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Commercial Airplanes DC10 Service Bulletin Number: DC10-53-182 Original Issue: June 28, 2013 ATA System: 5300 SUBJECT: FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment Frame to Cargo Liner Attachment Holes Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2013 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and 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: June 28, 2013 DC10-53-182 1 of 26
2.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 28, 2013 DC10-53-182 2 of 26 BOEING SERVICE BULLETIN DC10-53-182
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Table of Contents
Summary5
1. PLANNING INFORMATION7
A. Effectivity7
1. Airplanes7
2. Spares Affected ........................................ 1 0 B. Concurrent Requirements ...................................... 1 0 C. Reason ................................................ 1 1 D. Description .............................................. 1 1 E. Compliance .............................................. 1 2 F. Approval ............................................... 1 2 G. Manpower .............................................. 1 3 H. Weight and Balance Changes .................................... 1 3 I. Electrical Load Data ......................................... 1 4 J. References .............................................. 1 4
1. Existing Data: ......................................... 1 4
2. Data Supplied with this Service Bulletin: ........................... 1 4
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 4 K. Publications Affected ........................................ 1 4 L. Interchangeability and Intermixability of Parts ........................... 1 4 M. Software Accomplishment Summary ................................ 1 4
2. MATERIAL INFORMATION ........................................ 1 5 A. Material - Price and Availability ................................... 1 5 B. Industry Support Information .................................... 1 5 C. Parts Necessary for Each Airplane ................................. 1 5
1. Kits/Parts ............................................ 1 5
2. Parts and Materials Supplied by the Operator ........................ 1 6
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7 D. Parts Necessary to Change Spares ................................. 1 7 E. Special Tooling - Price and Availability ............................... 1 7 F. Special Tooling Necessary to do this Service Bulletin ....................... 1 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9 A. GENERAL INFORMATION ..................................... 1 9 B. WORK INSTRUCTIONS ....................................... 2 0 FIGURE 1: REMOVE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT FASTENERS .................................................. 2 1 FIGURE 2: INSPECT CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES . 23 FIGURE 3: CHANGE CARGO COMPARTMENT FRAME TO CARGO LINER ATTACHMENT HOLES . 25 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 28, 2013 DC10-53-182 3 of 26 BOEING SERVICE BULLETIN DC10-53-182
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 28, 2013 DC10-53-182 4 of 26 BOEING SERVICE BULLETIN DC10-53-182
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Commercial Airplanes DC10 Service Bulletin SummaryNumber: DC10-53-182Original Issue: June 28, 2013 ATA System: 5300 SUBJECT: FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment Frame to Cargo Liner Attachment Holes
CONCURRENT REQUIREMENTS None.
BACKGROUND Federal Aviation Administration (FAA) requirement 14 Code of Federal Regulations (CFR) Part 26.21, Amendment 26-6 with effective date May 24/2012, requires the establishment of a binding schedule for the release of new service actions (Service Bulletins) to support Widespread Fatigue Damage (WFD) rules Limit of Validity (LOV) from current regulatory limits, refer to 14 CFR Part 121.1115. To extend the LOV for airplanes in Paragraph
1.A.1, Effectivity, beyond the FAA published dates in Table 1 of 14 CFR Part 121.1115, new service actions have been identified. Inspecting and changing the frame fastener holes in the forward cargo compartment will extend the LOV. If the inspection and modification is not completed, there may be undetected cracks in the fastener holes which could result in the loss of fail safe structural integrity.
The left and right forward cargo compartment frames have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD).
ACTION This service bulletin provides instructions to do as follows:
1. Remove fasteners in the left and right hand sides of the forward cargo compartment.
2. Do an Eddy Current High Frequency (ETHF) inspection of the open fastener holes for cracks. Based on inspection findings do what follows:
Condition 1 - No Crack Detected
a. Install Hi-Loks.
Condition 2 - Crack Detected in Any Hole
a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing.
EFFECTIVITY DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-10F, and MD-10-30F Airplane(s). Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 28, 2013 DC10-53-182 5 of 26
COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the inspection and/or repair procedures 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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 28, 2013 DC10-53-182 6 of 26 BOEING SERVICE BULLETIN DC10-53-182
Commercial Airplanes DC10 Service Bulletin Number: DC10-53-182 Original Issue: June 28, 2013 ATA System: 5300 SUBJECT: FUSELAGE - Fuselage - Inspect/Change Left and Right Forward Cargo Compartment Frame to Cargo Liner Attachment Holes
1. PLANNING INFORMATION A. Effectivity
1. Airplanes
DESCRIPTIONCONFIGURATIONGROUP Airplanes with regular size forward cargo door.-1 Airplanes with oversize forward cargo door.-2 Airplane Models:
DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-10F, MD-10-30F GroupFuselage Number 11 12 13 14 15 16 17 18 19 110 111 112 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 28, 2013 DC10-53-182 7 of 26
GroupFuselage Number 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 228 129 130 131 132 133 234 135 236 137 138 139 240 241 142 243 244 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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GroupFuselage Number 145 246 147 148 149 150 151 152 253 154 155 156 257 158 159 260 161 162 263 164 165 266 167 168 269 170 271 172 273 174 275 176 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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GroupFuselage Number 277 178 279 180 181 282 183 284 285 186 287 288 189 290 291 292 293 294 195 196 297 298 299 2100 - 102 1103
2. Spares Affected None.
B. Concurrent Requirements None.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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C. Reason Federal Aviation Administration (FAA) requirement 14 Code of Federal Regulations (CFR) Part 26.21, Amendment 26-6 with effective date May 24/2012, requires the establishment of a binding schedule for the release of new service actions (Service Bulletins) to support Widespread Fatigue Damage (WFD) rules Limit of Validity (LOV) from current regulatory limits, refer to 14 CFR Part 121.1115. To extend the LOV for airplanes in Paragraph 1.A.1, Effectivity, beyond the FAA published dates in Table 1 of 14 CFR Part 121.1115, new service actions have been identified. Inspecting and changing the frame fastener holes in the forward cargo compartment will extend the LOV. If the inspection and modification is not completed, there may be undetected cracks in the fastener holes which could result in the loss of fail safe structural integrity.
The left and right forward cargo compartment frames have been determined to be structure that is susceptible to Widespread Fatigue Damage (WFD).
D. Description This service bulletin provides instructions to do as follows:
1. Remove fasteners in the left and right hand sides of the forward cargo compartment.
2. Do an Eddy Current High Frequency (ETHF) inspection of the open fastener holes for cracks.
Based on inspection findings do what follows:
Condition 1 - No Crack Detected
a. Install Hi-Loks.
Condition 2 - Crack Detected in Any Hole
a. Contact Boeing to get instructions for the repair for this service bulletin, and do the work instructed by Boeing.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones ZoneModel 125, 126DC-10-10, DC-10-10F, DC-10- 30F, MD-10-10F, MD-10-30F Group 2:
Affected Maintenance Zones ZoneModel 125, 126DC-10-10, DC-10-10F, DC-10- 30, DC-10-40 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.
Table 1: High Frequency Eddy Current Inspection for Cracks in Fuselage Frame Holes Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 72 months after the original issue date of this service bulletin.
Before 30,000 total flight cycles.
Do an Eddy Current High Frequency (ETHF) inspection of left and right forward cargo compartment frame to cargo liner attachment holes for cracks and do the work of the applicable condition that follows.
All Airplanes --Before further flight.
Install Hi-Loks.Condition 1 - No Crack Detected.
--Before further flight.
Contact Boeing to get instructions for the repair for this service bulletin and do the work instructed by Boeing.
Condition 2 - Crack Detected in Any Hole.
F. Approval For DC-10 Series Airplanes:
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin.
For MD-10 Series Airplanes:
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved. 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.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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