Commercial 

Airplanes 777

Service Bulletin

ALERT

Number: 777-55A0017

Original Issue: May 20, 2010

ATA System: 5518 2741

SUBJECT: STABILIZERS - Horizontal Stabilizer - Horizontal Stabilizer Jackscrew Fitting - Karon

Lined Bushing Inspection and Replacement

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

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Copyright © 2010 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable

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

This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

Treatment of the document and the information it contains is governed by contract with Boeing. For more

information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

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4.0
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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT

BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

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

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

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

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 20

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

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

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

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

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

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 23

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

FIGURE 1: INSPECTION AND MEASUREMENT OF BULKHEAD SUPPORT JACKSCREW FITTING

KARON LINED BUSHINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 2: INSPECTION AND MEASUREMENT OF HORIZONTAL STABILIZER JACKSCREW FITTING

KARON LINED BUSHINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

FIGURE 3: INSPECTION AND MEASUREMENT OF UPPER GIMBAL - BRAKE HOUSING AND UPPER

GIMBAL - BULKHEAD SUPPORT KARON LINED BUSHINGS . . . . . . . . . . . . . . . 35

FIGURE 4: INSPECTION AND MEASUREMENT OF TRIM ACTUATOR PRIMARY BRAKE HOUSING

KARON LINED BUSHINGS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

FIGURE 5: INSPECTION AND MEASUREMENT OF LOWER GIMBAL KARON LINED BUSHINGS . 39

FIGURE 6: INSPECTION AND MEASUREMENT OF PINS . . . . . . . . . . . . . . . . . . . . . . . 41

FIGURE 7: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING REMOVAL . . 43

FIGURE 8: BULKHEAD SUPPORT JACKSCREW FITTING INTERMEDIATE SLEEVE REPLACEMENT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 9: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING INSTALLATION

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

FIGURE 10: KARON LINED BUSHING SERVICE WEAR LIMITS . . . . . . . . . . . . . . . . . . . . . 55

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Commercial 

Airplanes 777

Service Bulletin

ALERT

Summary Number: 777-55A0017

Original Issue: May 20, 2010

ATA System: 5518 2741

SUBJECT: STABILIZERS - Horizontal Stabilizer - Horizontal Stabilizer Jackscrew Fitting - Karon

Lined Bushing Inspection and Replacement

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 work given in this service bulletin will find damage to Karon lined bushings and pins in the

HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) and HSTA attachment locations on the airplane structure.

There are twenty-four (24) Karon lined bushings and six (6) pins in the fuselage, horizontal stabilizer, HSTA

upper and lower gimbals, and HSTA primary brake housing. If the Karon liners in the bushings are damaged,

this may cause the Karon liners to completely disbond from the bushings. The completely disbonded Karon

liners may migrate out of the joint causing excessive joint clearance. A joint with excessive clearance would

result in fatigue cracking of the pins. The fatigue cracking of the pins in the HSTA and HSTA attachment locations

on the airplane structure can compromise the structural integrity of the joints resulting in loss of controllability

of the airplane.

The 24 Karon lined bushings are installed in the following joint locations: BULKHEAD SUPPORT JACKSCREW

FITTING, HORIZONTAL STABILIZER JACKSCREW FITTING, UPPER GIMBAL - BRAKE HOUSING, UPPER

GIMBAL - BULKHEAD SUPPORT, TRIM ACTUATOR PRIMARY BRAKE HOUSING, AND LOWER GIMBAL.

The bore of the bushings is lined with Karon, a material that is intended to reduce friction and resist wear.

Research tests have shown that Karon liners would not wear in service; therefore, lubrication and inspection of

these would not be necessary.

During a scheduled inspection of the HSTA components for 777-200, one operator found a Karon lined bushing

in the HORIZONTAL STABILIZER JACKSCREW FITTING with Karon liner broken into five pieces. The broken

Karon liner had worn and disbonded from the bushing. The broken Karon liner of the bushing was found on an

airplane that had accumulated 35,145 flight hours and 5,335 fight cycles.

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Boeing analysis shows that the broken Karon lined bushing was one of the 149 bushings that used an early

manufacturing process, which has since been improved. However, further investigation and analysis by Boeing

show that Karon lined bushings in the HSTA and HSTA attachment locations on the airplane structure using

both the early and the improved process could wear in service. The analysis also shows that the wear of the

Karon liner may cause excessive joint clearance, which could lead to fatigue cracking of the pins.

Accomplishment of the inspection in this service bulletin will find any disbond, tear, or wear in the 24 Karon lined

bushings; any gouge, crack, or wear in the 6 pins; and any gouge or crack in the fail-safe components in the

HSTA and HSTA attachment locations on the airplane structure. The inspection will make sure that Karon lined

bushings and pins are returned to the design standard.

Boeing Service Related Problem (SRP) 777-SRP-55-0042 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) article 777 FTD 55-07001

ACTION

Airplane Work

1. Remove hydraulic pressure, hydraulic power, and install safety tags to the HORIZONTAL STABILIZER

TRIM ACTUATOR (HSTA).

2. Gain access to HSTA area and remove the HSTA.

3. Do a Detailed Inspection and measurement of the Karon lined bushings for any disbond, tear, or wear. If

any disbond or tear is found, or the ID is greater than the allowable MAXIMUM DIAMETER on the Karon

lined bushings; then a bushing replacement is necessary. If no disbond, tear, and wear are found on the

bushings; then no bushing replacement is necessary.

4. Install the HSTA that is in a known serviceable condition or has been overhauled in accordance with this

service bulletin.

NOTE: If the replacement HSTA is not in a known serviceable condition, then do a Detailed Inspection

and measurement of the Karon lined bushings and pins; and a Detailed Inspection of the fail-safe

components of the replacement HSTA in accordance with this service bulletin before further flight.

Refer to Paragraph 3.A., General Information, for the applicable known serviceable conditions.

5. Do the Horizontal Stabilizer Trim Actuator Installation Test.

6. Close access and put the airplane back to a serviceable condition.

7. Repeat the Detailed Inspection and measurement of the Karon lined bushings at the time in accordance

with Paragraph 1.E., Compliance.

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Component (Horizontal Stabilizer Trim Actuator, HSTA) Work

1. Disassemble the HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) as necessary.

2. Do a Detailed Inspection and measurement of the Karon lined bushings for any disbond, tear, or wear. Do

a Detailed Inspection and measurement of the pins for any gouge, crack, or wear. Do a Detailed Inspection

of the fail-safe components for any gouge or crack.

3. If any disbond or tear is found, or the ID is greater than the MAXIMUM DESIGN DIMENSION on the Karon

lined bushings; then a bushing replacement is necessary. If no disbond, tear, and wear are found on the

bushings; then no bushing replacement is necessary.

4. If any gouge or crack is found, or the OD is less than the MINIMUM DESIGN DIMENSION on the pins; then

a pin replacement or refurbishment is necessary. If any gouge or crack is found on the fail-safe components,

then a replacement or refurbishment is necessary.

For any cracked pins that are found during the Detailed Inspection, replace the pin and do a magnetic

particle inspection of the fail-safe components as applicable. If any crack is found on the fail-safe components

during a magnetic particle inspection, then replacement is necessary.

If no gouge, crack, and wear are found on the pins; then a replacement or refurbishment is not necessary.

If no gouge and crack are found on the fail-safe components, then a replacement or refurbishment is not

necessary.

5. Assemble the HSTA.

EFFECTIVITY

777-200, 777-200LR, 777-300, and 777-300ER 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 available for airplanes in warranty as of March 3, 2007. Please refer to Paragraph

2.B., Industry Support Information.

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 777-55A0017

ALERT ALERT
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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Commercial 

Airplanes 777

Service Bulletin

ALERT

Number: 777-55A0017

Original Issue: May 20, 2010

ATA System: 5518 2741

SUBJECT: STABILIZERS - Horizontal Stabilizer - Horizontal Stabilizer Jackscrew Fitting - Karon

Lined Bushing Inspection and Replacement

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

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 893. At least one airplane after line number

893 is also affected by this service bulletin, and these airplanes are in Group(s) 1. These

airplanes will be added to the service bulletin's MyBoeingFleet.com (MBF) "get effectivity"

result when they are added to the MBF Fleet Profile Page.

GROUP CONFIGURATION DESCRIPTION

1 - 777-200, 777-200LR, 777-300, and 777-300ER airplanes.

Airplane Models:

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

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

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Variable Number Group

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

WB406 1

WB411 - WB413 1

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Variable Number Group

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

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

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Variable Number Group

WC581 1

WD001 - WD002 1

WD011 - WD018 1

WD031 - WD036 1

WD046 - WD055 1

WD066 - WD075 1

WD081 - WD088 1

WD091 1

WD501 - WD513 1

WD521 - WD541 1

WD546 - WD554 1

WD561 - WD573 1

WD581 - WD599 1

WD606 - WD609 1

WD621 - WD632 1

WD651 - WD665 1

WD671 - WD676 1

WD691 - WD709 1

WD741 - WD752 1

WD761 - WD771 1

WD786 - WD788 1

WD796 - WD813 1

WD826 - WD837 1

WD846 - WD861 1

WD871 - WD882 1

WD911 - WD914 1

WD921 - WD922 1

WD936 - WD939 1

WD946 - WD951 1

WD966 - WD969 1

WD981 - WD982 1

WD986 - WD987 1

WE001 - WE004 1

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Variable Number Group

WE011 - WE012 1

WE021 - WE022 1

WE071 1

WE081 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Accomplishment of work given in this service bulletin will find damage to Karon lined bushings and

pins in the HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) and HSTA attachment locations on

the airplane structure. There are twenty-four (24) Karon lined bushings and six (6) pins in the fuselage,

horizontal stabilizer, HSTA upper and lower gimbals, and HSTA primary brake housing. If the Karon

liners in the bushings are damaged, this may cause the Karon liners to completely disbond from the

bushings. The completely disbonded Karon liners may migrate out of the joint causing excessive joint

clearance. A joint with excessive clearance would result in fatigue cracking of the pins. The fatigue

cracking of the pins in the HSTA and HSTA attachment locations on the airplane structure can

compromise the structural integrity of the joints resulting in loss of controllability of the airplane.

The 24 Karon lined bushings are installed in the following joint locations: BULKHEAD SUPPORT

JACKSCREW FITTING, HORIZONTAL STABILIZER JACKSCREW FITTING, UPPER GIMBAL -

BRAKE HOUSING, UPPER GIMBAL - BULKHEAD SUPPORT, TRIM ACTUATOR PRIMARY BRAKE

HOUSING, AND LOWER GIMBAL. The bore of the bushings is lined with Karon, a material that is

intended to reduce friction and resist wear. Research tests have shown that Karon liners would not

wear in service; therefore, lubrication and inspection of these would not be necessary.

During a scheduled inspection of the HSTA components for 777-200, one operator found a Karon lined

bushing in the HORIZONTAL STABILIZER JACKSCREW FITTING with Karon liner broken into five

pieces. The broken Karon liner had worn and disbonded from the bushing. The broken Karon liner of

the bushing was found on an airplane that had accumulated 35,145 flight hours and 5,335 fight cycles.

Boeing analysis shows that the broken Karon lined bushing was one of the 149 bushings that used an

early manufacturing process, which has since been improved. However, further investigation and

analysis by Boeing show that Karon lined bushings in the HSTA and HSTA attachment locations on

the airplane structure using both the early and the improved process could wear in service. The analysis

also shows that the wear of the Karon liner may cause excessive joint clearance, which could lead to

fatigue cracking of the pins.

Accomplishment of the inspection in this service bulletin will find any disbond, tear, or wear in the 24

Karon lined bushings; any gouge, crack, or wear in the 6 pins; and any gouge or crack in the fail-safe

components in the HSTA and HSTA attachment locations on the airplane structure. The inspection will

make sure that Karon lined bushings and pins are returned to the design standard.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 20, 2010

777-55A0017

13 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Boeing Service Related Problem (SRP) 777-SRP-55-0042 is related to this service bulletin.

Boeing Fleet Team Digest (FTD) article 777 FTD 55-07001 is related to this service bulletin.

D. Description

Airplane Work

1. Remove hydraulic pressure, hydraulic power, and install safety tags to the HORIZONTAL

STABILIZER TRIM ACTUATOR (HSTA).

2. Gain access to HSTA area and remove the HSTA.

3. Do a Detailed Inspection and measurement of the Karon lined bushings for any disbond, tear, or

wear. If any disbond or tear is found, or the ID is greater than the allowable MAXIMUM DIAMETER

on the Karon lined bushings; then a bushing replacement is necessary. If no disbond, tear, and

wear are found on the bushings; then no bushing replacement is necessary.

4. Install the HSTA that is in a known serviceable condition or has been overhauled in accordance

with this service bulletin.

NOTE: If the replacement HSTA is not in a known serviceable condition, then do a Detailed

Inspection and measurement of the Karon lined bushings and pins; and a Detailed

Inspection of the fail-safe components of the replacement HSTA in accordance with this

service bulletin before further flight. Refer to Paragraph 3.A., General Information, for the

applicable known serviceable conditions.

5. Do the Horizontal Stabilizer Trim Actuator Installation Test.

6. Close access and put the airplane back to a serviceable condition.

7. Repeat the Detailed Inspection and measurement of the Karon lined bushings at the time in

accordance with Paragraph 1.E., Compliance.

Component (Horizontal Stabilizer Trim Actuator, HSTA) Work

1. Disassemble the HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) as necessary.

2. Do a Detailed Inspection and measurement of the Karon lined bushings for any disbond, tear, or

wear. Do a Detailed Inspection and measurement of the pins for any gouge, crack, or wear. Do a

Detailed Inspection of the fail-safe components for any gouge or crack.

3. If any disbond or tear is found, or the ID is greater than the MAXIMUM DESIGN DIMENSION on

the Karon lined bushings; then a bushing replacement is necessary. If no disbond, tear, and wear

are found on the bushings; then no bushing replacement is necessary.

4. If any gouge or crack is found, or the OD is less than the MINIMUM DESIGN DIMENSION on the

pins; then a pin replacement or refurbishment is necessary. If any gouge or crack is found on the

fail-safe components, then a replacement or refurbishment is necessary.

For any cracked pins that are found during the Detailed Inspection, replace the pin and do a

magnetic particle inspection of the fail-safe components as applicable. If any crack is found on the

fail-safe components during a magnetic particle inspection, then replacement is necessary.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 20, 2010

777-55A0017

14 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
If no gouge, crack, and wear are found on the pins; then a replacement or refurbishment is not

necessary. If no gouge and crack are found on the fail-safe components, then a replacement or

refurbishment is not necessary.

5. Assemble the HSTA.

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, 311, 312

777-300ER

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.

Table 1: Inspection of Karon Lined Bushings and Pins

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later )

Condition Action

Within 24 -

months after the

original issue

date of this service bulletin.

Before 32,000

total flight cycles.

Do a Detailed Inspection

of the Karon lined bushings for a disbond or tear

and measure the ID of

the Karon lined bushings

for wear in accordance

with PART 1 of Paragraph 3.B., Work Instructions,

All airplanes.

Do a Karon lined bushing Before further flight. -

replacement in accordance with PART 1 of

Paragraph 3.B., Work Instructions, as applicable

Any disbond or tear found,

or the ID is greater than the

allowable MAXIMUM DIAMETER on the Karon lined

bushings.

AND

Install HSTA that is in a

known serviceable condition or has been overhauled in accordance

with PART 2 of Paragraph 3.B., Work Instructions.(a)

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Table 1: Inspection of Karon Lined Bushings and Pins

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later )

Condition Action

Install HSTA that is in a Before further flight. -

known serviceable condition or has been overhauled in accordance

with PART 2 of Paragraph 3.B., Work Instructions.(a)

No disbond and tear found,

and the ID is less than or

equal to the allowable

MAXIMUM DIAMETER on

the Karon lined bushings.

16,000 flight cycles.Within 16,000 flight cycles from

the initial inspection.

Do a Detailed Inspection

of the Karon lined bushings for a disbond or tear

and measure the ID of

the Karon lined bushings

for wear in accordance

with PART 1 of Paragraph 3.B., Work Instructions.

Accomplished PART 1 of

Paragraph 3.B., Work Instructions, and installed

HSTA that is in a known

serviceable condition or

has been overhauled in

accordance with PART 2

of Paragraph 3.B., Work

Instructions.

(a) If the replacement HSTA is not in a known serviceable condition, then do a Detailed Inspection and

measurement of the Karon lined bushings and pins; and a Detailed Inspection of the fail-safe components

of the HSTA in accordance with PART 2 of Paragraph 3.B., Work Instructions, before further flight. Refer

to Paragraph 3.A., General Information, for the descriptions of HSTA's that are in a known serviceable

conditions.

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

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• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Table 1: Airplane Work - Inspection and Measurement of Karon Lined Bushings

Number of Per- Task Hours Elapsed Hours

sons

Task

PART 1: Prepara- 2 3.60 1.80

tion, Open Access,

and Actuator Removal

PART 1: BULK- 1 0.75 0.75

HEAD SUPPORT

JACKSCREW FITTING Karon lined

bushings (FIGURE

1)

PART 1: HORIZON- 1 0.75 0.75

TAL STABILIZER

JACKSCREW FITTING Karon lined

bushings (FIGURE

2)

PART 6: HSTA In- 2 5.6 2.8

stallation, HSTA Installation Test, and

Close Access.

TOTAL FOR EACH AIRPLANE 10.70 6.10

Note: More time is needed if bushing replacement is necessary. Refer to Table 3

for additional hours for bushing replacement.

Table 2: Component (Horizontal Stabilizer Trim Actuator, HSTA) Work - Inspection and

Measurement of Karon Lined Bushings and Pins

Number of Per- Task Hours Elapsed Hours

sons

Task

PART 2: UPPER 1 0.50 0.50

GIMBAL - BRAKE

HOUSING Karon

lined bushings

(FIGURE 3)

PART 2: UPPER 1 0.50 0.50

GIMBAL - BULKHEAD SUPPORT

Karon lined bushings (FIGURE 3)

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Table 2: Component (Horizontal Stabilizer Trim Actuator, HSTA) Work - Inspection and

Measurement of Karon Lined Bushings and Pins

Number of Per- Task Hours Elapsed Hours

sons

Task

PART 2: TRIM AC- 1 0.50 0.50

TUATOR PRIMARY

BRAKE HOUSING

Karon lined bushings (FIGURE 4)

PART 2: LOWER 1 0.75 0.75

GIMBAL Karon

lined bushings

(FIGURE 5)

PART 2: Pins (FIG- 1 0.50 0.50

URE 6)

TOTAL FOR EACH COMPONENT 2.75 2.75

Note: More time is needed if bushing and/or pin replacement/refurbishment are

necessary. Refer to Table 3 for additional hours for bushing replacement.

Table 3: Karon Lined Bushing Replacement

Number of Per- Task Hours Elapsed Hours

sons

Task

PART 1: BULK- 1 2.00 2.00

HEAD SUPPORT

JACKSCREW FITTING, Bushing Removal (FIGURE

7)(a)

PART 1: BULK- 1 2.15 2.15

HEAD SUPPORT

JACKSCREW FITTING, Intermediate

Sleeve Replacement (FIGURE 8)(a)

(b) (c)

PART 1: BULK- 1 1.00 1.00

HEAD SUPPORT

JACKSCREW FITTING, Bushing Installation (FIGURE

9)(a) (c)

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Table 3: Karon Lined Bushing Replacement

Number of Per- Task Hours Elapsed Hours

sons

Task

PART 1: HORIZON- 1 3.00 3.00

TAL STABILIZER

JACKSCREW FITTING, Bushing Replacement(a) (c)

PART 2: UPPER 1 1.75 1.75

GIMBAL - UPPER

BRAKE, Bushing

Replacement(a) (c)

PART 2: UPPER 1 1.75 1.75

GIMBAL - BULKHEAD SUPPORT,

Bushing Replacement(a) (c)

PART 2: TRIM AC- 1 1.75 1.75

TUATOR PRIMARY

BRAKE HOUSING,

Bushing Replacement(a) (c)

PART 2: LOWER 1 3.00 3.00

GIMBAL, Bushing

Replacement(a) (c)

(a) Hours given are for a typical in-line set replacement.

(b) Replacement of the intermediate sleeve is necessary if a damage is found on

the sleeve.

(c) More time will be necessary to perform machining steps.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Boeing Service Related Problem (SRP) 777-SRP-55-0042

b. Component Maintenance Manual (CMM) 27-41-03

c. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-20-02, 20-30-03, 20-50-03

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d. 777 Aircraft Maintenance Manual (AMM) 27-41-13

e. 777 Fleet Team Digest (FTD) 55-07001

f. 777 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-04

g. 777-200 Structural Repair Manual (SRM) 51-20-01, 55-10-90, REPAIR 1

h. 777-300 Structural Repair Manual (SRM) 51-20-01, 55-10-90, REPAIR 1

i. 777 Maintenance Planning Document (MPD) 27-290-00, 55-507-00

2. Data supplied with this Service Bulletin

None.

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

Drawing Number Title

SUPPORT ASSEMBLY - HORIZONTAL STABILIZER

JACKSCREW, STA 2245.70

148W9100

182W7400 SPLICE ASSEMBLY - FRONT SPAR, HORIZONTAL STABILIZER

251W4170 UPPER GIMBAL ASSEMBLY - STABILIZER TRIM

251W4140 HOUSING ASSEMBLY - PRIMARY BRAKE, STABILIZER TRIM

251W4180 GIMBAL ASSEMBLY - LOWER, ACTUATOR, STABILIZER TRIM

These drawings were used to prepare this service bulletin. These drawings are not necessary to

make the specified changes, and are not supplied with this service bulletin. These drawings may

not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications:

None.

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 affects FCS but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

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

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2. MATERIAL INFORMATION

A. Material - Price and Availability

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

12/31/2010

ROLT

(Weeks)

Part Number Name

BUSHING - JACKSCREW, 31 $541.00

SUPPORT

148W9106-2

BUSHING - JACKSCREW, 23 $1,135.00

HORIZONTAL STABILIZER

182W7404-1

BUSHING - GIMBAL, UPPER 33 $985.00

BRAKE HOUSING

251W4172-3

BUSHING - GIMBAL, LOWER 23 $1,072.00

HORIZONTAL STABILIZER

251W4172-4

BUSHING - GIMBAL, UPPER 23 $1,029.00

SUPPORT

251W4172-5

BUSHING - GIMBAL, BRAKE 23 $1,001.00

HOUSING

251W4172-6

PIN - UPPER GIMBAL, STABI- 86 $1,187.00

LIZER TRIM, BRAKE HOUSING

251W4173-3

PIN - UPPER GIMBAL, STABI- 76 $3,191.00

LIZER TRIM, SUPPORT

251W4175-3

PIN ASSEMBLY - NUT GIM- 45 $7,791.00

BAL, STABILIZER TRIM

251W4187-7 (ALTERNATIVE SUBSTITUTE,

-9)

SHAFT-SAFETY, UPPER GIM- 58 $839.00

BAL, STABILIZER TRIM

(SAFETY SHAFT)

251W4188-1

148W9107-1 INTERMEDIATE SLEEVE 52 $725.00

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

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Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are available for 777 airplanes in warranty as of March 7, 2007. For inspection

task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing

Commercial Airplanes Group - Warranties. If the condition described in this service bulletin is found

during the inspection for airplanes in warranty as of that date and additional task hours are required,

send a warranty claim to Boeing Commercial Airplanes Group - Warranties. Please refer to this service

bulletin number and reference the airplane variable numbers in your purchase order.

C. Parts Necessary For Each Airplane

1. Kits/Parts

Part Number / QTY Name Notes

Specification

BUSHING - JACKSCREW, SUP- -

PORT

148W9106-2 4

BUSHING - JACKSCREW, HORI- -

ZONTAL STABILIZER

182W7404-1 4

BUSHING - GIMBAL, UPPER -

BRAKE HOUSING

251W4172-3 4

BUSHING - GIMBAL, LOWER -

HORIZONTAL STABILIZER

251W4172-4 4

BUSHING - GIMBAL, UPPER SUP- -

PORT

251W4172-5 4

BUSHING - GIMBAL, BRAKE -

HOUSING

251W4172-6 4

PIN - UPPER GIMBAL, STABILIZER -

TRIM, BRAKE HOUSING

251W4173-3 2

PIN - UPPER GIMBAL, STABILIZER -

TRIM, SUPPORT

251W4175-3 2

PIN ASSEMBLY - NUT GIMBAL, -

STABILIZER TRIM

251W4187-7 (AL- 2

TERNATIVE SUBSTITUTE, -9)

SHAFT-SAFETY, UPPER GIMBAL, -

STABILIZER TRIM (SAFETY

SHAFT)

251W4188-1 1

148W9107-1 2 INTERMEDIATE SLEEVE -

2. Parts and Materials Supplied by the Operator

None.

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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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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. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently.

5. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Torque limits to tighten nuts and bolts are in 777 SRM, Chapter 51.

6. 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.

7. 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.

8. 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.

9. The Detailed inspection and measurement of Karon lined bushings and pins in the

HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) and HSTA attachment

locations on the airplane structure are necessary at the following joint locations:

– BULKHEAD SUPPORT JACKSCREW FITTING

– HORIZONTAL STABILIZER JACKSCREW FITTING

– UPPER GIMBAL - BRAKE HOUSING

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– UPPER GIMBAL - BULKHEAD SUPPORT

– TRIM ACTUATOR PRIMARY BRAKE HOUSING

– LOWER GIMBAL

10. The fail-safe components in the six joint locations of the HSTA are SHAFT-SAFETY,

UPPER GIMBAL, STABILIZER TRIM (SAFETY SHAFT) and the inner pin of PIN

ASSEMBLY - NUT GIMBAL, STABILIZER TRIM.

11. Each joint location has four (4) Karon lined bushings in the in-line set; 2 bushings

per side. If Karon lined bushing replacement is necessary for a joint, it is

recommended to replace the bushings in a set of 4. However, as a minimum replace

Karon lined bushings as a pair on either side of the joint.

12. The instructions identified in Paragraph 3.B., Work Instructions, and Figure(s) are

for a typical in-line set.

13. A replacement Horizontal Stabilizer Trim Actuator (HSTA) is in a known serviceable

condition if your records agree with one these conditions:

– The HSTA is new.

– The HSTA is overhauled as specified in the applicable CMM 27-41-03.

– The condition of the HSTA is found satisfactory with the tests and checks as

specified in CMM 27-41-03.

B. WORK INSTRUCTIONS

PART 1 - AIRPLANE WORK

1. Preparation, Open Access, and HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) Removal

a. Remove hydraulic pressure, hydraulic power, and install safety tags to the HSTA. Refer to

777 AMM 27-41-13 as an accepted procedure.

b. Gain access to the HSTA through service access door 311BL.

c. Remove the HSTA. Refer to 777 AMM 27-41-13 as an accepted procedure.

2. Inspection and Measurement of Karon Lined Bushings

a. Do a Detailed Inspection and measure the internal diameter (ID) of the BUSHING -

JACKSCREW, SUPPORT in the BULKHEAD SUPPORT JACKSCREW FITTING in accordance

with FIGURE 1.

(1) Condition 1: If any disbond or tear is found, or the ID is greater than the allowable

MAXIMUM DIAMETER in accordance with FIGURE 10 on the Karon lined bushings; then

do bushing replacement as follows:

(a) Remove the Karon lined bushings in accordance with FIGURE 7.

1) Condition 1: If any damage is found or the ID is greater than the allowable hole

diameter in accordance with FIGURE 7 on the intermediate sleeve, then replace

the intermediate sleeve in accordance with FIGURE 8. Do the following when

replacing the intermediate sleeve:

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a) Condition 1: If any damage is found or the ID is greater than the allowable

hole diameter in accordance with FIGURE 8 on the fitting, then contact

Boeing for alternative repair instructions.

b) Condition 2: If no damage is found and the ID is within the allowable hole

diameter in accordance with FIGURE 8 on the fitting, then continue with

the repair in accordance with FIGURE 8.

2) Condition 2: If no damage is found and the ID is within the allowable hole

diameter in accordance with FIGURE 7 on the intermediate sleeve, then

replacement of the intermediate sleeve is not necessary.

(b) Install the new Karon lined bushings in accordance with FIGURE 9.

(2) Condition 2: If no disbond and tear are found, and the ID is less than or equal to the

allowable MAXIMUM DIAMETER in accordance with FIGURE 10 on the Karon lined

bushings; then bushing replacement is not necessary.

b. Do a Detailed Inspection and measure the ID of the BUSHING - JACKSCREW, HORIZONTAL

STABILIZER in the HORIZONTAL STABILIZER JACKSCREW FITTING in accordance with

FIGURE 2.

(1) Condition 1: If any disbond or tear is found, or the ID is greater than the allowable

MAXIMUM DIAMETER in accordance with FIGURE 10 on the Karon lined bushings; then

do bushing replacement and finish the repair area of the fitting as necessary in accordance

with Structural Repair Manual 777-200 SRM 55-10-90, REPAIR 1 or 777-300 SRM

55-10-90, REPAIR 1.

(2) Condition 2: If no disbond and tear are found, and the ID is less than or equal to the

allowable MAXIMUM DIAMETER in accordance with FIGURE 10 on the Karon lined

bushings; then bushing replacement is not necessary.

3. Installation of the HSTA

a. Option 1: If the replacement HSTA is in a known serviceable condition, then install the HSTA.

Refer to 777 AMM 27-41-13 as an accepted procedure.

NOTE: If the replacement HSTA is not in a known serviceable condition, then do the Detailed

Inspection and measurement of the Karon lined bushings, pins, and fail-safe

components of the replacement HSTA as applicable in accordance with PART 2 of

Paragraph 3.B., Work Instructions. Refer to Paragraph 3.A., General Information,

for the descriptions of HSTA's that are in a known serviceable conditions.

b. Option 2: If the replacement or the existing HSTA is not in a known serviceable condition,

then do PART 2.

4. Do the Horizontal Stabilizer Trim Actuator Test. Refer to 777 AMM 27-41-13 as an accepted

procedure.

5. Close access and put the airplane back to a serviceable condition.

6. Repeat the Detailed Inspection and measurement of the Karon lined bushings at the time in

accordance with Paragraph 1.E., Compliance.

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PART 2 - COMPONENT (HORIZONTAL STABILIZER TRIM ACTUATOR, HSTA) WORK

1. Disassemble the HORIZONTAL STABILIZER TRIM ACTUATOR (HSTA) as necessary. Refer to

CMM 27-41-03 as an accepted procedure.

2. Do a Detailed Inspection and measure the ID of the BUSHING - GIMBAL, UPPER BRAKE

HOUSING in the UPPER GIMBAL - BRAKE HOUSING in accordance with FIGURE 3.

a. Condition 1: If any disbond or tear is found, or the ID is greater than MAXIMUM DESIGN

DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the Karon lined

bushings; then do bushing replacement and refinish the repair area of the gimbal as necessary.

Refer to Components Maintenance Manual CMM 27-41-03, REPAIR 8-1 and CMM 27-41-03,

REPAIR 8-2; respectively as an accepted procedure.

b. Condition 2: If no disbond and tear are found, and the ID is less than or equal to MAXIMUM

DESIGN DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the

Karon lined bushings; then bushing replacement is not necessary.

3. Do a Detailed Inspection and measure the ID of the BUSHING - GIMBAL, UPPER SUPPORT in

the UPPER GIMBAL - BULKHEAD SUPPORT in accordance with FIGURE 3.

a. Condition 1: If any disbond or tear is found, or the ID is greater than MAXIMUM DESIGN

DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the Karon lined

bushings; then do bushing replacement and refinish the repair area of the gimbal as necessary.

Refer to CMM 27-41-03, REPAIR 8-1 and CMM 27-41-03, REPAIR 8-2; respectively as an

accepted procedure.

b. Condition 2: If no disbond and tear are found, and the ID is less than or equal to MAXIMUM

DESIGN DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the

Karon lined bushings; then bushing replacement is not necessary.

4. Do a Detailed Inspection and measure the ID of the BUSHING - GIMBAL, BRAKE HOUSING in

the TRIM ACTUATOR PRIMARY BRAKE HOUSING in accordance with FIGURE 4.

a. Condition 1: If any disbond or tear is found, or the ID is greater than MAXIMUM DESIGN

DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the Karon lined

bushings; then do bushing replacement and refinish the repair area of the housing as

necessary. Refer to CMM 27-41-03, REPAIR 3-1 and CMM 27-41-03, REPAIR 3-2; respectively

as an accepted procedure.

b. Condition 2: If no disbond and tear are found, and the ID is less than or equal to MAXIMUM

DESIGN DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the

Karon lined bushings; then bushing replacement is not necessary.

5. Do a Detailed Inspection and measure the ID of the BUSHING - GIMBAL, LOWER HORIZONTAL

STABILIZER in the LOWER GIMBAL in accordance with FIGURE 5.

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a. Condition 1: If any disbond or tear is found, or the ID is greater than MAXIMUM DESIGN

DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the Karon lined

bushings; then do bushing replacement and refinish the repair area of the gimbal as necessary.

Refer to CMM 27-41-03, REPAIR 16-1 as an accepted procedure.

b. Condition 2: If no disbond and tear are found, and the ID is less than or equal to MAXIMUM

DESIGN DIMENSION as specified in FITS AND CLEARANCES of CMM 27-41-03 on the

Karon lined bushings; then bushing replacement is not necessary.

6. Do a Detailed Inspection of the pins and the safety shaft; and measure the outer diameter (OD)

of the pins in accordance with FIGURE 6.

a. Condition 1: If any crack is found, do the following as applicable:

(1) For the PIN - UPPER GIMBAL, STABILIZER TRIM, BRAKE HOUSING in the UPPER

GIMBAL, replace the pin.

(2) For the PIN - UPPER GIMBAL, STABILIZER TRIM, SUPPORT in the UPPER GIMBAL,

replace the pin. Also do a magnetic particle inspection of the SHAFT-SAFETY, UPPER

GIMBAL, STABILIZER TRIM (SAFETY SHAFT) for a crack. Refer to SOPM 20-20-01 as

an accepted procedure for magnetic particle inspection.

(a) Condition 1: If any crack is found, replace the safety shaft.

(b) Condition 2: If no crack is found, then refurbish the safety shaft as necessary. Refer

to CMM 27-41-03, REPAIR 10-1, as an accepted procedure for refurbishment of the

safety shaft.

(3) For the PIN ASSEMBLY - NUT GIMBAL, STABILIZER TRIM in the LOWER GIMBAL,

replace the outer pin or the entire assembly. If the outer pin is replaced, do a magnetic

particle inspection of the inner pin. Refer to SOPM 20-20-01 as an accepted procedure

for magnetic particle inspection.

(a) Condition 1: If any crack is found, replace the inner pin.

(b) Condition 2: If no crack is found, then refurbish the pin assembly as necessary. Refer

to CMM 27-41-03, REPAIR 1-1, as an accepted procedure for refurbishment of the

pins.

(4) For the SHAFT-SAFETY, UPPER GIMBAL, STABILIZER TRIM (SAFETY SHAFT), replace

the safety shaft.

b. Condition 2: If any gouge is found, do the following as applicable:

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777-55A0017

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
(1) For the PIN - UPPER GIMBAL, STABILIZER TRIM, BRAKE HOUSING in the UPPER

GIMBAL, replace or refurbish the pins. Refer to CMM 27-41-03, REPAIR 17-1 as an

accepted procedure for refurbishment of the pins.

(2) For the PIN - UPPER GIMBAL, STABILIZER TRIM, SUPPORT in the UPPER GIMBAL,

replace or refurbish the pins. Refer to CMM 27-41-03, REPAIR 17-1 as an accepted

procedure for refurbishment of the pins.

(3) For the PIN ASSEMBLY - NUT GIMBAL, STABILIZER TRIM in the LOWER GIMBAL,

replace or refurbish the pins. Refer to CMM 27-41-03, REPAIR 1-1, as an accepted

procedure for refurbishment of the pins.

(4) For the SHAFT, SAFETY, UPPER GIMBAL, STABILIZER TRIM (SAFETY SHAFT),

replace or refurbish the safety shaft. Refer to CMM 27-41-03, REPAIR 10-1, as an

accepted procedure for the refurbishment of the safety shaft.

c. Condition 3: If OD is less than MINIMUM DESIGN DIMENSION as specified in FITS AND

CLEARANCES of CMM 27-41-03 on the pins; then do the following as applicable:

(1) For the PIN - UPPER GIMBAL, STABILIZER TRIM, BRAKE HOUSING in the UPPER

GIMBAL, replace or refurbish the pins. Refer to CMM 27-41-03, REPAIR 17-1 as an

accepted procedure for refurbishment of the pins.

(2) For the PIN - UPPER GIMBAL, STABILIZER TRIM, SUPPORT in the UPPER GIMBAL,

replace or refurbish the pins. Refer to CMM 27-41-03, REPAIR 17-1 as an accepted

procedure for refurbishment of the pins.

(3) For the PIN ASSEMBLY - NUT GIMBAL, STABILIZER TRIM in the LOWER GIMBAL,

replace or refurbish the pins. Refer to CMM 27-41-03, REPAIR 1-1, as an accepted

procedure for refurbishment of the pins.

d. Condition 4: If no gouge, crack and wear are found on any of the pins and safety shaft as

applicable; and the OD is greater than or equal to MINIMUM DESIGN DIMENSION as specified

in FITS AND CLEARANCES of CMM 27-41-03 on the pins as applicable; then a replacement

or refurbishment is not necessary.

7. Assemble the HSTA. Refer to CMM 27-41-03 as an accepted procedure.

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 1: INSPECTION AND MEASUREMENT OF BULKHEAD SUPPORT JACKSCREW FITTING KARON

LINED BUSHINGS

(SHEET 1 OF 2)

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Original Issue: May 20, 2010

777-55A0017

31 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the Karon liner for any disbond or

tear.

BUSHING - 148W9106-2 4

JACKSCREW, SUPPORT

1 Inspect

Measure the ID of

the Karon lined

bushing for any

wear.

BUSHING - 148W9106-2 4

JACKSCREW, SUPPORT

2 Measure

FIGURE 1: INSPECTION AND MEASUREMENT OF BULKHEAD SUPPORT JACKSCREW FITTING KARON

LINED BUSHINGS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 2: INSPECTION AND MEASUREMENT OF HORIZONTAL STABILIZER JACKSCREW FITTING

KARON LINED BUSHINGS

(SHEET 1 OF 2)

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33 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the Karon liner for any disbond or

tear.

BUSHING - 182W7404-1 4

JACKSCREW, HORIZONTAL STABILIZER

1 Inspect

Measure the ID of

the Karon lined

bushing for any

wear.

BUSHING - 182W7404-1 4

JACKSCREW, HORIZONTAL STABILIZER

2 Measure

FIGURE 2: INSPECTION AND MEASUREMENT OF HORIZONTAL STABILIZER JACKSCREW FITTING

KARON LINED BUSHINGS

(SHEET 2 OF 2)

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777-55A0017

34 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 3: INSPECTION AND MEASUREMENT OF UPPER GIMBAL - BRAKE HOUSING AND UPPER

GIMBAL - BULKHEAD SUPPORT KARON LINED BUSHINGS

(SHEET 1 OF 2)

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777-55A0017

35 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the Karon liner for any disbond or

tear.

BUSHING - GIMBAL, 251W4172-3 4

UPPER BRAKE

HOUSING

1 Inspect

Do a Detailed Inspection of the Karon liner for any disbond or

tear.

BUSHING - GIMBAL, 251W4172-5 4

UPPER SUPPORT

2 Inspect

Measure the ID of

the Karon lined

bushing for any

wear.

BUSHING - GIMBAL, 251W4172-3 4

UPPER BRAKE

HOUSING

3 Measure

Measure the ID of

the Karon lined

bushing for any

wear.

BUSHING - GIMBAL, 251W4172-5 4

UPPER SUPPORT

4 Measure

FIGURE 3: INSPECTION AND MEASUREMENT OF UPPER GIMBAL - BRAKE HOUSING AND UPPER

GIMBAL - BULKHEAD SUPPORT KARON LINED BUSHINGS

(SHEET 2 OF 2)

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777-55A0017

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 4: INSPECTION AND MEASUREMENT OF TRIM ACTUATOR PRIMARY BRAKE HOUSING KARON

LINED BUSHINGS

(SHEET 1 OF 2)

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Original Issue: May 20, 2010

777-55A0017

37 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the Karon liner for any disbond or

tear.

BUSHING - GIMBAL, 251W4172-6 4

BRAKE HOUSING

1 Inspect

Measure the ID of

the Karon lined

bushing for any

wear.

BUSHING - GIMBAL, 251W4172-6 4

BRAKE HOUSING

2 Measure

FIGURE 4: INSPECTION AND MEASUREMENT OF TRIM ACTUATOR PRIMARY BRAKE HOUSING KARON

LINED BUSHINGS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 5: INSPECTION AND MEASUREMENT OF LOWER GIMBAL KARON LINED BUSHINGS

(SHEET 1 OF 2)

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Original Issue: May 20, 2010

777-55A0017

39 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the Karon liner for any disbond or

tear.

BUSHING - GIMBAL, 251W4172-4 4

LOWER HORIZONTAL

STABILIZER

1 Inspect

Measure the ID of

the Karon lined

bushing for any

wear.

BUSHING - GIMBAL, 251W4172-4 4

LOWER HORIZONTAL

STABILIZER

2 Measure

FIGURE 5: INSPECTION AND MEASUREMENT OF LOWER GIMBAL KARON LINED BUSHINGS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 6: INSPECTION AND MEASUREMENT OF PINS

(SHEET 1 OF 2)

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777-55A0017

41 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Do a Detailed Inspection of the pins on

the outer surface for

any gouge or crack.

PIN - UPPER GIMBAL, 251W4173-3 2

STABILIZER TRIM,

BRAKE HOUSING

1 Inspect

Do a Detailed Inspection of the pins on

the outer surface for

any gouge or

crack.(a)

PIN - UPPER GIMBAL, 251W4175-3 2

STABILIZER TRIM,

SUPPORT

2 Inspect

Do a Detailed Inspection of the outer pins

on the outer surface

for any gouge or

crack.(b)

251W4187-7 (ALTER- 2

NATIVE SUBSTITUTE,

-9)

PIN ASSEMBLY - NUT

GIMBAL, STABILIZER

TRIM

3 Inspect

Do a Detailed Inspection of the safety

shaft on the outer

surface for any

gouge or crack.(a)

SHAFT-SAFETY, UP- 251W4188-1 1

PER GIMBAL, STABILIZER TRIM (SAFETY

SHAFT)

4 Inspect

Measure the OD of

the pins for any

wear.

PIN - UPPER GIMBAL, 251W4173-3 2

STABILIZER TRIM,

BRAKE HOUSING

5 Measure

Measure the OD of

the pins for any

wear.

PIN - UPPER GIMBAL, 251W4175-3 2

STABILIZER TRIM,

SUPPORT

6 Measure

Measure the OD of

the pins for any

wear.

251W4187-7 (ALTER- 2

NATIVE SUBSTITUTE,

-9)

PIN ASSEMBLY - NUT

GIMBAL, STABILIZER

TRIM

7 Measure

(a) If any crack is found on PIN - UPPER GIMBAL, STABILIZER TRIM, SUPPORT, additional inspection

may be necessary on SHAFT-SAFETY, UPPER GIMBAL, STABILIZER TRIM (SAFETY SHAFT) in accordance with Paragraph 3.B., Work Instructions, PART 2, Section 6.

(b) The PIN ASSEMBLY - NUT GIMBAL, STABILIZER TRIM has outer and inner pins. If any crack is found

on the outer pin, additional inspection may be necessary on the inner pin in accordance with Paragraph

3.B., Work Instructions, PART 2, Section 6.

FIGURE 6: INSPECTION AND MEASUREMENT OF PINS

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 7: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING REMOVAL

(SHEET 1 OF 3)

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777-55A0017

43 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 7: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING REMOVAL

(SHEET 2 OF 3)

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777-55A0017

44 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: USE CARE WHEN YOU REMOVE THE BUSHINGS. THE BUSHINGS WERE INSTALLED

WITH AN INTERFERENCE FIT. IF YOU DO NOT OBEY, DAMAGE TO THE BULKHEAD

SUPPORT JACKSCREW FITTING CAN OCCUR.

Refer to SOPM 20-

50-03 as an accepted procedure.

BUSHING - 148W9106-2 4

JACKSCREW, SUPPORT

1 Remove

WARNING: KEEP THE SOLVENTS AWAY FROM SOURCES OF HEAT, FIRE OR SPARKS. IF YOU DO

NOT, AN EXPLOSION CAN OCCUR. DO NOT PERMIT THE SOLVENTS TO TOUCH YOUR

SKIN, EYES OR CLOTHING. DO NOT BREATHE THE VAPORS. WEAR PROTECTIVE

CLOTHING AND EYE PROTECTION. MAKE SURE THERE IS A GOOD FLOW OF CLEAN

AIR. IN A CONFINED SPACE, USE MECHANICAL VENTILATION FOR RESPIRATORY

PROTECTION. INJURY TO PERSONS CAN OCCUR.

CAUTION: USE CARE WHEN YOU WORK WITH THE INSIDE SURFACE OF THE BULKHEAD SUPPORT

JACKSCREW FITTING. MECHANICAL TOOLS AND ABRASION CAN CAUSE DAMAGE TO

THE FITTING HOLE. THE RESULT CAN BE A HOLE THAT IS LARGER THAN THE ALLOWABLE MAXIMUM HOLE DIMENSIONS.

Remove all the dust

and sealant from the

inner surface of the

hole. Refer to SOPM

20-30-03 as an accepted procedure.

INTERMEDIATE 148W9107-1 2

SLEEVE

2 Clean

Do a surface HFEC

inspection for a

crack on the inner

surface of the hole

in accordance with

777 NDT Part 6, 51-

00-04.(a)

INTERMEDIATE 148W9107-1 2

SLEEVE

3 Inspect

Measure the ID of

the sleeve.

INTERMEDIATE 148W9107-1 2

SLEEVE

4 Measure

(a) Penetrant inspection is optional to the surface HFEC inspection. Refer to SOPM 20-20-02 as an accepted

procedure.

FIGURE 7: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING REMOVAL

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 8: BULKHEAD SUPPORT JACKSCREW FITTING INTERMEDIATE SLEEVE REPLACEMENT

(SHEET 1 OF 4)

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777-55A0017

46 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 8: BULKHEAD SUPPORT JACKSCREW FITTING INTERMEDIATE SLEEVE REPLACEMENT

(SHEET 2 OF 4)

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777-55A0017

47 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. It is necessary

to replace the intermediate sleeve with a damage or ID greater than the allowable hole diameter.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

CAUTION: USE CARE WHEN YOU REMOVE THE BUSHINGS. THE BUSHINGS WERE INSTALLED

WITH AN INTERFERENCE FIT. IF YOU DO NOT OBEY, DAMAGE TO THE BULKHEAD

SUPPORT JACKSCREW FITTING CAN OCCUR.

Refer to SOPM 20-

50-03 as an accepted procedure.

INTERMEDIATE 148W9107-1 2

SLEEVE

1 Remove

FIGURE 8: BULKHEAD SUPPORT JACKSCREW FITTING INTERMEDIATE SLEEVE REPLACEMENT

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

WARNING: KEEP THE SOLVENTS AWAY FROM SOURCES OF HEAT, FIRE OR SPARKS. IF YOU DO

NOT, AN EXPLOSION CAN OCCUR. DO NOT PERMIT THE SOLVENTS TO TOUCH YOUR

SKIN, EYES OR CLOTHING. DO NOT BREATHE THE VAPORS. WEAR PROTECTIVE

CLOTHING AND EYE PROTECTION. MAKE SURE THERE IS A GOOD FLOW OF CLEAN

AIR. IN A CONFINED SPACE, USE MECHANICAL VENTILATION FOR RESPIRATORY

PROTECTION. INJURY TO PERSONS CAN OCCUR.

CAUTION: USE CARE WHEN YOU WORK WITH THE INSIDE SURFACE OF THE BULKHEAD SUPPORT

JACKSCREW FITTING. MECHANICAL TOOLS AND ABRASION CAN CAUSE DAMAGE TO

THE FITTING HOLE. THE RESULT CAN BE A HOLE THAT IS LARGER THAN THE ALLOWABLE MAXIMUM HOLE DIMENSIONS.

Remove all the dust

and sealant from the

inner surface of the

hole. Refer to SOPM

20-30-03 as an accepted procedure.

BULKHEAD SUPPORT - 2

JACKSCREW FITTING

2 Clean

Do a surface HFEC

inspection of the inner surface of the

hole for a crack in

accordance with 777

NDT Part 6, 51-00-

01.(a)

BULKHEAD SUPPORT - 2

JACKSCREW FITTING

3 Inspect

Measure the ID of

the hole.

BULKHEAD SUPPORT - 2

JACKSCREW FITTING

4 Measure

CAUTION: DO NOT CONTINUE WITH THE REPAIR IF A DAMAGE IS FOUND OR THE ID IS GREATER

THAN THE ALLOWABLE HOLE DIAMETER ON THE FITTING TO PREVENT MORE DAMAGE.

Refer to SOPM 20-

50-03 as an accepted procedure.

INTERMEDIATE 148W9107-1 2

SLEEVE

5 Install (New)

Machine the ID to

the diameters

shown. Refer to

SOPM 20-10-02 as

an accepted procedure.

INTERMEDIATE 148W9107-1 2

SLEEVE

6 Ream

(a) Penetrant inspection is optional to the surface HFEC inspection. Refer to SOPM 20-20-02 as an accepted

procedure.

FIGURE 8: BULKHEAD SUPPORT JACKSCREW FITTING INTERMEDIATE SLEEVE REPLACEMENT

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 9: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING INSTALLATION

(SHEET 1 OF 5)

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777-55A0017

50 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
FIGURE 9: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING INSTALLATION

(SHEET 2 OF 5)

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777-55A0017

51 of 55

BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply one layer of

BMS 10-11, Type I

primer to the mating

surfaces of the lug

face under the bushing flange. Refer to

777-200 SRM 51-

20-01 or 777-300

SRM 51-20-01 as an

accepted procedure.(a)

1 Apply TYPE I PRIMER BMS 10-11 -

FIGURE 9: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING INSTALLATION

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply the sealant

along the contact

surface between the

lug and bushing

flange. Refer to

SOPM 20-50-03 as

an accepted procedure.

2 Apply SEALANT BMS 5-95 -

WARNING: USE PROTECTION WHEN YOU DO WORK WITH LIQUID NITROGEN. MAKE SURE THAT

THE AREA HAS A GOOD FLOW OF CLEAN AIR. THE TEMPERATURE FOR LIQUID NITROGEN IS APPROXIMATELY MINUS 320 F (MINUS 196 C). IF YOU DO NOT OBEY, INJURY

TO PERSONS CAN BE THE RESULT.

Hold the assembly

in position until the

assembly is at room

temperature. Refer

to SOPM 20-50-03

as an accepted procedure.

BUSHING - 148W9106-2 4

JACKSCREW, SUPPORT

3 Install (New)

BUSHING - 148W9106-2 4 (b) (c)

JACKSCREW, SUPPORT

4 Ream

Line hone the bushing hole to the final

ID dimension. Make

the surface finish 32

microinches (0.8 micrometers ) Ra or

better.(b) (d)

BUSHING - 148W9106-2 4

JACKSCREW, SUPPORT

Hone

Clean the inner surface of the bushing

to make sure that all

the honing debris

and machining oil

are removed. Refer

to SOPM 20-30-03

as an accepted procedure.

BUSHING - 148W9106-2 -

JACKSCREW, SUPPORT

5 Clean

FIGURE 9: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING INSTALLATION

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a fillet seal on

the bushing flanges

and fill the gap between the bushings.

Refer to SOPM 20-

50-03 as an accepted procedure.

6 Apply SEALANT BMS 5-95 -

(a) If necessary, apply a chemical conversion coating to the mating surfaces of the lug face under the bushing

flange. Refer to 777-200 SRM 51-20-01 or 777-300 SRM 51-20-01 as an accepted procedure.

(b) Use a long piloted reamer as a tool to keep all bushing holes coaxial. The pilot part of the reamer must

be non-cutting to prevent damage to the bushing. Use a guide bush to slip into the adjacent bushing bore

to support the reamer and protect the initial bushings.

(c) Line ream the bushing hole to the inside diameter of 1.955 to 1.960 inches (49.66 to 49.78 mm). Machine

the Karon liner at 1000 surface feet per minute (SFPM) minimum with a feed rate between 0.001 and

0.003 inch (0.025 and 0.076 mm) per revolution. Machining can be done dry or with a water soluble

coolant. Use a diamond or carbide cutter with a 0.030 inch minimum radius.

(d) If necessary hone all the replacement bushings at the same time to keep them coaxial. Use the following

requirements for honing: Sunnen stone K6-A63 or equivalent (280 grit medium hard aluminum oxide),

speed of 300 to 1000 RPM (revolutions per minute), and Sunnen MB30 oil base coolant or equivalent.

FIGURE 9: BULKHEAD SUPPORT JACKSCREW FITTING KARON LINED BUSHING INSTALLATION

(SHEET 5 OF 5)

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777-55A0017

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT
Joint Location Part Name Part Number Service Wear Limits

MINIMUM DIAMETERMAXIMUM DIAMETER

BUSHING - 148W9106-2 ID: 2.0060 -

JACKSCREW, SUPPORT

BULKHEAD SUPPORT JACKSCREW

FITTING

BUSHING - 182W7404-1 ID: 2.0098 -

JACKSCREW, HORIZONTAL STABILIZER

HORIZONTAL STABILIZER

JACKSCREW FITTING

FIGURE 10: KARON LINED BUSHING SERVICE WEAR LIMITS

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-55A0017

ALERT ALERT