remove PLUG MS3126F16-8S 1

3 Remove / Keep BOLT BACS12HN3-6 8

4 Remove / Keep LIGHT ASSEMBLY 30-0909-( ) 1

5 Remove HOUSING ASSEMBLY 65-58288-( ) 1

FIGURE 1: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY

(SHEET 2 OF 2)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove / Keep BOLT BACB30NT3K2 8

Remove / Keep NUT BACN10JR3CFD 8

Remove / Keep SCREW BACS12CK3U8 5

Remove / Keep WASHER NAS1149C0332R 5

2 Remove PLUG MS3126F16-8S 1

3 Remove / Keep BOLT BACS12HN3-6 8

4 Remove / Keep LIGHT ASSEMBLY 30-0909-( ) 1

STROBE HOUSING 284A3162-6 1

ASSEMBLY

5 Remove / Keep

FIGURE 2: REMOVE THE TAIL ANTI-COLLISION LIGHT ASSEMBLY

(SHEET 2 OF 2)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Clean SURFACE - - (a) (b)

Measure to the given dimensions. Refer to view B-B.DISCONNECT 287A4811-119 1

BRACKET

2 Put / Hold

DISCONNECT 287A4811-119 1 (c)

BRACKET

Measure

Drill three 0.187-

0.190 inch holes.

3 Drill HOLE - 3

DISCONNECT 287A4811-119 1

BRACKET

4 Install (New)

BOLT, PROTRUDING BACB30NX6K4 3

HD

5 Install (New)

Install (New) COLLAR BACC30BH6 3

6 Measure SURFACE - - (d)

(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)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Clean SURFACE - - (a) (b)

Measure to the given dimensions. Refer to view B-B.DISCONNECT 287A4811-119 1

BRACKET

2 Put / Hold

DISCONNECT 287A4811-119 1

BRACKET

Measure

Drill three 0.187-

0.190 inch holes.

3 Drill HOLE - 3

DISCONNECT 287A4811-119 1

BRACKET

4 Install (New)

BOLT, PROTRUDING BACB30NX6K4 3

HD

5 Install (New)

Install (New) COLLAR BACC30BH6 3

6 Measure SURFACE - - (c)

(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)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

BOLT, PROTRUDING BACB30NX6K4 3

HD

1 Remove

Remove COLLAR BACC30BH6 3

BRACKET ASSY - 284A3862-( ) 1

SPARK GAP ARRESTER

2 Remove

3 Remove Marker BAC27DEX7380 1

FIGURE 5: REMOVAL OF SGLA DISCONNECT BRACKET AT STA 1156 BULKHEAD

(SHEET 2 OF 2)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Clean SURFACE - - (a) (b)

DISCONNECT 287A4811-119 1

BRACKET

2 Attach

BOLT, PROTRUDING BACB30NX6K4X 3 (c)

HD

3 Install (New)

Install (New) COLLAR BACC30BH6 3

4 Measure SURFACE - - (d)

(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)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Use existing fasteners.CLAMP, WIRE BUN- BACC10GU102 1

DLE

1 Install (New)

FIGURE 7: WIRE ROUTING FOR WIRE BUNDLE W4724 AND INSTALLATION OF CLAMP

(SHEET 2 OF 2)

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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

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

BMS13-48, TYPE 12, 2

CLASS 1, AWG 20

1 WIRE

Use to retie wire bundle. Refer to

SWPM 20-10-11 as an accepted

procedure.

LACING TAPE 280A2001-1 -

TFE TAPE, PERMACEL P- 829A9007-075 - (a)

440

Refer to SWPM 20-61-11 as an

accepted procedure.

2 CONTACT, SOCKET BACC47CP1S 2

FIGURE 8: WIRE CHANGE FOR WIRE BUNDLE W4724

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 737-33-1146
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to SWPM 20-74-12 as an

accepted procedure.

SLEEVE, SOLDER, HEAT BACS13CT3C 6

SHRINKABLE WITH 20

AWG SHIELD WIRE

3

Refer to SWPM 20-30-11 as an

accepted procedure.

4 TERMINAL, LUG BACT12AC3 2

Refer to SWPM 20-14-12 as an

accepted procedure.

INSULATION SLEEVING, 829A9003-180 2

HEAT SHRINKABLE,

BLACK, IN DIA 1/8",

CLASS 1

5

Clock the backshell on connector

D44582P to 10:00. Refer to SWPM

20-61-11 as an accepted procedure.

6 CONNECTOR, PLUG BACC63BP10C5SN 1

Refer to SWPM 20-25-12 as an

accepted procedure.

CLAMP, LOOP BACC10KE10 1

Imprinted "D44582P". Install ID

tape within 6 inches of connector.

ID - CONNECTOR 280A3160-10101 1

Seal unused connector cavities as

required.

PLUG MS27488-20-1 3

7 ID - WIRE 280A3160-10102 1 (b)

8 ID - WIRE 280A3160-10103 1 (b)

Refer to SWPM 20-30-12 as an

accepted procedure.

9 SPLICE D-150-0168 2

10 ID - SPLICE 280A3160-10105 1 Imprinted "SM34".

11 ID - SPLICE 280A3160-10104 1 Imprinted "SM33".

(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)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Use existing fasteners.CLAMP, WIRE BUN- BACC10GU104 1

DLE

1 Install (New)

FIGURE 9: WIRE ROUTING FOR WIRE BUNDLE W5726 AND INSTALLATION OF CLAMP

(SHEET 2 OF 2)

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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.

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

BMS13-48, TYPE 10, 2

CLASS 1, AWG 20

1 WIRE

Use to retie wire bundle. Refer to

SWPM 20-10-11 as an accepted

procedure.

LACING TAPE 280A2001-1 -

TFE TAPE, PERMACEL P- 829A9007-075 - (a)

440

FIGURE 10: WIRE CHANGE FOR WIRE BUNDLE W5726

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 737-33-1146
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

Refer to SWPM 20-61-11 as an

accepted procedure.

2 CONTACT, SOCKET BACC47CP1S 2

Refer to SWPM 20-23-17 as an

accepted procedure.

3 SLEEVE BACS13S232BNP 1

Refer to SWPM 20-23-17 as an

accepted procedure.

SLEEVE BACS13S312CNP 1

Refer to SWPM 20-14-12 as an

accepted procedure.

INSULATION SLEEVING, 829A9003-380 1

HEAT SHRINKABLE,

BLACK, IN DIA 3/8'',

CLASS 1

Refer to SWPM 20-30-11 as an

accepted procedure.

4 TERMINAL, LUG BACT12AC3 1

Refer to SWPM 20-14-12 as an

accepted procedure.

INSULATION SLEEVING, 829A9003-180 2

HEAT SHRINKABLE,

BLACK, IN DIA 1/8",

CLASS 1

5

6 ID - WIRE 280A3160-10201 1 (b)

7 ID - WIRE 280A3160-10202 1 (b)

Refer to SWPM 20-61-11 as an

accepted procedure.

8 CONNECTOR, PLUG BACC63BP10C5SN 1

Refer to SWPM 20-25-12 as an

accepted procedure.

CLAMP, LOOP BACC10KE10 1

Imprinted "D44582P". Install ID

tape within 6 inches of connector.

ID - CONNECTOR 280A3160-10101 1

Seal unused connector cavities as

required.

PLUG MS27488-20-1 3

Refer to SWPM 20-30-12 as an

accepted procedure.

9 TERMINAL BACT12C20 2

10 ID - SPLICE 280A3160-10204 1 Imprinted "SM24".

11 ID - SPLICE 280A3160-10203 1 Imprinted "SM23".

Refer to SWPM 20-14-12 as an

accepted procedure.

INSULATION SLEEVING, 829A9003-360 2

HEAT SHRINKABLE,

BLACK, IN DIA 3/16'',

CLASS 1

12

13 SLEEVE - PROTECTIVE 280A3160-10206 1 (c)

OVERSHIELD - TUBULAR 280A3160-10205 1 (d) (e) (f)

WIRE BRAID

14

FIGURE 10: WIRE CHANGE FOR WIRE BUNDLE W5726

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 737-33-1146
NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

15 WIRE - PIGTAIL 280A3160-10207 1

(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)

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BOEING SERVICE BULLETIN 737-33-1146
FIGURE 11: WIRE ROUTING FOR WIRE BUNDLE W7150

(SHEET 1 OF 1)

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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.

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

INSULATION SLEEVING, 829A9003-180 2 (a)

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)

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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)

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BOEING SERVICE BULLETIN 737-33-1146
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Insert INSERT, BLIND BACI12AD3CM14 1 (a)

CLAMP, WIRE BUN- BACC10GU103 1

DLE

Install (New)

Install (New) SCREW, CAP BACS12GU3K6 1

CLAMP, WIRE BUN- BACC10GU102 1

DLE

2 Install (New)

SPACERS FOR RIV- NAS42DD6-40FC 2

ETS

3 Install (New)

CLAMP, WIRE BUN- BACC10GU103 1

DLE

Install (New)

Install (New) SCREW, CAP BACS12GU3K17 1

CLAMP, WIRE BUN- BACC10GU102 1

DLE

4 Install (New)

SPACERS FOR RIV- NAS42DD6-64FC 1

ETS

5 Install (New)

CLAMP, WIRE BUN- BACC10GU104 1

DLE

Install (New)

Install (New) SCREW, CAP BACS12GU3K23 1

CLAMP, WIRE BUN- BACC10GU104 1

DLE

6 Install (New)

Install (New) SCREW, CAP BACS12GU3K6 1

CLAMP, WIRE BUN- BACC10GU103 1

DLE

7 Install (New)

Install (New) SCREW, CAP BACS12GU3K6 1

8 Clean SURFACE - - (b) (c)

9 Install (New) ASSY - W7152 280A3160-104 1 (d)

10 Install (New) CONNECTOR BACC63BV10F5S 1

Install (New) WASHER NAS1149DN432J 4

Install (New) SCREW NAS1801-04-7 4

Install (New) NUT BACN10JC04CD 4

Install (New) WASHER NAS1149DN432J 4

11 Connect PLUG BACC63BP10C5SL 1

12 Measure SURFACE - - (e)

(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)

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BOEING SERVICE BULLETIN 737-33-1146
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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)

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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.

NAME IDENTIFICATION QTY MORE DATA

FLAG

NOTE

WIRE BUNDLE - TAIL 286A7152-003 1 (a) (b)

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)

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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)

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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)

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BOEING SERVICE BULLETIN 737-33-1146
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Clean SURFACE - - (a)

2 Prepare SURFACE - - (b)

DUCT ASSY - EDUC- 355A1010-( ) 1 (c)

TOR INLET, APU

3 Put

FAIRING ASSY, UP- 354A4000-( ) 1

PER

4 Install (Kept)

5 Install (Kept) SCREW BACS12CK3U8 6 (d)

Install (Kept) WASHER NAS1149C0332R 6

MUFFLER ASSY-EXH, 354A3000-( ) 1 (e)

APU

6 Put

FAIRING ASSY - 354A4000-( ) 1 (f)

LOWER

7 Install (Kept)

8 Install (Kept) SCREW BACS12CK3U8 39 (g)

Install (Kept) WASHER NAS1523C3R 39

9 Install (Kept) SCREW BACS12CK3U7 9

Install (Kept) WASHER NAS1523C3R 9

10 Measure SURFACE - - (h)

11 Prepare SURFACE - - (k)

12 Attach LIGHT ASSEMBLY 30-0909-( ) 1 (l)

Install (Kept) BOLT BACS12HN3-6 8

13 Measure SURFACE - - (m)

Connect the new

plug to the light assembly.

14 Connect PLUG MS3126F16-8S 1

15 Measure SURFACE - - (n)

HOUSING ASSY - 284A3162Y6 1

RETROFIT

16 Align

Drill HOLE - 5 (i)

Drill HOLE - 8 (j)

Refer to 737-

600/700/800/900

AMM 33-44-04 as

an accepted procedure.

HOUSING ASSY - 284A3162Y6 1

RETROFIT

17 Install (New)

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)

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BOEING SERVICE BULLETIN 737-33-1146
STEP TASK NAME IDENTIFICATION QTY MORE DATA

18 Install (Kept) BOLT BACB30NT3K2 8

Install (Kept) NUT BACN10JR3CFD 8

19 Prepare SURFACE - - (o)

20 Install (New) SCREW BACS12CK3U8 5

Install (New) WASHER NAS1149C0332R 5

21 Measure SURFACE - - (p)

(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)

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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)

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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)

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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)

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76 of 78

BOEING SERVICE BULLETIN 737-33-1146
STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Clean SURFACE - - (a)

2 Prepare SURFACE - - (b)

DUCT ASSY - EDUC- 355A1010-( ) 1 (c)

TOR INLET, APU

3 Put

FAIRING ASSY, UP- 354A4000-( ) 1

PER

4 Install (Kept)

5 Install (Kept) SCREW BACS12CK3U8 6 (d)

Install (Kept) WASHER NAS1149C0332R 6

MUFFLER ASSY-EXH, 354A3000-( ) 1 (e)

APU

6 Put

FAIRING ASSY - 354A4000-( ) 1 (f)

LOWER

7 Install (Kept)

8 Install (Kept) SCREW BACS12CK3U8 39 (g)

Install (Kept) WASHER NAS1523C3R 39

9 Install (Kept) SCREW BACS12CK3U7 9

Install (Kept) WASHER NAS1523C3R 9

10 Measure SURFACE - - (h)

11 Prepare SURFACE - - (i)

12 Attach LIGHT ASSEMBLY 30-0909-( ) 1 (j)

Install (Kept) BOLT BACS12HN3-6 8

13 Measure SURFACE - - (k)

Connect the new

plug to the light assembly.

14 Connect PLUG MS3126F16-8S 1

15 Measure SURFACE - - (l)

Refer to 737-

600/700/800/900

AMM 33-44-04 as

an accepted procedure.

STROBE HOUSING 284A3162-6 1

ASSEMBLY

16 Install (Kept)

17 Install (Kept) BOLT BACB30NT3K2 8

Install (Kept) NUT BACN10JR3CFD 8

18 Prepare SURFACE - - (m)

19 Install (Kept) SCREW BACS12CK3U8 5

Install (Kept) WASHER NAS1149C0332R 5

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)

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BOEING SERVICE BULLETIN 737-33-1146
STEP TASK NAME IDENTIFICATION QTY MORE DATA

20 Measure SURFACE - - (n)

(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)

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737-33-1146

78 of 78

BOEING SERVICE BULLETIN 737-33-1146