# Boeing Special Attention Service Bulletin 767-25-0428: U.S. DOT/FAA - SB-767-25-0428-03

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2011-0719; AD 2012-11-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Special Attention Service Bulletin 767-25-0428](https://openairdocs.org/service-documents/boeing/sb-767-25-0428.md)
- Title as filed: U.S. DOT/FAA - SB-767-25-0428-03
- Pages: 66
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
Number: 767-25-0428
Original Issue: August 23, 2007
Revision 3: October 21, 2010
ATA System: 2566
SUBJECT: EQUIPMENT/FURNISHINGS - Door Mounted Escape System - Escape Slide
Deployment System - Type A Entry/Service Door Escape Slide Deployment Bar
Separation Link Assembly Change
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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2007 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Unpublished Work - All Rights Reserved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.
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2.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 7
B. Concurrent Requirements ...................................... 1 7
C. Reason ................................................ 1 8
D. Description .............................................. 1 9
E. Compliance .............................................. 1 9
F. Approval ............................................... 2 0
G. Manpower .............................................. 2 0
H. Weight and Balance Changes .................................... 2 1
I. Electrical Load Data ......................................... 2 1
J. References .............................................. 2 2
1. Existing Data: ......................................... 2 2
2. Data supplied with this Service Bulletin: ........................... 2 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 2
K. Publications Affected ........................................ 2 2
L. Interchangeability and Intermixability of Parts ........................... 2 2
2. MATERIAL INFORMATION ........................................ 2 3
A. Material - Price and Availability ................................... 2 3
B. Industry Support Information .................................... 2 3
C. Parts Necessary For Each Airplane ................................. 2 3
1. Kits/Parts: ........................................... 2 3
2. Parts and Materials Supplied by the Operator: ........................ 2 5
3. Parts Modified and Reidentified: ............................... 2 5
4. Parts Removed and Not Replaced: .............................. 2 5
D. Parts Necessary to Change Spares ................................. 2 5
E. Special Tooling - Price and Availability ............................... 2 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7
A. GENERAL INFORMATION ..................................... 2 7
B. WORK INSTRUCTIONS ....................................... 2 7
FIGURE 1: ENTRY/SERVICE DOOR BUSTLE REMOVAL [Group 1, 3] ................. 2 9
FIGURE 2: ENTRY/SERVICE DOOR BUSTLE REMOVAL [Group 2, 4] ................. 3 2
FIGURE 3: SEPARATION LINK ASSEMBLY REMOVAL [Group 1, 3] .................. 3 5
FIGURE 4: SEPARATION LINK ASSEMBLY REMOVAL [Group 2, 4] .................. 3 8
FIGURE 5: SEPARATION LINK ASSEMBLY INSTALLATION [Group 1, 3] ............... 4 1
FIGURE 6: SEPARATION LINK ASSEMBLY INSTALLATION [Group 2, 4] ............... 4 6
FIGURE 7: DEPLOYMENT BAR ASSEMBLY PART MARKING [Group 1] ............... 5 1
FIGURE 8: DEPLOYMENT BAR ASSEMBLY PART MARKING [Group 2] ............... 5 3
FIGURE 9: DEPLOYMENT BAR ASSEMBLY PART MARKING [Group 3] ............... 5 5
FIGURE 10: DEPLOYMENT BAR ASSEMBLY PART MARKING [Group 4] ............... 5 7
FIGURE 11: ENTRY/SERVICE DOOR BUSTLE INSTALLATION [Group 1, 3] .............. 5 9
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FIGURE 12: ENTRY/SERVICE DOOR BUSTLE INSTALLATION [Group 2, 4] .............. 6 3
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Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
Revision Transmittal SheetNumber: 767-25-0428Original Issue: August 23, 2007
Revision 3: October 21, 2010
ATA System: 2566
SUBJECT: EQUIPMENT/FURNISHINGS - Door Mounted Escape System - Escape Slide
Deployment System - Type A Entry/Service Door Escape Slide Deployment Bar
Separation Link Assembly Change
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive 2009-04-12, is related to this service bulletin.
No more work is necessary on airplanes changed in accordance with the original issue, Revision 1, or Revision
2 of this service bulletin.
REASON FOR REVISION
This revision is sent to add new Step 5 in FIGURE 11 and FIGURE 12. New Step 5 gives instructions to remove
the entry/service door ground lock installed in FIGURE 1 and FIGURE 2.
These sections were changed:
1. In Summary-Manpower and Paragraph 1.G., Manpower; changed manpower estimates.
2. In Figure 11; added new Step 5 for Group 1 and Group 3 airplanes.
3. In Figure 12; added new Step 5 for Group 2 and Group 4 airplanes.
The data given in Information Notice 767-25-0428 IN 03 is included in this revision.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
August 23, 2007Original Issue:
May 08, 2008Revision 1:
February 04, 2010Revision 2:
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October 21, 2010Revision 3:
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Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
SummaryNumber: 767-25-0428Original Issue: August 23, 2007
Revision 3: October 21, 2010
ATA System: 2566
SUBJECT: EQUIPMENT/FURNISHINGS - Door Mounted Escape System - Escape Slide
Deployment System - Type A Entry/Service Door Escape Slide Deployment Bar
Separation Link Assembly Change
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin will prevent the partial opening of the entry/service doors during emergency escape slide
deployment. If the entry/service doors do not fully open the exit may not be available for emergency evacuation
use.
Boeing has received five reports since 1993 of partial entry/service door opening during escape slide deployment
testing. Boeing has also received one report of partial entry/service door opening during an actual airplane
emergency evacuation.
These events were the result of the separation link assembly on the slide deployment bar not properly rotating
to release the deployment cable. It was found that the snap rings attaching the separation links to the deployment
bar were missing. Loss of a snap ring will result in movement of the separation link assembly past the stop
screws. Movement of the separation link assembly past the stop screws will prevent full rotation of the separation
link assembly and normal release of the deployment cable. If the deployment cables do not release from the
separation link assemblies on the deployment bar, the un-released deployment cables will prevent full opening
of the entry/service door. Service Letter 767-SL-25-101-A was issued to instruct operators to inspect the separation
link assemblies for missing or damaged snap links.
This service bulletin installs separation link assemblies secured with a nut and washer instead of a snap ring.
The installation of a separation link assembly secured with a nut and washer will prevent movement of the
separation link assembly past the stop screws and make sure the service/entry doors open fully in an emergency
evacuation.
Boeing Service Related Problem (SRP) 767-SRP-25-0258 is related to this service bulletin.
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ACTION (PRR B12901-81S)
— Remove bustle
— Remove existing separation link assembly
— Install new separation link assembly
— Install bustle
EFFECTIVITY
767-200/-300/-400ER Airplanes. Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-04-12 is related to this service bulletin.
Boeing recommends that the change given in this service bulletin be done within 4 years after the original issue
date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Group 1:
Elapsed HoursTotal Task Hours
4.854.85
Group 2:
Elapsed HoursTotal Task Hours
6.106.10
Group 3:
Elapsed HoursTotal Task Hours
4.854.85
Group 4:
Elapsed HoursTotal Task Hours
6.106.10
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-25-0428
GROUP 1, 3
GROUP 2, 4
AFT
SERVICE  AFT
DOOR  SERVICE
DOOR
FORWARD
SERVICE
DOOR  • AFT  MID  AFT
ENTRY  SERVICE  ENTRY
DOOR  DOOR  DOOR
FORWARD
MID
FORWARD  SERVICE  ENTRY DOOR
ENTRY DOOR  DOOR  FORWARD
SEE D  ENTRY DOOR
(4 LOCATIONS)  SEE A
(6 LOCATIONS)
DEPLOYMENT BAR
- REMOVE BUSTLE
- REMOVE EXISTING
SEPARATION LINK
- INSTALL NEW
SEPARATION LINK  UP
- INSTALL BUSTLE
INBD <  1362153
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Commercial 
Airplanes
767
Service Bulletin
SPECIAL ATTENTION
Number: 767-25-0428
Original Issue: August 23, 2007
Revision 3: October 21, 2010
ATA System: 2566
SUBJECT: EQUIPMENT/FURNISHINGS - Door Mounted Escape System - Escape Slide
Deployment System - Type A Entry/Service Door Escape Slide Deployment Bar
Separation Link Assembly Change
BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR B12901-81S for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
767 Airplanes with four Type A entry/service doors and have the
416T2184-2 deployment bar assembly.
-1
767 Airplanes with six Type A entry/service doors and have the
416T2184-2 deployment bar assembly.
-2
767 Airplanes with four Type A entry/service doors and have the
416T2184-3 deployment bar assembly.
-3
767 Airplanes with six Type A entry/service doors and have the
416T2184-3 deployment bar assembly.
-4
Airplane Models:
767-200, 767-300, 767-400ER
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GroupVariable Number
1VA002 - VA020
1VA301 - VA315
1VA501 - VA510
1VA512 - VA530
1VA701 - VA719
1VA801 - VA810
1VB001 - VB002
1VB051 - VB055
1VB101 - VB125
1VB201 - VB202
1VB251 - VB253
1VB281 - VB284
1VB301 - VB302
1VB321 - VB332
1VB371 - VB373
1VB401
3VB441 - VB444
1VE001 - VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE069
1VE083 - VE086
1VE101 - VE104
1VE116 - VE118
1VE121 - VE126
1VE141 - VE150
3VE151 - VE152
1VE171 - VE172
1VF001 - VF002
1VF041 - VF042
1VF051
1VF061 - VF062
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GroupVariable Number
1VF071 - VF072
1VF091 - VF093
1VF101 - VF102
3VF161 - VF162
3VF171 - VF172
3VF180 - VF184
3VF251
1VK001 - VK011
3VK012 - VK016
1VK021 - VK022
1VK031 - VK051
3VK052 - VK056
1VK081 - VK098
3VK099 - VK113
2VK131 - VK133
1VK141 - VK142
3VK143 - VK148
4VK161 - VK164
3VK171
3VK181
3VK186
2VL001 - VL006
2VL011
3VL701 - VL703
4VL751 - VL755
4VL806 - VL807
4VL871 - VL873
4VL891 - VL900
4VL911 - VL914
3VL931 - VL932
3VL941
1VN001 - VN015
3VN016 - VN041
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GroupVariable Number
1VN051 - VN062
3VN063 - VN064
1VN081 - VN088
3VN089 - VN099
2VN111 - VN120
4VN121 - VN127
2VN130 - VN132
4VN133 - VN137
1VN151 - VN157
3VN158
1VN163 - VN167
3VN168
2VN171 - VN173
4VN174
3VN194 - VN198
2VN211 - VN212
1VN221 - VN222
3VN223 - VN225
2VN231 - VN234
2VN241
4VN242 - VN243
1VN251 - VN259
3VN260 - VN276
1VN291
3VN292 - VN293
2VN301 - VN303
4VN304 - VN314
4VN371 - VN372
4VN376
4VN381 - VN388
4VN421
3VN422 - VN427
3VN436
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GroupVariable Number
2VN471 - VN472
1VN491 - VN494
3VN495 - VN513
2VN531 - VN532
2VN536
4VN537
2VN541
4VN542
4VN546 - VN547
4VN551
4VN556 - VN557
4VN561 - VN562
2VN631 - VN632
4VN633 - VN638
1VN651
3VN652 - VN658
3VN671 - VN672
3VN676
1VN681
3VN682 - VN691
3VN731 - VN732
3VN751 - VN753
4VN791 - VN792
3VN811 - VN813
4VN921 - VN922
3VN931 - VN936
4VN951 - VN953
3VN966 - VN972
4VQ001 - VQ021
4VQ071 - VQ086
3VR051 - VR060
3VR081
3VR084
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GroupVariable Number
3VR086 - VR089
3VR106 - VR107
3VR401
3VR421 - VR423
3VR426
3VR441
3VR461
3VR471 - VR472
4VS051 - VS056
4VS061
3VS066 - VS070
3VS073 - VS078
3VS091 - VS104
3VS111 - VS113
3VS131 - VS133
4VS136 - VS137
3VS176 - VS177
3VS186 - VS187
3VS196 - VS203
3VS206 - VS208
4VS211
4VS216 - VS217
3VS231
4VS246 - VS248
4VS261 - VS263
3VS266 - VS274
3VS291 - VS293
3VS301 - VS303
4VS306 - VS311
4VS316
4VS321 - VS324
4VS331 - VS333
4VS336 - VS337
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GroupVariable Number
3VS366 - VS367
3VS381 - VS382
3VS391 - VS392
3VS401
4VS426 - VS428
3VS466 - VS472
3VS486
4VS496 - VS497
4VS506 - VS507
3VS526
3VS546 - VS549
3VS701 - VS717
3VS721 - VS734
3VS751 - VS759
3VS821 - VS825
3VS841 - VS844
3VS861
4VS881 - VS883
4VS891
3VS896
3VS901 - VS905
3VS911 - VS912
4VS916
3VV001
2. Spares Affected
Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts
Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C., Parts
Necessary for Each Airplane for the recommended use.
B. Concurrent Requirements
None.
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C. Reason
This service bulletin will prevent the partial opening of the entry/service doors during emergency escape
slide deployment. If the entry/service doors do not fully open the exit may not be available for emergency
evacuation use.
Boeing has received five reports since 1993 of partial entry/service door opening during escape slide
deployment testing. Boeing has also received one report of partial entry/service door opening during
an actual airplane emergency evacuation.
These events were the result of the separation link assembly on the slide deployment bar not properly
rotating to release the deployment cable. It was found that the snap rings attaching the separation links
to the deployment bar were missing. Loss of a snap ring will result in movement of the separation link
assembly past the stop screws. Movement of the separation link assembly past the stop screws will
prevent full rotation of the separation link assembly and normal release of the deployment cable. If the
deployment cables do not release from the separation link assemblies on the deployment bar, the
un-released deployment cables will prevent full opening of the entry/service door. Service Letter
767-SL-25-101-A was issued to instruct operators to inspect the separation link assemblies for missing
or damaged snap links.
This service bulletin installs separation link assemblies secured with a nut and washer instead of a
snap ring. The installation of a separation link assembly secured with a nut and washer will prevent
movement of the separation link assembly past the stop screws and make sure the service/entry doors
open fully in an emergency evacuation.
Boeing Service Related Problem (SRP) 767-SRP-25-0258 is related to this service bulletin.
Revision 1 is sent to incorporate changes found during validation of this service bulletin.
These sections were changed:
1. In Kits/Parts, Section 2.C.1., added existing part numbers to parts table.
2. In Parts Modified and Reidentified, Section 2.C.3., Groups 1-2, deleted 767-25-0428 as the new
part number and deleted note (c).
3. In Parts Necessary to Change Spares, Section 2.D., added Spares Kit 015T1811-3
4. Figures 5 and 6, Steps 1 and 9, added reference to Figure 501 in CMM 25-66-30.
5. Figures 5 and 6, Steps 6 and 14, deleted reference to SOPM 20-50-01 and added torque values
of 15 - 16 in-lbs.
Revision 2 is sent to update the effectivity and add FAA Airworthiness Directive 2009-04-12. The part
number of a cap screw has been changed in figures 3, 4, 5 and 6, and an optional part number added.
Optional part numbers have also been added for the deployment bar assemblies in section 2.C.3, Parts
Modified and Reidentified, and figures 7, 8, 9 and 10.
The data given in Information Notice 767-25-0428 IN 02 is included in this revision. This Information
Notice was sent to provide the pricing information for the 015T1811-3 spares kit in section 2.A., Material
- Price and Availability. The price for the spares kit has been updated for this service bulletin.
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Revision 3 is sent to add new Step 5 in FIGURE 11 and FIGURE 12. New Step 5 gives instructions to
remove the entry/service door ground lock installed in FIGURE 1 and FIGURE 2.
The data given in Information Notice 767-25-0428 IN 03 is included in this revision.
D. Description
— Remove bustle
— Remove existing separation link assembly
— Install new separation link assembly
— Install bustle
No more work is necessary on airplanes changed as shown in the original issue of this service bulletin.
Revision 2 - No more work is necessary on airplanes changed as shown in the original issue and
Revision 1 of this service bulletin.
Revision 3 - No more work is necessary on airplanes changed in accordance with the original issue,
Revision 1, or Revision 2 of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1, 3:
Affected Maintenance Zones
ZoneModel
831, 833, 841, 843767-200, 767-300
Group 2:
Affected Maintenance Zones
ZoneModel
831, 833, 835, 841, 843, 845767-300
Group 4:
Affected Maintenance Zones
ZoneModel
831, 833, 835, 841, 843, 845767-300, 767-400ER
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive FAA AD 2009-04-12 is related to this
service bulletin.
Boeing recommends that the change given in this service bulletin be done within 4 years after the
original issue date of this service bulletin.
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft
Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin
as an alternative method of compliance to the requirements of paragraph (f) of AD 2009-04-12. All
provisions of AD 2009-04-12 that are not specifically referenced in the above statement remain fully
applicable and must be complied with.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 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:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.001.001FIGURE 1
1.001.001FIGURE 3
1.751.751FIGURE 5
0.100.101FIGURE 7
1.001.001FIGURE 11
4.854.85TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.001.001FIGURE 2
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Group 2:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.501.501FIGURE 4
2.502.501FIGURE 6
0.100.101FIGURE 8
1.001.001FIGURE 12
6.106.10TOTAL FOR EACH AIRPLANE
Group 3:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.001.001FIGURE 1
1.001.001FIGURE 3
1.751.751FIGURE 5
0.100.101FIGURE 9
1.001.001FIGURE 11
4.854.85TOTAL FOR EACH AIRPLANE
Group 4:
Elapsed HoursTask HoursNumber of Per-
sons
Task
1.001.001FIGURE 2
1.501.501FIGURE 4
2.502.501FIGURE 6
0.100.101FIGURE 10
1.001.001FIGURE 12
6.106.10TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data:
a. Engineering Change Memo PRR B12901-81S
b. Boeing Service Letter 767-SL-25-101-A
c. Boeing Service Related Problem (SRP) 767-SRP-25-0258
d. Component Maintenance Manual (CMM) 25-66-30
e. Federal Aviation Administration (FAA) Airworthiness Directive 2009-04-12
f. Standard Overhaul Practices Manual (SOPM) 20-41-02, 20-50-01, 20-50-10
g. 767 Aircraft Maintenance Manual (AMM) 52-11-13
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
DEPLOYMENT SYSTEM INSTL - ESCAPE SLIDE ENTRY DOOR416T2183
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
25-66767 Illustrated Parts Catalog
CMM 25-66-30Component Maintenance Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated 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
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane, and Paragraph
2.D., Parts Necessary to Change Spares, as shown below. If there is a limit to the quantity (QTY) of
available kits, a supply sequence is given by Spares. More kits become available as shown in the
Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.
Group 1, 3:
Unit Price thru
DEC 31, 2007
ROLT
(Weeks)
QTYDateNameKit Number
$7,114.00297608/03/07TOP KIT015T1811-1
Group 2, 4:
Unit Price thru
DEC 31, 2007
ROLT
(Weeks)
QTYDateNameKit Number
$10,671.00292608/03/07TOP KIT015T1811-2
Unit Price thru
OCT 31, 2010
ROLT
(Weeks)
NameKit Number
$2,039.0029SPARES
KIT
015T1811-3
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that
follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle,
Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
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NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for
each installation figure shown in the table below.
Figure Kit
65Top Kit
-1015T1811-1
1-015T1811-2
Kit 015T1811-1 - Group 1, 3:
NotesExisting Part
Number
NameFigureNew Part Number
5
Qty
(a) (b)
(c)
416T2232-1SEPARATION
LINK ASSY
4416T2232-5
(a) (b)
(c)
416T2232-2SEPARATION
LINK ASSY
4416T2232-6
NUT8BACN10YR4CM
WASHER8NAS1149C0432R
(a) Discard the existing part.
(b) The new part is used in production.
(c) You cannot use the existing part to replace the new or changed part.
Kit 015T1811-2 - Group 2, 4:
NotesExisting Part
Number
NameFigureNew Part Number
6
Qty
(a) (b)
(c)
416T2232-1SEPARATION
LINK ASSY
6416T2232-5
(a) (b)
(c)
416T2232-2SEPARATION
LINK ASSY
6416T2232-6
NUT12BACN10YR4CM
WASHER12NAS1149C0432R
(a) Discard the existing part.
(b) The new part is used in production.
(c) You cannot use the existing part to replace the new or changed part.
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2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number /
Specification
(a)Primer1ozBMS 10-11 Type 1
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for
supplier data.
3. Parts Modified and Reidentified:
The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the
number of parts changed on each airplane.
Group 1-2:
NotesNew Part NumberNameQTYExisting Part
Number
(a) (b)416T2184-4 (c) (d)DEPLOYMENT BAR
ASSEMBLY
-416T2184-2
(416T2184-3 op-
tional)
(a) Make the change given in this service bulletin.
(b) There is no equivalent Boeing part number for the changed part. Identify on the part that
the change given in this service bulletin was made.
(c) This part is used in production.
(d) This is the part number of the optional part after the change given in this service bulletin.
Group 3-4:
NotesNew Part NumberNameQTYExisting Part
Number
(a) (d)416T2184-4 (b) (c)DEPLOYMENT BAR
ASSEMBLY
-416T2184-3
(416T2184-2 op-
tional)
(a) Make the change given in this service bulletin.
(b) This is the part number after the change given in this service bulletin.
(c) This part is used in production
(d) There is no equivalent Boeing part number for the optional part. Identify on the optional
part that the change given in this service bulletin was made.
4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
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The parts shown below are for each deployment bar location.
QTYNamePart Number
1SPARES KIT015T1811-3 (a)
1SEPARATION LINK
ASSY
416T2232-5 (b)
1SEPARATION LINK
ASSY
416T2232-6 (b)
2NUTBACN10YR4CM
(b)
2WASHERNAS1149C0432R
(b)
(a) This kit contains all parts necessary to complete
the change for deployment bar location.
(b) These parts are contained in the 015T1811-3
SPARES KIT
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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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. For approved fastener and process material substitutions, refer to 767 SRM, Chapter
51, Alternate fasteners are given in 767 SRM Chapter 51 and Boeing Drawing
012W6100.
4. If the length of any fastener specified in this service bulletin does not meet the
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.
5. 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 ensure visual access to all surfaces in the
inspection area. This level of inspection is made under normal 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.
6. 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.
B. WORK INSTRUCTIONS
1. Group 1, 3:
Remove the bustle on the entry/service doors in accordance with FIGURE 1.
2. Group 2, 4:
Remove the bustle on the entry/service doors in accordance with FIGURE 2.
3. Group 1, 3:
Remove existing separation link assembly on the deployment bar in accordance with FIGURE 3.
4. Group 2, 4:
Remove existing separation link assembly on the deployment bar in accordance with FIGURE 4.
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5. Group 1, 3:
Install new separation link assembly in accordance with FIGURE 5.
6. Group 2, 4:
Install new separation link assembly in accordance with FIGURE 6.
7. Group 1:
Part mark deployment bar assembly in accordance with FIGURE 7.
8. Group 2:
Part mark deployment bar assembly in accordance with FIGURE 8.
9. Group 3:
Part mark deployment bar assembly in accordance with FIGURE 9.
10. Group 4:
Part mark deployment bar assembly in accordance with FIGURE 10.
11. Group 1, 3:
Install the bustle on the entry/service doors in accordance with FIGURE 11.
12. Group 2, 4:
Install the bustle on the entry/service doors in accordance with FIGURE 12.
13. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 1, 3.
AFT
SERVICE
DOOR
FORWARD
SERVICE  > AFT
DOOR  ENTRY
DOOR
FORWARD
ENTRY DOOR
SEE (A
(4 LOCATIONS)
ESCAPE SLIDE PACK
INFLATION
CYLINDER
REGULATOR
STOWAGE POUCH  SEE B
SEE
INBD
YELLOW INDICATOR
FLAG WINDOW
FIGURE 1: ENTRY/SERVICE DOOR BUSTLE REMOVAL
(SHEET 1 OF 3)
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### Page 30 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
- INFLATION
CYLINDER
REGULATOR
SAFETY
PIN
PRESSURE  SLIDE INSTALLATION IN A/C  REMOVE PIN AT TIME OF
GAGE
- FIRING
LANYARD
• ESCAPE SLIDE PACK
• DEPLOYMENT
BAR
— DEPLOYMENT
CABLE
GIRT BAR
CARRIER
- FLOOR LEVEL
UP
GIRT BAR
(IN GIRT BAR CARRIER)
FIGURE 1: ENTRY/SERVICE DOOR BUSTLE REMOVAL
(SHEET 2 OF 3)
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### Page 31

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Close and latch the entry/ser-
vice door.
--DOORClose1
WARNING: BE SURE TO INSTALL THE GROUND LOCK FOR THE ENTRY/SERVICE DOOR. WITHOUT
THE GROUND LOCK INSTALLED, THE DOOR CAN LIFT ACCIDENTALLY, CAUSING INJURY OR
DAMAGE.
Install the ground lock for the
entry/service door. Refer to 767
AMM 52-11-13 as an accepted
procedure.
--DOORLock2
Move the arm/disarm handle to
the DISARMED position. Make
sure the yellow flag indicators
are not shown in the windows
at the bottom of the entry/ser-
vice door.
--ARM/DISARM
HANDLE
Move3
---BUSTLERemove /
Keep
4
Remove the safety pin from the
pouch on the escape slide pack.
--SAFETY PINRemove /
Keep
5
WARNING: BE SURE TO INSTALL THE SAFETY PIN IN THE INFLATION CYLINDER REGULATOR. THE
ACCIDENTAL INFLATION OF THE ESCAPE SYSTEM CAN CAUSE INJURY OR DAMAGE.
Install safety pin in the inflation
cylinder regulator.
--SAFETY PINInstall (Kept)6
CAUTION: DO NOT PULL ON THE RELEASE CABLES WHEN THE GIRT BAR IS MOVED. A FORCE ON
THE CABLES CAN CAUSE THE ESCAPE SLIDE PACK TO RELEASE FROM THE ENTRY/SERVICE
DOOR
Remove deployment bar cables
from the separation links and
carefully allow them to retract
into the cables retractors
--DEPLOYMENT
BAR CABLES
Remove /
Keep
7
FIGURE 1: ENTRY/SERVICE DOOR BUSTLE REMOVAL
(SHEET 3 OF 3)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 2, 4.
AFT
SERVICE
DOOR
MID
SERVICE
DOOR  - AFT
ENTRY
DOOR
FORWARD
SERVICE
DOOR
MID
ENTRY DOOR
FORWARD
ENTRY DOOR
SEE A
(6 LOCATIONS)
ESCAPE SLIDE PACK
INFLATION
CYLINDER
REGULATOR
STOWAGE POUCH  SEE
UP  SEE C
INBD '
YELLOW INDICATOR
FLAG WINDOW  1362345
FIGURE 2: ENTRY/SERVICE DOOR BUSTLE REMOVAL
(SHEET 1 OF 3)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
INFLATION
CYLINDER
REGULATOR
SAFETY
PIN
PRESSURE  SLIDE INSTALLATION IN A/C  REMOVE PIN AT TIME OF
GAGE
- FIRING
LANYARD
ESCAPE SLIDE PACK
DEPLOYMENT
BAR
- DEPLOYMENT
CABLE
GIRT BAR
CARRIER
• FLOOR LEVEL
UP
'GIRT BAR  (IN GIRT BAR CARRIER)  1362372
FIGURE 2: ENTRY/SERVICE DOOR BUSTLE REMOVAL
(SHEET 2 OF 3)
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### Page 34

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Close and latch the entry/ser-
vice door.
--DOORClose1
WARNING: BE SURE TO INSTALL THE GROUND LOCK FOR THE ENTRY/SERVICE DOOR. WITHOUT
THE GROUND LOCK INSTALLED, THE DOOR CAN LIFT ACCIDENTALLY, CAUSING INJURY OR
DAMAGE.
Install the ground lock for the
entry/service door. Refer to 767
AMM 52-11-13 as an accepted
procedure.
--DOORLock2
Move the arm/disarm handle to
the DISARMED position. Make
sure the yellow flag indicators
are not shown in the windows
at the bottom of the entry/ser-
vice door.
--ARM/DISARM
HANDLE
Move3
---BUSTLERemove/Keep4
Remove the safety pin from the
pouch on the escape slide pack.
--SAFETY PINRemove/Keep5
WARNING: BE SURE TO INSTALL THE SAFETY PIN IN THE INFLATION CYLINDER REGULATOR. THE
ACCIDENTAL INFLATION OF THE ESCAPE SYSTEM CAN CAUSE INJURY OR DAMAGE.
Install safety pin in the inflation
cylinder regulator.
--SAFETY PINInstall (Kept)6
CAUTION: DO NOT PULL ON THE RELEASE CABLES WHEN THE GIRT BAR IS MOVED. A FORCE ON
THE CABLES CAN CAUSE THE ESCAPE SLIDE PACK TO RELEASE FROM THE ENTRY/SERVICE
DOOR
Remove deployment bar cables
from the separation links and
carefully allow them to retract
into the cables retractors
--DEPLOYMENT
BAR CABLES
Remove/Keep7
FIGURE 2: ENTRY/SERVICE DOOR BUSTLE REMOVAL
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 767-25-0428

### Page 35 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 1, 3.
AFT
SERVICE
DOOR
FORWARD
SERVICE  AFT
DOOR  ENTRY
DOOR
• FORWARD
ENTRY DOOR
SEE 1
(4 LOCATIONS)
DEPLOYMENT
BAR
SEE
INBD  1362407
FIGURE 3: SEPARATION LINK ASSEMBLY REMOVAL
(SHEET 1 OF 3)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
SEE (D
SEE C-
INBD
1362413
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
FIGURE 3: SEPARATION LINK ASSEMBLY REMOVAL
(SHEET 2 OF 3)
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### Page 37

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
-8MS16624-4031SNAP RINGRemove1
-8AN960C516LWASHERRemove
-4416T2232-1SEPARATION
LINK ASSY
Remove2
-4416T2231-1SPRINGRemove/Keep
-4BACW10P219TFTEFLON WASHERRemove/Keep
-4416T2232-2SEPARATION
LINK ASSY
Remove3
-4416T2231-2SPRINGRemove/Keep
-4BACW10P219TFTEFLON WASHERRemove/Keep
-8NAS1352C06-4P
(NAS1352-06H4P
optional)
CAP SCREWRemove/Keep4
Do a general visual inspection
of the separation link housing
assembly for worn primer
around the separation link as-
sembly.
-416T2215-1SEPARATION
LINK HOUSING
ASSEMBLY
Inspect5
Apply two coats of BMS 10-11,
Type 1 primer to housing if
worn. Refer to SOPM 20-41-02
as an accepted procedure.
-BMS 10-11PRIMERApply
FIGURE 3: SEPARATION LINK ASSEMBLY REMOVAL
(SHEET 3 OF 3)
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### Page 38 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 2, 4.
AFT
SERVICE
DOOR
>
MID  • AFT
SERVICE  ENTRY
DOOR  DOOR
FORWARD
SERVICE
DOOR
MID
ENTRY DOOR
FORWARD
ENTRY DOOR
SEE A
(6 LOCATIONS)
DEPLOYMENT
BAR
SEE
INBD <  1362459
FIGURE 4: SEPARATION LINK ASSEMBLY REMOVAL
(SHEET 1 OF 3)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
SEE •
SEE C
DINBD
1362452
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
FIGURE 4: SEPARATION LINK ASSEMBLY REMOVAL
(SHEET 2 OF 3)
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### Page 40

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
-12MS16624-4031SNAP RINGRemove1
-12AN960C516LWASHERRemove
-6416T2232-1SEPARATION
LINK ASSY
Remove2
-6416T2231-1SPRINGRemove/Keep
-6BACW10P219TFTEFLON WASHERRemove/Keep
-6416T2232-2SEPARATION
LINK ASSY
Remove3
-6416T2231-2SPRINGRemove/Keep
-6BACW10P219TFTEFLON WASHERRemove/Keep
-12NAS1352C06-4P
(NAS1352-06H4P
optional)
CAP SCREWRemove/Keep4
Do a general visual inspection
of the separation link housing
assembly for worn primer
around the separation link as-
sembly.
-416T2215-1SEPARATION
LINK HOUSING
ASSEMBLY
Inspect5
Apply two coats of BMS 10-11,
Type 1 primer to housing if
worn. Refer to SOPM 20-41-02
as an accepted procedure.
-BMS 10-11PRIMERApply
FIGURE 4: SEPARATION LINK ASSEMBLY REMOVAL
(SHEET 3 OF 3)
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### Page 41 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 1, 3.
AFT
SERVICE
DOOR
FORWARD
SERVICE  AFT
DOOR  ENTRY
DOOR
• FORWARD
ENTRY DOOR
SEE 1
(4 LOCATIONS)
SEE
INBD  1362665
FIGURE 5: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 1 OF 5)
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### Page 42 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
SEPARATION
LINK
HOUSING
PLACARD
SEE DO
SEPARATION
LINK HOUSING
SEE CO
PLACARD
UP
DINBD
1362682
FIGURE 5: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 2 OF 5)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
•SEPARATION LINK  (10
HOUSING PIN
SEPARATION LINK
~ SEE (G  HOUSING PIN  SEE
SEPARATION  SEPARATION
SPRING  LINK PIN  LINK PIN  SPRING
10
SEPARATION LINK
ASSEMBLY
SEPARATION LINK
ASSEMBLY
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
FIGURE 5: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 3 OF 5)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  43 of 66

### Page 44

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(f)-416T2231-1SPRINGInspect1
-4416T2231-1SPRINGInstall (Kept)2
-4BACW10P219TFTEFLON WASHERInstall (Kept)
(a)4416T2232-5SEPARATION LINK
ASSY
Install (New)
(b)-416T2232-5SEPARATION LINK
ASSY
Turn3
Install cap screw
hand tight.
4NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWInstall (Kept)
-4NAS1149C0432RWASHERInstall (New)4
Install nut hand tight.4BACN10YR4CMNUTInstall (New)
(c)-416T2232-5SEPARATION LINK
ASSY
Turn5
Torque cap screw to
15-16 in-lbs.
4NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWTorque6
Torque nut to 63 -
67 in-lbs
4BACN10YR4CMNUTTorque7
(d)-416T2232-5SEPARATION LINK
ASSY
Turn8
(f)-416T2231-2SPRINGInspect9
-4416T2231-2SPRINGInstall (Kept)10
-4BACW10P219TFTEFLON WASHERInstall (Kept)
(a)4416T2232-6SEPARATION LINK
ASSY
Install (New)
(b)-416T2232-6SEPARATION LINK
ASSY
Turn11
Install cap screw
hand tight.
4NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWInstall (Kept)
-4NAS1149C0432RWASHERInstall (New)12
Install nut hand tight.4BACN10YR4CMNUTInstall (New)
(c)-416T2232-6SEPARATION LINK
ASSY
Turn13
FIGURE 5: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 4 OF 5)
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767-25-0428Revision 3 October 21, 2010
44 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 45

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Torque cap screw to
15-16 in-lbs.
4NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWTorque14
Torque nut to 63 -
67 in-lbs
4BACN10YR4CMNUTTorque15
(e)-416T2232-6SEPARATION LINK
ASSY
Turn16
(a) Make sure that the separation link pin and the separation link housing pin are between the tabs on the
spring. Rotate the separation link assembly to verify smooth motion and that the spring is installed correctly
and providing resistance.
(b) Rotate the separation link assembly until the cap screw can be installed in the smaller gap between the
tabs on the separation link. The separation link should be oriented as shown on the placard beside the
separation link housing.
(c) Rotate the separation link assembly to verify smooth motion and that the spring is installed correctly and
providing resistance. No binding should occur.
(d) Verify that the separation link rotates CLOCKWISE against the spring torque and the separation link freely
snaps back against the cap screw when released as shown in the placard beside the separation link. No
bInding should occur.
(e) Verify that the separation link rotates COUNTER-CLOCKWISE against the spring torque and the separation
link freely snaps back against the cap screw when released as shown in the placard beside the separation
link. No binding should occur.
(f) Check unloaded spring dimensions against CMM 25-66-30, Figure 501. Check for nicks and scrapes that
could cause breakage or other permanent deformation such as bent tangs. Replace spring if any damage
is found.
FIGURE 5: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 5 OF 5)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2007
767-25-0428Revision 3 October 21, 2010
45 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 2, 4.
AFT
SERVICE
DOOR
>
MID  • AFT
SERVICE  ENTRY
DOOR  DOOR
FORWARD
SERVICE
DOOR
MID
ENTRY DOOR
FORWARD
ENTRY DOOR
SEE A
(6 LOCATIONS)
DEPLOYMENT
BAR
SEE
INBD  1363221
FIGURE 6: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 1 OF 5)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  46 of 66

### Page 47 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
SEPARATION
LINK
HOUSING
PLACARD
SEE D)F
SEPARATION
LINK HOUSING
SEE CO
PLACARD
UP
DINBD
1363225
FIGURE 6: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 2 OF 5)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  47 of 66

### Page 48 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
•SEPARATION LINK
HOUSING PIN
SEPARATION LINK
~ SEE  HOUSING PIN  SEE
(11)14
SEPARATION  SEPARATION
SPRING  LINK PIN  LINK PIN  SPRING
SEPARATION LINK
ASSEMBLY
SEPARATION LINK
ASSEMBLY
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
FIGURE 6: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 3 OF 5)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  48 of 66

### Page 49

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(f)-416T2231-1SPRINGInspect1
-6416T2231-1SPRINGInstall (Kept)2
-6BACW10P219TFTEFLON WASHERInstall (Kept)
(a)6416T2232-5SEPARATION LINK
ASSY
Install (New)
(b)-416T2232-5SEPARATION LINK
ASSY
Turn3
Install cap screw
hand tight.
6NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWInstall (Kept)
-6NAS1149C0432RWASHERInstall (New)4
Install nut hand tight.6BACN10YR4CMNUTInstall (New)
(c)-416T2232-5SEPARATION LINK
ASSY
Turn5
Torque cap screw to
15 - 16 in-lbs.
6NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWTorque6
Torque nut to 63 -
67 in-lbs
6BACN10YR4CMNUTTorque7
(d)-416T2232-5SEPARATION LINK
ASSY
Turn8
(f)-416T2231-2SPRINGInspect9
-6416T2231-2SPRINGInstall (Kept)10
-6BACW10P219TFTEFLON WASHERInstall (Kept)
(a)6416T2232-6SEPARATION LINK
ASSY
Install (New)
(b)-416T2232-6SEPARATION LINK
ASSY
Turn11
Install cap screw
hand tight.
6NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWInstall (Kept)
-6NAS1149C0432RWASHERInstall (New)12
Install nut hand tight.6BACN10YR4CMNUTInstall (New)
(c)-416T2232-6SEPARATION LINK
ASSY
Turn13
FIGURE 6: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 4 OF 5)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2007
767-25-0428Revision 3 October 21, 2010
49 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 50

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Torque cap screw to
15 - 16 in-lbs.
6NAS1352C06-4P
(NAS1352-06H4P op-
tional)
CAP SCREWTorque14
Torque nut to 63 -
67 in-lbs
6BACN10YR4CMNUTTorque15
(e)-416T2232-6SEPARATION LINK
ASSY
Turn16
(a) Make sure that the separation link pin and the separation link housing pin are between the tabs on the
spring. Rotate the separation link assembly to verify smooth motion and that the spring is installed correctly
and providing resistance.
(b) Rotate the separation link assembly until the cap screw can be installed in the smaller gap between the
tabs on the separation link. The separation link should be oriented as shown on the placard beside the
separation link housing.
(c) Rotate the separation link assembly to verify smooth motion and that the spring is installed correctly and
providing resistance. No binding should occur.
(d) Verify that the separation link rotates CLOCKWISE against the spring torque and the separation link freely
snaps back against the cap screw when released as shown in the placard beside the separation link. No
bInding should occur.
(e) Verify that the separation link rotates COUNTER-CLOCKWISE against the spring torque and the separation
link freely snaps back against the cap screw when released as shown in the placard beside the separation
link. No binding should occur.
(f) Check unloaded spring dimensions against CMM 25-66-30, Figure 501. Check for nicks and scrapes that
could cause breakage or other permanent deformation such as bent tangs. Replace spring if any damage
is found.
FIGURE 6: SEPARATION LINK ASSEMBLY INSTALLATION
(SHEET 5 OF 5)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2007
767-25-0428Revision 3 October 21, 2010
50 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 51 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 1.
AFT
SERVICE
DOOR
FORWARD
SERVICE  AFT
DOOR  ENTRY
DOOR  SEE B
FORWARD
ENTRY DOOR
SEE A  UP
(4 LOCATIONS)
INBD
• UP
DINBD
1363256
FIGURE 7: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 1 OF 2)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  51 of 66

### Page 52

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)4416T2184-2
(416T2184-3 option-
al)
DEPLOYMENT
BAR ASSY
Identify1
(a) If installing changed deployment bar assembly 416T2184-2 mark with service bulletin number 767-25-
0428. Refer to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
(b) If installing optional deployment bar assembly 416T2184-3 mark with part number 416T2184-4. Refer
to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
FIGURE 7: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2007
767-25-0428Revision 3 October 21, 2010
52 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 53 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 2.
AFT
SERVICE
DOOR
MID
SERVICE  AFT
DOOR  ENTRY
DOOR
FORWARD  SEE
SERVICE
DOOR
MID
ENTRY DOOR
FORWARD
UP
ENTRY DOOR
SEE
(6 LOCATIONS)  INBD
• UP
DINBD
1363264
FIGURE 8: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 1 OF 2)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  53 of 66

### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)6416T2184-2
(416T2184-3 option-
al)
DEPLOYMENT
BAR ASSY
Identify1
(a) If installing changed deployment bar assembly 416T2184-2 mark with service bulletin number 767-25-
0428. Refer to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
(b) If installing optional deployment bar assembly 416T2184-3 mark with part number 416T2184-4. Refer
to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
FIGURE 8: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2007
767-25-0428Revision 3 October 21, 2010
54 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 3.
AFT
SERVICE
DOOR
FORWARD
SERVICE  AFT
DOOR  ENTRY
DOOR  SEE B
FORWARD
ENTRY DOOR
SEE A  UP
(4 LOCATIONS)
INBD
• UP
DINBD
1363274
FIGURE 9: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 1 OF 2)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  55 of 66

### Page 56

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)4416T2184-3
(416T2184-2 option-
al)
DEPLOYMENT
BAR ASSY
Identify1
(a) If installing changed deployment bar assembly 416T2184-3 mark with part number 416T2184-4. Refer
to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
(b) If installing optional deployment bar assembly 416T2184-2 mark with service bulletin number 767-25-
0428. Refer to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
FIGURE 9: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2007
767-25-0428Revision 3 October 21, 2010
56 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 57 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 4.
AFT
SERVICE
DOOR
MID
SERVICE  AFT
DOOR  ENTRY
DOOR
FORWARD  SEE
SERVICE
DOOR
R  MID
ENTRY DOOR
FORWARD
UP
ENTRY DOOR
SEE
(6 LOCATIONS)  INBD
• UP
DINBD
1363282
FIGURE 10: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 1 OF 2)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  57 of 66

### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) (b)6416T2184-3
(416T2184-2 option-
al)
DEPLOYMENT
BAR ASSY
Identify1
(a) If installing changed deployment bar assembly 416T2184-3 mark with part number 416T2184-4. Refer
to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
(b) If installing optional deployment bar assembly 416T2184-2 mark with service bulletin number 767-25-
0428. Refer to SOPM 20-50-10 as an accepted procedure. Mark surface near the existing part mark.
FIGURE 10: DEPLOYMENT BAR ASSEMBLY PART MARKING
(SHEET 2 OF 2)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 23, 2007
767-25-0428Revision 3 October 21, 2010
58 of 66
BOEING SERVICE BULLETIN 767-25-0428

### Page 59 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
This Figure applies only to: Group 1, 3.
AFT
SERVICE
DOOR
FORWARD
SERVICE  > AFT
DOOR  ENTRY
DOOR
FORWARD
ENTRY DOOR
SEE A
(4 LOCATIONS)
ESCAPE SLIDE PACK
INFLATION
CYLINDER
REGULATOR
STOWAGE POUCH  SEE B
SEE
INBD
YELLOW INDICATOR
FLAG WINDOW  1363284
FIGURE 11: ENTRY/SERVICE DOOR BUSTLE INSTALLATION
(SHEET 1 OF 4)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  59 of 66

### Page 60 (OCR)

BOEING SERVICE BULLETIN 767-25-0428
- INFLATION
CYLINDER
REGULATOR
SAFETY
PIN
PRESSURE  SLIDE INSTALLATION IN A/C  REMOVE PIN AT TIME OF
GAGE
- FIRING
LANYARD
ESCAPE SLIDE PACK
- DEPLOYMENT
BAR
- DEPLOYMENT
CABLE
GIRT BAR
CARRIER
• FLOOR LEVEL
UP
GIRT BAR  0022981
(IN GIRT BAR CARRIER)
FIGURE 11: ENTRY/SERVICE DOOR BUSTLE INSTALLATION
(SHEET 2 OF 4)
Original Issue: August 23, 2007
Revision 3 October 21, 2010  BOEING PROPRIETARY -  767-25-0428
Copyright © Unpublished Work - See page 1 for details.  60 of 66

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