# Boeing Alert Service Bulletin 777-57A0050: Revision 4

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- Document: [Boeing Alert Service Bulletin 777-57A0050](https://openairdocs.org/service-documents/boeing/777-57a0050.md)
- Title as filed: SB-777-57A0050-04 BOEING
- Pages: 514
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- Page: https://openairdocs.org/service-documents/boeing/777-57a0050/file/9fdffc661b29

## Text

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### Page 1

Commercial 
Airplanes
777
Service Bulletin
Number: 777-57A0050
Original Issue: January 26, 2006
Revision 4: September 28, 2015
ATA System: 5710
SUBJECT: WINGS - Center and Outer Wings - Wire Bundle Teflon sleeve Installation and Fastener
Cap Sealing for Fuel Tank Wiring Hot Short Protection
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 © 2006 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
Original Issue: January 26, 2006
777-57A0050Revision 4: September 28, 2015
1 of 514
5.0

### Page 2

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Table of Contents
Revision Transmittal Sheet ............................................ 9
S u m m a r y  ..................................................... 1 3
1. PLANNING INFORMATION ........................................ 1 9
A . E f f e c t i v i t y  ............................................... 1 9
1. Airplanes ............................................ 1 9
2 . S p a r e s  A f f e c t e d  ........................................ 3 8
B. Concurrent Requirements ...................................... 3 8
C. Reason ................................................ 3 8
D. Description .............................................. 3 9
E. Compliance .............................................. 4 6
F . A p p r o v a l  ............................................... 4 7
G. Manpower .............................................. 4 7
H. Weight and Balance Changes .................................... 6 2
I. Electrical Load Data ......................................... 6 3
J . R e f e r e n c e s  .............................................. 6 3
1. Existing Data: ......................................... 6 3
2. Data Supplied with this Service Bulletin: ........................... 6 3
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 6 3
K. Publications Affected ........................................ 6 3
L. Interchangeability and Intermixability of Parts ........................... 6 4
M. Software Accomplishment Summary ................................ 6 4
2. MATERIAL INFORMATION ........................................ 6 5
A. Material - Price and Availability ................................... 6 5
B. Industry Support Information .................................... 6 5
C. Parts Necessary for Each Airplane ................................. 6 5
1 . K i t s / P a r t s :  ........................................... 6 5
2. Parts and Materials Supplied by the Operator: ........................ 6 6
3. Parts Modified and Reidentified: ............................... 6 9
4. Parts Removed and Not Replaced: .............................. 6 9
D. Parts Necessary to Change Spares ................................. 6 9
E. Special Tooling - Price and Availability ............................... 6 9
F. Special Tooling Necessary to do this Service Bulletin ....................... 6 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 7 1
A. GENERAL INFORMATION ..................................... 7 1
B. WORK INSTRUCTIONS ....................................... 7 2
FIGURE 1: SLEEVING INSTALLATION FOR 1 INCH OR SMALLER DIAMETER WIRE BUNDLE . . 95
FIGURE 2: SLEEVING INSTALLATION FOR LARGER THAN 1 INCH DIAMETER WIRE BUNDLE . 98
FIGURE 3: WING REAR SPAR ACCESS PANEL REMOVAL/INSTALLATION [Group 1-7, 9-43] . . 101
FIGURE 4: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 1-2, 4] . 104
FIGURE 5: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 3] .... 1 1 0
FIGURE 6: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 1-2, 4] . 116
FIGURE 7: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 3] . . . 124
FIGURE 8: LEADING EDGE FIXED PANEL REMOVAL/INSTALLATION [Group 1-4, 32-34, 36] . . . 132
FIGURE 9: LEFT WING INBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 1-4]
................................................. 1 3 7
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### Page 4

FIGURE 10: LEFT WING OUTBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group
1 - 2 ,  4 ]  ............................................. 1 4 4
FIGURE 11: LEFT WING OUTBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group
3 ]  ................................................ 1 4 5
FIGURE 12: RIGHT WING INBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group
1 - 4 ]  ............................................... 1 4 7
FIGURE 13: RIGHT WING OUTBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group
1 - 2 ,  4 ]  ............................................. 1 5 3
FIGURE 14: RIGHT WING OUTBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group
3 ]  ................................................ 1 5 5
FIGURE 15: WING-TO-BODY FAIRING / ECS BAY ACCESS PANEL REMOVAL/INSTALLATION [Group
1 - 4 ,  8 - 1 2 ,  1 7 ,  2 0 ,  2 2 ,  2 5 ,  3 1 ,  3 4 ,  3 9 ,  4 2 - 4 3 ]  ......................... 1 5 7
FIGURE 16: LEFT ECS BAY WIRE BUNDLE SLEEVING INSTALLATION [Group 1-4] ........ 1 5 9
FIGURE 17: RIGHT ECS BAY WIRE BUNDLE SLEEVING INSTALLATION [Group 1-4] ........ 1 6 3
FIGURE 18: LEFT FORWARD WING -TO-BODY FAIRING WIRE BUNDLE SLEEVING INSTALLATION
[Group 1-4] .......................................... 1 6 7
FIGURE 19: RIGHT FORWARD WING-TO-BODY FAIRING WIRE BUNDLE SLEEVING INSTALLATION
[Group 1-4] .......................................... 1 6 9
FIGURE 20: STATION 998 END WALL REMOVAL/INSTALLATION .................. 1 7 2
FIGURE 21: FRONT SPAR BULKHEAD WIRE BUNDLE SLEEVING INSTALLATION [Group 2, Configuration
1 ,  3 - 5 ]  ............................................. 1 7 3
FIGURE 22: FUEL TANK FASTENER CAP SEAL APPLICATION [Group 1-4] ............. 1 7 7
FIGURE 23: LEFT CENTER FUEL CHEEK TANK FASTENER CAP SEALING [Group 1-2, Configuration 1;
Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration 1-2] .... 1 7 9
FIGURE 24: RIGHT CENTER FUEL CHEEK TANK FASTENER CAP SEALING [Group 1-2, Configuration
1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration 1-2] . . 183
FIGURE 25: BODY CENTER FUEL TANK FASTENER CAP SEALING [Group 2, Configuration 1-2; Group
3, Configuration 1-2; Group 4, Configuration 1-2] ...................... 1 8 7
FIGURE 26: LEFT MAIN FUEL TANK REAR SPAR FASTENER CAP SEALING [Group 1-2, Configuration
1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration 1-2] . . 194
FIGURE 27: LEFT MAIN FUEL TANK FRONT SPAR FASTENER CAP SEALING [Group 1-2, Configuration
1; Group 2, Configuration 2; Group 4, Configuration 1-2] .................. 1 9 9
FIGURE 28: LEFT MAIN FUEL TANK FRONT SPAR FASTENER CAP SEALING [Group 3, Configuration
1 - 2 ]  ............................................... 2 1 3
FIGURE 29: RIGHT MAIN FUEL TANK REAR SPAR FASTENER CAP SEALING [Group 1-2, Configuration
1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration 1-2] . . 227
FIGURE 30: RIGHT MAIN FUEL TANK FRONT SPAR FASTENER CAP SEALING [Group 1-2, Configuration
1; Group 2, Configuration 2; Group 4, Configuration 1-2] .................. 2 3 2
FIGURE 31: RIGHT MAIN FUEL TANK FRONT SPAR FASTENER CAP SEALING [Group 3, Configuration
1 - 2 ]  ............................................... 2 4 6
FIGURE 32: FRONT SPAR BULKHEAD WIRE BUNDLE SLEEVING INSTALLATION [Group 2, Configuration
2 - 5 ]  ............................................... 2 6 0
FIGURE 33: FRONT SPAR BULKHEAD WIRE BUNDLE SLEEVING INSTALLATION [Group 3, Configuration
1, 3-5; Group 4, Configuration 1, 3-5] ............................ 2 6 4
FIGURE 34: FRONT SPAR BULKHEAD WIRE BUNDLE SLEEVING INSTALLATION [Group 3, Configuration
2-5; Group 4, Configuration 2-5] ............................... 2 6 8
FIGURE 35: LEFT ECS BAY WIRE BUNDLE SLEEVING INSPECTION [Group 8-12, 17, 20, 31, 34, 39,
42-43, Configuration 1] .................................... 2 7 2
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### Page 5

FIGURE 36: RIGHT ECS BAY WIRE BUNDLE SLEEVING INSPECTION [Group 8-12, 17, 20, 22, 25, 42-43,
Configuration 1] ........................................ 2 7 6
FIGURE 37: LEFT ECS BAY WIRE BUNDLE SLEEVING INSTALLATION [Group 8-12, 17, 20, 31, 34, 39,
42-43, Configuration 1] .................................... 2 8 0
FIGURE 38: RIGHT ECS BAY WIRE BUNDLE SLEEVING INSTALLATION [Group 8-12, 17, 20, 22, 25,
42-43, Configuration 1] .................................... 2 8 4
FIGURE 39: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 9-10, Configuration
1 ]  ................................................ 2 8 8
FIGURE 40: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 17, Configuration
1 ]  ................................................ 2 9 1
FIGURE 41: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 11, 42, Configuration
1 ]  ................................................ 2 9 5
FIGURE 42: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 15, 18, 22, 26,
31-32, 34, 37, 39, 41, Configuration 1] ............................ 2 9 9
FIGURE 43: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 13, 24, Configuration
1 ]  ................................................ 3 0 3
FIGURE 44: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 16, 19, 21, 25, 27,
30, 33, 36, 38, Configuration 1] ................................ 3 0 7
FIGURE 45: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 14, Configuration
1 ]  ................................................ 3 1 1
FIGURE 46: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 6, Configuration
1 ]  ................................................ 3 1 6
FIGURE 47: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 12, 23, 43,
Configuration 1] ........................................ 3 1 9
FIGURE 48: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 35, Configuration
1 ]  ................................................ 3 2 4
FIGURE 49: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 7, 29, Configuration
1 ]  ................................................ 3 2 7
FIGURE 50: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 9-11, 42,
Configuration 1] ........................................ 3 3 1
FIGURE 51: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 12, 20, 23, 25,
27, 43, Configuration 1] .................................... 3 3 5
FIGURE 52: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 40, Configuration
1 ]  ................................................ 3 3 9
FIGURE 53: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 36, 38,
Configuration 1] ........................................ 3 4 3
FIGURE 54: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 35, Configuration
1 ]  ................................................ 3 4 8
FIGURE 55: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 34, 37, 39, 41,
Configuration 1] ........................................ 3 5 3
FIGURE 56: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 14, 16, 24, 28-29,
Configuration 1] ........................................ 3 5 8
FIGURE 57: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 5, 15, 18, 21-22,
26, 30-33, Configuration 1] .................................. 3 6 2
FIGURE 58: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 13, Configuration
1 ]  ................................................ 3 6 6
FIGURE 59: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 9-10, Configuration
1 ]  ................................................ 3 6 9
FIGURE 60: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 17, Configuration
1 ]  ................................................ 3 7 2
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### Page 6

FIGURE 61: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 11, 42,
Configuration 1] ........................................ 3 7 6
FIGURE 62: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 15, 18, 22, 26,
31-32, 34, 37, 39, 41, Configuration 1] ............................ 3 8 0
FIGURE 63: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 13, 24,
Configuration 1] ........................................ 3 8 4
FIGURE 64: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 16, 19, 21, 25,
27, 30, 33, 36, 38, Configuration 1] ............................. 3 8 8
FIGURE 65: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 14, Configuration
1 ]  ................................................ 3 9 2
FIGURE 66: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 6, Configuration
1 ]  ................................................ 3 9 7
FIGURE 67: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 12, 23, 43,
Configuration 1] ........................................ 4 0 0
FIGURE 68: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 35, Configuration
1 ]  ................................................ 4 0 5
FIGURE 69: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 7, 29,
Configuration 1] ........................................ 4 0 8
FIGURE 70: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 9-11, 42,
Configuration 1] ........................................ 4 1 2
FIGURE 71: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 12, 20, 23, 25,
27, 43, Configuration 1] .................................... 4 1 6
FIGURE 72: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 40, Configuration
1 ]  ................................................ 4 2 0
FIGURE 73: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 36, 38,
Configuration 1] ........................................ 4 2 4
FIGURE 74: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 35, Configuration
1 ]  ................................................ 4 2 9
FIGURE 75: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 34, 37, 39, 41,
Configuration 1] ........................................ 4 3 4
FIGURE 76: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 14, 16, 24,
28-29, Configuration 1] .................................... 4 3 9
FIGURE 77: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 5, 15, 18, 21-22,
26, 30-33, Configuration 1] .................................. 4 4 3
FIGURE 78: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 13, Configuration
1 ]  ................................................ 4 4 7
FIGURE 79: RIGHT WING INBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 32-34,
36, Configuration 1] ...................................... 4 5 0
FIGURE 80: RIGHT WING INBOARD FRONT SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group
32-34, 36, Configuration 1] .................................. 4 5 2
FIGURE 81: FRONT SPAR BULKHEAD WIRE BUNDLE SLEEVING INSPECTION [Group 12, 18, 20-21,
23, 25, 27, 30, 33, 36, 38, 40, 43, Configuration 1; Group 44-45] ............. 4 5 4
FIGURE 82: FRONT SPAR BULKHEAD WIRE BUNDLE SLEEVING INSTALLATION [Group 12, 18, 20-21,
23, 25, 27, 30, 33, 36, 38, 40, 43, Configuration 1; Group 44-45] ............. 4 5 7
FIGURE 83: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 1, Configuration
2-4; Group 2, Configuration 3-5; Group 4, Configuration 3-5] ................ 4 6 0
FIGURE 84: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSPECTION [Group 3, Configuration
3 - 5 ]  ............................................... 4 6 4
FIGURE 85: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 1, Configuration
2-4; Group 2, Configuration 3-5; Group 4, Configuration 3-5] ................ 4 6 7
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### Page 7

FIGURE 86: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 3, Configuration
3 - 5 ]  ............................................... 4 7 1
FIGURE 87: RIGHT WING REAR SPAR WIRE BUNDLE CLAMP INSPECTION [Group 1, Configuration 2-4;
Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration 3-5] . . . 474
FIGURE 88: RIGHT WING REAR SPAR WIRE BUNDLE CLAMP REPLACEMENT [Group 1, Configuration
2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration 3-5] . 477
FIGURE 89: RIGHT MAIN FUEL TANK REAR SPAR FASTENER CAP SEAL INSPECTION [Group 1,
Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration
3 - 5 ]  ............................................... 4 8 0
FIGURE 90: RIGHT MAIN FUEL TANK REAR SPAR FASTENER CAP SEALING [Group 1, Configuration
2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration 3-5] . 482
FIGURE 91: WIRE BUNDLE SLEEVING INSTALLATION FOR LARGER THAN 1 INCH DIAMETER WIRE
BUNDLE - INSPECTION [Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3,
Configuration 3-5; Group 4, Configuration 3-5] ....................... 4 8 4
FIGURE 92: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 1, Configuration
2; Group 2, 4, Configuration 3] ................................ 4 8 6
FIGURE 93: RIGHT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 1, Configuration
2; Group 2, 4, Configuration 3] ................................ 4 8 9
FIGURE 94: RIGHT MAIN FUEL TANK REAR SPAR FASTENER CAP SEAL INSPECTION [Group 1,
Configuration 2; Group 2-4, Configuration 3] ........................ 4 9 2
FIGURE 95: RIGHT MAIN FUEL TANK REAR SPAR FASTENER CAP SEALING [Group 1, Configuration
2; Group 2-4, Configuration 3] ................................ 4 9 4
FIGURE 96: LEFT MAIN FUEL TANK REAR SPAR FASTENER CAP SEAL INSPECTION [Group 1,
Configuration 2-3; Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4, Configuration
3 - 4 ]  ............................................... 4 9 6
FIGURE 97: LEFT MAIN FUEL TANK REAR SPAR FASTENER CAP SEALING [Group 1, Configuration 2-3;
Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4, Configuration 3-4] . . . 499
FIGURE 98: RIGHT MAIN FUEL TANK REAR SPAR FASTENER CAP SEAL INSPECTION [Group 1,
Configuration 2-3; Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4, Configuration
3 - 4 ]  ............................................... 5 0 2
FIGURE 99: RIGHT MAIN FUEL TANK REAR SPAR FASTENER CAP SEALING [Group 1, Configuration
2-3; Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4, Configuration 3-4] . 505
FIGURE 100: LEFT WING REAR SPAR WIRE BUNDLE SLEEVING INSTALLATION [Group 1, Configuration
2-5; Group 2, Configuration 3-6; Group 3, Configuration 3-6; Group 4, Configuration 3-6; Group
5-43, Configuration 2] ..................................... 5 0 8
APPENDIX A: SADDLE CLAMP TA0910070( ) PART NUMBER AND DIMENSION DATA ........ 5 1 1
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### Page 9

Commercial 
Airplanes
777
Service Bulletin
Revision Transmittal SheetNumber: 777-57A0050Original Issue: January 26, 2006
Revision 4: September 28, 2015
ATA System: 5710
SUBJECT: WINGS - Center and Outer Wings - Wire Bundle Teflon sleeve Installation and Fastener
Cap Sealing for Fuel Tank Wiring Hot Short Protection
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2011-26-03 and AD 2010-24-12 are related
to this service bulletin.
NOTE: AD 2010-24-12 has been superseded by AD 2011-26-03.
Airplanes WF022-WF023, WF036-WF041, WF065-WF066, WF115-WF116, WF132-WF133, WF138-WF139,
WF156-WF159, WF166-WF170 were added to a new Group 44 of this service bulletin effectivity. Airplanes
WC587, WC593-WC595 were added to a new Group 45 of this service bulletin effectivity.
Effects of this Revision on airplanes on which Original Issue, Revision 1 thru Revision 3 was previously done:
ActionConditionGroup
Do Work Packages 12 thru 14,
16 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Original Issue.
Group 1, Configuration 2
Do Work Packages 12 thru 21.Airplanes that have accomplished Boeing SB
777-57A0050 Original Issue.
Group 2, 4, Configuration 3
Do Work Packages 12 thru 16,
18 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Original Issue.
Group 3, Configuration 3
Do Work Packages 12 thru 14,
16, 19 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 1.
Group 1, Configuration 3
Do Work Packages 12 thru 16,
19 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 1.
Group 2-4, Configuration 4
Do Work Packages 12 thru 14,
16, 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 2.
Group 1, Configuration 4
Do Work Packages 12 thru 16,
21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 2.
Group 2-4, Configuration 5
Do Work Package 21.Airplanes that have accomplished Boeing SB
777-57A0050 Revision 3.
Group 1, Configuration 5;
Group 2-4, Configuration 6;
Group 5-43, Configuration 2
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### Page 10

REASON FOR REVISION
This revision is sent to add some wire bundle W8173 clamp locations in the left wing rear spar that need Teflon
sleeve installation. Also, some discrepancies in the compliance data, and in the Accomplishment Instructions
and Figure group applicability data are corrected. Airplanes WF022-WF023, WF036-WF041, WF065-WF066,
WF115-WF116, WF132-WF133, WF138-WF139, WF156-WF159, WF166-WF170 are added to a new Group
44, and airplanes WC587, WC593-WC595 are added to a new Group 45 of this service bulletin effectivity. These
airplanes need to do a detailed inspection of the selected wire bundle clamps in the front spar bulkhead, to make
sure that Teflon sleeve is installed.
These sections were changed:
1. In Summary, Planning Information, Material Information, Accomplishment Instructions and all applicable
figures, changed the applicability data to add the new group and group configurations.
2. In Summary, Action, and Paragraph 1.D., Description, added Work Packages 17 thru 21.
3. In Summary, Compliance and Paragraph 1.E., Compliance, changed the FAA and Boeing compliance
data.
4. In Summary, Background, Summary Evaluation Table, changed the Kits/Parts required data.
5. In Paragraph 1.A., Effectivity, added new Groups 44 and 45.
6. In Paragraph 1.G., Manpower, added manpower data for Work Packages 17 thru 21.
7. In Paragraph 1.H., Weight and Balance Changes, Groups 1 thru 4, changed the weight and balance
data.
8. In Paragraph 1.J.1., Existing Data, added an FAA AD reference.
9. In Paragraph 2.C., Parts Necessary for Each Airplane, top kit table, added a footnote (b).
10. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator:
a. Added a footnote (j).
b. Added new Parts and Materials Supplied by the Operator tables.
11. In Paragraph 3.B., Work Instructions:
a. Work Package 4, steps 3.b and 5.a., added more floor panel data.
b. Work Package 8 and Work Package 12, added some notes.
c. Work Package 10, added applicability to Groups 44 and 45.
d. Work Package 12, steps 14 and 15, Work Package 13, steps 5 and 6, Work Package 14, step 4,
and Work Package 15, steps 4 and 5, changed the text.
e. Added Work Packages 17 thru 21.
12. Figures 4 and 5:
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### Page 11

a. Sheet 2, added the selected clamp locations for wire bundle W8173.
b. Step table, step 1, changed the quantity data.
c. Step table, added a footnote (a).
13. Figures 6 and 7:
a. Sheet 5, added a new circle note.
b. Added a new sheet 7.
c. Step table, added a footnote (b).
14. Figures 21, 32, 33, and 34, changed the applicability.
15. Figures 60, 61, 67, 68, 85 and 86, added a footnote (b).
16. Figures 50 and 70, added Group 9 applicability.
17. Figure 62, added Group 32 applicability.
18. Added new Figures 92 thru 100.
19. Added Appendix A: Saddle Clamp TA0910070( ) Part Number and Dimension Data.
The data given in Alternative Method of Compliance Notice 777-57A0050 AMOC 01 is included in this revision.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity and format changes,
to show the location of all content changes.
Pages with no vertical lines have no changes.
REVISION HISTORY
January 26, 2006Original Issue:
August 02, 2007Revision 1:
May 14, 2009Revision 2:
February 18, 2014Revision 3:
September 28, 2015Revision 4:
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### Page 13

Commercial 
Airplanes
777
Service Bulletin
SummaryNumber: 777-57A0050Original Issue: January 26, 2006
Revision 4: September 28, 2015
ATA System: 5710
SUBJECT: WINGS - Center and Outer Wings - Wire Bundle Teflon sleeve Installation and Fastener
Cap Sealing for Fuel Tank Wiring Hot Short Protection
CONCURRENT REQUIREMENTS
None.
BACKGROUND
This service bulletin will help to prevent possible sources of ignition within the fuel tanks caused by wiring shorts
at the clamp locations on the wire bundles that are routed on the fuel tank boundary structure. An ignition source
within the fuel tanks could result in a fire or an explosion.
This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank
System Fault Tolerance Evaluation Requirements". This service bulletin addresses the concerns of electrical
arcing that can be caused by the electrical energy present in the wire bundles within the fuel tank boundary
structure. Seven operators have reported pinched insulation or wiring damage under the clamp. In some cases,
bared wires were found. This condition can cause an electrical arcing on the fuel tank boundary structure or the
voltage can find a path to permanent fasteners that penetrate through the fuel tank and creates an electrical
arcing inside the fuel tank. This service bulletin provides instructions to install Teflon sleeve under the wire
bundle clamps and cap seal the penetrating fasteners that were determined to have a capability of creating
electrical arcing during a wiring short event.
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 ChangesYesWeight 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/Parts.YesKits/Parts Required
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### Page 14

ReferenceAffectedPlanning Data
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
ACTION (PRR 61998-4)
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration
1-2:
Work Package 1: Install Teflon sleeve under the selected clamps on the wire bundles in the wing rear spars.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration
1-2:
Work Package 2: Install Teflon sleeve under the selected clamps on the wire bundles in the wing inboard and
outboard front spars.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration
1-2:
Work Package 3: Install Teflon sleeve under the selected clamps on the wire bundles in the wing-to-body fairings
and left/right Environmental Control System (ECS) bays.
Group 2, Configuration 1-2; Group 3, Configuration 1-2; Group 4, Configuration 1-2:
Work Package 4: Install Teflon sleeve under the selected clamps on the wire bundles in the front spar bulkhead.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration
1-2:
Work Package 5: Cap seal the selected fasteners in the center wing fuel tanks.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration
1-2:
Work Package 6: Cap seal the selected fasteners in the left main and surge fuel tank.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4, Configuration
1-2:
Work Package 7: Cap seal the selected fasteners in the right main and surge fuel tank.
Group 5-7, 9-43, Configuration 1:
Work Package 8: Do a detailed inspection of the selected wire bundle clamps in the left and right rear wing
spars. If the wire bundle clamps have the Teflon sleeve installed then no more work is necessary. If any of the
clamps do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle clamps.
Group 32-34, 36, Configuration 1:
Work Package 9: Do a detailed inspection of the selected wire bundle clamps in the right wing inboard front
spar. If the wire bundle clamps have the Teflon sleeve installed then no more work is necessary. If any of the
clamps do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle clamps.
Group 12, 18, 20-21, 23, 25, 27, 30, 33, 36, 38, 40, 43, Configuration 1; Group 44-45:
Work Package 10: Do a detailed inspection of the selected wire bundle clamps in the front spar bulkhead. If the
wire bundle clamps have the Teflon sleeve installed then no more work is necessary. If any of the clamps do
not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle clamps.
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### Page 15

Group 8-12, 17, 20, 22, 25, 31, 34, 39, 42-43, Configuration 1:
Work Package 11: Do a detailed inspection of the selected wire bundle clamps in the left and right ECS bay. If
the wire bundle clamps have the Teflon sleeve installed then no more work is necessary. If any of the clamps
do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle clamps.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration
3-5:
Work Package 12: More work. Do a detailed inspection of the selected wire bundle clamps in the left rear wing
spar. If the wire bundle clamps have the Teflon sleeve installed then no more work is necessary. If any of the
wire bundle clamps do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle clamps.
Do a detailed inspection of a wire bundle clamp in the right rear wing spar at the approximate location IRSS
450. If the clamp type is not a saddle clamp, remove the existing clamp and replace it with a saddle clamp. Do
a detailed inspection of the applicable Teflon sleeve installed under the wire bundle clamps, on wire bundles
with a diameter more than 1 inch, in the left and right wing rear spars for correct installation. If all the Teflon
sleeve have been installed correctly, then no more work is necessary. If any of the Teflon sleeve have not been
installed correctly, then replace the Teflon sleeve.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration
3-5:
Work Package 13: More work. Do a detailed inspection of the applicable Teflon sleeve installed under the wire
bundle clamps, on wire bundles with a diameter more than 1 inch, in the left and right wing inboard and outboard
front spars for correct installation. If all the Teflon sleeve have been installed correctly, then no more work is
necessary. If any of the Teflon sleeve have not been installed correctly, then replace the Teflon sleeve.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration
3-5:
Work Package 14: More work. Do a detailed inspection of the selected Teflon sleeve installed under the wire
bundle clamps, on wire bundles with a diameter more than 1 inch, in the left and right wing-to-body fairings and
the left and right ECS Bays for correct installation. If all the Teflon sleeve have been installed correctly, then no
more work is necessary. If any of the Teflon sleeve have not been installed correctly, then replace the Teflon
sleeve.
Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration 3-5:
Work Package 15: More work. Do a detailed inspection of the applicable Teflon sleeve installed under the wire
bundle clamps, on wire bundles with a diameter more than 1 inch, in the front spar bulkhead for correct installation.
If all the Teflon sleeve have been installed correctly, then no more work is necessary. If any of the Teflon sleeve
have not been installed correctly, then replace the Teflon sleeve.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration
3-5:
Work Package 16: More work. Do a detailed inspection of the selected fasteners in the right main fuel tank rear
spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners are not cap
sealed, cap seal the fasteners.
Group 1, Configuration 2; Group 2, 4, Configuration 3:
Work Package 17: More work. Install Teflon sleeve under the selected wire bundle clamps in the left and right
rear wing spars.
Group 1, Configuration 2; Group 2-4, Configuration 3:
Work Package 18: More work. Do a detailed inspection of the selected fasteners in the right main fuel tank rear
spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners are not cap
sealed, cap seal the fasteners.
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### Page 16

Group 1, Configuration 2-3; Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4, Configuration
3-4:
Work Package 19: More work. Do a detailed inspection of the selected fasteners in the left main fuel tank rear
spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners are not cap
sealed, cap seal the fasteners.
Group 1, Configuration 2-3; Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4, Configuration
3-4:
Work Package 20: More work. Do a detailed inspection of the selected fasteners in the right main fuel tank rear
spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners are not cap
sealed, cap seal the fasteners.
Group 1, Configuration 2-5; Group 2, Configuration 3-6; Group 3, Configuration 3-6; Group 4, Configuration
3-6; Group 5-43, Configuration 2:
Work Package 21: More work. Install Teflon sleeve under the selected wire bundle clamps in the left rear wing
spar.
EFFECTIVITY
777-200, 777-200LR, 777-300, 777-300ER, 777F Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of
affected airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-26-03 is related to this service bulletin.
The effective date of AD 2011-26-03 is January 3, 2012.
For Group 1, Configuration 1, and Groups 2-4, Configurations 1-2 airplanes: Boeing recommends that the change
given in this service bulletin be done within 60 months after the effective date of AD 2010-24-12. The effective
date of AD 2010-24-12 is January 20, 2011.
NOTE: AD 2010-24-12 has been superseded by AD 2011-26-03.
For Group 1, Configurations 2-5; Groups 2-4, Configurations 3-6 airplanes and Groups 5-43 airplanes: Boeing
recommends that the change given in this service bulletin be done within 60 months after the Revision 3 date
of this service bulletin.
For Groups 44-45 airplanes: Boeing recommends that the change given in this service bulletin be done within
60 months after the Revision 4 date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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### Page 17 (OCR)

BOEING SERVICE BULLETIN 777-57A0050
RIGHT WING
REAR SPAR
RIGHT MAIN
FUEL TANK
RIGHT WING  BODY CENTER
FRONT SPAR  FUEL TANK
LEFT MAIN
FRONT SPAR  FUEL TANK
BULKHEAD  LEFT WING
REAR SPAR
LEFT WING
UNDER WING  FRONT SPAR
FAIRING
GROUP 1:
INSTALL TEFLON SLEEVING AROUND WIRE BUNDLES AND STRING TIE AT SELECTED CLAMP
LOCATIONS ON THE WING FRONT/REAR SPARS, UNDER WING FAIRING, LEFT/RIGHT
ENVIRONMENTAL CONTROL SYSTEM (ECS) BAYS AND ON THE FRONT SPAR BULKHEAD.
CAP SEAL SELECTED FASTENERS IN THE BODY CENTRE AND MAIN FUEL TANKS.
GROUPS 2-4:
INSTALL TEFLON SLEEVING AROUND WIRE BUNDLES AND STRING TIE AT SELECTED CLAMP
LOCATIONS ON THE WING FRONT/REAR SPARS, UNDER WING FAIRING AND LEFT/RIGHT ECS
BAYS. CAP SEAL SELECTED FASTENERS IN THE BODY CENTRE AND MAIN FUEL TANKS.
GROUPS 5-7, 9-43:
DO A DETAILED INSPECTION OF THE SELECTED WIRE BUNDLE CLAMPS IN THE LEFT/RIGHT
REAR WING SPARS. INSTALL TEFLON SLEEVING IF ANY CLAMP DOES NOT HAVE TEFLON
SLEEVING INSTALLED.
GROUPS 32-34, 36:
DO A DETAILED INSPECTION OF THE SELECTED WIRE BUNDLE CLAMPS IN THE RIGHT WING
FRONT SPAR. INSTALL TEFLON SLEEVING IF ANY CLAMP DOES NOT HAVE TEFLON
SLEEVING INSTALLED.
GROUPS 12, 18, 20-21, 23, 25, 27, 30, 33, 36, 38, 40, 43, 44-45:
DO A DETAILED INSPECTION OF THE SELECTED WIRE BUNDLE CLAMPS IN THE FRONT SPAR
BULKHEAD. INSTALL TEFLON SLEEVING IF ANY CLAMP DOES NOT HAVE TEFLON SLEEVING
INSTALLED.
GROUPS 8-12, 17, 20, 22, 25, 31, 34, 39, 42-43:
DO A DETAILED INSPECTION OF THE SELECTED WIRE BUNDLE CLAMPS IN THE LEFT/RIGHT
ECS BAYS. INSTALL TEFLON SLEEVING IF ANY CLAMP DOES NOT HAVE TEFLON SLEEVING
INSTALLED.
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### Page 18

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BLANK PAGE

### Page 19

Commercial 
Airplanes
777
Service Bulletin
Number: 777-57A0050
Original Issue: January 26, 2006
Revision 4: September 28, 2015
ATA System: 5710
SUBJECT: WINGS - Center and Outer Wings - Wire Bundle Teflon sleeve Installation and Fastener
Cap Sealing for Fuel Tank Wiring Hot Short Protection
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 applicable to 777-200, 777-200LR, 777-300, 777-300ER, 777F, line numbers
1-1058, 1060, 1065, 1072, 1074, 1088, 1090, 1100, 1102, 1110, 1112, 1117, 1120, 1126, 1134,
1138, 1144, 1146, 1152, 1156, 1158, 1172, 1178, 1180, 1188, 1192, 1208, 1210, 1212, 1230 in
45 Groups. The Variable Numbers and Group Information for the applicable airplanes is given
below. Refer to PRR 61998-4 and MRR 757015-016S for data about this change.
DESCRIPTIONCONFIGURATIONGROUP
777-200 airplanes before line number 504.-1
Airplanes that have not accomplished Boeing SB 777-57A0050
Original Issue, Revision 1, Revision 2 or Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Original
Issue.
2
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
1.
3
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
2.
4
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
5
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### Page 20

DESCRIPTIONCONFIGURATIONGROUP
777-200 airplanes before line number 504.-2
Airplanes with a W5164 wire bundle at the front spar bulkhead, that
have not accomplished Boeing SB 777-57A0050 Original Issue,
Revision 1, Revision 2 or Revision 3.
1
Airplanes without a W5164 wire bundle at the front spar bulkhead,
that have not accomplished Boeing SB 777-57A0050 Original Issue,
Revision 1, Revision 2 or Revision 3.
2
Airplanes that have accomplished Boeing SB 777-57A0050 Original
Issue.
3
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
1.
4
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
2.
5
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
6
777-300ER airplanes before line number 504.-3
Airplanes with a W5164 wire bundle at the front spar bulkhead, that
have not accomplished Boeing SB 777-57A0050 Original Issue,
Revision 1, Revision 2 or Revision 3.
1
Airplanes without a W5164 wire bundle at the front spar bulkhead,
that have not accomplished Boeing SB 777-57A0050 Original Issue,
Revision 1, Revision 2 or Revision 3.
2
Airplanes that have accomplished Boeing SB 777-57A0050 original
issue.
3
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
1.
4
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
2.
5
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
6
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### Page 21

DESCRIPTIONCONFIGURATIONGROUP
777-300 airplanes before line number 504.-4
Airplanes with a W5164 wire bundle at the front spar bulkhead, that
have not accomplished Boeing SB 777-57A0050 Original Issue,
Revision 1, Revision 2 or Revision 3.
1
Airplanes without a W5164 wire bundle at the front spar bulkhead,
that have not accomplished Boeing SB 777-57A0050 Original Issue,
Revision 1, Revision 2 or Revision 3.
2
Airplanes that have accomplished Boeing SB 777-57A0050 Original
Issue.
3
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
1.
4
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
2.
5
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
6
777-200LR airplanes line number 504 and after line number 504 that
need wire bundle sleeving inspection/installation.
-5
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-6
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-7
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 22

DESCRIPTIONCONFIGURATIONGROUP
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-8
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-9
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-10
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-11
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-12
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 23

DESCRIPTIONCONFIGURATIONGROUP
777-300 airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-13
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-14
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-15
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-16
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-17
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 24

DESCRIPTIONCONFIGURATIONGROUP
777-200LR airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-18
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-19
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-20
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777F airplanes after line number 504 that need wire bundle sleeving
inspection/installation.
-21
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-22
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 25

DESCRIPTIONCONFIGURATIONGROUP
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-23
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-24
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-25
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-26
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-27
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 26

DESCRIPTIONCONFIGURATIONGROUP
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-28
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-29
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777F airplanes after line number 504 that need wire bundle sleeving
inspection/installation.
-30
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-31
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-32
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 27

DESCRIPTIONCONFIGURATIONGROUP
777F airplanes after line number 504 that need wire bundle sleeving
inspection/installation.
-33
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-34
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-300ER airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-35
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777F airplanes after line number 504 that need wire bundle sleeving
inspection/installation.
-36
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-37
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 28

DESCRIPTIONCONFIGURATIONGROUP
777F airplanes after line number 504 that need wire bundle sleeving
inspection/installation.
-38
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-39
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-40
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200LR airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-41
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777-200 airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-42
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
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### Page 29

DESCRIPTIONCONFIGURATIONGROUP
777-200 airplane after line number 504 that needs wire bundle
sleeving inspection/installation.
-43
Airplanes that have not accomplished Boeing SB 777-57A0050
Revision 3.
1
Airplanes that have accomplished Boeing SB 777-57A0050 Revision
3.
2
777F airplanes after line number 504 that need wire bundle sleeving
inspection/installation.
-44
777-200 airplanes after line number 504 that need wire bundle
sleeving inspection/installation.
-45
Airplane Models:
777-200, 777-200LR, 777-300, 777-300ER, 777F
GroupVariable Number
1WA001 - WA017
1WA076 - WA080
1WA086 - WA093
1WA101 - WA104
1WA116 - WA119
1WA131 - WA137
1WA171 - WA175
1WA196 - WA198
1WA206 - WA212
1WA221 - WA223
1WA231 - WA232
1WA241 - WA250
1WA261 - WA266
1WA281
8WA282
17WA283
1WA301 - WA302
8WA303 - WA304
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### Page 30

GroupVariable Number
2WB001 - WB021
2WB031 - WB046
2WB051 - WB088
2WB101 - WB106
2WB121 - WB125
2WB131 - WB139
10WB140 - WB141
12WB142 - WB148
2WB151 - WB155
2WB161 - WB177
2WB181 - WB194
2WB201 - WB215
2WB231 - WB247
2WB271 - WB273
2WB276 - WB286
2WB291 - WB302
2WB306 - WB307
2WB311 - WB337
2WB341 - WB342
2WB366 - WB367
10WB368
2WB371 - WB388
2WB406
2WB411 - WB413
2WB416 - WB437
42WB438
43WB439
2WB446 - WB453
2WB476
2WB481 - WB484
4WB501 - WB510
6WB511
13WB512
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### Page 31

GroupVariable Number
4WB531 - WB537
4WB551 - WB554
4WB591 - WB597
4WB601 - WB606
4WB611 - WB620
6WB621 - WB622
4WB631 - WB638
4WB646 - WB649
2WC051 - WC073
2WC101 - WC104
2WC111 - WC115
10WC116
11WC117
12WC118 - WC120
12WC221 - WC222
27WC223 - WC224
2WC241 - WC243
2WC281 - WC290
2WC301 - WC306
10WC307 - WC308
2WC361 - WC362
10WC363 - WC364
2WC371 - WC374
2WC381 - WC390
11WC391 - WC393
12WC394 - WC395
2WC441
2WC446 - WC448
12WC449
2WC456
9WC457
10WC458
12WC459
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### Page 32

GroupVariable Number
10WC486 - WC488
11WC489
12WC490 - WC493
12WC506 - WC508
11WC521
12WC522
12WC531 - WC536
12WC546 - WC547
20WC548
12WC556
12WC566 - WC567
23WC571 - WC572
27WC573 - WC574
25WC581
40WC586
45WC587
40WC591 - WC592
45WC593 - WC595
5WD001 - WD002
15WD011 - WD018
18WD031 - WD032
15WD033 - WD036
18WD046
15WD047 - WD055
15WD066 - WD073
26WD074 - WD075
15WD081
22WD082 - WD086
31WD087 - WD088
39WD089
32WD091
31WD096
34WD101 - WD105
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### Page 33

GroupVariable Number
34WD111
37WD116
41WD117
3WD501 - WD502
7WD503 - WD504
14WD505 - WD506
16WD507
14WD508 - WD510
24WD511 - WD513
3WD521 - WD529
7WD530 - WD533
16WD534 - WD537
14WD538 - WD540
24WD541
7WD546
14WD547 - WD550
16WD551 - WD552
24WD553 - WD554
3WD561
7WD562 - WD564
14WD565 - WD568
16WD569 - WD571
19WD572
14WD573
7WD581 - WD588
14WD589 - WD590
16WD591 - WD594
14WD595 - WD599
7WD606 - WD607
14WD608 - WD609
7WD621 - WD626
14WD627 - WD629
16WD630 - WD632
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### Page 34

GroupVariable Number
7WD651 - WD652
14WD653 - WD654
16WD655 - WD658
19WD659
14WD660 - WD662
24WD663 - WD664
29WD665
7WD671 - WD675
24WD676
35WD677
14WD691 - WD696
16WD697 - WD701
19WD702 - WD704
14WD705 - WD709
16WD741 - WD745
19WD746
14WD747 - WD751
24WD752
16WD761 - WD768
19WD769 - WD770
24WD771
14WD786
16WD787
19WD788
16WD796 - WD799
19WD800 - WD802
14WD803 - WD806
24WD807 - WD811
28WD812
29WD813
35WD814 - WD819
16WD826 - WD828
14WD829 - WD830
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### Page 35

GroupVariable Number
24WD831 - WD834
29WD835 - WD837
16WD846
19WD847 - WD848
14WD849 - WD853
24WD854 - WD860
28WD861
35WD862 - WD867
16WD871
19WD872
14WD873 - WD876
24WD877 - WD880
28WD881
29WD882
35WD883 - WD888
19WD911 - WD912
24WD913 - WD914
35WD915 - WD917
24WD921 - WD922
35WD923 - WD925
14WD936 - WD939
35WD940 - WD942
14WD946
24WD947 - WD948
29WD949 - WD951
35WD952 - WD955
14WD966 - WD968
24WD969
29WD970
14WD981 - WD982
24WD986 - WD987
35WD991 - WD992
35WD996
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### Page 36

GroupVariable Number
24WE001 - WE002
29WE003 - WE004
29WE011 - WE012
24WE021
29WE022 - WE023
35WE024 - WE026
35WE031 - WE034
35WE051 - WE055
29WE071
35WE072
29WE081
35WE082 - WE084
35WE091 - WE093
29WE126 - WE127
35WE128 - WE137
35WE151 - WE160
35WE176 - WE177
35WE186 - WE204
35WE216 - WE217
35WE226 - WE230
35WE236 - WE240
35WE251 - WE253
35WE261
35WE271 - WE272
35WE301
21WF001 - WF004
21WF016 - WF019
30WF020
38WF021
44WF022 - WF023
21WF031 - WF032
38WF033 - WF035
44WF036 - WF041
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### Page 37

GroupVariable Number
21WF046 - WF049
30WF050 - WF051
33WF052 - WF053
36WF054 - WF055
38WF056 - WF064
44WF065 - WF066
38WF075
21WF076 - WF077
21WF081 - WF084
30WF085 - WF086
33WF087
36WF088
21WF096 - WF097
30WF098 - WF099
36WF100 - WF101
21WF106 - WF107
38WF108 - WF109
30WF111 - WF112
38WF113 - WF114
44WF115 - WF116
33WF121
36WF122
38WF123 - WF124
36WF131
44WF132 - WF133
38WF136 - WF137
44WF138 - WF139
38WF146 - WF147
38WF151 - WF152
44WF156 - WF159
44WF166 - WF170
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### Page 38

2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
This service bulletin will help to prevent possible sources of ignition within the fuel tanks caused by
wiring shorts at the clamp locations on the wire bundles that are routed on the fuel tank boundary
structure. An ignition source within the fuel tanks could result in a fire or an explosion.
This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel
Tank System Fault Tolerance Evaluation Requirements". This service bulletin addresses the concerns
of electrical arcing that can be caused by the electrical energy present in the wire bundles within the
fuel tank boundary structure. Seven operators have reported pinched insulation or wiring damage under
the clamp. In some cases, bared wires were found. This condition can cause an electrical arcing on
the fuel tank boundary structure or the voltage can find a path to permanent fasteners that penetrate
through the fuel tank and creates an electrical arcing inside the fuel tank. This service bulletin provides
instructions to install Teflon sleeve under the wire bundle clamps and cap seal the penetrating fasteners
that were determined to have a capability of creating electrical arcing during a wiring short event.
Revision 1 was sent to include these changes: For Group 1, 2 and 4 airplane only, include additional
clamp locations that require Teflon sleeve and fastener that requires to be cap sealed. Include lacing
tape as a material that needs to be supplied by the operator, clarify access panel numbers and clarify
the wiring configuration at the front spar bulkhead.
Revision 2 was sent to correct the quantity of fasteners that need to be cap sealed, and to give a
tolerance to the dimensions for Teflon sleeve installation. Also, a note is added to tell operators that if
ring posts are installed at the locations where the installation of Teflon sleeve on the wire bundles is
necessary, the ring posts must be replaced with clamps.
Revision 3 was sent to correct discrepancies found by operators during the accomplishment of this
service bulletin. Also, more wire bundle clamp locations that need Teflon sleeve installation are added.
These clamp configuration changes are necessary to help prevent a possible ignition source within the
fuel tanks caused by wiring shorts.
Revision 4 is sent to add some wire bundle W8173 clamp locations in the left wing rear spar that need
Teflon sleeve installation. Also, some discrepancies in the compliance data, and in the Accomplishment
Instructions and Figure group applicability data are corrected. Airplanes WF022-WF023, WF036-WF041,
WF065-WF066, WF115-WF116, WF132-WF133, WF138-WF139, WF156-WF159, WF166-WF170 are
added to a new Group 44, and airplanes WC587, WC593-WC595 are added to a new Group 45 of this
service bulletin effectivity. These airplanes need to do a detailed inspection of the selected wire bundle
clamps in the front spar bulkhead, to make sure that Teflon sleeve is installed.
The data given in Alternative Method of Compliance Notice 777-57A0050 AMOC 01 is included in this
revision.
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### Page 39

D. Description
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4,
Configuration 1-2:
Work Package 1: Install Teflon sleeve under the selected clamps on the wire bundles in the wing rear
spars.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4,
Configuration 1-2:
Work Package 2: Install Teflon sleeve under the selected clamps on the wire bundles in the wing
inboard and outboard front spars.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4,
Configuration 1-2:
Work Package 3: Install Teflon sleeve under the selected clamps on the wire bundles in the wing-to-body
fairings and left/right Environmental Control System (ECS) bays.
Group 2, Configuration 1-2; Group 3, Configuration 1-2; Group 4, Configuration 1-2:
Work Package 4: Install Teflon sleeve under the selected clamps on the wire bundles in the front spar
bulkhead.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4,
Configuration 1-2:
Work Package 5: Cap seal the selected fasteners in the center wing fuel tanks.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4,
Configuration 1-2:
Work Package 6: Cap seal the selected fasteners in the left main and surge fuel tank.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group 4,
Configuration 1-2:
Work Package 7: Cap seal the selected fasteners in the right main and surge fuel tank.
Group 5-7, 9-43, Configuration 1:
Work Package 8: Do a detailed inspection of the selected wire bundle clamps in the left and right rear
wing spars. If the wire bundle clamps have the Teflon sleeve installed then no more work is necessary.
If any of the clamps do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle
clamps.
Group 32-34, 36, Configuration 1:
Work Package 9: Do a detailed inspection of the selected wire bundle clamps in the right wing inboard
front spar. If the wire bundle clamps have the Teflon sleeve installed then no more work is necessary.
If any of the clamps do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle
clamps.
Group 12, 18, 20-21, 23, 25, 27, 30, 33, 36, 38, 40, 43, Configuration 1; Group 44-45:
Work Package 10: Do a detailed inspection of the selected wire bundle clamps in the front spar bulkhead.
If the wire bundle clamps have the Teflon sleeve installed then no more work is necessary. If any of
the clamps do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle clamps.
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### Page 40

Group 8-12, 17, 20, 22, 25, 31, 34, 39, 42-43, Configuration 1:
Work Package 11: Do a detailed inspection of the selected wire bundle clamps in the left and right ECS
bay. If the wire bundle clamps have the Teflon sleeve installed then no more work is necessary. If any
of the clamps do not have the Teflon sleeve installed, install Teflon sleeve under the wire bundle clamps.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4,
Configuration 3-5:
Work Package 12: More work. Do a detailed inspection of the selected wire bundle clamps in the left
rear wing spar. If the wire bundle clamps have the Teflon sleeve installed then no more work is
necessary. If any of the wire bundle clamps do not have the Teflon sleeve installed, install Teflon sleeve
under the wire bundle clamps. Do a detailed inspection of a wire bundle clamp in the right rear wing
spar at the approximate location IRSS 450. If the clamp type is not a saddle clamp, remove the existing
clamp and replace it with a saddle clamp. Do a detailed inspection of the applicable Teflon sleeve
installed under the wire bundle clamps, on wire bundles with a diameter more than 1 inch, in the left
and right wing rear spars for correct installation. If all the Teflon sleeve have been installed correctly,
then no more work is necessary. If any of the Teflon sleeve have not been installed correctly, then
replace the Teflon sleeve.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4,
Configuration 3-5:
Work Package 13: More work. Do a detailed inspection of the applicable Teflon sleeve installed under
the wire bundle clamps, on wire bundles with a diameter more than 1 inch, in the left and right wing
inboard and outboard front spars for correct installation. If all the Teflon sleeve have been installed
correctly, then no more work is necessary. If any of the Teflon sleeve have not been installed correctly,
then replace the Teflon sleeve.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4,
Configuration 3-5:
Work Package 14: More work. Do a detailed inspection of the selected Teflon sleeve installed under
the wire bundle clamps, on wire bundles with a diameter more than 1 inch, in the left and right
wing-to-body fairings and the left and right ECS Bays for correct installation. If all the Teflon sleeve
have been installed correctly, then no more work is necessary. If any of the Teflon sleeve have not
been installed correctly, then replace the Teflon sleeve.
Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration 3-5:
Work Package 15: More work. Do a detailed inspection of the applicable Teflon sleeve installed under
the wire bundle clamps, on wire bundles with a diameter more than 1 inch, in the front spar bulkhead
for correct installation. If all the Teflon sleeve have been installed correctly, then no more work is
necessary. If any of the Teflon sleeve have not been installed correctly, then replace the Teflon sleeve.
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4,
Configuration 3-5:
Work Package 16: More work. Do a detailed inspection of the selected fasteners in the right main fuel
tank rear spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners
are not cap sealed, cap seal the fasteners.
Group 1, Configuration 2; Group 2, 4, Configuration 3:
Work Package 17: More work. Install Teflon sleeve under the selected wire bundle clamps in the left
and right rear wing spars.
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### Page 41

Group 1, Configuration 2; Group 2-4, Configuration 3:
Work Package 18: More work. Do a detailed inspection of the selected fasteners in the right main fuel
tank rear spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners
are not cap sealed, cap seal the fasteners.
Group 1, Configuration 2-3; Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4,
Configuration 3-4:
Work Package 19: More work. Do a detailed inspection of the selected fasteners in the left main fuel
tank rear spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners
are not cap sealed, cap seal the fasteners.
Group 1, Configuration 2-3; Group 2, Configuration 3-4; Group 3, Configuration 3-4; Group 4,
Configuration 3-4:
Work Package 20: More work. Do a detailed inspection of the selected fasteners in the right main fuel
tank rear spar. If all the fasteners are cap sealed then no more work is necessary. If any of the fasteners
are not cap sealed, cap seal the fasteners.
Group 1, Configuration 2-5; Group 2, Configuration 3-6; Group 3, Configuration 3-6; Group 4,
Configuration 3-6; Group 5-43, Configuration 2:
Work Package 21: More work. Install Teflon sleeve under the selected wire bundle clamps in the left
rear wing spar.
NOTE: Boeing Service Bulletin (SB) 777-57A0051 contains similar changes in the same areas inside
the fuel tanks. Boeing recommends that the changes given in SB 777-57A0051 be done on
the commonly affected airplanes at the same time with the changes given in this service
bulletin.
Revision 1 - More work is necessary on airplanes changed as shown in the original issue of this service
bulletin. For Groups 1, 2 and 4 airplanes, Install one additional Teflon sleeve on W8473 in accordance
with FIGURE 4, View A. Install two additional Teflon sleeve on W8475 in accordance with FIGURE 6,
View A. Cap seal one additional fastener in accordance with FIGURE 26, View E and FIGURE 29,
View E if cap seal was done only on two out of three fasteners that are common to the outside support
bracket.
Revision 2 - More work is necessary on airplanes changed as shown in the original issue or Revision
1 of this service bulletin. For Group 1, 2 and 4 airplanes, cap seal one more fastener in accordance
with FIGURE 27, View A. Cap seal one more fastener in accordance with FIGURE 30, View A. For
Group 3 airplanes, cap seal one more fastener in accordance with FIGURE 28, View A. Cap seal one
more fastener in accordance with FIGURE 31, View A.
Revision 3 - More work is necessary on airplanes changed in accordance with the original issue,
Revision 1 or Revision 2 of this service bulletin. For Group 1, Configuration 2 and Groups 2 thru 4,
Configuration 3 airplanes do the following:
– Do a detailed inspection of the selected wire bundle clamp locations in the left rear wing spar. If
any of the clamp locations do not have the Teflon sleeve installed, install Teflon sleeve under the
wire bundle clamps. Do a detailed inspection of a wire bundle clamp in the right rear wing spar at
the approximate location IRSS 450. If the clamp type is not a saddle clamp, remove the existing
clamp and replace it with a saddle clamp. Refer to Work Package 12 for the work instructions.
– Do a detailed inspection of the selected Teflon sleeve installed under the wire bundle clamps, on
wire bundles with a diameter more than 1 inch to make sure the Teflon sleeve are correctly installed.
If any of the Teflon sleeve are not correctly installed, replace the Teflon sleeve. Refer to Work
Packages 12 thru 15 for the work instructions.
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– Do a detailed inspection of the selected fasteners in the right main fuel tank rear spar. If any of
the fasteners are not cap sealed, cap seal the fasteners. Refer to Work Package 16 for the work
instructions.
Effects of this Revision on airplanes on which Original Issue, Revision 1 thru Revision 3 was previously
done:
ActionConditionGroup
Do Work Packages 12 thru 14,
16 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Original Issue.
Group 1, Configuration 2
Do Work Packages 12 thru 21.Airplanes that have accomplished Boeing SB
777-57A0050 Original Issue.
Group 2, 4, Configuration 3
Do Work Packages 12 thru 16,
18 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Original Issue.
Group 3, Configuration 3
Do Work Packages 12 thru 14,
16, 19 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 1.
Group 1, Configuration 3
Do Work Packages 12 thru 16,
19 thru 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 1.
Group 2-4, Configuration 4
Do Work Packages 12 thru 14,
16, 21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 2.
Group 1, Configuration 4
Do Work Packages 12 thru 16,
21.
Airplanes that have accomplished Boeing SB
777-57A0050 Revision 2.
Group 2-4, Configuration 5
Do Work Package 21.Airplanes that have accomplished Boeing SB
777-57A0050 Revision 3.
Group 1, Configuration 5;
Group 2-4, Configuration 6;
Group 5-43, Configuration 2
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
135, 136, 191, 192, 511, 521, 526, 531, 532,
533, 541, 542, 543, 551, 611, 621, 626, 631,
632, 633, 641, 642, 643, 651
777-200
Group 2:
Affected Maintenance Zones
ZoneModel
125, 126, 133, 134, 135, 136, 191, 192, 511,
521, 526, 531, 532, 533, 541, 542, 543, 551,
611, 621, 626, 631, 632, 633, 641, 642, 643, 651
777-200
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Group 3:
Affected Maintenance Zones
ZoneModel
125, 126, 133, 134, 135, 136, 191, 192, 511,
521, 526, 531, 532, 533, 541, 542, 543, 551,
611, 621, 626, 631, 632, 633, 641, 642, 643, 651
777-300ER
Group 4:
Affected Maintenance Zones
ZoneModel
125, 126, 133, 134, 135, 136, 191, 192, 511,
521, 526, 531, 532, 533, 541, 542, 543, 551,
611, 621, 626, 631, 632, 633, 641, 642, 643, 651
777-300
Group 5:
Affected Maintenance Zones
ZoneModel
651, 652777-200LR
Group 6:
Affected Maintenance Zones
ZoneModel
551, 552777-300
Group 7, 19:
Affected Maintenance Zones
ZoneModel
551, 552777-300ER
Group 8:
Affected Maintenance Zones
ZoneModel
135777-200
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Group 9, 17:
Affected Maintenance Zones
ZoneModel
135, 551, 552777-200
Group 10-11, 20:
Affected Maintenance Zones
ZoneModel
135, 551, 552, 651, 652777-200
Group 12, 25, 43:
Affected Maintenance Zones
ZoneModel
125, 126, 135, 136, 551, 552, 651, 652777-200
Group 13:
Affected Maintenance Zones
ZoneModel
551, 552, 651, 652777-300
Group 14, 16, 24, 29:
Affected Maintenance Zones
ZoneModel
551, 552, 651, 652777-300ER
Group 15, 26, 37, 41:
Affected Maintenance Zones
ZoneModel
551, 552, 651, 652777-200LR
Group 18:
Affected Maintenance Zones
ZoneModel
125, 126, 551, 552, 651, 652777-200LR
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Group 21, 30, 38:
Affected Maintenance Zones
ZoneModel
125, 126, 551, 552, 651, 652777F
Group 22, 31, 39:
Affected Maintenance Zones
ZoneModel
136, 551, 552, 651, 652777-200LR
Group 23, 27:
Affected Maintenance Zones
ZoneModel
125, 126, 551, 552, 651, 652777-200
Group 28:
Affected Maintenance Zones
ZoneModel
651, 652777-300ER
Group 32:
Affected Maintenance Zones
ZoneModel
551, 552, 622, 623, 624, 651, 652777-200LR
Group 33, 36:
Affected Maintenance Zones
ZoneModel
125, 126, 551, 552, 622, 623, 624, 651, 652777F
Group 34:
Affected Maintenance Zones
ZoneModel
136, 551, 552, 622, 623, 624, 651, 652777-200LR
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Group 35:
Affected Maintenance Zones
ZoneModel
125, 126, 551, 552, 622, 623, 624, 651, 652777-300ER
Group 40:
Affected Maintenance Zones
ZoneModel
125, 126, 651, 652777-200
Group 42:
Affected Maintenance Zones
ZoneModel
135, 136, 551, 552, 651, 652777-200
Group 44:
Affected Maintenance Zones
ZoneModel
125, 126777F
Group 45:
Affected Maintenance Zones
ZoneModel
125, 126777-200
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-26-03 is related to this service
bulletin. The effective date of AD 2011-26-03 is January 3, 2012.
For Group 1, Configuration 1, and Groups 2-4, Configurations 1-2 airplanes: Boeing recommends that
the change given in this service bulletin be done within 60 months after the effective date of AD
2010-24-12. The effective date of AD 2010-24-12 is January 20, 2011.
NOTE: AD 2010-24-12 has been superseded by AD 2011-26-03.
For Group 1, Configurations 2-5; Groups 2-4, Configurations 3-6 airplanes and Groups 5-43 airplanes:
Boeing recommends that the change given in this service bulletin be done within 60 months after the
Revision 3 date of this service bulletin.
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### Page 47

For Groups 44-45 airplanes: Boeing recommends that the change given in this service bulletin be done
within 60 months after the Revision 4 date of this service bulletin.
F. Approval
This service bulletin was examined by the FAA. The changes specified in this service bulletin comply
with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency
(EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the
service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original
Boeing delivery configuration or as modified by other approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection
or modification) defined in this service bulletin as an alternative method of compliance to the requirements
of paragraph (g)(1) of AD 2011-26-03. All provisions of AD 2011-26-03 that are not specifically referenced
in the above statement remain fully applicable and must be complied with accordingly.
G. Manpower
The table below shows an estimate of the task-hours necessary to do this change 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 examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 4, Configuration 1-2:
Work Package 1 - Rear Spar Wire Bundle Teflon sleeve Installation
Elapsed HoursTask-HoursNumber of PersonsTask
1.002.002Open Access
3.877.752FIGURE 4
4.629.252FIGURE 6
0.621.252Close Access
10.1120.25TOTAL FOR EACH AIRPLANE
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### Page 48

Group 3, Configuration 1-2:
Work Package 1 - Rear Spar Wire Bundle Teflon sleeve Installation
Elapsed HoursTask-HoursNumber of PersonsTask
1.002.002Open Access
5.0010.002FIGURE 5
5.1310.252FIGURE 7
0.621.252Close Access
11.7523.50TOTAL FOR EACH AIRPLANE
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 4, Configuration 1-2:
Work Package 2 - Inboard And Outboard Front Spar Wire Bundle Teflon sleeve Installation
Elapsed HoursTask-HoursNumber of PersonsTask
2.2510.004Open Access
5.1310.252FIGURE 9 and FIGURE 10
5.1310.252FIGURE 12 and FIGURE 13
3.0612.254Close Access
15.5742.75TOTAL FOR EACH AIRPLANE
Group 3, Configuration 1-2:
Work Package 2 - Inboard And Outboard Front Spar Wire Bundle Teflon sleeve Installation
Elapsed HoursTask-HoursNumber of PersonsTask
2.2510.004Open Access
5.5011.002FIGURE 9 and FIGURE 11
5.5011.002FIGURE 12 and FIGURE 14
3.0612.254Close Access
16.3144.25TOTAL FOR EACH AIRPLANE
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group
4, Configuration 1-2:
Work Package 3 - Wing-To-Body Fairing / Environmental Control System (ECS) bay Wire
Bundle Teflon sleeve Installation
Elapsed HoursTask-HoursNumber of PersonsTask
0.621.252Open Access
2.404.802FIGURE 16
2.565.122FIGURE 17
1.002.002FIGURE 18
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### Page 49

Group 1-2, Configuration 1; Group 2, Configuration 2; Group 3, Configuration 1-2; Group
4, Configuration 1-2:
Work Package 3 - Wing-To-Body Fairing / Environmental Control System (ECS) bay Wire
Bundle Teflon sleeve Installation
Elapsed HoursTask-HoursNumber of PersonsTask
1.002.002FIGURE 19
0.500.501Close Access
8.0815.67TOTAL FOR EACH AIRPLANE
Group 2, Configuration 1-2; Group 3, Configuration 1-2; Group 4, Configuration 1-2:
Work Package 4 - Front Spar Bulkhead Wire Bundle Teflon sleeve Installation
Elapsed HoursTask-HoursNumber of PersonsTask
3.0012.004Open Access
2.755.502FIGURE 21, FIGURE 32,
FIGURE 33 or FIGURE 34
3.0012.004Close Access
8.7529.50TOTAL FOR EACH AIRPLANE
Group 1, Configuration 1:
Work Package 5 - Center Fuel Tank Fastener Cap Seal Application
Elapsed HoursTask-HoursNumber of PersonsTask
2.5410.184Open Access
11.2522.502FIGURE 23
11.2522.502FIGURE 24
1.124.504Close Access
26.1659.68TOTAL FOR EACH AIRPLANE
Group 2, Configuration 1-2; Group 3, Configuration 1-2; Group 4, Configuration 1-2:
Work Package 5 - Center Fuel Tank Fastener Cap Seal Application
Elapsed HoursTask-HoursNumber of PersonsTask
2.5710.304Open Access
11.2522.502FIGURE 23
11.2522.502FIGURE 24
36.7573.502FIGURE 25
1.174.674Close Access
62.99133.47TOTAL FOR EACH AIRPLANE
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### Page 50

Group 1-2, Configuration 1; Group 2, Configuration 2; Group 4, Configuration 1-2:
Work Package 6 - Left Main and Surge Fuel Tank Fastener Cap Seal Application
Elapsed HoursTask-HoursNumber of PersonsTask
3.5014.004Open Access
6.0018.003FIGURE 26
14.2557.004FIGURE 27
1.757.004Close Access
25.5096.00TOTAL FOR EACH AIRPLANE
Group 3, Configuration 1-2:
Work Package 6 - Left Main and Surge Fuel Tank Fastener Cap Seal Application
Elapsed HoursTask-HoursNumber of PersonsTask
3.5014.004Open Access
6.0018.003FIGURE 26
14.2557.004FIGURE 27
14.4457.754FIGURE 28
1.757.004Close Access
39.94153.75TOTAL FOR EACH AIRPLANE
Group 1-2, Configuration 1; Group 2, Configuration 2; Group 4, Configuration 1-2:
Work Package 7 - Right Main and Surge Fuel Tank Fastener Cap Seal Application
Elapsed HoursTask-HoursNumber of PersonsTask
3.5014.004Open Access
7.0021.003FIGURE 29
14.2557.004FIGURE 30
1.757.004Close Access
26.5099.00TOTAL FOR EACH AIRPLANE
Group 3, Configuration 1-2:
Work Package 7 - Right Main and Surge Fuel Tank Fastener Cap Seal Application
Elapsed HoursTask-HoursNumber of PersonsTask
3.5014.004Open Access
7.0021.003FIGURE 29
14.2557.004FIGURE 30
14.4457.754FIGURE 31
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Group 3, Configuration 1-2:
Work Package 7 - Right Main and Surge Fuel Tank Fastener Cap Seal Application
Elapsed HoursTask-HoursNumber of PersonsTask
1.757.004Close Access
40.94156.75TOTAL FOR EACH AIRPLANE
Group 5, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
1.001.001FIGURE 57
1.001.001FIGURE 77
2.252.251Close Access
6.506.50TOTAL FOR EACH AIRPLANE
Group 6, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 46
0.100.101FIGURE 66
2.252.251Close Access
4.704.70TOTAL FOR EACH AIRPLANE
Group 7, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 49
0.100.101FIGURE 69
2.252.251Close Access
4.704.70TOTAL FOR EACH AIRPLANE
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### Page 52

Group 9-10, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.050.051FIGURE 39
0.100.101FIGURE 50
0.100.101FIGURE 59
0.100.101FIGURE 70
2.252.251Close Access
4.854.85TOTAL FOR EACH AIRPLANE
Group 11, 42, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection And Installation
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.250.251FIGURE 41
0.100.101FIGURE 50
0.250.251FIGURE 61
0.100.101FIGURE 70
2.252.251Close Access
5.205.20TOTAL FOR EACH AIRPLANE
Group 12, 23, 43, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.300.301FIGURE 47
0.100.101FIGURE 51
0.500.501FIGURE 67
0.150.151FIGURE 71
2.252.251Close Access
5.555.55TOTAL FOR EACH AIRPLANE
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### Page 53

Group 13, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.200.201FIGURE 43
0.050.051FIGURE 58
0.300.301FIGURE 63
0.050.051FIGURE 78
2.252.251Close Access
5.105.10TOTAL FOR EACH AIRPLANE
Group 14, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.650.651FIGURE 45
0.300.301FIGURE 56
0.650.651FIGURE 65
0.300.301FIGURE 76
2.252.251Close Access
6.406.40TOTAL FOR EACH AIRPLANE
Group 15, 18, 22, 26, 31-32, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.600.601FIGURE 42
1.001.001FIGURE 57
0.600.601FIGURE 62
1.001.001FIGURE 77
2.252.251Close Access
7.707.70TOTAL FOR EACH AIRPLANE
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Group 16, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.750.751FIGURE 44
0.300.301FIGURE 56
0.750.751FIGURE 64
0.300.301FIGURE 76
2.252.251Close Access
6.606.60TOTAL FOR EACH AIRPLANE
Group 17, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.300.301FIGURE 40
0.300.301FIGURE 60
2.252.251Close Access
5.105.10TOTAL FOR EACH AIRPLANE
Group 19, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.750.751FIGURE 44
0.750.751FIGURE 64
2.252.251Close Access
6.006.00TOTAL FOR EACH AIRPLANE
Group 20, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.150.151FIGURE 51
0.150.151FIGURE 71
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Group 20, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Close Access
4.804.80TOTAL FOR EACH AIRPLANE
Group 21, 30, 33, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.750.751FIGURE 44
1.001.001FIGURE 57
0.750.751FIGURE 64
1.001.001FIGURE 77
2.252.251Close Access
8.008.00TOTAL FOR EACH AIRPLANE
Group 24, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.200.201FIGURE 43
0.300.301FIGURE 56
0.300.301FIGURE 63
0.300.301FIGURE 76
2.252.251Close Access
5.605.60TOTAL FOR EACH AIRPLANE
Group 25, 27, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.750.751FIGURE 44
0.100.101FIGURE 51
0.750.751FIGURE 64
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Group 25, 27, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
0.150.151FIGURE 71
2.252.251Close Access
6.256.25TOTAL FOR EACH AIRPLANE
Group 28, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.300.301FIGURE 56
0.300.301FIGURE 76
2.252.251Close Access
5.105.10TOTAL FOR EACH AIRPLANE
Group 29, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection And Installation
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 49
0.300.301FIGURE 56
0.100.101FIGURE 69
0.300.301FIGURE 76
2.252.251Close Access
5.305.30TOTAL FOR EACH AIRPLANE
Group 34, 37, 39, 41, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.600.601FIGURE 42
0.700.701FIGURE 55
0.600.601FIGURE 62
0.700.701FIGURE 75
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Group 34, 37, 39, 41, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Close Access
7.107.10TOTAL FOR EACH AIRPLANE
Group 35, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 48
0.200.201FIGURE 54
0.100.101FIGURE 68
0.200.201FIGURE 74
2.252.251Close Access
5.105.10TOTAL FOR EACH AIRPLANE
Group 36, 38, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.750.751FIGURE 44
0.200.201FIGURE 53
0.750.751FIGURE 64
0.200.201FIGURE 73
2.252.251Close Access
6.406.40TOTAL FOR EACH AIRPLANE
Group 40, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 52
0.100.101FIGURE 72
2.252.251Close Access
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Group 40, Configuration 1:
Work Package 8: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
4.704.70TOTAL FOR EACH AIRPLANE
Group 32-34, 36, Configuration 1:
Work Package 9: Inboard Front Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 79
0.150.151FIGURE 80
2.252.251Close Access
4.754.75TOTAL FOR EACH AIRPLANE
Group 12, 18, 20-21, 23, 25, 27, 30, 33, 36, 38, 40, 43, Configuration 1; Group 44-45:
Work Package 10: Front Spar Bulkhead Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 81
0.100.101FIGURE 82
2.252.251Close Access
4.704.70TOTAL FOR EACH AIRPLANE
Group 8-12, 17, 20, 42-43, Configuration 1:
Work Package 11: Environmental Control System (ECS) Bay Wire Bundle Teflon sleeve
Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.500.501FIGURE 35
0.500.501FIGURE 36
0.750.751FIGURE 37
0.800.801FIGURE 38
2.252.251Close Access
7.057.05TOTAL FOR EACH AIRPLANE
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### Page 59

Group 8-12, 17, 20, 22, 25, 42-43, Configuration 1:
Work Package 11: Environmental Control System (ECS) Bay Wire Bundle Teflon sleeve
Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.500.501FIGURE 36
0.800.801FIGURE 38
2.252.251Close Access
5.805.80TOTAL FOR EACH AIRPLANE
Group 8-12, 17, 20, 22, 25, 31, 34, 39, 42-43, Configuration 1:
Work Package 11: Environmental Control System (ECS) Bay Wire Bundle Teflon sleeve
Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.500.501FIGURE 35
0.750.751FIGURE 37
2.252.251Close Access
5.755.75TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 4, Configuration 3-5:
Work Package 12: More Work: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.150.151FIGURE 83
0.100.101FIGURE 85
0.050.051FIGURE 87
0.150.151FIGURE 88
2.252.251Close Access
4.954.95TOTAL FOR EACH AIRPLANE
Group 3, Configuration 3-5:
Work Package 12: More Work: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.252.251Open Access
0.100.101FIGURE 84
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 26, 2006
777-57A0050Revision 4: September 28, 2015
59 of 514
BOEING SERVICE BULLETIN 777-57A0050

### Page 60

Group 3, Configuration 3-5:
Work Package 12: More Work: Rear Spar Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
0.100.101FIGURE 86
0.050.051FIGURE 87
0.150.151FIGURE 88
0.600.601FIGURE 91
2.252.251Close Access
5.505.50TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group
4, Configuration 3-5:
Work Package 13: More Work: Inboard And Outboard Front Spar Wire Bundle Teflon sleeve
Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
2.605.202Open Access
0.300.301FIGURE 91
2.605.202Close Access
5.5010.70TOTAL FOR EACH AIRPLANE
Group 1, Configuration 2-4; Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group
4, Configuration 3-5:
Work Package 14: More Work: Wing-To-Body Fairing / Environmental Control System (ECS)
Bay Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
1.001.001Open Access
0.300.301FIGURE 91
1.001.001Close Access
2.302.30TOTAL FOR EACH AIRPLANE
Group 2, Configuration 3-5; Group 3, Configuration 3-5; Group 4, Configuration 3-5:
Work Package 15: More Work: Front Spar Bulkhead Wire Bundle Teflon sleeve Inspection
Elapsed HoursTask-HoursNumber of PersonsTask
3.0012.004Open Access
0.500.501FIGURE 91
3.0012.004Close Access
6.5024.50TOTAL FOR EACH AIRPLANE
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 26, 2006
777-57A0050Revision 4: September 28, 2015
60 of 514
BOEING SERVICE BULLETIN 777-57A0050

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