# Boeing Alert Service Bulletin 767-32A0227: Revision 1

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- Document: [Boeing Alert Service Bulletin 767-32A0227](https://openairdocs.org/service-documents/boeing/767-32a0227.md)
- Title as filed: U.S. DOT/FAA - Service Information
- Pages: 114
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
Number: 767-32A0227
Original Issue: April 25, 2012
Revision 1: September 13, 2012
ATA System: 3211
SUBJECT: LANDING GEAR - Main Gear - Pivot Joint Configuration Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). 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 © 2012 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
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 Boeing
liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection
with this document unless provided in writing by Boeing. BOEING is a trademark of Boeing Management
Company.
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767-32A0227Revision 1: September 13, 2012
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3.0

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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 7
D. Description .............................................. 1 8
E. Compliance .............................................. 1 8
F. Approval ............................................... 2 4
G. Manpower .............................................. 2 5
H. Weight and Balance Changes .................................... 2 6
I. Electrical Load Data ......................................... 2 7
J. References .............................................. 2 7
1. Existing Data: ......................................... 2 7
2. Data Supplied with this Service Bulletin: ........................... 2 7
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 8
K. Publications Affected ........................................ 2 8
L. Interchangeability and Intermixability of Parts ........................... 2 8
M. Software Accomplishment Summary ................................ 2 9
2. MATERIAL INFORMATION ........................................ 3 1
A. Material - Price and Availability ................................... 3 1
B. Industry Support Information .................................... 3 2
C. Parts Necessary for Each Airplane ................................. 3 2
1. Kits/Parts ............................................ 3 2
2. Parts and Materials Supplied by the Operator ........................ 3 2
3. Parts Modified and Reidentified ................................ 3 3
4. Parts Removed and Not Replaced .............................. 3 3
D. Parts Necessary to Change Spares ................................. 3 4
E. Special Tooling - Price and Availability ............................... 3 4
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 7
A. GENERAL INFORMATION ..................................... 3 7
B. WORK INSTRUCTIONS ....................................... 3 8
FIGURE 1: LEFT MLG PIVOT PIN INSPECTION [Group 1] ....................... 4 6
FIGURE 2: RIGHT MLG PIVOT PIN INSPECTION [Group 1] ...................... 4 8
FIGURE 3: LEFT MLG PIVOT JOINT BUSHING INSPECTION [Group 1] ................ 5 0
FIGURE 4: RIGHT MLG PIVOT JOINT BUSHING INSPECTION [Group 1] ............... 5 4
FIGURE 5: LEFT MLG TRUCK BEAM PIVOT LUG INSPECTION [Group 1] .............. 5 8
FIGURE 6: RIGHT MLG TRUCK BEAM PIVOT LUG INSPECTION [Group 1] ............. 6 1
FIGURE 7: MLG TRUCK BEAM BUSHING INSTALLATION [Group 1] ................. 6 4
FIGURE 8: LEFT MLG INNER CYLINDER PIVOT LUG INSPECTION [Group 1] ............ 6 8
FIGURE 9: RIGHT MLG INNER CYLINDER PIVOT LUG INSPECTION [Group 1] ........... 7 1
FIGURE 10: MLG INNER CYLINDER BUSHINGS INSTALLATION [Group 1] .............. 7 4
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FIGURE 11: LEFT MLG TRUCK BEAM PIVOT LUG INSPECTION [Group 2] .............. 7 6
FIGURE 12: RIGHT MLG TRUCK BEAM PIVOT LUG INSPECTION [Group 2] ............. 8 0
FIGURE 13: MLG TRUCK BEAM BUSHING INSTALLATION [Group 2] ................. 8 4
FIGURE 14: LEFT MLG INNER CYLINDER PIVOT LUG INSPECTION [Group 2] ............ 9 1
FIGURE 15: RIGHT MLG INNER CYLINDER PIVOT LUG INSPECTION [Group 2] ........... 9 5
FIGURE 16: MLG INNER CYLINDER BUSHINGS INSTALLATION [Group 2] .............. 9 9
APPENDIX A: PART MARKING REIDENTIFICATION TABLE ....................... 1 0 6
APPENDIX B: TRUCK BEAM BUSHING AND INNER CYLINDER BUSHING APPLICABILITY BASED ON
AIRPLANE MINOR MODEL ................................. 1 1 4
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Commercial 
Airplanes
767
Service Bulletin
Revision Transmittal SheetNumber: 767-32A0227Original Issue: April 25, 2012
Revision 1: September 13, 2012
ATA System: 3211
SUBJECT: LANDING GEAR - Main Gear - Pivot Joint Configuration Change
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplanes changed in accordance with the original issue of this service bulletin.
REASON FOR REVISION
This revision is sent to change part numbers, add an optional material and add part numbers to an appendix.
These sections were changed:
1. In Background, added a table of sections affected.
2. In Paragraph 1.J.2.a., Data Supplied with this Service Bulletin, changed the Revision level of two
drawing numbers.
3. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added an optional material.
4. In Paragraph 3.B., Work Instructions, changed the part numbers in a Note.
5. In Paragraph 3.B., Work Instructions, added an optional material to Step 9 of Figure 13.
6. In Appendix A, added assembly part number rows to the Group 2 table.
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
April 25, 2012Original Issue:
September 13, 2012Revision 1:
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Commercial 
Airplanes
767
Service Bulletin
SummaryNumber: 767-32A0227Original Issue: April 25, 2012
Revision 1: September 13, 2012
ATA System: 3211
SUBJECT: LANDING GEAR - Main Gear - Pivot Joint Configuration Change
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will change the configuration of the main landing gear (MLG) pivot joint
to reduce the amount of heat generated in the pivot pin, truck beam lugs and the shock strut inner cylinder lugs
during taxi, takeoff and landing. High levels of heat in the pivot joint can result in damage and cracks in the pivot
pin, truck beam lugs and inner cylinder lugs. The cracks could lead to fracture of the pivot joint components
which can result in the collapse of a MLG.
During MLG overhaul, pivot joint components have been found with cracks or heat damage eleven times on
767-400ER airplanes and 42 times on 767-200/-300/-300F airplanes. The earliest case of cracking was reported
at approximately 7.8 years from delivery for the 767-400ER and 7 years from delivery for the 767-200/-300/-300F.
Heat damage and cracks were found at the pivot joint location which is caused by the truck pitching motion
during normal airplane operations.
This service bulletin provides the instructions to install new bushings in the truck beam assemblies and shock
strut inner cylinder assemblies of the MLGs to reduce friction in the pivot joint. Reduced friction in the pivot joint
will lead to a lower amount of heat in the pivot joint which will prevent heat damage which can lead to cracks
and/or fracture of the pivot joint components.
Boeing Service Related Problem (SRP) 767-SRP-32-0172 is related to this service bulletin.
Boeing Fleet Team Digest (FTD) 767 FTD 32-10001 is related to this service bulletin.
Boeing Service Bulletin (SB) 767-32A0176 is related to this service bulletin.
Boeing SB 767-32-0220 is related to this service bulletin.
Boeing SB 767-32A0199 is related to the pivot pin and bushings in this service bulletin.
Boeing SB 767-32A0202 is related to the pivot pin in this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedYesSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
YesSpecial Tooling Required
ACTION (PRR B12901-102S)
Group 1:
Update maintenance program. Get access to the left and right MLG wheel wells. Remove the pivot pins of both
MLGs. Do a detailed inspection of the pivot pins, truck beam pivot joint bushings and inner cylinder pivot joint
bushings for heat damage and cracks. Remove the truck beam bushings and inner cylinder bushings and do a
detailed inspection of the lugs for cracks, chrome plate distress and corrosion. Repair or replace any damaged
parts. Install new truck beam bushings and inner cylinder bushings. Part mark the MLG components and
assemblies. Lubricate the pivot joint.
Group 2:
Update maintenance program. Get access to the left and right MLG wheel wells. Remove the truck beams of
both MLGs. Remove the truck beam bushings and inner cylinder bushings and do a detailed inspection of the
lugs for cracks, corrosion, bronze transfer and heat damage. Repair or replace any damaged parts. Install new
truck beam bushings and inner cylinder bushings. Part mark the MLG components and assemblies. Lubricate
the pivot joint.
EFFECTIVITY
767-200, 767-300, 767-300F and 767-400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of
affected airplanes.
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.
Refer to Paragraph 1.E., Compliance.
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INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures
given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Parts and/or Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-32A0227
GROUP 1:  UPDATE MAINTENANCE PROGRAM. GET ACCESS TO THE LEFT AND
RIGHT MLG WHEEL WELLS. REMOVE THE PIVOT PINS OF BOTH MLGS
DO A DETAILED INSPECTION OF THE PIVOT PINS, TRUCK BEAM PIVOT
JOINT BUSHINGS AND INNER CYLINDER PIVOT JOINT BUSHINGS FOR
HEAT DAMAGE AND  REMOVE THE TRUCK BEAM BUSHINGS
AND INNER CY  HINGS AND DO A DET  ILED INSPECTION
OF THE LUGS FOR  ATE DISTRESS AND CORROSION.
REPAIR OR REPI  ACE ANY DA  AGED PARTS. INSTALL NEW TRUCK
BEAM BUSHINGS AND INNER CYLINDER BUSHINGS. PART MARK THE
MLG COMPONENTS AND ASSEMBLIES. LUBRICATE THE PIVOT JOINT.
GROUP 2:  UPDATE MAINTENANCE PROGRAM. GET ACCESS TO THE LEFT AND
RIGHT MLG WHEEL WELLS. REMOVE THE TRUCK BEAMS OF BOTH
MLGS. REMOVE THE TRUCK BEAM BUSHINGS AND INNER CYLINDER
BUSHINGS AND DO A DETAILED INSPECTION OF THE LUGS FOR
CRACKS, CORROSION, BRONZE TRANSFER AND HEAT DAMAGE.
INSTALL NEW TRUCK BEAM BUSHINGS AND INNER CYLINDER
BUSHINGS. PART MARK THE MLG COMPONENTS AND ASSEMBLIES.
LUBRICATE THE PIVOT JOINT.
LEFT MAIN GEAR SHOWN,
RIGHT SIDE OPPOSITE
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Commercial 
Airplanes
767
Service Bulletin
Number: 767-32A0227
Original Issue: April 25, 2012
Revision 1: September 13, 2012
ATA System: 3211
SUBJECT: LANDING GEAR - Main Gear - Pivot Joint Configuration Change
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 airplane(s) shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR B12901-102S for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
767-400ER Airplanes with line number 758-965.-1
767-200, 767-300 and 767-300F Airplanes with line number 1-1017.-2
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
2VA001 - VA020
2VA301 - VA315
2VA501 - VA530
2VA701 - VA719
2VA801 - VA810
2VB001 - VB002
2VB051 - VB055
2VB101 - VB125
2VB201 - VB202
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GroupVariable Number
2VB251 - VB253
2VB281 - VB284
2VB301 - VB302
2VB321 - VB332
2VB371 - VB373
2VB401
2VB441 - VB444
2VE001 - VE003
2VE021 - VE023
2VE041 - VE043
2VE061 - VE069
2VE083 - VE086
2VE101 - VE104
2VE116 - VE118
2VE121 - VE126
2VE141 - VE152
2VE171 - VE172
2VF001 - VF002
2VF041 - VF042
2VF051
2VF061 - VF062
2VF071 - VF072
2VF091 - VF093
2VF101 - VF102
2VF161 - VF162
2VF171 - VF172
2VF180 - VF184
2VF251
2VK001 - VK016
2VK021 - VK022
2VK031 - VK056
2VK081 - VK113
2VK131 - VK133
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GroupVariable Number
2VK141 - VK148
2VK161 - VK164
2VK171
2VK181
2VK186
2VL001 - VL006
2VL011
2VL701 - VL703
2VL751 - VL755
2VL806 - VL807
2VL871 - VL873
2VL891 - VL900
2VL911 - VL914
2VL931 - VL932
2VL941
2VN001 - VN041
2VN051 - VN064
2VN081 - VN099
2VN111 - VN127
2VN130 - VN137
2VN151 - VN158
2VN163 - VN168
2VN171 - VN174
2VN191 - VN198
2VN211 - VN212
2VN221 - VN225
2VN231 - VN234
2VN241 - VN243
2VN251 - VN276
2VN291 - VN293
2VN301 - VN314
2VN371 - VN372
2VN376
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GroupVariable Number
2VN381 - VN388
2VN421 - VN427
2VN436
2VN471 - VN472
2VN491 - VN513
2VN531 - VN532
2VN536 - VN537
2VN541 - VN542
2VN546 - VN547
2VN551
2VN556 - VN557
2VN561 - VN562
2VN631 - VN638
2VN651 - VN658
2VN671 - VN672
2VN676
2VN681 - VN691
2VN731 - VN732
2VN751 - VN753
2VN791 - VN792
2VN811 - VN813
2VN921 - VN922
2VN931 - VN936
2VN951 - VN953
2VN966 - VN972
1VQ001 - VQ021
1VQ071 - VQ086
1VQ111
2VR051 - VR060
2VR081
2VR084
2VR086 - VR089
2VR106 - VR109
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GroupVariable Number
2VR201 - VR211
2VR251
2VR256 - VR260
2VR266 - VR277
2VR401
2VR421 - VR423
2VR426
2VR441
2VR461
2VR471 - VR472
2VS051 - VS056
2VS061
2VS066 - VS070
2VS073 - VS078
2VS091 - VS104
2VS111 - VS113
2VS131 - VS133
2VS136 - VS137
2VS176 - VS177
2VS186 - VS187
2VS196 - VS203
2VS206 - VS208
2VS211
2VS216 - VS217
2VS231
2VS246 - VS248
2VS261 - VS263
2VS266 - VS274
2VS291 - VS293
2VS301 - VS303
2VS306 - VS311
2VS316
2VS321 - VS324
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GroupVariable Number
2VS331 - VS333
2VS336 - VS337
2VS366 - VS367
2VS381 - VS382
2VS391 - VS392
2VS401
2VS426 - VS428
2VS466 - VS472
2VS486
2VS496 - VS497
2VS506 - VS507
2VS526
2VS546 - VS549
2VS701 - VS736
2VS751 - VS759
2VS821 - VS825
2VS841 - VS844
2VS861
2VS881 - VS883
2VS891
2VS896
2VS901 - VS912
2VS916
2VS921 - VS928
2VS931 - VS933
2VS941
2VS951 - VS954
2VS961 - VS967
2VS971 - VS976
2VT501
2VT511 - VT513
2VT521 - VT523
2VT531 - VT533
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GroupVariable Number
2VT541 - VT543
2VW701 - VW721
2VW851
2. Spares Affected
Group 1:
Examine your spares supply for 161T7130-1 truck beam assemblies and 161T7120-( ) inner
cylinder assemblies. If any 161T7130-1 truck beam assemblies or 161T7120-( ) inner cylinder
assemblies are found, do Part 6 - Truck Beam Detailed Inspection and Configuration Change
and/or Part 7 - Inner Cylinder Detailed Inspection and Configuration Change as applicable, in
accordance with Paragraph 3., Accomplishment Instructions.
Group 2:
Examine your spares supply for 161T1130-( ) and 161T1131-( ) truck beam assemblies and
161T1120-( ) and 015T1433-( ) inner cylinder assemblies. If any 161T1130-( ) or 161T1131-( )
truck beam assemblies or 161T1120-( ) or 015T1433-( ) inner cylinder assemblies are found, do
Part 8 - Truck Beam Detailed Inspection and Configuration Change and/or Part 9 - Inner Cylinder
Detailed Inspection and Configuration Change as applicable, in accordance with Paragraph 3.,
Accomplishment Instructions.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will change the configuration of the main landing gear (MLG)
pivot joint to reduce the amount of heat generated in the pivot pin, truck beam lugs and the shock strut
inner cylinder lugs during taxi, takeoff and landing. High levels of heat in the pivot joint can result in
damage and cracks in the pivot pin, truck beam lugs and inner cylinder lugs. The cracks could lead to
fracture of the pivot joint components which can result in the collapse of a MLG.
During MLG overhaul, pivot joint components have been found with cracks or heat damage eleven
times on 767-400ER airplanes and 42 times on 767-200/-300/-300F airplanes. The earliest case of
cracking was reported at approximately 7.8 years from delivery for the 767-400ER and 7 years from
delivery for the 767-200/-300/-300F. Heat damage and cracks were found at the pivot joint location
which is caused by the truck pitching motion during normal airplane operations.
This service bulletin provides the instructions to install new bushings in the truck beam assemblies and
shock strut inner cylinder assemblies of the MLGs to reduce friction in the pivot joint. Reduced friction
in the pivot joint will lead to a lower amount of heat in the pivot joint which will prevent heat damage
which can lead to cracks and/or fracture of the pivot joint components.
Revision 1 is sent to change part numbers, add an optional material and add part numbers to an
appendix.
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### Page 18

D. Description
Group 1:
Update maintenance program. Get access to the left and right MLG wheel wells. Remove the pivot
pins of both MLGs. Do a detailed inspection of the pivot pins, truck beam pivot joint bushings and inner
cylinder pivot joint bushings for heat damage and cracks. Remove the truck beam bushings and inner
cylinder bushings and do a detailed inspection of the bores for chrome plate distress and corrosion.
Repair or replace any damaged parts. Install new truck beam bushings and inner cylinder bushings.
Part mark the MLG components and assemblies. Lubricate the pivot joint.
Group 2:
Update maintenance program. Get access to the left and right MLG wheel wells. Remove the truck
beams of both MLGs. Remove the truck beam bushings and inner cylinder bushings and do a detailed
inspection of the bores for cracks, corrosion, bronze transfer and heat damage. Repair or replace any
damaged parts. Install new truck beam bushings and inner cylinder bushings. Part mark the MLG
components and assemblies. Lubricate the pivot joint.
Revision 1 - No more work is necessary on the airplanes changed in accordance with the original issue
of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
731, 741767-400ER
Group 2:
Affected Maintenance Zones
ZoneModel
731, 741767-200, 767-300, 767-300F
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.
Accomplish Part 1, Part 2 and Part 3 as required in Table 1, Table 2 and Table 3 below in accordance
with Paragraph 3., Accomplishment Instructions.
Evaluate the following conditions and actions based on each independent MLG individually.
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Table 1: Part 1 Pivot Joint Lubrication Maintenance Program Change
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Within 180 Days
After the Original
Issue Date of this
Service Bulletin
Do Part 1 - Pivot Joint
Lubrication Maintenance
Program Change. (a)
All Airplanes
(a) Since the FAA will possibly release an AD related to this service bulletin, an Alternative
Method of Compliance (AMOC) may be required for any changes to the intervals shown
in 767 MRB Item 32-087-01 after incorporation of Part 1 of this service bulletin.
Group 1:
Table 2: Part 2 and Part 3 MLG Pivot Pin and Bushing Detailed Inspection and MLG Pivot Joint Detailed
Inspection and Configuration Change
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
2,250 Days (b)Within 750 Days
After the Origi-
nal Issue Date
of this Service
Bulletin.
Within 1) or 2):
1) MLG has not
been over-
hauled: 2,250
Days After The
Date of Is-
suance of the
Original Certifi-
cate of Airworthi-
ness or the
Original Export
Certificate of
Airworthiness.
Do Part 2 - Pivot Pin and
Bushing Detailed Inspec-
tion. (a)
All Airplanes
2) MLG has
been over-
hauled: 2,250
Days Since Last
MLG Overhaul.
-AND-
--Within 3,750
Days After the
Original Issue
Date of this Ser-
vice Bulletin.
Do detailed and etch in-
spections and an FPI if
necessary, in accordance
with Part 3 - Pivot Joint
Detailed Inspection and
Configuration Change. (a)
(Terminating Action) (b)
(a) See Tables 4, 5, 6 and 7 for inspection findings and dispositions.
(b) Terminating Action is accomplishment of Parts 1 and 3 and all applicable actions from inspection findings
and dispositions.
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Group 2:
Table 3: Part 3 MLG Pivot Joint Detailed Inspection and Configuration Change
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
--Within 3,750
Days After the
Original Issue
Date of this Ser-
vice Bulletin.
Do detailed and etch in-
spections and an FPI in
accordance with Part 3 -
Pivot Joint Detailed In-
spection and Configura-
tion Change. (a)
All Airplanes
(Terminating Action) (b)
(a) See Tables 8 and 9 for inspection findings and dispositions.
(b) Terminating Action is accomplishment of Parts 1 and 3 and all applicable actions from inspection findings
and dispositions.
Group 1:
Table 4: Part 4 Pivot Pin Detailed Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Repair the pivot pin in
accordance with Part 4,
Condition 1, Option 1.
Condition 1: Bronze trans-
fer, heat discoloration,
darkened streaks or ther-
mal spray coating distress
is found.
-OR-
Replace the pivot pin with
a new, overhauled or
serviceable pivot pin in
accordance with Part 4,
Condition 1, Option 2.
--No further action required
for this pivot pin.
Condition 2: Bronze trans-
fer, heat discoloration,
darkened streaks and ther-
mal spray coating distress
is not found.
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Group 1:
Table 5: Part 5 Bushing Detailed Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Do detailed and etch in-
spections and an FPI if
necessary, in accordance
with Part 6 - Truck Beam
Detailed Inspection and
Configuration Change in
accordance with Part 5,
Condition 3.
Condition 3: The truck
beam bushings are not
within wear limits or any
crack is found or bushing
distress is found or smear-
ing of material into the lubri-
cation grooves is found or
grease does not appear in
the bushing inner diameter.
-Before further
flight.
Do detailed and etch in-
spections and an FPI if
necessary, in accordance
with Part 7 - Inner Cylin-
der Detailed Inspection
and Configuration
Change in accordance
with Part 5, Condition 4.
Condition 4: The inner
cylinder bushings are not
within wear limits or any
crack is found or bushing
distress is found or smear-
ing of material into the lubri-
cation grooves is found or
grease does not appear in
the bushing inner diameter.
--No further action is re-
quired for this pivot joint
location.
Condition 5: The truck
beam bushings and inner
cylinder bushings are with-
in wear limits, no crack
found, no bushing distress
is found, no smearing of
the material into the lubrica-
tion grooves is found and
grease appears in the
bushing inner diameter.
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Group 1:
Table 6: Part 6 Truck Beam Detailed Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Refinish the MLG truck
beam pivot lugs and in-
stall new bushings in ac-
cordance with Part 6,
Condition 6, Option 1.
Condition 6: No chrome
plate distress, no corrosion
and no crack found in the
truck beam pivot lugs.
-OR-
Replace the truck beam
with a new, overhauled or
serviceable truck beam
and install new bushings
in accordance with Part
6, Condition 6, Option 2.
-Before further
flight.
Repair the MLG truck
beam pivot lugs and in-
stall new bushings in ac-
cordance with Part 6,
Condition 7, Option 1.
Condition 7: Chrome plate
distress, corrosion or any
crack found in the truck
beam pivot lugs.
-OR-
Replace the truck beam
with a new, overhauled or
serviceable truck beam
and install new bushings
in accordance with Part
6, Condition 7, Option 2.
Group 1:
Table 7: Part 7 Inner Cylinder Detailed Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Refinish the MLG inner
cylinder pivot lugs and in-
stall new bushings in ac-
cordance with Part 7,
Condition 8, Option 1.
Condition 8: No chrome
plate distress, no corrosion
and no crack found in the
inner cylinder pivot lugs.
-OR-
Replace the inner cylin-
der with a new, over-
hauled or serviceable in-
ner cylinder and install
new bushings in accor-
dance with Part 7, Condi-
tion 8, Option 2.
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Group 1:
Table 7: Part 7 Inner Cylinder Detailed Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Repair the MLG inner
cylinder pivot lugs and in-
stall new bushings in ac-
cordance with Part 7,
Condition 9, Option 1.
Condition 9: Chrome plate
distress, corrosion or any
crack found in the inner
cylinder pivot lugs.
-OR-
Replace the inner cylin-
der with a new, over-
hauled or serviceable in-
ner cylinder and install
new bushings in accor-
dance with Part 7, Condi-
tion 9, Option 2.
Group 2:
Table 8: Part 8 Truck Beam Detailed Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Refinish the MLG truck
beam pivot lugs and in-
stall new bushings in ac-
cordance with Part 8,
Condition 10, Option 1.
Condition 10: No crack is
found, no corrosion is
found, no heat damage is
found and no bronze
transfer is found in the
truck beam lugs. -OR-
Replace the truck beam
with a new, overhauled or
serviceable truck beam
and install new bushings
in accordance with Part
8, Condition 10, Option 2.
-Before further
flight.
Repair the MLG truck
beam pivot lugs and in-
stall new bushings in ac-
cordance with Part 8,
Condition 11, Option 1.
Condition 11: Any crack is
found, any corrosion is
found, any heat damage is
found or any bronze trans-
fer is found in the truck
beam lugs. -OR-
Replace the truck beam
with a new, overhauled or
serviceable truck beam
and install new bushings
in accordance with Part
8, Condition 11, Option 2.
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Group 2:
Table 9: Part 9 Inner Cylinder Detailed Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further
flight.
Refinish the MLG inner
cylinder pivot lugs and in-
stall new bushings in ac-
cordance with Part 9,
Condition 12, Option 1.
Condition 12: No crack is
found, no corrosion is
found, no heat damage is
found and no bronze
transfer is found in the in-
ner cylinder lugs. -OR-
Replace the inner cylin-
der with a new, over-
hauled or serviceable in-
ner cylinder and install
new bushings in accor-
dance with Part 9, Condi-
tion 12, Option 2.
-Before further
flight.
Repair the MLG inner
cylinder pivot lugs and in-
stall new bushings in ac-
cordance with Part 9,
Condition 13, Option 1.
Condition 13: Any crack is
found, any corrosion is
found, any heat damage is
found or any bronze trans-
fer is found in the inner
cylinder lugs. -OR-
Replace the inner cylin-
der with a new, over-
hauled or serviceable in-
ner cylinder and install
new bushings in accor-
dance with Part 9, Condi-
tion 13, Option 2.
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.
The Manager of the FAA Seattle Aircraft Certification Office approves the MLG truck beam and inner
cylinder inspection, repair and bushing replacement defined in this service bulletin as an AMOC to the
applicable related investigative and corrective actions mandated by paragraph (i) of FAA AD 2006-07-14.
All provisions of FAA AD 2006-07-14 that are not specifically referenced in the above statements remain
fully applicable and must be complied with accordingly.
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### Page 25

The Manager of the FAA Seattle Aircraft Certification Office approves the MLG truck beam and inner
cylinder inspection, repair and bushing replacement given in the Accomplishment Instructions in SB
767-32A0227, Revision 1 in conjunction with the replacement of the MLG bogie beam pivot pins in
accordance with Part 5 of the Accomplishment Instructions of SB 767-32A0199, Revision 2, as an
AMOC to the pin replacement required by paragraph (j) of FAA AD 2006-07-14. All provisions of FAA
AD 2006-07-14 that are not specifically referenced in the above statement remain fully applicable and
must be complied with accordingly.
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 PersonsTask
4.2021.005Part 2: Open Access
2.002.001Part 4: FIGURE 1
2.002.001Part 4: FIGURE 2
3.256.502Part 5: FIGURE 3
3.256.502Part 5: FIGURE 4
4.2021.005Part 2: Close Access
18.90 (a)59.00 (a)TOTAL FOR EACH AIRPLANE
(a) This estimate does not include possible additional inspections and configuration
changes accomplished in Part 6 and Part 7. If additional inspections and
configuration changes are required, more time may be necessary.
Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
4.2021.005Part 3: Open Access
3.757.502Part 6: FIGURE 5
3.757.502Part 6: FIGURE 6
7.5030.004Part 6: FIGURE 7
3.7515.004Part 7: FIGURE 8
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Group 1:
Elapsed HoursTask HoursNumber of PersonsTask
3.7515.004Part 7: FIGURE 9
7.5030.004Part 7: FIGURE 10
4.2021.005Part 3: Close Access
38.40 (a) (b)147.00 (a) (b)TOTAL FOR EACH AIRPLANE
(a) This estimate does not include possible restoration. If restoration is required,
more time may be necessary.
(b) This estimate applies to the instructions in this service bulletin only. If overhaul
is done, no additional manpower is required.
Group 2:
Elapsed HoursTask HoursNumber of PersonsTask
4.2021.005Open Access
3.757.502Part 8: FIGURE 11
3.757.502Part 8: FIGURE 12
7.5030.004Part 8: FIGURE 13
3.7515.004Part 9: FIGURE 14
3.7515.004Part 9: FIGURE 15
7.5030.004Part 9: FIGURE 16
4.2021.005Close Access
38.40 (a) (b)147.00 (a) (b)TOTAL FOR EACH AIRPLANE
(a) This estimate does not include possible restoration. If restoration is required,
more time may be necessary.
(b) This estimate applies to the instructions in this service bulletin only. If overhaul
is done, no additional manpower is required.
H. Weight and Balance Changes
Group 1:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
-852.2-0.8767-400ER
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### Page 27

Group 2:
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
-852.2-0.8767-200
-852.2-0.8767-300
-852.2-0.8767-300F
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Engineering Change Memo PRR B12901-102S
b. Boeing Service Bulletin 767-32-0220, 767-32A0176, 767-32A0199, 767-32A0202
c. Boeing Service Letter 767-SL-12-018, 767-SL-32-072, 767-SL-51-036
d. Boeing Service Related Problem (SRP) 767-SRP-32-0172
e. Component Maintenance Manual (CMM) 32-00-05, 32-11-33, 32-11-36, 32-11-40, 32-11-50
f. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2006-07-14
g. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-20-02, 20-30-02,
20-30-03, 20-41-03, 20-42-10, 20-50-10
h. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-12, 20-10-19
i. 767 Aircraft Maintenance Manual (AMM) 12-21-14, 32-00-15, 32-00-20, 32-11-17, 32-11-18
j. 767 Fleet Team Digest (FTD) 32-10001
k. 767 Maintenance Review Board Report (MRB)
l. 767-400 Aircraft Maintenance Manual (AMM) 12-21-14, 32-00-15, 32-00-20, 32-11-17, 32-11-18
2. Data Supplied with this Service Bulletin:
a. Drawings:
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### Page 28

ADCNDCN/REVSheetTitleDrawing No
--1Misc Tool 767-200/-300 Only - Bushing
Removal/Install/Honing MLG Inner Cyl Fork
and Truck Beam
MIT161T1120MLG
--2
-A3
--4
-A1Misc Tool 767-400 Only - Bushing Re-
moval/Install/Honing MLG Inner Cyl Fork
and Truck Beam
MIT161T7120MLG
--2
--3
-A4
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Buildup Assembly - Main Landing Gear161T1000
Component Instl - Buildup Assembly, Main Landing Gear161T7000
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:
Chapter-SectionPublication
12-21, 32-11767 Aircraft Maintenance Manual
32-11767 Illustrated Parts Catalog
ATA 32767 Maintenance Review Board Report
32-11Component Maintenance Manual
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
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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M. Software Accomplishment Summary
Not affected.
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BLANK PAGE

### Page 31

2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the parts 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 parts 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 Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
QTYDateNamePart Number
$4,134.00Contact Boeing
Spares
--Bushing, Pivot Bore
Truck Beam
161T2877-3
$4,134.002004January 9,
2012
Bushing, Pivot Bore
Truck Beam (a)
161T2877-4
$1,681.00Contact Boeing
Spares
--Bushing, Pivot Bore In-
ner Cylinder
161T2875-20
$1,681.002004January 6,
2012
Bushing, Pivot Bore In-
ner Cylinder (a)
161T2875-21
(a) Oversized part.
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 Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
$1,816.00Contact Boeing
Spares
Bushing, Pivot Bore Truck Beam161T1250-2
$1,816.00Contact Boeing
Spares
Bushing, Pivot Bore Truck Beam (a)161T1262-2
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### Page 32

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 Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NamePart Number
$1,230.00Contact Boeing
Spares
Bushing, Pivot Bore Inner Cylinder161T1251-2
$1,230.00Contact Boeing
Spares
Bushing, Pivot Bore Inner Cylinder (a)161T1263-2
(a) Oversized part.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes inspection and/or repair
procedures given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
Group 1:
NotesNameQTYPart Number /
Specification
(a)Primer-BMS 10-79, TYPE
III
Grease-MIL-PRF-32014
(a)Corrosion Inhibiting Compound-BMS 3-38
If necessary. (a)Corrosion Inhibiting Compound-BMS 3-26
If necessary. (a)Corrosion Preventive Compound-MIL-C-11796 Class
3
Bushing, Pivot Bore Truck Beam4161T2877-3
(b)Bushing, Pivot Bore Truck Beam4161T2877-4
Bushing, Pivot Bore Inner Cylinder8161T2875-20
(b)Bushing, Pivot Bore Inner Cylinder8161T2875-21
Only needed if existing seal
rings are worn.
Seal Ring4716A1FSL-731-
5717
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Group 1:
NotesNameQTYPart Number /
Specification
(a) See the Qualified Parts List at the end of the Boeing Material Specification (BMS) for
supplier data.
(b) Oversized Part.
Group 2:
NotesNameQTYPart Number /
Specification
(a)Primer-BMS 10-11, TYPE
I (BMS 10-79,
TYPE III, optional)
Grease-MIL-PRF-32014
(a)Corrosion Inhibiting Compound-BMS 3-38
If necessary. (a)Corrosion Inhibiting Compound-BMS 3-26
If necessary. (a)Corrosion Preventive Compound-MIL-C- 11796
Class 3
(a)Sealant-BMS 5-95
Bushing, Pivot Bore Truck Beam4161T1250-2
(b)Bushing, Pivot Bore Truck Beam4161T1262-2
Bushing, Pivot Bore Inner Cylinder8161T1251-2
(b)Bushing, Pivot Bore Inner Cylinder8161T1263-2
Only needed if existing
grease seals are worn.
Grease Seal4704A5FRL-731
Only needed if existing
backup rings are worn.
Backup Ring4704A5FRL5717
(a) See the Qualified Parts List at the end of the Boeing Material Specification (BMS) for
supplier data.
(b) Oversized part.
NOTE: Refer to 767-SL-32-072 for additional part interchangeability.
3. Parts Modified and Reidentified
Refer to APPENDIX A for Part Marking and Reidentification.
4. Parts Removed and Not Replaced
None.
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D. Parts Necessary to Change Spares
To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
Group 1:
QTYNamePart Number
4Bushing, Pivot Bore Truck Beam161T2877-3
4Bushing, Pivot Bore Truck Beam161T2877-4 (a)
8Bushing, Pivot Bore Inner Cylinder161T2875-20
8Bushing, Pivot Bore Inner Cylinder161T2875-21 (a)
(a) Oversized Part.
Group 2:
QTYNamePart Number
4Bushing, Pivot Bore Truck Beam161T1250-2
4Bushing, Pivot Bore Truck Beam161T1262-2 (a)
8Bushing, Pivot Bore Inner Cylinder161T1251-2
8Bushing, Pivot Bore Inner Cylinder161T1263-2 (a)
(a) Oversized part.
E. Special Tooling - Price and Availability
Boeing can supply the tool(s) shown in Paragraph 2.F., Special Tooling Necessary to do this Service
Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of
the service bulletin by e-mail to ServiceBulletinRentalLoanTools@boeing.com. The tool(s) are subject
to the terms and conditions of the Boeing standard purchase order acknowledgement. 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 Boeing Part Page
2. Fax to (425) 965-8237
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### Page 35

Group 1:
Rental Data:
Daily Price as of
the Original Issue
date of this ser-
vice bulletin (US
Dollars)
NameTool Kit Number
$380.00Misc Tool 767-400 Only - Bush-
ing Removal/Install/Honing MLG
Inner Cyl Fork and Truck Beam
MIT161T7120MLG
Group 2:
Rental Data:
Daily Price as of
the Original Issue
date of this ser-
vice bulletin (US
Dollars)
NameTool Kit Number
$400.00Misc Tool 767-200/-300 Only -
Bushing Removal/Install/Honing
MLG Inner Cyl Fork and Truck
Beam
MIT161T1120MLG
F. Special Tooling Necessary to do this Service Bulletin
To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.
Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be
necessary. Examine operator tool supply to make sure all necessary tools are available.
Group 1:
NameTool Kit Number
Misc Tool 767-400 Only - Bushing Removal/Install/Honing MLG
Cyl Fork and Truck Beam
MIT161T7120MLG
Group 2:
NameTool Kit Number
Misc Tool 767-200/-300 Only - Bushing Removal/Install/Honing
MLG Inner Cyl Fork and Truck Beam
MIT161T1120MLG
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BLANK PAGE

### Page 37

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. 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
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. 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.
6. 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.
7. 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.
8. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
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9. 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.
10. Boeing Service Letter 767-SL-51-036, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
11. Refer to Appendix A for Part Marking Reidentification Table.
12. Refer to Appendix B for Bushing Applicability Table.
13. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
14. 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.
15. 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.
16. 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.
17. 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.
18. Overhaul of the Main Landing Gear and installation of 161T2877-3 or 161T2877-4
and 161T2875-20 or 161T2875-21 bushings, or 161T1250-2 or 161T1262-2 and
161T1251-2 or 161T1263-2 bushings, as applicable, satisfies the intent of Parts 2
and 3 of this service bulletin, as applicable.
B. WORK INSTRUCTIONS
Part 1 - Pivot Joint Lubrication Maintenance Program Change
1. Update airplane maintenance program to incorporate 767 MRB Item 32-087-01.
Group 1:
Part 2 - Pivot Pin and Bushing Detailed Inspection
1. Install the Main Landing Gear (MLG) and Nose Landing Gear (NLG) downlock pins. Refer to
767-400 AMM 32-00-20 as an accepted procedure.
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2. Install the MLG and NLG door safety pins. Refer to 767-400 AMM 32-00-15 as an accepted
procedure.
3. Remove the left and right MLG pivot pins. Refer to 767-400 AMM 32-11-18 as an accepted
procedure.
4. Do a detailed inspection of the left and right MLG pivot pins in accordance with Part 4 - Pivot Pin
Detailed Inspection.
5. Do a detailed inspection of the left and right MLG truck beam and inner cylinder bushings in
accordance with Part 5 - Bushing Detailed Inspection.
6. Install the left and right MLG pivot pins. Refer to 767-400 AMM 32-11-18 as an accepted procedure.
7. Lubricate the MLG pivot joints. Refer to 767-400 AMM 12-21-14 as an accepted procedure. Refer
to 767-SL-12-018 for cold weather lubrication.
8. Remove the MLG and NLG door safety pins. Refer to 767-400 AMM 32-00-15 as an accepted
procedure.
9. Remove the MLG and NLG downlock pins. Refer to 767-400 AMM 32-00-20 as an accepted
procedure.
10. Put the airplane back into serviceable condition.
NOTE: Overhaul of the MLG and installation of 161T2877-3 or 161T2877-4 and 161T2875-20
or 161T2875-21 bushings satisfies the intent of Parts 2 and 3 of this service bulletin.
Part 3 - Pivot Joint Inspection and Configuration Change
1. Install the Main Landing Gear (MLG) and Nose Landing Gear (NLG) downlock pins. Refer to 767
AMM 32-00-20 or 767-400 AMM 32-00-20 as an accepted procedure, as applicable.
2. Install the MLG and NLG door safety pins. Refer to 767 AMM 32-00-15 or 767-400 AMM 32-00-15
as an accepted procedure, as applicable.
3. Remove the left and right MLG truck beams. Refer to 767 AMM 32-11-18 or 767-400 AMM 32-11-18
as an accepted procedure, as applicable.
4. Do detailed and etch inspections, an FPI if necessary, and the configuration changes of the left
and right MLG truck beam in accordance with:
a. Group 1:
Part 6 - Truck Beam Detailed Inspection and Configuration Change.
b. Group 2:
Part 8 - Truck Beam Detailed Inspection and Configuration Change.
5. Do detailed and etch inspections, an FPI if necessary, and the configuration changes of the left
and right MLG inner cylinder in accordance with:
a. Group 1:
Part 7 - Inner Cylinder Detailed Inspection and Configuration Change.
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b. Group 2:
Part 9 - Inner Cylinder Detailed Inspection and Configuration Change.
6. Install the left and right MLG truck beams. Refer to 767 AMM 32-11-18 or 767-400 AMM 32-11-18
as an accepted procedure, as applicable.
7. Install new, overhauled or serviceable left and right MLG pivot pins. Refer to 767 AMM 32-11-18
or 767-400 AMM 32-11-18 as an accepted procedure, as applicable.
8. Lubricate the MLG pivot joints. Refer to 767 AMM 12-21-14 or 767-400 AMM 12-21-14 as an
accepted procedure. Refer to 767-SL-12-018 for cold weather lubrication.
9. Remove the MLG and NLG door safety pins. Refer to 767 AMM 32-00-15 or 767-400 AMM 32-00-15
as an accepted procedure, as applicable.
10. Remove the MLG and NLG downlock pins. Refer to 767 AMM 32-00-20 or 767-400 AMM 32-00-20
as an accepted procedure, as applicable.
11. Put the airplane back into serviceable condition.
Group 1:
NOTE: Overhaul of the MLG and installation of 161T2877-3 or 161T2877-4 and 161T2875-20
or 161T2875-21 bushings satisfies the intent of Parts 2 and 3 of this service bulletin.
Group 2:
NOTE: Overhaul of the MLG and installation of 161T1250-2 or 161T1262-2 and 161T1251-2 or
161T1263-2 bushings satisfies the intent of Part 3 of this service bulletin.
Group 1:
Part 4 - Pivot Pin Detailed Inspection
1. Do a detailed inspection of the left and right MLG pivot pins in accordance with the figures below:
Right MLGLeft MLG
FIGURE 2FIGURE 1
a. Condition 1: Bronze transfer, heat discoloration, darkened streaks or thermal spray coating
distress is found.
(1) Option 1: Repair the pivot pin.
(a) Repair the pivot pin. Refer to CMM 32-11-36, Repair 19-1 as an accepted procedure.
(2) Option 2: Replace the pivot pin with a new, overhauled or serviceable pivot pin.
(a) Replace the pivot pin with a new, overhauled or serviceable pivot pin. Refer to 767-400
AMM 32-11-18 as an accepted procedure.
b. Condition 2: Bronze transfer, heat discoloration, darkened streaks and thermal spray coating
distress is not found.
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(1) No further action required for this pivot pin.
Group 1:
Part 5 - Bushing Detailed Inspection
1. Do a detailed inspection of the MLG pivot joint truck beam bushings and inner cylinder bushings
in accordance with the figures below:
Right MLGLeft MLG
FIGURE 4FIGURE 3
a. Condition 3: The truck beam bushings are not within wear limits or any crack is found or
bushing distress is found or smearing of material into the lubrication grooves is found or grease
does not appear in the bushing inner diameter.
(1) Do Part 6 - Truck Beam Inspection and Configuration Change.
b. Condition 4: The inner cylinder bushings are not within wear limits or any crack is found or
bushing distress is found or smearing of material into the lubrication grooves is found or grease
does not appear in the bushing inner diameter.
(1) Do Part 7 - Inner Cylinder Inspection and Configuration Change.
c. Condition 5: The truck beam bushings and inner cylinder bushings are within wear limits, no
crack found, no bushing distress is found, no smearing of the material into the lubrication
grooves is found and grease appears in the bushing inner diameter.
(1) No further action is required for this pivot joint location.
Group 1:
Part 6 - Truck Beam Detailed Inspection and Configuration Change
1. Do a detailed inspection of the MLG truck beam pivot lugs, and, if no distress, no corrosion, and
no cracking is found, do an FPI in accordance with the figures below:
Right MLGLeft MLG
FIGURE 6FIGURE 5
a. Condition 6: No chrome plate distress, no corrosion and no crack found in the truck beam
pivot lugs.
(1) Option 1: Refinish the MLG truck beam pivot lugs and install new bushings.
(a) Refinish the MLG truck beam pivot lugs, if necessary. Refer to CMM 32-11-36, Repair
12-2 as an accepted procedure.
(b) Install new bushings in the MLG truck beam pivot lugs in accordance with FIGURE
7. Refer to CMM 32-11-36, Repair 12-1 as an accepted procedure.
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(2) Option 2: Replace the truck beam with a new, overhauled or serviceable truck beam and
install new bushings.
(a) Replace the truck beam with a new, overhauled or serviceable truck beam that has
new bushings installed in accordance with FIGURE 7. Refer to 767-400 AMM
32-11-18 as an accepted procedure.
b. Condition 7: Chrome plate distress, corrosion or any crack found in the truck beam pivot lugs.
(1) Option 1: Repair the MLG truck beam pivot lugs and install new bushings.
(a) Repair the MLG truck beam pivot lugs. Refer to CMM 32-11-36, Repair 12-1 and
12-2 as an accepted procedure.
(b) Install new bushings in the MLG truck beam pivot lugs in accordance with FIGURE
7. Refer to CMM 32-11-36, Repair 12-2 as an accepted procedure.
(2) Option 2: Replace the truck beam with a new, overhauled or serviceable truck beam and
install new bushings.
(a) Replace the truck beam with a new, overhauled or serviceable truck beam that has
new bushings installed in accordance with FIGURE 7. Refer to 767-400 AMM
32-11-18 as an accepted procedure.
Group 1:
Part 7 - Inner Cylinder Detailed Inspection and Configuration Change
1. Do a detailed inspection of the MLG inner cylinder pivot lugs, and, if no distress, no corrosion, and
no cracking is found, do an FPI in accordance with the figures below:
Right MLGLeft MLG
FIGURE 9FIGURE 8
a. Condition 8: No chrome plate distress, no corrosion and no crack found in the inner cylinder
pivot lugs.
(1) Option 1: Refinish the MLG inner cylinder pivot lugs and install new bushings.
(a) Refinish the MLG inner cylinder pivot lugs, if necessary. Refer to CMM 32-11-33,
Repair 3-2 as an accepted procedure.
(b) Install new bushings in the MLG inner cylinder pivot lugs in accordance with FIGURE
10. Refer to CMM 32-11-33, Repair 3-1 as an accepted procedure.
(2) Option 2: Replace the inner cylinder with a new, overhauled or serviceable inner cylinder
and install new bushings.
(a) Replace the inner cylinder with a new, overhauled or serviceable inner cylinder that
has new bushings installed in accordance with FIGURE 10. Refer to 767-400 AMM
32-11-17 as an accepted procedure.
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b. Condition 9: Chrome plate distress, corrosion or any crack found in the inner cylinder pivot
lugs.
(1) Option 1: Repair the MLG inner cylinder pivot lugs and install new bushings.
(a) Repair the MLG inner cylinder pivot lugs. Refer to CMM 32-11-33, Repair 3-1 and
3-2 as an accepted procedure.
(b) Install new bushings in the MLG inner cylinder pivot lugs in accordance with FIGURE
10. Refer to CMM 32-11-33, Repair 3-1 as an accepted procedure.
(2) Option 2: Replace the inner cylinder with a new, overhauled or serviceable inner cylinder
and install new bushings.
(a) Replace the inner cylinder with a new, overhauled or serviceable inner cylinder that
has new bushings installed in accordance with FIGURE 10. Refer to 767-400 AMM
32-11-17 as an accepted procedure.
Group 2:
Part 8 - Truck Beam Detailed Inspection and Configuration Change
1. Do detailed and etch inspections and an FPI of the MLG truck beam pivot lugs in accordance with
the figures below:
Right MLGLeft MLG
FIGURE 12FIGURE 11
a. Condition 10: No crack is found, no corrosion is found, no heat damage is found and no bronze
transfer is found in the truck beam lug lugs.
(1) Option 1: Refinish the MLG truck beam pivot lugs and install new bushings.
(a) Refinish the MLG truck beam pivot lugs, if necessary. Refer to CMM 32-11-50, Repair
1-2 as an accepted procedure.
(b) Install new bushings in the MLG truck beam pivot lugs in accordance with FIGURE
13. Refer to CMM 32-11-50, Repair 1-1 as an accepted procedure.
(2) Option 2: Replace the truck beam with a new, overhauled or serviceable truck beam and
install new bushings.
(a) Replace the truck beam with a new, overhauled or serviceable truck beam that has
new bushings installed in accordance with FIGURE 13. Refer to 767 AMM 32-11-18
as an accepted procedure.
b. Condition 11: Any crack is found, any corrosion is found, any heat damage is found or any
bronze transfer is found in the truck beam lugs.
(1) Option 1: Repair the MLG truck beam pivot lugs and install new bushings.
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(a) Repair the MLG truck beam pivot lugs. Refer to CMM 32-11-50, Repair 1-1 and 1-2
as an accepted procedure.
(b) Install new bushings in the MLG truck beam pivot lugs in accordance with FIGURE
13. Refer to CMM 32-11-50, Repair 1-1 as an accepted procedure.
(2) Option 2: Replace the truck beam with a new, overhauled or serviceable truck beam and
install new bushings.
(a) Replace the truck beam with a new, overhauled or serviceable truck beam that has
new bushings installed in accordance with FIGURE 13. Refer to 767 AMM 32-11-18
as an accepted procedure.
Group 2:
Part 9 - Inner Cylinder Detailed Inspection and Configuration Change
1. Do detailed and etch inspections and an FPI of the MLG inner cylinder pivot lugs in accordance
with the figures below:
Right MLGLeft MLG
FIGURE 15FIGURE 14
a. Condition 12: No crack is found, no corrosion is found, no heat damage is found and no bronze
transfer is found in the inner cylinder lugs.
(1) Option 1: Refinish the MLG inner cylinder pivot lugs and install new bushings.
(a) Refinish the MLG inner cylinder pivot lugs, if necessary. Refer to CMM 32-11-40,
Repair 2-2 as an accepted procedure.
(b) Install new bushings in the MLG inner cylinder pivot lugs in accordance with FIGURE
16. Refer to CMM 32-11-40, Repair 2-1 as an accepted procedure.
(2) Option 2: Replace the inner cylinder with a new, overhauled or serviceable inner cylinder
and install new bushings.
(a) Replace the inner cylinder with a new, overhauled or serviceable inner cylinder that
has new bushings installed in accordance with FIGURE 16. Refer to 767 AMM
32-11-17 as an accepted procedure.
b. Condition 13: Any crack is found, any corrosion is found, any heat damage is found or any
bronze transfer is found in the inner cylinder lugs.
(1) Option 1: Repair the MLG inner cylinder pivot lugs and install new bushings.
(a) Repair the MLG inner cylinder pivot lugs. Refer to CMM 32-11-40, Repair 2-1 and
2-2 as an accepted procedure.
(b) Install new bushings in the MLG inner cylinder pivot lugs in accordance with FIGURE
16. Refer to CMM 32-11-40, Repair 2-2 as an accepted procedure.
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(2) Option 2: Replace the inner cylinder with a new, overhauled or serviceable inner cylinder
and install new bushings.
(a) Replace the inner cylinder with a new, overhauled or serviceable inner cylinder that
has new bushings installed in accordance with FIGURE 16. Refer to 767 AMM
32-11-17 as an accepted procedure.
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-32A0227
This Figure applies only to: Group 1.
TEND
LEFT MAIN GEAR
OE PIVOT PIN
2032601
FIGURE 1: LEFT MLG PIVOT PIN INSPECTION
(SHEET 1 OF 2)
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### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
1-Pivot PinClean1
Do a Detailed Inspec-
tion of the outer di-
ameter for bronze
transfer, heat discol-
oration, darkened
streaks and thermal
spray coating dis-
tress. (a) (b)
1-Pivot PinInspect2
(a) Refer to CMM 32-00-05 for information about damage identification.
(b) Color changes, darkened streaks or bronze transfer deposits which are removed by hand sanding with
a non-metallic fine abrasive material is acceptable.
FIGURE 1: LEFT MLG PIVOT PIN INSPECTION
(SHEET 2 OF 2)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 767-32A0227
This Figure applies only to: Group 1.
A
RIGHT MAIN GEAR
PIVOT PIN 1
2032610
FIGURE 2: RIGHT MLG PIVOT PIN INSPECTION
(SHEET 1 OF 2)
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### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
1-Pivot PinClean1
Do a Detailed Inspec-
tion of the outer di-
ameter for bronze
transfer, heat discol-
oration, darkened
streaks and thermal
spray coating dis-
tress. (a) (b)
1-Pivot PinInspect2
(a) Refer to CMM 32-00-05 for information about damage identification.
(b) Color changes, darkened streaks or bronze transfer deposits which are removed by hand sanding with
a non-metallic fine abrasive material is acceptable.
FIGURE 2: RIGHT MLG PIVOT PIN INSPECTION
(SHEET 2 OF 2)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN 767-32A0227
This Figure applies only to: Group 1.
LEFT MAIN GEAR
4 2 LOCATIONS
_ A
2032614
FIGURE 3: LEFT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 1 OF 4)
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### Page 51

FIGURE 3: LEFT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 2 OF 4)
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### 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 this figure.
More DataQtyIdentificationNameTaskStep
Clean inner diame-
ter, grease grooves
and around flange
area. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
2-Truck Beam BushingsClean1
Clean inner diame-
ter, grease grooves
and around flange
area. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
4-Inner Cylinder BushingsClean
Do a Detailed Inspec-
tion of the bushing
inner diameter and
flanges for cracks,
smearing of material
into the lubrication
grooves and bushing
distress. (a) (b)
2-Truck Beam BushingsInspect2
Do a Detailed Inspec-
tion of the bushing
inner diameter and
flanges for cracks,
smearing of material
into the lubrication
grooves and bushing
distress. (a) (b)
4-Inner Cylinder BushingsInspect
Do a Detailed Inspec-
tion for wear limits.
Refer to CMM 32-
11-36 as an accept-
ed procedure.
2-Truck Beam BushingsInspect3
Do a Detailed Inspec-
tion for wear limits.
Refer to CMM 32-
11-36 as an accept-
ed procedure.
4-Inner Cylinder BushingsInspect
FIGURE 3: LEFT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 25, 2012
767-32A0227Revision 1 September 13, 2012
52 of 114
BOEING SERVICE BULLETIN 767-32A0227

### Page 53

More DataQtyIdentificationNameTaskStep
Through the truck
beam and inner
cylinder lube fittings.
Grease should ap-
pear in the bushing
inner diameter. Re-
fer to 767-400 AMM
12-21-14 as an ac-
cepted procedure.
(c)
--GreaseApply4
(a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.
(b) Darkened areas, heat discoloration and burnishing that can be removed by hand sanding with a non-
metallic fine abrasive material are acceptable and are not considered signs of bushing distress.
(c) If grease does not appear in the bushing inner diameter, BMS3-32 can be applied through the lube fitting
and passage to remove dried grease as an accepted procedure. Lube passages that are cleared of dried
grease with BMS3-32 are acceptable. Using other fluids or solvents other than BMS3-32 for cleaning lube
passages is not allowed.
FIGURE 3: LEFT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 25, 2012
767-32A0227Revision 1 September 13, 2012
53 of 114
BOEING SERVICE BULLETIN 767-32A0227

### Page 54 (OCR)

BOEING SERVICE BULLETIN 767-32A0227
This Figure applies only to: Group 1.
FEND
RIGHT MAIN GEAR
Лмво
2 LOCATIONS 4
2032618
FIGURE 4: RIGHT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 1 OF 4)
Original Issue: April 25, 2012
Revision 1 September 13, 2012  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright @ Unpublished
Work - See page 1 for details.  54 of 114

### Page 55

FIGURE 4: RIGHT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 2 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 25, 2012
767-32A0227Revision 1 September 13, 2012
55 of 114
BOEING SERVICE BULLETIN 767-32A0227

### 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 this figure.
More DataQtyIdentificationNameTaskStep
Clean inner diame-
ter, grease grooves
and around flange
area. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
2-Truck Beam BushingsClean1
Clean inner diame-
ter, grease grooves
and around flange
area. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
4-Inner Cylinder BushingsClean
Do a Detailed Inspec-
tion of the bushing
inner diameter and
flanges for cracks,
smearing of material
into the lubrication
grooves and bushing
distress. (a) (b)
2-Truck Beam BushingsInspect2
Do a Detailed Inspec-
tion of the bushing
inner diameter and
flanges for cracks,
smearing of material
into the lubrication
grooves and bushing
distress. (a) (b)
4-Inner Cylinder BushingsInspect
Do a Detailed Inspec-
tion for wear limits.
Refer to CMM 32-
11-36 as an accept-
ed procedure.
2-Truck Beam BushingsInspect3
Do a Detailed Inspec-
tion for wear limits.
Refer to CMM 32-
11-36 as an accept-
ed procedure.
4-Inner Cylinder BushingsInspect
FIGURE 4: RIGHT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 3 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 25, 2012
767-32A0227Revision 1 September 13, 2012
56 of 114
BOEING SERVICE BULLETIN 767-32A0227

### Page 57

More DataQtyIdentificationNameTaskStep
Through the truck
beam and inner
cylinder lube fittings.
Grease should ap-
pear in the bushing
inner diameter. Re-
fer to 767-400 AMM
12-21-14 as an ac-
cepted procedure.
(c)
--GreaseApply4
(a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.
(b) Darkened areas, heat discoloration and burnishing that can be removed by hand sanding with a non-
metallic fine abrasive material are acceptable and are not considered signs of bushing distress.
(c) If grease does not appear in the bushing inner diameter, BMS3-32 can be applied through the lube fitting
and passage to remove dried grease as an accepted procedure. Lube passages that are cleared of dried
grease with BMS3-32 are acceptable. Using other fluids or solvents other than BMS3-32 for cleaning lube
passages is not allowed.
FIGURE 4: RIGHT MLG PIVOT JOINT BUSHING INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 25, 2012
767-32A0227Revision 1 September 13, 2012
57 of 114
BOEING SERVICE BULLETIN 767-32A0227

### Page 58 (OCR)

BOEING SERVICE BULLETIN 767-32A0227
This Figure applies only to: Group 1.
LEFT MAIN GEAR
2032659
FIGURE 5: LEFT MLG TRUCK BEAM PIVOT LUG INSPECTION
(SHEET 1 OF 3)
Original Issue: April 25, 2012
Revision 1 September 13, 2012  Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.

### Page 59 (OCR)

BOEING SERVICE BULLETIN 767-32A0227
TRUCK  [INBD
BEAM  A-A
TRUCK
BEAM
2) 3
INBD
B-B  2032685
FIGURE 5: LEFT MLG TRUCK BEAM PIVOT LUG INSPECTION
(SHEET 2 OF 3)
Original Issue: April 25, 2012
Revision 1 September 13, 2012  Export Controlled ECCN: 9E991 - BOEING  767-32A0227
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  59 of 114

### Page 60

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for this figure.
More DataQtyIdentificationNameTaskStep
2-Seal RingRemove / Keep1
Refer to tool
MIT161T7120MLG
instructions. Refer to
CMM 32-11-36 as
an accepted proce-
dure.
2-Truck Beam BushingsRemove
Clean bore, cham-
fers and faces. Refer
to SOPM 20-30-03
as an accepted pro-
cedure.
2-Truck Beam Pivot LugsClean2
Do a Detailed Inspec-
tion of the entire
bore, chamfers and
faces for cracks,
signs of chrome
plate distress and
corrosion. (a)
2-Truck Beam Pivot LugsInspect3
If no cracks, signs of
chrome plate dis-
tress and corrosion
are found, inspect
the chrome plated
surface of the entire
bore, chamfers and
faces for cracks with
a Flourescent Pene-
trant Inspection. Re-
fer to SOPM 20-20-
02 as an accepted
procedure, except
do not remove the
chrome plate and do
not chemically etch.
(a) (b)
2-Truck Beam Pivot LugsInspect
(a) Refer to CMM 32-00-05 for information about damage identification.
(b) Background fluorescence due to micro-cracks in the chrome plate is acceptable.
FIGURE 5: LEFT MLG TRUCK BEAM PIVOT LUG INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: April 25, 2012
767-32A0227Revision 1 September 13, 2012
60 of 114
BOEING SERVICE BULLETIN 767-32A0227

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