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McDonnell DouglasCommercial Airplanes DC10 Service Bulletin Number: DC10-53-111 Original Issue: December 05, 1980 Revision 6: March 03, 2009 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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 1989 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, 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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.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 6: March 03, 2009 1 of 67
5.0
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 6: March 03, 2009 2 of 67 BOEING SERVICE BULLETIN DC10-53-111
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Table of Contents
Revision Transmittal Sheet5
Summary7
1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 7 B. Concurrent Requirements ...................................... 1 7 C. Reason ................................................ 1 7 D. Description .............................................. 1 7 E. Compliance .............................................. 1 9 F . Approval ............................................... 1 9 G. Manpower .............................................. 1 9 H. Weight and Balance Changes .................................... 2 0 I. Electrical Load Data ......................................... 2 0 J. References .............................................. 2 0
1. Existing Data: .......................................... 2 0
2. Data supplied with this Service Bulletin: ........................... 2 0
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 0 K. Publications Affected ......................................... 2 1 L. Interchangeability and Intermixability of Parts ........................... 2 1
2. MATERIAL INFORMATION ........................................ 2 3 A. Material - Price and Availability ................................... 2 3 B. Industry Support Information .................................... 2 3 C. Parts Necessary For Each Airplane ................................. 2 3
1. Kits/Parts: ............................................ 2 3
2. Parts and Materials Supplied by the Operator: ........................ 2 4
3. Parts Modified and Reidentified: ................................ 2 5
4. Parts Removed and Not Replaced: .............................. 2 5 D. Parts Necessary to Change Spares ................................. 2 5 E. Special Tooling - Price and Availability ............................... 2 5 F . Special Tooling Necessary to do this Service Bulletin ....................... 2 5
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 7 A. GENERAL INFORMATION ..................................... 2 7 B. WORK INSTRUCTIONS ....................................... 2 8 FIGURE 1: CONVENTIONAL WING TO FUSELAGE FILLETS - INSTALLATION OF BONDING STRAPS [Group 1, Configuration 1] ................................... 3 0 FIGURE 2: CONVENTIONAL WING TO FUSELAGE FILLETS - REPLACEMENT OF BONDING STRAPS [Group 2, Configuration 1] ................................... 3 9 FIGURE 3: CONVENTIONAL WING TO FUSELAGE FILLETS - REPOSITION ONE BONDING STRAP AND REPLACEMENT OF FASTENERS [Group 1-2, Configuration 2] ........... 5 8 Appendix A: BONDING STRAP INSTALLATION PROCEDURE ...................... 6 7 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 6: March 03, 2009 3 of 67 BOEING SERVICE BULLETIN DC10-53-111
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 6: March 03, 2009 4 of 67 BOEING SERVICE BULLETIN DC10-53-111
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McDonnell DouglasCommercial Airplanes DC10 Service Bulletin Revision Transmittal SheetNumber: DC10-53-111Original Issue: December 05, 1980 Revision 6: March 03, 2009 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 No more work is necessary on airplanes changed as shown on revision 5 of this service bulletin.
More work is necessary on airplanes changed as shown in original release through revision 4 of this service bulletin. Measure electrical resistance of previously installed braided bonding straps. An additional 0.5 hours required.
REASON FOR REVISION This revision is sent to incorporate comments reported by operators which will clarify service bulletin instructions.
The data given in Information Notice DC10-53-111, IN 01 is included in this revision.
These sections were changed:
1. In Paragraph 1.D., Description, clarified group configuration description.
2. In Paragraph 1.F ., Approval, added Revision 6 and Alternative Method Of Compliance (AMOC) information.
3. In Paragraph 1.G., Manpower, added hours for electrical resistance check of previously installed braided bonding straps and correction of electrical bonds that failed.
4. In Paragraph 1.H., Weight and Balance Changes, reinstated weight and balance table removed from revision
4.
5. In Paragraph 3.B.1., Work Instructions, added resistance check for braided bonding straps previously installed.
6. In Figure 1, Sheet 2, Corrected fastener pattern.
7. In Figure 3, Added "as required" statement prior to step table.
Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity paragraph for changes.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 6: March 03, 2009 5 of 67
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:
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 6: March 03, 2009 6 of 67 BOEING SERVICE BULLETIN DC10-53-111
McDonnell DouglasCommercial Airplanes DC10 Service Bulletin SummaryNumber: DC10-53-111Original Issue: December 05, 1980 Revision 6: March 03, 2009 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 is 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/as 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 6: March 03, 2009 7 of 67
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 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.
Federal Aviation Administration (FAA) Airworthiness Directive 2006-16-03 is related to 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 Boeing Supplied Kits/Parts.
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 6: March 03, 2009 8 of 67 BOEING SERVICE BULLETIN DC10-53-111
BOEING SERVICE BULLETIN DC10-53-111 00000/00 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 U51648 Original Issue: December 05, 1980 Revision 6: March 03, 2009 DC10-53-111 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 67
BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 6: March 03, 2009 10 of 67 BOEING SERVICE BULLETIN DC10-53-111
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McDonnell DouglasCommercial Airplanes DC10 Service Bulletin Number: DC10-53-111 Original Issue: December 05, 1980 Revision 6: March 03, 2009 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.
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 6: March 03, 2009 11 of 67
GroupFuselage Number 11 110 2100 1101 - 103 2104 1105 - 106 1108 111 1110 - 113 2114 1115 - 116 2117 1118 - 119 112 1120 2121 - 123 1124 2125 1126 2127 1128 - 129 113 1130 - 133 2134 - 135 1136 2137 1138 - 139 114 1140 2141 1142 - 145 2146 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: December 05, 1980 DC10-53-111Revision 6: March 03, 2009 12 of 67 BOEING SERVICE BULLETIN DC10-53-111