# Boeing Alert Service Bulletin 777-32A0082: No revision named

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- Title as filed: U.S. DOT/FAA - SB-777-32A0082-00
- Pages: 61
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### Page 1

Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-32A0082
Original Issue: December 09, 2010
ATA System: 3211
SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder
Pivot Joint Lubrication and Inspection
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 © 2010 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, 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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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 4
B. Concurrent Requirements ...................................... 1 4
C. Reason ................................................ 1 4
D. Description .............................................. 1 4
E. Compliance .............................................. 1 5
F. Approval ............................................... 2 1
G. Manpower .............................................. 2 1
H. Weight and Balance Changes .................................... 2 2
I. Electrical Load Data ......................................... 2 2
J. References .............................................. 2 2
1. Existing Data .......................................... 2 2
2. Data supplied with this Service Bulletin ............................ 2 3
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 3
K. Publications Affected ........................................ 2 3
L. Interchangeability and Intermixability of Parts ........................... 2 4
2. MATERIAL INFORMATION ........................................ 2 5
A. Material - Price and Availability ................................... 2 5
B. Industry Support Information .................................... 2 5
C. Parts Necessary For Each Airplane ................................. 2 5
1. Kits/Parts ............................................ 2 5
2. Parts and Materials Supplied by the Operator ........................ 2 5
3. Parts Modified and Reidentified ................................ 2 6
4. Parts Removed and Not Replaced .............................. 2 6
D. Parts Necessary to Change Spares ................................. 2 6
E. Special Tooling - Price and Availability ............................... 2 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9
A. GENERAL INFORMATION ..................................... 2 9
B. WORK INSTRUCTIONS ....................................... 2 9
FIGURE 1: LEFT MLG CENTER AXLE INSPECTION .......................... 3 3
FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION ......................... 3 5
FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION .................. 3 7
FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION .................. 4 0
FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION .................. 4 3
FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION ................. 4 6
FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT . . 49
FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT . 55
APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT
INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL ............. 6 1
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Commercial 
Airplanes
777
Service Bulletin
ALERT
SummaryNumber: 777-32A0082Original Issue: December 09, 2010
ATA System: 3211
SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder
Pivot Joint Lubrication and Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will detect and prevent heat damage and possible cracks in the main
landing gear (MLG) center axle and shock strut inner cylinder lugs (pivot joint) on 777 airplanes. The airplanes
are subject to increased heat buildup in the MLG pivot joint which can cause cracks in the pivot joint components.
The cracks could lead to fracture of the center axle or inner cylinder lugs. Fracture of the center axle or inner
cylinder lugs can result in the collapse of a MLG.
During MLG overhaul, 28 center axles have been found with cracks at the inner cylinder/truck beam pivot joint
location. There have been no reports of a center axle fracture. Heat damage and cracks were found at the pivot
joint location which is caused by the truck pitching motion during normal airplane operations. Cracks were found
in areas common to the inner cylinder pivot bushings where heat damage had occurred.
This service bulletin provides the instructions for increased lubrication, inspection and repair of the MLG pivot
joint components. Increased lubrication of the MLG pivot joint components will prevent heat damage which can
lead to cracks and/or fracture of the pivot joint components.
Boeing Service Related Problem (SRP) 777-SRP-32-0159 is related to this service bulletin.
Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin.
The Work Instructions of this service bulletin are equivalent to the Work Instructions of Boeing Service Bulletin
(SB) 777-32-0080, which is related to this service bulletin.
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ACTION
Get access to the left and right MLG wheel wells. Lubricate the pivot joint of both MLGs and repeat the lubrication.
Remove the landing gear center axles of both MLGs. Do a detailed, magnetic particle and, if necessary, nital
etch inspection of the MLG pivot joints, including the center axle, inner cylinder bushings and inner cylinder lug
bores. If no damage is found, repeat the inspection. If damage is found, repair or replace the damaged parts
and repeat the inspection.
EFFECTIVITY
777-200, -300, -200LR, -300ER and 777F 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.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service
bulletin.
Boeing is offering an MLG center axle exchange program for those Customers who would like to purchase an
exchange axle to facilitate their inspection/overhaul program. Please contact Boeing for availability and detailed
terms and conditions.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability
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BOEING SERVICE BULLETIN 777-32A0082
ALERT  ALERT
LUBRICATE THE PIVOT JOINT OF BOTH MLGS AND REPEAT THE
LUBRICATION.  DO A DETAILED, MAGNETIC PARTICLE AND, IF
NECESSARY, NITAL ETCH INSPECTION OF THE MLG PIVOT
JOINTS, INCLUDING THE CENTER AXLE, INNER CYLINDER
BUSHINGS AND INNER CYLINDER LUG BORES. IF NO DAMAGE IS
FOUND, REPEAT THE INSPECTION. IF DAMAGE IS FOUND
INSPECTION.  REPAIR OR REPLACE THE DAMAGED PARTS AND REPEAT THE  1853457
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Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-32A0082
Original Issue: December 09, 2010
ATA System: 3211
SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder
Pivot Joint Lubrication and Inspection
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
777-200, -300 Airplanes line numbers 1 through 914.-1
Airplanes that have not done pivot joint lubrication every 50 flight
cycles or 25 days, whichever occurs later, since main landing gear
was new, last overhauled, last Part 2 Inspection of this service bulletin
or last Part 2 Inspection of SB 777-32-0080.
1
Airplanes that have done pivot joint lubrication every 50 flight cycles
or 25 days, whichever occurs later, since main landing gear was new,
last overhauled, last Part 2 Inspection of this service bulletin or last
Part 2 Inspection of SB 777-32-0080.
2
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DESCRIPTIONCONFIGURATIONGROUP
777-200LR, -300ER and 777F Airplanes line numbers 1 through 914.-2
Airplanes that have not done pivot joint lubrication every 50 flight
cycles or 25 days, whichever occurs later, since main landing gear
was new, last overhauled, last Part 2 Inspection of this service bulletin
or last Part 2 Inspection of SB 777-32-0080.
1
Airplanes that have done pivot joint lubrication every 50 flight cycles
or 25 days, whichever occurs later, since main landing gear was new,
last overhauled, last Part 2 Inspection of this service bulletin or last
Part 2 Inspection of SB 777-32-0080.
2
Airplane Models:
777-200, 777-200LR, 777-300, 777-300ER, 777F
GroupVariable Number
1WA001 - WA017
1WA076 - WA080
1WA086 - WA093
1WA101 - WA104
1WA116 - WA119
1WA131 - WA137
1WA171 - WA175
1WA196 - WA198
1WA206 - WA212
1WA221 - WA223
1WA231 - WA232
1WA241 - WA250
1WA261 - WA266
1WA281 - WA283
1WA301 - WA304
1WB001 - WB021
1WB031 - WB046
1WB051 - WB088
1WB101 - WB106
1WB121 - WB125
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GroupVariable Number
1WB131 - WB148
1WB151 - WB155
1WB161 - WB177
1WB181 - WB194
1WB201 - WB215
1WB231 - WB247
1WB271 - WB273
1WB276 - WB286
1WB291 - WB302
1WB306 - WB307
1WB311 - WB337
1WB341 - WB342
1WB366 - WB368
1WB371 - WB388
1WB406
1WB411 - WB413
1WB416 - WB439
1WB446 - WB453
1WB476
1WB481 - WB484
1WB501 - WB512
1WB531 - WB537
1WB551 - WB554
1WB591 - WB597
1WB601 - WB606
1WB611 - WB622
1WB631 - WB638
1WB646 - WB649
1WC051 - WC073
1WC101 - WC104
1WC111 - WC120
1WC221 - WC224
1WC241 - WC243
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GroupVariable Number
1WC281 - WC290
1WC301 - WC308
1WC361 - WC364
1WC371 - WC374
1WC381 - WC395
1WC441
1WC446 - WC449
1WC456 - WC459
1WC486 - WC493
1WC506 - WC508
1WC521 - WC522
1WC531 - WC536
1WC546 - WC548
1WC556
1WC566 - WC567
1WC571 - WC574
1WC581
2WD001 - WD002
2WD011 - WD018
2WD031 - WD036
2WD046 - WD055
2WD066 - WD075
2WD081 - WD088
2WD091
2WD096
2WD101 - WD103
2WD501 - WD513
2WD521 - WD541
2WD546 - WD554
2WD561 - WD573
2WD581 - WD599
2WD606 - WD609
2WD621 - WD632
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GroupVariable Number
2WD651 - WD665
2WD671 - WD676
2WD691 - WD709
2WD741 - WD752
2WD761 - WD771
2WD786 - WD788
2WD796 - WD813
2WD826 - WD837
2WD846 - WD861
2WD871 - WD883
2WD911 - WD914
2WD921 - WD922
2WD936 - WD939
2WD946 - WD951
2WD966 - WD970
2WD981 - WD982
2WD986 - WD987
2WD996
2WE001 - WE004
2WE011 - WE012
2WE021 - WE024
2WE031
2WE051 - WE052
2WE071
2WE081 - WE082
2WE126 - WE131
2WF001 - WF004
2WF016 - WF020
2WF031 - WF032
2WF046 - WF053
2WF076 - WF077
2WF081 - WF088
2WF096 - WF099
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GroupVariable Number
2WF106 - WF107
2WF111 - WF112
2WF121
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will detect and prevent heat damage and possible cracks in
the main landing gear (MLG) center axle and shock strut inner cylinder lugs (pivot joint) on 777 airplanes.
The airplanes are subject to increased heat buildup in the MLG pivot joint which can cause cracks in
the pivot joint components. The cracks could lead to fracture of the center axle or inner cylinder lugs.
Fracture of the center axle or inner cylinder lugs can result in the collapse of a MLG.
During MLG overhaul, 28 center axles have been found with cracks at the inner cylinder/truck beam
pivot joint location. There have been no reports of a center axle fracture. Heat damage and cracks
were found at the pivot joint location which is caused by the truck pitching motion during normal airplane
operations. Cracks were found in areas common to the inner cylinder pivot bushings where heat damage
had occurred.
This service bulletin provides the instructions for increased lubrication, inspection and repair of the
MLG pivot joint components. Increased lubrication of the MLG pivot joint components will prevent heat
damage which can lead to cracks and/or fracture of the pivot joint components.
Boeing Service Related Problem (SRP) 777-SRP-32-0159 is related to this service bulletin.
Boeing Service Letter (SL) 777-SL-32-059 is related to this service bulletin.
The Work Instructions of this service bulletin are equivalent to the Work Instructions of Boeing Service
Bulletin (SB) 777-32-0080, which is related to this service bulletin.
D. Description
Get access to the left and right MLG wheel wells. Lubricate the pivot joint of both MLGs and repeat the
lubrication. Remove the landing gear center axles of both MLGs. Do a detailed, magnetic particle and,
if necessary, nital etch inspection of the MLG pivot joints, including the center axle, inner cylinder
bushings and inner cylinder lug bores. If no damage is found, repeat the inspection. If damage is found,
repair or replace the damaged parts and repeat the inspection.
The work in this service bulletin is done in the maintenance zone(s) given below.
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Group 1:
Affected Maintenance Zones
ZoneModel
731, 741777-200, 777-300
Group 2:
Affected Maintenance Zones
ZoneModel
731, 741777-200LR, 777-300ER, 777F
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 and Part 2 as required in Table 1, Table 2, Table 3, Table 4, Table 5 and Table 6
below in accordance with Paragraph 3., Accomplishment Instructions.
Evaluate the following conditions and actions based on each independent MLG individually.
Table 1: MLG Pivot Joint Lubrication Compliance Data
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
50 flight cycles or
25 days, whichever
occurs later. (a)
Within 120 Days
After the Original
Issue Date of this
Service Bulletin.
Do Part 1 - MLG Pivot
Joint Lubrication. (a)
All Airplanes
(a) Refer to 777 MPD Section 1 Item 12-081-00 and 777 MRB Section 1 Item 12-081-00.
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Group 1, Configuration 1:
Table 2: MLG Pivot Joint Inspection for 777-200 and -300 Airplanes That Do Not Do Pivot Joint Lubrication
Every 50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear was New, Last
Overhauled, Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of SB 777-32-0080.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,750 DaysWithin 1,125
Days After the
Original Issue
Date of this Ser-
vice Bulletin.
Before 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 - MLG Pivot
Joint Inspection. (a) (b)
See Table 6 for disposi-
tion of conditions found.
All Airplanes
2) MLG has
been over-
hauled: 2,250
Days Since Last
MLG Overhaul.
(a) Overhaul of the MLG satisfies the intent of Part 2.
(b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2.
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Group 1, Configuration 2:
Table 3: MLG Pivot Joint Inspection for 777-200 and -300 Airplanes That Do Pivot Joint Lubrication Every
50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear was New, Last Overhauled,
Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of SB 777-32-0080.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,750 DaysWithin 375 Days
After the Origi-
nal Issue Date
of this Service
Bulletin.
Before 1) or 2):
1) MLG has not
been over-
hauled: 3,750
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 - MLG Pivot
Joint Inspection. (a) (b)
See Table 6 for disposi-
tion of conditions found.
All Airplanes
2) MLG has
been over-
hauled: 3,750
Days Since Last
MLG Overhaul.
(a) Overhaul of the MLG satisfies the intent of Part 2.
(b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2.
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Group 2, Configuration 1:
Table 4: MLG Pivot Joint Inspection for 777-200LR, -300ER and 777F Airplanes That Do Not Do Pivot
Joint Lubrication Every 50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear
was New, Last Overhauled, Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of
SB 777-32-0080.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 DaysWithin 1,125
Days After the
Original Issue
Date of this Ser-
vice Bulletin.
Before 1) or 2):
1) MLG has not
been over-
hauled: 1,825
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 - MLG Pivot
Joint Inspection. (a) (b)
See Table 6 for disposi-
tion of conditions found.
All Airplanes
2) MLG has
been over-
hauled: 1,825
Days Since Last
MLG Overhaul.
(a) Overhaul of the MLG satisfies the intent of Part 2.
(b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2.
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Group 2, Configuration 2:
Table 5: MLG Pivot Joint Inspection for 777-200LR, -300ER and 777F Airplanes That Do Pivot Joint Lu-
brication Every 50 Flight Cycles or 25 Days, Whichever Occurs Later, Since Main Landing Gear was
New, Last Overhauled, Last Part 2 Inspection of this Service Bulletin or Last Part 2 Inspection of SB
777-32-0080.
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
3,000 DaysWithin 300 Days
After the Origi-
nal Issue Date
of this Service
Bulletin.
Before 1) or 2):
1) MLG has not
been over-
hauled: 3,000
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 - MLG Pivot
Joint Inspection. (a) (b)
See Table 6 for disposi-
tion of conditions found.
All Airplanes
2) MLG has
been over-
hauled: 3,000
Days Since Last
MLG Overhaul.
(a) Overhaul of the MLG satisfies the intent of Part 2.
(b) Completion of Part 2 of SB 777-32-0080 satisfies the intent of Part 2.
Table 6: Parts 2-5 Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
--Before further
flight.
Do Part 4 - Inner Cylinder
Bushing Inspection.
Condition 1: No crack, no
chicken wire cracks, no
corrosion and no chrome
plate distress found.
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Table 6: Parts 2-5 Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
--Before further
flight.
Repair the center axle in
accordance with Part 3,
Condition 2, Option 1.
Condition 2: Chicken wire
cracks found, or corrosion
is found, or chrome plate
distress is found with no
other crack found.
-OR-
Replace the center axle
with a new, overhauled or
serviceable center axle in
accordance with Part 3,
Condition 2, Option 2.
-AND-
--Before further
flight.
Do Part 4 - Inner Cylinder
Bushing Inspection.
--Before further
flight.
Repair the center axle in
accordance with Part 3,
Condition 3, Option 1.
Condition 3: Any crack
found, excluding chicken
wire cracks.
-OR-
Replace the center axle
with a new, overhauled or
serviceable center axle in
accordance with Part 3,
Condition 3, Option 2.
-AND-
--Before further
flight.
Do Part 5 - Inner Cylinder
Lug Bore Inspection.
---No further action is re-
quired for this inner cylin-
der location.
Condition 4: Bushings are
within wear limits, no crack
found, no bushing distress
is found, no smearing of
the material into the lubrica-
tion grooves is found, no
corrosion is found and the
grease flow is not restrict-
ed.
--Before further
flight.
Do Part 5 - Inner Cylinder
Lug Bore Inspection.
Condition 5: 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 corrosion is found
or the grease flow is restrict-
ed.
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Table 6: Parts 2-5 Inspection Findings and Disposition
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
--Before further
flight.
Refinish the lug bore and
faces and install new
bushings in accordance
with Part 5, Condition 6.
Condition 6: No crack is
found, no corrosion is
found, no heat damage is
found and no bronze
transfer is found.
--Before further
flight.
Repair the inner cylinder
in accordance with Part
5, Condition 7, Option 1.
Condition 7: Any crack is
found, any corrosion is
found, any heat damage is
found or any bronze trans-
fer is found in the inner
cylinder bore.
-OR-
Repair the inner cylinder
in accordance with Part
5, Condition 7, Option 2.
-OR-
Replace inner cylinder
with a new, overhauled or
serviceable inner cylinder
in accordance with Part
5, Condition 7, Option 3.
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.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection 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.
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Elapsed HoursTask HoursNumber of Per-
sons
Task
2.004.002Part 1 (a)
2.004.00TOTAL FOR EACH
AIRPLANE
(a) Additional time may be required for cold weather lubrication. Refer to 777-SL-
12-006 for cold weather lubrication recommendations when temperatures are
below 0 degrees Celsius.
Elapsed HoursTask HoursNumber of Per-
sons
Task
9.0054.006Part 2
5.005.001Part 3: Figure 1
5.005.001Part 3: Figure 2
2.252.251Part 4: Figure 3
2.252.251Part 4: Figure 4
4.50 (a)9.00 (a)2Part 5: Figure 5
4.50 (a)9.00 (a)2Part 5: Figure 6
(b)(b)Part 5: Figure 7
(b)(b)Part 5: Figure 8
34.5090.50TOTAL FOR EACH AIRPLANE
(a) Estimate assumes Condition 6 is found. If Condition 7 is found, more time will
be necessary.
(b) Estimate assumes Condition 6 is found. If Condition 7 is found, work in FIGURE
7 and FIGURE 8 will require additional time.
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Boeing Service Bulletin 777-32-0080
b. Boeing Service Letter 777-SL-12-006, 777-SL-32-001, 777-SL-32-059, 777-SL-32-061
c. Boeing Service Related Problem (SRP) 777-SRP-32-0159
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d. Component Maintenance Manual (CMM) 32-00-07, 32-11-03, 32-11-07, 32-11-64, 32-11-65
e. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-10-03, 20-20-01, 20-20-02,
20-30-02, 20-30-03, 20-42-10
f. 777 Aircraft Maintenance Manual (AMM) 12-21-14, 32-00-15, 32-00-30, 32-11-04, 32-11-18,
32-11-26
g. 777 Maintenance Planning Data (MPD) Section 1Item 12-081-00
h. 777 Maintenance Review Board Report (MRB)
2. Data supplied with this Service Bulletin
a. Drawings:
ADCNDCN/REVSheetTitleDrawing No
-B1Misc Tool Replacement and Honing Kit In-
ner Cyl Ctr Axle
MIT161W1122
--2
--3
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Installation - Main Landing Gear161W0000
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
32-11Component Maintenance Manual
Section 2, ATA 12777 Maintenance Review Board Report
Section 1, ATA 12777 Maintenance Planning Data Document
32-11777 Maintenance Manual
32-11777 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
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L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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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
Unit Price as of the
original issue date
of this Service Bul-
letin (US Dollars)
ROLT as of
the original
issue date of
this Service
Bulletin (Cal-
endar Days)
NamePart Number
$54,030.00623Center Axle Assy161W1163-13
$54,030.00623Center Axle Assy161W1163-15
$242,622.001624Inner Cylinder Assy161W1255-7
$254,847.001344Inner Cylinder Assy161W2120-3
$2,928.00301Bushing, Inner Cylinder161W1122-2
$3,526.00301Bushing, Inner Cylinder161W1122-3
B. Industry Support Information
Boeing warranty remedies are not available for the inspection and/or repair procedures given in this
service bulletin.
Boeing is offering an MLG center axle exchange program for those Customers who would like to
purchase an exchange axle to facilitate their inspection/overhaul program. Please contact Boeing for
availability and detailed terms and conditions.
C. Parts Necessary For Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
NotesNameQTYPart Number /
Specification
Grease-Royco 11MS
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NotesNameQTYPart Number /
Specification
(c)Sealant-BMS 5-95
(c)Primer-BMS 10-79, Type
III
(c)Corrosion Inhibiting Compound-BMS 3-23, Type II,
Class 1
(c) Optional.Corrosion Inhibiting Compound-BMS 3-26, Type I
(c)Shock Strut Fluid-BMS 3-32
Refer to APPENDIX A for
part number applicability.
Center Axle Assy2161W1163-1, -3, -
5, -7, -11, -13, or-
15
Refer to APPENDIX A for
part number applicability.
Inner Cylinder Assy2161W1120-3, -5
Refer to APPENDIX A for
part number applicability.
Inner Cylinder Assy2161W1255-1, -5, -
7
Refer to APPENDIX A for
part number applicability.
Inner Cylinder Assy2161W2120-1, -3
(a)Bushing, Inner Cylinder4161W1122-2
Oversized part. (a) (b)Bushing, Inner Cylinder4161W1122-3
(a) This part can be fabricated. Refer to CMM 32-11-03 or CMM 32-11-65 as an accepted
procedure, as applicable.
(b) The 161W1122-3 bushing is preferred over the 161W1122-2 bushing due to larger lube
passages.
(c) See the Qualified Parts List at the end of the Boeing Material Specification (BMS) for
supplier data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service
Bulletin. Send a Purchase Order to the Director of Spares. Give this service bulletin number and the
date the tools will be used.
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Purchase Data:
Unit PriceNameTool Kit Number
Contact Boeing
Spares for Current
Pricing Information
Misc Tool - Bushing Replace-
ment and Honing Kit - Inner Cyl
Ctr Axle
MIT161W1122
The kits are subject to the terms and conditions of the Boeing standard purchase order
acknowledgement. After the Price date, new price data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
Reference this service bulletin number and submit 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. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
(Service Bulletin 777-32-0080 R01)
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.
NameTool Kit Number
Misc Tool - Bushing Replace-
ment and Honing Kit - Inner Cyl
Ctr Axle
MIT161W1122
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### Page 29

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. Use the approved fastener and process material substitutions in accordance with
777 SRM, Chapter 51. Alternate fasteners are listed in 777 SRM Chapter 51 and
Boeing Drawing 012W6100.
5. 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.
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.
7. Refer to Appendix A for Part Interchangeability Based on Airplane Model.
B. WORK INSTRUCTIONS
PART 1 - MAIN LANDING GEAR PIVOT JOINT LUBRICATION
1. Install the main landing gear (MLG) and nose landing gear (NLG) downlock pins. Refer to 777
AMM 32-00-30 as an accepted procedure.
2. Install the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.
3. Lubricate the MLG pivot joints. Refer to 777 AMM 12-21-14 as an accepted procedure. Refer to
777-SL-12-006 for cold weather lubrication.
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4. Remove the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.
5. Remove the MLG and NLG downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure.
6. Put the airplane back into serviceable condition.
PART 2 - MLG PIVOT JOINT INSPECTION
1. Install the main landing gear (MLG) and nose landing gear (NLG) downlock pins. Refer to 777
AMM 32-00-30 as an accepted procedure.
2. Install the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.
3. Remove the left and right MLG center axles. Refer to 777 AMM 32-11-26 as an accepted procedure.
4. Do Part 3 - Center Axle Inspection.
5. Install the left and right MLG center axles. Refer to 777 AMM 32-11-26 as an accepted procedure.
6. Remove the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.
7. Remove the MLG and NLG downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure.
8. Put the airplane back into serviceable condition.
PART 3 - CENTER AXLE INSPECTION
1. Inspect the center axles in accordance with the figures below:
RIGHT MLGLEFT MLG
FIGURE 2FIGURE 1
a. Condition 1: No crack, no chicken wire cracks, no corrosion and no chrome plate distress
found.
(1) Do Part 4 - Inner Cylinder Bushing Inspection.
b. Condition 2: Chicken wire cracks found, or corrosion is found, or chrome plate distress is
found with no other crack found.
(1) Option 1: Repair the center axle. Refer to CMM 32-11-07 Repair 7-2 or CMM 32-11-64
Repair 5-2 as an accepted procedure, as applicable.
(2) Option 2: Replace the center axle with a new, overhauled or serviceable center axle.
Refer to 777 AMM 32-11-26 as an accepted procedure. Refer to APPENDIX A for center
axle assembly interchangeability based on airplane type.
(3) Do Part 4 - Inner Cylinder Bushing Inspection.
c. Condition 3: Any crack found, excluding chicken wire cracks.
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(1) Option 1: Repair the center axle. Refer to CMM 32-11-07 Repair 7-2 or CMM 32-11-64
Repair 5-2 as an accepted procedure, as applicable.
(2) Option 2: Replace the center axle with a new, overhauled or serviceable center axle.
Refer to 777 AMM 32-11-26 as an accepted procedure. Refer to APPENDIX A for center
axle assembly interchangeability based on airplane type.
(3) Do Part 5 - Inner Cylinder Lug Bore Inspection.
PART 4 - INNER CYLINDER BUSHING INSPECTION
1. Inspect the inner cylinder bushings and lug faces in accordance with the figures below:
RIGHT MLGLEFT MLG
FIGURE 4FIGURE 3
a. Condition 4: Bushings are within wear limits, no crack found, no bushing distress is found, no
smearing of the material into the lubrication grooves is found, no corrosion is found and the
grease flow is not restricted.
(1) No further action is required for this inner cylinder location.
b. Condition 5: 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 corrosion is found or the
grease flow is restricted.
(1) Do Part 5 - Inner Cylinder Lug Bore Inspection.
PART 5 - INNER CYLINDER LUG BORE INSPECTION
1. Inspect the inner cylinder lug bores in accordance with the figures below, as applicable:
RIGHT MLGLEFT MLG
FIGURE 6FIGURE 5
a. Condition 6: No crack is found, no corrosion is found, no heat damage is found and no bronze
transfer is found in the inner cylinder lug bore or face.
(1) Refinish the lug bore and faces. Refer to SOPM 20-42-10 and CMM 32-11-03 Repair 4-2
or CMM 32-11-65 Repair 5-2 as accepted procedures, as applicable.
(2) Install new bushings. Refer to CMM 32-11-03 Repair 4-1 or CMM 32-11-65 Repair 5-1
as accepted procedures, as applicable.
b. Condition 7: Any crack is found, any corrosion is found, any heat damage is found or any
bronze transfer is found in the inner cylinder lug bore or face.
(1) Option 1: Repair the inner cylinder in accordance with the figures below, as applicable:
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RIGHT MLGLEFT MLG
FIGURE 8FIGURE 7
(2) Option 2: Repair the inner cylinder. Refer to CMM 32-11-03 Repair 4-2 or CMM 32-11-65
Repair 5-2 as accepted procedures, as applicable.
(3) Option 3: Replace inner cylinder with a new, overhauled or serviceable inner cylinder.
Refer to 777 AMM 32-11-04 as an accepted procedure. Refer to APPENDIX A for inner
cylinder assembly interchangeability based on airplane type.
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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 MLG.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
1-Center AxleClean1
Do a Detailed Inspec-
tion of the outer di-
ameter chrome for
chicken wire cracks,
corrosion and
chrome plate dis-
tress. (a) (b) (c) (d)
1-Center AxleInspect2
Do a Magnetic Parti-
cle Inspection of the
outer diameter
chrome for cracks in
the area common to
the inner cylinder
bushings plus a min-
imum of 2 inches on
both sides. Refer to
SOPM 20-20-01 as
an accepted proce-
dure.
1-Center AxleInspect3
FIGURE 1: LEFT MLG CENTER AXLE INSPECTION
(SHEET 1 OF 2)
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MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(a) Signs of chrome plate distress includes ladder cracks, material or bronze transfer, darkened streaks,
plating which is smeared, chipped, cracked, flaked, a different color, or gone. Visually examine the plated
surface with light at an angle, but do not use magnification. Look at the surfaces from different angles.
The sharp point of a dental explorer can be used to find cracks in the chrome plating. Refer to CMM 32-
00-07 for information about chrome plate distress identification.
(b) Chicken Wire Cracks are defined as cracks that occur when stresses created in the chrome deposit during
plating are relieved. The cracks are evident in the deposited chrome when viewed from a perpendicular
plane as a pattern similar to chicken wire. Crack size can vary with plating conditions.
(c) Color changes, darkened streaks or bronze transfer deposits which are removed by hand sanding with
a non-metallic fine abrasive material is acceptable.
(d) A Fluorescent Penetrant Inspection can be used to supplement the detailed inspection of large areas for
chrome plate distress. Refer to SOPM 20-20-02 as an accepted procedure.
FIGURE 1: LEFT MLG CENTER AXLE INSPECTION
(SHEET 2 OF 2)
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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 MLG.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
1-Center AxleClean1
Do a Detailed Inspec-
tion of the outer di-
ameter chrome for
chicken wire cracks,
corrosion and
chrome plate dis-
tress. (a) (b) (c) (d)
1-Center AxleInspect2
FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION
(SHEET 1 OF 2)
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MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a Magnetic Parti-
cle Inspection of the
outer diameter
chrome for cracks in
the area common to
the inner cylinder
bushings plus a min-
imum of 2 inches on
both sides. Refer to
SOPM 20-20-01 as
an accepted proce-
dure.
1-Center AxleInspect3
(a) Signs of chrome plate distress includes ladder cracks, material or bronze transfer, darkened streaks,
plating which is smeared, chipped, cracked, flaked, a different color, or gone. Visually examine the plated
surface with light at an angle, but do not use magnification. Look at the surfaces from different angles.
The sharp point of a dental explorer can be used to find cracks in the chrome plating. Refer to CMM 32-
00-07 for information about chrome plate distress identification.
(b) Chicken Wire Cracks are defined as cracks that occur when stresses created in the chrome deposit during
plating are relieved. The cracks are evident in the deposited chrome when viewed from a perpendicular
plane as a pattern similar to chicken wire. Crack size can vary with plating conditions.
(c) Color changes, darkened streaks or bronze transfer deposits which are removed by hand sanding with
a non-metallic fine abrasive material is acceptable.
(d) A Fluorescent Penetrant Inspection can be used to supplement the detailed inspection of large areas for
chrome plate distress. Refer to SOPM 20-20-02 as an accepted procedure.
FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION
(SHEET 2 OF 2)
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BOEING SERVICE BULLETIN 777-32A0082
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4) 2 LOCATIONS
(5) 4 LOCATIONS
12 з
1853449
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 MLG.
FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION
(SHEET 1 OF 3)
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### Page 38

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Clean inner diame-
ters, grease grooves
and around flange
area. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
2-Inner Cylinder BushingsClean1
Do a Detailed Inspec-
tion of the bushing
inner diameters and
flanges for cracks,
smearing of material
into the lubrication
grooves and bushing
distress. (a) (b) (e)
(f)
2-Inner Cylinder BushingsInspect2
For wear limits. Re-
fer to CMM 32-11-07
or CMM 32-11-64 as
an accepted proce-
dure, as applicable.
2-Inner Cylinder BushingsInspect3
Through the lube fit-
tings to make sure
the grease flow is
not restricted.
Grease should ap-
pear through at least
two grease holes in
the bushing. (c) (d)
(g)
-ROYCO 11MSGreaseApply4
Do a Detailed Inspec-
tion for corrosion. (h)
4-Inner Cylinder Lug
Face
Inspect5
(a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.
(b) Darkened areas, heat discoloration and burnishing which are removed by hand sanding with a non-
metallic fine abrasive material is acceptable.
(c) Clean lube passages if grease flow is restricted. A room temperature or heated shock strut fluid such as
BMS 3-32 can be applied through the lube fitting and passage to remove dried grease as an accepted
procedure. Repeat application of grease and cleaning of lube passages until grease flow is not restricted.
(d) Temporary plugging of bushing through-wall holes is allowed to redirect grease to other through-wall
holes.
(e) Bushing distress and smearing of material into the lubrication grooves that has been removed by honing
the bushing up to a diameter of 6.7545 inches is acceptable. Refer to tool MIT161W1122 for honing in-
structions. Final bushing bore diameters must be within 0.0015 inches of each other.
FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
38 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 39

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(f) For improved access to bushing flanges, it is acceptable to remove the truck beam. Refer to 777 AMM
32-11-18 as an accepted procedure.
(g) If the bushing has one grease hole, make sure grease appears through that hole.
(h) 777-SL-32-061 has information about corrosion prevention.
FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
39 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 40 (OCR)

BOEING SERVICE BULLETIN 777-32A0082
ALERT  ALERT
2 LOCATIONS 4
4 LOCATIONS 5)
1853450
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 MLG.
FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION
(SHEET 1 OF 3)
Original Issue: December 09, 2010
BOEING PROPRIETARY -  777-32A0082
Copyright © Unpublished Work - See page 1 for details.  40 of 61

### Page 41

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Clean inner diame-
ters, grease grooves
and around flange
area. Refer to
SOPM 20-30-03 as
an accepted proce-
dure.
2-Inner Cylinder BushingsClean1
Do a Detailed Inspec-
tion of the bushing
inner diameters and
flanges for cracks,
smearing of material
into the lubrication
grooves and bushing
distress. (a) (b) (e)
(f)
2-Inner Cylinder BushingsInspect2
For wear limits. Re-
fer to CMM 32-11-07
or CMM 32-11-64 as
an accepted proce-
dure, as applicable.
2-Inner Cylinder BushingsInspect3
Through the lube fit-
tings to make sure
the grease flow is
not restricted.
Grease should ap-
pear through at least
two grease holes in
the bushing. (c) (d)
(g)
-ROYCO 11MSGreaseApply4
Do a Detailed Inspec-
tion for corrosion. (h)
4-Inner Cylinder Lug
Face
Inspect5
(a) Bushing distress is defined as burnishing, galling, heat discoloration or darkened area.
(b) Darkened areas, heat discoloration and burnishing which are removed by hand sanding with a non-
metallic fine abrasive material is acceptable.
(c) Clean lube passages if grease flow is restricted. A room temperature or heated shock strut fluid such as
BMS 3-32 can be applied through the lube fitting and passage to remove dried grease as an accepted
procedure. Repeat application of grease and cleaning of lube passages until grease flow is not restricted.
(d) Temporary plugging of bushing through-wall holes is allowed to redirect grease to other through-wall
holes.
(e) Bushing distress and smearing of material into the lubrication grooves that has been removed by honing
the bushing up to a diameter of 6.7545 inches is acceptable. Refer to tool MIT161W1122 for honing in-
structions. Final bushing bore diameters must be within 0.0015 inches of each other.
FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
41 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 42

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(f) For improved access to bushing flanges, it is acceptable to remove the truck beam. Refer to 777 AMM
32-11-18 as an accepted procedure.
(g) If the bushing has one grease hole, make sure grease appears through that hole.
(h) 777-SL-32-061 has information about corrosion prevention.
FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
42 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 777-32A0082
ALERT  ALERT
2345018
2 LOCATIONS
2 LOCATIONS 1
1853453
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 MLG.
FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION
(SHEET 1 OF 3)
Original Issue: December 09, 2010
BOEING PROPRIETARY -  777-32A0082
Copyright © Unpublished Work - See page 1 for details.  43 of 61

### Page 44

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator
equivalent tools can be used.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to tool
MIT161W1122 in-
structions. (a)
2-Inner Cylinder BushingsRemove1
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
2-Inner Cylinder Bore and
Face
Clean2
from lug bores and
faces common to the
bushing flange (un-
painted surface).
Make sure primer
has been completely
removed. Refer to
SOPM 20-30-02 as
an accepted proce-
dure.
--PrimerRemove3
Do a Detailed Inspec-
tion of the lug bore
inner diameter for
cracks, corrosion or
bronze transfer and
the lug bore face for
cracks or corrosion.
2-Inner Cylinder Bore and
Face
Inspect4
Do a Penetrant In-
spection for corro-
sion. Refer to SOPM
20-20-02 as an ac-
cepted procedure.
(c) (d)
2-Inner Cylinder Bore and
Face
Inspect5
Do a Magnetic Parti-
cle Inspection for
cracks. Refer to
SOPM 20-20-01 as
an accepted proce-
dure. (d)
2-Inner Cylinder Bore and
Face
Inspect6
FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
44 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 45

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b) From the lug
bores and faces.
Remove the cadmi-
um plate by manual
application of ammo-
nium nitrate solution.
Refer to SOPM 20-
30-02 as an accept-
ed procedure. Make
sure adjacent areas
are protected where
cadmium plating re-
moval is not re-
quired. (d)
--Cadmium PlatingRemove7
(b) Do a Local Etch
of Large Parts In-
spection of the base
metal where the
cadmium plating
was removed to de-
tect heat damage.
Refer to SOPM 20-
10-02 as an accept-
ed procedure. Make
sure adjacent areas
are protected where
the nital etch inspec-
tion is not required.
Ammonium Persul-
fate method is not
allowed. (d)
2-Inner Cylinder Lug BoreInspect8
(a) Bushing removal is only required at the location where corrosion, bushing damage, bushing beyond wear
limit or axle crack was found.
(b) This step is only required if a crack or bronze transfer is found on the inner cylinder lug bore or if a crack
is found on the center axle.
(c) Bushing removal can result in smeared cadmium in the lug bore. Smeared cadmium can give false indi-
cations of corrosion. Remove cadmium and reinspect to make sure any corrosion indications resulting
from smeared cadmium are removed.
(d) This step is not necessary if the only bushing condition resulting in bushing removal was grease flow re-
striction unless damage was found during the Detailed Inspection.
FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
45 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 46 (OCR)

BOEING SERVICE BULLETIN 777-32A0082
ALERT  ALERT
134€013
2 LOCATIONS
O 2 LOCATIONS
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 MLG.
FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION
(SHEET 1 OF 3)
Original Issue: December 09, 2010
BOEING PROPRIETARY -  777-32A0082
Copyright © Unpublished Work - See page 1 for details.  46 of 61

### Page 47

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator
equivalent tools can be used.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to tool
MIT161W1122 in-
structions. (a)
2-Inner Cylinder BushingsRemove1
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
2-Inner Cylinder Bore and
Face
Clean2
from lug bores and
faces common to
bushing flange (un-
painted surface).
Make sure primer
has been completely
removed. Refer to
SOPM 20-30-02 as
an accepted proce-
dure.
--PrimerRemove3
Do a Detailed Inspec-
tion of the lug bore
inner diameter for
cracks, corrosion or
bronze transfer and
the lug bore face for
cracks or corrosion.
2-Inner Cylinder Bore and
Face
Inspect4
Do a Penetrant In-
spection for corro-
sion. Refer to SOPM
20-20-02 as an ac-
cepted procedure.
(c) (d)
2-Inner Cylinder Bore and
Face
Inspect5
Do a Magnetic Parti-
cle Inspection for
cracks. Refer to
SOPM 20-20-01 as
an accepted proce-
dure. (d)
2-Inner Cylinder Bore and
Face
Inspect6
FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION
(SHEET 2 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
47 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 48

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b) From the lug
bores and faces.
Remove the cadmi-
um plate by manual
application of ammo-
nium nitrate solution.
Refer to SOPM 20-
30-02 as an accept-
ed procedure. Make
sure adjacent areas
are protected where
cadmium plating re-
moval is not re-
quired. (d)
--Cadmium PlatingRemove7
(b) Do a Local Etch
of Large Parts In-
spection of the base
metal where the
cadmium plating
was removed to de-
tect heat damage.
Refer to SOPM 20-
10-02 as an accept-
ed procedure. Make
sure adjacent areas
are protected where
the nital etch inspec-
tion is not required.
Ammonium Persul-
fate method is not
allowed. (d)
2-Inner Cylinder Lug BoreInspect8
(a) Bushing removal is only required at the location where corrosion, bushing damage, bushing beyond wear
limit or axle crack was found.
(b) This step is only required if a crack or bronze transfer is found on the inner cylinder lug bore or if a crack
is found on the center axle.
(c) Bushing removal can result in smeared cadmium in the lug bore. Smeared cadmium can give false indi-
cations of corrosion. Remove cadmium and reinspect to make sure any corrosion indications resulting
from smeared cadmium are removed.
(d) This step is not necessary if the only bushing condition resulting in bushing removal was grease flow re-
striction unless damage was found during the Detailed Inspection.
FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION
(SHEET 3 OF 3)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
48 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 49 (OCR)

BOEING SERVICE BULLETIN 777-32A0082
ALERT  ALERT
11) 15) 2 LOCATIONS
2 LOCATIONS  7
2 LOCATIONS
2 LOCATIONS (12 17)
1853455
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 MLG.
FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 1 OF 6)
Original Issue: December 09, 2010
BOEING PROPRIETARY -  777-32A0082
Copyright © Unpublished Work - See page 1 for details.  49 of 61

### Page 50

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator
equivalent tools can be used.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
As necessary to re-
move any corrosion,
heat damage, cracks
or bronze transfer.
Maximum 0.020 inch
increase in the diam-
eter with a maximum
lug bore diameter of
7.1015 inches. Refer
to tool
MIT161W1122 in-
structions. Refer to
SOPM 20-10-02 as
an accepted proce-
dure. (a)
--Inner Cylinder Lug BoreHone1
As necessary to re-
move any cracks or
corrosion. Blend out
shallow surface irreg-
ularities and or shal-
low discrete pits less
than 0.005 inch in
depth. Refer to
SOPM 20-10-02 as
an accepted proce-
dure.
--Inner Cylinder Lug
Face
Repair2
Do a detailed inspec-
tion of the repaired
area for corrosion
and bronze transfer
using 10 power
magnification. Re-
peat repair proce-
dure beginning at
Step 1 if corrosion or
bronze transfer is
found.
--Inner Cylinder Bore and
Face
Inspect3
FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 2 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
50 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 51

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a penetrant in-
spection of the re-
paired areas for
cracks and corro-
sion. Refer to SOPM
20-20-02 as an ac-
cepted procedure.
Repeat repair proce-
dure beginning at
Step 1 if crack or
corrosion is found.
--Inner Cylinder Bore and
Face
Inspect4
Do a Magnetic Parti-
cle inspection of the
repaired areas for
cracks. Refer to
SOPM 20-20-01 as
an accepted proce-
dure. Repeat repair
procedure beginning
at Step 1 if crack is
found.
--Inner Cylinder Bore and
Face
Inspect5
Do a Local Etch of
Large Parts Inspec-
tion of the repaired
areas to detect heat
damage. Refer to
SOPM 20-10-02 as
an accepted proce-
dure. Make sure ad-
jacent areas are
protected where the
nital etch inspection
is not required. Re-
peat repair proce-
dure beginning at
Step 1 if heat dam-
age is found.
--Inner Cylinder Bore and
Face
Inspect6
Flapper peen the re-
paired areas. Refer
to SOPM 20-10-03
as an accepted pro-
cedure.
--Inner Cylinder Bore and
Face
Shot Peen7
Record the before
plating dimensions
to help size new
bushings.
--Inner Cylinder Bore and
Face
Measure8
FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 3 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
51 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 52

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Apply low hydrogen
embrittlement stylus
cadmium plating to
areas where cadmi-
um plating was re-
moved, except 72
square inch limit can
be exceeded for the
post bake require-
ment. Refer to
SOPM 20-42-10 as
an accepted proce-
dure.
--Low Hydrogen Embrit-
tlement Cadmium Plate
Apply9
to the entire bore
and in other areas
where primer was
removed. Refer to
CMM 32-11-03 Re-
pair 4-2 or CMM 32-
11-65 Repair 5-2 as
an accepted proce-
dure, as applicable.
-BMS 10-79, TYPE IIIPrimerApply10
at the lubrication fit-
tings until grease
appears in the
bores. If necessary,
clean the lubrication
passages. Remove
any excess grease.
-ROYCO 11MSGreaseApply11
Refer to CMM 32-
11-03 Repair 4-2 or
CMM 32-11-65 Re-
pair 5-2 as an ac-
cepted procedure,
as applicable.
-161W1122-3Inner Cylinder BushingMake12
Apply a thin layer to
the bores, chamfers
and faces of the in-
ner cylinder that will
contact the bush-
ings.
-BMS 5-95SealantApply13
FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 4 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
52 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 53

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to CMM 32-
11-03 Repair 4-1 or
CMM 32-11-65 Re-
pair 5-1 as an ac-
cepted procedure,
as applicable. Refer
to tool
MIT161W1122 in-
structions.
--Inner Cylinder BushingsInstall (New)14
at the lubrication fit-
tings until grease
appears in the
bores. Refer to CMM
32-11-03 Repair 4-1
or CMM 32-11-65
Repair 5-1 as an ac-
cepted procedure,
as applicable. (d)
-ROYCO 11MSGreaseApply15
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
--Inner Cylinder Lug
Face
Clean16
Fillet seal bushing
flange and shank
end. Refer to CMM
32-11-03 Repair 4-1
or CMM 32-11-65
Repair 5-1 as an ac-
cepted procedure,
as applicable.
-BMS 5-95SealantApply
as necessary to
meet the dimension-
al requirements. Re-
fer to CMM 32-11-03
Repair 4-1 or CMM
32-11-65 Repair 5-1,
as an accepted pro-
cedure as applica-
ble. Refer to tool
MIT161W1122 in-
structions. (b) (c)
--Inner Cylinder BushingsHone17
(a) Lug bores must be concentric within 0.0015 inches.
(b) Bushing bores must be concentric within 0.0005 inches.
(c) Final bushing bore diameters must be within 0.0015 inches of each other.
FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 5 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
53 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 54

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(d) Temporary plugging of through-wall holes is allowed to redirect grease to other through-wall holes.
FIGURE 7: LEFT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 6 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
54 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 777-32A0082
ALERT  ALERT
LEND
2 LOCATIONS (11 15
7  2 LOCATIONS
9) 10 13 14
2 LOCATIONS
(12 17) 2 LOCATIONS  1853456
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 MLG.
FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 1 OF 6)
Original Issue: December 09, 2010
BOEING PROPRIETARY -  777-32A0082
Copyright © Unpublished Work - See page 1 for details.  55 of 61

### Page 56

NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator
equivalent tools can be used.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
As necessary to re-
move any corrosion,
heat damage, cracks
or bronze transfer.
Maximum 0.020 inch
increase in the diam-
eter with a maximum
lug bore diameter of
7.1015 inches. Refer
to tool
MIT161W1122 in-
structions. Refer to
SOPM 20-10-02 as
an accepted proce-
dure. (a)
--Inner Cylinder Lug BoreHone1
As necessary to re-
move any cracks or
corrosion. Blend out
shallow surface irreg-
ularities and or shal-
low discrete pits less
than 0.005 inch in
depth. Refer to
SOPM 20-10-02 as
an accepted proce-
dure.
--Inner Cylinder Lug
Face
Repair2
Do a detailed inspec-
tion of the repaired
area for corrosion
and bronze transfer
using 10 power
magnification. Re-
peat repair proce-
dure beginning at
Step 1 if corrosion or
bronze transfer is
found.
--Inner Cylinder Bore and
Face
Inspect3
FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 2 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
56 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 57

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a penetrant in-
spection of the re-
paired areas for
cracks and corro-
sion. Refer to SOPM
20-20-02 as an ac-
cepted procedure.
Repeat repair proce-
dure beginning at
Step 1 if crack or
corrosion is found.
--Inner Cylinder Bore and
Face
Inspect4
Do a Magnetic Parti-
cle inspection of the
repaired areas for
cracks. Refer to
SOPM 20-20-01 as
an accepted proce-
dure. Repeat repair
procedure beginning
at Step 1 if crack is
found.
--Inner Cylinder Bore and
Face
Inspect5
Do a Local Etch of
Large Parts Inspec-
tion of the repaired
areas to detect heat
damage. Refer to
SOPM 20-10-02 as
an accepted proce-
dure. Make sure ad-
jacent areas are
protected where the
nital etch inspection
is not required. Re-
peat repair proce-
dure beginning at
Step 1 if heat dam-
age is found.
--Inner Cylinder Bore and
Face
Inspect6
Flapper peen the re-
paired areas. Refer
to SOPM 20-10-03
as an accepted pro-
cedure.
--Inner Cylinder Bore and
Face
Shot Peen7
Record the before
plating dimensions
to help size new
bushings.
--Inner Cylinder Bore and
Face
Measure8
FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 3 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
57 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 58

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Apply low hydrogen
embrittlement stylus
cadmium plating to
areas where cadmi-
um plating was re-
moved, except 72
square inch limit can
be exceeded for the
post bake require-
ment. Refer to
SOPM 20-42-10 as
an accepted proce-
dure.
--Low Hydrogen Embrit-
tlement Cadmium Plate
Apply9
to the entire bore
and in other areas
where primer was
removed. Refer to
CMM 32-11-03 Re-
pair 4-2 or CMM 32-
11-65 Repair 5-2 as
an accepted proce-
dure, as applicable.
-BMS 10-79, TYPE IIIPrimerApply10
at the lubrication fit-
tings until grease
appears in the
bores. If necessary,
clean the lubrication
passages. Remove
any excess grease.
-ROYCO 11MSGreaseApply11
Refer to CMM 32-
11-03 Repair 4-2 or
CMM 32-11-65 Re-
pair 5-2 as an ac-
cepted procedure,
as applicable.
-161W1122-3Inner Cylinder BushingMake12
Apply a thin layer to
the bores, chamfers
and faces of the in-
ner cylinder that will
contact the bush-
ings.
-BMS 5-95SealantApply13
FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 4 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
58 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 59

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to CMM 32-
11-03 Repair 4-1 or
CMM 32-11-65 Re-
pair 5-1 as an ac-
cepted procedure,
as applicable. Refer
to tool
MIT161W1122 in-
structions.
--Inner Cylinder BushingsInstall (New)14
at the lubrication fit-
tings until grease
appears in the
bores. Refer to CMM
32-11-03 Repair 4-1
or CMM 32-11-65
Repair 5-1 as an ac-
cepted procedure,
as applicable. (d)
-ROYCO 11MSGreaseApply15
Refer to SOPM 20-
30-03 as an accept-
ed procedure.
--Inner Cylinder Lug
Face
Clean16
Fillet seal bushing
flange and shank
end. Refer to CMM
32-11-03 Repair 4-1
or CMM 32-11-65
Repair 5-1 as an ac-
cepted procedure,
as applicable.
-BMS 5-95SealantApply
as necessary to
meet the dimension-
al requirements. Re-
fer to CMM 32-11-03
Repair 4-1 or CMM
32-11-65 Repair 5-1
as an accepted pro-
cedure, as applica-
ble. Refer to tool
MIT161W1122 in-
structions. (b) (c)
--Inner Cylinder BushingsHone17
(a) Lug bores must be concentric within 0.0015 inches.
(b) Bushing bores must be concentric within 0.0005 inches.
(c) Final bushing bore diameters must be within 0.0015 inches of each other.
FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 5 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
59 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

### Page 60

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(d) Temporary plugging of through-wall holes is allowed to redirect grease to other through-wall holes.
FIGURE 8: RIGHT MLG INNER CYLINDER LUG BORE REPAIR AND BUSHING REPLACEMENT
(SHEET 6 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 09, 2010
777-32A0082
60 of 61
BOEING SERVICE BULLETIN 777-32A0082
ALERTALERT

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