# Boeing Alert Service Bulletin 777-53A0068: No revision named

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- Document: [Boeing Alert Service Bulletin 777-53A0068](https://openairdocs.org/service-documents/boeing/777-53a0068.md)
- Title as filed: U.S. DOT/FAA - SB-777-53A0068-00
- Pages: 76
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### Page 1

Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-53A0068
Original Issue: June 12, 2013
ATA System: 5345 5365 2315
SUBJECT: FUSELAGE - Sections 44 and 46 - Crown Skin Panel - Corrosion and Crack on Fuselage
Skin Below SATCOM Antenna Adapter Plate - Inspection
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 © 2013 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Unpublished Work.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
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connection with this document unless provided in writing by Boeing.
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Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 7
B. Concurrent Requirements ...................................... 1 7
C. Reason ................................................ 1 7
D. Description .............................................. 1 9
E. Compliance .............................................. 2 0
F. Approval ............................................... 3 9
G. Manpower .............................................. 4 0
H. Weight and Balance Changes .................................... 4 2
I. Electrical Load Data ......................................... 4 2
J. References .............................................. 4 2
1. Existing Data: ......................................... 4 2
2. Data Supplied with this Service Bulletin: ........................... 4 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 3
K. Publications Affected ........................................ 4 3
L. Interchangeability and Intermixability of Parts ........................... 4 3
M. Software Accomplishment Summary ................................ 4 3
2. MATERIAL INFORMATION ........................................ 4 5
A. Material - Price and Availability ................................... 4 5
B. Industry Support Information .................................... 4 5
C. Parts Necessary for Each Airplane ................................. 4 5
1. Kits/Parts ............................................ 4 5
2. Parts and Materials Supplied by the Operator ........................ 4 5
3. Parts Modified and Reidentified ................................ 4 5
4. Parts Removed and Not Replaced .............................. 4 5
D. Parts Necessary to Change Spares ................................. 4 5
E. Special Tooling - Price and Availability ............................... 4 5
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 7
A. GENERAL INFORMATION ..................................... 4 7
B. WORK INSTRUCTIONS ....................................... 4 8
FIGURE 1: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE
FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE [Group 1-2] . . . 53
FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION
[Group 1-2] ........................................... 5 5
FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION
[Group 1-2] ........................................... 5 8
FIGURE 4: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE
FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE [Group 2] .... 6 1
FIGURE 5: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION
[Group 2] ............................................ 6 3
FIGURE 6: SECTION 44 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION
[Group 2] ............................................ 6 6
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FIGURE 7: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE
FASTENER COMMON TO BONDING JUMPER AND ADAPTER PLATE [Group 3-4; Group 5,
Configuration 3-4] ....................................... 6 9
FIGURE 8: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION
[Group 3-4; Group 5, Configuration 3-4] ............................ 7 1
FIGURE 9: SECTION 46 - 2-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION
[Group 3-4; Group 5, Configuration 3-4] ............................ 7 4
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Commercial 
Airplanes
777
Service Bulletin
ALERT
SummaryNumber: 777-53A0068Original Issue: June 12, 2013
ATA System: 5345 5365 2315
SUBJECT: FUSELAGE - Sections 44 and 46 - Crown Skin Panel - Corrosion and Crack on Fuselage
Skin Below SATCOM Antenna Adapter Plate - Inspection
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
This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin under 2-bay
and 3-bay satellite communication (SATCOM) antenna adapter plates located in Sections 44 and 46. There
could be fretting and damage to the fuselage skin finish due to a contact between the adapter plate bonding
jumper and fuselage skin. Removal of finish in the fuselage skin results in exposure to corrosion, which can lead
to cracks. Cracks in the fuselage skin that are not found and repaired can propagate to the point where the
fuselage skin structure cannot sustain limit load. When the fuselage skin cannot sustain limit load, this can
results in possible rapid decompression and loss of structural integrity.
One operator reported a 16 inch crack under the 3-bay SATCOM antenna adapter plate in the crown skin of the
fuselage between STA 1601 and STA 1622 (Section 46), and S-1L and S-2L on an airplane that was 14 years
old with approximately 14,000 total flight cycles. This crack was found while doing Maintenance Planning Data
(MPD) inspection, 777 MPD Section 2, 53-598-00, which requires fuselage skin inspection between STA 1434
and STA 1832. As a part of the MPD inspection, removal of antennas and adapter plates are necessary to
access the entire fuselage skin. Subsequent to this crack finding, the same operator inspected 42 other airplanes
that are between 6 and 16 years old and found some local corrosion, but no other cracking.
Boeing has performed metallurgical fracture analysis of the section of the fuselage skin with the 16 inch crack,
which was sent in by the operator. The damaged fuselage skin showed that the braided section of the bonding
jumper cable was contacting the skin. The contact between the bonding jumper and fuselage skin results in
fretting and removal of the fuselage skin finish. The removal of finish results in exposure to corrosion. The
damaged skin panel showed severe exfoliation corrosion in the area where the braided section of the bonding
jumper contacted the skin. The fracture analysis showed that primary crack initiated at the area of the exfoliation
corrosion. The analysis also showed that cracking progressed by intergranular stress corrosion partially through
thickness for 13.5 inches along the interior surface of the skin. Further propagation of the crack through to the
exterior surface occurred by fatigue.
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In addition, Boeing has performed an analysis of SATCOM antenna installations. The installation drawing for
3-bay SATCOM antenna in Section 46 show no clearance between the fuselage skin and the fastener attaching
the SATCOM lug adapter plate to the bonding jumper. Due to the lack of clearance, the fastener may come in
contact with the fuselage skin. Furthermore, the fastener is located between stringers where the fastener can
have a contact with the fuselage due to pillowing out effect when the fuselage is pressurized. The fastener
contact with the fuselage skin results in fretting that causes removal of the fuselage skin finish, which results in
exposure to corrosion.
Boeing has also determined that there are 2-bay and 3-bay SATCOM antennas that are installed at two locations.
The "2-bay" and "3-bay" terminologies are used to describe the length of the antenna in terms of frame bays.
The 2-bay SATCOM antennas are 2 frame bays long and are installed in Section 46. The 3-bay SATCOM
antennas are 3 frame bays long and are installed in Section 44 or Section 46, or both. Airplanes can be delivered
with either 2-bay or 3-bay SATCOM antenna in Section 46 as a primary option. If a SATCOM antenna is installed
in Section 46, additional 3-bay SATCOM antenna in Section 44 can be installed as a dual option. The analysis
showed that both 2-bay and 3-bay SATCOM antennas in Sections 44 and 46 can have similar issues related
to bonding jumper and the fastener contacting the skin that results in fretting and removal of fuselage skin finish.
The fretting and presence of corrosion are factors that can lead to fuselage skin cracking.
This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin under 2-bay
and 3-bay SATCOM antenna adapter plates located in Sections 44 and 46 of the airplane.
Boeing Service Related Problem (SRP) 777-SRP-53-0418 is related to this service bulletin. A future service
bulletin will be issued to give a terminating action for the continued inspections given in this service bulletin.
NOTE: There has been a production change to the bonding jumper installation for 3-bay SATCOM antennas
in Section 44 at line number 1068 and on, and in Section 46 at line number 1077 and on. There has
not been a production change to the bonding jumper installation for 2-bay SATCOM antennas.
Boeing Fleet Team Digest (FTD) 777 FTD 53-12001 is related to this service bulletin.
This table is provided to operators for planning purposes only. Refer to the applicable sections for more
information.
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
NoOperator Supplied Material
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ReferenceAffectedPlanning Data
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION
Group 5, Configuration 1-2, 5:
No action is necessary in accordance with this service bulletin.
Group 1-4; Group 5, Configuration 3-4:
Get internal and external access to SATCOM antenna(s). Do repetitive internal and external detailed and surface
high frequency eddy current (HFEC) inspections of the visible fuselage skin and doubler, if installed. If any
corrosion or crack is found, do a repair in accordance with 777 SRM or contact Boeing for repair instructions
and do the repair. If an indication is found that shows a contact of the fastener attaching the SATCOM lug adapter
plate to the bonding jumper, contact Boeing for repair instructions and do the repair. After the repair, repeat the
inspections in accordance with this service bulletin. Put the airplane back to a serviceable condition.
EFFECTIVITY
777-200, 777-200LR, 777-300, 777-300ER, and 777F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the
list of affected airplane(s).
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.
Group 5, Configuration 1-2, 5:
None. No action is necessary in accordance with this service bulletin.
Group 1-4; Group 5, Configuration 3-4:
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of June 25, 2012. 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.
MANPOWER
Group 5, Configuration 1-2, 5:
None. No action is necessary in accordance with this service bulletin.
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### Page 8

Group 1:
Elapsed HoursTotal Task HoursAirplanes
13.4017.60Group 1:
Section 46 - 3-
Bay SATCOM
Antenna - Fuse-
lage Skin Inspec-
tion
Group 2:
Elapsed HoursTotal Task HoursAirplanes
26.8035.20Group 2:
Sections 44 and
46 - 3-Bay SAT-
COM Antenna -
Fuselage Skin
Inspection
Group 3-4; Group 5, Configuration 3-4:
Elapsed HoursTotal Task HoursAirplanes
13.4017.60Group 3-4; 5,
Configuration 3-
4:
Section 46 - 2-
Bay SATCOM
Antenna - Fuse-
lage Skin Inspec-
tion
MATERIAL INFORMATION
None.
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### Page 9 (OCR)

BOEING SERVICE BULLETIN 777-53A0068
ALERT  ALERT
STA
1601
STA
1077
GET ACCESS TO 2-BAY AND 3-BAY
SATCOM ANTENNAS IN SECTIONS 44 AND
46 AS APPLICABLE. DO INTERNAL AND
EXTERNAL DETAILED AND SURFACE HFEC
INSPECTIONS OF THE FUSELAGE SKIN
UNDER THE SATCOM ANTENNAS. FOR
CORRECTIVE ACTION, DO A REPAIR IN
ACCORDANCE WITH 777 SRM OR
CONTACT BOEING FOR REPAIR
INSTRUCTIONS AND DO THE REPAIR.
CONTINUE TO DO REPEAT INSPECTIONS
OF THE FUSELAGE SKIN AND DOUBLER, IF
INSTALLED.  PUT THE AIRPLANE BACK TO
A SERVICEABLE CONDITION.
3-BAY SATCOM
ANTENNA SHOWN  S-2L
(2-BAY SATCOM
ANTENNA SIMILAR)  S-1L
" S-2R
2182690
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Commercial 
Airplanes
777
Service Bulletin
ALERT
Number: 777-53A0068
Original Issue: June 12, 2013
ATA System: 5345 5365 2315
SUBJECT: FUSELAGE - Sections 44 and 46 - Crown Skin Panel - Corrosion and Crack on Fuselage
Skin Below SATCOM Antenna Adapter Plate - Inspection
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
Refer to Service Bulletin Index D624W001 Part 3 for Airplane Variable Number, Line Number, and
Serial Number data.
This service bulletin is for the airplane(s) shown below.
NOTE: This service bulletin is for the airplanes identified in the Group Configuration table. The
effectivity list shown below includes airplanes up to line number 1202. Some airplanes
before line number 1202 may be affected by this service bulletin but not included in the
effectivity list because they are being delivered out of sequence. At least one airplane,
either before or after line number 1202 or both, is affected by this service bulletin and
these airplanes are in Group(s) 5. These airplanes will be added to the service bulletin's
MyBoeingFleet.com (MBF) "get effectivity" result when they are added to the MBF Fleet
Profile Page.
DESCRIPTIONCONFIGURATIONGROUP
Airplanes line number 1 through 1076 with 3-bay SATCOM antenna
in Section 46. These airplanes do not have SATCOM antenna in
Section 44.
-1
Airplanes line number 1 through 1067 with 3-bay SATCOM antenna
in Sections 44 and 46.
-2
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DESCRIPTIONCONFIGURATIONGROUP
Airplanes line number 1 through 1123 with 2-bay SATCOM antenna
in Section 46. These airplanes do not have SATCOM antenna in
Section 44.
-3
Airplanes line number 1068 through 1123 with 3-bay SATCOM
antenna in Section 44 and 2-bay SATCOM antenna in Section 46.
-4
Airplanes not delivered at the original issue date of this service bulletin
and the SATCOM antenna configuration is unknown.
-5
Airplanes with 3-bay SATCOM antenna in Section 46. These airplanes
have a production change to the bonding jumper installation for 3-bay
SATCOM antenna in Section 46. These airplanes do not have
SATCOM antenna in Section 44.
1
Airplanes with 3-bay SATCOM antenna in Sections 44 and 46. These
airplanes have a production change to the bonding jumper installation
for 3-bay SATCOM antenna in Sections 44 and 46.
2
Airplanes with 2-bay SATCOM antenna in Section 46. These airplanes
do not have a production change to the bonding jumper installation
for 2-bay SATCOM antenna in Section 46. These airplanes do not
have SATCOM antenna in Section 44.
3
Airplanes with 3-bay SATCOM antenna in Section 44 and 2-bay
SATCOM antenna in Section 46. These airplanes have a production
change to the bonding jumper installation for 3-bay SATCOM antenna
in Section 44. These airplanes do not have a production change to
the bonding jumper installation for 2-bay SATCOM antenna in Section
46.
4
Airplanes with no SATCOM antenna.5
Airplane Models:
777-200, 777-200LR, 777-300, 777-300ER, 777F
GroupVariable Number
1WB105 - WB106
1WB140 - WB148
1WB151 - WB155
1WB176 - WB177
1WB181 - WB194
1WB201 - WB215
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GroupVariable Number
1WB231 - WB247
2WB271 - WB273
2WB276 - WB286
2WB291 - WB302
1WB311 - WB337
1WB341 - WB342
1WB366 - WB368
1WB371 - WB388
2WB406
1WB416 - WB439
1WB446 - WB453
2WB476
1WB501 - WB512
1WB611 - WB622
1WB631 - WB638
1WB646 - WB649
1WC051 - WC073
1WC101 - WC104
1WC116 - WC120
1WC221 - WC224
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
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GroupVariable Number
1WC546 - WC548
1WC556
1WC566 - WC567
3WC571 - WC574
1WC581
1WC586
1WD001 - WD002
2WD011 - WD018
1WD031 - WD036
1WD046 - WD051
3WD052 - WD055
1WD066 - WD075
3WD081 - WD089
3WD091
3WD096
3WD101 - WD106
3WD111
1WD116 - WD117
5WD121
1WD501 - WD513
1WD521 - WD541
1WD546 - WD554
1WD561 - WD573
1WD581 - WD594
3WD595 - WD599
1WD606 - WD609
1WD621 - WD632
1WD651 - WD665
1WD671 - WD675
3WD676
1WD677
1WD691 - WD709
1WD741 - WD752
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GroupVariable Number
1WD761 - WD771
1WD786 - WD788
1WD796 - WD819
5WD820 - WD824
1WD826 - WD837
1WD846 - WD850
3WD851 - WD867
3WD871 - WD892
5WD893 - WD894
3WD911 - WD918
3WD921 - WD929
1WD936 - WD939
3WD940 - WD944
5WD945
3WD946 - WD957
3WD966 - WD970
1WD981 - WD982
1WD986 - WD987
1WD991 - WD992
5WD994
1WD996
1WE001 - WE004
1WE011 - WE012
3WE021 - WE026
1WE031 - WE034
3WE051 - WE055
3WE071 - WE072
5WE073 - WE075
3WE081 - WE084
1WE091 - WE093
5WE095
3WE126 - WE137
3WE141 - WE142
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GroupVariable Number
5WE143 - WE144
3WE151 - WE165
5WE166 - WE167
1WE176 - WE177
3WE186 - WE208
5WE209 - WE211
1WE216 - WE217
5WE218
1WE226 - WE231
1WE236 - WE240
5WE244
1WE251 - WE253
1WE261 - WE263
5WE266
3WE271 - WE276
5WE277 - WE278
5WE291 - WE292
3WE301 - WE309
5WE310 - WE311
4WE331 - WE334
5WE335 - WE336
5WE352 - WE356
5WE376 - WE377
5WE386 - WE387
5WE396
5WE417 - WE420
5WE426
5WE436
5WE441
3WF001 - WF004
3WF016 - WF022
5WF023
3WF031 - WF038
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GroupVariable Number
5WF039 - WF040
3WF046 - WF064
5WF065 - WF066
3WF075 - WF077
3WF081 - WF088
3WF096 - WF101
3WF106 - WF109
3WF111 - WF115
3WF121 - WF124
3WF131 - WF133
3WF136 - WF138
5WF139
3WF146 - WF147
3WF151 - WF152
5WF156 - WF157
5WF166
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin
under 2-bay and 3-bay satellite communication (SATCOM) antenna adapter plates located in Sections
44 and 46. There could be fretting and damage to the fuselage skin finish due to a contact between
the adapter plate bonding jumper and fuselage skin. Removal of finish in the fuselage skin results in
exposure to corrosion, which can lead to cracks. Cracks in the fuselage skin that are not found and
repaired can propagate to the point where the fuselage skin structure cannot sustain limit load. When
the fuselage skin cannot sustain limit load, this can results in possible rapid decompression and loss
of structural integrity.
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### Page 18

One operator reported a 16 inch crack under the 3-bay SATCOM antenna adapter plate in the crown
skin of the fuselage between STA 1601 and STA 1622 (Section 46), and S-1L and S-2L on an airplane
that was 14 years old with approximately 14,000 total flight cycles. This crack was found while doing
Maintenance Planning Data (MPD) inspection, 777 MPD Section 2, 53-598-00, which requires fuselage
skin inspection between STA 1434 and STA 1832. As a part of the MPD inspection, removal of antennas
and adapter plates are necessary to access the entire fuselage skin. Subsequent to this crack finding,
the same operator inspected 42 other airplanes that are between 6 and 16 years old and found some
local corrosion, but no other cracking.
Boeing has performed metallurgical fracture analysis of the section of the fuselage skin with the 16
inch crack, which was sent in by the operator. The damaged fuselage skin showed that the braided
section of the bonding jumper cable was contacting the skin. The contact between the bonding jumper
and fuselage skin results in fretting and removal of the fuselage skin finish. The removal of finish results
in exposure to corrosion. The damaged skin panel showed severe exfoliation corrosion in the area
where the braided section of the bonding jumper contacted the skin. The fracture analysis showed that
primary crack initiated at the area of the exfoliation corrosion. The analysis also showed that cracking
progressed by intergranular stress corrosion partially through thickness for 13.5 inches along the interior
surface of the skin. Further propagation of the crack through to the exterior surface occurred by fatigue.
In addition, Boeing has performed an analysis of SATCOM antenna installations. The installation
drawing for 3-bay SATCOM antenna in Section 46 show no clearance between the fuselage skin and
the fastener attaching the SATCOM lug adapter plate to the bonding jumper. Due to the lack of clearance,
the fastener may come in contact with the fuselage skin. Furthermore, the fastener is located between
stringers where the fastener can have a contact with the fuselage due to pillowing out effect when the
fuselage is pressurized. The fastener contact with the fuselage skin results in fretting that causes
removal of the fuselage skin finish, which results in exposure to corrosion.
Boeing has also determined that there are 2-bay and 3-bay SATCOM antennas that are installed at
two locations. The "2-bay" and "3-bay" terminologies are used to describe the length of the antenna in
terms of frame bays. The 2-bay SATCOM antennas are 2 frame bays long and are installed in Section
46. The 3-bay SATCOM antennas are 3 frame bays long and are installed in Section 44 or Section 46,
or both. Airplanes can be delivered with either 2-bay or 3-bay SATCOM antenna in Section 46 as a
primary option. If a SATCOM antenna is installed in Section 46, additional 3-bay SATCOM antenna in
Section 44 can be installed as a dual option. The analysis showed that both 2-bay and 3-bay SATCOM
antennas in Sections 44 and 46 can have similar issues related to bonding jumper and the fastener
contacting the skin that results in fretting and removal of fuselage skin finish. The fretting and presence
of corrosion are factors that can lead to fuselage skin cracking.
This service bulletin gives instructions to inspect for corrosion and cracks in the crown fuselage skin
under 2-bay and 3-bay SATCOM antenna adapter plates located in Sections 44 and 46 of the airplane.
Boeing Service Related Problem (SRP) 777-SRP-53-0418 is related to this service bulletin. A future
service bulletin will be issued to give a terminating action for the continued inspections given in this
service bulletin.
NOTE: There has been a production change to the bonding jumper installation for 3-bay SATCOM
antennas in Section 44 at line number 1068 and on, and in Section 46 at line number 1077
and on. There has not been a production change to the bonding jumper installation for 2-bay
SATCOM antennas.
Boeing Fleet Team Digest (FTD) 777 FTD 53-12001 is related to this service bulletin.
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### Page 19

D. Description
Group 5, Configuration 1-2, 5:
No action is necessary in accordance with this service bulletin.
Group 1-4; Group 5, Configuration 3-4:
Get internal and external access to SATCOM antenna(s). Do repetitive internal and external detailed
and surface high frequency eddy current (HFEC) inspections of the visible fuselage skin and doubler,
if installed. If any corrosion or crack is found, do a repair in accordance with 777 SRM or contact Boeing
for repair instructions and do the repair. If an indication is found that shows a contact of the fastener
attaching the SATCOM lug adapter plate to the bonding jumper, contact Boeing for repair instructions
and do the repair. After the repair, repeat the inspections in accordance with this service bulletin. Put
the airplane back to a serviceable condition.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
253, 254777-200, 777-200LR, 777-300,
777-300ER
Group 2:
Affected Maintenance Zones
ZoneModel
243, 244, 253, 254777-200, 777-200LR
Group 3:
Affected Maintenance Zones
ZoneModel
253, 254777-200, 777-200LR, 777-
300ER, 777F
Group 4:
Affected Maintenance Zones
ZoneModel
253, 254777-300ER
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### Page 20

Group 5:
Affected Maintenance Zones
ZoneModel
253, 254777-200, 777-200LR, 777-300,
777-300ER, 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.
Group 5, Configuration 1-2, 5:
None. No action is necessary in accordance with this service bulletin.
Group 5, Configuration 3-4:
Refer to Table 13 for the Compliance Information for Section 46 - 2-Bay SATCOM Antenna.
Group 1-4:
Use the Compliance Information Index tables to find the applicable Fuselage Skin Inspection compliance
table for each affected SATCOM antenna. Refer to the following table for the Compliance Information
Index tables.
Group 1-4:
NOTE: In the compliance table titles, the compliance information in terms of "Days" refers to the time
since the date of issuance of the original certificate of airworthiness or the original export
certificate of airworthiness.
Group 1-4:
Group 4Group 3Group 2Group 1Compliance Infor-
mation Index Ta-
ble
SATCOM Antenna
Location/Description
--XXTable 1Section 46 - 3-Bay SATCOM
Antenna
--X-Table 5Section 44 - 3-Bay SATCOM
Antenna
XX--Table 9Section 46 - 2-Bay SATCOM
Antenna
Group 1-2:
Table 1: Section 46 - 3-Bay SATCOM Antenna - Compliance Information Index
ActionCondition Questionnaire
If No, go to the next question.If Yes, go to Table 2.1. Does the airplane have more than or equal to
14,000 total flight cycles at the time of the original
issue date of this service bulletin?
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### Page 21

Group 1-2:
Table 1: Section 46 - 3-Bay SATCOM Antenna - Compliance Information Index
ActionCondition Questionnaire
If No, go to the next question.If Yes, go to Table 2.2. For the airplane, at the time of the original issue
date of this service bulletin, has the time been more
than or equal to 5,250 days since the date of is-
suance of the original certificate of airworthiness or
the original export certificate of airworthiness?
If No, go to the next question.If Yes, go to Table 3.3. Does the airplane have more than or equal to
12,000 total flight cycles and less than 14,000 total
flight cycles at the time of the original issue date of
this service bulletin?
If No, go to Table 4.(a)If Yes, go to Table 3.4. For the airplane, at the time of the original issue
date of this service bulletin, has the time been more
than or equal to 4,500 days and less than 5,250 days
since the date of issuance of the original certificate
of airworthiness or the original export certificate of
airworthiness?
(a) At the time of the original issue date of this service bulletin, the airplane has less than 12,000 total flight
cycles and has been less than 4,500 days since the date of issuance of the original certificate of airworthi-
ness or the original export certificate of airworthiness.
Group 1-2:
Table 2: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or
Equal to 14,000 Total Flight Cycles or 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 120 days after the original
issue date of this service bul-
letin.(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
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### Page 22

Group 1-2:
Table 2: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or
Equal to 14,000 Total Flight Cycles or 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601
to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
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### Page 23

Group 1-2:
Table 3: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified
in Table 2; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or
More than or Equal to 4,500 and Less than 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs First)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 750 flight
cycles or 375
days after the
original issue
date of this ser-
vice bulletin,
whichever oc-
curs first.(a)
Within 120 days
after reaching
one of the follow-
ing (whichever
occurs first):
– 14,000 total
flight cy-
cles.
– 5,250 days
from the
date of is-
suance of
the original
certificate
of airworthi-
ness or the
original ex-
port certifi-
cate of air-
worthiness
whichever
occurs first.
(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
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### Page 24

Group 1-2:
Table 3: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified
in Table 2; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or
More than or Equal to 4,500 and Less than 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs First)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601
to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
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### Page 25

Group 1-2:
Table 4: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than
12,000 Total Flight Cycles and 4,500 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 750 flight
cycles or 375
days after the
original issue
date of this ser-
vice bulletin,
whichever oc-
curs first.(a)
Before 12,000
total flight cycles
or within 4,500
days from the
date of issuance
of the original
certificate of air-
worthiness or
the original ex-
port certificate
of airworthiness,
whichever oc-
curs first.(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
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### Page 26

Group 1-2:
Table 4: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than
12,000 Total Flight Cycles and 4,500 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601
to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
Group 2:
Table 5: Section 44 - 3-Bay SATCOM Antenna - Compliance Information Index
ActionCondition Questionnaire
If No, go to the next question.If Yes, go to Table 6.1. Does the airplane have more than or equal to
14,000 total flight cycles at the time of the original
issue date of this service bulletin?
If No, go to the next question.If Yes, go to Table 6.2. For the airplane, at the time of the original issue
date of this service bulletin, has the time been more
than or equal to 5,250 days since the date of is-
suance of the original certificate of airworthiness or
the original export certificate of airworthiness?
If No, go to the next question.If Yes, go to Table 7.3. Does the airplane have more than or equal to
12,000 total flight cycles and less than 14,000 total
flight cycles at the time of the original issue date of
this service bulletin?
If No, go to Table 8.(a)If Yes, go to Table 7.4. For the airplane, at the time of the original issue
date of this service bulletin, has the time been more
than or equal to 4,500 days and less than 5,250 days
since the date of issuance of the original certificate
of airworthiness or the original export certificate of
airworthiness?
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### Page 27

Group 2:
Table 5: Section 44 - 3-Bay SATCOM Antenna - Compliance Information Index
ActionCondition Questionnaire
(a) At the time of the original issue date of this service bulletin, the airplane has less than 12,000 total flight
cycles and has been less than 4,500 days since the date of issuance of the original certificate of airworthi-
ness or the original export certificate of airworthiness.
Group 2:
Table 6: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or
Equal to 14,000 Total Flight Cycles or 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 120 days after the original
issue date of this service bul-
letin.(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
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### Page 28

Group 2:
Table 6: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than or
Equal to 14,000 Total Flight Cycles or 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1077
to STA 1098 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
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### Page 29

Group 2:
Table 7: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified
in Table 6; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or
More than or Equal to 4,500 and Less than 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs First)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 750 flight
cycles or 375
days after the
original issue
date of this ser-
vice bulletin,
whichever oc-
curs first.(a)
Within 120 days
after reaching
one of the follow-
ing (whichever
occurs first):
– 14,000 total
flight cy-
cles.
– 5,250 days
from the
date of is-
suance of
the original
certificate
of airworthi-
ness or the
original ex-
port certifi-
cate of air-
worthiness
whichever
occurs first.
(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Export Controlled ECCN: 9E991 - BOEING
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Original Issue: June 12, 2013
777-53A0068
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BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 30

Group 2:
Table 7: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified
in Table 6; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or
More than or Equal to 4,500 and Less than 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs First)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1077
to STA 1098 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
30 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 31

Group 2:
Table 8: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than
12,000 Total Flight Cycles and 4,500 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 750 flight
cycles or 375
days after the
original issue
date of this ser-
vice bulletin,
whichever oc-
curs first.(a)
Before 12,000
total flight cycles
or within 4,500
days from the
date of issuance
of the original
certificate of air-
worthiness or
the original ex-
port certificate
of airworthiness,
whichever oc-
curs first.(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
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BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 32

Group 2:
Table 8: Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than
12,000 Total Flight Cycles and 4,500 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1077
to STA 1098 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
Group 3-4:
Table 9: Section 46 - 2-Bay SATCOM Antenna - Compliance Information Index
ActionCondition Questionnaire
If No, go to the next question.If Yes, go to Table 10.1. Does the airplane have more than or equal to
14,000 total flight cycles at the time of the original
issue date of this service bulletin?
If No, go to the next question.If Yes, go to Table 10.2. For the airplane, at the time of the original issue
date of this service bulletin, has the time been more
than or equal to 5,250 days since the date of is-
suance of the original certificate of airworthiness or
the original export certificate of airworthiness?
If No, go to the next question.If Yes, go to Table 11.3. Does the airplane have more than or equal to
12,000 total flight cycles and less than 14,000 total
flight cycles at the time of the original issue date of
this service bulletin?
If No, go to Table 12.(a)If Yes, go to Table 11.4. For the airplane, at the time of the original issue
date of this service bulletin, has the time been more
than or equal to 4,500 days and less than 5,250 days
since the date of issuance of the original certificate
of airworthiness or the original export certificate of
airworthiness?
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
32 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 33

Group 3-4:
Table 9: Section 46 - 2-Bay SATCOM Antenna - Compliance Information Index
ActionCondition Questionnaire
(a) At the time of the original issue date of this service bulletin, the airplane has less than 12,000 total flight
cycles and has been less than 4,500 days since the date of issuance of the original certificate of airworthi-
ness or the original export certificate of airworthiness.
Group 3-4:
Table 10: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than
or Equal to 14,000 Total Flight Cycles or 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 120 days after the original
issue date of this service bul-
letin.(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
33 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 34

Group 3-4:
Table 10: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with More than
or Equal to 14,000 Total Flight Cycles or 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601
to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
34 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 35

Group 3-4:
Table 11: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified
in Table 10; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or
More than or Equal to 4,500 and Less than 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs First)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 750 flight
cycles or 375
days after the
original issue
date of this ser-
vice bulletin,
whichever oc-
curs first.(a)
Within 120 days
after reaching
one of the follow-
ing (whichever
occurs first):
– 14,000 total
flight cy-
cles.
– 5,250 days
from the
date of is-
suance of
the original
certificate
of airworthi-
ness or the
original ex-
port certifi-
cate of air-
worthiness
whichever
occurs first.
(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
35 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 36

Group 3-4:
Table 11: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Except for Airplanes Identified
in Table 10; Airplanes with More than or Equal to 12,000 and Less than 14,000 Total Flight Cycles; or
More than or Equal to 4,500 and Less than 5,250 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs First)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601
to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
36 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 37

Group 3-4:
Table 12: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than
12,000 Total Flight Cycles and 4,500 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.(a)
Within 750 flight
cycles or 375
days after the
original issue
date of this ser-
vice bulletin,
whichever oc-
curs first.(a)
Before 12,000
total flight cycles
or within 4,500
days from the
date of issuance
of the original
certificate of air-
worthiness or
the original ex-
port certificate
of airworthiness,
whichever oc-
curs first.(a)
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.(a)
All airplanes.
(b)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
37 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 38

Group 3-4:
Table 12: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes with Less than
12,000 Total Flight Cycles and 4,500 Days
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) Previous accomplishment of internal or external detailed inspection of the fuselage skin from STA 1601
to STA 1622 and from S-1L to S-1R meets the requirements of the initial internal and external detailed
and surface HFEC inspection of the visible fuselage skin in accordance with Paragraph 3.B., Work In-
structions, Part 2.
Refer to 777 MPD Section 2, 53-598-00, Boeing Multi-Operator Message (MOM-MOM-12-0466-01B),
and 777 FTD 53-12001 for additional information related to this service bulletin issue.
(b) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
Group 5, Configuration 3-4:
Table 13: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes Not Yet Delivered
at the Original Issue Date of this Service Bulletin
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
1,500 flight cycles
or 750 days,
whichever occurs
first.
Before 12,000 total flight cycles or
within 4,500 days from the date of
issuance of the original certificate
of airworthiness or the original ex-
port certificate of airworthiness,
whichever occurs first.
Do internal and external
detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
All airplanes.
(a)Before further flight.Do a 777 SRM repair in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2, or contact
Boeing for repair instruc-
tions and do the repair.
Any corrosion found
or
Any crack found.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
38 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 39

Group 5, Configuration 3-4:
Table 13: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection - Airplanes Not Yet Delivered
at the Original Issue Date of this Service Bulletin
Repeat Interval
(Not to Exceed)
Compliance TimeActionCondition
-Before further flight.Contact Boeing for repair
instructions and do the
repair.
Any indication found that
shows a contact of the fas-
tener attaching the SAT-
COM lug adapter plate to
the bonding jumper given
in Paragraph 3.B., Work
Instructions, Part 2.
and
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler, if installed, in
accordance with Para-
graph 3.B., Work Instruc-
tions, Part 2.
Any blend repair accom-
plished within Allowable
Damage 1 limits in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
1,500 flight cycles
or 750 days,
whichever occurs
first.
Within 1,500 flight cycles or 750
days after the repair, whichever
occurs first.
Repeat internal and exter-
nal detailed and surface
HFEC inspections of the
visible fuselage skin and
doubler in accordance
with Paragraph 3.B.,
Work Instructions, Part 2.
Any fuselage skin repair
doubler installed in accor-
dance with 777 SRM 53-
00-01 given in Paragraph
3.B., Work Instructions,
Part 2.
(a) For airplanes on which any blend repair is accomplished within allowable damage 1 limits in accordance
with 777 SRM 53-00-01 and for airplanes on which any fuselage skin repair doubler is installed in accor-
dance 777 SRM 53-00-01 given in Paragraph 3.B., Work Instructions, Part 2, refer to the applicable rows
in this table for additional inspections.
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 tables below show an estimate of the task hours necessary to do this inspection for each airplane.
This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator
task hour data if necessary. The estimate does not include lost time. These are some examples of lost
time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Group 5, Configuration 1-2, 5:
None. No action is necessary in accordance with this service bulletin.
Group 1:
Table 1: Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection
Elapsed HoursTask HoursNumber of PersonsTask
2.002.001Open Access - Inter-
nal
2.104.202Open Access - Exter-
nal
0.200.201FIGURE 1
3.003.001FIGURE 2
2.002.001FIGURE 3
2.002.001Close Access - Inter-
nal
2.104.202Close Access - Exter-
nal
13.4017.60TOTAL FOR EACH AIRPLANE
Group 2:
Table 2: Sections 44 and 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection
Elapsed HoursTask HoursNumber of PersonsTask
Section 44 - 3-Bay SATCOM Antenna
2.002.001Open Access - Inter-
nal
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Group 2:
Table 2: Sections 44 and 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection
Elapsed HoursTask HoursNumber of PersonsTask
2.104.202Open Access - Exter-
nal
0.200.201FIGURE 4
3.003.001FIGURE 5
2.002.001FIGURE 6
2.002.001Close Access - Inter-
nal
2.104.202Close Access - Exter-
nal
Section 46 - 3-Bay SATCOM Antenna
2.002.001Open Access - Inter-
nal
2.104.202Open Access - Exter-
nal
0.200.201FIGURE 1
3.003.001FIGURE 2
2.002.001FIGURE 3
2.002.001Close Access - Inter-
nal
2.104.202Close Access - Exter-
nal
26.8035.20TOTAL FOR EACH AIRPLANE
Group 3-4; Group 5, Configuration 3-4:
Table 3: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection
Elapsed HoursTask HoursNumber of PersonsTask
2.002.001Open Access - Inter-
nal
2.104.202Open Access - Exter-
nal
0.200.201FIGURE 7
3.003.001FIGURE 8
2.002.001FIGURE 9
2.002.001Close Access - Inter-
nal
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Group 3-4; Group 5, Configuration 3-4:
Table 3: Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection
Elapsed HoursTask HoursNumber of PersonsTask
2.104.202Close Access - Exter-
nal
13.4017.60TOTAL 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-53-0418
c. Service Bulletin Index D624W001
d. Standard Overhaul Practices Manual (SOPM) 20-50-19
e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-10
f. 777 Aircraft Maintenance Manual (AMM) 23-15-08, 23-15-23, 25-80-00, 53-61-51
g. 777 Fleet Team Digest (FTD) 53-12001
h. 777 Maintenance Planning Data (MPD) Section 2, 53-598-00
i. 777 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01
j. 777-200 Structural Repair Manual (SRM) 51-10-02, 53-00-01
k. 777-300 Structural Repair Manual (SRM) 51-10-02, 53-00-01
l. 777F Structural Repair Manual (SRM) 51-10-02, 53-00-01
2. Data Supplied with this Service Bulletin:
None.
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3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
SUPPORT INSTL - SATCOM, HIGH GAIN TOP MOUNT144W0026
SUPPORT INSTL - SATCOM, HIGH GAIN TOP MOUNT146W0027
The table above lists applicable drawings used to prepare this service bulletin. The drawings are
not necessary to make the specified changes, and are not supplied with this service bulletin. The
drawings may not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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 June 25, 2012. 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 number(s) 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
None.
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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### Page 47

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
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. 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.
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.
8. 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.
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9. 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.
10. 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.
11. 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.
12. Shaded areas in Figures are to separate the non-critical and non-authoritative
information from the critical and authoritative information.
13. The satellite communication (SATCOM) antenna is also referred to as Top Mount
High Gain Antenna (TMHGA). For this service bulletin, "SATCOM antenna" is used
to refer to the antenna.
B. WORK INSTRUCTIONS
Group 5, Configuration 1-2, 5:
No action is necessary in accordance with this service bulletin. These airplanes either have a production
change to the bonding jumper installation for 3-bay SATCOM antenna or do not have any SATCOM
antennas installed.
Group 1-4; Group 5, Configuration 3-4:
Part 1 - Access
1. Group 1-2:
Section 46 - 3-Bay SATCOM Antenna - Internal Access:
a. Open the circuit breaker to the SATCOM antenna and remove interior furnishings. Refer to
777 AMM 23-15-08 as an accepted procedure.
b. Remove insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure.
2. Group 2:
Section 44 - 3-Bay SATCOM Antenna - Internal Access:
a. Open the circuit breaker to the SATCOM antenna and remove interior furnishings. Refer to
777 AMM 23-15-08 as an accepted procedure.
b. Remove insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure.
3. Group 3-4; Group 5, Configuration 3-4:
Section 46 - 2-Bay SATCOM Antenna - Internal Access:
a. Open the circuit breaker to the SATCOM antenna and remove interior furnishings. Refer to
777 AMM 23-15-08 as an accepted procedure.
b. Remove insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure.
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4. Group 1-2:
Section 46 - 3-Bay SATCOM Antenna - External Access:
a. Remove the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure.
b. Remove the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure. During
the removal of the adapter plate, locate and mark the location of the fastener common to the
adapter plate and bonding jumper on the fuselage skin or doubler, if installed, in accordance
with FIGURE 1.
5. Group 2:
Section 44 - 3-Bay SATCOM Antenna - External Access:
a. Remove the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure.
b. Remove the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure. During
the removal of the adapter plate, locate and mark the location of the fastener common to the
adapter plate and bonding jumper on the fuselage skin or doubler, if installed, in accordance
with FIGURE 4.
6. Group 3-4; Group 5, Configuration 3-4:
Section 46 - 2-Bay SATCOM Antenna - External Access:
a. Remove the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure.
b. Remove the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure. During
the removal of the adapter plate, locate and mark the location of the fastener common to the
adapter plate and bonding jumper on the fuselage skin or doubler, if installed, in accordance
with FIGURE 7.
Group 1-4; Group 5, Configuration 3-4:
Part 2 - Inspection
1. Group 1-2:
Section 46 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection:
Do internal detailed and surface high frequency eddy current (HFEC) inspections of the visible
fuselage skin in accordance with FIGURE 2. If a fuselage skin repair doubler is installed, do detailed
and surface HFEC inspections of the visible doubler in the specified inspection area in accordance
with the figure.
Do external detailed and surface HFEC inspections of the visible fuselage skin in accordance with
FIGURE 3. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections
of the visible doubler in the specified inspection area in accordance with the figure.
NOTE: Previous accomplishment of internal or external detailed inspection of the fuselage skin
from STA 1601 to STA 1622 and from S-1L to S-1R meets the intent of the initial internal
and external detailed and surface HFEC inspection of the visible fuselage skin.
a. If any corrosion is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300
SRM 53-00-01; or contact Boeing for repair instructions and do the repair. General corrosion
damage removal procedure and inspection is specified in 777-200 SRM 51-10-02 or 777-300
SRM 51-10-02.
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(1) If a blend repair was accomplished within Allowable Damage 1 limits in accordance with
777-200 SRM 53-00-01 or 777-300 SRM 53-00-01, repeat the internal and external
detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
(2) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for
repair instructions and do the repair to make sure that there is sufficient clearance between
the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to
the bonding jumper.
If a fuselage skin repair doubler was installed, repeat the internal and external detailed
and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
b. If any crack is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300 SRM
53-00-01; or contact Boeing for repair instructions and do the repair.
(1) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for
repair instructions and do the repair to make sure that there is sufficient clearance between
the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to
the bonding jumper.
(2) If a fuselage skin repair doubler was installed, repeat the internal and external detailed
and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
c. If any indication is found that shows a contact of the fastener attaching the SATCOM lug
adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair.
Indications of the fastener contact include imprint, gouge, rubbing, and scratch. After the
repair, repeat the internal and external detailed and surface HFEC inspections at the time
given in Paragraph 1.E., Compliance.
2. Group 2:
Section 44 - 3-Bay SATCOM Antenna - Fuselage Skin Inspection:
Do internal detailed and surface HFEC inspections of the visible fuselage skin in accordance with
FIGURE 5. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections
of the visible doubler in the specified inspection area in accordance with the figure.
Do external detailed and surface HFEC inspections of the visible fuselage skin in accordance with
FIGURE 6. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections
of the visible doubler in the specified inspection area in accordance with the figure.
NOTE: Previous accomplishment of internal or external detailed inspection of the fuselage skin
from STA 1077 to STA 1098 and from S-1L to S-1R meets the intent of the initial internal
and external detailed and surface HFEC inspection of the visible fuselage skin.
a. If any corrosion is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300
SRM 53-00-01; or contact Boeing for repair instructions and do the repair. General corrosion
damage removal procedure and inspection is specified in 777-200 SRM 51-10-02 or 777-300
SRM 51-10-02.
(1) If a blend repair was accomplished within Allowable Damage 1 limits in accordance with
777-200 SRM 53-00-01 or 777-300 SRM 53-00-01, repeat the internal and external
detailed and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
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(2) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for
repair instructions and do the repair to make sure that there is sufficient clearance between
the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to
the bonding jumper.
If a fuselage skin repair doubler was installed, repeat the internal and external detailed
and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
b. If any crack is found, do a repair in accordance with 777-200 SRM 53-00-01 or 777-300 SRM
53-00-01; or contact Boeing for repair instructions and do the repair.
(1) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for
repair instructions and do the repair to make sure that there is sufficient clearance between
the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to
the bonding jumper.
(2) If a fuselage skin repair doubler was installed, repeat the internal and external detailed
and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
c. If any indication is found that shows a contact of the fastener attaching the SATCOM lug
adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair.
Indications of the fastener contact include imprint, gouge, rubbing, and scratch. After the
repair, repeat the internal and external detailed and surface HFEC inspections at the time
given in Paragraph 1.E., Compliance.
3. Group 3-4; Group 5, Configuration 3-4:
Section 46 - 2-Bay SATCOM Antenna - Fuselage Skin Inspection:
Do internal detailed and surface HFEC inspections of the visible fuselage skin in accordance with
FIGURE 8. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections
of the visible doubler in the specified inspection area in accordance with the figure.
Do external detailed and surface HFEC inspections of the visible fuselage skin in accordance with
FIGURE 9. If a fuselage skin repair doubler is installed, do detailed and surface HFEC inspections
of the visible doubler in the specified inspection area in accordance with the figure.
NOTE: Previous accomplishment of internal or external detailed inspection of the fuselage skin
from STA 1601 to STA 1622 and from S-1L to S-1R meets the intent of the initial internal
and external detailed and surface HFEC inspection of the visible fuselage skin.
a. If any corrosion is found, do a repair in accordance with 777-200 SRM 53-00-01, 777-300
SRM 53-00-01, or 777F SRM 53-00-01; or contact Boeing for repair instructions and do the
repair. General corrosion damage removal procedure and inspection is specified in 777-200
SRM 51-10-02, 777-300 SRM 51-10-02, or 777F SRM 51-10-02.
(1) If a blend repair was accomplished within Allowable Damage 1 limits in accordance with
777-200 SRM 53-00-01, 777-300 SRM 53-00-01, or 777F SRM 53-00-01, repeat the
internal and external detailed and surface HFEC inspections at the time given in Paragraph
1.E., Compliance.
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(2) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for
repair instructions and do the repair to make sure that there is sufficient clearance between
the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to
the bonding jumper.
If a fuselage skin repair doubler was installed, repeat the internal and external detailed
and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
b. If any crack is found, do a repair in accordance with 777-200 SRM 53-00-01, 777-300 SRM
53-00-01, or 777F SRM 53-00-01; or contact Boeing for repair instructions and do the repair.
(1) If external repair doubler is necessary in accordance with 777 SRM, contact Boeing for
repair instructions and do the repair to make sure that there is sufficient clearance between
the fuselage skin or doubler, and fastener attaching the SATCOM lug adapter plate to
the bonding jumper.
(2) If a fuselage skin repair doubler was installed, repeat the internal and external detailed
and surface HFEC inspections at the time given in Paragraph 1.E., Compliance.
c. If any indication is found that shows a contact of the fastener attaching the SATCOM lug
adapter plate to the bonding jumper, contact Boeing for repair instructions and do the repair.
Indications of the fastener contact include imprint, gouge, rubbing, and scratch. After the
repair, repeat the internal and external detailed and surface HFEC inspections at the time
given in Paragraph 1.E., Compliance.
Group 1-4; Group 5, Configuration 3-4:
Part 3 - Restoration
1. Internal Restoration
a. Install insulation blankets. Refer to 777 AMM 25-80-00 as an accepted procedure.
b. Install interior furnishings. Refer to 777 AMM 23-15-08 as an accepted procedure.
2. External Restoration
a. Install the adapter plate. Refer to 777 AMM 53-61-51 as an accepted procedure for installing
the adapter plate. Refer to SWPM 20-20-10 as an accepted procedure for installing the bonding
jumper.
After the installation of the fastener attaching the adapter plate to the bonding jumper,
encapsulate the fastener, washer, nut, and periphery of the bonding jumper with BMS 5-95.
Refer to SOPM 20-50-19 as an accepted procedure. Make sure there is no contact between
the sealant of the cap sealed fastener and fuselage skin or doubler, if installed. Use of a
boroscope or feeler gauge is an acceptable method to ensure there is no contact.
3. Install the SATCOM antenna. Refer to 777 AMM 23-15-23 as an accepted procedure. Close the
circuit breaker to the SATCOM antenna. Refer to AMM 23-15-08 or 23-15-23 as an accepted
procedure.
4. Put the airplane back to a serviceable condition.
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### Page 53 (OCR)

BOEING SERVICE BULLETIN 777-53A0068
ALERT  ALERT
This Figure applies only to: Group 1-2.
STA
1601
STA
_1643
—1622  STA
160+  STA
STA
. 1580
S-2L
* S-1L
$ S-1R
S-2R
LEWD
2182210
FIGURE 1: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER
COMMON TO BONDING JUMPER AND ADAPTER PLATE
(SHEET 1 OF 2)
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### Page 54

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--FUSELAGE
SKIN/DOUBLER
Locate1
(a) Directly under the fastener common to the adapter plate and bonding jumper, locate and mark the location
of the fastener on the fuselage skin or doubler, if installed, within 0.25 inch using a felt tip marker. The
location of the mark will be used to identify the inspection area in FIGURE 3.
FIGURE 1: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - MARK AND LOCATE FASTENER
COMMON TO BONDING JUMPER AND ADAPTER PLATE
(SHEET 2 OF 2)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
54 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 55 (OCR)

BOEING SERVICE BULLETIN 777-53A0068
ALERT  ALERT
This Figure applies only to: Group 1-2.
STA
1601
- 1622  STA
STA
- 1601
S-2L
-S-1L A
I S-1R
S-2R
2182241
FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION
(SHEET 1 OF 3)
Original Issue: June 12, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  777-53A0068
Work - See page 1 for details.  55 of 76

### Page 56 (OCR)

BOEING SERVICE BULLETIN 777-53A0068
ALERT  ALERT
STA  STA  STA  STA  STA
1643  1622  1601  1580  1567.5
3- S-2R
- S-1R
S-1L
- S-2L
FWD
A-A
STA
3.0 MINIMUM  3.0 MINIMUM  1601
1.0
MINIMUM  •p 0  - S-1L
1.0
EDGE OF STRINGER
ADJACENT TO THE
FUSELAGE SKIN
4.0
MINIMUM  ' EDGE OF
SHEAR TIE
C
- 5.0 MINIMUM  - 3.0 -
SURFACE HFEC  FWD
INSPECTION  2182320
FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION
(SHEET 2 OF 3)
Original Issue: June 12, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  777-53A0068
Work - See page 1 for details.  56 of 76

### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--FUSELAGE
SKIN/DOUBLER
Inspect1
(b)--FUSELAGE
SKIN/DOUBLER
Inspect2
(a) Do a detailed inspection of the visible fuselage skin for cracks. Do the inspection in the area between
STA 1567.5 and STA 1643, and S-2L and S-2R.
If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified
inspection area.
(b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual
Part 6, 51-00-01.
If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the
specified inspection area.
FIGURE 2: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - INTERNAL INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
57 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

### Page 58 (OCR)

BOEING SERVICE BULLETIN 777-53A0068
ALERT  ALERT
This Figure applies only to: Group 1-2.
STA
1601
STA
_1643
STA
1622
—160T  STA
•
— 1580  STA
FEND  * S-1R  A SILY  S-2L
2182337
FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION
(SHEET 1 OF 3)
Original Issue: June 12, 2013
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  777-53A0068
Work - See page 1 for details.  58 of 76

### Page 59 (OCR)

BOEING SERVICE BULLETIN 777-53A0068
ALERT  ALERT
1- S-2L
•19  — S-1L
— S-1R
-— S-2R
STA  STA  STA  STA  STA
1643  1622  1601  FWD  1580  1567.5
A-A
MINIMUM -  . 1.5
MINIMUM
MINIMUM
1.5
MINIMUM
- S-1L
MARKED LOCATION OF
FASTENER ON THE
FWD  FUSELAGE
INSPECTION  SURFACE HFEC  2182365
FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION
(SHEET 2 OF 3)
Original Issue: June 12, 2013
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  777-53A0068
Work - See page 1 for details.  59 of 76

### Page 60

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--FUSELAGE
SKIN/DOUBLER
Inspect1
(b)--FUSELAGE
SKIN/DOUBLER
Inspect2
(c)--FUSELAGE
SKIN/DOUBLER
Inspect3
(a) Do a detailed inspection of the visible fuselage skin for corrosion and cracks, and for any indication that
shows a contact of the fastener attaching the SATCOM lug adapter plate to the bonding jumper. Do the
inspection in the area between STA 1567.5 and STA 1643, and S-2L and S-2R. Indications of the fastener
contact include imprint, gouge, rubbing, and scratch.
If a fuselage skin repair doubler is installed, do a detailed inspection of the visible doubler in the specified
inspection area.
(b) Do a surface HFEC inspection of the visible fuselage skin for cracks in accordance with 777 NDT Manual
Part 6, 51-00-01. The marked location on the fuselage was accomplished in FIGURE 1.
If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the visible doubler in the
specified inspection area.
(c) Do a surface HFEC inspection of the fuselage skin around the edge of the bonding jumper for cracks in
accordance with 777 NDT Manual Part 6, 51-00-01.
If a fuselage skin repair doubler is installed, do a surface HFEC inspection of the doubler in the specified
inspection area.
FIGURE 3: SECTION 46 - 3-BAY SATCOM ANTENNA - FUSELAGE SKIN - EXTERNAL INSPECTION
(SHEET 3 OF 3)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 12, 2013
777-53A0068
60 of 76
BOEING SERVICE BULLETIN 777-53A0068
ALERTALERT

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