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Table 2 - Fitting Repair (At One Location) Elapsed HoursTask HoursNumber of PersonsTask
(a) Total time required may vary depending upon conditions found during inspections.
H. Weight and Balance Changes None.
I. Electrical Load Data Not applicable.
J. References
1. Existing Data:
a. Boeing Nondestructive Test Manual, 707/720 Airplanes, Part 4, 57-40-07, Figure 1 and Part 6, 51-00-00, Figures 4, 11, 16, 19, 20, 23 and 24
b. Service Bulletin 707-1798, "Nacelle Strut Upper Support Fitting Inspection and Bracket Modification"
c. Service Bulletin 707-2090, "Nacelle Strut Upper Support Fitting Replacement"
d. Service Bulletin 707-3173, "Inboard Nacelle Strut Overwing Support Fitting Modification"
e. Service Bulletin 707A3183, "Inboard Nacelle Strut Midspar Fitting Inspection and Replacement"
f. Service Bulletin 707-3478, "Master Service Bulletin"
g. Service Bulletin 707-3479, "Master Service Bulletin"
h. Service Bulletin 707-3480, "Master Service Bulletin"
i. Service Bulletin 707A3364, "Nacelle Strut Diagonal Brace End Fitting Inspection and Modification"
j. Service Bulletin 707A3514, "NACELLES - Nacelle Strut - Front Spar Fitting - Inspection and Replacement"
k. 707 Aircraft Maintenance Manual (AMM) 12-2-0, 28-0, 71-5-0
l. 707-120 Structural Repair Manual (SRM) 51-2-5, 51-2-10, 51-2-11, 707-320 SRM 51-2-5, 51-2-10, 51-2-11 or 720 SRM 51-2-5, 51-2-10, 51-2-11
m. Standard Overhaul Practices Manual (SOPM) 20-50-01, 20-43-03
n. Boeing Service Letter 707-SL-51-029 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 17, 1979 A3365Revision 3: March 09, 2017 25 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
o. Boeing Service Related Problem (SRP) 707-54-0155
p. 707 Fleet Team Digest (FTD) 54-05001
2. Data Supplied with this Service Bulletin:
None.
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.
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: August 17, 1979 A3365Revision 3: March 09, 2017 26 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
2. MATERIAL INFORMATION A. Material - Price and Availability None.
B. Industry Support Information Boeing warranty remedies are not available for the inspection and repair or replacement given in this service bulletin.
C. Parts Necessary for Each Airplane
1. Kits/Parts None.
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)Bolt1BACB30US()P()
(a) (b)Bolt4BACB30MB()A()
(a) (b)Bolt2BACB30NF()-()
(a) (b)Bolt2BACB30FM()A()
(a) (b)Bolt2BACB30FN()A()
(a) (b)Nut1BACN10HR()
(a) (b)Nut2BACN10JC()CD
(a) (b)Collar4BACC30X()
(a) (b)Collar2BACC30M()
(b)Washer (Plain or Countersink)8BACW10BP()
(c) (b) (d)Primer8 ozBMS 10-11, Type I
(e) (f)Chemical Conversion Coating8 ozType 2, Class A
(a) Refer to 707 Structural Repair Manual Chapter 51 for alternate fasteners.
(b) QTY for each overwing support fitting.
(c) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 17, 1979 A3365Revision 3: March 09, 2017 27 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
NotesNameQTYPart Number / Specification
(d) 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.
(e) 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 the material after September 2017 and that users of this material comply with the risk mitigation measures and operational conditions.
(f) Refer to SOPM 20-43-03 for a list of materials and supplier data.
3. Parts Modified and Reidentified None.
4. Parts Removed and Not Replaced None.
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: August 17, 1979 A3365Revision 3: March 09, 2017 28 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: 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.
NOTE: 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 Structural Repair Manual, Chapter 51.
— Values for engine maintenance tasks are included in Chapter 70 of 707 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: August 17, 1979 A3365Revision 3: March 09, 2017 29 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
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. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200.
12. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS are in Paragraph 1.E., Compliance.
B. WORK INSTRUCTIONS CAUTION: BEFORE REMOVAL OF ANY FASTENER ON THE OVERWING SUPPORT FITTING,
SUPPORT THE WEIGHT OF THE ENGINE TO PREVENT POSSIBLE DAMAGE TO THE STRUT STRUCTURE OR ENGINE. REFER TO 707 AIRCRAFT MAINTENANCE MANUAL SUBJECT 71-5-0 AS AN ACCEPTED PROCEDURE.
1. At the inboard and outboard nacelle struts, remove the overwing support fitting fairings and strut-to-wing fairings per operator's standard procedures (Ref. 707 Aircraft Maintenance Manual Subject 12-2-0) as required to gain access to the overwing support fitting-to-wing front spar upper chord attachments. See FIGURE 1.
2. Inspect the four overwing support fittings in accordance with FIGURE 1 for any crack at the attachment fasteners. Repeat the inspections at the times specified in Paragraph 1.E., Compliance.
If no crack is found, reinstall the fairings.
3. For any holes in the overwing support fitting with no crack, there is an option for those holes to be low interference cold worked to extend fatigue life in accordance with FIGURE 2.
4. For any repairs that require the removal of fasteners common to the skin or chord, defuel and purge the wing tanks per operator's standard procedures (Ref. 707 Aircraft Maintenance Manual Subject 28-0) and contact The Boeing Company for repair instructions, and do the repair,or replace the cracked part.
5. If cracked overwing support fitting cannot be repaired, replace fitting in accordance with Service Bulletin 707-3173.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 17, 1979 A3365Revision 3: March 09, 2017 30 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
6. Upon completion of cracked part repair or replacement, refuel the wing tanks and check for leaks.
Refer to 707 Aircraft Maintenance Manual Subject 28-0 as an accepted procedure.
7. Put the airplane back to serviceable condition.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 17, 1979 A3365Revision 3: March 09, 2017 31 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
BOEING SERVICE BULLETIN A3365
ALERT ALERT
STRUT-TO-WING FAIRING OVERWING FITTING
FAIRING
INBOARD AND OUTBOARD
NACELLE STRUT WING
1)3)
WING FRONT SPAR UPPER CHORD 2540172 FIGURE 1: OVERWING SUPPORT FITTING INSPECTION (SHEET 1 OF 3) Original Issue: August 17, 1979 Revision 3 March 09, 2017 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished A3365 Work - See page 1 for details. 32 of 37
1. Accomplish a detailed inspection of the upper surface of the overwing support fitting for any crack propagating from the bolt hole immediately forward of the wing front spar upper chord and from the four fastener holes common to the fitting and the chord. At the forward bolt, also inspect the radius between the lower flange and the central portion of the fitting for any crack propagating from the lower edge of the hole.
2. Do a magnetic inspection of the overwing support fitting to find if the material is aluminum or steel. At the forward bolt hole, inspect the fitting upper surface around the bolt and the flange radius with a surface High Frequency Eddy Current (HFEC) in accordance with Boeing Nondestructive Test Manual 707/720 Airplanes, Part 6, Subject 51-00-00, Figure 4 or 23 for aluminum fittings, or Figure 24 for steel fittings; or remove the bolt and inspect hole with an open hole HFEC inspection in accordance Boeing Nondestructive Test Manual 707/720 Airplanes, Part 6, Subject 51-00-00, Figure 11 or 16 for aluminum fittings, or Figure 19 for steel fittings.
NOTE: Holes bushed as a result of crack removal by oversizing require removal of the support bracket for bushing removal and hole probe inspection. Bracket removal requires wing tank entry.
FIGURE 1: OVERWING SUPPORT FITTING INSPECTION (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 17, 1979 A3365Revision 3 March 09, 2017 33 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
3. At the four holes attaching the overwing support fitting to the spar chord, do an ultrasonic inspection of the fitting holes for aluminum overwing support fittings only in accordance with Boeing Nondestructive Test Manual 707/720 Airplanes, Part 4, Subject 57-40-07, Figure 1. Or inspect the upper surface with a surface HFEC inspection in accordance withBoeing Nondestructive Test Manual 707/720 Airplanes, Part 6, Subject 51-00-00, Figure 4 or 23 for aluminum fittings, or Figure 24 for steel fittings. The upper surface HFEC inspection must be done for steel fittings.
4. If no crack is found and the bolt forward of the spar chord has been removed for inspection, reinstall bolt with wet primer and torque as follows:
Torque (Inch-Pounds) Bolt Diameter (Inches) 220 to 3603/8 370 to 6107/16 630 to 9501/2
5. If any crack is found visually, by surface HFEC inspection or ultrasonically, remove the fastener nearest to the crack and do an open hole HFEC inspection. If no other crack is found after doing an open hole HFEC inspection at the hole nearest to the crack, do the next step. If any crack is found during an open hole HFEC inspection in any of the five holes in the overwing support fitting, remove the remaining overwing support fitting fasteners in the initial inspection area, and the fasteners attaching the fitting support bracket to the forward face of the upper chord vertical flange. Do a magnetic inspection of the support bracket, front spar upper chord and wing skin to find if the material is aluminum or steel. Do an open hole HFEC inspection of the fitting, wing skin, chord and bracket holes for any crack in accordance with Boeing Nondestructive Test Manual 707/720 Airplanes, Part 6, Subject 51-00-00 Figure 11 or 16 for each aluminum part, or Figure 19 for each steel part. If no other crack is found after doing the open hole HFEC inspection at the remaining holes in the overwing support fitting, wing skin, chord and support bracket, do the next step.
6. If any crack is found in the overwing support fitting, support bracket, the wing skin or the spar chord, contact The Boeing Company for repair instructions and do the repair, or replace the part.
FIGURE 1: OVERWING SUPPORT FITTING INSPECTION (SHEET 3 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 17, 1979 A3365Revision 3 March 09, 2017 34 of 37 BOEING SERVICE BULLETIN A3365
ALERTALERT
BOEING SERVICE BULLETIN А3365
ALERT ALERT
FRONT SPAR UPPER
CHORD HORIZONTAL FLANGE
OVERWING
SUPPORT
FITTING WING UPPER
SUPPORT BRACKET SKIN + + + FWD WING FRONT SPAR
FITTING WING UPPER
FITTING SKIN
A-A WING FRONT SPAR UPPER CHORD B-B BRACKET 2540223 _ FIGURE 2: OVERWING SUPPORT FITTING REPLACEMENT FASTENERS AND OPTIONAL COLD WORK (SHEET 1 OF 3) Original Issue: August 17, 1979 Revision 3 March 09, 2017 PROPRIETARY - Copyright ® Unpublished Export Controlled ECCN: 9E991 - BOEING A3365 Work - See page 1 for details. 35 01 37
1. At the bolt hole forward of the upper chord, if no crack is found, an optional low interference cold working of the hole to a maximum of 5/8 inch diameter is permitted in accordance with 707-120 SRM 51-2-11, 707-320 SRM 51-2-11 or 720 SRM 51-2-11 for bolts if overwing support fitting is aluminum. Apply chemical conversion coating, Type 2, Class A to hole if reamed after optional low interference cold working. Refer to SOPM 20-43-03 as an accepted procedure.
NOTE: Airplanes changed by the initial release of Service Bulletin 707-3365 must contact Boeing for instructions.
2. Install support bracket and install overwing fitting-to-bracket bolt with wet primer. See Table 1 for replacement bolts. Torque fitting-to-bracket bolt as follows:
NOTE: Do not make a change to the fasteners that are in both the spar and the overwing fitting if they were changed by Service Bulletin 707-3422.
Torque (Inch-Pounds) Bolt Diameter (Inches) 370 to 6107/16 630 to 9501/2 1000 to 13009/16
3. At an overwing support fitting-to-chord fastener hole, if no crack is found, an optional low interference cold working of the hole to a maximum of 15/32 inch diameter is permitted in accordance with 707-120 SRM 51-2-11, 707-320 SRM 51-2-11 or 720 SRM 51-2-11 for Hi-Loks if overwing support fitting is aluminum. Apply chemical conversion coating, Type 2, Class A to hole if reamed after optional low interference cold working. Refer to SOPM 20-43-03 as an accepted procedure.
NOTE: Airplanes changed by the initial release of Service Bulletin 707-3365 must contact Boeing for instructions.
4. Install fastener with wet primer and restore tank sealant per operator's standard procedure. See Table 1 for replacement bolts. Select appropriate diameters and lengths to suit airplane configuration.
NOTE: Do not make a change to the fasteners that are in both the spar and the overwing fitting if they were changed by Service Bulletin 707-3422.
TABLE 1 - Replacement Bolts ReplacementLocation BACB30US()P()BoltHole forward of front spar upper chord.
BACN10HR()Nut BACW10BP (Plain or csk)Washer FIGURE 2: OVERWING SUPPORT FITTING REPLACEMENT FASTENERS AND OPTIONAL COLD WORK (SHEET 2 OF 3) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 17, 1979 A3365Revision 3 March 09, 2017 36 of 37 BOEING SERVICE BULLETIN A3365