Commercial 

Airplanes 777

Service Bulletin

Number: 777-55A0015

Original Issue: April 19, 2007

Revision 3: November 24, 2009

ATA System: 5527

SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly 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

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ECCN: 9E991

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Copyright © 2007 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Unpublished Work - All Rights Reserved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.

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6.0
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BOEING SERVICE BULLETIN 777-55A0015

BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

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

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

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

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

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

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

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

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

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

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 21

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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION . . . . . . . . . . . . . . . . . . 29

FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION . . . . . . . . . . . . . . . . . 33

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BOEING SERVICE BULLETIN 777-55A0015

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Revision Transmittal Sheet Number: 777-55A0015

Original Issue: April 19, 2007

Revision 3: November 24, 2009

ATA System: 5527

SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly Inspection

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed as shown in the original issue, Revision 1, or Revision 2 of

this service bulletin.

No airplanes were added to the service bulletin effectivity.

Federal Aviation Administration (FAA) Airworthiness Directive 2007-26-05, Amendment 39-15307, is related to

this service bulletin.

REASON FOR REVISION

This revision is sent to clarify the access and restoration instructions; and clarify the words "date on this service

bulletin" and provide terminating action information in the compliance tables.

These sections were changed:

1. In Table 1 of Paragraph 1.E., Compliance, the words "date on this service bulletin" was changed to "original

issue date of this service bulletin."

2. In Tables 1 and 2 of Paragraph 1.E., Compliance, terminating action information for the inspection

requirements as given in this service bulletin was added. Also clarified the action "Replace any cracked

fitting" and condition "Replaced Fittings" by referencing Paragraph 3.B., PART 4.

3. In Paragraph 1.J., References, added 777 Aircraft Maintenance Manual (AMM) 12-12-01 and 27-31-09.

Deleted the reference 777 AMM 55-27-01. Also added Boeing Service Bulletin 777-55A0016.

4. In Paragraph 1.K., Publications Affected, damage tolerance evaluation statement was added.

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5. In Paragraph 3.A., General Information, added a note to give an option to change the sequence of steps

in Paragraph 3.B., Work Instructions.

6. In Paragraph 3.B., Work Instructions, the words "refer to" are added and deleted the words "as given in" to

address PART 3 and PART 5.

7. In PART 3 and PART 5 of Paragraph 3.B., Work Instructions, procedure from 777 AMM 27-31-09 was

added to clarify the access and restoration instructions to have the elevator in the "up" position instead of

"down" position. Also rearranged access and restoration instructions to have the access panel removed

first for access and installed last for restoration.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: April 19, 2007

Revision 1: January 31, 2008

Revision 2: December 04, 2008

Revision 3: November 24, 2009

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BOEING SERVICE BULLETIN 777-55A0015
Commercial 

Airplanes 777

Service Bulletin

Summary Number: 777-55A0015

Original Issue: April 19, 2007

Revision 3: November 24, 2009

ATA System: 5527

SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly Inspection

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to do surface High Frequency Eddy Current (HFEC) or dye penetrant

inspections of the elevator actuator fittings at left and right Elevator Stations 169.79 and 194.79 for cracks.

Cracked actuator fittings may lack adequate residual strength to react flight loads. Cracked actuator fittings can

become detached from the elevator, resulting in an unrestrained elevator. An unrestrained elevator is an

unacceptable flutter condition which can result in a loss of airplane control.

One operator has told Boeing that a cracked left outboard actuator fitting was found on a 777 airplane with

17,346 flight-hours and 14,043 flight-cycles. The crack extended through the lower inboard flange of the fitting

and into the vertical flange. Analysis by Boeing indicates that this crack resulted from fatigue due to higher than

anticipated stress levels in the fitting flanges.

Accomplishment of the inspections shown in this service bulletin will make sure that fatigue cracks in the elevator

actuator support fittings are found and cracked fittings replaced before the actuator fittings can become detached

from the elevator.

Boeing Service Related Problem (SRP) 777-SRP-55-0040 is related to this service bulletin.

ACTION

Get access to the elevator actuator fittings at left and right Elevator Stations 169.79 and 194.79. Do surface

High Frequency Eddy Current (HFEC) or dye penetrant inspections of the actuator fittings for cracks. If cracks

are found, replace the cracked fittings with new fittings of the same part number or an approved optional part

number. Do the inspections again at the times given in Paragraph 1.E., Compliance.

EFFECTIVITY

777-200, 777-200LR, 777-300 and 777-300ER airplanes. Refer to Paragraph 1.A., Effectivity, for the list of

affected airplanes.

COMPLIANCE

See Service Bulletin Paragraph 1.E. for compliance information.

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Federal Aviation Administration (FAA) Airworthiness Directive 2007-26-05, Amendment 39-15307 is related to

this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of November 17, 2006. Please refer to

Paragraph 2.B., Industry Support Information.

MANPOWER

Airplanes Total Task Hours Elapsed Hours

All - Initial Inspection 9.5 4.75

All - Repeat Inspection 9.5 4.75

MATERIAL INFORMATION

None.

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BOEING SERVICE BULLETIN 777-55A0015
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BOEING SERVICE BULLETIN 777-55A0015

BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Number: 777-55A0015

Original Issue: April 19, 2007

Revision 3: November 24, 2009

ATA System: 5527

SUBJECT: STABILIZERS - Elevator Attach Fittings - Elevator Actuator Fitting Assembly Inspection

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.

GROUP CONFIGURATION DESCRIPTION

1 - All 777-200 airplanes line number 1 through 40.

777-200, 777-200LR, 777-300, and 777-300ER airplanes line number

41 to 717.

2 -

Airplane Models:

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

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA087 1

WA088 - WA093 2

WA101 - WA104 1

WA116 - WA117 1

WA118 - WA119 2

WA131 - WA135 1

WA136 - WA137 2

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Variable Number Group

WA171 - WA173 1

WA174 - WA175 2

WA196 - WA197 1

WA198 2

WA206 - WA212 2

WA221 - WA223 2

WA231 - WA232 2

WA241 - WA250 2

WA261 - WA266 2

WA281 - WA283 2

WA301 - WA304 2

WB001 - WB021 2

WB031 - WB046 2

WB051 - WB088 2

WB101 - WB106 2

WB121 - WB125 2

WB131 - WB147 2

WB151 - WB155 2

WB161 - WB177 2

WB181 - WB194 2

WB201 - WB215 2

WB231 - WB247 2

WB271 - WB273 2

WB276 - WB286 2

WB291 - WB302 2

WB306 - WB307 2

WB311 - WB337 2

WB341 - WB342 2

WB366 - WB368 2

WB371 - WB388 2

WB406 2

WB411 - WB413 2

WB416 - WB439 2

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BOEING SERVICE BULLETIN 777-55A0015
Variable Number Group

WB446 - WB453 2

WB476 2

WB481 - WB484 2

WB501 - WB512 2

WB531 - WB537 2

WB551 - WB554 2

WB591 - WB597 2

WB601 - WB606 2

WB611 - WB622 2

WB631 - WB638 2

WB646 - WB649 2

WC051 - WC073 2

WC101 - WC104 2

WC111 - WC119 2

WC221 - WC222 2

WC241 - WC243 2

WC281 - WC290 2

WC301 - WC308 2

WC361 - WC364 2

WC371 - WC374 2

WC381 - WC395 2

WC441 2

WC446 - WC449 2

WC456 - WC459 2

WC486 - WC493 2

WC506 - WC508 2

WC521 - WC522 2

WC531 - WC536 2

WC546 - WC548 2

WC556 2

WC566 - WC567 2

WD001 - WD002 2

WD011 - WD015 2

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BOEING SERVICE BULLETIN 777-55A0015
Variable Number Group

WD031 - WD036 2

WD046 - WD049 2

WD066 - WD067 2

WD501 - WD507 2

WD521 - WD538 2

WD546 - WD552 2

WD561 - WD572 2

WD581 - WD594 2

WD606 - WD609 2

WD621 - WD632 2

WD651 - WD659 2

WD671 - WD675 2

WD691 - WD706 2

WD741 - WD748 2

WD761 - WD770 2

WD786 - WD788 2

WD796 - WD802 2

WD826 - WD829 2

WD846 - WD849 2

WD871 - WD872 2

WD911 - WD912 2

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to do surface High Frequency Eddy Current (HFEC) or dye

penetrant inspections of the elevator actuator fittings at left and right Elevator Stations 169.79 and

194.79 for cracks. Cracked actuator fittings may lack adequate residual strength to react flight loads.

Cracked actuator fittings can become detached from the elevator, resulting in an unrestrained elevator.

An unrestrained elevator is an unacceptable flutter condition which can result in a loss of airplane

control.

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BOEING SERVICE BULLETIN 777-55A0015
One operator has told Boeing that a cracked left outboard actuator fitting was found on a 777 airplane

with 17,346 flight-hours and 14,043 flight-cycles. The crack extended through the lower inboard flange

of the fitting and into the vertical flange. Analysis by Boeing indicates that this crack resulted from

fatigue due to higher than anticipated stress levels in the fitting flanges.

Accomplishment of the inspections shown in this service bulletin will make sure that fatigue cracks in

the elevator actuator support fittings are found and cracked fittings replaced before the actuator fittings

can become detached from the elevator.

Revision 1 was sent to clarify the areas of the fitting to be inspected. Figures 1 and 2 were changed

to show the inspection area. In addition, references to FAA NPRM 2007-NM-109-AD have been added.

Revision 2 was sent to remove airplanes after line number 717 from the service bulletin effectivity. The

inspections shown in this service bulletin are not necessary on airplanes line number 718 and on, which

have redesigned elevator actuator fittings installed during production.

Revision 3 is sent to clarify the access and restoration instructions; and clarify the words "date on this

service bulletin" and provide terminating action information in the compliance tables.

These sections were changed:

1. In Table 1 of Paragraph 1.E., Compliance, the words "date on this service bulletin" was changed

to "original issue date of this service bulletin."

2. In Tables 1 and 2 of Paragraph 1.E., Compliance, terminating action information for the inspection

requirements as given in this service bulletin was added. Also clarified the action "Replace any

cracked fitting" and condition "Replaced Fittings" by referencing Paragraph 3.B., PART 4.

3. In Paragraph 1.J., References, added 777 Aircraft Maintenance Manual (AMM) 12-12-01 and

27-31-09. Deleted the reference 777 AMM 55-27-01. Also added Boeing Service Bulletin

777-55A0016.

4. In Paragraph 1.K., Publications Affected, damage tolerance evaluation statement was added.

5. In Paragraph 3.A., General Information, added a note to give an option to change the sequence

of steps in Paragraph 3.B., Work Instructions.

6. In Paragraph 3.B., Work Instructions, the words "refer to" are added and deleted the words "as

given in" to address PART 3 and PART 5.

7. In PART 3 and PART 5 of Paragraph 3.B., Work Instructions, procedure from 777 AMM 27-31-09

was added to clarify the access and restoration instructions to have the elevator in the "up" position

instead of "down" position. Also rearranged access and restoration instructions to have the access

panel removed first for access and installed last for restoration.

Boeing Service Related Problem (SRP) 777-SRP-55-0040 is related to this service bulletin.

D. Description

Get access to the elevator actuator fittings at left and right Elevator Stations 169.79 and 194.79. Do

surface HFEC or dye penetrant inspections of the actuator fittings for cracks. If cracks are found, replace

the cracked fittings with new fittings of the same part number or an approved optional part number. Do

the inspections again at the times given in Paragraph 1.E., Compliance, Table 2.

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BOEING SERVICE BULLETIN 777-55A0015
Airplanes line number 718 and on have redesigned elevator actuator fittings installed during production.

Revision 3 - No more work is necessary on airplanes changed as shown in the original issue, Revision

1, or Revision 2 of this service bulletin. Continue to do repeat inspections as given in Revision 3.

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

Group 1:

Affected Maintenance Zones

Model Zone

777-200 336, 346

Group 2:

Affected Maintenance Zones

Model Zone

777-200, 777-200LR, 777-300, 336, 346

777-300ER

E. Compliance

Boeing recommends that the inspection given in this service bulletin be done at the times given in the

table that follows:

Table 1: Elevator Actuator Fitting Initial Inspection

Condition Action (a) Compliance Time

Within 90 days after the original

issue date of this service bulletin.

Do a HFEC or dye-penetrant inspection of the elevator actuator

fittings for any crack as given in

Paragraph 3.B., Part 1.

All airplanes with 14,000 total flightcycles or more as of the original issue date of this service bulletin

Within 12 months after the original

issue date of this service bulletin,

or within 90 days after the airplane reaches 14,000 total flightcycles, whichever occurs first.

Do a HFEC or dye-penetrant inspection of the elevator actuator

fittings for any crack as given in

Paragraph 3.B., Part 1.

All airplanes with 10,000 total flightcycles or more, but less than 14,000

total flight-cycles, as of the original

issue date of this service bulletin

Before 10,000 total flight-cycles

or within 12 months after the

original issue date of this service

bulletin, whichever occurs later.

Do a HFEC or dye-penetrant inspection of the elevator actuator

fittings for any crack as given in

Paragraph 3.B., Part 1.

All airplanes with less than 10,000

total flight-cycles as of the original

issue date of this service bulletin

Do a HFEC, dye-penetrant, or As given in Table 2

detailed inspection of uncracked

elevator actuator fittings for any

crack as given in Table 2.

Fittings found not cracked during

inspection

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BOEING SERVICE BULLETIN 777-55A0015
Table 1: Elevator Actuator Fitting Initial Inspection

Condition Action (a) Compliance Time

Replace any cracked fitting with Before further flight.

a new fitting of the same part

number as given in Paragraph

3.B., Part 4.

Fittings found cracked during inspection

Do a HFEC, dye-penetrant, or As given in Table 2

detailed inspection of uncracked

elevator actuator fittings for any

crack as given in Table 2.

Replaced cracked fitting with a new

fitting of the same part number as

given in Paragraph 3.B., Part 4.

(a) Boeing Service Bulletin 777-55A0016 gives instructions to replace the existing elevator actuator fitting

assemblies with a new and improved actuator fitting assemblies. As an alternative, accomplishment

of Boeing Service Bulletin 777-55A0016 is terminating action for the inspection requirements as

given in this service bulletin.

Table 2: Elevator Actuator Fitting Repeat Inspections

Repeat Interval

(Not to Exceed)

Condition Action (c) Compliance Time

Within 1,200 flight- -

cycles after the initial inspection given

in Table 1.

Do a HFEC, dye penetrant, or detailed

inspection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 2.

Fittings previously inspected

using HFEC as given in Table 1

Within 1,000 flight- -

cycles after the initial inspection given

in Table 1.

Do a HFEC, dye penetrant, or detailed

inspection of the elevator actuator fittings for any crack as given in Paragraph 3.B., Part 2.

Fittings previously inspected

using dye penetrant as given

in Table 1

Within 10,000 flight- -

cycles after the fitting was replaced, if

a new fitting was installed.

Do a HFEC, dye penetrant, or detailed

inspection of the replaced fittings for

any crack as given in Paragraph 3.B.,

Part 2.

Fittings previously replaced

with a new fitting of the same

part number as given in

Paragraph 3.B., Part 4, as

given in Table 1

350 flight-cycles af- 350 flight-cycles

ter the last detailed

inspection

Do a detailed inspection of the uncracked elevator actuator fittings for

any crack as given in Paragraph 3.B.,

Part 2. (a)

Fittings found not cracked

during the repeat inspection

1,000 flight-cycles1,000 flight-cycles

after the last dye

penetrant inspection

Do a dye penetrant inspection of the

uncracked elevator actuator fittings for

any crack as given in Paragraph 3.B.,

Part 2. (a)

1,200 flight-cycles

1,200 flight-cycles

after the last HFEC

inspection

Do a HFEC inspection of the uncracked elevator actuator fittings for

any crack as given in Paragraph 3.B.,

Part 2. (a)

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BOEING SERVICE BULLETIN 777-55A0015
Table 2: Elevator Actuator Fitting Repeat Inspections

Repeat Interval

(Not to Exceed)

Condition Action (c) Compliance Time

Replace any cracked fitting with a new Before further flight. -

fitting of the same part number as given in Paragraph 3.B., Part 4.

Fittings found cracked during

the repeat inspection

10,000 flight-cycles (b)

after the fitting was

replaced, if a new

fitting was installed.

Do a HFEC, dye penetrant, or detailed

inspection of the replaced fittings for

any crack as given in Paragraph 3.B.,

Part 2.

Replaced Fittings with a new

fitting of the same part number as given in Paragraph

3.B., Part 4

(a) Do any one of the optional detailed, dye penetrant, or HFEC inspections at the time and repeat interval

shown.

(b) Do repeated inspections of the replaced fittings at the intervals specified above for fittings found not

cracked.

(c) Boeing Service Bulletin 777-55A0016 gives instructions to replace the existing elevator actuator fitting

assemblies with a new and improved actuator fitting assemblies. As an alternative, accomplishment of

Boeing Service Bulletin 777-55A0016 is terminating action for the inspection requirements as given in

this service bulletin.

Federal Aviation Administration (FAA) Airworthiness Directive 2007-26-05, Amendment 39-15307 is

related to this service bulletin.

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.

This SB has been approved by the FAA. In addition, the manager of the Seattle Aircraft Certification

Office (ACO) approves the inspection procedures and methods with the corresponding compliance

times, as well as the added optional replacement of the existing fittings with the new, improved fatigue

details fittings per SB 777-55A0016 as terminating action for the inspection requirements, specified in

Table 1 and Table 2 under Paragraph 1.E. "Compliance," of SB 777-55A0015, Revision 3 - Stabilizers

- Elevator Attach Fittings - Elevator Actuator Fitting Assembly inspection as an AMOC to the inspection

methods and corresponding compliance times specified in Table 1 and Table 2, under paragraph 1.E.,

"Compliance," of SB 777-55A0015, Revision Original Issue, dated April 19, 2007; required by paragraph

(f) of AD 2007-26-05. All provisions of AD 2007-26-05 that are not specified referenced in the preceding

sentence remain fully applicable and must be complied with.

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Furthermore, the manager of the Seattle Aircraft Certification Office (SACO) approves the incorporation

of Boeing PRR 62777-59S as an AMOC to the inspection and replacement requirements of paragraph

(f) of AD 2007-26-05.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to inspect the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Number of Task Hours Elapsed Hours

Persons

Task

Open Access 2 3 1.5

Figure 1 2 3.5 1.75

Close Access 2 3 1.5

TOTAL FOR EACH AIRPLANE 9.5 4.75

Number of Task Hours Elapsed Hours

Persons

Task

Open Access 2 3 1.5

Figure 2 2 3.5 1.75

Close Access 2 3 1.5

TOTAL FOR EACH AIRPLANE 9.5 4.75

NOTE: More time will be necessary for fitting replacement if cracks are found.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

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J. References

1. Existing Data:

a. 777 Aircraft Maintenance Manual (AMM) 12-12-01, 27-31-09 , 27-31-10, 29-11-00

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

c. 777 Structural Repair Manual (SRM) Chapter 51

d. Component Maintenance Manual (CMM) 55-20-23, 55-20-24

e. Service Related Problem (SRP) 777-SRP-55-0040

f. Standard Overhaul Practices Manual (SOPM) 20-20-02

g. FAA AD 2007-26-05, Amendment 39-15307

h. Boeing Service Bulletin 777-55A0016

2. Data supplied with this Service Bulletin:

None.

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

None.

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

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each

Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin

does not show the Boeing price and supply data.

B. Industry Support Information

Boeing warranty remedies are available for 777 airplanes in warranty as of November 17, 2006. 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 and parts

are required, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. Please refer

to this service bulletin number and reference the airplane variable number in your purchase order.

C. Parts Necessary For Each Airplane

1. Kits/Parts:

None.

2. Parts and Materials Supplied by the Operator:

NOTE: The parts that follow may be necessary if cracked fittings are found. The number in the

QTY column is the maximum number of parts that may be necessary for one airplane.

Group 1:

Part Number QTY Name Existing Part Number Notes

Outboard Elevator Actuator Fit- 183W1300-1 (a)

ting Assembly - Left Side

183W1300-5 1

Outboard Elevator Actuator Fit- 183W1300-2 (b)

ting Assembly - Right Side

183W1300-6 1

Inboard Elevator Actuator Fit- 183W1300-3 (c)

ting Assembly - Left Side

183W1300-7 1

Inboard Elevator Actuator Fit- 183W1300-4 (d)

ting Assembly - Right Side

183W1300-8 1

(a) 183W1300-1 is optional to 183W1300-5.

(b) 183W1300-2 is optional to 183W1300-6.

(c) 183W1300-3 is optional to 183W1300-7.

(d) 183W1300-4 is optional to 183W1300-8.

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BOEING SERVICE BULLETIN 777-55A0015
Group 2:

Part Number QTY Name Existing Part Number Notes

Outboard Elevator Actuator Fit- 183W1312-1 (a)

ting Assembly - Left Side

183W1312-5 1

Outboard Elevator Actuator Fit- 183W1312-2 (b)

ting Assembly - Right Side

183W1312-6 1

Inboard Elevator Actuator Fitting 183W1322-1 (c)

Assembly - Left Side

183W1322-5 1

Inboard Elevator Actuator Fitting 183W1322-2 (d)

Assembly - Right Side

183W1322-6 1

(a) 183W1312-1 is optional to 183W1312-5.

(b) 183W1312-2 is optional to 183W1312-6.

(c) 183W1322-1 is optional to 183W1322-5.

(d) 183W1322-2 is optional to 183W1322-6.

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 777-55A0015
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

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

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

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

OTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

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

— Linear dimensions are in inches

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

or minus 0.03 inch.

— Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

— Angular tolerance is plus or minus 2 degrees

— Hole dimensions for standard solid rivets are given in 777 SRM, Chapter 51

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

4. These work instructions refer to procedures included on 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.

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. 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.

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BOEING SERVICE BULLETIN 777-55A0015
B. WORK INSTRUCTIONS

PART 1 - INITIAL INSPECTION

1. Get access. Refer to PART 3 as an accepted procedure.

2. Do surface High Frequency Eddy Current (HFEC) or dye penetrant inspections of the elevator

actuator fittings as given in Figure 1.

3. If any cracked fitting is found, replace the cracked fitting as given in PART 4. After fitting

replacement, start to do inspections of any replaced fitting as given in PART 1 at the time given

in Paragraph 1.E., Compliance.

4. Restore access. Refer to PART 5 as an accepted procedure.

5. Put the airplane back in a serviceable condition. Do repeat inspections of uncracked fittings as

given in PART 2 at the times given in Table 2 of Paragraph 1.E., Compliance.

PART 2 - REPEAT INSPECTION

1. Get access. Refer to PART 3 as an accepted procedure.

2. Do surface High Frequency Eddy Current (HFEC), dye penetrant, or detailed inspections of the

elevator actuator fittings as given in Figure 2.

3. If any cracked fitting is found, replace the affected fitting as given in PART 4. After fitting

replacement, start to do inspections of any replaced fitting as given in PART 1 at the time given

in Paragraph 1.E., Compliance.

4. Restore access. Refer to PART 5 as an accepted procedure.

5. Put the airplane back in a serviceable condition. Do repeat inspections of uncracked fittings as

given in PART 2 at the times given in Table 2 of Paragraph 1.E., Compliance.

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BOEING SERVICE BULLETIN 777-55A0015
PART 3 - ACCESS

1. On the left horizontal stabilizer, remove and keep access panels 335EB, 335FB (or 335EXB), and

335RB (or 335RBX) for access to the elevator actuator fittings.

2. On the right horizontal stabilizer, remove and keep access panels 345EB, 345FB (or 345EXB),

and 345RB (or 345RBX) for access to the elevator actuator fittings.

WARNING: YOU MUST PREVENT ALL POSSIBLE OPERATION OF THE HORIZONTAL STABILIZER

WHEN YOU WORK ON OR NEAR IT. THE HORIZONTAL STABILIZER MOVES QUICKLY

AND WITH FORCE. IF THE STABILIZER MOVES WHEN PERSONS ARE IN THE

TORSION BOX COMPARTMENT OR NEAR THE STABILIZER, YOU CAN CAUSE

INJURY TO THEM.

WARNING: MAKE SURE THAT PERSONNEL AND EQUIPMENT ARE CLEAR OF THE ELEVATOR

SURFACES BEFORE YOU REMOVE HYDRAULIC PRESSURE TO THE PCUS. WHEN

YOU REMOVE HYDRAULIC PRESSURE, THE SURFACE WILL LOWER SLOWLY.

ACCIDENTAL MOVEMENT OF ELEVATOR SURFACES CAN CAUSE INJURIES TO

PERSONNEL AND DAMAGE TO EQUIPMENT.

3. Refer to one of the following methods as an accepted procedure to prevent all possible operation

of the horizontal stabilizer and the elevator assembly:

NOTE: The procedure that follows is from 777 AMM 27-31-09.

a. Do these steps to move the elevator up manually:

(1) Depressurize the hydraulic system and reservoir. Refer to 777 AMM 29-11-00 as an

accepted procedure.

(2) Operate the control column several times to remove the remaining hydraulic pressure.

(3) On the P61 panel, move the FLT CONTROL HYD VALVE POWER - TAIL switches to

the SHUT OFF position.

(4) Open these circuit breakers and install safety tags:

Left Power Management Panel, P110

Row Col Number Name

K 27 C27609 ELEV PCU RIB(BLK)/ROB(BYP)

Power Supply Assembly Center, M24301

Row Col Number Name

A 7 CBA7-C ELEV PCU

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Power Supply Assembly Left, M24101

Row Col Number Name

A 7 CBA7-L ELEV PCU LIB (BLK) LOB (BYP)

Power Supply Assembly Right, M24201

Row Col Number Name

A 7 CBA7-R ELEV PCU

(5) Operate the manual bypass valve on the two elevator Power Control Units (PCUs):

(a) Install the elevator PCU bypass pin, SPL-1708, on the manual bypass valves on the

two elector PCUs.

(b) Push the trailing edge of the elevator up.

NOTE: The elevator will only move slowly because of the resistance in the PCUs.

(6) Install the rudder and elevator power control unit lock, SPL-1712, on one of the elevator

PCUs.

(7) Remove the elevator PCU bypass pin, SPL-1708, from the manual bypass valves.

CAUTION: BEFORE YOU USE THIS PROCEDURE, MAKE SURE THAT THERE IS NO LOCK

INSTALLED ON ANY OF THE ELEVATOR PCUS. THE PCUS CAN BE DAMAGED

IF HYDRAULIC POWER IS SUPPLIED WHEN THE LOCKS ARE INSTALLED ON

THEM.

b. Do these steps to move the elevator up with hydraulic power:

(1) Make sure the PRIMARY FLIGHT COMPUTER switch (on the overhead panel, P5) is in

the AUTO position.

(2) Move and hold the Captain's or the First Officer's control column full aft to put the elevators

in the up position.

(3) Open these circuit breakers and install safety tags:

Left Power Management Panel, P110

Row Col Number Name

K 27 C27609 ELEV PCU RIB(BLK)/ROB(BYP)

Power Supply Assembly Center, M24301

Row Col Number Name

A 7 CBA7-C ELEV PCU

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Power Supply Assembly Left, M24101

Row Col Number Name

A 7 CBA7-L ELEV PCU LIB (BLK) LOB (BYP)

Power Supply Assembly Right, M24201

Row Col Number Name

A 7 CBA7-R ELEV PCU

(4) On the P61 panel, move the FLT CONTROL HYD VALVE POWER - TAIL switches to

the SHUT OFF position.

(5) Depressurize the hydraulic system and reservoir. Refer to 777 AMM 29-11-00 as an

accepted procedure.

(6) Operate the control column several times to remove the remaining hydraulic pressure.

(7) Release the control column.

(8) Make sure that there is no elevator movement.

WARNING: MAKE SURE THE CIRCUIT BREAKERS FOR THE PCUS ARE OPEN AND

HYDRAULIC POWER FOR THE ELEVATOR PCUS IS REMOVED BEFORE

YOU INSTALL THE SAFETY LOCKS. IF THE CIRCUIT BREAKERS FOR THE

PCUS ARE CLOSED, THE ELEVATOR CAN FALL WHILE YOU INSTALL THE

SAFETY LOCKS. IF HYDRAULIC POWER FOR THE PCUS IS ON, THE

ELEVATOR CAN MOVE DOWN VERY FAST WHILE YOU INSTALL THE

SAFETY LOCKS. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE

EQUIPMENT.

(9) Install the rudder and elevator power control unit lock, SPL-1712, on one of the elevator

PCUs.

PART 4 - FITTING REPLACEMENT

1. Remove the affected elevator. Refer to 777 AMM 27-31-10 as an accepted procedure.

2. Group 1:

Replace any cracked fitting with a new fitting of the same part number as given in CMM 55-20-23

or an approved optional part number.

3. Group 2:

Replace any cracked fitting with a new fitting of the same part number as given in CMM 55-20-24

or an approved optional part number.

4. Install the elevator. Refer to 777 AMM 27-31-10 as an accepted procedure.

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BOEING SERVICE BULLETIN 777-55A0015
PART 5 - RESTORE ACCESS

1. Refer to the following steps an accepted procedure to restore access:

NOTE: These steps are from 777 AMM 27-31-09.

a. Remove the rudder and elevator power control unit lock, SPL-1712.

b. Remove the safety tags and close these circuit breakers:

Left Power Management Panel, P110

Row Col Number Name

K 27 C27609 ELEV PCU RIB(BLK)/ROB(BYP)

Power Supply Assembly Center, M24301

Row Col Number Name

A 7 CBA7-C ELEV PCU

Power Supply Assembly Left, M24101

Row Col Number Name

A 7 CBA7-L ELEV PCU LIB (BLK) LOB (BYP)

Power Supply Assembly Right, M24201

Row Col Number Name

A 7 CBA7-R ELEV PCU

c. Pressurize the main hydraulic system. Refer to 777 AMM 29-11-00 as an accepted procedure.

d. On the P61 panel, move the FLT CONTROL HYD POWER - TAIL switches to the NORM

position.

e. Fill the hydraulic reservoir as needed. Refer to 777 AMM 12-12-01 as an accepted procedure.

2. Install the access panels that were removed for access to the elevator actuator fittings.

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BOEING SERVICE BULLETIN 777-55A0015
FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015
FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015
FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

number shown below is the number of areas affected for each actuator fitting. There are a total of four affected

actuator fittings on each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

For cracks at locations where the

fitting transitions into the upper

and lower flanges. Use surface

HFEC, as given in 777 NDT,

Part 6, 51-00-01, Procedure 1 or

2 or dye penetrant as given in

SOPM 20-20-02.

1 Inspect Actuator Fitting - 8

For cracks at the fitting edge.

Use surface HFEC, as given in

777 NDT, Part 6, 51-00-01, Procedure 1 or 2 or dye penetrant

as given in SOPM 20-20-02.

2 Inspect Actuator Fitting - 2

FIGURE 1: ELEVATOR ACTUATOR FITTING INITIAL INSPECTION

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015
FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015
FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015
FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

number shown below is the number of areas affected for each actuator fitting. There are a total of four affected

actuator fittings on each airplane.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

For cracks at locations where the

fitting transitions into the upper

and lower flanges. Use surface

HFEC as given in 777 NDT, Part

6, 51-00-01, Procedure 1 or 2,

dye penetrant as given in SOPM

20-20-02, or a detailed inspection

1 Inspect Actuator Fitting - 8

For cracks at the fitting edge.

Use surface HFEC, as given in

777 NDT, Part 6, 51-00-01, Procedure 1 or 2 or dye penetrant

as given in SOPM 20-20-02.

2 Inspect Actuator Fitting - 2

FIGURE 2: ELEVATOR ACTUATOR FITTING REPEAT INSPECTION

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 777-55A0015