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Commercial Airplanes DC8 Service Bulletin Number: DC8-57-104 Original Issue: August 18, 2014 ATA System: 5710 SUBJECT: WINGS - Wing Plating Skin and Stringers - Lower Wing Skins, Stringers, and Splice Fittings at Stations Xw=+408 and Xw=-408 From Stringer 51 to Stringer 65 Inspection and Repair or Modification 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 © 2014 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Unpublished Work.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: August 18, 2014 DC8-57-104 1 of 54
3.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 18, 2014 DC8-57-104 2 of 54 BOEING SERVICE BULLETIN DC8-57-104
BLANK PAGE
Table of Contents
Summary5
1. PLANNING INFORMATION9
A. Effectivity9
1. Airplanes9
2. Spares Affected ........................................ 1 4 B. Concurrent Requirements ...................................... 1 4 C. Reason ................................................ 1 4 D. Description .............................................. 1 4 E. Compliance .............................................. 1 6 F. Approval ............................................... 1 7 G. Manpower .............................................. 1 7 H. Weight and Balance Changes .................................... 1 8 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: ........... 2 0 K. Publications Affected ........................................ 2 0 L. Interchangeability and Intermixability of Parts ........................... 2 0 M. Software Accomplishment Summary ................................ 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 1
3. Parts Modified and Reidentified: ............................... 2 4
4. Parts Removed and Not Replaced: .............................. 2 4 D. Parts Necessary to Change Spares ................................. 2 4 E. Special Tooling - Price and Availability ............................... 2 4 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 9 FIGURE 1: ETHF INSPECTION FOR CRACKS AT THE OPEN FASTENER HOLES COMMON TO LEFT WING SKIN, WING STRINGERS, AND STRINGER SPLICE FITTING AT STATION XW= 408.00 FROM STRINGER 51 TO STRINGER 65 [Group 1-3, Configuration 2] ........... 3 1 FIGURE 2: ETHF INSPECTION FOR CRACKS AT THE OPEN FASTENER HOLES COMMON TO RIGHT WING SKIN, WING STRINGERS, AND STRINGER SPLICE FITTING AT STATION XW= -408.00 FROM STRINGER 51 TO STRINGER 65 [Group 1-3, Configuration 2] ........... 3 6 FIGURE 3: ETLF INSPECTION FOR CRACKS AT THE LEFT WING AND EXTERNAL DOUBLER MODIFICATIONS OUTER PERIMETER OF FASTENERS AT STATION XW = 408.00 [Group 1-3, Configuration 2] ...................................... 4 1 FIGURE 4: ETLF INSPECTION FOR CRACKS AT THE RIGHT WING AND EXTERNAL DOUBLER MODIFICATIONS OUTER PERIMETER OF FASTENERS AT STATION XW = -408.00 [Group 1-3, Configuration 2] ...................................... 4 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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FIGURE 5: ETLF INSPECTION FOR CRACKS AT THE LEFT WING AND EXTERNAL DOUBLER MODIFICATIONS OUTER PERIMETER OF FASTENERS AT STATION XW = 408.00 [Group 1-3, Configuration 2] ...................................... 4 7 FIGURE 6: ETLF INSPECTION FOR CRACKS AT THE RIGHT WING AND EXTERNAL DOUBLER MODIFICATIONS OUTER PERIMETER OF FASTENERS AT STATION XW = -408.00 [Group 1-3, Configuration 2] ...................................... 5 1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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Commercial Airplanes DC8 Service Bulletin SummaryNumber: DC8-57-104Original Issue: August 18, 2014 ATA System: 5710 SUBJECT: WINGS - Wing Plating Skin and Stringers - Lower Wing Skins, Stringers, and Splice Fittings at Stations Xw=+408 and Xw=-408 From Stringer 51 to Stringer 65 Inspection and Repair or Modification
CONCURRENT REQUIREMENTS None.
BACKGROUND 14 Code of Federal Regulations (CFR) Part 26.21, Amendment 26-5 with effective date January 14, 2011, requires the release of new service actions (Service Bulletins) to support airplane operation up to the Widespread Fatigue Damage (WFD) regulation Limit of Validity (LOV). New service actions has been identified to support operation up to the DC-8 LOV. Inspection and modification of the lower wing skin, stringers and splice fittings in the left and right wings will support operation up to the DC-8 LOV. If the inspection and repair or modification are not completed, there may be undetected cracks in the lower skins, stringers, and/or splice fittings fastener holes which could result in the loss of fail safe structural integrity.
The left and right lower surface wing splices at XW = + 408 and XW = -408 have been determined to be structures that are susceptible to Widespread Fatigue Damage (WFD).
Boeing Fleet Team Digest (FTD) DC-8 FTD FTD-51-12001 is related to this service bulletin.
ACTION This service bulletin provides instructions to do as follows:
Group 1-3, Configuration 1:
1. Contact The Boeing Company to get instructions for the repair and do the work instructed by The Boeing Company.
Group 1-3, Configuration 2:
1. Do Eddy Current High Frequency (ETHF) inspection for cracks of the fastener open holes common to the lower skins, stringers, and splice fittings at stations Xw=408 and Xw=-408 from stringer 51 to stringer
65. Based on inspection findings do what follows:
CONDITION 1: ANY CRACK FOUND IN ANY HOLE
a. Contact The Boeing Company to get instructions for the repair and do the work instructed by The Boeing Company.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 18, 2014 DC8-57-104 5 of 54
CONDITION 2: NO CRACK FOUND IN ANY HOLE
a. Install external doublers and fasteners.
b. Do external doubler Eddy Current Low Frequency (ETLF) Inspection around fasteners. Based on inspection findings do what follows:
CONDITION 3: NO CRACK FOUND AROUND ANY EXTERNAL DOUBLER FASTENER
a. Do repeat external Eddy Current Low Frequency (ETLF) Inspection around fastener at intervals specified in Paragraph 1.E., Compliance.
CONDITION 4: ANY CRACK FOUND AROUND ANY EXTERNAL DOUBLER FASTENER
a. Contact The Boeing Company to get instructions for the repair and do the work instructed by The Boeing Company.
EFFECTIVITY DC8 Airplane(s) DC-8-55, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-71F, DC-8-72F, DC-8-73F,DC-8F-54, and DC-8F-55. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplane(s).
COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory.
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 Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN DC8-57-104
LOWER WING SKINS, STRINGERS
AND SPLICE FITTINGS AT STATIONS XW=408.000 AND Xw=-408.000 FROM STRINGER 51 TO STRINGER 65 INSPECTION AND REPAIR OR MODIFICATION 2310960 Original Issue: August 18, 2014 Export Controlled ECCN: 9E991 - BOEING DC8-57-104 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 54
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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BLANK PAGE
Commercial Airplanes DC8 Service Bulletin Number: DC8-57-104 Original Issue: August 18, 2014 ATA System: 5710 SUBJECT: WINGS - Wing Plating Skin and Stringers - Lower Wing Skins, Stringers, and Splice Fittings at Stations Xw=+408 and Xw=-408 From Stringer 51 to Stringer 65 Inspection and Repair or Modification
1. PLANNING INFORMATION A. Effectivity
1. Airplanes This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP DC-8-55, DC-8F-54, DC-8F-55, DC-8-71F-1 DC-8 Airplanes with previous structural repairs at the lower skins, stringers, and/or splice.
1 DC8- Airplanes with NO previous repairs at the lower skins, stringers, and/or splice fitting.
2 DC-8-61F-2 DC-8 Airplanes with previous structural repairs at the lower skins, stringers, and/or splice.
1 DC-8 Airplanes with NO previous repairs at the lower skins, stringers, and/or splice.
2 DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-72F, DC-8-73F-3 DC-8 Airplanes with previous structural repairs at the lower skins, stringers, and/or splice.
1 DC-8 Airplanes with NO previous repairs at the lower skins, stringers, and/or splice.
2 Airplane Models:
DC-8-55, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-71F, DC-8-72F, DC-8-73F, DC-8F-54, DC-8F-55 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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GroupFuselage Number 1122 1157 1175 1178 - 179 1180 1182 1185 1187 1189 1195 1197 1199 1200 - 201 1203 1207 - 209 1210 1215 1218 1220 1223 1225 1229 1232 1234 - 236 1238 1240 - 242 1244 1246 - 248 1250 - 256 1259 1261 - 262 1265 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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GroupFuselage Number 1267 - 269 3270 1271 - 272 1274 - 278 3279 1282 - 284 3286 2287 1288 - 289 1292 3293 1294 - 295 3298 - 299 3300 1302 3303 - 304 2305 - 306 3307 1308 3309 3311 - 312 1313 1316 - 317 3318 - 319 1320 - 321 3322 - 323 1326 3327 1328 - 329 1331 3332 - 335 1337 - 339 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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GroupFuselage Number 1340 - 343 3344 1346 3347 - 348 1350 - 351 2352 3353 1354 1356 1358 2360 3361 - 362 1363 2364 3365 - 367 1368 - 369 3370 - 371 1372 - 373 3375 - 379 3380 1381 - 382 3383 3385 - 386 1387 - 388 3389 3391 - 396 1397 - 399 1400 3401 3403 1404 1406 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
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