Commercial 

Airplane

Group 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0080

Date: July 10, 2008

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.

ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2008 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Unpublished Work - All Rights Reserved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, MD-10, MD-11, MD-80, MD-88, MD-90, 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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3.0
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BOEING SERVICE BULLETIN 777-32-0080

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 19

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 22

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 22

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE 1: INSPECTION OF THE LEFT MLG PIVOT JOINT . . . . . . . . . . . . . . . . . . . . . . 26

FIGURE 2: INSPECTION OF THE RIGHT MLG PIVOT JOINT . . . . . . . . . . . . . . . . . . . . . . 29

APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT

INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL . . . . . . . . . . . . . 32

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BOEING SERVICE BULLETIN 777-32-0080
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BOEING SERVICE BULLETIN 777-32-0080

BLANK PAGE
Commercial 

Airplane

Group 777

Service Bulletin

SPECIAL ATTENTION

Summary Number: 777-32-0080

Date: July 10, 2008

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder

Pivot Joint - Lubrication and Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

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 airplanes that visit Short

Wavelength Roughness (SWR) Level 2 runways. Airplanes that visit SWR Level 2 runways 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 partial collapse of a MLG and loss of control during ground operations.

The type of runway surface roughness that causes damage to the MLG pivot joint is described by a factor called

SWR. SWR Level 1 airports are airports outside of the Commonwealth of Independent States (CIS) and specified

airports within the CIS for which data has shown acceptable pivot joint response. SWR Level 2 airports are all

other airports within the CIS that are not identified as SWR Level 1. CIS means the following countries: Armenia,

Azerbaijan, Belarus, Georgia, Kazakhstan, Kyrgyzstan, Moldova, Russia, Tajikistan, Turkmenistan, Ukraine,

and Uzbekistan. Refer to Boeing Service Letter 777-SL-32-058 for an active list of SWR Level 1 and SWR Level

2 runways.

SWR Level 2 runways have caused fractures of MLG pivot joint components of 757 and 767 airplanes. One 757

airplane experienced fractures in both MLG bogie beams at the same landing. That airplane had accumulated

4,952 flight hours and 1,055 flight cycles. One 767 MLG bogie beam fracture occurred as the airplane was

making a U-turn at the end of the runway, before takeoff. All three bogie beams fractured at the pivot joint, which

caused the inner cylinder to contact the ground.

This service bulletin provides the instructions for increased lubrication, inspection and repair of the MLG pivot

joint components on airplanes that visit SWR Level 2 runways. 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-32-0145 is related to this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.

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ACTION

Group 1, Configuration 1:

No action required by this service bulletin.

Group 1, Configuration 2-3:

Get access to the left and right MLG wheel wells. Lubricate the pivot joint of both MLGs. Remove the landing

gear trucks, center axles and inner cylinder lugs bushings of both MLGs. Do a detailed, magnetic particle and

nital etch inspection of the MLG pivot joints, including the center axle and inner cylinder lug bores. If no damage

is found, repeat the inspection. If damage is found, repair or replace the damaged parts. Install new bushings

in the inner cylinder lug bores.

EFFECTIVITY

All 777-200, 777-200LR, 777-300, 777-300ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of

affected airplanes.

COMPLIANCE

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.

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 777-32-0080
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BOEING SERVICE BULLETIN 777-32-0080
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BOEING SERVICE BULLETIN 777-32-0080

BLANK PAGE
Commercial 

Airplane

Group 777

Service Bulletin

SPECIAL ATTENTION

Number: 777-32-0080

Date: July 10, 2008

ATA System: 3211

SUBJECT: LANDING GEAR - Main Landing Gear - Shock Strut and Center Axle Inner Cylinder

Pivot Joint - Lubrication and Inspection

BOEING RECOMMENDS THAT EACH OPERATOR EXAMINE THIS SERVICE BULLETIN IMMEDIATELY.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line

Number, and Serial Number data.

NOTE: This Service Bulletin is for the airplanes identified below. The Effectivity list shown below

is complete for airplanes through line number 769. Airplanes after line number 769 are

also affected by this service bulletin, and are in Group(s): 1

GROUP CONFIGURATION DESCRIPTION

1 - All 777-200, 777-200LR, 777-300, 777-300ER Airplanes.

1 Airplanes that have never visited an SWR Level 2 airport.

Airplanes that do pivot joint lubrication before and after every visit to

an SWR Level 2 airport.

2

Airplanes that do not do pivot joint lubrication before and after every

visit to an SWR Level 2 airport.

3

Airplane Models:

777-200, 777-200LR, 777-300, 777-300ER

Variable Number Group

WA001 - WA017 1

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Variable Number Group

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

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

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BOEING SERVICE BULLETIN 777-32-0080
Variable Number Group

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 - WC222 1

WC241 - WC243 1

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

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BOEING SERVICE BULLETIN 777-32-0080
Variable Number Group

WC566 - WC567 1

WD001 - WD002 1

WD011 - WD015 1

WD031 - WD036 1

WD046 - WD054 1

WD066 - WD068 1

WD081 - WD082 1

WD501 - WD510 1

WD521 - WD539 1

WD546 - WD552 1

WD561 - WD573 1

WD581 - WD599 1

WD606 - WD609 1

WD621 - WD632 1

WD651 - WD662 1

WD671 - WD675 1

WD691 - WD709 1

WD741 - WD751 1

WD761 - WD770 1

WD786 - WD788 1

WD796 - WD805 1

WD826 - WD830 1

WD846 - WD852 1

WD871 - WD876 1

WD911 - WD912 1

WD936 - WD939 1

WD966 - WD968 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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BOEING SERVICE BULLETIN 777-32-0080
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 airplanes

that visit Short Wavelength Roughness (SWR) Level 2 runways. Airplanes that visit SWR Level 2

runways 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 partial collapse of a MLG and loss of

control during ground operations.

The type of runway surface roughness that causes damage to the MLG pivot joint is described by a

factor called SWR. SWR Level 1 airports are airports outside of the Commonwealth of Independent

States (CIS) and specified airports within the CIS for which data has shown acceptable pivot joint

response. SWR Level 2 airports are all other airports within the CIS that are not identified as SWR

Level 1. CIS means the following countries: Armenia, Azerbaijan, Belarus, Georgia, Kazakhstan,

Kyrgyzstan, Moldova, Russia, Tajikistan, Turkmenistan, Ukraine, and Uzbekistan. Refer to Boeing

Service Letter 777-SL-32-058 for an active list of SWR Level 1 and SWR Level 2 runways.

SWR Level 2 runways have caused fractures of MLG pivot joint components of 757 and 767 airplanes.

One 757 airplane experienced fractures in both MLG bogie beams at the same landing. That airplane

had accumulated 4,952 flight hours and 1,055 flight cycles. One 767 MLG bogie beam fracture occurred

as the airplane was making a U-turn at the end of the runway, before takeoff. All three bogie beams

fractured at the pivot joint, which caused the inner cylinder to contact the ground.

This service bulletin provides the instructions for increased lubrication, inspection and repair of the

MLG pivot joint components on airplanes that visit SWR Level 2 runways. 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-32-0145 is related to this service bulletin.

D. Description

Group 1, Configuration 1:

No action required.

Group 1, Configuration 2-3:

Get access to the left and right MLG wheel wells. Lubricate the pivot joint of both MLGs. Remove the

landing gear trucks, center axles and inner cylinder lugs bushings of both MLGs. Do a detailed, magnetic

particle and nital etch inspection of the MLG pivot joints, including the center axle and inner cylinder

lug bores. If no damage is found, repeat the inspection. If damage is found, repair or replace the

damaged parts. Install new bushings in the inner cylinder lug bores.

The work in this service bulletin is done in the maintenance zone(s) given below.

Affected Maintenance Zones

Model Zone

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

777-300ER

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BOEING SERVICE BULLETIN 777-32-0080
E. Compliance

NOTE: For the following tables, a SWR Level 2 runway visit is defined as one landing at an SWR Level

2 runway followed by one takeoff from an SWR Level 2 runway.

Group 1, Configuration 1:

Table 1: Airplanes That Have Never Visited a SWR Level 2 Runway

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

No action required by this - -

service bulletin.

All Airplanes

Group 1, Configuration 2:

Table 2: Airplanes That Do Pivot Joint Lubrication Before and After Every Visit to a SWR Level 2 Runway

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Immediately before

and after each

SWR Level 2

Runway Visit. (b)

Within 30 Days -

After the Date

on this Service

Bulletin

Do Part 1 - MLG Pivot

Joint Lubrication (c)

All Airplanes (a)

-ANDEvery 800 SWR

Level 2 Runways

Visits

Within 12

months After the

Date on this

Service Bulletin.

Before 800

Total SWR

Level 2 Runway

Visits

Do Part 2 - MLG Pivot

Joint Inspection (c)

-OR-

-OR- Within 48 months

of next SWR Level

2 Runway Visit,

whichever is first.

(a)

Within 48

Months of the

First SWR Level

2 Runway Visit,

whichever is

first

Before further - -

flight.

Remove the inner

cylinder and repair the

inner cylinder lug bores

as given in Paragraph

3.B., Work Instructions

Part 2, Paragraph 5.a.1.

Condition 1: inner cylinder

lug bores are damaged

within the repair limits as

given in Paragraph 3.B.,

Work Instructions Part 2,

Paragraph 5.a.

-ORReplace the inner

cylinder with a new,

overhauled or serviceable

inner cylinder as given in

Paragraph 3.B., Work

Instructions Part 2,

Paragraph 5.a.2.

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BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 2:

Table 2: Airplanes That Do Pivot Joint Lubrication Before and After Every Visit to a SWR Level 2 Runway

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Before further - -

flight.

Replace the inner

cylinder with a new,

overhauled or serviceable

inner cylinder as given in

Paragraph 3.B., Work

Instructions Part 2,

Paragraph 5.b.1.

Condition 2: inner cylinder

lug bores are damaged

more than the repair limits

as given in Paragraph 3.B.,

Work Instructions Part 2,

Paragraph 5.b.

Before further - -

flight.

No repair required.

Replace the finish on the

inner cylinder lug bores

as given in Paragraph

3.B., Work Instructions

Part 2, Paragraph 5.c.1.

Condition 3: No damage to

inner cylinder lug bores.

Before further - -

flight.

Repair the center axle as

given in Paragraph 3.B.,

Work Instructions Part

2,Paragraph 5.d.1.

Condition 4: Center axle is

damaged within the repair

limits as given in

Paragraph 3.B., Work

Instructions Part

2,Paragraph 5.d.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle

as given in Paragraph

3.B., Work Instructions

Part 2,Paragraph 5.d.2.

Before further - -

flight.

Replace the center axle

with a new, overhauled or

serviceable center axle

as given in Paragraph

3.B., Work Instructions

Part 2,Paragraph 5.e.1.

Condition 5: Center axle is

damaged more than the

repair limits as given in

Paragraph 3.B., Work

Instructions Part

2,Paragraph 5.e.

Condition 6: No damage to No repair required. - - -

center axle.

(a) If no visits to an SWR Level 2 runway have taken place since the last inspection as given in this service

bulletin, or since last MLG overhaul, then no action is required until the first SWR Level 2 runway visit

occurs.

(b) Refer to 777 MPD Item 12-080-00 for additional routine lubrication requirements.

(c) As given in Paragraph 3.B., Work Instructions.

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BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 3:

Table 3: Airplanes That Do Not Do Pivot Joint Lubrication Before and After Every Visit to a SWR Level

2 Runway

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Every 20 flight

cycles. (b)

Within 30 Days -

After the Date

on the Service

Bulletin

Do Part 1 - MLG Pivot

Joint Lubrication (c)

All Airplanes (a)

-ANDEvery 500 SWR

Level 2 Runway

Visits

Within 12

months After the

Date on this

Service Bulletin.

Before 500

Total SWR

Runway Level 2

Visits

Do Part 2 - MLG Pivot

Joint Inspection (c)

-OR-

-OR- Within 18 months

of next SWR Level

2 Runway Visit,

whichever is first.

(a)

Within 18

Months of the

First SWR Level

2 Runway Visit,

whichever is

first.

Before further - -

flight.

Remove the inner

cylinder and repair the

inner cylinder lug bores

as given in Paragraph

3.B., Work Instructions

Part 2, Paragraph 5.a.1.

Condition 1: inner cylinder

lug bores are damaged

within the repair limits as

given in Paragraph 3.B.,

Work Instructions Part 2,

Paragraph 5.a.

-ORReplace the inner

cylinder with a new,

overhauled or serviceable

inner cylinder as given in

Paragraph 3.B., Work

Instructions Part 2,

Paragraph 5.a.2.

Before further - -

flight.

Replace the inner

cylinder with a new,

overhauled or serviceable

inner cylinder as given in

Paragraph 3.B., Work

Instructions Part 2,

Paragraph 5.b.1.

Condition 2: inner cylinder

lug bores are damaged

more than the repair limits

as given in Paragraph 3.B.,

Work Instructions Part 2,

Paragraph 5.b.

No repair required. - - -

Replace the finish on the

inner cylinder lug bores

as given in Paragraph

3.B., Work Instructions

Part 2, Paragraph 5.c.1.

Condition 3: No damage to

inner cylinder lug bores.

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BOEING SERVICE BULLETIN 777-32-0080
Group 1, Configuration 3:

Table 3: Airplanes That Do Not Do Pivot Joint Lubrication Before and After Every Visit to a SWR Level

2 Runway

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs First)

Condition Action

Before further - -

flight.

Repair the center axle as

given in Paragraph 3.B.,

Work Instructions Part

2,Paragraph 5.d.1.

Condition 4: Center axle is

damaged within the repair

limits as given in

Paragraph 3.B., Work

Instructions Part

2,Paragraph 5.d.

-ORReplace the center axle

with a new, overhauled or

serviceable center axle

as given in Paragraph

3.B., Work Instructions

Part 2,Paragraph 5.d.2.

Before further - -

flight.

Replace the center axle

with a new, overhauled or

serviceable center axle

as given in Paragraph

3.B., Work Instructions

Part 2,Paragraph 5.e.1.

Condition 5: Center axle is

damaged more than the

repair limits as given in

Paragraph 3.B., Work

Instructions Part

2,Paragraph 5.e.

Condition 6: No damage to No repair required. - - -

center axle.

(a) If no visits to an SWR Level 2 runway have taken place since the last inspection as given in this service

bulletin, or since last MLG overhaul, then no action is required until the first SWR Level 2 runway visit

occurs.

(b) This repeat interval satisfies 777 MPD Item 12-080-00 routine lubrication requirements.

(c) As given in Paragraph 3.B., Work Instructions.

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.

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BOEING SERVICE BULLETIN 777-32-0080
G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection and possible

repair 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.

Number of Task Hours Elapsed Hours

Persons

Task

Part 1 2 4.00 2.00

Part 2: Figure 1 6 42.00 7.00

Part 2: Figure 2 6 42.00 7.00

TOTAL FOR EACH AIRPLANE 88.00 (a) 16.00 (a)

(a) Estimate does not include repairs. Should any repairs be required, more time

may be necessary.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Boeing Service Letter 777-SL-32-058

b. Boeing Service Related Problem (SRP) 777-SRP-32-0145

c. Component Maintenance Manual (CMM) 32-00-07, 32-11-03, 32-11-07, 32-11-65

d. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-20-01, 20-20-02

e. 777 Aircraft Maintenance Manual (AMM) 12-21-14, 32-00-15, 32-00-30, 32-11-04, 32-11-18,

32-11-26

f. 777 Maintenance Planning Data (MPD) Item 12-080-00

g. 777 Non-Destructive Testing (NDT) Manual Part 6, 51-00-04

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BOEING SERVICE BULLETIN 777-32-0080
2. Data supplied with this Service Bulletin

None.

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

None.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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BOEING SERVICE BULLETIN 777-32-0080

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the parts shown in Paragraph 2.C., Parts Necessary for Each Airplane as shown

below. Parts availability is shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date

Boeing gets the purchase order.

Unit Price thru

December 31, 2008

ROLT

(Weeks)

Part Number Name

161W1163-13 (a) Center Axle Assy 94 $45,806.00

161W1163-15 (a) Center Axle Assy 91 $46,902.00

161W1255-7 Inner Cylinder Assy 140 $206,795.00

161W2120-3 Inner Cylinder Assy 89 $233,801.00

161W1122-2 Bushing, Inner Cylinder 40 $2,686.00

(a) For alternate part numbers that can be used, refer to APPENDIX A.

The parts are subject to the terms and conditions of the Boeing standard purchase order

acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United

States dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that

follow:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

3. Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes inspection, and/or repair

procedures given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

None.

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BOEING SERVICE BULLETIN 777-32-0080
2. Parts and Materials Supplied by the Operator

Part Number / QTY Name Notes

Specification

Royco 11MS - Grease

BMS 5-95 - Sealant

BMS 10-79 Type III - Primer

Refer to APPENDIX A for

part number applicability.

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

-5, -7, -11, -13, or

-15

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, -7 2 Inner Cylinder Assy

Refer to APPENDIX A for

part number applicability.

161W2120-1, -3 2 Inner Cylinder Assy

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

(a) This part can be fabricated as given in CMM 32-11-03 or CMM 32-11-65, as applicable.

Oversized bushings can also be fabricated.

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

None.

F. Special Tooling Necessary to do this Service Bulletin

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

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

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

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BOEING SERVICE BULLETIN 777-32-0080
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. For approved fastener and process material substitutions, refer to 777 SRM, Chapter

51. Alternate fasteners are given 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 "as

given in" are included in the instruction, the procedure in the Boeing document must

be used.

B. WORK INSTRUCTIONS

Group 1, Configuration 1:

1. No action required by this service bulletin.

Group 1, Configuration 2-3:

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.

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BOEING SERVICE BULLETIN 777-32-0080
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.

Group 1, Configuration 2-3:

Part 2 - Main Landing Gear Pivot Joint Inspection

1. Install the MLG and 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 trucks. Refer to 777 AMM 32-11-18 as an accepted procedure.

4. Remove the bushings from the inner cylinder lugs and discard. Refer to CMM 32-11-03 or CMM

32-11-65 as accepted procedures, as applicable.

5. Inspect the center axle and inner cylinder lug bores of the left MLG as given in FIGURE 1 and the

right MLG as given in FIGURE 2.

a. Condition 1: inner cylinder lug bores are damaged within the repair limits as given in CMM

32-11-03 or CMM 32-11-65, as applicable.

(1) Option 1: Remove the inner cylinder. Refer to 777 AMM 32-11-04 as an accepted

procedure. Repair the inner cylinder lug bores as given in CMM 32-11-03 Repair 4-2 or

CMM 32-11-65 Repair 5-2, as applicable.

(2) Option 2: Replace the inner cylinder with a new, overhauled or serviceable inner cylinder.

Refer to 777 AMM 32-11-04 as an accepted procedure.

b. Condition 2: inner cylinder lug bores are damaged more than the repair limits as given in CMM

32-11-03 or CMM 32-11-65, as applicable.

(1) Replace the inner cylinder with a new, overhauled or serviceable inner cylinder. Refer to

777 AMM 32-11-04 as an accepted procedure.

c. Condition 3: No damage to inner cylinder lug bores.

(1) No repair required. Replace the finish on the inner cylinder lug bores as given in CMM

32-11-03 Repair 4-2 or CMM 32-11-65 Repair 5-2, as applicable.

d. Condition 4: Center axle is damaged within the repair limits as given in CMM 32-11-07.

(1) Option 1: Repair the center axle as given in CMM 32-11-07 Repair 7-2.

(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 interchangeability based on airplane type.

e. Condition 5: Center axle is damaged more than the repair limits as given in CMM 32-11-07.

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BOEING SERVICE BULLETIN 777-32-0080
(1) 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

interchangeability based on airplane type.

f. Condition 6: No damage to center axle.

(1) No repair required.

6. Install new inner cylinder bushings. Refer to CMM 32-11-03 or CMM 32-11-65 as accepted

procedures, as applicable.

7. Install the left and right MLG trucks. Refer to 777 AMM 32-11-18 as an accepted procedure.

8. Remove the MLG and NLG door safety pins. Refer to 777 AMM 32-00-15 as an accepted procedure.

9. Remove the MLG and NLG downlock pins. Refer to 777 AMM 32-00-30 as an accepted procedure.

10. Put the airplane back into serviceable condition.

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BOEING SERVICE BULLETIN 777-32-0080
FIGURE 1: INSPECTION OF THE LEFT MLG PIVOT JOINT

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed

Inspection of the

outer diameter for

evidence of bronze

transfer, corrosion

and damage to the

chrome plate. (a)

1 Inspect Center Axle - -

outer diameter for

cracks with a

Magnetic Particle

Inspection as given

in SOPM 20-20-01.

Inspect Center Axle - -

FIGURE 1: INSPECTION OF THE LEFT MLG PIVOT JOINT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed

Inspection for

corrosion, bronze

transfer or other

damage.

Inner Cylinder Lug - -

Bores

2 Inspect

If any damage,

corrosion, or bronze

transfer is found on

the bore, remove the

cadmium plate from

the area where

damage, corrosion,

or bronze transfer

was found. Remove

the cadmium plate

by manual

application of

ammonium nitrate

solution.

Remove Cadmium plating - -

Do a Nital Etch

Inspection of the

base metal to detect

heat damage as

given in SOPM

20-10-02.

Inner Cylinder Lug - -

Bores

Inspect

for cracks with either

a Penetrant

Inspection as given

in SOPM 20-20-02,

an Eddy Current

Inspection as given

in 777 NDT Part 6,

51-00-04 or a

Magnetic Particle

Inspection as given

in SOPM 20-20-01.

Inner Cylinder Lug - -

Bores

Inspect

(a) Refer to CMM 32-00-07 for information about damage identification.

FIGURE 1: INSPECTION OF THE LEFT MLG PIVOT JOINT

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
FIGURE 2: INSPECTION OF THE RIGHT MLG PIVOT JOINT

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed

Inspection of the

outer diameter for

evidence of bronze

transfer, corrosion

and damage to the

chrome plate. (a)

1 Inspect Center Axle - -

outer diameter for

cracks with a

Magnetic Particle

Inspection as given

in SOPM 20-20-01.

Inspect Center Axle - -

FIGURE 2: INSPECTION OF THE RIGHT MLG PIVOT JOINT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed

Inspection for

corrosion, bronze

transfer or other

damage.

Inner Cylinder Lug - -

Bores

2 Inspect

If any damage,

corrosion, or bronze

transfer is found on

the bore, remove the

cadmium plate from

the area where

damage, corrosion,

or bronze transfer

was found. Remove

the cadmium plate

by manual

application of

ammonium nitrate

solution.

Remove Cadmium plating - -

Do a Nital Etch

Inspection of the

base metal to detect

heat damage as

given in SOPM

20-10-02.

Inner Cylinder Lug - -

Bores

Inspect

for cracks with either

a Penetrant

Inspection as given

in SOPM 20-20-02,

an Eddy Current

Inspection as given

in777 NDT Part 6,

51-00-04 or a

Magnetic Particle

Inspection as given

in SOPM 20-20-01.

Inner Cylinder Lug - -

Bores

Inspect

(a) Refer to CMM 32-00-07 for information about damage identification.

FIGURE 2: INSPECTION OF THE RIGHT MLG PIVOT JOINT

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-32-0080
Applicable Inner Cylinder

Assemblies

Applicable Center Axle

Assemblies

Maximum Taxi

Gross Weight

Airplane

Model

777-200 547,000 lbs 161W1163-1, -3, -5, -7, -11, -13 161W1120-3, -5

161W1255-1, -5, -7

777-200ER 652,000 lbs 161W1163-1, -3, -5, -7, -11, -13 161W1255-1, -5, -7

777-200ER/IGW 658,000 lbs 161W1163-3, -7, -13 161W1255-7

777-300 662,000 lbs 161W1163-3, -7, -13 161W1255-7

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

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

APPENDIX A: CENTER AXLE ASSEMBLY AND INNER CYLINDER ASSEMBLY REPLACEMENT

INTERCHANGEABILITY BASED ON AIRPLANE MINOR MODEL

(SHEET 1 OF 1)

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