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

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ECCN: 9E991

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Unpublished Work - All Rights Reserved

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subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

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5.0
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BOEING SERVICE BULLETIN 777-32A0082

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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 23

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 27

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 1: LEFT MLG CENTER AXLE INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . 33

FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 3: LEFT MLG INNER CYLINDER BUSHING INSPECTION . . . . . . . . . . . . . . . . . . 37

FIGURE 4: RIGHT MLG INNER CYLINDER BUSHING INSPECTION . . . . . . . . . . . . . . . . . . 40

FIGURE 5: LEFT MLG INNER CYLINDER LUG BORE INSPECTION . . . . . . . . . . . . . . . . . . 43

FIGURE 6: RIGHT MLG INNER CYLINDER LUG BORE INSPECTION . . . . . . . . . . . . . . . . . 46

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 . . . . . . . . . . . . . 61

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BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

ALERT

Summary 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.

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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BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

1 - 777-200, -300 Airplanes line numbers 1 through 914.

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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GROUP CONFIGURATION DESCRIPTION

2 - 777-200LR, -300ER and 777F Airplanes line numbers 1 through 914.

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

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

WA101 - WA104 1

WA116 - WA119 1

WA131 - WA137 1

WA171 - WA175 1

WA196 - WA198 1

WA206 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

WA261 - WA266 1

WA281 - WA283 1

WA301 - WA304 1

WB001 - WB021 1

WB031 - WB046 1

WB051 - WB088 1

WB101 - WB106 1

WB121 - WB125 1

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ALERT ALERT
Variable Number Group

WB131 - WB148 1

WB151 - WB155 1

WB161 - WB177 1

WB181 - WB194 1

WB201 - WB215 1

WB231 - WB247 1

WB271 - WB273 1

WB276 - WB286 1

WB291 - WB302 1

WB306 - WB307 1

WB311 - WB337 1

WB341 - WB342 1

WB366 - WB368 1

WB371 - WB388 1

WB406 1

WB411 - WB413 1

WB416 - WB439 1

WB446 - WB453 1

WB476 1

WB481 - WB484 1

WB501 - WB512 1

WB531 - WB537 1

WB551 - WB554 1

WB591 - WB597 1

WB601 - WB606 1

WB611 - WB622 1

WB631 - WB638 1

WB646 - WB649 1

WC051 - WC073 1

WC101 - WC104 1

WC111 - WC120 1

WC221 - WC224 1

WC241 - WC243 1

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Variable Number Group

WC281 - WC290 1

WC301 - WC308 1

WC361 - WC364 1

WC371 - WC374 1

WC381 - WC395 1

WC441 1

WC446 - WC449 1

WC456 - WC459 1

WC486 - WC493 1

WC506 - WC508 1

WC521 - WC522 1

WC531 - WC536 1

WC546 - WC548 1

WC556 1

WC566 - WC567 1

WC571 - WC574 1

WC581 1

WD001 - WD002 2

WD011 - WD018 2

WD031 - WD036 2

WD046 - WD055 2

WD066 - WD075 2

WD081 - WD088 2

WD091 2

WD096 2

WD101 - WD103 2

WD501 - WD513 2

WD521 - WD541 2

WD546 - WD554 2

WD561 - WD573 2

WD581 - WD599 2

WD606 - WD609 2

WD621 - WD632 2

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Variable Number Group

WD651 - WD665 2

WD671 - WD676 2

WD691 - WD709 2

WD741 - WD752 2

WD761 - WD771 2

WD786 - WD788 2

WD796 - WD813 2

WD826 - WD837 2

WD846 - WD861 2

WD871 - WD883 2

WD911 - WD914 2

WD921 - WD922 2

WD936 - WD939 2

WD946 - WD951 2

WD966 - WD970 2

WD981 - WD982 2

WD986 - WD987 2

WD996 2

WE001 - WE004 2

WE011 - WE012 2

WE021 - WE024 2

WE031 2

WE051 - WE052 2

WE071 2

WE081 - WE082 2

WE126 - WE131 2

WF001 - WF004 2

WF016 - WF020 2

WF031 - WF032 2

WF046 - WF053 2

WF076 - WF077 2

WF081 - WF088 2

WF096 - WF099 2

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ALERT ALERT
Variable Number Group

WF106 - WF107 2

WF111 - WF112 2

WF121 2

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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BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
Group 1:

Affected Maintenance Zones

Model Zone

777-200, 777-300 731, 741

Group 2:

Affected Maintenance Zones

Model Zone

777-200LR, 777-300ER, 777F 731, 741

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)

Condition Action Compliance Time

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)

Condition Action

Within 1,125 3,750 Days

Days After the

Original Issue

Date of this Service Bulletin.

Before 1) or 2):

1) MLG has not

been overhauled: 2,250

Days After The

Date of Issuance of the

Original Certificate of Airworthiness or the

Original Export

Certificate of

Airworthiness.

Do Part 2 - MLG Pivot

Joint Inspection. (a) (b)

See Table 6 for disposition of conditions found.

All Airplanes

2) MLG has

been overhauled: 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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ALERT ALERT
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)

Condition Action

Within 375 Days 3,750 Days

After the Original Issue Date

of this Service

Bulletin.

Before 1) or 2):

1) MLG has not

been overhauled: 3,750

Days After The

Date of Issuance of the

Original Certificate of Airworthiness or the

Original Export

Certificate of

Airworthiness.

Do Part 2 - MLG Pivot

Joint Inspection. (a) (b)

See Table 6 for disposition of conditions found.

All Airplanes

2) MLG has

been overhauled: 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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BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
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)

Condition Action

Within 1,125 3,000 Days

Days After the

Original Issue

Date of this Service Bulletin.

Before 1) or 2):

1) MLG has not

been overhauled: 1,825

Days After The

Date of Issuance of the

Original Certificate of Airworthiness or the

Original Export

Certificate of

Airworthiness.

Do Part 2 - MLG Pivot

Joint Inspection. (a) (b)

See Table 6 for disposition of conditions found.

All Airplanes

2) MLG has

been overhauled: 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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BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
Group 2, Configuration 2:

Table 5: MLG Pivot Joint Inspection for 777-200LR, -300ER and 777F 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)

Condition Action

Within 300 Days 3,000 Days

After the Original Issue Date

of this Service

Bulletin.

Before 1) or 2):

1) MLG has not

been overhauled: 3,000

Days After The

Date of Issuance of the

Original Certificate of Airworthiness or the

Original Export

Certificate of

Airworthiness.

Do Part 2 - MLG Pivot

Joint Inspection. (a) (b)

See Table 6 for disposition of conditions found.

All Airplanes

2) MLG has

been overhauled: 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)

Condition Action Compliance Time

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)

Condition Action Compliance Time

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.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 2, Option 2.

-ANDBefore 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.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle in

accordance with Part 3,

Condition 3, Option 2.

-ANDBefore further - -

flight.

Do Part 5 - Inner Cylinder

Lug Bore Inspection.

No further action is re- - - -

quired for this inner cylinder location.

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.

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 restricted.

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ALERT ALERT
Table 6: Parts 2-5 Inspection Findings and Disposition

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

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 transfer is found in the inner

cylinder bore.

-ORRepair the inner cylinder

in accordance with Part

5, Condition 7, Option 2.

-ORReplace 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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Number of Per- Task Hours Elapsed Hours

sons

Task

Part 1 (a) 2 4.00 2.00

TOTAL FOR EACH 4.00 2.00

AIRPLANE

(a) Additional time may be required for cold weather lubrication. Refer to 777-SL12-006 for cold weather lubrication recommendations when temperatures are

below 0 degrees Celsius.

Number of Per- Task Hours Elapsed Hours

sons

Task

Part 2 6 54.00 9.00

Part 3: Figure 1 1 5.00 5.00

Part 3: Figure 2 1 5.00 5.00

Part 4: Figure 3 1 2.25 2.25

Part 4: Figure 4 1 2.25 2.25

Part 5: Figure 5 2 9.00 (a) 4.50 (a)

Part 5: Figure 6 2 9.00 (a) 4.50 (a)

Part 5: Figure 7 (b) (b)

Part 5: Figure 8 (b) (b)

TOTAL FOR EACH AIRPLANE 90.50 34.50

(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:

Drawing No Title Sheet DCN/REV ADCN

Misc Tool Replacement and Honing Kit In- 1 B -

ner Cyl Ctr Axle

MIT161W1122

2 - -

3 - -

3. Installation Drawings Used in the Preparation of this Service Bulletin

Drawing Number Title

161W0000 Installation - Main Landing Gear

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:

Publication Chapter-Section

Component Maintenance Manual 32-11

777 Maintenance Review Board Report Section 2, ATA 12

777 Maintenance Planning Data Document Section 1, ATA 12

777 Maintenance Manual 32-11

777 Illustrated Parts Catalog 32-11

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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ALERT ALERT
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 Bulletin (US Dollars)

ROLT as of

the original

issue date of

this Service

Bulletin (Calendar Days)

Part Number Name

161W1163-13 Center Axle Assy 623 $54,030.00

161W1163-15 Center Axle Assy 623 $54,030.00

161W1255-7 Inner Cylinder Assy 1624 $242,622.00

161W2120-3 Inner Cylinder Assy 1344 $254,847.00

161W1122-2 Bushing, Inner Cylinder 301 $2,928.00

161W1122-3 Bushing, Inner Cylinder 301 $3,526.00

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

Part Number / QTY Name Notes

Specification

Royco 11MS - Grease

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Part Number / QTY Name Notes

Specification

BMS 5-95 - Sealant (c)

BMS 10-79, Type - Primer (c)

III

BMS 3-23, Type II, - Corrosion Inhibiting Compound (c)

Class 1

BMS 3-26, Type I - Corrosion Inhibiting Compound (c) Optional.

BMS 3-32 - Shock Strut Fluid (c)

Refer to APPENDIX A for

part number applicability.

161W1163-1, -3, - 2 Center Axle Assy

5, -7, -11, -13, or15

Refer to APPENDIX A for

part number applicability.

161W1120-3, -5 2 Inner Cylinder Assy

Refer to APPENDIX A for

part number applicability.

161W1255-1, -5, - 2 Inner Cylinder Assy

7

Refer to APPENDIX A for

part number applicability.

161W2120-1, -3 2 Inner Cylinder Assy

161W1122-2 4 Bushing, Inner Cylinder (a)

161W1122-3 4 Bushing, Inner Cylinder Oversized part. (a) (b)

(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:

Tool Kit Number Name Unit Price

Contact Boeing

Spares for Current

Pricing Information

Misc Tool - Bushing Replacement 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.

Tool Kit Number Name

Misc Tool - Bushing Replacement and Honing Kit - Inner Cyl

Ctr Axle

MIT161W1122

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ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. 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:

LEFT MLG RIGHT MLG

FIGURE 1 FIGURE 2

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:

LEFT MLG RIGHT MLG

FIGURE 3 FIGURE 4

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:

LEFT MLG RIGHT MLG

FIGURE 5 FIGURE 6

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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LEFT MLG RIGHT MLG

FIGURE 7 FIGURE 8

(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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ALERT ALERT
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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SOPM 20-

30-03 as an accepted procedure.

1 Clean Center Axle - 1

Do a Detailed Inspection of the outer diameter chrome for

chicken wire cracks,

corrosion and

chrome plate distress. (a) (b) (c) (d)

2 Inspect Center Axle - 1

Do a Magnetic Particle Inspection of the

outer diameter

chrome for cracks in

the area common to

the inner cylinder

bushings plus a minimum of 2 inches on

both sides. Refer to

SOPM 20-20-01 as

an accepted procedure.

3 Inspect Center Axle - 1

FIGURE 1: LEFT MLG CENTER AXLE INSPECTION

(SHEET 1 OF 2)

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STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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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ALERT ALERT
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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SOPM 20-

30-03 as an accepted procedure.

1 Clean Center Axle - 1

Do a Detailed Inspection of the outer diameter chrome for

chicken wire cracks,

corrosion and

chrome plate distress. (a) (b) (c) (d)

2 Inspect Center Axle - 1

FIGURE 2: RIGHT MLG CENTER AXLE INSPECTION

(SHEET 1 OF 2)

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ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Magnetic Particle Inspection of the

outer diameter

chrome for cracks in

the area common to

the inner cylinder

bushings plus a minimum of 2 inches on

both sides. Refer to

SOPM 20-20-01 as

an accepted procedure.

3 Inspect Center Axle - 1

(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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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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STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean inner diameters, grease grooves

and around flange

area. Refer to

SOPM 20-30-03 as

an accepted procedure.

1 Clean Inner Cylinder Bushings - 2

Do a Detailed Inspection of the bushing

inner diameters and

flanges for cracks,

smearing of material

into the lubrication

grooves and bushing

distress. (a) (b) (e)

(f)

2 Inspect Inner Cylinder Bushings - 2

For wear limits. Refer to CMM 32-11-07

or CMM 32-11-64 as

an accepted procedure, as applicable.

3 Inspect Inner Cylinder Bushings - 2

Through the lube fittings to make sure

the grease flow is

not restricted.

Grease should appear through at least

two grease holes in

the bushing. (c) (d)

(g)

4 Apply Grease ROYCO 11MS -

Do a Detailed Inspection for corrosion. (h)Inner Cylinder Lug - 4

Face

5 Inspect

(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 nonmetallic 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 instructions. 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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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

ALERT ALERT
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)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 09, 2010

777-32A0082

40 of 61

BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean inner diameters, grease grooves

and around flange

area. Refer to

SOPM 20-30-03 as

an accepted procedure.

1 Clean Inner Cylinder Bushings - 2

Do a Detailed Inspection of the bushing

inner diameters and

flanges for cracks,

smearing of material

into the lubrication

grooves and bushing

distress. (a) (b) (e)

(f)

2 Inspect Inner Cylinder Bushings - 2

For wear limits. Refer to CMM 32-11-07

or CMM 32-11-64 as

an accepted procedure, as applicable.

3 Inspect Inner Cylinder Bushings - 2

Through the lube fittings to make sure

the grease flow is

not restricted.

Grease should appear through at least

two grease holes in

the bushing. (c) (d)

(g)

4 Apply Grease ROYCO 11MS -

Do a Detailed Inspection for corrosion. (h)Inner Cylinder Lug - 4

Face

5 Inspect

(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 nonmetallic 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 instructions. 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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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

ALERT ALERT
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)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 09, 2010

777-32A0082

43 of 61

BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to tool

MIT161W1122 instructions. (a)

1 Remove Inner Cylinder Bushings - 2

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Bore and - 2

Face

2 Clean

from lug bores and

faces common to the

bushing flange (unpainted surface).

Make sure primer

has been completely

removed. Refer to

SOPM 20-30-02 as

an accepted procedure.

3 Remove Primer - -

Do a Detailed Inspection of the lug bore

inner diameter for

cracks, corrosion or

bronze transfer and

the lug bore face for

cracks or corrosion.

Inner Cylinder Bore and - 2

Face

4 Inspect

Do a Penetrant Inspection for corrosion. Refer to SOPM

20-20-02 as an accepted procedure.

(c) (d)

Inner Cylinder Bore and - 2

Face

5 Inspect

Do a Magnetic Particle Inspection for

cracks. Refer to

SOPM 20-20-01 as

an accepted procedure. (d)

Inner Cylinder Bore and - 2

Face

6 Inspect

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(b) From the lug

bores and faces.

Remove the cadmium plate by manual

application of ammonium nitrate solution.

Refer to SOPM 20-

30-02 as an accepted procedure. Make

sure adjacent areas

are protected where

cadmium plating removal is not required. (d)

7 Remove Cadmium Plating - -

(b) Do a Local Etch

of Large Parts Inspection of the base

metal where the

cadmium plating

was removed to detect heat damage.

Refer to SOPM 20-

10-02 as an accepted procedure. Make

sure adjacent areas

are protected where

the nital etch inspection is not required.

Ammonium Persulfate method is not

allowed. (d)

8 Inspect Inner Cylinder Lug Bore - 2

(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 indications 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 restriction 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

ALERT ALERT
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)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 09, 2010

777-32A0082

46 of 61

BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to tool

MIT161W1122 instructions. (a)

1 Remove Inner Cylinder Bushings - 2

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Bore and - 2

Face

2 Clean

from lug bores and

faces common to

bushing flange (unpainted surface).

Make sure primer

has been completely

removed. Refer to

SOPM 20-30-02 as

an accepted procedure.

3 Remove Primer - -

Do a Detailed Inspection of the lug bore

inner diameter for

cracks, corrosion or

bronze transfer and

the lug bore face for

cracks or corrosion.

Inner Cylinder Bore and - 2

Face

4 Inspect

Do a Penetrant Inspection for corrosion. Refer to SOPM

20-20-02 as an accepted procedure.

(c) (d)

Inner Cylinder Bore and - 2

Face

5 Inspect

Do a Magnetic Particle Inspection for

cracks. Refer to

SOPM 20-20-01 as

an accepted procedure. (d)

Inner Cylinder Bore and - 2

Face

6 Inspect

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(b) From the lug

bores and faces.

Remove the cadmium plate by manual

application of ammonium nitrate solution.

Refer to SOPM 20-

30-02 as an accepted procedure. Make

sure adjacent areas

are protected where

cadmium plating removal is not required. (d)

7 Remove Cadmium Plating - -

(b) Do a Local Etch

of Large Parts Inspection of the base

metal where the

cadmium plating

was removed to detect heat damage.

Refer to SOPM 20-

10-02 as an accepted procedure. Make

sure adjacent areas

are protected where

the nital etch inspection is not required.

Ammonium Persulfate method is not

allowed. (d)

8 Inspect Inner Cylinder Lug Bore - 2

(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 indications 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 restriction 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

ALERT ALERT
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)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 09, 2010

777-32A0082

49 of 61

BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

As necessary to remove any corrosion,

heat damage, cracks

or bronze transfer.

Maximum 0.020 inch

increase in the diameter with a maximum

lug bore diameter of

7.1015 inches. Refer

to tool

MIT161W1122 instructions. Refer to

SOPM 20-10-02 as

an accepted procedure. (a)

1 Hone Inner Cylinder Lug Bore - -

As necessary to remove any cracks or

corrosion. Blend out

shallow surface irregularities and or shallow discrete pits less

than 0.005 inch in

depth. Refer to

SOPM 20-10-02 as

an accepted procedure.

Inner Cylinder Lug - -

Face

2 Repair

Do a detailed inspection of the repaired

area for corrosion

and bronze transfer

using 10 power

magnification. Repeat repair procedure beginning at

Step 1 if corrosion or

bronze transfer is

found.

Inner Cylinder Bore and - -

Face

3 Inspect

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a penetrant inspection of the repaired areas for

cracks and corrosion. Refer to SOPM

20-20-02 as an accepted procedure.

Repeat repair procedure beginning at

Step 1 if crack or

corrosion is found.

Inner Cylinder Bore and - -

Face

4 Inspect

Do a Magnetic Particle inspection of the

repaired areas for

cracks. Refer to

SOPM 20-20-01 as

an accepted procedure. Repeat repair

procedure beginning

at Step 1 if crack is

found.

Inner Cylinder Bore and - -

Face

5 Inspect

Do a Local Etch of

Large Parts Inspection of the repaired

areas to detect heat

damage. Refer to

SOPM 20-10-02 as

an accepted procedure. Make sure adjacent areas are

protected where the

nital etch inspection

is not required. Repeat repair procedure beginning at

Step 1 if heat damage is found.

Inner Cylinder Bore and - -

Face

6 Inspect

Flapper peen the repaired areas. Refer

to SOPM 20-10-03

as an accepted procedure.

Inner Cylinder Bore and - -

Face

7 Shot Peen

Record the before

plating dimensions

to help size new

bushings.

Inner Cylinder Bore and - -

Face

8 Measure

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply low hydrogen

embrittlement stylus

cadmium plating to

areas where cadmium plating was removed, except 72

square inch limit can

be exceeded for the

post bake requirement. Refer to

SOPM 20-42-10 as

an accepted procedure.

Low Hydrogen Embrit- - -

tlement Cadmium Plate

9 Apply

to the entire bore

and in other areas

where primer was

removed. Refer to

CMM 32-11-03 Repair 4-2 or CMM 32-

11-65 Repair 5-2 as

an accepted procedure, as applicable.

10 Apply Primer BMS 10-79, TYPE III -

at the lubrication fittings until grease

appears in the

bores. If necessary,

clean the lubrication

passages. Remove

any excess grease.

11 Apply Grease ROYCO 11MS -

Refer to CMM 32-

11-03 Repair 4-2 or

CMM 32-11-65 Repair 5-2 as an accepted procedure,

as applicable.

12 Make Inner Cylinder Bushing 161W1122-3 -

Apply a thin layer to

the bores, chamfers

and faces of the inner cylinder that will

contact the bushings.

13 Apply Sealant BMS 5-95 -

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to CMM 32-

11-03 Repair 4-1 or

CMM 32-11-65 Repair 5-1 as an accepted procedure,

as applicable. Refer

to tool

MIT161W1122 instructions.

14 Install (New) Inner Cylinder Bushings - -

at the lubrication fittings 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 accepted procedure,

as applicable. (d)

15 Apply Grease ROYCO 11MS -

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Lug - -

Face

16 Clean

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 accepted procedure,

as applicable.

Apply Sealant BMS 5-95 -

as necessary to

meet the dimensional requirements. Refer to CMM 32-11-03

Repair 4-1 or CMM

32-11-65 Repair 5-1,

as an accepted procedure as applicable. Refer to tool

MIT161W1122 instructions. (b) (c)

17 Hone Inner Cylinder Bushings - -

(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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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

ALERT ALERT
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)

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 09, 2010

777-32A0082

55 of 61

BOEING SERVICE BULLETIN 777-32A0082

ALERT ALERT
NOTE: Tool MIT161W1122 was developed to accomplish the repair procedures in this figure. Operator

equivalent tools can be used.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

As necessary to remove any corrosion,

heat damage, cracks

or bronze transfer.

Maximum 0.020 inch

increase in the diameter with a maximum

lug bore diameter of

7.1015 inches. Refer

to tool

MIT161W1122 instructions. Refer to

SOPM 20-10-02 as

an accepted procedure. (a)

1 Hone Inner Cylinder Lug Bore - -

As necessary to remove any cracks or

corrosion. Blend out

shallow surface irregularities and or shallow discrete pits less

than 0.005 inch in

depth. Refer to

SOPM 20-10-02 as

an accepted procedure.

Inner Cylinder Lug - -

Face

2 Repair

Do a detailed inspection of the repaired

area for corrosion

and bronze transfer

using 10 power

magnification. Repeat repair procedure beginning at

Step 1 if corrosion or

bronze transfer is

found.

Inner Cylinder Bore and - -

Face

3 Inspect

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a penetrant inspection of the repaired areas for

cracks and corrosion. Refer to SOPM

20-20-02 as an accepted procedure.

Repeat repair procedure beginning at

Step 1 if crack or

corrosion is found.

Inner Cylinder Bore and - -

Face

4 Inspect

Do a Magnetic Particle inspection of the

repaired areas for

cracks. Refer to

SOPM 20-20-01 as

an accepted procedure. Repeat repair

procedure beginning

at Step 1 if crack is

found.

Inner Cylinder Bore and - -

Face

5 Inspect

Do a Local Etch of

Large Parts Inspection of the repaired

areas to detect heat

damage. Refer to

SOPM 20-10-02 as

an accepted procedure. Make sure adjacent areas are

protected where the

nital etch inspection

is not required. Repeat repair procedure beginning at

Step 1 if heat damage is found.

Inner Cylinder Bore and - -

Face

6 Inspect

Flapper peen the repaired areas. Refer

to SOPM 20-10-03

as an accepted procedure.

Inner Cylinder Bore and - -

Face

7 Shot Peen

Record the before

plating dimensions

to help size new

bushings.

Inner Cylinder Bore and - -

Face

8 Measure

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply low hydrogen

embrittlement stylus

cadmium plating to

areas where cadmium plating was removed, except 72

square inch limit can

be exceeded for the

post bake requirement. Refer to

SOPM 20-42-10 as

an accepted procedure.

Low Hydrogen Embrit- - -

tlement Cadmium Plate

9 Apply

to the entire bore

and in other areas

where primer was

removed. Refer to

CMM 32-11-03 Repair 4-2 or CMM 32-

11-65 Repair 5-2 as

an accepted procedure, as applicable.

10 Apply Primer BMS 10-79, TYPE III -

at the lubrication fittings until grease

appears in the

bores. If necessary,

clean the lubrication

passages. Remove

any excess grease.

11 Apply Grease ROYCO 11MS -

Refer to CMM 32-

11-03 Repair 4-2 or

CMM 32-11-65 Repair 5-2 as an accepted procedure,

as applicable.

12 Make Inner Cylinder Bushing 161W1122-3 -

Apply a thin layer to

the bores, chamfers

and faces of the inner cylinder that will

contact the bushings.

13 Apply Sealant BMS 5-95 -

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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to CMM 32-

11-03 Repair 4-1 or

CMM 32-11-65 Repair 5-1 as an accepted procedure,

as applicable. Refer

to tool

MIT161W1122 instructions.

14 Install (New) Inner Cylinder Bushings - -

at the lubrication fittings 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 accepted procedure,

as applicable. (d)

15 Apply Grease ROYCO 11MS -

Refer to SOPM 20-

30-03 as an accepted procedure.

Inner Cylinder Lug - -

Face

16 Clean

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 accepted procedure,

as applicable.

Apply Sealant BMS 5-95 -

as necessary to

meet the dimensional requirements. Refer to CMM 32-11-03

Repair 4-1 or CMM

32-11-65 Repair 5-1

as an accepted procedure, as applicable. Refer to tool

MIT161W1122 instructions. (b) (c)

17 Hone Inner Cylinder Bushings - -

(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

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(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

ALERT ALERT
Applicable Inner Cylinder

Assemblies (a)

Applicable Center Axle

Assemblies (a)

Maximum Taxi Gross

Weight

Airplane Model

161W1163-1, -3, -5, -7, -9, 161W1120-3, -5

-11, -13, -15

777-200 547,000 lbs

161W1255-1, -5, -7

161W1163-1, -3, -5, -7, -9, 161W1255-1, -5, -7

-11, -13, -15

777-200ER 652,000 lbs

161W1163-3, -7, -9, -13, - 161W1255-7

15

777-200ER/IGW 658,000 lbs

161W1163-3, -7, -9, -13, - 161W1255-7

15

777-300 662,000 lbs

777-200LR 768,800 lbs 161W1163-9, -15 161W2120-1, -3

777-300ER 777,000 lbs 161W1163-9, -15 161W2120-1, -3

777F 768,800 lbs 161W1163-9, -15 161W2120-1, -3

(a) Refer to 777-SL-32-001 for additional interchangeability information.

APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT

INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: December 09, 2010

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