# Boeing Alert Service Bulletin 777-57A0064: Revision 1

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- Document: [Boeing Alert Service Bulletin 777-57A0064](https://openairdocs.org/service-documents/boeing/777-57a0064.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 104
- PDF: https://openairdocs.org/files/sha256/c3/67/c367266f5be7178cc6e0814cc943372ab73bbc8e2ddb9630df07d287f5d0490b
- Page: https://openairdocs.org/service-documents/boeing/777-57a0064/file/c367266f5be7

## Text

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### Page 1

Commercial 
Airplanes
777
Service Bulletin
Number: 777-57A0064
Original Issue: March 26, 2009
Revision 1: May 06, 2010
ATA System: 5741 2781
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge - Outboard Slat
Main Track Downstop Assembly and Slat Can - Inspection, Repair And Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2009 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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2.0

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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 3
A. Effectivity ............................................... 1 3
1. Airplanes ............................................ 1 3
2. Spares Affected ........................................ 1 6
B. Concurrent Requirements ...................................... 1 6
C. Reason ................................................ 1 6
D. Description .............................................. 1 8
E. Compliance .............................................. 1 9
F. Approval ............................................... 2 2
G. Manpower .............................................. 2 3
H. Weight and Balance Changes .................................... 2 6
I. Electrical Load Data ......................................... 2 7
J. References .............................................. 2 7
1. Existing Data .......................................... 2 7
2. Data supplied with this Service Bulletin ............................ 2 7
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 7
K. Publications Affected ........................................ 2 7
L. Interchangeability and Intermixability of Parts ........................... 2 7
2. MATERIAL INFORMATION ........................................ 2 9
A. Material - Price and Availability ................................... 2 9
B. Industry Support Information .................................... 3 1
C. Parts Necessary For Each Airplane ................................. 3 1
1. Kits/Parts ............................................ 3 1
2. Parts and Materials Supplied by the Operator ........................ 3 1
3. Parts Modified and Reidentified ................................ 3 4
4. Parts Removed and Not Replaced .............................. 3 4
D. Parts Necessary to Change Spares ................................. 3 4
E. Special Tooling - Price and Availability ............................... 3 4
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 4
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 5
A. GENERAL INFORMATION ..................................... 3 5
B. WORK INSTRUCTIONS ....................................... 3 6
FIGURE 1: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
[Group 1] ............................................ 4 7
FIGURE 2: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
[Group 1] ............................................ 5 0
FIGURE 3: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
[Group 2] ............................................ 5 3
FIGURE 4: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
[Group 2] ............................................ 5 6
FIGURE 5: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK
[Group 1] ............................................ 5 9
FIGURE 6: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE
CHECK [Group 1] ....................................... 6 2
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FIGURE 7: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK
[Group 2] ............................................ 6 5
FIGURE 8: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE
CHECK [Group 2] ....................................... 6 8
FIGURE 9: LEFT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 1] . 71
FIGURE 10: RIGHT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 1] . 73
FIGURE 11: LEFT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 2] . 75
FIGURE 12: RIGHT WING - OUTBOARD SLATS - MAIN TRACK SLAT CAN - INSPECTION [Group 2] . 77
FIGURE 13: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE -
REPLACEMENT [Group 1] .................................. 7 9
FIGURE 14: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE -
REPLACEMENT [Group 1] .................................. 8 2
FIGURE 15: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE -
REPLACEMENT [Group 2] .................................. 8 5
FIGURE 16: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP FITTING HARDWARE -
REPLACEMENT [Group 2] .................................. 8 8
FIGURE 17: OUTBOARD SLATS - MAIN TRACK SLAT CAN - REPAIR ................. 9 1
FIGURE 18: LEFT WING - OUTBOARD SLAT NUMBER 3 - OUTBOARD MAIN TRACK SLAT CAN -
INSPECTION [Group 2] .................................... 9 3
FIGURE 19: RIGHT WING - OUTBOARD SLAT NUMBER 12 - OUTBOARD MAIN TRACK SLAT CAN -
INSPECTION [Group 2] .................................... 9 5
FIGURE 20: LEFT WING - OUTBOARD SLAT NUMBER 2 AND 3 - OUTBOARD AND INBOARD MAIN
TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT .............. 9 7
FIGURE 21: RIGHT WING - OUTBOARD SLAT NUMBER 12 AND 13 - OUTBOARD AND INBOARD MAIN
TRACK DOWNSTOP FITTING HARDWARE - REPLACEMENT ............. 1 0 0
APPENDIX A: REWORK INSTRUCTIONS - 116W4802-3 AND -4 DOWNSTOP FITTING INTO 116W4802-1
AND -2 DOWNSTOP FITTING ................................ 1 0 3
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Commercial 
Airplanes
777
Service Bulletin
Revision Transmittal SheetNumber: 777-57A0064Original Issue: March 26, 2009
Revision 1: May 06, 2010
ATA System: 5741 2781
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge - Outboard Slat
Main Track Downstop Assembly and Slat Can - Inspection, Repair And Change
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-100-AD, is related to
this service bulletin.
REASON FOR REVISION
1. This revision is sent to:
a. Clarify that the rework limits for weld beads are measured from the slat can surface and do not include
the weld bead height. The weld bead can be blended flush with the can surface before rework limits
apply.
b. Delete the requirement in Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can
Inspection and Outboard and Inboard Main Track Stop Hardware Replacement that required
accomplishment of Part 2 - Slat Main Track Stop Hardware Torque Check. Checking the torque of the
fasteners prior to replacement is not necessary. Failure of Part 2 - Slat Main Track Stop Hardware
Torque Check requires the hardware to be replaced which is already being accomplished.
c. Add note in the General Information section that allows the installation of a fastener with a different
grip length if required to meet SRM requirements. Subsequent to the release of the original issue of
this service bulletin, an operator reported that a different grip length bolt was required to meet SRM
requirements.
In addition, operators have reported difficulty in obtaining BACB30LR4-35 bolts. Boeing has reviewed
and determined that a BACB30LR4-36 bolt with a BACW10BP4APU washer is an acceptable option.
d. Revise incorrect chamfer callout in Appendix A. See Information Notice (IN) IN-01.
e. Verify that a post machining stress relief bake is not required in Appendix A. See Information Notice
(IN) IN-02.
f. Correct the Standard Overhaul Practices Manual (SOPM) in Appendix A for the optional part marking.
See Information Notice (IN) IN-02.
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g. Add scrubbing part with a scotchbrite pad (or equivalent) as an option to solvent cleaning in Appendix
A. See Information Notice (IN) IN-02.
h. Clarify the Part 1 - Slat Track Stop Hardware Installation Inspection action that requires Part 3 - Slat
Can Inspection be accomplished does not apply to the outboard main track locations of slats no. 3 and
12 on Group 1 Airplanes. Subsequent to the release of the original issue of this service bulletin, an
operator requested this clarification be added.
i. Clarify the areas where the slat can repair is applicable by adding commas inadvertantly missing in
the original issue.
j. Clarify in figures 13 through 16 that the downstops can be kept and reinstalled.
k. Clarify the locator in Figure 5 to show the correct locations affected.
l. Add reference to FAA NPRM 2009-NM-100-AD.
m. Updated service bulletin to current requirements.
2. The following sections were changed in this revision:
a. Summary:
(1) Compliance - Add reference to FAA NPRM 2009-NM-100-AD.
b. 1. Planning
(1) Paragraph 1.E., Compliance:
(a) Add reference to FAA NPRM 2009-NM-100-AD.
(b) Table 1 - Clarified that certain main track locations on Group 1 Airplanes do not require Part
3 - Slat Can Inspection.
(2) Paragraph 1.J.1., Existing Data - Added Federal Aviation Administration (FAA) Notice of Proposed
Rule Making NPRM 2009-NM-100-AD. Revised SOPM Callout.
(3) Paragraph 1.K., Publications Affected - Added Damage Tolerance Based Structural Inspections
requirements.
c. 3. Accomplishment Instructions
(1) Paragraph 3.A., General Information:
(a) Note 5 - Added new note allowing installation of a different grip length fastener if required to
meet SRM requirements.
(2) Paragraph 3.B., Work Instructions:
(a) Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and
Outboard and Inboard Main Track Stop Hardware Replacement
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1) Step 4 - Deleted requirement to do Part 2 - Slat Main Track Stop Hardware Torque Check.
(b) FIGURE 5:
1) Illustration - Clarified locator to show correct locations affected.
(c) FIGURE 13:
1) Step Table - Clarified that downstop fittings can be kept in step 1.
(d) FIGURE 14:
1) Step Table - Clarified that downstop fittings can be kept in step 1.
(e) FIGURE 15:
1) Step Table - Clarified downstop fittings can be kept in step 1. Clarified that kept downstop
fittings can be installed in step 2.
(f) FIGURE 16:
1) Step Table - Clarified downstop fittings can be kept in step 1. Clarified that kept downstop
fittings can be installed in step 2.
(g) FIGURE 17:
1) Illustration - Deleted extra circle note 4 not used in step table.
2) Step Table - Clarified the areas where the slat can repair is applicable by adding commas.
Clarify rework limits at weld bead.
(h) FIGURE 20:
1) Step Table - Added optional bolt and washer in step 2.
(i) FIGURE 21:
1) Step Table - added optional bolt and washer in step 2.
d. APPENDIX A:
(1) Illustration - Revised Chamfer callout.
(2) Step Table
(a) Step 1 and 2 - Verified that post machining stress relief bake is not required. Revised SOPM
callout to the correct callout for part marking.
(b) Step 3 - Added scrubbing with scotchbrite (or equivalent) as an option to solvent cleaning.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
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Pages with no vertical lines have no important changes.
REVISION HISTORY
March 26, 2009Original Issue:
May 06, 2010Revision 1:
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Commercial 
Airplanes
777
Service Bulletin
SummaryNumber: 777-57A0064Original Issue: March 26, 2009
Revision 1: May 06, 2010
ATA System: 5741 2781
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge - Outboard Slat
Main Track Downstop Assembly and Slat Can - Inspection, Repair And Change
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Paragraph 1.E., Compliance
Accomplishment of the inspections and changes in this service bulletin will help detect and prevent damage to
the outboard slat main track slat cans. Damage to the outboard slat main track slat cans can allow fuel leakage
into the fixed wing leading edge in excess of the capacity of the drainage system. The fuel leakage from the
excess fuel could result in an uncontained fire.
Each outboard slat main track has a downstop attached to the aft end of the slat track assembly. The downstop
consists of two fittings that are secured to the track with a bolt and nut. The main tracks travel through holes in
the front spar web when the slat is retracted. In areas of the wing where fuel is stored, a slat can is installed on
the wet side of the spar to surround the main track and contain the fuel. One operator reported finding a hole in
the inboard main track slat can for outboard slat number 12. The hole was caused when the bolt securing the
downstop migrated out of the fitting and contacted the slat can. It is believed the locking element of the nut was
not fully engaged and the nut securing the bolt backed off and allowed the bolt to migrate. In addition, in production
it was discovered that a downstop was contacting the weld on a slat can at the outboard main track location on
slat numbers 3 and 12. This contact could cause wear damage and eventually a hole in the slat can. Holes in
the slat can can allow fuel leakage into the wing fixed leading edge. It is possible that the hole could be large
enough to alow fuel leakage in excess of the capacity of the drainage provisions in the fixed leading edge. The
excess fuel leakage could result in an uncontained fire.
Inspections of the bolt, nut, and downstop will ensure that parts are correctly installed and prevent the bolt from
migrating out and puncturing the slat can. Replacement of the hardware will ensure that parts are correctly
installed. Inspection of the slat can will ensure that there are no holes or wear damage that could result in a hole
in the slat can.
Boeing Service Related Problem (SRP) 777-SRP-57-0219 is related to this service bulletin.
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ACTION (PRR 62777-63S)
Part 1 - Slat Track Stop Hardware Installation Inspection
Extend the slats. Remove or open the fixed leading edge access panels at each of the affected outboard slat
main track locations. Do a Detailed inspection (DET) of the stop hardware at the end of each track to determine
if the stop is installed and the thread protrusion from the nut is within limits. Install or close the fixed leading
edge access panels. Retract the slats.
Part 2 - Slat Main Track Stop Hardware Torque Check
Extend the slats. Remove or open the fixed leading edge access panels at each of the affected outboard slat
main track locations. Measure the torque of the nuts to determine if the the nut is shanked out on the bolt. Install
or close the fixed leading edge access panels. Retract the slats.
Part 3 - Slat Can Inspection
Do a Detailed inspection (DET) of the slat can for holes and gouges.
Part 4 - Stop Hardware Replacement
Replace the bolt and nut, and the stop fitting if required.
Part 5 - Slat Can Repair
Remove the slat at the affected main track location. Remove the slat main track at the affected main track
location. Blend out gouges and wear damage as required. Install the slat main tracks. Install the Slat
Part 6 - Slat Can Replacement
Drain and purge the outboard main tanks and prepare for entry. Remove the lower wing access panel in the
wing rib bay which the affected slat can is located. Remove the slat at the affected main track location. Remove
the slat main track at the affected main track location. Replace the slat can. Install the lower wing access panel.
Install the slat main tracks. Install the Slat
Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and Inboard
Main Track Stop Hardware Replacement
Extend the slats. Remove or open the fixed leading edge access panels at each of the outboard slats number
3 and 12 outboard and inboard main track locations. Do a DET of the slat cans at the outboard slat number 3
and 12 outboard main track locations for holes and wear damage. Replace the downstop hardware for the
outboard slats number 3 and 12 outboard and inboard main track locations. Install or close the fixed leading
edge access panels. Retract the slats.
EFFECTIVITY
777-200, -200LR, -300, -300ER Airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-100-AD, is related to
this service bulletin.
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See Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of April 9, 2008. Please refer to Paragraph
2.B., Industry Support Information.
MANPOWER
Group 1:
Elapsed
Hours
Total Task
Hours
1.7517.50Part 1 - Slat Track Stop Hardware Installation Inspection
4.2014.70Part 2 - Slat Main Track Stop Hardware Torque Check
7.007.00Part 3 - Slat Can Inspection
0.30 (a)0.30 (a)Part 4 - Stop Hardware Replacement
8.00 (b)12.00 (b)Part 5 - Slat Can Repair
14.50 (b)30.50 (b)Part 6 - Slat Can Replacement
(a) Estimate is for hardware replacement for each main track location.
(b) Estimate is for each slat can.
Group 2:
Elapsed
Hours
Total Task
Hours
9.0021.00Part 1 - Slat Track Stop Hardware Installation Inspection
4.9016.90Part 2 - Slat Main Track Stop Hardware Torque Check
9.009.00Part 3 - Slat Can Inspection
0.30 (a)0.30 (a)Part 4 - Stop Hardware Replacement
8.00 (b)12.00 (b)Part 5 - Slat Can Repair
14.50 (b)30.50 (b)Part 6 - Slat Can Replacement
4.508.00Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main
Track Slat Can Inspection and Outboard and Inboard
Main Track Stop Hardware Replacement
(a) Estimate is for hardware replacement for each main track location.
(b) Estimate is for each slat can
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
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BOEING SERVICE BULLETIN 777-57A0064
Refer to Paragraph 2.A., Material - Price and Availability
SLAT SLAT
7 LOCATIONS  6  5  SLAT
4  SLAT
SLAT
2  SLAT
GROUP 2
AIRPLANES ONLY
SLATS 1-6 SHOWN,
SLATS 9-14 OPPOSITE  PART 3:
DO A DET OF THE SLAT CAN FOR DAMAGE.
PART 5:
REPAIR GOUGES IN THE SLAT CAN.
PART 6:
REPLACE THE SLAT CAN.
PART 7:
GROUP 2 AIRPLANES: DO A DET OF THE OUT-
BOARD MAIN TRACK SLAT CAN FOR SLATS
NUMBERS 3 AND 12 FOR HOLES OR WEAR
DAMAGE. REPLACE THE DOWNSTOP HARDWARE
AT SLAT NUMBERS 3 AND 12 INBOARD AND
OUTBOARD MAIN TRACK LOCATIONS.
PART 1:
DO A DET TO DETERMINE IF THE
DOWNSTOP AND HARDWARE ARE
INSTALLED AND THE BOLT THREAD
PROTRUSION IS WITHIN LIMITS.
PART 2:
MEASURE THE TORQUE OF
THE NUT OF THE DOWN
STOP ATTACH HARDWARE.
PART 4:
REPLACE THE DOWNSTOP
HARDWARE
WD
TYPICAL MAIN TRACK LOCATION
FWD
A-A  1673711
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Revision 1: May 06, 2010  777-57A0064
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Commercial 
Airplanes
777
Service Bulletin
Number: 777-57A0064
Original Issue: March 26, 2009
Revision 1: May 06, 2010
ATA System: 5741 2781
SUBJECT: WINGS - Leading Edge and Leading Edge Devices - Leading Edge - Outboard Slat
Main Track Downstop Assembly and Slat Can - Inspection, Repair And Change
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below. An equivalent change is on subsequent
production airplanes. Refer to PRR 62777-63S for data about this change.
Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
777-200, and -300 Airplanes line numbers 1 through 730. These
airplanes have slat cans at the following main track locations:
outboard slat numbers 4, 5, 6, 9, 10, and 11 (inboard and outboard
main tracks) and slats 3 and 12 (inboard main track only).
-1
777-200LR and -300ER Airplanes line numbers 423 through 729.
These airplanes have slat cans at the following main track locations:
outboard slat numbers 2, 3, 4, 5, 6, 9, 10, 11, 12, and 13 (inboard
and outboard main tracks).
-2
Airplane Models:
777-200, 777-200LR, 777-300, 777-300ER
GroupVariable Number
1WA001 - WA017
1WA076 - WA080
1WA086 - WA093
1WA101 - WA104
1WA116 - WA119
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GroupVariable Number
1WA131 - WA137
1WA171 - WA175
1WA196 - WA198
1WA206 - WA212
1WA221 - WA223
1WA231 - WA232
1WA241 - WA250
1WA261 - WA266
1WA281 - WA283
1WA301 - WA304
1WB001 - WB021
1WB031 - WB046
1WB051 - WB088
1WB101 - WB106
1WB121 - WB125
1WB131 - WB148
1WB151 - WB155
1WB161 - WB177
1WB181 - WB194
1WB201 - WB215
1WB231 - WB247
1WB271 - WB273
1WB276 - WB286
1WB291 - WB302
1WB306 - WB307
1WB311 - WB337
1WB341 - WB342
1WB366 - WB368
1WB371 - WB388
1WB406
1WB411 - WB413
1WB416 - WB439
1WB446 - WB453
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GroupVariable Number
1WB476
1WB481 - WB484
1WB501 - WB512
1WB531 - WB537
1WB551 - WB554
1WB591 - WB597
1WB601 - WB606
1WB611 - WB622
1WB631 - WB638
1WB646 - WB649
1WC051 - WC073
1WC101 - WC104
1WC111 - WC119
1WC221 - WC222
1WC241 - WC243
1WC281 - WC290
1WC301 - WC308
1WC361 - WC364
1WC371 - WC374
1WC381 - WC395
1WC441
1WC446 - WC449
1WC456 - WC459
1WC486 - WC493
1WC506 - WC508
1WC521 - WC522
1WC531 - WC536
1WC546 - WC548
1WC556
1WC566 - WC567
2WD001 - WD002
2WD011 - WD015
2WD031 - WD036
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GroupVariable Number
2WD046 - WD050
2WD066 - WD067
2WD501 - WD508
2WD521 - WD539
2WD546 - WD552
2WD561 - WD572
2WD581 - WD594
2WD606 - WD609
2WD621 - WD632
2WD651 - WD660
2WD671 - WD675
2WD691 - WD708
2WD741 - WD749
2WD761 - WD770
2WD786 - WD788
2WD796 - WD803
2WD826 - WD830
2WD846 - WD850
2WD871 - WD872
2WD911 - WD912
2WD936
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of the inspections and changes in this service bulletin will help detect and prevent
damage to the outboard slat main track slat cans. Damage to the outboard slat main track slat cans
can allow fuel leakage into the fixed wing leading edge in excess of the capacity of the drainage system.
The fuel leakage from the excess fuel could result in an uncontained fire.
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Each outboard slat main track has a downstop attached to the aft end of the slat track assembly. The
downstop consists of two fittings that are secured to the track with a bolt and nut. The main tracks travel
through holes in the front spar web when the slat is retracted. In areas of the wing where fuel is stored,
a slat can is installed on the wet side of the spar to surround the main track and contain the fuel. One
operator reported finding a hole in the inboard main track slat can for outboard slat number 12. The
hole was caused when the bolt securing the downstop migrated out of the fitting and contacted the slat
can. It is believed the locking element of the nut was not fully engaged and the nut securing the bolt
backed off and allowed the bolt to migrate. In addition, in production it was discovered that a downstop
was contacting the weld on a slat can at the outboard main track location on slat numbers 3 and 12.
This contact could cause wear damage and eventually a hole in the slat can. Holes in the slat can can
allow fuel leakage into the wing fixed leading edge. It is possible that the hole could be large enough
to alow fuel leakage in excess of the capacity of the drainage provisions in the fixed leading edge. The
excess fuel leakage could result in an uncontained fire.
Inspections of the bolt, nut, and downstop will ensure that parts are correctly installed and prevent the
bolt from migrating out and puncturing the slat can. Replacement of the hardware will ensure that parts
are correctly installed. Inspection of the slat can will ensure that there are no holes or wear damage
that could result in a hole in the slat can.
Boeing Service Related Problem (SRP) 777-SRP-57-0219 is related to this service bulletin.
1. This revision is sent to:
a. Clarify that the rework limits for weld beads are measured from the slat can surface and do
not include the weld bead height. The weld bead can be blended flush with the can surface
before rework limits apply.
b. Delete the requirement in Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat
Can Inspection and Outboard and Inboard Main Track Stop Hardware Replacement that
required accomplishment of Part 2 - Slat Main Track Stop Hardware Torque Check. Checking
the torque of the fasteners prior to replacement is not necessary. Failure of Part 2 - Slat Main
Track Stop Hardware Torque Check requires the hardware to be replaced which is already
being accomplished.
c. Add note in the General Information section that allows the installation of a fastener with a
different grip length if required to meet SRM requirements. Subsequent to the release of the
original issue of this service bulletin, an operator reported that a different grip length bolt was
required to meet SRM requirements.
In addition, operators have reported difficulty in obtaining BACB30LR4-35 bolts. Boeing has
reviewed and determined that a BACB30LR4-36 bolt with a BACW10BP4APU washer is an
acceptable option.
d. Revise incorrect chamfer callout in Appendix A. See Information Notice (IN) IN01.
e. Verify that a post machining stress relief bake is not required in Appendix A. See Information
Notice (IN) IN02.
f. Correct the Standard Overhaul Practices Manual (SOPM) in Appendix A for the optional part
marking. See Information Notice (IN) IN02.
g. Add scrubbing part with a scotchbrite pad (or equivalent) as an option to solvent cleaning in
Appendix A. See Information Notice (IN) IN02.
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h. Clarify the Part 1 - Slat Track Stop Hardware Installation Inspection action that requires Part
3 - Slat Can Inspection be accomplished does not apply to the outboard main track locations
of slats no. 3 and 12 on Group 1 Airplanes. Subsequent to the release of the original issue of
this service bulletin, an operator requested this clarification be added.
i. Clarify the areas where the slat can repair is applicable by adding commas inadvertantly
missing in the original issue.
j. Clarify in figures 13 through 16 that the downstops can kept and reinstalled.
k. Clarify the locator in Figure 5 to show the correct locations affected.
l. Add reference to FAA NPRM 2009-NM-100-AD.
m. Updated service bulletin to current requirements.
D. Description
Part 1 - Slat Track Stop Hardware Installation Inspection
Extend the slats. Remove or open the fixed leading edge access panels at each of the affected outboard
slat main track locations. Do a Detailed inspection (DET) of the stop hardware at the end of each track
to determine if the stop is installed and the thread protrusion from the nut is within limits. Install or close
the fixed leading edge access panels. Retract the slats.
Part 2 - Slat Main Track Stop Hardware Torque Check
Extend the slats. Remove or open the fixed leading edge access panels at each of the affected outboard
slat main track locations. Measure the torque of the nuts to determine if the the nut is shanked out on
the bolt. Install or close the fixed leading edge access panels. Retract the slats.
Part 3 - Slat Can Inspection
Do a Detailed inspection (DET) of the slat can for holes and gouges.
Part 4 - Stop Hardware Replacement
Replace the bolt and nut, and the stop fitting if required.
Part 5 - Slat Can Repair
Remove the slat at the affected main track location. Remove the slat main track at the affected main
track location. Blend out gouges and wear damage as required. Install the slat main tracks. Install the
Slat
Part 6 - Slat Can Replacement
Drain and purge the outboard main tanks and prepare for entry. Remove the lower wing access panel
in the wing rib bay which the affected slat can is located. Remove the slat at the affected main track
location. Remove the slat main track at the affected main track location. Replace the slat can. Install
the lower wing access panel. Install the slat main tracks. Install the Slat
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Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and
Inboard Main Track Stop Hardware Replacement
Extend the slats. Remove or open the fixed leading edge access panels at each of the outboard slats
number 3 and 12 outboard and inboard main track locations. Do a DET of the slat cans at the outboard
slat number 3 and 12 outboard main track locations for holes and wear damage. Replace the downstop
hardware for the outboard slats number 3 and 12 outboard and inboard main track locations. Install or
close the fixed leading edge access panels. Retract the slats.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of
this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
521, 621777-200, 777-300
Group 2:
Affected Maintenance Zones
ZoneModel
521, 621777-200LR, 777-300ER
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-100-AD, is
related to this service bulletin.
1. Accomplish Part 1 through Part 7, as required in Tables 1 through 4 below in accordance with
Paragraph 3., Accomplishment Instructions.
2. Evaluate and accomplish the required actions in Tables 1 through 4 below separately for each
outboard slat main track location.
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Table 1: Part 1 - Slat Track Stop Hardware Installation Inspection
Compliance TimeActionCondition
Within 6 months after
the date on this service
bulletin.
Do a Detailed inspection (DET) of the slat main track
stop hardware to determine if the bolt, nut, or stops
are missing and to determine if the thread protrusion
of the bolt from the nut is within limits in accordance
with Part 1 - Slat Track Stop Hardware Installation
Inspection (a).
All Airplanes
1) Within 1125 days af-
ter the date on this ser-
vice bulletin or within
6000 flight-cycles after
the date on this service
bulletin, whichever is
first.
Measure the torque of the nuts of the slat main track
stop installation hardware in accordance with Part 2
- Slat Main Track Stop Hardware Torque Check. See
Table 2 for disposition of conditions found in Part 2
- Slat Main Track Stop Hardware Torque Check.
Condition 1 -
1) Bolt, nut and stop are not
missing;
and
2) Thread protrusion is within
limits.
Before further flight.Do a Detailed Inspection (DET) of the inside of the
slat can for holes and gouges in accordance with
Part 3 - Slat Can Inspection (b) . See Table 3: Part
3 - Slat Can Inspection for disposition of conditions
found in Part 3 - Slat Can Inspection (b) .
Condition 2 -
1) Nut, bolt, or stop is missing;
or
2) Thread protrusion is not
within limits.
(a) Slat main track locations inspected in accordance with Boeing Multi-Operator Message (MOM) number
1-835739989-1 have accomplished the intent of Part 1 - Slat Track Stop Hardware Installation Inspection
in this service bulletin.
(b) Does not apply to Group 1 Airplanes Slat 3 Outboard Main Track Location or Slat 12 Outboard Main Track
Location.
Table 2: Part 2 - Slat Main Track Stop Hardware Torque Check
Compliance TimeActionCondition
-No further action is required at the affected main
track location.
Condition 3 -
Torque requirement is met.
(Terminating Action for that main track location).
Before further flight.Replace the slat main track stop hardware in accor-
dance with Part 4 - Stop Hardware Replacement at
the affected main track location.
Condition 4 -
Torque requirement is not met
(Terminating Action for that main track location)
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Table 3: Part 3 - Slat Can Inspection
Compliance TimeActionCondition
Before further flight.Replace the slat main track stop hardware in accor-
dance with Part 4 - Stop Hardware Replacement at
the affected main track location.
Condition 5 -
No hole or gouge found.
(Terminating Action for that main track location)
Before further flight.Do Option 1 or Option 2:Condition 6 -
Option 1 -1) No hole found;
Repair the slat can in accordance with Part 5 - Slat
Can Repair and replace the slat main track stop
hardware in accordance with Part 4 - Stop Hardware
Replacement at the affected main track location.
and
2) Any gouge found is within
limits.
(Terminating Action for that main track location)
or
Option 2-
Replace the slat can in accordance with Part 6 - Slat
Can Replacement and replace the slat main track
stop hardware in accordance with Part 4 - Stop
Hardware Replacement at the affected main track
location.
(Terminating Action for that main track location)
Before further flight.Replace the slat can in accordance with Part 6 - Slat
Can Replacement and replace the slat main track
stop hardware in accordance with Part 4 - Stop
Hardware Replacement at the affected main track
location.
Condition 7 -
1) Any hole found;
or
2) Any gouge found that is not
within limits.
(Terminating Action for that main track location)
Group 2:
Table 4: Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard
and Inboard Main Track Stop Hardware Replacement
Compliance TimeActionCondition
Within 6 months after
the date on this service
bulletin.
Do a Detailed Inspection (DET) of the inside of the
slat can for outboard slats 3 and 12 outboard main
track location for holes and wear damage in accor-
dance with Part 7 - Outboard Slat Numbers 3 and 12
Outboard Main Track Slat Can Inspection and Out-
board and Inboard Main Track Stop Hardware Re-
placement (a).
Group 2 Airplanes
Within 6 months after
the date on this service
bulletin.
Replace the slat main track hardware for outboard
slats 3 and 12 inboard main track location in accor-
dance with Part 7 - Outboard Slat Numbers 3 and 12
Outboard Main Track Slat Can Inspection and Out-
board and Inboard Main Track Stop Hardware Re-
placement (a).
Group 2 Airplanes
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Group 2:
Table 4: Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard
and Inboard Main Track Stop Hardware Replacement
Compliance TimeActionCondition
Before further flight.Replace the slat main track stop hardware in accor-
dance with Part 7 - Outboard Slat Numbers 3 and 12
Outboard Main Track Slat Can Inspection and Out-
board and Inboard Main Track Stop Hardware Re-
placement.
Condition 8 -
No hole or gouge found.
(Terminating Action for that main track location)
Before further flight.Replace the slat main track stop hardware in accor-
dance with Part 7 - Outboard Slat Numbers 3 and 12
Outboard Main Track Slat Can Inspection and Out-
board and Inboard Main Track Stop Hardware Re-
placement at the affected main track location.
Condition 9 -
1) No hole found;
and
2) Any wear damage found is
on the weld bead only or is
within limits. And
Within 1125 Days after
the wear damage was
found.
Do Option 1 or Option 2:
Option 1 -
Repair the slat can in accordance with Part 5 - Slat
Can Repair. (Terminating Action for that main track
location)
or
Option 2 -
Replace the slat can in accordance with Part 6 - Slat
Can (Terminating Action for that main track location)
Before further flight.Replace the slat can in accordance with Part 6 - Slat
Can Replacement and replace the slat main track
stop hardware in accordance with Part 7 - Outboard
Slat Numbers 3 and 12 Outboard Main Track Slat
Can Inspection and Outboard and Inboard Main
Track Stop Hardware Replacement at the affected
main track location.
Condition 10 -
1) Any hole found;
or
2) Any wear damage found that
is not within limits.
(Terminating Action for that main track location)
(a) Slat main track locations inspected and modified in accordance with Boeing Multi-Operator Message
(MOM) number 1-888175443-1 have accomplished the intent of Part 7 - Outboard Slat Numbers 3 and
12 - Outboard Main Track - Slat Can Inspection and Stop Hardware Replacement.
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.
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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 the inspection, change or repair
for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate
with operator task hour data if necessary. The estimate does not include lost time. These are some
examples of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
1. Part 1 - Slat Track Stop Hardware Installation Inspection
Group 1:
Elapsed
Hours
Task HoursNumber of
Persons
Task
1.757.004Open Access
Inspect
1.751.751...Left Wing - FIGURE 1
1.751.751...Right Wing - FIGURE 2
1.757.004Close Access
7.0017.50TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
2.008.004Open Access
Inspect
2.502.501...Left Wing - FIGURE 3
2.502.501...Right Wing - FIGURE 4
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Group 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
2.008.004Close Access
9.0021.00TOTAL FOR EACH AIRPLANE
2. Part 2 - Slat Main Track Stop Hardware Torque Check
Group 1:
Elapsed
Hours
Task HoursNumber of
Persons
Task
1.757.004Open Access
Torque Check
0.350.351...Left Wing - FIGURE 5
0.350.351...Right Wing - FIGURE 6
1.757.004Close Access
4.2014.70TOTAL FOR EACH AIRPLANE
Group 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
2.008.004Open Access
Inspect
0.450.451...Left Wing - FIGURE 7
0.450.451...Right Wing - FIGURE 8
2.008.004Close Access
4.9016.90TOTAL FOR EACH AIRPLANE
3. Part 3 - Slat Can Inspection
Group 1:
Elapsed
Hours
Task HoursNumber of
Persons
Task
Inspect
3.503.501...Left Wing - FIGURE 9
3.503.501...Right Wing - FIGURE 10
7.007.00TOTAL FOR EACH AIRPLANE
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Group 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
Inspect
4.504.501...Left Wing - FIGURE 11
4.504.501...Right Wing - FIGURE 12
9.009.00TOTAL FOR EACH AIRPLANE
4. Part 4 - Stop Hardware Replacement
Group 1:
Elapsed
Hours
Task HoursNumber of
Persons
Task
Replace
0.30 (a)0.30 (a)1...Left Wing - FIGURE 13
0.30 (a)0.30 (a)1...Right Wing - FIGURE 14
(a) Estimate is for hardware replacement at each main track location.
Group 2:
Elapsed
Hours
Task HoursNumber of
Persons
Task
Replace
0.30 (a)0.30 (a)1...Left Wing - FIGURE 15
0.30 (a)0.30 (a)1...Right Wing - FIGURE 16
0.30 (a)0.30 (a)1...Left Wing - FIGURE 20
0.30 (a)0.30 (a)1...Right Wing - FIGURE 21
(a) Estimate is for hardware replacement at each main track location.
5. Part 5 - Slat Can Repair
Elapsed
Hours
Task HoursNumber of
Persons
Task
2.004.002Remove Slat
1.501.501Remove Slat Main Track
1.001.001Repair Slat Can - FIGURE 17
1.501.501Install Slat Main Track
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Elapsed
Hours
Task HoursNumber of
Persons
Task
2.004.002Install Slat
8.0012.00TOTAL FOR EACH SLAT CAN
6. Part 6 - Slat Can Replacement
Elapsed
Hours
Task HoursNumber of
Persons
Task
3.0012.004Defuel / Mop / Purge Outboard Main Tank
0.250.251Open Access
2.004.002Remove Slat
1.501.501Remove Slat Main Track
3.003.001Replace Slat Can
1.501.501Install Slat Main Track
2.004.002Install Slat
0.250.251Close Access
1.004.004Refuel Tanks
14.5030.50TOTAL FOR EACH SLAT CAN
7. Group 2:
Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard
and Inboard Main Track Stop Hardware Replacement
Elapsed
Hours
Task HoursNumber of
Persons
Task
1.753.502Open Access
Inspect
0.500.501...Left Wing - FIGURE 18
0.500.501...Right Wing - FIGURE 19
Replace Stop hardware
0.600.601...Left Wing - FIGURE 20
0.600.601...Right Wing - FIGURE 21
1.753.502Close Access
4.508.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
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I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Engineering Change Memo PRR 62777-63S
b. Boeing Service Related Problem (SRP) 777-SRP-57-0219
c. Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2009-NM-100-AD
d. Standard Overhaul Practices Manual (SOPM) 20-10-02, 20-30-03, 20-43-03, 20-50-10
e. 777 Aircraft Maintenance Manual (AMM) 06-44-00, 27-81-00, 27-81-15, 27-81-43, 28-11-00,
28-11-01, 28-26-00, 78-31-00
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
Slat Instl- Slats 1 Thru 6, Outbd, Wing LE114W4000
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the
specified changes, and is not supplied with this service bulletin. This drawing may not be applicable
to all airplane configurations or operators.
K. Publications Affected
1. Publications:
Chapter-SectionPublication
27-81777 Illustrated Parts Catalog
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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BLANK PAGE

### Page 29

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.
Group 1:
Unit Price thru Apr
30/09
ROLT
(Weeks)
NamePart Number
$ 3,237.0047Slat Can - Slat No. 6 - Inboard112W2615-21
$ 3,237.0047Slat Can - Slat No. 9 - Inboard112W2615-22
$ 3,237.0047Slat Can - Slat No. 6 - Outboard112W2615-23
$ 3,237.0047Slat Can - Slat No. 9 - Outboard112W2615-24
$ 3,237.0047Slat Can - Slat No. 5 and 10 -
Inboard
112W2615-25
$ 3,237.0052Slat Can - Slat No. 3 - Inboard112W2615-43
$ 3,237.0052Slat Can - Slat No. 12 - Inboard112W2615-44
$ 3,237.0052Slat Can - Slat No. 4 and 11 -
Outboard
112W2615-45
$ 3,237.0052Slat Can - Slat No 4 and 11 -
Inboard
112W2615-47
$ 3,237.0052Slat Can - Slat No. 5 and 10 -
Outboard
112W2615-49
$ 365.0032Downstop Fitting116W4802-3
$ 299.0037Downstop Fitting116W4802-4
$ 12.8095BoltBACB30LR4-36
$ 0.3710NutBACN10JC4CD
(BACN10JC4CM Opt.)
Group 2:
Unit Price thru Apr
30/09
ROLT
(Weeks)
NamePart Number
$ 3,237.0047Slat Can - Slat No. 6 - Inboard112W2615-21
$ 3,237.0047Slat Can - Slat No. 9 - Inboard112W2615-22
$ 3,237.0047Slat Can - Slat No. 6 - Outboard112W2615-23
$ 3,237.0047Slat Can - Slat No. 9 - Outboard112W2615-24
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Group 2:
Unit Price thru Apr
30/09
ROLT
(Weeks)
NamePart Number
$ 3,237.0047Slat Can - Slat No. 5 and 10 -
Inboard
112W2615-25
$ 3,237.0052Slat Can - Slat No. 5 - Outboard112W2615-27
$ 3,237.0047Slat Can - Slat No. 10 - Out-
board
112W2615-28
$ 3,237.0052Slat Can - Slat No. 4 - Inboard112W2615-29
$ 3,237.0052Slat Can - Slat No. 11 - Inboard112W2615-30
$ 3,237.0052Slat Can - Slat No. 4 - Outboard112W2615-31
$ 3,237.0052Slat Can - Slat No. 11 - Out-
board
112W2615-32
$ 3,237.0052Slat Can - Slat No. 3 - Inboard112W2615-33
$ 3,237.0052Slat Can - Slat No. 12 - Inboard112W2615-34
$ 3,237.0052Slat Can - Slat No. 3 - Outboard112W2615-35
$ 3,237.0052Slat Can - Slat No. 12 - Out-
board
112W2615-36
$ 3,231.0050Slat Can - Slat No. 2 - Inboard112W2615-51
$ 3,231.0050Slat Can - Slat No. 13 - Inboard112W2615-52
$ 3,231.0050Slat Can - Slat No. 2 - Outboard112W2615-53
$ 3,231.0050Slat Can - Slat No. 13 - Out-
board
112W2615-54
$ 365.0032Downstop Fitting116W4802-1
$ 299.0032Downstop Fitting116W4802-2
$ 365.0032Downstop Fitting116W4802-3
$ 299.0037Downstop Fitting116W4802-4
$ 34.0095BoltBACB30LR4-35
$ 12.8095BoltBACB30LR4-36
$ 0.3710NutBACN10JC4CD
(BACN10JC4CM Opt.)
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:
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1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Mail to:
Spares Customer Support - MC 36-65
Boeing Spares Department
P.O. Box 3707
Seattle, Washington 98124-2207 USA
B. Industry Support Information
Boeing warranty remedies are available for 777 airplanes in warranty as of April 9, 2008. 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 numbers in your purchase order.
C. Parts Necessary For Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
Group 1:
NotesNameQTY
(c)
Part Number /
Specification
Slat Can - Slat No. 6 - Inboard1112W2615-21
Slat Can - Slat No. 9 - Inboard1112W2615-22
Slat Can - Slat No. 6 - Outboard1112W2615-23
Slat Can - Slat No. 9 - Outboard1112W2615-24
Slat Can - Slat No. 5 and 10 - In-
board
2112W2615-25
Slat Can - Slat No. 3 - Inboard1112W2615-43
Slat Can - Slat No. 12 - Inboard1112W2615-44
Slat Can - Slat No. 4 and 11 - Out-
board
2112W2615-45
Slat Can - Slat No 4 and 11 - In-
board
2112W2615-47
Slat Can - Slat No. 5 and 10 - Out-
board
2112W2615-49
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Group 1:
NotesNameQTY
(c)
Part Number /
Specification
Downstop Fitting14116W4802-3
Downstop Fitting14116W4802-4
(b)Chemical Conversion Coating - Fuel
Tank
1 Oz.ALODINE 600
Bolt14BACB30LR4-36
Nut14BACN10JC4CD
(BACN10JC4CM
Opt.)
(a)Primer - Fuel Tank1 Oz.BMS 10-20, TYPE
II
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for
supplier data.
(b) See SOPM 20-43-03 for supplier data
(c) The quantity shown is the total quantity required per airplane if all parts at all affected
main track locations require replacement. Parts only require replacement if the parts do
not meet the requirements shown in this service bulletin.
Group 2:
NotesNameQTY
(c)
Part Number /
Specification
Slat Can - Slat No. 6 - Inboard1112W2615-21
Slat Can - Slat No. 9 - Inboard1112W2615-22
Slat Can - Slat No. 6 - Outboard1112W2615-23
Slat Can - Slat No. 9 - Outboard1112W2615-24
Slat Can - Slat No. 5 - Outboard2112W2615-25
Slat Can - Slat No. 3 - Inboard1112W2615-27
Slat Can - Slat No. 10 - Outboard1112W2615-28
Slat Can - Slat No. 4 - Inboard1112W2615-29
Slat Can - Slat No. 11 - Inboard1112W2615-30
Slat Can - Slat No. 4 - Outboard1112W2615-31
Slat Can - Slat No. 11 - Outboard1112W2615-32
Slat Can - Slat No. 3 - Inboard1112W2615-33
Slat Can - Slat No. 12 - Inboard1112W2615-34
Slat Can - Slat No. 2 - Inboard1112W2615-51
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Group 2:
NotesNameQTY
(c)
Part Number /
Specification
Slat Can - Slat No. 13 - Inboard1112W2615-52
Slat Can - Slat No. 2 - Outboard1112W2615-53
Slat Can - Slat No. 13 - Outboard1112W2615-54
Downstop Fitting4116W4802-1
Downstop Fitting4116W4802-2
Downstop Fitting12116W4802-3
Downstop Fitting12116W4802-4
Chemical Conversion Coating - Fuel
Tank
1 Oz.ALODINE 600
(b)Bolt4BACB30LR4-35
(BACB30LR4-36
with a
BACW10BP4APU
Washer opt.)
(b)Bolt12BACB30LR4-36
Nut16BACN10JC4CD
(BACN10JC4CM
Opt.)
(a)Primer - Fuel Tank1 Oz.BMS 10-20, TYPE
II
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for
supplier data.
(b) See SOPM 20-43-03 for supplier data
(c) The quantity shown is the total quantity required per airplane if all parts at all affected
main track locations require replacement. Parts only require replacement if the parts do
not meet the requirements shown in this service bulletin.
Group 2:
Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and
Inboard Main Track Stop Hardware Replacement
NotesExisting Part NumberNameQTYPart Number /
Specification
(c)-Slat Can - Slat No. 3 - Outboard1112W2615-35
(c)-Slat Can - Slat No. 12 - Outboard1112W2615-36
(d)116W4802-3Downstop Fitting4116W4802-1
(d)116W4802-4Downstop Fitting4116W4802-2
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Group 2:
Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard and
Inboard Main Track Stop Hardware Replacement
NotesExisting Part NumberNameQTYPart Number /
Specification
(b)-Chemical Conversion Coating - Fuel
Tank
1 Oz.ALODINE 600
-Bolt4BACB30LR4-35
(BACB30LR4-36
with a
BACW10BP4APU
Washer opt.)
-Nut4BACN10JC4CD
(BACN10JC4CM
Opt.)
(a)-Primer - fuel tank1 Oz.BMS 10-20, TYPE
II
(a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
(b) See SOPM 20-43-03 for supplier data
(c) The quantity shown is the total quantity required per airplane if all the parts at the affected main track
locations require replacement. Parts only require replacement if the parts do not meet the requirements
shown in this service bulletin.
(d) Refer to APPENDIX A for instructions to rework the 116W4802-3, -4 into 116W4802-1 and 2.
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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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. Use the approved fastener and process material substitutions in accordance with
777 SRM, Chapter 51. Alternate fasteners are listed in 777 SRM Chapter 51 and
Boeing Drawing 012W6100.
5. If the length of any fastener specified in this service bulletin does not meet the
installation standards in 777 SRM, Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards in 777 SRM, Chapter 51 may be used. Maximum 36 grip length at stop
fitting locations.
6. A Detailed Inspection (DET) 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.
7. 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.
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8. Group 1 Airplanes - Evaluate and accomplish the required actions in Tables 1 through
3 in Paragraph 1.E., Compliance, separately for each main track location for outboard
slat numbers 3 (inboard main track), 4 (inboard and outboard main tracks), 5 (inboard
and outboard main tracks), 6 (inboard and outboard main tracks), 9 (inboard and
outboard main tracks), 10 (inboard and outboard main tracks), 11 (inboard and
outboard main tracks), and 12 (inboard main track).
9. Group 2 Airplanes - Evaluate and accomplish the required actions in Tables 1 through
3 in Paragraph 1.E., Compliance, separately for each main track location for outboard
slat numbers 2 (inboard and outboard main tracks), 3 (inboard main track), 4 (inboard
and outboard main tracks), 5 (inboard and outboard main tracks), 6 (inboard and
outboard main tracks), 9 (inboard and outboard main tracks), 10 (inboard and outboard
main tracks), 11 (inboard and outboard main tracks), 12 (inboard main track), and
13 (inboard and outboard main tracks).
10. Group 2 Airplanes - Evaluate and accomplish the required actions in Table 4 in
Paragraph 1.E., Compliance, separately for each main track location for outboard
slat numbers 3 (outboard main track) and 12 (outboard main track).
B. WORK INSTRUCTIONS
Part 1 - Slat Track Stop Hardware Installation Inspection
1. Deactivate the thrust reverser for ground maintenance. Refer to 777 AMM 78-31-00 as an accepted
procedure.
2. Extend the slats to the fully extended position and deactivate. Refer to 777 AMM 27-81-00 as an
accepted procedure.
3. Group 1:
Remove or open the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
6543
InbdOutbdInbdOutbdInbdOutbdInbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB
(a) Fuel access panel.
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Right Wing - Main Track Location
Slat
9101112
InbdOutbdInbdOutbdInbdOutbdInbd
621BB621DAB (a)
or 621DB (b)
621EB621GB621JB621MB621PB621RB
(a) Access panel.
(b) Optional fuel access panel.
4. Group 2:
Remove or open the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
65432
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB521WB521YB
(a) Fuel Access Panel.
Right Wing - Main Track Location
Slat
910111213
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
621BB621DAB (a)
or 621DB (b)
621EB621GB621JB621MB621PB621RB621WB621YB
(a) Access panel.
(b) Optional fuel access panel.
5. Do a Detailed inspection (DET) of the slat main track stop hardware to determine if the bolt, nut,
or stops are missing and to determine if the thread protrusion of the bolt from the nut is within limits
in accordance with the figures below:
Group 1:
Left wing, outboard slat numbers 3 (inboard main track), 4 (inboard and outboard main tracks), 5
(inboard and outboard main tracks), and 6 (inboard and outboard main tracks) in accordance with
FIGURE 1. Right wing, outboard slat numbers 12 (inboard main track), 11 (inboard and outboard
main tracks), 10 (inboard and outboard main tracks), and 9 (inboard and outboard main tracks) in
accordance with FIGURE 2.
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Group 2:
Left wing, outboard slat numbers 2 (inboard and outboard main tracks), 3 (inboard main track), 4
(inboard and outboard main tracks), 5 (inboard and outboard main tracks), and 6 (inboard and
outboard main tracks) in accordance with FIGURE 3. Right wing, outboard slat numbers 13 (inboard
and outboard main tracks), 12 (inboard main track), 11 (inboard and outboard main tracks), 10
(inboard and outboard main tracks), and 9 (inboard and outboard main tracks) in accordance with
FIGURE 4.
a. Condition 1 - 1) Bolt, nut and stop are not missing; and 2) Thread protrusion is within limits.
Measure the torque of the nuts of the outboard slat main track stop installation hardware in
accordance with Part 2 - Slat Main Track Stop Hardware Torque Check within the threshold
in Table 1 in Paragraph 1.E., Compliance.
b. Condition 2 - 1) Nut, bolt, or stop is missing; or 2) Thread protrusion is not within limits.
Do a Detailed Inspection (DET) of the slat can for holes and gouges in accordance with Part
3 - Slat Can Inspection within the threshold in Table 1 in Paragraph 1.E., Compliance.
6. Group 1:
Install or close the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
6543
InbdOutbdInbdOutbdInbdOutbdInbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB
(a) Fuel access panel.
Right Wing - Main Track Location
Slat
9101112
InbdOutbdInbdOutbdInbdOutbdInbd
621BB621DAB (a)
or 621DB (b)
621EB621GB621JB621MB621PB621RB
(a) Access panel.
(b) Optional fuel access panel.
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7. Group 2:
Install or close the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
65432
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB521WB521YB
(a) Fuel access panel.
Right Wing - Main Track Location
Slat
910111213
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
621BB621DAB (a)
or 621DB (b)
621EB621GB621JB621MB621PB621RB621WB621YB
(a) Access panel.
(b) Optional fuel access panel.
8. Activate and retract the slats. Refer to 777 AMM 27-81-00 as an accepted procedure.
9. Activate the thrust reverser. Refer to 777 AMM 78-31-00 as an accepted procedure.
10. Put the airplane back to a serviceable condition.
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Part 2 - Slat Main Track Stop Hardware Torque Check
1. Deactivate the thrust reverser for ground maintenance. Refer to 777 AMM 78-31-00 as an accepted
procedure.
2. Extend the slats to the fully extended position and deactivate. Refer to 777 AMM 27-81-00 as an
accepted procedure.
3. Group 1:
Remove or open the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
6543
InbdOutbdInbdOutbdInbdOutbdInbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB
(a) Fuel access panel.
Right Wing - Main Track Location
Slat
9101112
InbdOutbdInbdOutbdInbdOutbdInbd
621BB621DAB (a)or 621DB (b)621EB621GB621JB621MB621PB621RB
(a) Access panel.
(b) Optional fuel access panel.
4. Group 2:
Remove or open the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
65432
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB521WB521YB
(a) Fuel access panel.
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Right Wing - Main Track Location
Slat
910111213
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
621BB621DAB (a)or 621DB (b)621EB621GB621JB621MB621PB621RB621WB621YB
(a) Access panel.
(b) Optional fuel access panel.
5. Measure the torque of the nuts of the outboard slat main track stop installation hardware in
accordance with the figures below:
Group 1:
Left wing, outboard slat numbers 3 (inboard main track), 4 (inboard and outboard main tracks), 5
(inboard and outboard main tracks), and 6 (inboard and outboard main tracks) in accordance with
FIGURE 5. Right wing, outboard slat numbers 12 (inboard main track), 11 (inboard and outboard
main tracks), 10 (inboard and outboard main tracks), and 9 (inboard and outboard main tracks )
in accordance with FIGURE 6.
Group 2:
Left wing, outboard slat numbers 2 (inboard and outboard main tracks), 3 (inboard main track), 4
(inboard and outboard main tracks), 5 (inboard and outboard main tracks), and 6 (inboard and
outboard main tracks) in accordance with FIGURE 7. Right wing, outboard slat numbers 13 (inboard
and outboard main tracks), 12 (inboard main track), 11 (inboard and outboard main tracks), 10
(inboard and outboard main tracks), and 9 (inboard and outboard main tracks ) in accordance with
FIGURE 8.
a. Condition 3 - Torque requirements is met.
No further action is required at that main track location. This is terminating action for that main
track location.
b. Condition 4 - Torque requirements is not met.
Replace the slat main track stop hardware in accordance with Part 4 - Stop Hardware
Replacement within the threshold in Table 2 in Paragraph 1.E., Compliance. This is terminating
action for that main track location.
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6. Group 1:
Install or close the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
6543
InbdOutbdInbdOutbdInbdOutbdInbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB
(a) Fuel access panel.
Right Wing - Main Track Location
Slat
9101112
InbdOutbdInbdOutbdInbdOutbdInbd
621BB621DAB (a)or 621DB (b)621EB621GB621JB621MB621PB621RB
(a) Access panel.
(b) Optional fuel access panel.
7. Group 2:
Install or close the access panels shown below. Refer to 777 AMM 06-44-00 as an accepted
procedure.
Left Wing - Main Track Location
Slat
65432
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
521BB521DB (a)521EB521GB521JB521MB521PB521RB521WB521YB
(a) Fuel access panel.
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Right Wing - Main Track Location
Slat
910111213
InbdOutbdInbdOutbdInbdOutbdInbdInbdOutbd
621BB621DAB (a)or 621DB (b)621EB621GB621JB621MB621PB621RB621WB621YB
(a) Access panel.
(b) Optional fuel access panel.
8. Activate and retract the slats. Refer to 777 AMM 27-81-00 as an accepted procedure.
9. Activate the thrust reverser. Refer to 777 AMM 78-31-00 as an accepted procedure.
10. Put the airplane back to a serviceable condition.
Part 3 - Slat Can Inspection
1. Do a Detailed Inspection (DET) of the inside of the slat can using a borescope, at the affected
main track location, for holes and gouges in accordance with the figures below:
Group 1:
Left wing in accordance with FIGURE 9. Right wing in accordance with FIGURE 10.
Group 2:
Left wing in accordance with FIGURE 11. Right wing in accordance with FIGURE 12.
a. Condition 5 - No hole or gouge found.
Replace the slat main track stop hardware in accordance with Part 4 - Stop Hardware
Replacement at the affected main track location within the threshold in Table 3 of Paragraph
1.E., Compliance. This is terminating action for that main track location.
b. Condition 6 - 1) No hole found; and 2) Any gouge found is within limits.
Do Option 1 or Option 2:
(1) Option 1
Repair the slat can in accordance with Part 5 - Slat Can Repair and replace the slat main
track stop hardware in accordance with Part 4 - Stop Hardware Replacement at the
affected main track location within the threshold in Table 3 of Paragraph 1.E., Compliance.
This is terminating action for that main track location.
(2) Option 2-
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Replace the slat can in accordance with Part 6 - Slat Can Replacement and replace the slat
main track stop hardware in accordance with Part 4 - Stop Hardware Replacement at the
affected main track location within the threshold in Table 3 of Paragraph 1.E., Compliance.
This is terminating action for that main track location.
c. Condition 7 - 1) Any hole found; or 2) Any gouge found that is not within limits.
Replace the slat can in accordance with Part 6 - Slat Can Replacement and replace the slat
main track stop hardware in accordance with Part 4 - Stop Hardware Replacement at the
affected main track location within the threshold in Table 3 of Paragraph 1.E., Compliance.
This is terminating action for that main track location.
Part 4 - Stop Hardware Replacement
1. Group 1:
Left Wing - Replace the slat main track stop hardware at the affected main track location in
accordance with FIGURE 13. Right Wing - Replace the slat main track stop hardware at the affected
main track location in accordance with FIGURE 14.
2. Group 2:
Left Wing -Replace the slat main track stop hardware at the affected main track location for slat
numbers 4 through 6 (inboard and outboard main track locations) in accordance with FIGURE 15
and slat number 2 (inboard and outboard main track locations) in accordance with FIGURE 20.
Right Wing -Replace the slat main track stop hardware at the affected main track location for slat
numbers 9 through 11 (inboard and outboard main track locations) in accordance with FIGURE
16 and slat number 13 (inboard and outboard main track locations) in accordance with FIGURE
21.
Part 5 - Slat Can Repair
1. Remove the slat at the affected main track location. Refer to 777 AMM 27-81-15 as an accepted
procedure.
2. Remove the slat main track at the affected main track location. Refer to 777 AMM 27-81-43 as an
accepted procedure.
3. Repair gouges in slat can in accordance with FIGURE 17.
4. Install the slat main track. Refer to 777 AMM 27-81-43 as an accepted procedure
5. Install the slat. Refer to 777 AMM 27-81-15 as an accepted procedure.
Part 6 - Slat Can Replacement
1. Defuel and purge left and right outboard fuel tank as required for entry. Refer to 777 AMM 28-26-00
and 777 AMM 28-11-00 as accepted procedures.
2. Remove the slat at the affected main track location. Refer to 777 AMM 27-81-15 as an accepted
procedure.
3. Remove the slat main track at the affected main track location. Refer to 777 AMM 27-81-43 as an
accepted procedure.
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4. Remove the applicable lower wing skin access panel to access rib bay where affected slat can is
located. Refer to 777 AMM 06-44-00 and 777 AMM 28-11-01 as accepted procedures.
5. Replace the slat can.
6. Install the applicable lower wing skin access panel to access rib bay where the affected slat can
is located. Refer to 777 AMM 06-44-00 and 777 AMM 28-11-01 as accepted procedures.
7. Install the slat main track. Refer to 777 AMM 27-81-43 as an accepted procedure
8. Install the slat. Refer to as 777 AMM 27-81-15 an accepted procedure.
Group 2:
Part 7 - Outboard Slat Numbers 3 and 12 Outboard Main Track Slat Can Inspection and Outboard
and Inboard Main Track Stop Hardware Replacement
1. Deactivate the thrust reverser for ground maintenance. Refer to 777 AMM 78-31-00 as an accepted
procedure.
2. Extend the slats to the fully extended position and deactivate. Refer to 777 AMM 27-81-00 as an
accepted procedure.
3. Remove access panels 521RB and 521TB (Left Wing - Slat Number 3 - Outboard and Inboard
Main Track location) and 621RB and 621TB (Right Wing - Slat Number 12 - Outboard and Inboard
Main Track location). Refer to 777 AMM 06-44-00 as an accepted procedure.
4. Replace the slat main track stop hardware at slat number 3 inboard main track in accordance with
FIGURE 20 and slat number 12 inboard main track in accordance with FIGURE 21, within the
threshold in Table 4 of Paragraph 1.E., Compliance.
NOTE: Accomplish Part 1 - Slat Track Stop Hardware Installation Inspection prior to accomplishing
this step.
5. Do a Detailed Inspection (DET) of the inside of the slat can using a borescope at slat numbers 3
(outboard main track) in accordance with FIGURE 18 and the slat can at slat number 12 (outboard
main track) in accordance with FIGURE 19, for holes and wear damage.
a. Condition 8 - No hole or wear damage found.
Replace the slat main track stop hardware at the affected main track location, slat number 3
outboard main track in accordance with FIGURE 20 or slat number 12 outboard main track
in accordance with FIGURE 21, within the threshold in Table 4 of Paragraph 1.E., Compliance.
This is terminating action for that main track location.
b. Condition 9 - 1) No hole found; and 2) Any wear damage found is on the weld bead only or
is within limits..
Replace the slat main track stop hardware at the affected main track location, slat number 3
outboard main track in accordance with FIGURE 20 or slat number 12 outboard main track
in accordance with FIGURE 21, within the threshold in Table 4 of Paragraph 1.E., Compliance
and do option 1 or 2 below:
(1) Option 1-
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BOEING SERVICE BULLETIN 777-57A0064

### Page 46

Repair the slat can in accordance with Part 5 - Slat Can Repair at the affected main track
location within the threshold in Table 4 of Paragraph 1.E., Compliance. This is terminating
action for that main track location.
(2) Option 2 -
Replace the slat can in accordance with Part 6 - Slat Can Replacement at the affected
main track location within the threshold in Table 4 of Paragraph 1.E., Compliance. This
is terminating action for that main track location.
c. Condition 10 - 1) Any hole found; or 2) Any wear damage found that is not within limits.
Replace the slat can in accordance with Part 6 - Slat Can Replacement and replace the slat
main track stop hardware at the affected main track location, slat number 3 outboard main
track in accordance with FIGURE 20 or slat number 12 outboard main track in accordance
with FIGURE 21, within the threshold in Table 4 of Paragraph 1.E., Compliance. This is
terminating action for that main track location.
6. Install access panels 521RB and 521TB (Left Wing - Slat Number 3 - Outboard and Inboard Main
Track location) and 621TB (Right Wing - Slat Number 12 - Outboard and Inboard Main Track
location). Refer to 777 AMM 06-44-00 as an accepted procedure.
7. Activate and retract the slats. Refer to 777 AMM 27-81-00 as an accepted procedure.
8. Activate the thrust reverser. Refer to 777 AMM 78-31-00 as an accepted procedure.
9. Put the airplane back to a serviceable condition.
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### Page 47 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
This Figure applies only to: Group 1.
7 LOCATIONS  SLAT SLAT SLAT
4  SLAT
SLAT
2 SLAT
=WD
TYPICAL MAIN TRACK LOCATION
1676465
FIGURE 1: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 1 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  777-57A0064
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Copyright © Unpublished Work - See page 1 for details.  47 of 104

### Page 48 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
DOWNSTOP ACCESS HOLE
TYPICAL MAIN TRACK IN
RETRACTED POSITION
TYPICAL SLAT CAN
TYPICAL MAIN TRACK IN
EXTENTED POSITION  A-A
FWD
STOP
FITTING
NUT C  • STOP  FITTING  © NUT  - CHAMFER
) BOLT
BOLT
MAIN TRACK  2) 1 THREAD  MINIMUM OF
C  1676526
FIGURE 1: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 2 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  50110 80

### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one main track location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a DET to deter-
mine if the downstop
fittings are present.
2-Downstop fittingInspect1
Do a DET to deter-
mine if the nut is
present.
1-NutInspect
Do a DET to deter-
mine if the bolt is
present.
1-BoltInspect
Do a DET to deter-
mine the number of
threads protruding
from the nut. A mini-
mum of one thread
plus the chamfer
must protrude from
the nut.
1-BoltInspect2
FIGURE 1: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 777-57A0064

### Page 50 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
This Figure applies only to: Group 1.
SLAT  SLAT SLAT SLAT  11  A 7 LOCATIONS
SLAT  12
SLAT 13
14
•WD
TYPICAL MAIN TRACK LOCATION
1676546
FIGURE 2: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 1 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.

### Page 51 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
DOWNSTOP ACCESS HOLE
TYPICAL MAIN TRACK IN
RETRACTED POSITION
TYPICAL SLAT CAN
TYPICAL MAIN TRACK IN
FWD  EXTENTED POSITION
A-A
1) STOP  /FITTING
STOP
FITTING
C NUT  CHAMFER
NUT 1
BOLT
BOLT
MAIN TRACK
MINIMUM OF
1 THREAD
1676560
FIGURE 2: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 2 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  51 of 104

### Page 52

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one main track location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a DET to deter-
mine if the downstop
fittings are present.
2-Downstop fittingInspect1
Do a DET to deter-
mine if the nut is
present.
1-NutInspect
Do a DET to deter-
mine if the bolt is
present.
1-BoltInspect
Do a DET to deter-
mine the number of
threads protruding
from the nut. A mini-
mum of one thread
plus the chamfer
must protrude from
the nut.
1-BoltInspect2
FIGURE 2: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 3 OF 3)
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52 of 104
BOEING SERVICE BULLETIN 777-57A0064

### Page 53 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
This Figure applies only to: Group 2.
SLAT SLAT
9 LOCATIONS  6  SLAT
4  SLAT
SLAT
2 SLAT
=WD
TYPICAL MAIN TRACK LOCATION
1676575
FIGURE 3: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 1 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  777-57A0064
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Copyright © Unpublished Work - See page 1 for details.  53 of 104

### Page 54 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
DOWNSTOP ACCESS HOLE
TYPICAL MAIN TRACK IN
RETRACTED POSITION
TYPICAL SLAT CAN
TYPICAL MAIN TRACK IN
EXTENTED POSITION  A-A
FWD
STOP
FITTING
NUT C  • STOP  FITTING  © NUT  - CHAMFER
→ BOLT
BOLT
MAIN TRACK  2 MINREADOF
C  1676576
FIGURE 3: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 2 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.

### Page 55

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one main track location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a DET to deter-
mine if the downstop
fittings are present.
2-Downstop fittingInspect1
Do a DET to deter-
mine if the nut is
present.
1-NutInspect
Do a DET to deter-
mine if the bolt is
present.
1-BoltInspect
Do a DET to deter-
mine the number of
threads protruding
from the nut. A mini-
mum of one thread
plus the chamfer
must protrude from
the nut.
1-BoltInspect2
FIGURE 3: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 3 OF 3)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: March 26, 2009
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55 of 104
BOEING SERVICE BULLETIN 777-57A0064

### Page 56 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
This Figure applies only to: Group 2.
SLAT SLAT SLAT SLAT
SLAT
SLAT 13
14
•WD
TYPICAL MAIN TRACK LOCATION
1676580
FIGURE 4: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 1 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.

### Page 57 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
DOWNSTOP ACCESS HOLE
TYPICAL MAIN TRACK IN
RETRACTED POSITION
TYPICAL SLAT CAN
TYPICAL MAIN TRACK IN
FWD  EXTENTED POSITION
A-A
-ITTING
STOP
FITTING
C NUT  CHAMFER
NUT 1
BOLT
BOLT
MAIN TRACK
MINIMUM OF
1676581
FIGURE 4: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 2 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  57 of 104

### Page 58

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one main track location.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a DET to deter-
mine if the downstop
fittings are present.
2-Downstop fittingInspect1
Do a DET to deter-
mine if the nut is
present.
1-NutInspect
Do a DET to deter-
mine if the bolt is
present.
1-BoltInspect
Do a DET to deter-
mine the number of
threads protruding
from the nut. A mini-
mum of one thread
plus the chamfer
must protrude from
the nut.
1-BoltInspect2
FIGURE 4: RIGHT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - INSPECTION
(SHEET 3 OF 3)
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Original Issue: March 26, 2009
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58 of 104
BOEING SERVICE BULLETIN 777-57A0064

### Page 59 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
This Figure applies only to: Group 1.
SLAT SLAT
7 LOCATIONS  6  5  SLAT
4  SLAT
3  SLAT
2 SLAT
FWD
TYPICAL MAIN TRACK LOCATION
1676584
FIGURE 5: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK
(SHEET 1 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  777-57A0064
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### Page 60 (OCR)

BOEING SERVICE BULLETIN 777-57A0064
DOWNSTOP ACCESS HOLE
TYPICAL MAIN TRACK IN
RETRACTED POSITION
TYPICAL SLAT CAN
TYPICAL MAIN TRACK IN
EXTENTED POSITION  A-A
FWD
STOP
FITTING
STOP
FITTING
NUT (1
BOLT
MAIN TRACK
1676587
FIGURE 5: LEFT WING - OUTBOARD SLATS - MAIN TRACK DOWNSTOP ASSEMBLY - TORQUE CHECK
(SHEET 2 OF 3)
Original Issue: March 26, 2009
Revision 1 May 06, 2010  777-57A0064
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  60 of 104

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