# Boeing Alert Service Bulletin 777-57A0097: Revision 1

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- Document: [Boeing Alert Service Bulletin 777-57A0097](https://openairdocs.org/service-documents/boeing/777-57a0097.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin - SB-777-57A0097-00
- Pages: 45
- PDF: https://openairdocs.org/files/sha256/9f/48/9f486fb2efc95865183ced5ac212b93822799489045f724870aecba161840ed4
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## Text

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### Page 1

Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-57A0097
Original Issue: January 10, 2014
ATA System: 5720
SUBJECT: WINGS - Outer Wing - Underwing Fittings Sealant at Wing Panel Gaps - Inspection
and Repair
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). 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 © 2014 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries 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
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 1
B. Concurrent Requirements ...................................... 1 1
C. Reason ................................................ 1 1
D. Description .............................................. 1 2
E. Compliance .............................................. 1 2
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 6
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 7
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 8
E. Special Tooling - Price and Availability ............................... 1 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 2 1
FIGURE 1: LEFT WING - WING SKIN PANEL GAP SEALANT INSPECTION [Group 1, 3] ...... 2 4
FIGURE 2: RIGHT WING - WING SKIN PANEL GAP SEALANT INSPECTION [Group 2-3] ...... 2 8
FIGURE 3: LEFT WING - WING SKIN PANEL GAP SEALANT REPAIR [Group 1, 3] ......... 3 2
FIGURE 4: RIGHT WING - WING SKIN PANEL GAP SEALANT REPAIR [Group 2-3] ......... 3 5
FIGURE 5: LEFT WING - WING SKIN PANEL GAP CORROSION INSPECTION [Group 1, 3] .... 3 8
FIGURE 6: RIGHT WING - WING SKIN PANEL GAP CORROSION INSPECTION [Group 2-3] .... 4 1
APPENDIX A: SEALANT REMOVAL TOOLS AND PROCEDURES ..................... 4 4
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Commercial 
Airplanes
777
Service Bulletin
ALERT
SummaryNumber: 777-57A0097Original Issue: January 10, 2014
ATA System: 5720
SUBJECT: WINGS - Outer Wing - Underwing Fittings Sealant at Wing Panel Gaps - Inspection
and Repair
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will find if sealant was applied to the wing skin panel gaps above the
underwing fittings. Missing sealant in the wing skin panel gaps above the underwing fittings can allow undetected
corrosion to develop in the wing skin panels above the underwing fittings. Undetected corrosion in the wing skin
panels above the underwing fittings can result in undetected fatigue cracks in the wing skin panels. Undetected
fatigue cracks in the wing skin panels can result in the loss of limit load capability of the wing skins and structural
failure of the wings.
Boeing found that sealant may not have been applied in production to the wing skin panel gaps above the
underwing fittings on certain underwing fittings on certain 777 airplanes. Sealant is required to be applied to the
wing skin panel gaps above the underwing fittings prior to installation of the underwing fittings. A review of Boeing
installation records found that sealant may not have been applied above certain underwing fittings on certain
previously delivered and in-production 777 airplanes. The affected in-production 777 airplanes have been
inspected to make sure sealant is applied to the wing skin panel gaps above the underwing fittings. Production
installation procedures have also been addressed to make sure sealant is applied to the wing skin panel gaps
above the underwing fittings on future 777 production airplanes.
This service bulletin gives instructions to inspect and restore the sealant in the wing skin panel gaps above the
underwing fittings. If sealant is missing, this service bulletin also gives instructions to inspect for corrosion in the
wing skin panels gaps to prevent possible fatigue cracks in the wing skin panels, loss of limit load capability of
the wing skins and potential subsequent structural failure of the wings.
Boeing Fleet Team Digest (FTD) 777 FTD 57-13003 is related to this service bulletin.
Boeing Service Related Problem (SRP) 777-SRP-57-0265 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
Paragraph 1.K., Publications AffectedNoPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsNoKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin and APPENDIX A for
additional optional tool information.
NoSpecial Tooling Required
ACTION
Do a Detailed Inspection (DET) of the wing skin panel gaps above the underwing fittings for any missing sealant,
on the left wing (applicable to Groups 1,3) and on the right wing (applicable to Groups 2-3). If sealant is missing,
do a DET of the wing skin panel gaps above the underwing fittings for corrosion. If any corrosion is found, contact
Boeing for repair instructions, do the repair, and restore the missing sealant and the sealant that was previously
removed to gain inspection access. If no corrosion is found, restore the missing sealant and the sealant that
was previously removed to gain inspection access. If sealant is not missing, restore the sealant that was previously
removed to gain inspection access.
EFFECTIVITY
777-200/-200LR/-300ER, 777F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of August 7, 2013. Please refer to Paragraph
2.B., Industry Support Information. The warranty remedies will expire eight years from the original issue date of
this service bulletin.
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MANPOWER
Elapsed
Hours
Total
Task
Hours
Airplanes
15.8551.85Group 1 and Group 2 Airplanes
19.70103.70Group 3 Airplanes
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
DO A DETAILED INSPECTION (DET) OF THE WING
SKIN PANEL GAPS ABOVE THE UNDERWING
-ITINGS FOR ANY MISSING SEALANT, ON THE
LEFT WING (APPLICABLE TO  GROUPS 1,3) AND ON
THE RIGHT  WING (APPLICABLE  TO GROUPS 2-3).
IF SEALANT IS MISSING,  DO A DET OF THE WING
SKIN PANEL GAPS ABOVE THE UNDERWING
OR CORROSION. IF ANY CORROSION IS
FOUND  NTACT BOEING FOR REPAIR
INSTRI  ONS, DO THE REPAIR, AND RESTORE
THE MISS  NG SEA  ANT AND THE SEALANT THAT
WAS PREV  IOUSL  REMOVED TO GAIN
INSPE  ACCESS. IF NO CORROSION IS
FOUND.  THE MISS  G SEALANT AND
THE SEA  VOUSLY REMOVED
TO GAIN I  NSPEC  ESS. IF SEALANT IS NOT
MISSING. RE  STORE  SEALANT THAT WAS
PREVIOUSLY REMOVED TO GAIN INSPECTION
ACCESS
_ TYPICAL
LEFT WING SHOWN (APPLICABLE TO GROUPS 1,3)
RIGHT WING OPPOSITE (APPLICABLE TO GROUPS 2-3)
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### Page 9

Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-57A0097
Original Issue: January 10, 2014
ATA System: 5720
SUBJECT: WINGS - Outer Wing - Underwing Fittings Sealant at Wing Panel Gaps - Inspection
and Repair
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplane(s) shown below.
Refer to Service Bulletin Index D624W001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
DESCRIPTIONCONFIGURATIONGROUP
777-200/-200LR/-300ER and 777F airplanes that require inspection
for missing sealant on the left wing only.
-1
777-300ER and 777F airplanes that require inspection for missing
sealant on the right wing only.
-2
777-300ER and 777F airplanes that require inspection for missing
sealant on both the left and the right wings.
-3
Airplane Models:
777-200, 777-200LR, 777-300ER, 777F
GroupVariable Number
1WC593
1WD106
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GroupVariable Number
2WD889
1WD890 - WD892
1WD918
1WD923 - WD925
1WD927
2WD928
1WD941 - WD943
1WD956 - WD957
1WD993
1WE094
1WE141
1WE159 - WE164
1WE203
3WE206
1WE207 - WE208
1WE240
1WE242 - WE243
2WE262
1WE263 - WE265
1WE272
3WE273
1WE274
1WE276
1WE301
1WE303 - WE304
1WE307
1WE331
1WE333
1WE351
1WE416
1WF035
3WF037
1WF038
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GroupVariable Number
2WF062
1WF064
1WF146 - WF147
1WF152
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will find if sealant was applied to the wing skin panel gaps above
the underwing fittings. Missing sealant in the wing skin panel gaps above the underwing fittings can
allow undetected corrosion to develop in the wing skin panels above the underwing fittings. Undetected
corrosion in the wing skin panels above the underwing fittings can result in undetected fatigue cracks
in the wing skin panels. Undetected fatigue cracks in the wing skin panels can result in the loss of limit
load capability of the wing skins and structural failure of the wings.
Boeing found that sealant may not have been applied in production to the wing skin panel gaps above
the underwing fittings on certain underwing fittings on certain 777 airplanes. Sealant is required to be
applied to the wing skin panel gaps above the underwing fittings prior to installation of the underwing
fittings. A review of Boeing installation records found that sealant may not have been applied above
certain underwing fittings on certain previously delivered and in-production 777 airplanes. The affected
in-production 777 airplanes have been inspected to make sure sealant is applied to the wing skin panel
gaps above the underwing fittings. Production installation procedures have also been addressed to
make sure sealant is applied to the wing skin panel gaps above the underwing fittings on future 777
production airplanes.
This service bulletin gives instructions to inspect and restore the sealant in the wing skin panel gaps
above the underwing fittings. If sealant is missing, this service bulletin also gives instructions to inspect
for corrosion in the wing skin panels gaps to prevent possible fatigue cracks in the wing skin panels,
loss of limit load capability of the wing skins and potential subsequent structural failure of the wings.
Boeing Fleet Team Digest (FTD) 777 FTD 57-13003 is related to this service bulletin.
Boeing Service Related Problem (SRP) 777-SRP-57-0265 is related to this service bulletin.
Export Controlled ECCN: 9E991 - BOEING
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D. Description
Do a Detailed Inspection (DET) of the wing skin panel gaps above the underwing fittings for any missing
sealant, on the left wing (applicable to Groups 1,3) and on the right wing (applicable to Groups 2-3). If
sealant is missing, do a DET of the wing skin panel gaps above the underwing fittings for corrosion. If
any corrosion is found, contact Boeing for repair instructions, do the repair, and restore the missing
sealant and the sealant that was previously removed to gain inspection access. If no corrosion is found,
restore the missing sealant and the sealant that was previously removed to gain inspection access. If
sealant is not missing, restore the sealant that was previously removed to gain inspection access.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
533777-200, 777-200LR, 777-
300ER, 777F
Group 2:
Affected Maintenance Zones
ZoneModel
633777-300ER, 777F
Group 3:
Affected Maintenance Zones
ZoneModel
533, 633777-300ER, 777F
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
The Conditions, Actions and Compliance times shown apply to each wing panel gap location
independently.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
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Table 1: Detailed Inspection Intervals for Missing Sealant
Repeat Interval (Not
to Exceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 4000 flight cy-
cles or 750 days,
whichever occurs
first, after the original
issue date of this
service bulletin
Within 6000 flight cy-
cles or 1500 days,
whichever occurs
first, from the date of
issuance of the origi-
nal certificate of air-
worthiness or the
original export certifi-
cate of airworthiness.
Do PART 1: WING
SKIN PANEL GAPS
- DETAILED
SEALANT INSPEC-
TION for missing
sealant in the wing
skin panel gaps
above the underwing
fittings.
All Airplanes
--Before further flight.Do PART 2: WING
SKIN PANEL GAPS
- SEALANT
RESTORATION
(Terminating Action)
CONDITION 1: NO
MISSING SEALANT
FOUND
--Before further flight.Do PART 3: WING
SKIN PANEL GAPS
- DETAILED CORRO-
SION INSPECTION
for corrosion in the
wing skin panel gaps
above the underwing
fittings.
CONDITION 2:
MISSING SEALANT
FOUND
--Before further flight.ACTION 1: Contact
Boeing for repair in-
structions and do the
repair.
CONDITION 3: ANY
CORROSION
FOUND
ACTION 2: Do PART
2: WING SKIN PAN-
EL GAPS -
SEALANT
RESTORATION
(Terminating Action)
--Before further flight.Do PART 2: WING
SKIN PANEL GAPS
- SEALANT
RESTORATION
(Terminating Action)
CONDITION 4: NO
CORROSION
FOUND
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this inspection for each wing
panel gap location in the area of the underwing fittings. 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.
Group 1:
Table 1: Manpower Information for Group 1 Airplanes
Elapsed HoursTask HoursNumber of PersonsTask
6.0024.004Open Access
1.751.751FIGURE 1
1.001.001FIGURE 3
1.101.101FIGURE 5
6.0024.004Close Access
15.8551.85TOTAL FOR EACH AIRPLANE
Group 2:
Table 2: Manpower Information for Group 2 Airplanes
Elapsed HoursTask HoursNumber of PersonsTask
6.0024.004Open Access
1.751.751FIGURE 2
1.001.001FIGURE 4
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Group 2:
Table 2: Manpower Information for Group 2 Airplanes
Elapsed HoursTask HoursNumber of PersonsTask
1.101.101FIGURE 6
6.0024.004Close Access
15.8551.85TOTAL FOR EACH AIRPLANE
Group 3:
Table 3: Manpower Information for Group 3 Airplanes
Elapsed HoursTask HoursNumber of PersonsTask
6.0048.008Open Access
1.751.751FIGURE 1
1.751.751FIGURE 2
1.001.001FIGURE 3
1.001.001FIGURE 4
1.101.101FIGURE 5
1.101.101FIGURE 6
6.0048.008Close Access
19.70103.70TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None.
I. Electrical Load Data
Not changed.
J. References
1. Existing Data:
a. Boeing Service Letter 777-SL-51-013
b. Boeing Service Related Problem (SRP) 777-SRP-57-0265
c. Service Bulletin Index D624W001
d. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-43-03, 20-50-01, 20-50-19
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19
f. 777 Aircraft Maintenance Manual (AMM) 51-31-01, 54-52-04, 78-11-02
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g. 777 Fleet Team Digest (FTD) 57-13003
2. Data Supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
Nacelle Support Installation - Lower Panel112W7000
The table above lists applicable drawing used to prepare this service bulletin. The drawing is not
necessary to make the specified changes, and is not supplied with this service bulletin. The drawing
may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
M. Software Accomplishment Summary
Not affected.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
None.
B. Industry Support Information
Boeing warranty remedies are available for 777 airplanes in warranty as of August 7, 2013. For inspection
labor task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing
Warranty & Product Assurance Contracts. If the condition described in this service bulletin is found
during the inspection for airplanes in warranty as of that date and additional task hours are required,
send a warranty claim to Boeing Warranty & Product Assurance Contracts. Please refer to this service
bulletin number and reference the airplane variable numbers in your purchase order. The warranty
remedies will expire eight years from the original issue date of this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts
None.
2. Parts and Materials Supplied by the Operator
The following parts or materials are necessary to do the change in this service bulletin. Parts and
materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine
operator part and material supply to make sure all necessary parts and materials are available.
NotesNameQTYPart Number /
Specification
(a)Sealant1 QtBMS 5-95
(a)Primer8 OzBMS 10-79, Type
III
(a)Corrosion Inhibiting Compound8 OzSOPM 20-43-03
(a)Enamel8 OzBMS 10-60, Type
II
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)
for supplier data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
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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. Refer to APPENDIX A for optional
tools that Boeing used to do this rework.
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### Page 19

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
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 and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 777 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 777
Airplane Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 777
Airplane Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,
and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
6. The necessary conditions for selection of clamp type and size are included in SWPM
20-10-12. If any wire bundle support clamp specified in this service bulletin does not
make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted
procedure to select a clamp that fits correctly.
7. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate
full threaded fasteners (screws) needed for installation in this service bulletin.
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### Page 20

8. 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.
9. 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.
10. Boeing Service Letter 777-SL-51-013, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
11. Refer to APPENDIX A for information on tools and procedures used by Boeing for
the production rework equivalent to this Service Bulletin.
12. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
13. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
14. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
15. If shading is used, shaded areas in Figures are to separate the non-critical and
non-authoritative information from the critical and authoritative information.
16. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
17. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS
are in Paragraph 1.E., Compliance.
18. The CONDITIONS, ACTIONS and OPTIONS shown apply to each wing panel gap
location independently.
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### Page 21

19. Some steps in the Work Instructions are identified as Required for Compliance (RC).
If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps
identified as RC must be done to comply with the AD. Alternative procedures for
steps not identified with RC can be used if the RC steps can still be done as specified,
and the airplane can be put back in a serviceable condition. An Alternative Method
of Compliance (AMOC) is not necessary for deviations to steps that are not identified
as RC.
B. WORK INSTRUCTIONS
1. Do PART 1: WING SKIN PANEL GAPS - DETAILED SEALANT INSPECTION for missing sealant
in the wing skin panel gaps above the underwing fittings.
CONDITION 1: NO MISSING SEALANT FOUND
a. Do PART 2: WING SKIN PANEL GAPS - SEALANT RESTORATION (Terminating Action).
CONDITION 2: MISSING SEALANT FOUND
a. Do PART 3: WING SKIN PANEL GAPS - DETAILED CORROSION INSPECTION for corrosion
in the wing skin panel gaps above the underwing fittings.
CONDITION 3: ANY CORROSION FOUND
(1) ACTION 1: Contact Boeing for repair instructions and do the repair.
(2) ACTION 2: Do PART 2: WING SKIN PANEL GAPS - SEALANT RESTORATION
(Terminating Action).
CONDITION 4: NO CORROSION FOUND
(1) Do PART 2: WING SKIN PANEL GAPS - SEALANT RESTORATION (Terminating Action).
PART 1: WING SKIN PANEL GAPS - DETAILED SEALANT INSPECTION
1. Remove the aft fairing. Refer to 777 AMM 54-52-04 as an accepted procedure.
NOTE: It is recommended to remove the aft turbine exhaust plug before the removal of the aft
fairing, to prevent any damage to the aft turbine exhaust plug. Refer to 777 AMM 78-11-02
as an accepted procedure.
2. RC - Do a Detailed Inspection (DET) for missing sealant in the wing skin panel gaps above the
underwing fittings in accordance with the figures below:
Group 1:
Right WingLeft Wing
-FIGURE 1
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### Page 22

Group 2:
Right WingLeft Wing
FIGURE 2-
Group 3:
Right WingLeft Wing
FIGURE 2FIGURE 1
PART 2: WING SKIN PANEL GAPS - SEALANT RESTORATION
1. RC - Restore the sealant in accordance with the figures below:
Group 1:
Right WingLeft Wing
-FIGURE 3
Group 2:
Right WingLeft Wing
FIGURE 4-
Group 3:
Right WingLeft Wing
FIGURE 4FIGURE 3
2. Install the aft fairing. Refer to 777 AMM 54-52-04 as an accepted procedure.
NOTE: If the aft turbine exhaust plug was removed for access, install the aft turbine exhaust
plug. Refer to 777 AMM 78-11-02 as an accepted procedure.
3. Put the airplane back to a serviceable condition.
PART 3: WING SKIN PANEL GAPS - DETAILED CORROSION INSPECTION
1. RC - Do a detailed inspection for corrosion in accordance with the figures below.
Group 1:
Right WingLeft Wing
-FIGURE 5
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### Page 23

Group 2:
Right WingLeft Wing
FIGURE 6-
Group 3:
Right WingLeft Wing
FIGURE 6FIGURE 5
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### Page 24 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
This Figure applies only to: Group 1, 3.
00GS
BD
FIGURE 1: LEFT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 1 OF 4)
Original Issue: January 10, 2014
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### Page 25 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
UNDERWING  SEALANT
FITTING
WING SKIN
PANEL
0.50
MINIMUM  2.25
- 1.75
2.25
1.75
SEALANT  0.50
MINIMUM
WING SKIN
PANEL  TYPICAL
A-A
2283189
FIGURE 1: LEFT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 2 OF 4)
Original Issue: January 10, 2014
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### Page 26

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 this figure.
CAUTION: USE ONLY NON-METALLIC TOOLS TO REMOVE THE SEALANT IN THE WING SKIN PANEL
GAPS IN THE AREA OF THE UNDERWING FITTINGS. USE OF METALLIC TOOLS CAN CAUSE
DAMAGE TO THE WING SKIN.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove sealant from the wing skin
panel gaps not covered by the under-
wing fittings in the area shown. Refer to
777 AMM 51-31-01 as an accepted pro-
cedure.
--SealantRemove1
(a)
Remove sealant from the wing skin
panel gaps covered by the underwing
fittings in the area shown. Refer to 777
AMM 51-31-01 as an accepted proce-
dure.
--SealantRemove2
(a)
Do a Detailed Inspection (DET) for any
void that may indicate missing sealant
in the area beyond the sealant portion
that was removed.
--SealantInspect3
(a) (b)
(a) Refer to APPENDIX A for additional optional tool information.
FIGURE 1: LEFT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 3 OF 4)
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### Page 27

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b) Any solvent used for sealant removal should be allowed to dry for a minimum of 15 minutes before inspecting
the remaining sealant.
It is acceptable to modify an existing non-metallic sealant scraping tool to fit into the wing skin panel gaps,
which are 0.06 inch to 0.2 inch wide.
One method to inspect for the presence or absence of sealant is to lightly tap the remaining sealant in the
wing skin panel gaps above the underwing fittings using a rubber mallet and a non-metallic tool. Another
method for this inspection is to probe the sealant using a non-metallic tool by applying firm hand pressure
to the existing sealant.
The presence of properly applied sealant in the wing skin panel gaps above the underwing fittings is indi-
cated by resistance against the non-metallic tool when the non-metallic tool is tapped with a rubber mallet,
or when firm hand pressure is applied to it. The non-metallic tool should not advance into the existing
sealant when tapped or when firm hand pressure it applied to it.
Missing sealant is indicated by reduced resistance of the sealant being tapped or manually pressed with
the non-metallic tool. Obvious movement of the non-metallic tool into the existing sealant also indicates
the absence of sealant. Missing sealant may also be indicated by any obvious sealant discontinuities
found during the minimum of 0.5 inch sealant removal from the wing skin panel gaps, for access. The
non-metallic tools used for sealant removal for access may advance suddenly, indicating incorrectly applied
sealant at that location during production.
FIGURE 1: LEFT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 4 OF 4)
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### Page 28 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
This Figure applies only to: Group 2-3.
000
2283580
FIGURE 2: RIGHT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 1 OF 4)
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### Page 29 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
SEALANT  -FITTING  UNDERWING
WING SKIN
PANEL
0.50
MINIMUM
1.25.
• 2.25
1.75.
0.50  SEALANT
MINIMUM
WING SKIN
PANEL
TYPICAL
A-A
2283579
FIGURE 2: RIGHT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 2 OF 4)
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### Page 30

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 this figure.
CAUTION: USE ONLY NON-METALLIC TOOLS TO REMOVE THE SEALANT IN THE WING SKIN PANEL
GAPS IN THE AREA OF THE UNDERWING FITTINGS. USE OF METALLIC TOOLS CAN CAUSE
DAMAGE TO THE WING SKIN.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Remove sealant from the wing skin
panel gaps not covered by the under-
wing fittings in the area shown. Refer to
777 AMM 51-31-01 as an accepted pro-
cedure.
--SealantRemove1
(a)
Remove sealant from the wing skin
panel gaps covered by the underwing
fittings in the area shown. Refer to 777
AMM 51-31-01 as an accepted proce-
dure.
--SealantRemove2
(a)
Do a Detailed Inspection (DET) for any
void that may indicate missing sealant
in the area beyond the sealant portion
that was removed.
--SealantInspect3
(a) (b)
(a) Refer to APPENDIX A for additional optional tool information.
FIGURE 2: RIGHT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 3 OF 4)
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ALERTALERT

### Page 31

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
(b) Any solvent used for sealant removal should be allowed to dry for a minimum of 15 minutes before inspecting
the remaining sealant.
It is acceptable to modify an existing non-metallic sealant scraping tool to fit into the wing skin panel gaps,
which are 0.06 inch to 0.2 inch wide.
One method to inspect for the presence or absence of sealant is to lightly tap the remaining sealant in the
wing skin panel gaps above the underwing fittings using a rubber mallet and a non-metallic tool. Another
method for this inspection is to probe the sealant using a non-metallic tool by applying firm hand pressure
to the existing sealant.
The presence of properly applied sealant in the wing skin panel gaps above the underwing fittings is indi-
cated by resistance against the non-metallic tool when the non-metallic tool is tapped with a rubber mallet,
or when firm hand pressure is applied to it. The non-metallic tool should not advance into the existing
sealant when tapped or when firm hand pressure it applied to it.
Missing sealant is indicated by reduced resistance of the sealant being tapped or manually pressed with
the non-metallic tool. Obvious movement of the non-metallic tool into the existing sealant also indicates
the absence of sealant. Missing sealant may also be indicated by any obvious sealant discontinuities
found during the minimum of 0.5 inch sealant removal from the wing skin panel gaps, for access. The
non-metallic tools used for sealant removal for access may advance suddenly, indicating incorrectly applied
sealant at that location during production.
FIGURE 2: RIGHT WING - WING SKIN PANEL GAP SEALANT INSPECTION
(SHEET 4 OF 4)
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### Page 32 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
This Figure applies only to: Group 1, 3.
00GS
IBD
FIGURE 3: LEFT WING - WING SKIN PANEL GAP SEALANT REPAIR
(SHEET 1 OF 3)
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### Page 33 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
UNDERWING  SEALANT
FITTING
WING SKIN
PANEL
12 3 45 6
SEALANT
23 45 6
WING SKIN
PANEL
TYPICAL
A-A
2283586
FIGURE 3: LEFT WING - WING SKIN PANEL GAP SEALANT REPAIR
(SHEET 2 OF 3)
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### Page 34

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 this figure.
CAUTION: USE ONLY NON-METALLIC TOOLS TO REMOVE THE SEALANT IN THE WING SKIN PANEL
GAPS IN THE AREA OF THE UNDERWING FITTINGS. USE OF METALLIC TOOLS CAN CAUSE
DAMAGE TO THE WING SKIN.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-30-03 as an accepted
procedure.
--Wing Skin Panel GapClean1
(a)
to any bare aluminum surface.--Chemical Conversion
Coating
Apply2
Refer to SOPM 20-43-03 as an accepted
procedure.
to any surface where primer was re-
moved.
BMS 10-79, Type
III
PrimerApply3
Refer to SOPM 20-50-19 as an accepted
procedure.
-BMS 5-95SealantApply4
(a)
BMS10-79, Type IIIPrimerApply5
BMS10-60, Type IIEnamelApply6
(a) If the sealant was removed from the entire gap area above the underwing fitting, then clean the entire
area where sealant was removed before new sealant is applied.
FIGURE 3: LEFT WING - WING SKIN PANEL GAP SEALANT REPAIR
(SHEET 3 OF 3)
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ALERTALERT

### Page 35 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
This Figure applies only to: Group 2-3.
000
2283585
FIGURE 4: RIGHT WING - WING SKIN PANEL GAP SEALANT REPAIR
(SHEET 1 OF 3)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
SEALANT  FITTING  UNDERWING  WING SKIN
' PANEL
DE3460
SEALANT
1) 2)(4
WING SKIN
PANEL
TYPICAL
A-A  2283583
FIGURE 4: RIGHT WING - WING SKIN PANEL GAP SEALANT REPAIR
(SHEET 2 OF 3)
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### Page 37

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 this figure.
CAUTION: USE ONLY NON-METALLIC TOOLS TO REMOVE THE SEALANT IN THE WING SKIN PANEL
GAPS IN THE AREA OF THE UNDERWING FITTINGS. USE OF METALLIC TOOLS CAN CAUSE
DAMAGE TO THE WING SKIN.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Refer to SOPM 20-30-03 as an accepted
procedure.
--Wing Skin Panel GapClean1
(a)
to any bare aluminum surface.--Chemical Conversion
Coating
Apply2
Refer to SOPM 20-43-03 as an accepted
procedure.
to any surface where primer was re-
moved.
BMS 10-79, Type
III
PrimerApply3
Refer to SOPM 20-50-19 as an accepted
procedure.
-BMS 5-95SealantApply4
(a)
BMS10-79, Type IIIPrimerApply5
BMS10-60, Type IIEnamelApply6
(a) If the sealant was removed from the entire gap area above the underwing fitting, then clean the entire
area where sealant was removed before new sealant is applied.
FIGURE 4: RIGHT WING - WING SKIN PANEL GAP SEALANT REPAIR
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 777-57A0097
ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
This Figure applies only to: Group 1, 3.
00GS
BD
FIGURE 5: LEFT WING - WING SKIN PANEL GAP CORROSION INSPECTION
(SHEET 1 OF 3)
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### Page 39 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
UNDERWING  SEALANT
FITTING
WING SKIN
PANEL
SEALANT
WING SKIN
PANEL  TYPICAL
ASSIS INSPECTION AREA  A-A  2283588
FIGURE 5: LEFT WING - WING SKIN PANEL GAP CORROSION INSPECTION
(SHEET 2 OF 3)
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### Page 40

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each location where missing sealant was found.
CAUTION: USE ONLY NON-METALLIC TOOLS TO REMOVE THE SEALANT IN THE WING SKIN PANEL
GAPS IN THE AREA OF THE UNDERWING FITTINGS. USE OF METALLIC TOOLS CAN CAUSE
DAMAGE TO THE WING SKIN.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
from the area directly above the under-
wing fitting, where sealant was not previ-
ously removed. Refer to 777 AMM 51-
31-01 as an accepted procedure.
--SealantRemove1
(a)
Refer to SOPM 20-30-03 as an accepted
procedure.
--Wing Skin Panel GapClean
Do a DET for corrosion. A borescope or
Remote Visual Inspection (RVI) is recom-
mended. Refer to APPENDIX A for addi-
tional optional borescope information.
--Wing Skin Panel GapInspect2
(a) Use non-metallic tools to abrade most of the sealant in the wing skin panel gaps without damaging the
adjacent wing and underwing fitting structure and finishes. Refer to APPENDIX A for additional tool infor-
mation.
FIGURE 5: LEFT WING - WING SKIN PANEL GAP CORROSION INSPECTION
(SHEET 3 OF 3)
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BOEING SERVICE BULLETIN 777-57A0097
ALERTALERT

### Page 41 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
This Figure applies only to: Group 2-3.
000
FIGURE 6: RIGHT WING - WING SKIN PANEL GAP CORROSION INSPECTION
(SHEET 1 OF 3)
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### Page 42 (OCR)

BOEING SERVICE BULLETIN 777-57A0097
ALERT  ALERT
SEALANT  FITTING  UNDERWING
WING SKIN
PANEL
SEALANT
WING SKIN
PANEL
TYPICAL
SY INSPECTION AREA  A-A  2283589
FIGURE 6: RIGHT WING - WING SKIN PANEL GAP CORROSION INSPECTION
(SHEET 2 OF 3)
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### Page 43

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 this figure.
CAUTION: USE ONLY NON-METALLIC TOOLS TO REMOVE THE SEALANT IN THE WING SKIN PANEL
GAPS IN THE AREA OF THE UNDERWING FITTINGS. USE OF METALLIC TOOLS CAN CAUSE
DAMAGE TO THE WING SKIN.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
from the area directly above the under-
wing fitting, where sealant was not previ-
ously removed. Refer to 777 AMM 51-
31-01 as an accepted procedure.
--SealantRemove1
(a)
Refer to SOPM 20-30-03 as an accepted
procedure.
--Wing Skin Panel GapClean
Do a DET for corrosion. A borescope or
Remote Visual Inspection (RVI) is recom-
mended. Refer to APPENDIX A for addi-
tional optional borescope information.
--Wing Skin Panel GapInspect2
(a) Use non-metallic tools to abrade most of the sealant in the wing skin panel gaps without damaging the
adjacent wing and underwing fitting structure and finishes. Refer to APPENDIX A for additional tool infor-
mation.
FIGURE 6: RIGHT WING - WING SKIN PANEL GAP CORROSION INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
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Work - See page 1 for details.
Original Issue: January 10, 2014
777-57A0097
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BOEING SERVICE BULLETIN 777-57A0097
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### Page 44

This Appendix includes information about the non-metallic tools and materials that were used by Boeing for the
removal of sealant and the inspection for corrosion in production. Other procedures and other non-metallic tools
and materials may be used at the operators' discretion. This information is for reference only.
CAUTION: USE ONLY NON-METALLIC TOOLS TO REMOVE THE SEALANT IN THE WING SKIN PANEL
GAPS IN THE AREA OF THE UNDERWING FITTINGS. USE OF METALLIC TOOLS CAN CAUSE
DAMAGE TO THE WING SKIN.
SEALANT REMOVAL TOOLS USED BY BOEING FOR THE WORK EQUIVALENT TO PART 1 DETAILED
(DET) INSPECTION
The following non-metallic tools were used by Boeing in production for the work equivalent to PART 1 sealant
removal in this service bulletin:
– Existing non-metallic sealant scrapers modified to match the width of the wing panel gaps, which are 0.06
inch to 0.2 inch wide.
– Small manual saws fabricated from Torlon polyamide-imide stock.
– Non-metallic drill bits fabricated from polyether imide (PEI) stock to make the sealant removal more time
effective.
Refer to Fleet Team Digest (FTD) article 777 FTD 57-13003 for additional tool photographs and information.
SEALANT REMOVAL TOOLS AND PROCEDURES USED IN PREPARATION FOR THE CORROSION
INSPECTION
Where missing sealant was found during the DET in Part 1, any sealant in the wing panel gap above the entire
width of the affected underwing fitting was required to be removed. This was done in production in preparation
for the corrosion inspection work that is equivalent to Part 3 DET in this service bulletin.
The sealant removal from the remaining area above the affected underwing fitting required non-metallic tools
capable to abrade most of the sealant in the wing skin panel gaps without damaging the adjacent wing and
underwing fitting structure and finishes. Some tool variations that were used to remove the sealant in the wing
skin panel gap above the entire width of the affected underwing fitting include, but are not limited to:
– Teflon or nylon rope that was knotted to create a rough surface that can abrade the sealant in the gap above
the underwing fittings
– Wire ties connected together to create a rough surface similar to the knotted Teflon or nylon rope mentioned
above
– OREGON brand Flexiblade nylon stock with 0.118 inch, 0.105 inch, and 0.099 inch cross sections (part
numbers 21-602, 21-601, and 21-600, respectively). Refer to http://www.oregonproducts.com for additional
information on this product.
BORESCOPE INFORMATION
APPENDIX A:  SEALANT REMOVAL TOOLS AND PROCEDURES
(SHEET 1 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 10, 2014
777-57A0097
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BOEING SERVICE BULLETIN 777-57A0097
ALERTALERT

### Page 45

Boeing performed a Remote Visual Inspection (RVI) of the wing panel gap for corrosion using an Olympus
IPLEX TX 2.4 mm (0.094 inch) videoscope. This videoscope was sufficiently small to fit in the wing panel gap,
which is 0.06 inch to 0.2 inch wide. Refer to http://www.olympus-ims.com for additional information on this
videoscope.
APPENDIX A:  SEALANT REMOVAL TOOLS AND PROCEDURES
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 10, 2014
777-57A0097
45 of 45
BOEING SERVICE BULLETIN 777-57A0097
ALERTALERT

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