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Commercial Airplanes DC10 Service Bulletin Number: DC10-53-111 Original Issue: December 05, 1980 Revision 7: March 16, 2011 ATA System: 5350 SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional Wing-to-Fuselage Fillets Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 1989 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 1 of 66
4.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 2 of 66 BOEING SERVICE BULLETIN DC10-53-111
BLANK PAGE
Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 5 B. Concurrent Requirements ...................................... 1 5 C. Reason ................................................ 1 5 D. Description .............................................. 1 6 E. Compliance .............................................. 1 7 F. Approval ............................................... 1 7 G. Manpower .............................................. 1 8 H. Weight and Balance Changes .................................... 1 9 I. Electrical Load Data ......................................... 1 9 J. References .............................................. 1 9
1. Existing Data: ......................................... 1 9
2. Data supplied with this Service Bulletin: ........................... 1 9
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 9 K. Publications Affected ........................................ 2 0 L. Interchangeability and Intermixability of Parts ........................... 2 0
2. MATERIAL INFORMATION ........................................ 2 1 A. Material - Price and Availability ................................... 2 1 B. Industry Support Information .................................... 2 1 C. Parts Necessary For Each Airplane ................................. 2 1
1. Kits/Parts: ........................................... 2 1
2. Parts and Materials Supplied by the Operator: ........................ 2 2
3. Parts Modified and Reidentified: ............................... 2 3
4. Parts Removed and Not Replaced: .............................. 2 3 D. Parts Necessary to Change Spares ................................. 2 3 E. Special Tooling - Price and Availability ............................... 2 3 F. Special Tooling Necessary to do this Service Bulletin ....................... 2 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 5 A. GENERAL INFORMATION ..................................... 2 5 B. WORK INSTRUCTIONS ....................................... 2 6 FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS [Group 1, Configuration 1] ................................... 2 8 FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS [Group 2, Configuration 1] ................................... 3 7 FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND REPLACEMENT OF FASTENERS [Group 1-2, Configuration 2] ........... 5 6 Appendix A: BONDING STRAP INSTALLATION PROCEDURE ..................... 6 6
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 3 of 66 BOEING SERVICE BULLETIN DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 4 of 66 BOEING SERVICE BULLETIN DC10-53-111
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Commercial Airplanes DC10 Service Bulletin Revision Transmittal SheetNumber: DC10-53-111Original Issue: December 05, 1980 Revision 7: March 16, 2011 ATA System: 5350 SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional Wing-to-Fuselage Fillets This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-26-17, is related to this service bulletin.
No more work is necessary on the airplane(s) changed in accordance with Revision 6 of this service bulletin.
REASON FOR REVISION This revision is sent to re-instate one airplane inadvertently dropped from the effectivity of this service bulletin.
These sections were changed:
1. In Paragraph 1.A., Effectivity, reinstated fuselage number 317 into effectivity.
2. In Paragraph 1.E., Compliance, added new Federal Aviation Administration (FAA) Airworthiness Directive (AD).
3. In Paragraph 1.F. Approval, changed approval statement for newly referenced AD.
4. In Paragraph 1.J.1., Existing Data, added new AD.
5. In Paragraph 1.K., Publications, added Damage Tolerance Based Structural Inspections information.
6. In Paragraph 2.C., Parts Necessary for Each Airplane, changed supplier address.
7. In Paragraph 2.C.2., Parts and Materials Supplied by Operator, changed supplier address.
8. In Paragraph 3.A., General information, added new note.
9. In Figure 1, added information about part number substitution.
10. In Figure 2, added information about part number substitution.
11. In Figure 3, added information about part number substitution.
12. In Appendix, clarified work requirements.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 5 of 66
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY December 05, 1980Original Issue:
October 07, 1983Revision 1:
November 17, 1986Revision 2:
August 24, 1992Revision 3:
September 21, 2006Revision 4:
March 19, 2008Revision 5:
March 03, 2009Revision 6:
March 16, 2011Revision 7:
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 6 of 66 BOEING SERVICE BULLETIN DC10-53-111
Commercial Airplanes DC10 Service Bulletin SummaryNumber: DC10-53-111Original Issue: December 05, 1980 Revision 7: March 16, 2011 ATA System: 5350 SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional Wing-to-Fuselage Fillets
CONCURRENT REQUIREMENTS None.
BACKGROUND An engineering review of the conventional wing to fuselage fillet by Boeing revealed the requirement for bonding the fuselage mounted fillet support ribs to the fixed leading edge ribs. In the event of a severe lightning strike, the integrity of the electrical/electronic components interfaced with the wiring routed through the wing leading edge could be impaired. This condition is attributed to induced transients being imposed on wiring in the wing root area.
Installation of the new bonding straps to electrically connect the metallic frame of the fillet to the metal ribs of the wing leading edge will substantially reduce the induced electrical transients.
Service Bulletin Revision 4 was the result of the safety assessments conducted by Boeing under a Special Federal Aviation Ruling (SFAR) 88, Fuel Tank System Fault Tolerance Evaluation Requirements.
ACTION Group 1, Configuration 1:
Airplanes that have not Previously Accomplished Service Bulletin DC10-53-111
1. Installs ten new braided bonding straps between the metallic frame of the left and right wing to fuselage fillets and the wing leading edge ribs.
Group 2, Configuration 1:
Airplanes that have not Previously Accomplished Service Bulletin DC10-53-111
1. Replaces ten existing metal bonding straps with ten new braided bonding straps between the metallic frame of the left and right wing to fuselage fillets and the wing leading edge ribs.
Group 1-2, Configuration 2:
Airplanes that have Previously Accomplished Service Bulletin DC10-53-111
1. Verifies one existing braided bonding strap between the metallic frame of the left and right wing to fuselage fillets and the wing leading edge ribs is installed correctly and corrects the installation if required. Measures electrical resistance of previously installed braided bonding straps.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 7 of 66
EFFECTIVITY DC-10 and MD-10 Airplanes with conventional wing to fuselage fillets. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
Airplane factory serial number 47840 (Number 337) assigned to operator has had the original modification incorporated at manufacturers facility as an installation verification.
COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-26-17 is related to this service bulletin.
Boeing recommends that this service bulletin be accomplished at the first convenient maintenance period after receipt of parts, but not to exceed 7500 flight-hours from the issue date of Revision 3 of this service bulletin.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER Group 1, Configuration 1:
Elapsed HoursTotal Task HoursAirplanes
8.316.6DC-10 and MD-10 Group 2, Configuration 1:
Elapsed HoursTotal Task HoursAirplanes
12.424.8DC-10 and MD-10 Group 1-2, Configuration 2:
Elapsed HoursTotal Task HoursAirplanes
2.4 - 7.33.8 - 13.4DC-10 and MD-10
MATERIAL INFORMATION Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 8 of 66 BOEING SERVICE BULLETIN DC10-53-111
BOEING SERVICE BULLETIN DC10-53-111 GROUP 1 CONFIG 1:
INSTALLS TEN NEW BRAIDED
BONDING STRAPS ON CONVENTIONAL
WING TO FUSELAGE FILLETS GROUP 2 CONFIG 1:
REMOVE TEN METAL BONDING STRAPS
AND INSTALLS TEN NEW BRAIDED
BONDING STRAPS ON CONVENTIONAL
WING TO FUSELAGE FILLETS GROUPS 1-2, CONFIG 2:
REPOSITION ONE BRAIDED BONDING
STRAP ON CONVENTIONAL WING TO
FUSELAGE FILLETS
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE Original Issue: December 05, 1980 Revision 7: March 16, 2011 BOEING PROPRIETARY - DC10-53-111 Copyright © Unpublished Work - See page 1 for details. 9 of 66
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 10 of 66 BOEING SERVICE BULLETIN DC10-53-111
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Commercial Airplanes DC10 Service Bulletin Number: DC10-53-111 Original Issue: December 05, 1980 Revision 7: March 16, 2011 ATA System: 5350 SUBJECT: FUSELAGE - Aerodynamic Fairings - Install Electrical Bonding Straps on Conventional Wing-to-Fuselage Fillets
1. PLANNING INFORMATION A. Effectivity
1. Airplanes NOTE: This service bulletin is applicable only to airplanes with conventional wing to fuselage fillets. Airplanes that have installed the Cruise Performance Improvement Package (CPIP) fillets using Boeing Service Bulletin DC10-53-103 or DC10-53-119 should accomplish Boeing Service Bulletin DC10-53-109.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP Airplanes that did not receive metal bonding straps during production.-1 Airplanes that have not previously accomplished Service Bulletin DC10-53-111.
1 Airplanes that have previously accomplished Service Bulletin DC10-53-111.
2 Airplanes that received metal bonding straps during production.-2 Airplanes that have not previously accomplished Service Bulletin DC10-53-111.
1 Airplanes that have previously accomplished Service Bulletin DC10-53-111.
2 Airplane Models:
DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-30F (KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 11 of 66
GroupFuselage Number 11 22 13 - 21 123 - 28 130 - 32 233 134 - 43 145 147 - 56 257 158 - 59 161 - 62 263 164 - 70 172 273 174 275 176 277 - 78 179 - 80 183 185 - 86 288 189 290 - 91 192 293 - 95 196 - 98 299 - 100 1101 - 103 2104
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 7: March 16, 2011 12 of 66 BOEING SERVICE BULLETIN DC10-53-111