# Boeing Service Bulletin A3364: SB-707-00A3364-04-- - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2018-0504; AD 2018-19-32 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Service Bulletin A3364](https://openairdocs.org/service-documents/boeing/a3364.md) - Title as filed: SB-707-00A3364-04-- - Pages: 57 - PDF: https://openairdocs.org/files/sha256/ce/b8/ceb89d08ee66a3f79d5e209c1980d4fed872b639f5f5ab2e8499efdd2438a893 - Page: https://openairdocs.org/service-documents/boeing/a3364/file/ceb89d08ee66 ## Text Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Commercial Airplanes 707 Service Bulletin ALERT Number: A3364 Original Issue: June 29, 1979 Revision 4: February 21, 2017 ATA System: 5401 SUBJECT: NACELLE STRUT DIAGONAL BRACE END FITTING INSPECTION AND 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 © 1989 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 Unpublished Work.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 29, 1979 A3364Revision 4: February 21, 2017 1 of 57 4.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 2 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19 E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 26 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 40 3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 41 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 FIGURE 1: DETAILED INSPECTION OF FITTINGS AND DIAGONAL BRACE TUBE . . . . . . . . . 46 FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND ALTERNATIVE DYE PENETRANT INSPECTION OF DIAGONAL BRACE TUBE, FITTINGS AND MODIFICATION . . . . . . 48 FIGURE 3: FITTING AND DIAGONAL BRACE TUBE REPLACEMENT . . . . . . . . . . . . . . . . . 52 APPENDIX A: PART DEMAND INTENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 3 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 4 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT BLANK PAGE ### Page 5 Commercial Airplanes 707 Service Bulletin ALERT Revision Transmittal SheetNumber: A3364Original Issue: June 29, 1979 Revision 4: February 21, 2017 ATA System: 5401 SUBJECT: NACELLE STRUT DIAGONAL BRACE END FITTING INSPECTION AND MODIFICATION This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Airworthiness Directive AD 82-24-03 is related to this service bulletin. The Federal Aviation Administration (FAA) will possibly release an additional Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Effects of this Revision on airplanes on which Original Issue, Revision 1, Revision 2 or Revision 3 was previously done: ActionConditionGroup Do a detailed inspection of the for- ward mating fitting, aft mating fitting, diagonal brace end fittings and diag- onal brace tube. Compliance times have been changed. All AirplanesAll Do a surface High Frequency Eddy Current (HFEC) inspection of the forward mating fitting, aft mating fit- ting and diagonal brace end fittings. Compliance times have been changed. Do an open hole HFEC inspection of the forward mating fitting, aft mating fitting, diagonal brace end fittings and diagonal brace tube. Compliance times have been changed. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 5 of 57 ### Page 6 REASON FOR REVISION This revision is sent to change the inspection interval for all HFEC and alternative dye penetrant inspections, and to add detailed inspections of the diagonal brace tube around the fasteners at each diagonal brace end fitting for any crack and open hole HFEC inspections of the diagonal brace tube end fitting fastener holes. The option of shot peening parts has been removed from this service bulletin. The open hole HFEC inspection of the forward mating fitting lugs has been added. The surface HFEC inspection of the aft mating (drag) fitting lugs has been added. The data given in Notice of Status Change 707 A3364NSC1, A3364NSC2 and A3364NSC3 is included in this revision. Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph 3.A., General Information - Notes. These sections were changed: 1. Added Summary, Concurrent Requirements. 2. In Summary, Background, revised paragraph, added references to Service Related Problem (SRP) and Fleet Team Digest (FTD). 3. In Summary, Action, revised paragraph. 4. In Summary, Effectivity, revised paragraph. 5. Added Summary, Compliance. 6. Added Summary, Industry Support Information. 7. In Summary, Manpower, revised paragraph. 8. In Summary, Material Information, revised paragraph. 9. In Summary, revised summary illustration. 10. In Paragraph 1.A.1., Airplanes, updated effectivity format, removed airplane variable numbers 00003, 00102, 00114, 00154-00156, 00450, 00451, 00602, 05828 and 05829, from the service bulletin effectivity. 11. Added Paragraph 1.B., Concurrent Requirements. 12. In Paragraph 1.C., Reason, revised paragraph, added references to SRP and FTD, added reason for revision. 13. In Paragraph 1.D., Description, revised paragraph, added effects of this revision and added tables for affected maintenance zones. 14. Added Paragraph 1.E., Compliance. 15. In Paragraph 1.F., Approval, revised and added paragraph, added Alternative Method of Compliance (AMOC) statement. 16. In Paragraph 1.G., Manpower, revised paragraph and tables. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 6 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 7 17. In Paragraph 1.H., Weight and Balance Changes, revised table. 18. Added Paragraph 1.I., Electrical Load Data. 19. In Paragraph 1.J.1., Existing Data, updated the list of references. 20. Added Paragraph 1.J.3., Installation Drawings Used in the Preparation of this Service Bulletin. 21. Added Paragraph 1.K.2., Damage Tolerance Based Structural Inspections. 22. Added Paragraph 1.L., Interchangeability and Intermixability of Parts. 23. Added Paragraph 1.M., Software Accomplishment Summary. 24. In Paragraph 2.A., Material - Price and Availability, revised the paragraph, updated kit/part table. 25. Added Paragraph 2.B., Industry Support Information. 26. In Paragraph 2.C.1., Parts Necessary for Each Airplane, added paragraph, added note, corrected part number. 27. In Paragraph 2.C.2., Parts and Materials Supplied by the Operator, added paragraph, added table. 28. Added Paragraph 2.C.3., Parts Modified and Reidentified. 29. Added Paragraph 2.C.4., Parts Removed and Not Replaced. 30. In Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin, revised paragraph. 31. Added Paragraph 3.A., General Information. 32. In Paragraph 3.B., Work Instructions, revised work instructions. 33. In Figures 1 thru 3, revised circle note numbers, revised steps. 34. Added Appendix A, Part Demand Intent survey. 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 June 29, 1979Original Issue: November 30, 1979Revision 1: December 20, 1979Revision 2: May 29, 1981Revision 3: February 21, 2017Revision 4: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 7 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 8 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT BLANK PAGE ### Page 9 Commercial Airplanes 707 Service Bulletin ALERT SummaryNumber: A3364Original Issue: June 29, 1979 Revision 4: February 21, 2017 ATA System: 5401 SUBJECT: NACELLE STRUT DIAGONAL BRACE END FITTING INSPECTION AND MODIFICATION THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND As of the Revision 3 date of this service bulletin, 29 operators have reported 66 cracked diagonal brace end fittings, 45 cracked forward mating fittings and 9 cracked aft mating fittings on airplanes with 23,200 to 63,200 flight-hours (8,300 to 34,200 flights). Cracking is attributed to fatigue in the end fittings and stress corrosion or fatigue in the mating fittings. The inboard and outboard nacelle struts are also supported by the more critical midspar fittings which are inspected/replaced in service bulletin 707A3183 Revision 6. Service Bulletin 707A3183 Revision 6 has been created to address the fracture of the midspar fitting that resulted in the separation of the inboard strut and engine from the airplane. Service Bulletin 707A3183 Revision 6 has new detailed inspections and High Frequency Eddy Current (HFEC) inspections. Existing service and regulatory actions for other nacelle strut fittings are insufficient to ensure timely detection of cracking which could lead to separation of an engine. As a result, Service Bulletin 707A3364 Revision 4 has been created to align the HFEC inspection intervals of the diagonal brace tube, end fittings, and mating fittings with those for the midspar fittings. Subsequent to release of Revision 3 of this service bulletin, an operator had reported complete separation of the body of an outboard nacelle strut diagonal brace forward end fitting as a result of a crack which ran circumferentially around the forward row of fastener holes. The airplane had accumulated 43,773 flight-hours and 14,735 flights. The fitting had previously been detail inspected in accordance with this service bulletin, but the cracking was not detected until the brace was removed during major overhaul. Boeing Service Related Problem (SRP) 707-SRP-54-0155 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 707 FTD 54-05001 is related to this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 9 of 57 ### Page 10 ACTION Do detailed inspections and HFEC inspections of the nacelle strut diagonal brace end fittings, diagonal brace tube, forward mating fitting and aft mating fitting (or alternative dye penetrant inspection of vertical webs on aft mating fitting), and repeat the inspections at the intervals specified in Paragraph 1.E., Compliance. If any crack is found in the nacelle strut diagonal brace end fittings, diagonal brace tube, forward mating fitting or aft mating fitting, do the repair in accordance with this service bulletin. If any crack cannot be repaired in accordance with this service bulletin, replace the cracked part in accordance with this service bulletin, or contact The Boeing Company for repair instructions and do the repair. Parts oversized beyond the limits specified in this service bulletin must be replaced. Modified or replaced parts must continue the repeat inspections. EFFECTIVITY All 707 and 720 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive AD 82-24-03 is related to this service bulletin. The effective date of AD 82-24-03 is November 23, 1982. The Federal Aviation Administration (FAA) will possibly release an additional 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 configuration changes, inspection, and/or repair procedures given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Operator Supplied Parts/Materials. Refer to Paragraph 2.A., Material - Price and Availability. Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 10 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 11 (OCR) ALERT Original Issue: June 29, 1979 Revision 4: February 21, 2017 BOEING SERVICE BULLETIN A3364 ALERT DO DETAILED INSPECTIONS AND HFEC INSPECTIONS OF END FITTINGS, MATING FITTINGS (OR ALTERNATIVE DYE PENETRANT INSPECTION OF VERTICAL WEBS ON AFT MATING FITTING) AND DIAGONAL BRACE TUBE FOR ANY CRACK INBOARD AND OUTBOARD NACELLE STRUT DIAGONAL BRACE Export Controlled ECCN: 9E991 - BOEING A3364 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 57 ### Page 12 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 12 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT BLANK PAGE ### Page 13 Commercial Airplanes 707 Service Bulletin ALERT Number: A3364 Original Issue: June 29, 1979 Revision 4: February 21, 2017 ATA System: 5401 SUBJECT: NACELLE STRUT DIAGONAL BRACE END FITTING INSPECTION AND MODIFICATION THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is applicable to all 707 and 720 Airplanes, in 7 Groups. The Variable Numbers and Group Information for the applicable airplanes is given below. Refer to Service Bulletin Index D6-1647 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP All 707-100B LONG BODY, 707-100B SHORT BODY Airplanes.-1 All 707-100 LONG BODY Airplanes.-2 All 707-200, 707-300 Airplanes.-3 All 707-400 Airplanes.-4 All 707-300B, 707-300C Airplanes.-5 All 720 Airplanes.-6 All 720B Airplanes.-7 Airplane Models: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 13 of 57 ### Page 14 707-100 LONG BODY, 707-100B LONG BODY, 707-100B SHORT BODY, 707-200, 707-300, 707-300B, 707-300C, 707-400, 720, 720B GroupVariable Number 6B0001 - B0029 7B0101 - B0125 6B0201 - B0203 6B0301 - B0306 6B0401 - B0402 6B0501 - B0515 7B2001 - B2008 7B2091 - B2092 7B2101 - B2116 7B2191 - B2194 7B2199 7B2201 - B2227 7B2401 - B2403 7B2501 - B2502 7B2551 - B2553 7B2601 - B2608 100001 - 00002 100004 - 00006 100101 100103 - 00113 100115 - 00153 300201 - 00205 200301 - 00305 200401 - 00415 100416 - 00449 100471 - 00475 100501 - 00513 100601 100701 - 00703 302001 - 02020 302101 - 02121 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 14 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 15 GroupVariable Number 302201 - 02207 302301 - 02303 302401 - 02418 404001 - 04005 404020 - 04022 404101 - 04106 404201 - 04218 404271 - 04272 404301 - 04303 505001 - 05060 505101 - 05138 505201 - 05208 505301 - 05312 505401 505601 - 05605 505631 - 05635 505701 - 05703 505801 - 05802 505821 - 05827 505831 - 05833 505851 - 05854 505891 - 05892 505921 - 05923 505941 - 05942 505961 - 05970 506001 - 06002 506101 506401 - 06404 506451 506461 507001 - 07017 507041 - 07059 507071 - 07081 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 15 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 16 GroupVariable Number 507101 - 07109 507181 507191 507201 - 07215 507251 - 07271 507401 - 07407 507451 - 07458 507501 - 07504 507601 - 07626 507661 - 07662 507681 - 07684 507701 - 07702 507801 - 07821 507901 - 07907 508001 - 08008 508021 508051 - 08056 508071 - 08077 508101 - 08104 508121 - 08129 508141 - 08144 508151 - 08153 508171 - 08173 508191 - 08192 508201 - 08210 508221 - 08224 508241 - 08244 508251 508261 508271 508301 - 08320 508324 - 08330 508333 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 16 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 17 GroupVariable Number 508401 - 08410 508451 - 08452 508471 - 08475 508501 - 08502 508551 - 08553 508581 - 08582 509001 - 09006 509101 - 09107 509161 - 09167 509201 - 09204 509221 - 09223 509227 509231 - 09232 509251 509271 509281 509286 - 09290 509411 509421 509438 509441 2. Spares Affected None. B. Concurrent Requirements None. C. Reason Inspection of the inboard and outboard nacelle strut diagonal brace tube, diagonal brace end fittings and mating fittings may detect cracks that could reduce the effectiveness of the four point attachment of the strut to the wing and lead to an engine separation. The original telegraphic issue of this bulletin followed reports of cracks in 6 end fittings in the outboard nacelle strut diagonal braces, in 34 forward mating fittings on the nacelle struts, and in 4 aft mating fittings on the lower surface of the wing. The affected airplanes had accumulated from 23,200 to 59,400 flight hours and 8,400 to 17,800 flights. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 17 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 18 The diagonal brace end fitting cracks initiated in the fastener holes nearest the end of the brace tube and propagated into the exposed portion of the fitting at the root of the fitting lugs. Cracking is attributed to fatigue. The forward mating fitting cracks initiated in the lug holes and propagated directly aft to the edge of the lug. Cracking is attributed to stress corrosion. The aft mating fitting cracks were in the vertical web forward and aft of the fitting lug and are attributed to stress corrosion and fatigue. The original issue of the bulletin advised a one-time detailed inspection for cracks in the exposed surface of the brace end fittings, the forward mating fitting on the nacelle strut and the aft mating fitting on the wing lower surface. Revision 1 formalized the original telegraphic issue of the bulletin, advised repeat inspections of the affected fittings and provided crack removal, modification and fitting replacement instructions. The repeat inspections of the two mating fittings could be accomplished by doing a detailed or High Frequency Eddy Current (HFEC) or alternative dye penetrant inspection. The brace end fittings could be detail inspected, by low frequency eddy current (LFEC) inspection without removing the fitting attach fasteners, or by HFEC inspection with the fasteners removed. Modifying the brace end fittings and the mating fittings provided a flight inspection-free period. Telegraphic Revision 2 of the bulletin clarified the time at which repeat inspections should commence. As of the Revision 3 date of this service bulletin, 29 operators have reported 66 cracked diagonal brace end fittings, 45 cracked forward mating fittings and 9 cracked aft mating fittings on airplanes with 23,200 to 63,200 flight-hours (8,300 to 34,200 flights). In two later reports, the cracks in the diagonal brace end fittings initiated and propagated immediately inside the end of the brace tube before emerging into the exposed portion of the fitting. Such cracks can only be detected when they emerge, or with an open hole HFEC inspection through the hole between the fitting lugs, or when the fitting is removed from the tube. In another report on the aft mating fitting on the wing lower surface, the lower half of the lug separated from the fitting on an airplane with 49,400 flight-hours and 15,950 flights. The crack initiated in the bore of the lug hole and propagated as a result of fatigue and stress corrosion. Detection of such cracks would require removal of the lug hole bushing and HFEC inspection, or detailed inspection of the lug edge. Revision 3 of the bulletin was issued to change the inspection requirements, limit oversizing of the end fitting-to-tube attach holes on the outboard nacelle strut diagonal brace on specific airplanes, and provide part information and part replacement instructions. Subsequent to release of Revision 3 of this service bulletin, an operator had reported complete separation of the body of an outboard nacelle strut diagonal brace forward end fitting as a result of a crack which ran circumferentially around the forward row of fastener holes. The airplane had accumulated 43,773 flight-hours and 14,735 flights. The fitting had previously been detail inspected in accordance with this service bulletin, but the cracking was not detected until the brace was removed during major overhaul. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 18 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 19 Revision 4 is sent to change the inspection interval for all HFEC and alternative dye penetrant inspections, and to add detailed inspections of the diagonal brace tube around the fasteners at each diagonal brace end fitting for any crack and open hole HFEC inspections of the diagonal brace tube end fitting fastener holes. The option of shot peening parts has been deleted. The open hole HFEC inspection of the forward mating fitting lugs has been added. The surface HFEC inspection of the aft mating (drag) fitting lugs has been added. Repair options for the end fittings have been removed. The data given in Notice of Status Change 707 A3364NSC1, A3364NSC2 and A3364NSC3 is included in this revision. Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph 3.A., General Information - Notes. Boeing Service Related Problem (SRP) 707-SRP-54-0155 is related to this service bulletin. Boeing Fleet Team Digest (FTD) 707 FTD 54-05001 is related to this service bulletin. D. Description Do detailed inspections and HFEC inspections of the nacelle strut diagonal brace end fittings, diagonal brace tube, forward mating fitting and aft mating fitting (or alternative dye penetrant inspection of vertical webs on aft mating fitting) for any crack. Repeat detailed inspections and HFEC inspections for any crack in these areas. Repeat exterior detailed inspections consist of a detailed inspection of the exposed portion of the diagonal brace end fittings for any crack propagating from the fitting-to-tube attach fastener holes, the innermost end of the fitting, or the outer surface of the fitting where it locates just inside the tube end. If any crack is found in the end fitting, replace the end fitting. At both ends of the diagonal brace tube, do a detailed inspection for any crack propagating from the tube-to-fitting fastener holes. If any crack is found in the end of the diagonal brace tube, replace the diagonal brace tube. At the forward mating fitting on the nacelle strut, do a detailed inspection of the exposed portions of the fitting lugs, paying particular attention to the aft end of the lugs. At the aft mating fitting on the wing lower surface, do a detailed inspection of the vertical webs and the exposed portions of the lug sides and edge for any crack propagating from the lug hole. Repeat interior detailed inspection and HFEC inspection of the diagonal brace end fitting interiors, by removing the brace end coupling pins and inserting an angled surface probe through the hole between the fitting lugs. Required inspection areas are the innermost end of the fitting, around the fitting-to-tube attach fastener heads, and the inner surface for any crack propagating from the outer surface just inside the tube end. In addition to the interior inspection, remove the diagonal brace end fittings from the tube. Do a HFEC inspection of the fitting outer surface area that locates just inside the tube end, and the innermost end of the fitting. Also, do a HFEC inspection on the fastener holes for any crack in the end fitting and the diagonal brace tube. If any crack is found in the diagonal brace end fitting, replace the end fitting. If any crack is found in the diagonal brace tube, replace the diagonal brace tube. At the forward mating fitting on the nacelle strut, do a HFEC inspection and a detailed inspection of the fitting lugs for any crack. HFEC inspection requires removal of the diagonal brace-to-fitting coupling pin and surface HFEC inspection around the lug hole edges without removing the bushings. Additional inspection of the forward mating fitting lugs requires removing the lug hole bushings to do an open hole HFEC inspection of the lug holes. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 19 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 20 At the aft mating fitting on the lower surface of the wing, do a HFEC or alternative dye penetrant inspection and a detailed inspection of the vertical webs of the fitting for any crack. Do a surface HFEC inspection of the fitting lug at the sides and edges of the lugs, and then remove the lug hole bushing and do an open hole HFEC inspection, and oversizing of the hole to remove any undetectable crack. Hole size limitations allow only two such oversizings. If any crack is found in any mating fitting, except for any crack in the lug holes of the forward or aft mating fitting within repair limits, replace the fitting. Effects of this Revision on airplanes on which Original Issue, Revision 1, Revision 2 or Revision 3 was previously done: ActionConditionGroup Do a detailed inspection of the for- ward mating fitting, aft mating fitting, diagonal brace end fittings and diag- onal brace tube. Compliance times have been changed. All AirplanesAll Do a surface HFEC inspection of the forward mating fitting, aft mating fit- ting and diagonal brace end fittings. Compliance times have been changed. Do an open hole HFEC inspection of the forward mating fitting, aft mating fitting, diagonal brace end fittings and diagonal brace tube. Compliance times have been changed. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 4-55, 4-56, 4-57, 4-58707-100B LONG BODY, 707- 100B SHORT BODY Group 2: Affected Maintenance Zones ZoneModel 4-55, 4-56, 4-57, 4-58707-100 LONG BODY Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 20 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 21 Group 3: Affected Maintenance Zones ZoneModel 4-55, 4-56, 4-57, 4-58707-200, 707-300 Group 4: Affected Maintenance Zones ZoneModel 4-55, 4-56, 4-57, 4-58707-400 Group 5: Affected Maintenance Zones ZoneModel 4-55, 4-56, 4-57, 4-58707-300B, 707-300C Group 6: Affected Maintenance Zones ZoneModel 4-55, 4-56, 4-57, 4-58720 Group 7: Affected Maintenance Zones ZoneModel 4-55, 4-56, 4-57, 4-58720B E. Compliance Federal Aviation Administration (FAA) Airworthiness Directive AD 82-24-03 is related to this service bulletin. The effective date of AD 82-24-03 is November 23, 1982. 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. Accomplish paragraphs 1 thru 4, based on the applicable conditions in the paragraphs below and Tables 1 thru 4, in accordance with Paragraph 3. Accomplishment Instructions. To detect any crack in the nacelle strut diagonal brace and associated fittings accomplish the following on airplanes with nacelle strut diagonal braces and associated fittings which have accumulated 7,500 or more flight cycles: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 21 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 22 1. If an inspection was not done in accordance with this service bulletin before the Revision 4 date of this service bulletin, within 500 flight cycles after the effective date of AD 82-24-03, do a detailed inspection of the nacelle strut diagonal braces and associated fittings in accordance with Revision 4 of this service bulletin and repeat detailed inspections and HFEC inspection thereafter at the intervals specified in Tables 1, 2, 3, and 4. 2. If an inspection was done in accordance with this service bulletin before the Revision 4 date of this service bulletin, do all of the following: a. Detailed Inspection: Within 250 flight cycles after the Revision 4 date of this service bulletin, do detailed inspections of the nacelle strut diagonal brace end fittings, diagonal brace tube, forward mating fitting and aft mating fitting for any crack, and repeat the inspections at the intervals specified in Tables 1, 2, 3 and 4 below. b. HFEC or Dye Penetrant Inspections: (1) Do whichever occurs first: (a) Accomplish the inspections specified in AD 82-24-03. (b) Within 1,500 flight cycles or 48 months, after the Revision 4 date of this service bulletin, whichever occurs first, do a HFEC inspection of the nacelle strut diagonal brace end fittings, forward mating fitting and aft mating fitting (or alternative dye penetrant inspection of vertical webs on aft mating fitting) for any crack. (2) Within 1,500 flight cycles or 48 months, after the Revision 4 date of this service bulletin, whichever occurs first, do an initial HFEC inspection of the diagonal brace tube for any crack. (3) Repeat the inspections at the intervals specified in Tables 1, 2, 3 and 4 below. 3. If any crack is found in the nacelle strut diagonal brace end fittings, diagonal brace tube, forward mating fitting or aft mating fitting, except for any crack in the lug holes of the forward or aft mating fitting within repair limits, replace the cracked part in accordance with this service bulletin, or contact The Boeing Company for repair instructions and do the repair before further flight. Parts oversized beyond the limits specified in this service bulletin must be replaced before further flight. 4. For Group 3, 4, and 6 airplanes, if the outboard diagonal brace end fitting (forward or aft) attach holes have been oversized in accordance with Revision 3 of this service bulletin, replace the diagonal brace assembly within 1,000 flight cycles after the Revision 4 date of this service bulletin. Table 1: Forward Mating Fitting Repeat Intervals Not To ExceedType Inspection 250 flight cycles.Detailed inspection 1,500 flight cycles or 48 months, whichever occurs first.Surface HFEC inspection 1,500 flight cycles or 48 months, whichever occurs first.Open hole HFEC inspection Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 22 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 23 Table 2: Aft Mating Fitting Repeat Intervals Not To ExceedType Inspection 250 flight cycles.Detailed inspection 1,500 flight cycles or 48 months, whichever occurs first.Surface HFEC inspection or al- ternative dye penetrant inspec- tion of web. 1,500 flight cycles or 48 months, whichever occurs first.Surface HFEC inspection of lug and open hole HFEC inspection of lug hole with bushing re- moved then hole oversized. Table 3: Diagonal Brace End Fittings Repeat Intervals Not To ExceedType Inspection 250 flight cycles.Detailed inspection 1,500 flight cycles or 48 months, whichever occurs first.Exterior surface (with fitting re- moved) and interior surface HFEC inspection. 1,500 flight cycles or 48 months, whichever occurs first.HFEC open hole inspection (with fitting removed) with hole oversizing. Table 4: Diagonal Brace Tube Repeat Intervals Not To ExceedType Inspection 250 flight cycles.Detailed inspection 1,500 flight cycles or 48 months, whichever occurs first.Open hole HFEC inspection F. Approval 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. In addition, the Manager of the FAA Los Angeles 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 AD 82-24-03. All provisions of AD 82-24-03 that are not specifically referenced in the above statement remain fully applicable and must be complied with. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 23 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 24 G. Manpower The table below shows an estimate of the task hours necessary to do this service bulletin 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 inspect the work • Time to cure the materials • Time to make the parts • Time to find the tools Detailed Inspection Elapsed HoursTask HoursNumber of PersonsTask 3124Open Access 144Inspect 5204Close Access 936TOTAL FOR EACH AIRPLANE High Frequency Eddy Current (HFEC) Inspection and Modification Elapsed HoursTask HoursNumber of PersonsTask 8486Open Access 482Inspect 321281Change (a) 12726Close Access 24128TOTAL FOR EACH AIRPLANE (b) (a) If required. (b) Total does not include hours required for change. Additional Hours for Fitting Replacement at One Location Elapsed HoursTask HoursNumber of PersonsTask 12322 - 4Diagonal Brace Fwd End Fitting (a) 12322 - 4Diagonal Brace Aft End Fitting (a) 32902 - 4Diagonal Brace Fwd Mating Fitting (b) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 24 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 25 Additional Hours for Fitting Replacement at One Location Elapsed HoursTask HoursNumber of PersonsTask 32962 - 4Diagonal Brace Aft Mating Fitting (c) 11.5232Diagonal Brace Tube (a) (a) Hours include additional access and restoration time. (b) Hours include engine removal and reinstallation. (c) Hours include fuel tank entry and fuel leak check. Estimate does not include bushing fabrication time. H. Weight and Balance Changes Change in Basic Moment (Pound- Inches) Change in Basic Weight (Pounds) Replaced Part (a)0.8Forward Mating Fit- ting (a)0.2Brace End Fitting -NegligibleAft Mating Fitting (a)-3.9Diagonal Brace Tube (a) Depends on location of replaced part. I. Electrical Load Data Not applicable. J. References 1. Existing Data: a. Service Bulletin Index D6-1647 b. Boeing 707/720 Nondestructive Test (NDT) Manual, Part 1, 51-06-00 Figure 1, and Part 6, 51-00-00 Figures 4, 11, 16, and 23 c. Boeing Service Bulletin 707A3183, R06, "Inboard and Outboard Nacelle Strut Midspar Fitting Inspection and Replacement" d. 707 Aircraft Maintenance Manual (AMM) subject 54-1-41 e. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 82-24-03 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 25 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 26 f. Standard Overhaul Practices Manual (SOPM) 20-20-02, 20-43-03, 20-50-01 g. 707-100/200 Structural Repair Manual (SRM) 51-6-1 h. Notice of Status Change (NSC) 707 A3364NSC1, A3364NSC2 and A3364NSC3 i. Boeing Service Letter 707-SL-51-029 j. Boeing Service Related Problem (SRP) 707-SRP-54-0155 k. 707 Fleet Team Digest (FTD) 54-05001 2. Data Supplied with this Service Bulletin: a. Drawings: ADCNDCN/REVSheetTitleDrawing No --DWGSeal Instl.-Lower Spar Fitting, Inboard and Outboard Strut, Kit 65C20681 --PL --DWGFitting Inst.-Strut Lower Spar, 707-120b, - 320B, -320C and 720B, Kit 65C20682 --PL --DWGFitting Instl.-Strut Lower Spar, 707-220, - 320 and -420, Kit 65C20683 --PL --DWGFitting Instl.-Strut Lower Spar, 707-120 and 720, Kit 65C20684 --PL --DWGSupport Instl.-Aft Drag, Inboard Nacelle, Kit65C21732 --PL --DWGSupport Instl.-Aft Drag, Outboard Nacelle, Kit 65C21733 --PL 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. K. Publications Affected 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 26 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 27 L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 27 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 28 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 28 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT BLANK PAGE ### Page 29 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary for Each Airplane . Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits/parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the Revision 4 date of this Ser- vice Bulletin (US Dollars) ROLT as of the Revision 4 date of this Service Bul- letin (Calendar Days) NameKit Number --Support-Aft Drag Outboard Nacelle5-72316-3029 --Support-Aft Drag Outboard Nacelle5-72316-3030 --Support-Aft Drag Outboard Nacelle5-72316-3031 --Support-Aft Drag Outboard Nacelle5-72316-3032 --Support-Aft Drag Inboard Nacelle5-72319-3021 --Support-Aft Drag Inboard Nacelle5-72319-3022 --Support-Aft Drag Inboard Nacelle5-72319-3025 --Support-Aft Drag Inboard Nacelle5-72319-3026 --Support-Aft Drag Inboard Nacelle5-72319-3029 --Support-Aft Drag Inboard Nacelle5-72319-3030 --Fitting Assy - Lower Attachment Outboard Nacelle 5-84468-3004 --Fitting Assy - Lower Attachment Outboard Nacelle 5-84468-3008 --Fitting Assy - Lower Attachment Inboard Nacelle 5-84488-3006 --Tube-Brace, Outboard Nacelle9-61138-3000 --Fitting Assy - Lower Attachment Inboard Nacelle 65-2525-12 --Fitting-Upper, Diag. Brace. Inboard Nacelle65-2526-4 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 29 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 30 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the Revision 4 date of this Ser- vice Bulletin (US Dollars) ROLT as of the Revision 4 date of this Service Bul- letin (Calendar Days) NameKit Number --Fitting-Lower, Diag. Brace, Inboard Nacelle65-2527-3 --Fitting Assy - Lower Attachment Outboard Nacelle 65-2541-2 --Fitting Assy - Lower Attachment Inboard Nacelle 65-13348-3 --Fitting Assy - Lower Attachment Outboard Nacelle 65-13349-3 --Fitting Assy - Lower Attachment Outboard Nacelle 65-13761-2 --Fitting-Upper, Diag. Brace, Outboard Nacelle65-14295-2 --Fitting-Upper, Diag. Brace, Outboard Nacelle65-25783-3 --Fitting-Upper, Diag. Brace, Outboard Nacelle65C20447-1 --Fitting-Upper, Diag. Brace, Outboard Nacelle65C20447-3 --Fitting-Lower, Diag. Brace, Outboard Nacelle65C20449-1 --Fitting-Lower, Diag. Brace, Outboard Nacelle65C20449-3 --Fitting-Upper, Diag. Brace, Inboard Nacelle65C20451-1 --Fitting-Lower, Diag. Brace, Inboard Nacelle65C20452-1 --Fitting-Lower, Diag. Brace, Inboard Nacelle65C20452-3 --Fitting-Upper, Diag. Brace, Inboard Nacelle65C20453-1 --Fitting-Lower, Diag. Brace, Inboard Nacelle65C20454-1 --Fitting-Upper, Diag. Brace, Inboard Nacelle65C20455-1 --Fitting Assy - Lower Attachment Outboard Nacelle 65C20675-1 --Fitting Assy - Lower Attachment Outboard Nacelle 65C20675-3 --Fitting Assy - Lower Attachment Inboard Nacelle 65C20676-1 --Fitting Assy - Lower Attachment Outboard Nacelle 65C20677-1 --Fitting Assy - Lower Attachment Inboard Nacelle 65C20678-1 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 30 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 31 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the Revision 4 date of this Ser- vice Bulletin (US Dollars) ROLT as of the Revision 4 date of this Service Bul- letin (Calendar Days) NameKit Number --Fitting Assy - Lower Attachment, Outboard Nacelle 65C20679-1 --Fitting Assy - Lower Attachment, Inboard Nacelle 65C20680-1 --Fitting Assy - Lower Attachment, Inboard Nacelle 65C20680-3 --Tube-Brace, Outboard Nacelle69-2020 --Fitting Assy - Diagonal Brace, Outboard Nacelle 69-71626-1 --Fitting Assy - Diagonal Brace, Outboard Nacelle 69-71626-3 --Fitting Assy - Diagonal Brace, Outboard Nacelle 69-71626-5 --Seal Assy. - Diag. Brace, Outboard Nacelle69-71636-1 --Seal Assy. - Diag. Brace, Inboard Nacelle69-71637-1 The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each Airplane. As an alternative, operators can purchase the kits/parts from Boeing Spares. The Boeing price data shown below is given for planning purposes. Supply data can be given if requested. The kits/parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the Revision 4 date of this Ser- vice Bulletin (US Dollars) ROLT as of the Revision 4 date of this Service Bul- letin (Weeks) NameKit Number --Replacement Fastener Kit65-92050-1 --Replacement Fastener Kit65-92050-2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 31 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 32 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the Revision 4 date of this Ser- vice Bulletin (US Dollars) ROLT as of the Revision 4 date of this Service Bul- letin (Weeks) NameKit Number --Replacement Fastener Kit65-92050-3 --Replacement Fastener Kit65-92050-4 --Replacement Fastener Kit65-92050-5 --Replacement Fastener Kit65-92050-6 --Replacement Fastener Kit65-92050-7 --Replacement Fastener Kit65-92050-8 --Replacement Fastener Kit65-92050-9 --Replacement Fastener Kit65-92050-10 --Replacement Fastener Kit65-92050-11 --Replacement Fastener Kit65-92050-12 --Replacement Fastener Kit65-92050-13 --Replacement Fastener Kit65-92050-14 --Replacement Fastener Kit65-92050-15 --Replacement Fastener Kit65-92050-16 --Replacement Fastener Kit65-92050-17 --Replacement Fastener Kit65-92050-18 --Replacement Fastener Kit65-92050-19 --Replacement Fastener Kit65-92050-20 --Replacement Fastener Kit65-92050-21 --Replacement Fastener Kit65-92050-22 --Replacement Fastener Kit65-92050-23 --Replacement Fastener Kit65-92050-24 --Replacement Fastener Kit65-92050-25 --Replacement Fastener Kit65-92050-26 --Replacement Fastener Kit65-92050-27 --Replacement Fastener Kit65-92050-28 --Replacement Fastener Kit65-92050-29 --Replacement Fastener Kit65-92050-30 --Replacement Fastener Kit65-92050-31 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 32 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 33 REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION Unit Price as of the Revision 4 date of this Ser- vice Bulletin (US Dollars) ROLT as of the Revision 4 date of this Service Bul- letin (Weeks) NameKit Number --Replacement Fastener Kit65-92050-32 Operators are encouraged to complete the survey provided in APPENDIX A of this service bulletin to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts. B. Industry Support Information Boeing warranty remedies are not available for the configuration changes, inspection and/or repair procedures given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: One part for each location and the applicable fastener kits are necessary for each airplane. Outboard Nacelle Strut Diagonal Brace Parts AftForwardGroup CouplingEnd FittingEnd FittingCoupling 65-92050-2765-25783-365-13761-2 or 69- 71626-1 65-92050-281, 5 65-92050-2265C20447-165C20449-165-92050-322 65-92050-3065-25783-369-71626-565-92050-313, 4 65-92050-2265C20447-365C20449-365-92050-236 65-92050-2965-14295-269-71626-365-92050-287 Group 7 airplanes also require new seal assembly 69-71637-1 if a forward end fitting is replaced. New forward and aft end fittings, brace tubes and attach fasteners are required if the outboard nacelle strut diagonal brace end fitting-to-tube attach holes have been oversized. For Groups 3 and 4 airplanes, order tube 69-2020. For Group 6 airplanes, order tube 9-61138-3000. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 33 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 34 Inboard Nacelle Strut Diagonal Brace Parts AftForwardGroup CouplingEnd FittingEnd FittingCoupling 65-92050-2065-2526-4 or 65C20451-1 65C20452-165-92050-211, 5 65-92050-2565C20453-165C20454-165-92050-262, 6 65-92050-1965-2526-4 or 65C20451-1 65C20452-165-92050-213, 4 65-92050-2465C20455-165-2527-3 or 65C20452-3 65-92050-217 Group 7 airplanes also require new seal assembly 69-71636-1 if a forward end fitting is replaced. Nacelle Strut Diagonal Brace Mating Fittings Forward Mating Fitting in Strut Inboard StrutOutboard StrutGroup 65-13348-3 or 65C20678-165-13349-3 or 65C20679-11, 5, 7 5-84488-3006 or 65C20676-15-84468-3004 or 65C20675-32 65-2525-12 or 65C20680-165-2541-2 or 65C20677-13 65C20680-365-2541-2 or 65C20677-14 5-84488-3006 or 65C20676-15-84468-3008 or 65C20675-16 Aft Mating Fitting on Wing Inboard Strut 5-72319-( )Outboard Strut 5-72316-( )Group R.H.L.H.R.H.L.H. -3030-3029-3032-30311 thru 3, 6 -3022-3021-3032-30314, 5 -3026-3025-3030-30297 Part Replacement Fastener Kits 65-92050-( ) Diagonal Brace End Fittings and Mating Fittings Mating FittingsDiagonal Brace End FittingsGroup Inboard BraceOutboard BraceInboard BraceOutboard Brace AftFwdAftFwdAftFwdAftFwd -8-13-11-12-4-4-1-11 -8-18-11-17-5-5-2-22 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 34 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 35 Part Replacement Fastener Kits 65-92050-( ) Diagonal Brace End Fittings and Mating Fittings Mating FittingsDiagonal Brace End FittingsGroup Inboard BraceOutboard BraceInboard BraceOutboard Brace AftFwdAftFwdAftFwdAftFwd -8-15-11-14-4-4-2-23 -9-16-11-14-4-4-2-24 -9-13-11-12-4-4-1-15 -8-19-10-17-5-5-2-26 -7-13-10-12-4-6-1-37 Kit 65-92050 NotesExisting Part Number Name65-92050-( )New Part Number -6-5-4-3-2-1 QTY --Bolt-9----BACB30FM12-7 --Bolt-9----BACB30FM12-8 --Bolt9-9-9-BACB30FM12-9 --Bolt---9-9BACB30FM12-10 --Bolt9-9---BACB30FM12-11 --Bolt----9-BACB30FM12-12 --Bolt---6-6BACB30FM12-13 --Bolt---3-3BACB30FM14-13 --Bolt2--2--BACB30LJ3-2 --Collar181818151815BACC30M12 --Collar---3-3BACC30M14 --Nut2-2--BACN10JC3CM Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -12-11-10-9-8-7 QTY --Bolt2-----BACB30FM8-6 --Bolt1-----BACB30FM8-7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 35 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 36 Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -12-11-10-9-8-7 QTY --Bolt1-----BACB30FM8-8 --Bolt3-----BACB30FM8-9 --Bolt3-----BACB30FM8-10 --Bolt8-----BACB30FM10-12 --Bolt8-----BACB30FM16-17 --Bolt6-----BACB30FM16-18 --Bolt2-----BACB30FN6-5 --Bolt7-----BACB30MB6-12 --Bolt-22755BACB30MC8-6 --Bolt---111BACB30MC8-7 --Bolt-23101212BACB30MC8-8 --Bolt-67151111BACB30MC8-9 --Bolt---666BACB30MC8-10 --Bolt-820244BACB30MC8-11 --Bolt-410111715BACB30MC8-12 --Bolt-204311BACB30MC8-13 --Bolt-73122BACB30MC8-14 --Bolt----35BACB30MC8-15 --Bolt--24--BACB30MC8-16 --Bolt-2----BACB30MC8-18 --Bolt---2--BACB30MC8-20 --Collar2-----BACC30M6 --Collar10-----BACC30M8 --Collar8-----BACC30M10 --Collar14-----BACC30M16 --Collar7-----BACC30X6 --Collar-5151626262BACC30X8 --Rivet18-----BACR15BA6D7 --Rivet23-----BACR15BB6D5 --Rivet6-----BACR15BB6D8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 36 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 37 Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -12-11-10-9-8-7 QTY --Rivet8-----BACR15BB6D9 --Rivet9-----BACR15BB6D16 Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -18-17-16-15-14-13 QTY --Bolt24----BACB30FM6-2 --Bolt66--3-BACB30FM6-5 --Bolt-8--8-BACB30FM6-6 --Bolt----4-BACB30FM8-5 --Bolt642432BACB30FM8-6 --Bolt----1-BACB30FM8-7 --Bolt10666-6BACB30FM8-8 --Bolt----6-BACB30FM8-9 --Bolt-6----BACB30FM8-12 --Bolt4-666-BACB30FM10-11 --Bolt-----6BACB30FM10-14 --Bolt-----2BACB30FM10-15 --Bolt414--4-BACB30FM14-10 --Bolt--10-10-BACB30FM14-11 --Bolt---106-BACB30FM14-12 --Bolt----8-BACB30FM14-13 --Bolt-----6BACB30FM16-15 --Bolt-----4BACB30FM16-18 --Bolt52----BACB30FN6-4 --Bolt8-88-4BACB30FN6-5 --Bolt----2-BACB30FN6-6 --Bolt-----6BACB30FN6-7 --Bolt84--7-BACB30MB6-8 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 37 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 38 Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -18-17-16-15-14-13 QTY --Bolt6355-5BACB30MB6-9 --Collar1020881310BACC30M6 --Collar516810148BACC30M8 --Collar14-6668BACC30M10 --Collar-14101028-BACC30M14 --Collar-----10BACC30M16 --Collar-75575BACC30X6 --Rivet716----BACR15BA6D6 --Rivet14-16161616BACR15BA6D7 --Rivet421--24-BACR15BB6D5 --Rivet5-1212-10BACR15BB6D6 --Rivet--141416-BACR15BB6D8 --Rivet-84--12BACR15BB6D9 --Rivet--559-BACR15BB6D14 --Rivet-----5BACR15BB6D17 --Rivet-----2BACR15CE6D6 --Rivet-----2BACR15CE6D9 Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -24-23-22-21-20-19 QTY --Washer-1----60-4849-9 --Washer1---1160-6961-4 --Washer--1---60-6961-6 --Bolt----1-65-23413-12 --Bolt1-----65-23413-13 --Bolt--1---65-23413-15 --Bolt-----165-23413-18 --Bolt-1----66-21024 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 38 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 39 Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -24-23-22-21-20-19 QTY --Washer---1--AN960PD1416 --Bolt---1--BACB30LJ14-69 --Nut-1---1BACN10JC12 --Nut1--11-BACN10JC14 --Nut--1---BACN10JC17 --Washer---1--BACW10BN14AC Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( )New Part Number -30-29-28-27-26-25 QTY --Washer-----160-6961-4 --Washer11-1--60-6961-6 --Bolt1-----65-23413-16 --Bolt-----165-23413-17 --Bolt---1--65-23413-20 --Bolt-1----65-23413-21 --Washer----1-AN960PD1216 --Washer--1---AN960PD1616 --Bolt----1-BACB30LJ12-70 --Bolt--1---BACB30LJ16-91 --Nut----11BACN10JC12 --Nut-111--BACN10JC16 --Nut1-----BACN10JC17 --Washer----1-BACW10BN12AC --Washer--1---BACW10BN16AC Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 39 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 40 Kit 65-92050 - Continued NotesExisting Part Number Name65-92050-( ) New Part Number -32-31 QTY --Washer11AN960PD1416 --Bolt1-BACB30LJ14-89 --Bolt-1BACB30LJ14-92 --Nut11BACN10JC14 --Washer11BACW10BN14AC 2. Parts and Materials Supplied by the Operator The following parts or materials are necessary to do the change in this service bulletin. Parts and materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine operator part and material supply to make sure all necessary parts and materials are available. NotesNameQTYPart Number / Specification (a) (b)PRIMER8 ozBMS10-11, Type 1 (c) (d)CHEMICAL CONVERSION COAT- ING 8 ozTYPE 2, CLASS A (a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) Some types of primer contain Strontium Chromate and will not be available in the European Union (EU) after January 2019 without an authorization. EU operators are encouraged to make sure their suppliers are authorized to provide this material after January 2019 and that users of this material comply with the risk mitigation measures and operational conditions. (c) Refer to SOPM 20-43-03 for material sources. (d) Some types of Chemical Conversion Coating contain Chromium Trioxide Chromic Acid and will not be available in the European Union (EU) after September 2017 without an authorization. EU operators are encouraged to make sure their suppliers are authorized to provide this material after September 2017 and that users of this material comply with the risk mitigation measures and operational conditions. 3. Parts Modified and Reidentified None. 4. Parts Removed and Not Replaced None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 40 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 41 D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 41 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 42 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 42 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT BLANK PAGE ### Page 43 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION NOTE: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: – Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch – Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque Values: — Values for structural fasteners are given in 707/720 Structural Repair Manual, Chapter 51. — Values for airframe maintenance tasks are included in Chapter 20 of 707/720 Aircraft Maintenance Manual (AMM). — Non-standard torque values for maintenance tasks are included in the applicable installation step. 4. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51. 5. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin. 6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 43 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 44 7. These work instructions refer to procedures included in other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. 8. Boeing Service Letter 707-SL-51-029, Damage Reporting and Repair Plan/Design Guidelines, is an acceptable procedure to request information from Boeing for additional structural repair instructions. The Service Letter describes what information must be provided to Boeing before a structural repair can be provided. 9. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 10. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 11. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 12. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200. 13. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance. B. WORK INSTRUCTIONS 1. Remove the inboard and outboard nacelle strut diagonal brace fairings. Refer to operator's standard procedure to obtain access to the diagonal brace tubes, diagonal brace end fittings and mating fittings. 2. Do a detailed inspection of all affected fittings and the diagonal brace tubes in accordance with FIGURE 1. 3. If a High Frequency Eddy Current (HFEC) inspection of the diagonal brace tube or brace end fittings and HFEC or alternative dye penetrant inspection of the mating fittings are scheduled, support the weight of the airplane on jacks at wing and body Jack Points I, II, VI. Refer to 707/720 Structural Repair Manual Subject 51-6-1 as an accepted procedure. 4. With airplane stabilized on jacks, support the weight of the engine and strut to remove all load from the brace coupling pins. If engine has been removed for any reason, support the weight of the nacelle strut. Remove coupling pins and remove diagonal braces from mating fittings. 5. Do a HFEC inspection of the fittings (or alternative dye penetrant inspection of vertical webs on aft mating fittings) and do a HFEC inspection of the diagonal brace tube in accordance withFIGURE 2. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 44 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 45 6. If bushing is removed on mating fittings for an open hole HFEC inspection, do the repair of the fitting hole and bushing within the allowable limits in accordance with FIGURE 2. 7. If any crack is found, except for any crack in the lug holes of the forward or aft mating fitting within repair limits, replace the cracked fitting or diagonal brace tube in accordance with FIGURE 3. If any crack is found in the aft mating fitting on the lower surface of the wing, defuel and purge the wing tank. Refer to 707/720 Maintenance Manual Chapter 28 as an accepted procedure. If any crack is found in the forward mating fitting, remove engine. Refer to 707/720 Maintenance Manual Subject 71-5-0 as an accepted procedure. 8. After replacement of an aft mating fitting, refuel the wing tank and check for fuel leaks at the fitting. If any leak is found contact The Boeing Company for repair instructions and do the repair. After replacement of a forward mating fitting, reinstall engine and check engine systems. 9. Upon completion of inspection, repair, modification or replacement, remove supports at engine or strut, remove airplane jacks and reinstall fairings. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4: February 21, 2017 45 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 46 (OCR) BOEING SERVICE BULLETIN A3364 ALERT ALERT 5) INBOARD AND OUTBOARD NACELLE STRUT DIAGONAL BRACE TYPICAL EACH END 2538461 FIGURE 1: DETAILED INSPECTION OF FITTINGS AND DIAGONAL BRACE TUBE (SHEET 1 OF 2) Original Issue: June 29, 1979 Revision 4 February 21, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 57 ### Page 47 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. 1. Do a detailed inspection for any crack in the exposed surface of the inboard and outboard nacelle strut diagonal brace end fittings. Particular attention should be given to the surface of the fitting where it enters the tube. Use of a bright light and mirror is suggested as an aid in inspecting the less accessible areas of the fitting. 2. At both ends of the diagonal brace tube, do a detailed inspection for any crack around the fasteners attached to the end fittings. 3. If any crack is found on the diagonal brace end fittings or the diagonal brace tube, support engine as described in the general accomplishment instructions, remove coupling pins and attach fasteners and replace cracked parts in accordance with FIGURE 3. 4. At the forward mating fitting on the nacelle strut, do a detailed inspection of the exposed portions of the fitting lugs for any crack. Particular attention should be given to the central area of the aft edge of the lugs. 5. If any crack is found in the edge of a lug, support engine and remove the coupling pin. Typical cracks originate at the lug hole and propagate approximately horizontally to the edge of the lug. Replace such cracked fittings in accordance with FIGURE 3. If a different type crack is found, contact The Boeing Company for repair instructions and do the repair. 6. At the aft mating fitting on the wing lower surface, do a detailed inspection of the edge of the lug and the forward and aft vertical webs of the fitting. Use of a bright light and mirror is suggested as an aid in inspecting the less accessible area of the lug edge. Particular attention should also be given to the forward web radius where the web meets the fitting lug and to the aft web where the web angle changes or the web thickness changes. 7. If any crack is found, replace the cracked fitting in accordance with FIGURE 3. FIGURE 1: DETAILED INSPECTION OF FITTINGS AND DIAGONAL BRACE TUBE (SHEET 2 OF 2) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4 February 21, 2017 47 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 48 (OCR) BOEING SERVICE BULLETIN A3364 ALERT ALERT INBOARD AND OUTBOARD NACELLE TYPICAL EACH END STRUT DIAGONAL BRACE B-B POSSIBLE CRACK LOCATIONS END FITTING 4 INNERMOST END END FITTING OUTER SURFACE TYPICAL EACH END OUTER BRACE TUBE INNER RADIUS RADIUS A-A 2538498 FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND ALTERNATIVE DYE PENETRANTINSPECTION OF DIAGONAL BRACE TUBE, FITTINGS AND MODIFICATION (SHEET 1 OF 4) Original Issue: June 29, 1979 Revision 4 February 21, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING A3364 Work - See page 1 for details. 48 of 57 ### Page 49 (OCR) BOEING SERVICE BULLETIN A3364 ALERT ALERT EMOT 16) AFT MATING FITTING INBOARD NACELLE (16) AFT MATING FITTING OUTBOARD NACELLE (13) 15) 13 15 2538474 FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND ALTERNATIVE DYE PENETRANT INSPECTION OF DIAGONAL BRACE TUBE, FITTINGS AND MODIFICATION (SHEET 2 OF 4) Original Issue: June 29, 1979 Revision 4 February 21, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING A3364 Work - See page 1 for details. 49 of 57 ### Page 50 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. NOTE: Do surface HFEC inspection of flat and curved surfaces of fittings in accordance with 707/720 Nondestructive Test (NDT) Manual, Part 6, 51-00-00, Figures 4 or 23. Do open hole HFEC inspection of holes in the fittings or brace tube, in accordance with 707/720 NDT Manual, Part 6, 51-00-00, Figures 11 or 16. For the interior inspection of the end fittings, use a shielded right angle pencil probe in accordance with 707/720 NDT Manual Part 1, 51-06-00, Figure 1. Probe should be 7 to 8 inches long with the angled portion 1 inch long. For dye penetrant inspection of vertical webs on aft mating fitting, refer to SOPM 20-20-02 as an accepted procedure. 1. Do an interior surface HFEC inspection of the diagonal brace end fittings by inserting an angled HFEC surface probe through the hole between the lugs of the end fitting. 2. Do a surface HFEC inspection of the inner surface of fitting for any crack at the intersection of the inner radius and the inner surface, at the innermost end of the fitting, and around the heads of the fitting-to-tube attach fasteners. NOTE: Cracks in the fitting just inside the end of the tube typically occur in the inboard or outboard side in line with the lug holes. Cracks in the innermost end of the fitting typically occur at the intersections of the flat areas of the fitting interior. 3. Do an exterior surface HFEC inspection of the diagonal brace end fittings by removing the fitting-to-tube attach fasteners and removing the fitting from tube. 4. Do a surface HFEC inspection around the fitting attach holes, the outer surface of the tubular portion which nests just inside the end of the brace tube, when installed, and the inner end of the fitting. Pay particular attention to the inboard and outboard areas of the outer surface at the tube end location and to the thinner portions of the inner end of the fitting where the flat areas of the interior intersect. 5. With the fitting-to-tube attach fasteners removed, do an open hole HFEC inspection of the diagonal brace tube for any crack. 6. If any crack is found in the diagonal brace tube, replace the diagonal brace tube. 7. If any crack is found in any end fitting, replace the fitting. 8. If an inboard or outboard diagonal brace end fitting attach fastener hole on a Group 3, 4, or 6 airplane has already been oversized to 1/2 inch diameter to remove any crack, replace the brace assembly. 9. At the forward mating fitting in the nacelle strut without removing the bushings, do a surface HFEC inspection for any crack in the edges of the lug holes. If no crack is found during the HFEC inspection of the edges of the lug holes, then repeat HFEC inspections at intervals specified in Paragraph 1.E., Compliance. Another alternative for inspecting the edges of the lugs is to remove the lug hole bushings and perform open hole HFEC inspection of the forward mating fitting lug holes. If open hole HFEC inspection with bushings removed is done, oversize the hole (in accordance with Step 10), fabricate and install a replacement bushing (in accordance with Step 12). FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND ALTERNATIVE DYE PENETRANT INSPECTION OF DIAGONAL BRACE TUBE, FITTINGS AND MODIFICATION (SHEET 3 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4 February 21, 2017 50 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 51 10. If any crack indication is noted, remove the bushing and do an open hole HFEC inspection of the lug hole. If the crack can be removed by oversizing the hole by 1/16 inch diameter, oversize and reinspect to confirm crack removal. Oversizing is based on the assumption that the lug hole has not been previously oversized or the lug thickness reduced. If either has been done previously, replace the forward mating fitting or contact The Boeing Company for repair instructions and do the repair. 11. If the crack has not been removed, replace the forward mating fitting or contact The Boeing Company for repair instructions and do the repair. 12. Fabricate an aluminum-nickel-bronze bushing similar to the removed bushing, but with an outside diameter 0.0001 to 0.0017 inch larger than the lug hole. Outer and inner diameters of new bushing should be concentric within 0.01 inch T.I.R. Remove sharp edges of bushing and apply brush cadmium plating to the outside diameter and ends of the bushing. Finished outside diameter of new bushing should provide an interference fit of 0.0005 to 0.0025 inch in the lug hole. Coat inside of lug hole with wet primer and shrink fit install bushing. Line ream new bushing hole to size. 13. At the aft mating fitting on the lower surface of the wing with the bushing in the lug hole, do a surface HFEC inspection at the sides of the lug for any crack. Then remove the bushing from the lug hole and do an open hole HFEC inspection for any crack. If no crack is found, oversize hole by 1/16 inch diameter to remove any undetectable crack. If any crack is found, oversize the hole by 1/16 inch diameter, do an open hole HFEC inspection to confirm removal and oversize an additional 1/16 inch diameter to remove any undetectable crack. If the crack can not be removed, replace fitting or contact The Boeing Company for repair instructions and do the repair. NOTE: If the lug hole has already been oversized or the lug thickness reduced, during normal maintenance rework, contact The Boeing Company for repair instructions and do the repair. The original hole size should be 1.187 (inboard fitting 5-72319-) and 1.377 (outboard fitting 5-72316-) inch diameter. Original lug thickness should be 1.40 inches for inboard fittings 5-72319-3001, -3002, -3003, -3004, -3011, -3012, -3013, -3014, -3017, -3018, -3021, -3022, -3029 and -3030, and 1.72 inches for fittings 5-72319-3007, -3008, -3015, -3016, -3025 and -3026. Original lug thickness should be 1.50 inches for outboard fittings 5-72316-3007, -3008, -3017, -3018, -3021, -3022, -3031 and -3032, and 1.68 inches for fittings 5-72316-3013, -3014, -3019, -3020, -3023, -3024, -3029 and -3030. 14. Do a HFEC or alternative dye penetrant inspection of the vertical webs of the aft mating fittings for any crack at the forward web radius where the web meets the fitting lug and at the aft web where the web angle changes or the web thickness changes. If any crack is found, replace fitting. 15. Fabricate and install a new bushing in the aft mating fitting lug hole as in Step 12, except that the outer and inner diameters should be concentric within 0.003 inch T.I.R. and the interference fit should be 0.0010 to 0.0024 inch in the lug hole. Ream bushing hole to size. Apply chemical conversion coating and two coats of BMS10-11, Type 1, primer to fitting webs and lug surfaces and allow to dry one hour. 16. Repeat inspection of the aft mating fitting after modification of the aft mating fitting lug hole as specified in Paragraph 1.E., Compliance. If the basic lug hole diameter was not oversized more than 1/16 inch or the lug thickness reduced at any time, the modification may be repeated before the next repeat inspection. If the lug hole was oversized by 1/8 inch diameter as a result of any crack, or the lug thickness reduced, replace fitting. FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) AND ALTERNATIVE DYE PENETRANT INSPECTION OF DIAGONAL BRACE TUBE, FITTINGS AND MODIFICATION (SHEET 4 OF 4) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4 February 21, 2017 51 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 52 (OCR) BOEING SERVICE BULLETIN A3364 ALERT ALERT WING FRONT NACELLE SPAR STRUT DIAGONAL BRACE (2) DIMENSION Y - FAIRING 91U AFT MATING FITTING 2) DIMENSION 'X' FWD FORWARD MATING FITTING STRUT DIAGONAL BRACE (TYPICAL FOR INBOARD AND OUTBOARD NACELLE, EXCEPT AS NOTED) DIMENSION "X" Airplane Group Brace Length (Inches) All Airplane Groups Outboard 51.65 Inboard 51.05 DIMENSION "Y" Airplane Group Brace Length (Inches) 1, 5, 7 Outboard 2.63 3,4 Outboard 2.70 2, 6 Outboard 2.84 1, 3, 4, 5, 7 Inboard 2.41 2, 6 Inboard 2.51 FIGURE 3: FITTING AND DIAGONAL BRACE TUBE REPLACEMENT (SHEET 1 OF 5) Original Issue: June 29, 1979 Revision 4 February 21, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 57 A3364 ### Page 53 (OCR) BOEING SERVICE BULLETIN A3364 ALERT ALERT TORQUE NUT 800-1000 IN-LBS A BRACE END DIAGONAL BRACE 6) FITTING TUBE BRACE END FITTING TORQUE NUT 600-700 IN-LBS - B - B ) COUPLING PIN BLOCK • DRAIN HOLE A-A UP 5) SEAL ASSEMBLY B-B APPLICABLE TO THE FOREMOST AND AFTMOST ROW OF FASTENERS ON THE OUTBOARD DIAGONAL BRACE ON GROUP 1, 5, 7 AIRPLANES ONLY. (VIEW LOOKING UP) D-D D IF SEAL ASSEMBLY C-C 2538706 FIGURE 3: FITTING AND DIAGONAL BRACE TUBE REPLACEMENT (SHEET 2 OF 5) Original Issue: June 29, 1979 Revision 4 February 21, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING A3364 Work - See page 1 for details. 53 of 57 ### Page 54 (OCR) BOEING SERVICE BULLETIN A3364 ALERT ALERT FASTENER NOTES NOTE: SPOTFACING INSTRUCTIONS ARE APPLICABLE ONLY TO LATEST DESIGN END FITTINGS EARLIER DESIGN FITTINGS HAVE A FLAT INTERIOR SURFACE AT EACH HOLE LOCATION. • DRILL 0.437 (+0.005 OR -0.000) INCH DIAMETER HOLE. SPOTFACE INNER END OF HOLE 0.875 (+0.020 OR -0.000) INCH DIAMETER WITH 0.03 - 0.06 INCH RADIUS. SPOTFACE MINIMUM DEPTH (+0.02 OR -0.00 INCH) TO PROVIDE FULL FLAT SURFACE FOR UNDERSIDE OF BOLT HEAD. BOLT BACB30FM14-() (BACB30FM14A() OPTIONAL), COLLAR BACC30M14. INSTALL THREE PLACES EACH FITTING. THESE THREE FASTENERS TO BE IN END-TO-END ALIGNMENT. • DRILL 0.375 (+0.004 OR -0.000) INCH DIAMETER HOLE. SPOTFACE INNER END OF HOLE 0.750 (+0.020 OR -0.000) INCH DIAMETER WITH 0.03 - 0.06 INCH RADIUS. SPOTFACE MINIMUM DEPTH (+0.02 OR -0.00 INCH) TO PROVIDE FULL FLAT SURFACE FOR UNDERSIDE OF BOLT HEAD. BOLT BACB30FM12-() (BACB30FM12A() OPTIONAL), COLLAR BACC30M12. AT ALL END FITTING ATTACH FASTENER LOCATIONS NOT SPECIFIED PER SECTION B-B, DRILL, SPOTFACE AND INSTALL FASTENERS PER SYMBOL O • DRILL 0.218 (+0.011 OR -0.000) INCH DIAMETER HOLES IN NEW SEAL ASSEMBLIES 69-71636-1 AND 69-71637-1 TO MATCH EXISTING HOLES IN STRUCTURE. INSTALL BOLT BACB30LJ3-2 AND NUT BACN10JC3CM TWO PLACES. SEAL BOLTS AND NUTS. 2541272 The step numbers shown below agree with the numbers shown in the circle symbols in the figure. NOTE: 1. When replacing any cracked fitting, the mating fitting or diagonal brace assembly is used to locate the new fitting in place. Because of this, if more than one fitting is cracked at any one nacelle strut, complete the replacement at each location before removing and discarding the next cracked fitting. Also ensure that the supported position of the engine, or strut, does not change in relation to the stabilized position of the wing. 2. Revisions 1 and 2 of this service bulletin referred to Drawing 65C20477, supplied with Revision 1, for fitting replacement instructions. The instructions in this Figure 3 of the bulletin and on the drawings supplied with this Revision 3 of the bulletin supersede and replace the instructions in Drawing 65C20477. Fitting replacement that has already been accomplished in accordance with Drawing 65C20477 is satisfactory provided limitations specified in Revision 3 or Revision 4 of the bulletin have not been exceeded. Diagonal Brace End Fitting Replacement. 1. If both end fittings have been removed from the brace tube for inspection, reinstall the fitting which is not cracked. If both fittings are cracked, temporarily reinstall one of the cracked fittings. Retain coupling pin blocks, if installed. If forward end fitting is being replaced on a Group 7 airplane, remove and discard forward seal assembly. FIGURE 3: FITTING AND DIAGONAL BRACE TUBE REPLACEMENT (SHEET 3 OF 5) Original Issue: June 29, 1979 Revision 4 February 21, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished A3364 Work - See page 1 for details. 54 of 57 ### Page 55 2. Insert new fitting in tube and install coupling pins. Check distance between centerline of couplings and between tube end and coupling centerlines. If the strut-to-wing relationship has been maintained, distance between coupling centerlines will be as shown. 3. Drill new fitting to match holes in brace tube, spotface inner end of holes if latest design fitting is installed, and install fitting attach fasteners. Install coupling pin and install pin block if previously installed. 4. If both end fittings were cracked, remove the second fitting from the tube and install new fitting as previously described. Reinstall retained coupling pin, and pin block if previously installed. 5. If brace forward end fitting is replaced on a Group 7 airplane, install new seal assembly 69-71637-1 (outboard strut) or 69-71636-1 (inboard strut). On all affected airplanes, seal forward end of brace in accordance with Drawing 65C20681. Diagonal Brace Tube Replacement. 6. If the diagonal brace tube is replaced, the end fittings must also be replaced. Refer to AMM 54-1-41 as an accepted procedure for diagonal brace tube removal and replacement. Forward Mating Fitting Replacement. 7. Remove and retain seal assembly. See Drawing 65C20681. On Group 1, 5 and 7 airplanes, replace forward mating fitting in accordance with Drawing 65C20682. On Group 3 and 4 airplanes, replace in accordance with Drawing 65C20683. On Group 2 and 6 airplanes, replace in accordance with Drawing 65C20684. NOTE: 1. On each of the three drawings, installation of "pull" type lockbolts BACB30DX and BACB30GW is indicated at several locations. At operator's option, BACB30MB and BACB30FM hexagon drive bolts respectively may be used instead of the lockbolts. 2. At locations where the nacelle strut aft web requires cutting for fitting replacement, operators may salvage the lower portion of the cut web or fabricate a new web portion, 0.05 inch thick, and splice plate, 0.06 inch thick, from 7075-T6 clad sheet QQ-A-250/13. Apply chemical conversion coating and two coats of BMS10-11, Type I primer to the parts. Alternatively, the 65C21734-( ) parts may be obtained from Boeing. 8. Reinstall seal assembly in accordance with Drawing 65C20681 and restore sealant. Aft Mating Fitting Replacement. 9. Before removing cracked fitting, mark outline of fitting on lower surface of wing lower skin with soft marking pencil. Remove aft diagonal brace-to-fitting coupling pin and lower the aft brace clear of the fitting. Remove fitting-to-wing attach fasteners and remove and discard cracked fitting. Salvage parts specified on Drawings 65C21732 (inboard nacelle fitting) and 65C21733 (outboard nacelle fitting). 10. Attach new fitting to aft end of diagonal brace with coupling pin and position fitting against wing surface. If nacelle strut-to-wing relationship has been maintained, new fitting will locate to marked outline of removed fitting. Check for any gap between inboard and outboard side of fitting and wing surface. If necessary, shim to remove gap. FIGURE 3: FITTING AND DIAGONAL BRACE TUBE REPLACEMENT (SHEET 4 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4 February 21, 2017 55 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 56 11. With fitting held firmly against wing lower surface, drill fitting to match existing holes in structure. Remove fitting, deburr holes and complete installation of fitting in accordance with the applicable drawing. FIGURE 3: FITTING AND DIAGONAL BRACE TUBE REPLACEMENT (SHEET 5 OF 5) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: June 29, 1979 A3364Revision 4 February 21, 2017 56 of 57 BOEING SERVICE BULLETIN A3364 ALERTALERT ### Page 57 (OCR) BOEING SERVICE BULLETIN A3364 ALERT ALERT Boeing Part Demand Intent After review of this service bulletin (SB), Boeing asks that the primary engineer fill out this survey to help Boeing predict the quantity and timing of the Boeing supplied kits. Airline: Contact Name: Date: Contact E-mail: • Yes • No Have/will you recommend to your airline to accomplish this SB? • Yes • No Would issuance of an Airworthiness Directive change this decision? When would you likely be starting this SB incorporation? Month/ Year_ How many airplanes per month do you plan to accomplish? Airplane/Month How many total airplanes do you plan to complete? Total Airplanes For inspection related SBs, are you planning to replace on condition, or a fleet campaign to replace on all airplanes regardless of condition? - On Condition Campaign If you are not incorporating this SB at this time will you please help us understand the reason(s) why? Your input will help us provide better customer support. - Cost Prohibitive Continue Inspections _ Other Operator Comments: Within 45 days of the SB issue, or as soon after as possible, please scan this form and send to: sbsolutions@boeing.com Disclaimer: The data provided in this survey will be used for planning purposes only and does not constitute a commitment on any part of the airlines to purchase the parts in question, nor does it constitute 2406498 a commitment on the part of Boeing to deliver the parts in question. This survey is a projection to help Boeing forecast demand levels and timing to better support the customers schedule. APPENDIX A: PART DEMAND INTENT (SHEET 1 OF 1) Original Issue: June 29, 1979 Revision 4 February 21, 2017 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING A3364 Work - See page 1 for details. 57 of 57 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.