Commercial 

Airplanes 707

Service Bulletin

ALERT

Number: A3183

Original Issue: June 27, 1975

Revision 6: February 07, 2014

ATA System: 5410

SUBJECT: NACELLE - Inboard and Outboard Nacelle Strut - Midspar Fitting - Inspection and

Replacement

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.

ECCN: 9E991

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Unpublished Work.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 27, 1975

Revision 6: February 07, 2014 A3183

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8.0
Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT

BLANK PAGE
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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 37

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 39

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 45

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 47

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

FIGURE 1: THIS FIGURE IS DELETED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62

FIGURE 2: THIS FIGURE IS DELETED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63

FIGURE 3: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64

FIGURE 4: NACELLE STRUT # 2 AND # 3 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67

FIGURE 5: NACELLE STRUT # 2 AND # 3 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70

FIGURE 6: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75

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ALERT ALERT
FIGURE 7: NACELLE STRUT # 1 AND # 4 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78

FIGURE 8: NACELLE STRUT # 1 AND # 4 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

FIGURE 9: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM -

MID INTERVAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86

FIGURE 10: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM -

MID INTERVAL INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89

FIGURE 11: NACELLE STRUT # 1, # 2, # 3 AND # 4 INBOARD SIDE OVERWING SUPPORT FITTING

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92

FIGURE 12: NACELLE STRUT # 1, # 2, # 3 AND # 4 OUTBOARD SIDE OVERWING SUPPORT FITTING

INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94

FIGURE 13: NACELLE STRUT # 1, # 2, # 3 AND # 4 OUTBOARD SIDE OVERWING FASTENER

INSTALLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96

APPENDIX A: EXISTING PARTS ACCOUNTABILITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . 98

APPENDIX B: NACELLE STRUT # 1 AND # 4 - DRAG FITTING - CHAMFER / RADIUS INSPECTION . 101

APPENDIX C: BUSHING DIMENSIONS FOR DRAG FITTING ATTACHMENT HOLES . . . . . . . . . 103

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Commercial 

Airplanes 707

Service Bulletin

ALERT

Revision Transmittal Sheet Number: A3183

Original Issue: June 27, 1975

Revision 6: February 07, 2014

ATA System: 5410

SUBJECT: NACELLE - Inboard and Outboard Nacelle Strut - Midspar Fitting - Inspection and

Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

More work is necessary on the airplane(s) changed in accordance with Revision 5 of this service bulletin. Install

new inboard and outboard midspar fittings to each nacelle strut in accordance with the midspar fitting life-limit

program. Also, do detailed inspection and High Frequency Eddy Current (HFEC) inspection of the nacelle strut

midspar fittings in accordance with midspar fitting life-limit program mid interval inspection.

Federal Aviation Administration (FAA) Airworthiness Directive AD 93-11-02 is related to this service bulletin.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-16-12 is related to this service bulletin.

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.

Airplane line numbers 0910-0912, 0914-0915, 0917-0919, 0922-0923, 0925-0925, 0928-0929, 0936-0936,

0938-0938, 0941-0941 were added to Group 1 of this service bulletin effectivity.

REASON FOR REVISION

This revision is sent to give instructions to install new inboard and outboard midspar fittings to each nacelle strut

and to add detailed inspections and High Frequency Eddy Current (HFEC) inspections of each nacelle strut

midspar fitting. Instructions for detailed inspections and HFEC inspections of each nacelle strut torque bulkhead,

midspar chord, drag fitting and front spar support are added.

These sections were changed:

1. Background: Is updated and a new planning table added.

2. Action and Description: Is updated to install new inboard and outboard midspar fittings to each nacelle

strut and to add new detailed inspections and High Frequency Eddy Current (HFEC) inspections of

the midspar fittings, torque bulkhead, midspar chords, drag fitting and front spar support with the engine

and nacelle removed from the airplane.

3. Summary, Effectivity, statement is updated.

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4. Summary, Compliance: Added/Changed Federal Aviation Administration (FAA) Airworthiness Directive

statements.

5. Summary, Industry Support Information: Section is added.

6. Summary, Manpower: Is updated to show a new reference.

7. Paragraph 1.E., Compliance: Added/Changed Federal Aviation Administration (FAA) Airworthiness

Directive statements. Added compliance times and tables.

8. Paragraph 1.F., Approval: Is updated and new approval statements are added.

9. Paragraph 1.G., Manpower: New manpower times and tables are added.

10. Paragraph 1.J.1., Existing Data: Reference to Standard Overhaul Practices Manual (SOPM), Boeing

Service Related Problem (SRP) and Non-Destructive Testing (NDT) and an Airworthiness Directive

are added.

11. Paragraph 1.J.2., Data Supplied With This Service Bulletin: New drawings are added.

12. Paragraph 1.J.3., Installation Drawings Used in the Preparation of this Service Bulletin: New drawings

are added.

13. Paragraph 1.K., Publications Affected: A new publication is added.

14. Paragraph 1.M., Software Accomplishment Summary: Section is added.

15. Paragraph 2.A., Material - Price and Availability: Is updated to show price and availability of new top

kits.

16. Paragraph 2.C.1., Kits/Parts: Are updated to show two new top kits.

17. Paragraph 3.A., General Information: The notes section is updated.

18. Paragraph 3.B., Work Instructions: Are updated to include installation of new inboard and outboard

midspar fittings to each nacelle strut and new detailed inspections and High Frequency Eddy Current

(HFEC) inspections of the midspar fittings, torque bulkhead, midspar chords, drag fitting and front spar

support with the engine and nacelle removed from the airplane.

19. FIGURE 1 and FIGURE 2: Are deleted.

20. FIGURE 3 and FIGURE 6: Are added to inspect the midspar fittings.

21. FIGURE 4 and FIGURE 7: Are added to inspect the torque bulkhead and midspar chords.

22. FIGURE 5 and FIGURE 8: Are added to inspect the drag fittings and front spar supports.

23. FIGURE 9 and FIGURE 10: Are added to inspect the midspar fittings.

24. FIGURE 11, FIGURE 12 and FIGURE 13: Are added to inspect the inboard and outboard overwing

support fitting.

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ALERT ALERT
25. Appendix A: The existing parts accountability data has been moved from the material information

section to Appendix A.

26. Appendix B: Is added to show drag fitting chamfer/radius data for nacelle struts # 1 and # 4.

27. Appendix C: Is added to show bushing dimensions for drag fittings attachment holes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: June 27, 1975

Revision 1: May 13, 1977

Revision 2: January 28, 1988

Revision 3: January 31, 1991

Revision 4: July 09, 1992

Revision 5: September 16, 1993

Revision 6: February 07, 2014

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ALERT ALERT

BLANK PAGE
Commercial 

Airplanes 707

Service Bulletin

ALERT

Summary Number: A3183

Original Issue: June 27, 1975

Revision 6: February 07, 2014

ATA System: 5410

SUBJECT: NACELLE - Inboard and Outboard Nacelle Strut - Midspar Fitting - Inspection and

Replacement

THIS BULLETIN 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 SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect for any crack and to install a new number (#) 1, # 2, # 3 and #

4 engine nacelle strut inboard and outboard midspar fitting. If the work given in this service bulletin is not

accomplished, a crack in the inboard and outboard midspar fitting may go undetected. An undetected crack

could result in the loss of structural integrity of the midspar fitting which could cause an unsafe separation of

the engine which may result in a wing fire and/or the loss of the airplane.

Operators have reported more than 45 cracked midspar fittings on more than 40 turbofan airplanes with

approximately 9,900 to 63,000 flight hours. On five airplanes, fracture of the midspar fittings resulted in separation

of the inboard strut and engine from the airplane in flight. In two of those instances, the inboard nacelle strut

contacted the outboard engine, causing it to separate from the airplane. Operators have also reported cracking

in the transition radius of the # 1 and # 4 engine nacelle strut inboard and outboard midspar fittings. There have

been several documented cases of the outboard engine departing the airplane in flight. However, the midspar

fittings cannot be clearly shown to be the major cause of the outboard engines departing the airplane.

The reported cracks on the # 1, # 2, # 3 and # 4 engine nacelle strut inboard and outboard midspar fittings were

found to be vertical at the lug hole or across the double horizontal tangs at the radius where tangs merge with

lug. Analysis indicates the 4330 steel midspar fittings cracked as a result of stress corrosion and/or fatigue at

lug and fatigue at tangs.

A new life limiting program for the # 1, # 2, # 3 and # 4 engine nacelle strut inboard and outboard midspar fittings

and a redesign of the # 1 and # 4 engine nacelle strut inboard and outboard midspar fittings will prevent an

unsafe separation of an engine due to an undetected cracked condition in a midspar fitting.

Boeing Service Related Problem (SRP) 707-SRP-54-0105 is related to this service bulletin.

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This table is provided to operators for planning purposes only. Refer to the applicable sections for more

information.

Planning Data Affected Reference

Spares Affected Yes Paragraph 1.A.2., Spares Affected

AD Related Yes Paragraph 1.E., Compliance

Weight and Balance Change Yes Paragraph 1.H., Weight and Balance Changes

Electrical Load Changed No Paragraph 1.I., Electrical Load Data

Publications Affected Yes Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew Yes Paragraph 1.K., Publications Affected

Operations Manual and/or FAA Approved Airplane Flight Manual)

Kits/Parts Required Yes Paragraph 2.C.1., Kits/Parts

Paragraph 2.C.2., Parts and Materials Supplied

by the Operator

Operator Supplied Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION (PRR 18114-RS, PRR 17941)

Midspar Fitting Life-Limit Program:

Remove each engine and nacelle strut from the airplane. Remove the inboard and outboard midspar fittings

from each nacelle strut. Do a detailed inspection and a High Frequency Eddy Current (HFEC) inspection of each

nacelle strut inboard and outboard midspar fitting for any crack. If any crack equal to or larger than 0.3 inch is

found in the inboard or outboard midspar fitting, do detailed inspection and HFEC inspection of the overwing

support fitting for any crack. If any crack is found in overwing support fitting contact Boeing for repair instructions

and do the repair instructed by Boeing or install a new overwing support fitting in accordance with Boeing service

bulletin 3173 (707-3173). Do an open hole HFEC inspection of the vacated holes on each torque bulkhead and

each midspar chord for any crack. If any crack is found in a torque bulkhead or midspar chord rivet hole, oversize

the hole or contact Boeing for repair instructions and do the repair instructed by Boeing. If any crack is found in

a torque bulkhead or midspar chord bolt hole, contact Boeing for repair instructions and do the repair instructed

by Boeing. Do an open hole HFEC inspection of each drag fitting attachment hole for any crack. If any crack is

found in a drag fitting attachment hole, contact Boeing for repair instructions and do the repair instructed by

Boeing. If no crack is found in a drag fitting attachment hole, install new operator supplied bushings. Do an open

hole and a surface HFEC inspection of each front spar support for any crack. If any crack is found in the front

spar support, install a new front spar support in accordance with Boeing service bulletin 3366 (707-3366). Install

new inboard and outboard midspar fittings.

Midspar Fitting Life-Limit Program Mid Interval Inspection:

Remove each engine and nacelle strut from the airplane. Do a detailed inspection and a HFEC inspection of

each nacelle strut inboard and outboard midspar fitting for any crack. If any crack is found in the inboard or

outboard midspar fitting, remove the torque bulkhead and each inboard and outboard midspar fittings. Do an

open hole HFEC inspection of the vacated holes on the torque bulkhead and midspar chord for any crack. If

any crack is found in the torque bulkhead or midspar chord rivet hole, oversize the hole or contact Boeing for

repair instructions and do the repair instructed by Boeing. If any crack is found in the torque bulkhead or midspar

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
chord bolt hole, contact Boeing for repair instructions and do the repair instructed by Boeing. If any crack equal

to or larger than 0.3 inch is found in the inboard or outboard midspar fitting, do a detailed inspection and an

open hole HFEC inspection of the overwing support fitting for any crack. If any crack is found in overwing support

fitting contact Boeing for repair instructions and do the repair instructed by Boeing or install a new overwing

support fitting in accordance with Boeing service bulletin 3173 (707-3173). Do an open hole HFEC inspection

of each drag fitting attachment hole for any crack. If any crack is found in a drag fitting attachment hole, contact

Boeing for repair instructions and do the repair instructed by Boeing. If no crack is found in a drag fitting attachment

hole, install new operator supplied bushings. Do an open hole and a surface HFEC inspection of each front spar

support for any crack. If any crack is found in the front spar support, install a new front spar support in accordance

with Boeing service bulletin 3366 (707-3366). If any crack is found in the inboard or outboard midspar fitting,

replace the midspar fitting.

EFFECTIVITY

All 707-100 LONG BODY, -100B LONG BODY, -100B SHORT BODY, -200, -300, -300B, -300C, -400, and 720,

720B Airplane(s). Refer to Paragraph 1.A., Effectivity, for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive AD 93-11-02 is related to this service bulletin.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-16-12 is related to this service bulletin.

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection, and/or repair procedures given in this service

bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: June 27, 1975

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Export Controlled ECCN: 9E991 - BOEING

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Original Issue: June 27, 1975

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Commercial 

Airplanes 707

Service Bulletin

ALERT

Number: A3183

Original Issue: June 27, 1975

Revision 6: February 07, 2014

ATA System: 5410

SUBJECT: NACELLE - Inboard and Outboard Nacelle Strut - Midspar Fitting - Inspection and

Replacement

THIS BULLETIN 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 SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplane(s) shown below.

Refer to Service Bulletin Index D6-1647 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

All 707-100 LONG BODY, -100B LONG BODY, -100B SHORT BODY,

707-200, 707-300, 707-300B, 707-300C, 707-400, 720, 720B

Airplanes

1 -

Airplane Models:

707-100 LONG BODY, 707-100B LONG BODY, 707-100B SHORT BODY, 707-200, 707-300,

707-300B, 707-300C, 707-400, 720, 720B

Variable Number Group

B0001 - B0029 1

B0101 - B0125 1

B0201 - B0203 1

B0301 - B0306 1

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Variable Number Group

B0401 - B0402 1

B0501 - B0515 1

B2001 - B2008 1

B2091 - B2092 1

B2101 - B2116 1

B2191 - B2194 1

B2199 1

B2201 - B2227 1

B2401 - B2403 1

B2501 - B2502 1

B2551 - B2553 1

B2601 - B2608 1

00001 - 00002 1

00004 - 00006 1

00101 1

00103 - 00113 1

00115 - 00153 1

00201 - 00205 1

00301 - 00305 1

00401 - 00449 1

00471 - 00475 1

00501 - 00513 1

00601 1

00701 - 00703 1

02001 - 02020 1

02101 - 02121 1

02201 - 02207 1

02301 - 02303 1

02401 - 02418 1

04001 - 04005 1

04020 - 04022 1

04101 - 04106 1

04201 - 04218 1

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ALERT ALERT
Variable Number Group

04271 - 04272 1

04301 - 04303 1

05001 - 05060 1

05101 - 05138 1

05201 - 05208 1

05301 - 05312 1

05401 1

05601 - 05605 1

05631 - 05635 1

05701 - 05703 1

05801 - 05802 1

05821 - 05827 1

05831 - 05833 1

05851 - 05854 1

05891 - 05892 1

05921 - 05923 1

05941 - 05942 1

05961 - 05970 1

06001 - 06002 1

06101 1

06401 - 06404 1

06451 1

06461 1

07001 - 07017 1

07041 - 07059 1

07071 - 07081 1

07101 - 07109 1

07181 1

07191 1

07201 - 07215 1

07251 - 07271 1

07401 - 07407 1

07451 - 07458 1

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ALERT ALERT
Variable Number Group

07501 - 07504 1

07601 - 07626 1

07661 - 07662 1

07681 - 07684 1

07701 - 07702 1

07801 - 07821 1

07901 - 07907 1

08001 - 08008 1

08021 1

08051 - 08056 1

08071 - 08077 1

08101 - 08104 1

08121 - 08129 1

08141 - 08144 1

08151 - 08153 1

08171 - 08173 1

08191 - 08192 1

08201 - 08210 1

08221 - 08224 1

08241 - 08244 1

08251 1

08261 1

08271 1

08301 - 08320 1

08324 - 08330 1

08333 1

08401 - 08410 1

08451 - 08452 1

08471 - 08475 1

08501 - 08502 1

08551 - 08553 1

08581 - 08582 1

09001 - 09006 1

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ALERT ALERT
Variable Number Group

09101 - 09107 1

09161 - 09167 1

09201 - 09204 1

09221 - 09223 1

09227 1

09231 - 09232 1

09251 1

09271 1

09281 1

09286 - 09290 1

09411 1

09421 1

09438 1

09441 1

2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts

Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for

the recommended use.

B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instructions to inspect for any crack and to install a new number (#) 1, # 2,

# 3 and # 4 engine nacelle strut inboard and outboard midspar fitting. If the work given in this service

bulletin is not accomplished, a crack in the inboard and outboard midspar fitting may go undetected.

An undetected crack could result in the loss of structural integrity of the midspar fitting which could

cause an unsafe separation of the engine which may result in a wing fire and/or the loss of the airplane.

Operators have reported more than 45 cracked midspar fittings on more than 40 turbofan airplanes

with approximately 9,900 to 63,000 flight hours. On five airplanes, fracture of the midspar fittings resulted

in separation of the inboard strut and engine from the airplane in flight. In two of those instances, the

inboard nacelle strut contacted the outboard engine, causing it to separate from the airplane. Operators

have also reported cracking in the transition radius of the # 1 and # 4 engine nacelle strut inboard and

outboard midspar fittings. There have been several documented cases of the outboard engine departing

the airplane in flight. However, the midspar fittings cannot be clearly shown to be the major cause of

the outboard engines departing the airplane.

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ALERT ALERT
The reported cracks on the # 1, # 2, # 3 and # 4 engine nacelle strut inboard and outboard midspar

fittings were found to be vertical at the lug hole or across the double horizontal tangs at the radius

where tangs merge with lug. Analysis indicates the 4330 steel midspar fittings cracked as a result of

stress corrosion and/or fatigue at lug and fatigue at tangs.

A new life limiting program for the # 1, # 2, # 3 and # 4 engine nacelle strut inboard and outboard

midspar fittings and a redesign of the # 1 and # 4 engine nacelle strut inboard and outboard midspar

fittings will prevent an unsafe separation of an engine due to an undetected cracked condition in a

midspar fitting.

Revision 1 was issued to provide improved access for inspection at the root of the upper tang of the

fitting where primary cracking occurs.

Revision 2 was issued to modify inspection requirements so that repeat inspections on affected airplanes

were accomplished at 1500 flight hours, 600 flight cycles, or 750 flight cycles, depending on model,

whichever comes first. The 1.30 inch material removal dimension in Detail I and II of Figure 1 was

changed to 1.50 inch to allow improved space for cleaning. Also, Notice of Status Change, dated

November 30, 1979, was incorporated that added Boeing service Bulletin 3377, "Engine Nacelle Droop

Strip Installation" to prior or concurrent incorporation recommendation.

Revision 3 was issued to tell operators of the 707/720 Structures Working Group recommendations.

Revision 4 was issued as a partial revision by telegraph to tell operators that the Accomplishment

Instructions and Circle Notes 5, 8, and 9 in Figure 1, Inspection, were revised. It included the removal

of the sailboat fairing, more cleaning, and new improved Borescope inspection instructions.

Revision 5 is issued as a follow-up of partial release telegraphic Revision 4.

New information about availability of replacement fittings is given. Figure 1 and 2 titles are changed to

more accurately describe their contents. The illustrations in the Summary Page and in Figures 1 and

2 are revised to show locators. A new View A-A in Figure 1 is added to show a new lug area for

inspection. Man hour requirements for Borescope inspection are included. Reference to new

Airworthiness Directive (AD) 93-11-02, Amendment 39-8594, dated June 4, 1993, is included. Operators

are referred to this AD for compliance thresholds for this bulletin. Therefore, the flight hour and flight

cycle data for inspection thresholds in Notice of Status Change SB 3183 NSC 2 is not included in this

revision.

Revision 6 is sent to give instructions to install new inboard and outboard midspar fittings to each

nacelle strut and to add detailed inspections and High Frequency Eddy Current (HFEC) inspections of

each nacelle strut midspar fitting. Instructions for detailed inspections and HFEC inspections of each

nacelle strut torque bulkhead, midspar chord, drag fitting and front spar support are added.

Boeing Service Related Problem (SRP) 707-SRP-54-0105 is related to this service bulletin.

D. Description

Midspar Fitting Life-Limit Program:

Remove each engine and nacelle strut from the airplane. Remove the inboard and outboard midspar

fittings from each nacelle strut. Do a detailed inspection and a High Frequency Eddy Current (HFEC)

inspection of each nacelle strut inboard and outboard midspar fitting for any crack. If any crack equal

to or larger than 0.3 inch is found in the inboard or outboard midspar fitting, do detailed inspection and

HFEC inspection of the overwing support fitting for any crack. If any crack is found in overwing support

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ALERT ALERT
fitting contact Boeing for repair instructions and do the repair instructed by Boeing or install a new

overwing support fitting in accordance with Boeing service bulletin 3173 (707-3173). Do an open hole

HFEC inspection of the vacated holes on each torque bulkhead and each midspar chord for any crack.

If any crack is found in a torque bulkhead or midspar chord rivet hole, oversize the hole or contact

Boeing for repair instructions and do the repair instructed by Boeing. If any crack is found in a torque

bulkhead or midspar chord bolt hole, contact Boeing for repair instructions and do the repair instructed

by Boeing. Do an open hole HFEC inspection of each drag fitting attachment hole for any crack. If any

crack is found in a drag fitting attachment hole, contact Boeing for repair instructions and do the repair

instructed by Boeing. If no crack is found in a drag fitting attachment hole, install new operator supplied

bushings. Do an open hole and a surface HFEC inspection of each front spar support for any crack. If

any crack is found in the front spar support, install a new front spar support in accordance with Boeing

service bulletin 3366 (707-3366). Install new inboard and outboard midspar fittings.

Midspar Fitting Life-Limit Program Mid Interval Inspection:

Remove each engine and nacelle strut from the airplane. Do a detailed inspection and a HFEC inspection

of each nacelle strut inboard and outboard midspar fitting for any crack. If any crack is found in the

inboard or outboard midspar fitting, remove the torque bulkhead and each inboard and outboard midspar

fittings. Do an open hole HFEC inspection of the vacated holes on the torque bulkhead and midspar

chord for any crack. If any crack is found in the torque bulkhead or midspar chord rivet hole, oversize

the hole or contact Boeing for repair instructions and do the repair instructed by Boeing. If any crack

is found in the torque bulkhead or midspar chord bolt hole, contact Boeing for repair instructions and

do the repair instructed by Boeing. If any crack equal to or larger than 0.3 inch is found in the inboard

or outboard midspar fitting, do a detailed inspection and an open hole HFEC inspection of the overwing

support fitting for any crack. If any crack is found in overwing support fitting contact Boeing for repair

instructions and do the repair instructed by Boeing or install a new overwing support fitting in accordance

with Boeing service bulletin 3173 (707-3173). Do an open hole HFEC inspection of each drag fitting

attachment hole for any crack. If any crack is found in a drag fitting attachment hole, contact Boeing

for repair instructions and do the repair instructed by Boeing. If no crack is found in a drag fitting

attachment hole, install new operator supplied bushings. Do an open hole and a surface HFEC inspection

of each front spar support for any crack. If any crack is found in the front spar support, install a new

front spar support in accordance with Boeing service bulletin 3366 (707-3366). If any crack is found in

the inboard or outboard midspar fitting, replace the midspar fitting.

NOTE: Prior or concurrent incorporation of Boeing service bulletin 3377 (707-3377), "Engine Nacelle

Droop Strip Installation", is recommended.

Revision 6 - More work is necessary on the airplane(s) changed in accordance with Revision 5 of this

service bulletin. Install new inboard and outboard midspar fittings to each nacelle strut in accordance

with the midspar fitting life-limit program. Also, do detailed inspection and High Frequency Eddy Current

(HFEC) inspection of the nacelle strut midspar fittings in accordance with midspar fitting life-limit program

mid interval inspection.

The work in this service bulletin is done in the maintenance zone(s) given below.

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ALERT ALERT
Affected Maintenance Zones

Model Zone

707-100 LONG BODY, 707- 4-55, 4-56, 4-57, 4-58

100B LONG BODY, 707-100B

SHORT BODY, 707-200, 707-

300, 707-300B, 707-300C, 707-

400, 720, 720B

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive AD 93-11-02 is related to this service

bulletin.

Federal Aviation Administration (FAA) Airworthiness Directive AD 2012-16-12 is related to this service

bulletin.

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.

NOTE: Table 1 is not intended to be mandated by the FAA. The actions in Table 1 do not satisfy the

requirements of Table 2, 3, 4 and 5.

Table 1: Engine Number (#) 1, 2, 3 and 4 Nacelle Strut Inspection

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Action 1.1: Do a side Before every flight. Before every flight.

force inspection of the

engine # 1, # 2, # 3 and

# 4 to inspect for any unusual structural noises in

accordance with Paragraph 3.B., Work Instructions Part 1.a.

All airplanes.

(a)

Action 1.2: Do a general

visual inspection of engine # 1, # 2, # 3 and # 4

nacelle strut for signs of

droop or flexure damage

in accordance with Paragraph 3.B., Work Instructions Part 1.b.

(a)

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ALERT ALERT
Table 1: Engine Number (#) 1, 2, 3 and 4 Nacelle Strut Inspection

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Before further

flight.

Before further

flight.

Do the Life-Limit Program-Mid Interval Inspections in accordance with

Paragraph 3.B., Work Instructions Part 4 or Part

5.

If any signs of droop or

flexure damage or any unusual structural noises or

broken midspar fitting are

found during the inspections accomplished in accordance with Action 1.1 or

Action 1.2.

(a) It is Boeing's intention, that this action does not have to be accomplished by a qualified

mechanic.

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ALERT ALERT
Table 2: Nacelle Strut # 2 and # 3 Midspar Fitting Life-Limit Program

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

3,000 flight cycles

or 96 months,

whichever occurs

first. (a)

Within 18

months after the Revision 6 date

of this service bulletin.

Within 600

flight cycles

after the

Revision 6

date of this

service bulletin.

Remove the inboard and outboard midspar fittings in accordance with Paragraph 3.B.,

Work Instructions, Part 2.d.

All airplanes.

Action 2.1: Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of the inboard and outboard

midspar fittings for any crack in

accordance with Paragraph

3.B., Work Instructions, Part 2.e.

Action 2.2: Do an open hole

HFEC inspections of the torque

bulkhead, midspar chord, drag

fitting and front spar support for

any crack in accordance with

Paragraph 3.B., Work Instructions, Part 2.f., Part 2.g. & Part

2.i.

Action 2.3: Do a surface HFEC

inspection of the front spar support for any crack in accordance

with Paragraph 3.B., Work Instructions, Part 2.j.

Action 2.4: Do an open hole Before further flight. -

HFEC inspection for any crack

in the two forward most fastener

holes common to the inboard

side of the nacelle strut overwing support fitting and the wing

front spar upper chord in accordance with Paragraph 3.B.,

Work Instructions, Part 6.

Any crack equal to or larger

than 0.3 inch found during the

inspections accomplished in

accordance with Action 2.1.

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(1).

No crack is found during the inspections accomplished in accordance with Action 2.4.

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ALERT ALERT
Table 2: Nacelle Strut # 2 and # 3 Midspar Fitting Life-Limit Program

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Action 2.5: Do an open hole Before further flight. -

HFEC inspection of the two forward most fastener holes common to the outboard side of the

nacelle strut overwing support

fitting and the wing front spar

upper chord for any crack in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(2).

Any crack found during the inspections accomplished in accordance with Action 2.4.

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part

6.a.(2)(a).

No crack is found during the inspections accomplished in accordance with Action 2.5.

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 6.a.(3).

Any crack found during the inspections accomplished in accordance with Action 2.4 or Action 2.5.

Or

Install a new nacelle strut overwing support fitting in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(3)

and Boeing service bulletin

3173 (707-3173).

Action 2.6: Oversize holes and Before further flight. -

do an open hole HFEC inspection in accordance with Paragraph 3.B., Work Instructions,

Part 2.f.(1).

Any crack is found in a vacated

torque bulkhead and midspar

chord rivet hole during the inspections accomplished in accordance with Action 2.2.

Oversize the crack free rivet Before further flight. -

holes and install new midspar

fittings in accordance with

Paragraph 3.B., Work Instructions, Part 2.f.(1)(a).

If the crack is removed by

oversizing procedure accomplished in accordance with Action 2.6.

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part

2.f.(1)(b).

If the crack is not removed during the oversizing procedure

accomplished in accordance

with Action 2.6.

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ALERT ALERT
Table 2: Nacelle Strut # 2 and # 3 Midspar Fitting Life-Limit Program

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part 2.f.(2).

Any crack is found in a vacated

torque bulkhead and midspar

chord bolt hole during the inspections accomplished in accordance with Action 2.2.

Install new inboard and out- Before further flight. -

board midspar fittings and the

existing torque bulkhead in accordance with Paragraph 3.B.,

Work Instructions, Part 2.f.(3).

No crack is found in the

midspar chords or the torque

bulkhead during the inspections

accomplished in accordance

with Action 2.2.

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 2.g.(1).

Any crack found in a drag fitting

attachment hole during the inspections accomplished in accordance with Action 2.2.

Install new bushings in accor- Before further flight. -

dance with Paragraph 3.B.,

Work Instructions, Part 2.g.(2).

No crack found in the drag fitting attachment holes during

the inspections accomplished

in accordance with Action 2.2.

Install a new front spar support Before further flight. -

in accordance with Paragraph

3.B., Work Instructions, Part

2.i.(1); Part 2.j.(1) and Boeing

service bulletin 3366 (707-

3366).

Any crack found in the front

spar support during the inspections accomplished in accordance with Action 2.2 or Action

2.3.

(a) There is no terminating action for the repeat inspections.

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ALERT ALERT
Table 3: Nacelle Strut # 1 and # 4 Midspar Fitting Life-Limit Program

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

3,000 flight cycles

or 96 months,

whichever occurs

first. (a)

Within 18

months after the Revision 6 date

of this service bulletin.

Within 600

flight cycles

after the

Revision 6

date of this

service bulletin.

Remove the inboard and outboard midspar fittings in accordance with Paragraph 3.B.,

Work Instructions, Part 3.d.

All airplanes.

Action 3.1: Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of the inboard and outboard

midspar fittings for any crack in

accordance with Paragraph

3.B., Work Instructions, Part 3.e.

Action 3.2: Do an open hole

HFEC inspections of the torque

bulkhead, midspar chord, drag

fitting and front spar support for

any crack in accordance with

Paragraph 3.B., Work Instructions, Part 3.f., Part 3.g. and

Part 3.i.

Action 3.3: Do a surface HFEC

inspection of the front spar support for any crack in accordance

with Paragraph 3.B., Work Instructions, Part 3.j.

Action 3.4: Do an open hole Before further flight. -

HFEC inspection for any crack

in the two forward most fastener

holes common to the inboard

side of the nacelle strut overwing support fitting and the wing

front spar upper chord in accordance with Paragraph 3.B.,

Work Instructions, Part 6.

Any crack equal to or larger

than 0.3 inch found during the

inspections accomplished in

accordance with Action 3.1.

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(1).

No crack is found during the inspections accomplished in accordance with Action 3.4.

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ALERT ALERT
Table 3: Nacelle Strut # 1 and # 4 Midspar Fitting Life-Limit Program

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Action 3.5: Do an open hole Before further flight. -

HFEC inspection of the two forward most fastener holes common to the outboard side of the

nacelle strut overwing support

fitting and the wing front spar

upper chord for any crack in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(2).

Any crack found during the inspections accomplished in accordance with Action 3.4.

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part

6.a.(2)(a).

No crack is found during the inspections accomplished in accordance with Action 3.5.

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 6.a.(3).

Any crack found during the inspections accomplished in accordance with Action 3.4 or Action 3.5.

Or

Install a new nacelle strut overwing support fitting in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(3)

and Boeing service bulletin

3173 (707-3173).

Action 3.6: Oversize hole and Before further flight. -

do an open hole HFEC inspection in accordance with Paragraph 3.B., Work Instructions,

Part 3.f.(1).

Any crack is found in a vacated

torque bulkhead and midspar

chord rivet hole during the inspections accomplished in accordance with Action 3.2.

Oversize the crack free rivet Before further flight. -

holes and install new midspar

fittings in accordance with

Paragraph 3.B., Work Instructions, Part 3.f.(1)(a).

If the crack is removed by

oversizing procedure accomplished in accordance with Action 3.6.

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part

3.f.(1)(b).

If the crack is not removed during the oversizing procedure

accomplished in accordance

with Action 3.6.

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ALERT ALERT
Table 3: Nacelle Strut # 1 and # 4 Midspar Fitting Life-Limit Program

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part 3.f.(2).

Any crack is found in a vacated

torque bulkhead and midspar

chord bolt hole during the inspections accomplished in accordance with Action 3.2.

Install new inboard and out- Before further flight. -

board midspar fittings and the

existing torque bulkhead in accordance with Paragraph 3.B.,

Work Instructions, Part 3.f.(3).

No crack is found in the

midspar chords or the torque

bulkhead during the inspections

accomplished in accordance

with Action 3.2.

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 3.g.(1).

Any crack found in a drag fitting

attachment hole during the inspections accomplished in accordance with Action 3.2.

Install new bushings in accor- Before further flight. -

dance with Paragraph 3.B.,

Work Instructions, Part 3.g.(2).

No crack found in the drag fitting attachment holes during

the inspections accomplished

in accordance with Action 3.2.

Install a new front spar support Before further flight. -

in accordance with Paragraph

3.B., Work Instructions, Part

3.i.(1), Part 3.j.(1) and Boeing

service bulletin 3366 (707-

3366).

Any crack found in the front

spar support during the inspections accomplished in accordance with Action 3.2 or Action

3.3.

(a) There is no terminating action for the repeat inspections.

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ALERT ALERT
Table 4: Nacelle Strut # 2 and # 3 Midspar Fitting Life-Limit Program Mid Interval Inspection

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Within 48 (a)

months

from the

last

midspar fitting replacement.

Within

1,500 flight

cycles from

the last

midspar fitting replacement.

Action 4.1: Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of the inboard and outboard

midspar fittings for any crack in

accordance with Paragraph

3.B., Work Instructions, Part 4.c.

All airplanes.

Action 4.2: Do an open hole

HFEC inspections of the drag

fitting and front spar support for

any crack in accordance with

Paragraph 3.B., Work Instructions, Part 4.d. and Part 4.f.

Action 4.3: Do a surface HFEC

inspection of the front spar support for any crack in accordance

with Paragraph 3.B., Work Instructions, Part 4.g.

Remove the inboard and out- Before further flight. -

board midspar fittings in accordance with Paragraph 3.B.,

Work Instructions, Part

4.c.(1)(b).

Any crack found during the inspections accomplished in accordance with Action 4.1.

Action 4.4: Do an open hole Before further flight. -

HFEC inspection of the fastener

holes in the midspar chords and

torque bulkhead for any crack

in accordance with Paragraph

3.B., Work Instructions, Part

4.c.(1)(c).

Action 4.5: Do an open hole Before further flight. -

HFEC inspection for any crack

in the two forward most fastener

holes common to the inboard

side of the nacelle strut overwing support fitting and the wing

front spar upper chord in accordance with Paragraph 3.B.,

Work Instructions, Part 6.

Any crack equal to or larger

than 0.3 inch found during the

inspections accomplished in

accordance with Action 4.1.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Table 4: Nacelle Strut # 2 and # 3 Midspar Fitting Life-Limit Program Mid Interval Inspection

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Action 4.6: Oversize the hole Before further flight. -

and do an open hole HFEC inspection in accordance with

Paragraph 3.B., Work Instructions, Part 4.c.(1)(c)1).

Any crack found in a vacated

torque bulkhead and midspar

chord rivet hole during the inspections accomplished in accordance with Action 4.4.

Oversize the crack free rivet Before further flight. -

holes and install new midspar

fittings in accordance with

Paragraph 3.B., Work Instructions, Part 4.c.(1)(c)1)a).

If the crack is removed by

oversizing procedure accomplished in accordance with Action 4.6.

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part

4.c.(1)(c)1)b).

If the crack is not removed during the oversizing procedure

accomplished in accordance

with Action 4.6.

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part

4.c.(1)(c)2).

Any crack found in a torque

bulkhead and midspar chord

bolt hole accomplished in accordance with Action 4.4.

Install the torque bulkhead and Before further flight. -

new inboard and outboard

midspar fittings in accordance

with Paragraph 3.B., Work Instructions, Part 4.c.(1)(c)3).

No crack is found in the

midspar chords or the torque

bulkhead accomplished in accordance with Action 4.4.

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(1).

No crack is found during the inspections accomplished in accordance with Action 4.5.

Action 4.7: Do an open hole Before further flight. -

HFEC inspection of the two forward most fastener holes common to the outboard side of the

nacelle strut overwing support

fitting and the wing front spar

upper chord for any crack in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(2).

Any crack found during the inspections accomplished in accordance with Action 4.5.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Table 4: Nacelle Strut # 2 and # 3 Midspar Fitting Life-Limit Program Mid Interval Inspection

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part

6.a.(2)(a).

No crack is found during the inspections accomplished in accordance with Action 4.7.

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 6.a.(3).

Any crack found during the inspections accomplished in accordance with Action 4.5 and

Action 4.7.

Or

Install a new nacelle strut overwing support fitting in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(3)

and Boeing service bulletin

3173 (707-3173).

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 4.d.(1).

Any crack is found in a drag fitting attachment hole during the

inspections accomplished in

accordance with Action 4.2.

Install new bushings in accor- Before further flight. -

dance with Paragraph 3.B.,

Work Instructions, Part 4.d.(2).

No crack found in the drag fitting attachment holes during

the inspections accomplished

in accordance with Action 4.2.

Install a new front spar support Before further flight. -

in accordance with Paragraph

3.B., Work Instructions, Part

4.f.(1), Part 4.g.(1) and Boeing

service bulletin 3366 (707-

3366).

Any crack is found in the front

spar support during the inspections accomplished in accordance with Action 4.2 and Action 4.3.

(a) New midspar fittings are installed after accomplishment of the inspections given in Table 2. After installation

of the new midspar fittings, the mid interval inspection compliance time becomes applicable once more.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Table 5: Nacelle Strut # 1 and # 4 Midspar Fitting Life-Limit Program Mid Interval Inspection

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Within 48 (a)

months

from the

last

midspar fitting replacement.

Within

1,500 flight

cycles from

the last

midspar fitting replacement.

Action 5.1: Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of the inboard and outboard

midspar fittings for any crack in

accordance with Paragraph

3.B., Work Instructions, Part 5.c.

All airplanes.

Action 5.2: Do an open hole

HFEC inspections of the drag

fitting and front spar support for

any crack in accordance with

Paragraph 3.B., Work Instructions, Part 5.d. and Part 5.f.

Action 5.3: Do a surface HFEC

inspection of the front spar support for any crack in accordance

with Paragraph 3.B., Work Instructions, Part 5.g.

Remove the inboard and out- Before further flight. -

board midspar fittings in accordance with Paragraph 3.B.,

Work Instructions, Part

5.c.(1)(b).

Any crack found during the inspections accomplished in accordance with Action 5.1.

Action 5.4: Do an open hole Before further flight. -

HFEC inspection of the fastener

holes in the midspar chords and

torque bulkhead for any crack

in accordance with Paragraph

3.B., Work Instructions, Part

5.c.(1)(c).

Before fur- -

ther flight.

Action 5.5: Do an open hole

HFEC inspection for any crack

in the two forward most fastener

holes common to the inboard

side of the nacelle strut overwing support fitting and the wing

front spar upper chord in accordance with Paragraph 3.B.,

Work Instructions, Part 6.

Any crack equal to or larger

than 0.3 inch found during the

inspections accomplished in

accordance with Action 5.1.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Table 5: Nacelle Strut # 1 and # 4 Midspar Fitting Life-Limit Program Mid Interval Inspection

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Action 5.6: Oversize the hole Before further flight. -

and do an open hole HFEC inspection in accordance with

Paragraph 3.B., Work Instructions, Part 5.c.(1)(c)1).

Any crack found in a vacated

torque bulkhead and midspar

chord rivet hole during the inspections accomplished in accordance with Action 5.4.

Oversize the crack free rivet Before further flight. -

holes and install new midspar

fittings in accordance with

Paragraph 3.B., Work Instructions, Part 5.c.(1)(c)1)a).

If the crack is removed by

oversizing procedure accomplished in accordance with Action 5.6.

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part

5.c.(1)(c)1)b).

If the crack is not removed during the oversizing procedure

accomplished in accordance

with Action 5.6

Contact Boeing for repair instruc- Before further flight. -

tions and new inboard and outboard midspar fitting installation

instructions and do the work instructed by Boeing in accordance with Paragraph 3.B.,

Work Instructions, Part

5.c.(1)(c)2).

Any crack found in a torque

bulkhead and midspar chord

bolt hole during the inspections

accomplished in accordance

with Action 5.4.

Install the torque bulkhead and Before further flight. -

new inboard and outboard

midspar fittings in accordance

with Paragraph 3.B., Work Instructions, Part 5.c.(1)(c)3).

No crack is found in the

midspar chords or the torque

bulkhead during the inspections

accomplished in accordance

with Action 5.4.

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(1).

No crack is found during the inspections accomplished in accordance with Action 5.5.

Action 5.7: Do an open hole Before further flight. -

HFEC inspection of the two forward most fastener holes common to the outboard side of the

nacelle strut overwing support

fitting and the wing front spar

upper chord for any crack in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(2).

Any crack found during the inspections accomplished in accordance with Action 5.5.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Table 5: Nacelle Strut # 1 and # 4 Midspar Fitting Life-Limit Program Mid Interval Inspection

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs

First)

Condition Action

Install oversize fasteners in ac- Before further flight. -

cordance with Paragraph 3.B.,

Work Instructions, Part

6.a.(2)(a).

No crack is found during the inspections accomplished in accordance with Action 5.7.

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 6.a.(3).

Any crack found during the inspections accomplished in accordance with Action 5.5 and

Action 5.7.

Or

Install a new nacelle strut overwing support fitting in accordance with Paragraph 3.B.,

Work Instructions, Part 6.a.(3)

and Boeing service bulletin

3173 (707-3173).

Contact Boeing for repair instruc- Before further flight. -

tions and do the repair instructed by Boeing in accordance with

Paragraph 3.B., Work Instructions, Part 5.d.(1).

Any crack is found in a drag fitting attachment hole during the

inspections accomplished in

accordance with Action 5.2.

Install new bushings in accor- Before further flight. -

dance with Paragraph 3.B.,

Work Instructions, Part 5.d.(2).

No crack found in the drag fitting attachment holes during

the inspections accomplished

in accordance with Action 5.2.

Install a new front spar support Before further flight. -

in accordance with Paragraph

3.B., Work Instructions, Part

5.f.(1), Part 5.g.(1) and Boeing

service bulletin 3366 (707-

3366).

Any crack is found in the front

spar support during the inspections accomplished in accordance with Action 5.2 and Action 5.3.

(a) New midspar fittings are installed after accomplishment of the inspections given in Table 3. After installation

of the new midspar fittings, the mid interval inspection compliance time becomes applicable once more.

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.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
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.

This service bulletin has been approved by the Federal Aviation Administration (FAA). In addition, the

Manager of the FAA Seattle Aircraft Certification Office approves replacement of the midspar fittings

on the inboard nacelle struts in accordance with Service Bulletin A3183, Revision 6 as an AMOC to

the replacement of the midspar fittings specified in paragraph (e) of AD 93-11-02. All provisions of AD

93-11-02 that are not specifically referenced in the above statement remain fully applicable and must

be complied with accordingly.

In addition, the Manager of the FAA Seattle Aircraft Certification Office approves accomplishment of

the mid-interval inspections specified in Table 4 of paragraph 1.E., Compliance, of Service Bulletin

A3183, Revision 6, as an AMOC to the next inspection required by paragraph (h) of AD 2012-16-12

provided the mid-interval inspections are accomplished within 1,500 flight cycles or 48 months from

the last midspar fitting replacement, whichever occurs first. The repetitive inspections must continue

thereafter as specified in paragraph (h) of AD 2012-16-12. All provisions of AD 2012-16-12 that are

not specifically referenced in the above statement remain fully applicable and must be complied with

accordingly.

G. Manpower

Approximately 260 man-hours and two persons are necessary to do this inspection and replacement

for each airplane.

Man hour savings resulting from common access may be gained by concurrent accomplishment of

Boeing service bulletin 2313 (707-2313), "Nacelle Strut Forward Drag Support Fitting Replacement

and Midspar Bushing Installation", Boeing service bulletin 2958 (707-2958), "Nacelle Strut Spar Chord

Modification", and Boeing service bulletin 3173 (707-3173), "Inboard Nacelle Strut Overwing Support

Fitting Modification and Replacement" on commonly affected airplanes.

The tables below shows an estimate of the task hours necessary to do the inspection and replacement

for each midspar fitting. 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.

TABLE 1 : ENGINE NUMBER (#)1, # 2, # 3 AND # 4 NACELLE STRUT INSPECTION

Task Number of Persons Task Hours Elapsed Hours

General Visual in- 1 0.40 0.40

spection

Side Force Inspec- 1 0.40 0.40

tion

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
TABLE 1 : ENGINE NUMBER (#)1, # 2, # 3 AND # 4 NACELLE STRUT INSPECTION

Task Number of Persons Task Hours Elapsed Hours

TOTAL FOR EACH AIRPLANE 0.80 0.80

TABLE 2: NACELLE STRUT #1, # 2, #3 AND # 4 MIDSPAR FITTING LIFE-LIMIT PROGRAM

Task Number of Persons Task Hours Elapsed Hours

Open Access 8 48.00 6.00

Midspar Fitting Re- 4 18.00 4.50

moval

FIGURE 3 2 4.00 2.00

FIGURE 4 2 21.20 10.60

FIGURE 5 2 8.20 4.10

FIGURE 6 2 4.00 2.00

FIGURE 7 2 21.20 10.60

FIGURE 8 2 8.20 4.10

Midspar Fitting Instal- 4 18.00 4.50

lation

Close Access 8 48.00 6.00

Test 4 8.00 2.00

TOTAL FOR EACH AIRPLANE 206.80 (a) 56.40 (a)

(a) The estimated task hours do not include time to make repairs.

TABLE 3: NACELLE STRUT #1, # 2, #3 AND # 4 MIDSPAR FITTING LIFE-LIMIT PROGRAM

MID INTERVAL INSPECTION

Task Number of Persons Task Hours Elapsed Hours

Open Access 8 48.00 6.00

FIGURE 4 (a) 2 21.20 10.60

FIGURE 5 2 8.20 4.10

FIGURE 7 (a) 2 21.20 10.60

FIGURE 8 2 8.20 4.10

FIGURE 9 2 4.00 2.00

FIGURE 10 2 4.00 2.00

Close Access 8 48.00 6.00

Test 4 8.00 2.00

TOTAL FOR EACH AIRPLANE 128.40 (b) (c) 26.20 (b)(c)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
TABLE 3: NACELLE STRUT #1, # 2, #3 AND # 4 MIDSPAR FITTING LIFE-LIMIT PROGRAM

MID INTERVAL INSPECTION

Task Number of Persons Task Hours Elapsed Hours

(a) This task is only required if a crack is found in a midspar fitting.

(b) The estimated task hours do not include time for midspar fitting installation or

repairs.

(c) The estimated task hours do not include time for the inspection of the torque

bulkhead and midspar chords of the nacelle strut.

TABLE 4: OVERWING SUPPORT FITTING INSPECTION

Task Number of Persons Task Hours Elapsed Hours

FIGURE 11 1 2.20 2.20

FIGURE 12 1 2.80 2.80

FIGURE 13 1 2.20 2.20

TOTAL FOR EACH AIRPLANE 7.20 7.20

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

Airplane (Pounds)

707 + 1.0 + 836

I. Electrical Load Data

Not applicable.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 18114-RS, PRR 17941

b. 707 Maintenance Manual Subjects 12-3-1, 71-5-0, 54-01-0

c. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-43-03, 20-50-03, 20-50-10,

20-50-19

d. Boeing service bulletin 2313 (707-2313), "Nacelle Strut Forward Drag Support Fitting

Replacement and Bushing Installation"

e. Boeing service bulletin 2958 (707-2958), "Nacelle Strut Spar Chord Modification"

f. Boeing service bulletin 3173 (707-3173), "Inboard Nacelle Strut Overwing Support Fitting

Modification and Replacement"

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
g. Boeing service bulletin 3377 (707-3377), "Engine Nacelle Droop Strip Installation"

h. Boeing service bulletin 3366 (707-3366), "Nacelle Support Fitting Inspection, Modification and

Replacement"

i. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2012-16-12, 93-11-02

j. Boeing Service Related Problem (SRP) 707-SRP-54-0105

k. Service Bulletin Index D6-1647

l. 707, 720 Non-Destructive Testing (NDT) Manual Part 6, 51-00-00, Figure 4, Figure 13, Figure

16, Figure 23, Figure 24, Part 6, 57-40-07, Figure 2

m. 707-100/200 Structural Repair Manual (SRM) 51-2-5

n. 707-300/400 Structural Repair Manual (SRM) 51-2-5

2. Data Supplied with this Service Bulletin:

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

Retrofit Kit, Midspar Fitting Replacement 1 - -

Instl, Outboard Nacelle Strut

65C13839

65C13873 Top Kit - Midspar Fitting Replacement 1 - -

2 - -

Kit - Clevis trim Drag Support, Inboard Na- 1 - -

celle

65C14192

3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

65-2516 INBOARD STRUT - NACELLE, ASSEMBLY OF

65-2494 OUTBOARD STRUT NAC ASSY OF STRUCTURE

64-1062 MIDSPAR INSTALLATION - OUTBOARD NACELLE STRUT

64-1065 MIDSPAR INSTALLATION - INBOARD NACELLE STRUT

The table above lists applicable drawings used to prepare this service bulletin. The drawings are

not necessary to make the specified changes, and are not supplied with this service bulletin. The

drawings may not be applicable to all airplane configurations or operators.

K. Publications Affected

Publication Chapter-Section

707 Illustrated Parts Catalog 54-01, 57-03

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Publication Chapter-Section

707 Operations Manual 03-20

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.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane, and Paragraph

2.D., Parts Necessary to Change Spares. Operators are encouraged to share schedule requirements

with Boeing for incorporation of the service bulletin. The kits 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 02

date of this Service Bulletin (US

Dollars)

ROLT as of the

Revision 02 date

of this Service

Bulletin (Calendar

Days)

Kit Number Name

TOP KIT, MIDSPAR FITTING REPLACEMENT IN- 518 $7,737.00

STL - INBOARD NACELLE STRUT

65C13873-1

TOP KIT, MIDSPAR FITTING REPLACEMENT IN- 518 $7,867.00

STL - INBOARD NACELLE STRUT

65C13873-2

TOP KIT, MIDSPAR FITTING REPLACEMENT IN- 518 $7,800.00

STL - INBOARD NACELLE STRUT

65C13873-3

RETROFIT KIT, MIDSPAR FITTING REPLACEMENT 245 (a)

INSTL, OUTBOARD NACELLE STRUT

65C13839-1

RETROFIT KIT, MIDSPAR FITTING REPLACEMENT 245 (a)

INSTL, OUTBOARD NACELLE STRUT

65C13839-2

(a) No price available. Contact Boeing for unit price.

NOTE: (10) each Midspar Fittings 65-2536-25 and -26 are available July 8, 1993, as end-item parts.

B. Industry Support Information

Boeing warranty remedies are not available for the 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 .

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
NOTE: Four strut kits and the items shown in Paragraph 2.C.2., Parts and Materials Supplied

by the Operator , are necessary for each airplane.

65C13873 - KIT, INBOARD NACELLE STRUT MIDSPAR FITTING REPLACEMENT

Part Number Name

65C13873-1 TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - INBOARD NACELLE STRUT

(a)

65C13873-2 TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - INBOARD NACELLE STRUT

(b)

65C13873-3 TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - INBOARD NACELLE STRUT

(c)

65C13839-1 RETROFIT KIT, MIDSPAR FITTING REPLACEMENT INSTL, OUTBOARD NACELLE STRUT

(d)

65C13839-2 RETROFIT KIT, MIDSPAR FITTING REPLACEMENT INSTL, OUTBOARD NACELLE STRUT

(e)

(a) Necessary to modify each inboard strut on affected 707-100B LONG BODY, -100B SHORT BODY, -300B,

-300C, and 720B turbofan airplanes.

(b) Necessary to modify each inboard strut on affected 707-200 and -300 turbojet airplanes.

(c) Necessary to modify each inboard strut on affected 707-100 LONG BODY, -400, and 720 turbojet airplanes.

(d) Necessary to modify each outboard strut on affected 707-100B LONG BODY, -100B SHORT BODY, -

300B, -300C, and 720B turbofan airplanes.

(e) Necessary to modify each outboard strut on affected 707-200 and -300 turbojet airplanes.

Kit 65C13873

New Part Number QTY Name Notes

-1 -2 -3

TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - -

INBOARD NACELLE STRUT

65C13873-1 - . .

TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - -

INBOARD NACELLE STRUT

65C13873-2 . - .

TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - -

INBOARD NACELLE STRUT

65C13873-3 . . -

65C13873-4 1 1 . SUPPORT ANGLE -

65C13873-5 . . 1 SUPPORT ANGLE -

65C13873-6 2 2 . SHIM -

65C13873-7 1 1 1 SUPPORT ANGLE -

64-1065-15 2 2 2 SHIM -

64-1065-16 2 2 2 SHIM -

64-1065-17 2 2 2 SHIM -

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ALERT ALERT
Kit 65C13873

New Part Number QTY Name Notes

-1 -2 -3

65-2536-15 1 1 1 LT MID SPAR FITTING ASSY -

65-2536-16 1 1 1 RT MID SPAR FITTING ASSY -

65-2536-25 1 1 1 LT MID SPAR FITTING ASSY -

65-2536-26 1 1 1 RT MID SPAR FITTING ASSY -

65-2747-805 . . 2 FILLER -

KIT - CLEVIS TRIM - DRAG SUPPORT - INBOARD -

NACELLE

65C14192 1 1 1

66-1044-6 4 4 4 LUG SHIM -

66-1044-7 2 2 2 LUG SHIM -

66-1044-8 2 2 2 LUG SHIM -

66-1044-9 2 2 2 LUG SHIM -

66-1044-10 2 2 2 LUG SHIM -

66-1044-11 2 2 2 LUG SHIM -

66-1971-1 . . 2 FILLER -

66-1971-3 . . 2 FILLER -

BACB30FP8A-4 . . 4 SHEAR HI-LOCK (a)

BACB30FP8A-5 4 4 . SHEAR HI-LOCK (a)

BACB30FP8A-7 2 2 6 SHEAR HI-LOCK (a)

BACB30FP8A-8 16 6 4 SHEAR HI-LOCK (a)

BACB30FP8A-9 8 4 . SHEAR HI-LOCK (a)

BACB30FP8A-10 2 . . SHEAR HI-LOCK (a)

BACB30FP8A-11 2 . . SHEAR HI-LOCK (a)

BACB30KK8A-4 . . 2 SHEAR HI-LOCK (a)

BACB30KK8A-5 2 2 . SHEAR HI-LOCK (a)

BACB30KK8A-7 1 1 3 SHEAR HI-LOCK (a)

BACB30KK8A-8 8 3 2 SHEAR HI-LOCK (a)

BACB30KK8A-9 4 2 . SHEAR HI-LOCK (a)

BACB30KK8A-10 1 . . SHEAR HI-LOCK (a)

BACB30KK8A-11 1 . . SHEAR HI-LOCK (a)

BACB30MC12A-13 . 4 4 TENSION HI-LOCK (a)

BACB30MC12A-16 4 . . TENSION HI-LOCK (a)

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ALERT ALERT
Kit 65C13873

New Part Number QTY Name Notes

-1 -2 -3

BACB30MC12A-21 . 4 4 TENSION HI-LOCK (a)

BACB30MC12A-23 . 4 4 TENSION HI-LOCK (a)

BACB30MC12A-24 . 4 4 TENSION HI-LOCK (a)

BACB30MC12A-26 4 4 4 TENSION HI-LOCK (a)

BACB30MC12A-27 4 . . TENSION HI-LOCK (a)

BACB30MC12A-28 4 . . TENSION HI-LOCK (a)

BACB30MC12A-29 4 . . TENSION HI-LOCK (a)

BACB30MC12A-31 8 8 8 TENSION HI-LOCK (a)

BACB30MD12A-13 . 2 2 TENSION HI-LOCK (a)

BACB30MD12A-16 2 . . TENSION HI-LOCK (a)

BACB30MD12A-21 . 2 2 TENSION HI-LOCK (a)

BACB30MD12A-23 . 2 2 TENSION HI-LOCK (a)

BACB30MD12A-24 . 2 2 TENSION HI-LOCK (a)

BACB30MD12A-26 2 2 2 TENSION HI-LOCK (a)

BACB30MD12A-27 2 . . TENSION HI-LOCK (a)

BACB30MD12A-28 2 . . TENSION HI-LOCK (a)

BACB30MD12A-29 2 . . TENSION HI-LOCK (a)

BACB30MD12A-31 4 4 4 TENSION HI-LOCK (a)

BACC30AC12 14 14 14 COLLAR -

BACC30M8 34 16 14 COLLAR -

BACC30R8 17 8 7 COLLAR -

BACC30X12 28 28 28 COLLAR -

BACB30NE7-11X . 2 . BOLT (a)

BACB30NE7-13X 2 . . BOLT (a)

BACB30NE7-18X . 4 . BOLT (a)

BACB30NE7-11Y . 2 . BOLT (a)

BACB30NE7-13Y 2 . . BOLT (a)

BACB30NE7-18Y . 4 . BOLT (a)

BACB30MT7T-11X . . 2 BOLT (a)

BACB30MT7T-18X . . 4 BOLT (a)

BACB30MT7T-22X 4 . . BOLT (a)

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ALERT ALERT
Kit 65C13873

New Part Number QTY Name Notes

-1 -2 -3

BACB30MT7T-11Y . . 2 BOLT (a)

BACB30MT7T-18Y . . 4 BOLT (a)

BACB30MT7T-22Y 4 . . BOLT (a)

BACN10HR7 6 6 6 NUT -

BACN10JR3 2 2 2 NUTPLATE -

BACR15BA3D4 4 4 4 RIVET (a)

BACR15ET7D6 10 10 7 RIVET (a)

BACR15ET7D9 . . 4 RIVET (a)

BACR15ET9D9 4 24 24 RIVET (a)

SPS-X-66149-7.5-16.7 4 . . WASHER, PLI -

BACW10BP-71AC 6 6 6 WASHER, CSK -

BACW10BP-71AP 6 6 6 WASHER, PLAIN -

NAS603-8P 2 2 2 SCREW (a)

NAS603-10BP 2 2 2 SCREW (a)

BACW10BP-72AC 6 6 6 WASHER, CSK -

BACW10BP-72AP 6 6 6 WASHER,CSK -

(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer

than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,

substitute fasteners may be supplied in kits.

Kit 65C13839

New Part Number QTY Name Notes

-1 -2

RETROFIT KIT, MIDSPAR FITTING REPLACEMENT INSTL, -

OUTBOARD NACELLE STRUT

65C13839-1 - .

RETROFIT KIT, MIDSPAR FITTING REPLACEMENT INSTL, -

OUTBOARD NACELLE STRUT

65C13839-2 . -

64-1062-7 2 2 SHIM (a)

64-1062-8 2 2 SHIM (a)

64-1062-9 2 2 SHIM (a)

65-2534-21 1 1 FITTING ASSY, MID SPAR, OUTBOARD NACELLE STRUT (a)

65-2534-22 1 1 FITTING ASSY, MID SPAR, OUTBOARD NACELLE STRUT (a)

BACB30FP10A10 . 2 BOLT (a)

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ALERT ALERT
Kit 65C13839

New Part Number QTY Name Notes

-1 -2

BACB30FP10A11 4 4 BOLT O/S (a)

BACB30FP10A12 2 . BOLT (a)

BACB30FP10A13 2 . BOLT, PROTRUDING HD (a)

BACB30FP8A10 2 . BOLT (a)

BACB30FP8A11 2 . BOLT (a)

BACB30FP8A12 2 . BOLT (a)

BACB30FP8A13 2 . BOLT (a)

BACB30FP8A15 2 . BOLT, PROTRUDING HD (a)

BACB30FP8A16 2 . BOLT (a)

BACB30FP8A5 4 4 BOLT (a)

BACB30FP8A6 2 2 BOLT (a)

BACB30FP8A7 14 6 BOLT (a)

BACB30FP8A8 4 4 BOLT (a)

BACB30FP8A9 4 . BOLT (a)

BACB30MC12A15 . 4 BOLT (a)

BACB30MC12A16 4 . BOLT, PROTRUDING HD (a)

BACB30MC12A19 . 4 BOLT (a)

BACB30MC12A22 . 4 BOLT, PROTRUDING HD (a)

BACB30MC12A23 . 4 BOLT (a)

BACB30MC12A24 4 . BOLT, HEX DRIVE (a)

BACB30MC12A25 4 . BOLT (a)

BACB30MC12A26 4 . O/S BOLT (a)

BACB30MC12A29 4 4 BOLT (a)

BACB30MC12A30 4 4 BOLT, HEX DRIVE (a)

BACB30MC6A6 . 16 BOLT (a)

BACB30US7K13X . 2 BOLT, 12 PT HEAD (a)

BACB30US7K15X 2 . BOLT, 12 PT HEAD (a)

BACB30US7K18X . 4 BOLT, 12 PT HEAD (a)

BACB30US7K20X 4 . BOLT, 12 PT HEAD (a)

BACC30BH12 24 24 COLLAR -

BACC30M10 8 6 COLLAR -

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ALERT ALERT
Kit 65C13839

New Part Number QTY Name Notes

-1 -2

BACC30M6 . 16 COLLAR -

BACC30M8 34 16 COLLAR -

BACN10HR7CD 6 6 NUT -

BACR15BB7D6C 23 37 RIVET, UNIVERSAL HD (b)

BACW10BP71AC 6 6 WASHER, PLAIN -

BACW10BP71AP 6 6 WASHER, PLAIN -

(a) Discard the existing part.

(b) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer

than indicated. Also, if any fasteners part numbers listed are not available or have been superseded,

substitute fasteners may be supplied in kits.

2. Parts and Materials Supplied by the Operator

NOTE: Refer to 707 Structural Repair Manual Chapter 51 for alternative fasteners.

Part Number / QTY Name Notes

Specification

AMS-QQ-P-416, As Required Cadmium Plate -

Type 1, Class 2

Type 2, Class A As Required Chemical Conversion Coating -

BMS 3-23 or BMS As Required Corrosion Inhibiting Compound -

3-35

BMS 5-95, Class As Required Sealant -

B2

BMS 10-11, Type I As Required Primer -

BMS 11-7 As Required Cleaning Solvent -

BACB30MB12-10 As Required Bolt (a) (b)

BACC30BH12 As Required Collar (a) (b)

69-2860-1 As Required Straight Bushing - Non Plated (c) (g)

69-2860-2 As Required Straight Bushing - Non Plated (c) (g)

69-2860-50 As Required Straight Bushing - Plated (d) (g) (h)

69-2860-51 As Required Straight Bushing - Plated (d) (g) (h)

69-2860-59 As Required Straight Bushing - Plated (d) (g) (h)

69-2860-3 As Required Straight Bushing - Non Plated (e) (g)

69-2860-4 As Required Straight Bushing - Non Plated (e) (g)

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ALERT ALERT
Part Number / QTY Name Notes

Specification

69-2860-52 As Required Straight Bushing - Plated (f) (g) (h)

69-2860-53 As Required Straight Bushing - Plated (f) (g) (h)

69-42475-5 As Required Flanged Bushing - Plated (f) (g) (h)

69-42475-6 As Required Flanged Bushing - Plated (f) (g) (h)

69-42475-9 As Required Flanged Bushing - Plated (d) (g) (h)

69-42475-10 As Required Flanged Bushing - Plated (d) (g) (h)

69-42475-15 As Required Flanged Bushing - Plated (d) (g) (h)

69-42475-18 As Required Flanged Bushing - Plated (f) (g) (h)

See 707 Maintenance or Overhaul Manual Chapter 20 for procurement.

(a) This part is only required if oversizing in accordance with FIGURE 12 or FIGURE 13 is required.

(b) A total of four bolts and collars could be required for each nacelle overwing support fitting.

(c) This part is required with Top Kit 65C13873-2 and is necessary to modify drag fitting attachment holes on

affected 707-200 and -300 turbojet airplanes.

(d) This part is required with Top Kit 65C13873-1 and is necessary to modify drag fitting attachment holes on

affected 707-100B LONG BODY, -100B SHORT BODY, -300B, -300C, and 720B turbofan airplanes.

(e) This part is required with Top Kit 65C13839-2 and is necessary to modify drag fitting attachment holes on

affected 707-200 and -300 turbojet airplanes.

(f) This part is required with Top Kit 65C13839-1 and is necessary to modify drag fitting attachment holes on

affected 707-100B LONG BODY, -100B SHORT BODY, -300B, -300C, and 720B turbofan airplanes.

(g) Refer to APPENDIX C for bushing dimensions for drag fittings attachment holes.

(h) This part requires cadmium plating.

3. Parts Modified and Reidentified

Refer to APPENDIX A for existing parts accountability.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

To get the kits shown below, refer to Paragraph 2.A., Material - Price and Availability .

See Drawing 65C13873, Sheet 1, for kit components.

In addition, the applicable operator furnished materials listed in Paragraph 2.C.2., Parts and Materials

Supplied by the Operator , are necessary to supplement each of the following kits:

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ALERT ALERT
65C13873 - KIT, INBOARD NACELLE STRUT MIDSPAR FITTING REPLACEMENT

Part Number Name QTY

65C13873-1 TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - INBOARD NACELLE STRUT -

(a)

65C13873-2 TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - INBOARD NACELLE STRUT -

(b)

65C13873-3 TOP KIT, MIDSPAR FITTING REPLACEMENT INSTL - INBOARD NACELLE STRUT -

(c)

(a) Necessary to modify each affected spare equipped strut assembly 65-2510-3001 through -3110, and each

spare strut structure assembly 65-2516-3000, -3026, and -3030.

(b) Necessary to modify each affected spare equipped strut assembly 65-2510-1 and -2, and each spare strut

structure assembly 65-2516-1 and -3027.

(c) Necessary to modify each affected spare equipped strut assembly 50-8227-( ), and each spare strut

structure assembly 5-85617-( ).

65C13839 - KIT, OUTBOARD NACELLE STRUT MIDSPAR FITTING REPLACEMENT

Part Number Name QTY

RETROFIT KIT, MIDSPAR FITTING REPLACEMENT INSTL, OUTBOARD NACELLE -

STRUT

65C13839-1

(a)

RETROFIT KIT, MIDSPAR FITTING REPLACEMENT INSTL, OUTBOARD NACELLE -

STRUT

65C13839-2

(b)

(a) Necessary to modify each affected spare equipped strut assembly 65-2488-3001 through -3128, -501, -

502, and each spare strut structure assembly 65-2494-3000, -3015, -3019, -501.

(b) Necessary to modify each affected spare equipped strut assembly 65-2488-1 and -2, and each spare strut

structure assembly 65-2494, -1, and -3016.

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.

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ALERT ALERT
Export Controlled ECCN: 9E991 - BOEING

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ALERT ALERT

BLANK PAGE
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. 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

– Torque limits to tighten nuts and bolts are in SRM Chapter 51

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

4. Use the approved fastener and process 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.

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.

7. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

8. 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.

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ALERT ALERT
9. 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.

10. Refer to Appendix A for nacelle struts # 1, # 2, # 3 and # 4 existing parts accountability

data.

11. Refer to Appendix B for nacelle struts # 1 and # 4, drag fitting chamfer/radius data.

12. Refer to Appendix C for bushing dimensions for drag fittings attachment holes.

13. 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.

14. 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.

15. 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.

16. This service bulletin includes functional test procedures for the systems changed by

this service bulletin. More functional tests can possibly be necessary in accordance

with standard maintenance practices because of interruption to other airplane systems.

17. At locations where "Boeing service bulletin XXXX" is shown, the XXXX is the base

number for a 707 Boeing service bulletin. Where "(707-XXXX)" is mentioned in the

service bulletin, it is the same as Boeing service bulletin XXXX.

18. Some Boeing parts are supplied in a temporary configuration. Those parts are

identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is

permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'

(dash) part number. Boeing Drawing 005W0900 contains more data.

B. WORK INSTRUCTIONS

1. PART 1 - Engine Number (#) 1, # 2, # 3 And # 4 Nacelle Strut Inspection

a. Do a side force inspection of the engine # 1, # 2, # 3 and # 4. Apply alternating side forces

by hand to each side of engine nose cowl to inspect for any unusual structural noises.

NOTE: If a fitting is not completely severed, fore and aft movement between a cracked lug

and forward drag fitting clevis or between cracked tang ends may not be apparent

during this inspection. However, any unusual structural noises during this inspection

can indicate the start of a break.

(1) If any broken midspar fitting or any unusual structural noises is found, do the Life-Limit

Program - Mid Interval Inspections in accordance with Part 4 or Part 5.

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ALERT ALERT
b. Do a General Visual inspection of the engine # 1, # 2, # 3 and # 4 nacelle strut for signs of

droop below normal position. Look at the stripe if present for misalignment. In addition, do a

General Visual inspection of the fairing straps, access panels and fairings between strut and

wing for Flexure damage (buckles, wrinkles, cracks, elongated holes, loose or broken fasteners,

etc). Noticeable nacelle droop or flexure damage may indicate that one or both midspar fittings

are broken.

(1) If any buckles, wrinkles, cracks, elongated holes, loose or broken fasteners, flexure

damage to sheet metal or noticeable nacelle droop are found, do the Life-Limit Program

- Mid Interval Inspections in accordance with Part 4 or Part 5.

2. PART 2 - Engine # 2 and # 3 Nacelle Strut - Midspar Fitting - Life-Limit Program.

a. Remove the engine # 2 and # 3 from the airplane. Refer to 707 Aircraft Maintenance Manual

71-5-0 as an accepted procedure.

b. Remove the nacelle strut # 2 and # 3 from the airplane. Refer to 707 Aircraft Maintenance

Manual 54-01-0 as an accepted procedure.

c. Remove/keep the upper portion of the torque bulkhead. Refer to Boeing drawing number

65C13873, Sheet 1 and Sheet 2, zones 1 thru 8 for 707B/C and 720B turbofan airplanes, and

Zones 7 thru 13 for 707 and 720 turbojet airplanes.

CAUTION: MAKE SURE THE LUG BORE LOCATIONS OF THE OLD MIDSPAR FITTINGS

ARE ACCURATELY MAINTAINED ON THE INSTALLATION OF THE NEW MIDSPAR

FITTINGS. IF THE LUG BORE LOCATIONS ARE NOT ACCURATELY MAINTAINED

MISALIGNMENT OF THE NACELLE STRUT AND THE WING FORWARD DRAG

FITTINGS CAN OCCUR.

d. Remove the nacelle strut # 2 and # 3 inboard and outboard midspar fittings. Refer to Boeing

drawing number 65CI3873, Sheet 1 and Sheet 2, zones 1 thru 8 for 707B/C and 720B turbofan

airplanes, and Zones 7 thru 13 for 707 and 720 turbojet airplanes.

NOTE: New midspar fittings are supplied undrilled. As an option fabricate tooling as necessary

to maintain the lug bore locations of the old midspar fittings.

e. Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of

the removed nacelle strut # 2 and nacelle strut # 3 inboard and outboard midspar fittings for

any crack in accordance with FIGURE 3.

(1) If any crack equal to or larger than 0.3 inch is found in the inboard or outboard midspar

fitting, do the Part 6 - Overwing Support Fitting - Inspection and accomplish the remaining

Part 2 inspections.

(2) If every crack found is less than 0.3 inch, or if no crack is found, in the inboard or outboard

midspar fitting, continue with the Part 2 inspections.

f. Do an open hole High Frequency Eddy Current (HFEC) inspections of the vacated holes on

the torque bulkhead and midspar chords of the nacelle strut for any crack in accordance with

FIGURE 4.

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ALERT ALERT
(1) If any crack is found in a vacated torque bulkhead or midspar chord rivet hole, oversize

the 3/16 inch rivet hole to 0.218 - 0.233 inch diameter and do an open hole High Frequency

Eddy Current (HFEC) inspection for any crack in accordance with 707, 720 NDT Manual

Part 6, 51-00-00, Figure 16, using a 0.02 notch calibration.

(a) If no crack is found in the oversized rivet hole, oversize the crack free rivet hole to

0.263-0.265 inch diameter and install new inboard and outboard midspar fittings and

existing torque bulkhead with the applicable BACR15BB8D*C oversize fasteners as

necessary and in accordance with Boeing drawing number 65C13873, Sheet 1 and

Sheet 2, zones 1 thru 8 for 707B/C and 720B turbofan airplanes, and Zones 7 thru

13 for 707 and 720 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore tooling and

match drill with existing fastener holes in the midspar and torque bulkhead

installations. Make sure fastener Edge Distance (ED) is not less than 1D +

0.050 inch.

(b) If any crack is found in the oversized rivet hole, contact Boeing for repair instructions

and do the repair instructed by Boeing. Any repair must include replacement of the

inboard and outboard midspar fittings with new fittings.

(2) If any crack is found in a vacated torque bulkhead or midspar chord bolt hole, contact

Boeing for repair instructions and do the repair instructed by Boeing. Any repair must

include replacement of the inboard and outboard midspar fittings with new fittings.

(3) If no crack is found in a vacated torque bulkhead or midspar chord fastener hole, install

new inboard and outboard midspar fittings and the existing torque bulkhead in accordance

with Boeing drawing number 65C13873, Sheet 1 and Sheet 2, zones 1 thru 8 for 707B/C

and 720B turbofan airplanes, and Zones 7 thru 13 for 707 and 720 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore tooling and match

drill with existing fastener holes in the midspar and torque bulkhead installations.

Make sure fastener Edge Distance (ED) is not less than 1D + 0.050 inch.

g. Do an open hole High Frequency Eddy Current (HFEC) inspection of the drag fitting attachment

holes for any crack in accordance with FIGURE 5.

(1) If any crack is found in a drag fitting attachment hole contact Boeing for repair instructions

and do the repair instructed by Boeing.

(2) If no crack is found in the drag fitting attachment holes, install new operator supplied

bushings in accordance with FIGURE 5. Refer to APPENDIX C for bushing dimensions.

h. Make sure the corner radius or chamfer at the forward inside edges of the left and right wing

forward drag fitting will clear the larger shoulder radius of the mating surface of the new midspar

fitting. If the drag fitting will not clear the larger shoulder radius of the mating surface of the

new midspar fitting, chamfer the drag fittings in accordance with drawing 65C14192, Sheet

1.

(1) If required, re-identify all trimmed drag fittings to indicate incorporation of this service

bulletin. Apply stencil markings (service bulletin number) to a visible area of the drag

fitting. Refer to SOPM 20-50-10 as an accepted procedure. Make sure that trimmed

fittings are used for all subsequent fitting replacements.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
i. Do an open hole High Frequency Eddy Current (HFEC) inspection of the front spar support

attachment holes for any crack in accordance with FIGURE 5.

(1) If any crack is found in the front spar support attachment holes, install a new front spar

support in accordance with Boeing service bulletin 3366 (707-3366).

j. Do a surface High Frequency Eddy Current (HFEC) inspection of the front spar support for

any crack in accordance with FIGURE 5.

(1) If any crack is found in the front spar support, install a new front spar support in accordance

with Boeing service bulletin 3366 (707-3366).

k. Apply sealant to the midspar area in accordance with drawing 65CI3873, Sheet 1 and Sheet

2, zones1 thru 8 for 707B/C and 720B turbofan airplanes, and Zones 7 thru 13 for 707 and

720 turbojet airplanes.

l. Apply Corrosion Inhibiting Compound (CIC) BMS 3-23, TYPE II, CLASS 2 to the midspar

fitting areas. Refer to SOPM 20-43-03 as an accepted procedure.

NOTE: Each operator should evaluate his airplanes environment, the inhibitor used, and

the application schedule to ensure adequate corrosion protection. Although Boeing

has developed BMS 3-23 as a standard for organic corrosion inhibitors compound

and recommends its use, other water displacing corrosion preventive compounds

can be satisfactory, based on operator evaluation and experience.

m. Install the nacelle strut # 2 and # 3 to the airplane. Refer to 707 Aircraft Maintenance Manual

54-01-0 as an accepted procedure.

NOTE: On installation of nacelle strut to the airplane, make sure to install new lug shims (if

and as required) to reduce lug-to-clevis gap below 0.002 inch.

n. Install the engine # 2 and # 3 to the airplane. Refer to 707 Aircraft Maintenance Manual 71-5-0

as an accepted procedure.

o. Put the airplane back to a serviceable condition.

3. PART 3 - Engine # 1 and # 4 Nacelle Strut - Midspar Fitting - Life-Limit Program.

a. Remove the engine # 1 and # 4 from the airplane. Refer to 707 Aircraft Maintenance Manual

71-5-0 as an accepted procedure.

b. Remove the nacelle strut # 1 and # 4 from the airplane. Refer to 707 Aircraft Maintenance

Manual 54-01-0 as an accepted procedure.

c. Remove/keep the torque bulkhead. Refer to Boeing drawing number 65C13839 Sheet 1,

zones 1 thru 17 for 707-100B LONG BODY, -100B SHORT BODY, -300B, -300C and 720B

turbofan airplanes, and Zones 20 thru 32 for 707-200 and 300 turbojet airplanes.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
CAUTION: MAKE SURE THE LUG BORE LOCATIONS OF THE OLD MIDSPAR FITTINGS

ARE ACCURATELY MAINTAINED ON THE INSTALLATION OF THE NEW MIDSPAR

FITTINGS. IF THE LUG BORE LOCATIONS ARE NOT ACCURATELY MAINTAINED

MISALIGNMENT OF THE NACELLE STRUT AND THE WING FORWARD DRAG

FITTINGS CAN OCCUR.

d. Remove the nacelle strut # 1 and # 4 inboard and outboard midspar fittings. Refer to Boeing

drawing number 65C13839 Sheet 1, zones 1 thru 17 for 707-100B LONG BODY, -100B

SHORT BODY, -300B, -300C and 720B turbofan airplanes, and Zones 20 thru 32 for 707-200

and 300 turbojet airplanes.

NOTE: New midspar fittings are supplied undrilled. As an option fabricate tooling as necessary

to maintain the lug bore locations of the old midspar fittings.

e. Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of

the removed nacelle strut # 1 and nacelle strut # 4 inboard and outboard midspar fittings for

any crack in accordance with FIGURE 6.

(1) If any crack equal to or larger than 0.3 inch is found in the inboard or outboard midspar

fitting, do the Part 6 - Overwing Support Fitting - Inspection and accomplish the remaining

Part 3 inspections.

(2) If every crack found is less than 0.3 inch, or if no crack is found, in the inboard or outboard

midspar fitting, continue with the Part 3 inspections.

f. Do an open hole High Frequency Eddy Current (HFEC) inspections of the vacated holes on

the torque bulkhead and midspar chords of the nacelle strut for any crack in accordance with

FIGURE 7.

(1) If any crack is found in a vacated torque bulkhead or midspar chord rivet hole, oversize

the 3/16 inch rivet hole to 0.218 - 0.233 inch diameter and do an open hole High Frequency

Eddy Current (HFEC) inspection for any crack in accordance with 707, 720 NDT Manual

Part 6, 51-00-00, Figure 16, using a 0.02 notch calibration.

(a) If no crack is found in the oversized rivet hole, oversize the crack free rivet hole to

0.263-0.265 inch diameter and install new inboard and outboard midspar fittings and

existing torque bulkhead with the applicable BACR15BB8D*C oversize fasteners as

necessary and in accordance with Boeing drawing number 65C13839 Sheet 1, zones

1 thru 17 for 707-100B LONG BODY, -100B SHORT BODY, -300B, -300C and 720B

turbofan airplanes, and Zones 20 thru 32 for 707-200 and 300 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore tooling and

match drill with existing fastener holes in the midspar and torque bulkhead

installations. Make sure fastener Edge Distance (ED) is not less than 1D +

0.050 inch.

(b) If any crack is found in the oversized rivet hole, contact Boeing for repair instructions

and do the repair instructed by Boeing. Any repair must include replacement of the

inboard and outboard midspar fittings with new fittings.

(2) If any crack is found in a vacated torque bulkhead or midspar chord bolt hole, contact

Boeing for repair instructions and do the repair instructed by Boeing. Any repair must

include replacement of the inboard and outboard midspar fittings with new fittings.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
(3) If no crack is found in a vacated torque bulkhead or midspar chord fastener hole, install

new inboard and outboard midspar fittings and the existing torque bulkhead in accordance

with Boeing drawing number 65C13839 Sheet 1, zones 1 thru 17 for 707-100B LONG

BODY, -100B SHORT BODY, -300B, -300C and 720B turbofan airplanes, and Zones 20

thru 32 for 707-200 and 300 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore tooling and match

drill with existing fastener holes in the midspar and torque bulkhead installations.

Make sure fastener Edge Distance (ED) is not less than 1D + 0.050 inch.

g. Do an open hole High Frequency Eddy Current (HFEC) inspection of the drag fitting attachment

holes for any crack in accordance with FIGURE 8.

(1) If any crack is found in a drag fitting attachment hole contact Boeing for repair instructions

and do the repair instructed by Boeing.

(2) If no crack is found in the drag fitting attachment holes, install new operator supplied

bushings in accordance with FIGURE 8. Refer to APPENDIX C for bushing dimensions.

h. Make sure the corner radius or chamfer at the forward inside edges of the left and right wing

forward drag fitting will clear the larger shoulder radius of the mating surface of the new midspar

fitting. If the drag fitting will not clear the larger shoulder radius of the mating surface of the

new midspar fitting, chamfer the drag fittings in accordance with APPENDIX B.

(1) If required, re-identify all trimmed drag fittings to indicate incorporation of this service

bulletin. Apply stencil markings (service bulletin number) to a visible area of the drag

fitting. Refer to SOPM 20-50-10 as an accepted procedure. Make sure that trimmed

fittings are used for all subsequent fitting replacements.

i. Do an open hole High Frequency Eddy Current (HFEC) inspection of the front spar support

attachment holes for any crack in accordance with FIGURE 8.

(1) If any crack is found in the front spar support attachment holes, install a new front spar

support in accordance with Boeing service bulletin 3366 (707-3366).

j. Do a surface High Frequency Eddy Current (HFEC) inspection of the front spar support for

any crack in accordance with FIGURE 8.

(1) If any crack is found in the front spar support, install a new front spar support in accordance

with Boeing service bulletin 3366 (707-3366).

k. Apply sealant to the midspar area in accordance with Boeing drawing number 65C13839

Sheet 1.

l. Apply Corrosion Inhibiting Compound (CIC) BMS 3-23, TYPE II, CLASS 2 to the midspar

fitting areas. Refer to SOPM 20-43-03 as an accepted procedure.

NOTE: Each operator should evaluate his airplanes environment, the inhibitor used, and

the application schedule to ensure adequate corrosion protection. Although Boeing

has developed BMS 3-23 as a standard for organic corrosion inhibitors compound

and recommends its use, other water displacing corrosion preventive compounds

can be satisfactory, based on operator evaluation and experience.

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
m. Install the nacelle strut # 1 and # 4 to the airplane. Refer to 707 Aircraft Maintenance Manual

54-01-0 as an accepted procedure.

NOTE: On installation of nacelle strut to the airplane, make sure to install new lug shims (if

and as required) to reduce lug-to-clevis gap below 0.002 inch.

n. Install the engine # 1 and # 4 to the airplane. Refer to 707 Aircraft Maintenance Manual 71-5-0

as an accepted procedure.

o. Put the airplane back to a serviceable condition.

4. PART 4 - Engine # 2 And # 3 Nacelle Strut - Midspar Fitting - Life-Limit Program - Mid Interval

Inspection

a. Remove the engine # 2 and # 3 from the airplane. Refer to 707 Aircraft Maintenance Manual

71-5-0 as an accepted procedure.

b. Remove the nacelle strut # 2 and # 3 from the airplane. Refer to 707 Aircraft Maintenance

Manual 54-01-0 as an accepted procedure.

c. Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of

nacelle strut # 2 and nacelle strut # 3 inboard and outboard midspar fittings for any crack in

accordance with FIGURE 9.

(1) If any crack is found in the inboard or outboard midspar fitting, do the steps that follow:

(a) Remove/keep the upper portion of the torque bulkhead in accordance with Boeing

drawing number 65CI3873, Sheet 1 and Sheet 2, zones 1 thru 8 for 707B/C and

720B turbofan airplanes, and Zones 7 thru 13 for 707 and 720 turbojet airplanes.

CAUTION: MAKE SURE THE LUG BORE LOCATIONS OF THE OLD MIDSPAR

FITTINGS ARE ACCURATELY MAINTAINED ON THE INSTALLATION

OF THE NEW MIDSPAR FITTINGS. IF THE LUG BORE LOCATIONS ARE

NOT ACCURATELY MAINTAINED MISALIGNMENT OF THE NACELLE

STRUT AND THE WING FORWARD DRAG FITTINGS CAN OCCUR.

(b) Remove the inboard and outboard midspar fittings in accordance with Boeing drawing

number 65CI3873, Sheet 1 and Sheet 2, zones 1 thru 8 for 707B/C and 720B turbofan

airplanes, and Zones 7 thru 13 for 707 and 720 turbojet airplanes.

NOTE: New midspar fittings are supplied undrilled. As an option fabricate tooling

as necessary to maintain the lug bore locations of the old midspar fittings.

(c) Do an open hole High Frequency Eddy Current (HFEC) inspections of the vacated

holes on the torque bulkhead and midspar chords of the nacelle strut for any crack

in accordance with FIGURE 4.

1) If any crack is found in a vacated torque bulkhead or midspar chord rivet hole,

oversize the 3/16 inch rivet hole to 0.218 - 0.233 inch diameter and do an open

hole High Frequency Eddy Current (HFEC) inspection for any crack in

accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 16, using a

0.02 notch calibration.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
a) If no crack is found in the oversized rivet hole, oversize the crack free rivet

hole to 0.263-0.265 inch diameter and install new inboard and outboard

midspar fittings and existing torque bulkhead with the applicable

BACR15BB8D*C oversize fasteners as necessary and in accordance with

Boeing drawing number 65CI3873, Sheet 1 and Sheet 2, zones 1 thru 8

for 707B/C and 720B turbofan airplanes, and Zones 7 thru 13 for 707 and

720 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore

tooling and match drill with existing fastener holes in the midspar

and torque bulkhead installations. Make sure fastener Edge

Distance (ED) is not less than 1D + 0.050 inch.

b) If any crack is found in the oversized rivet hole, contact Boeing for repair

instructions and do the repair instructed by Boeing. Any repair must include

replacement of the inboard and outboard midspar fittings with new fittings.

2) If any crack is found in a vacated torque bulkhead or midspar chord bolt hole,

contact Boeing for repair instructions and do the repair instructed by Boeing.

Any repair must include replacement of the inboard and outboard midspar fittings

with new fittings.

3) If no crack is found in a vacated torque bulkhead or midspar chord fastener hole,

install new inboard and outboard midspar fittings and the existing torque bulkhead

in accordance with Boeing drawing number 65CI3873, Sheet 1 and Sheet 2,

zones 1 thru 8 for 707B/C and 720B turbofan airplanes, and Zones 7 thru 13

for 707 and 720 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore tooling

and match drill with existing fastener holes in the midspar and torque

bulkhead installations. Make sure fastener Edge Distance (ED) is not

less than 1D + 0.050 inch.

(2) If any crack equal to or larger than 0.3 inch is found in the inboard or outboard midspar

fitting, do the Part 6 - Overwing Support Fitting - Inspection and accomplish the remaining

Part 4 inspections.

(3) If every crack found is less than 0.3 inch, or if no crack is found, in the inboard or outboard

midspar fitting, continue with the Part 4 inspections.

d. Do an open hole High Frequency Eddy Current (HFEC) inspection of the drag fitting attachment

holes for any crack in accordance with FIGURE 5.

(1) If any crack is found in a drag fitting attachment hole contact Boeing for repair instructions

and do the repair instructed by Boeing.

(2) If no crack is found in the drag fitting attachment holes, install new operator supplied

bushings in accordance with FIGURE 5. Refer to APPENDIX C for bushing dimensions.

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
e. Make sure the corner radius or chamfer at the forward inside edges of the left and right wing

forward drag fitting will clear the larger shoulder radius of the mating surface of the new midspar

fitting. If the drag fitting will not clear the larger shoulder radius of the mating surface of the

new midspar fitting, chamfer the drag fittings in accordance with drawing 65C14192, Sheet

1.

(1) If required, re-identify all trimmed drag fittings to indicate incorporation of this service

bulletin. Apply stencil markings (service bulletin number) to a visible area of the drag

fitting. Refer to SOPM 20-50-10 as an accepted procedure. Make sure that trimmed

fittings are used for all subsequent fitting replacements.

f. Do an open hole High Frequency Eddy Current (HFEC) inspection of the front spar support

attachment holes for any crack in accordance with FIGURE 5.

(1) If any crack is found in the front spar support attachment holes, install a new front spar

support in accordance with Boeing service bulletin 3366 (707-3366).

g. Do a surface High Frequency Eddy Current (HFEC) inspection of the front spar support in

accordance with FIGURE 5.

(1) If any crack is found in the front spar support, install a new front spar support in accordance

with Boeing service bulletin 3366 (707-3366).

h. Apply sealant to the midspar area in accordance with drawing 65CI3873, Sheet 1 and Sheet

2, zones1 thru 8 for 707B/C and 720B turbofan airplanes, and Zones 7 thru 13 for 707 and

720 turbojet airplanes.

i. Apply Corrosion Inhibiting Compound (CIC) BMS 3-23, TYPE II, CLASS 2 to the midspar

fitting areas. Refer to SOPM 20-43-03 as an accepted procedure.

NOTE: Each operator should evaluate his airplanes environment, the inhibitor used, and

the application schedule to ensure adequate corrosion protection. Although Boeing

has developed BMS 3-23 as a standard for organic corrosion inhibitors compound

and recommends its use, other water displacing corrosion preventive compounds

can be satisfactory, based on operator evaluation and experience.

j. Install the nacelle strut # 2 and # 3 to the airplane. Refer to 707 Aircraft Maintenance Manual

54-01-0 as an accepted procedure.

NOTE: On installation of nacelle strut to the airplane, make sure to install new lug shims (if

and as required) to reduce lug-to-clevis gap below 0.002 inch.

k. Install the engine # 2 and # 3 to the airplane. Refer to 707 Aircraft Maintenance Manual 71-5-0

as an accepted procedure.

l. Put the airplane back to a serviceable condition.

5. PART 5 - Engine # 1 And # 4 Nacelle Strut - Midspar Fitting - Life-Limit Program - Mid Interval

Inspection

a. Remove the engine # 1 and # 4 from the airplane. Refer to 707 Aircraft Maintenance Manual

71-5-0 as an accepted procedure.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
b. Remove the nacelle strut # 1 and # 4 from the airplane. Refer to 707 Aircraft Maintenance

Manual 54-01-0 as an accepted procedure.

c. Do a detailed inspection and a surface High Frequency Eddy Current (HFEC) inspection of

nacelle strut # 1 and nacelle strut # 4 inboard and outboard midspar fittings for any crack in

accordance with FIGURE 10.

(1) If any crack is found in the inboard or outboard midspar fitting, do the steps that follow:

(a) Remove/keep the torque bulkhead in accordance with Boeing drawing number

65C13839 Sheet 1, zones 1 thru 17 for 707-100B LONG BODY, -100B SHORT

BODY, -300B, -300C and 720B turbofan airplanes, and Zones 20 thru 32 for 707-200

and 300 turbojet airplanes.

CAUTION: MAKE SURE THE LUG BORE LOCATIONS OF THE OLD MIDSPAR

FITTINGS ARE ACCURATELY MAINTAINED ON THE INSTALLATION

OF THE NEW MIDSPAR FITTINGS. IF THE LUG BORE LOCATIONS ARE

NOT ACCURATELY MAINTAINED MISALIGNMENT OF THE NACELLE

STRUT AND THE WING FORWARD DRAG FITTINGS CAN OCCUR.

(b) Remove the inboard and outboard midspar fittings in accordance with Boeing drawing

number 65C13839 Sheet 1, zones 1 thru 17 for 707-100B LONG BODY, -100B

SHORT BODY, -300B, -300C and 720B turbofan airplanes, and Zones 20 thru 32

for 707-200 and 300 turbojet airplanes.

NOTE: New midspar fittings are supplied undrilled. As an option fabricate tooling

as necessary to maintain the lug bore locations of the old midspar fittings.

(c) Do an open hole High Frequency Eddy Current (HFEC) inspections of the vacated

holes on the torque bulkhead and midspar chords of the nacelle strut for any crack

in accordance with FIGURE 7.

1) If any crack is found in a vacated torque bulkhead or midspar chord rivet hole,

oversize the 3/16 inch rivet hole to 0.218 - 0.233 inch diameter and do an open

hole High Frequency Eddy Current (HFEC) inspection for any crack in

accordance with 707, 720 NDT Manual Part 6, 51-00-00, Figure 16, using a

0.02 notch calibration.

a) If no crack is found in the oversized rivet hole, oversize the crack free rivet

hole to 0.263-0.265 inch diameter and install new inboard and outboard

midspar fittings and existing torque bulkhead with the applicable

BACR15BB8D*C oversize fasteners as necessary and in accordance with

Boeing drawing number 65C13839 Sheet 1, zones 1 thru 17 for 707-100B

LONG BODY, -100B SHORT BODY, -300B, -300C and 720B turbofan

airplanes, and Zones 20 thru 32 for 707-200 and 300 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore

tooling and match drill with existing fastener holes in the midspar

and torque bulkhead installations. Make sure fastener Edge

Distance (ED) is not less than 1D + 0.050 inch.

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
b) If any crack is found in the oversized rivet hole, contact Boeing for repair

instructions and do the repair instructed by Boeing. Any repair must include

replacement of the inboard and outboard midspar fittings with new fittings.

2) If any crack is found in a vacated torque bulkhead or midspar chord bolt hole,

contact Boeing for repair instructions and do the repair instructed by Boeing.

Any repair must include replacement of the inboard and outboard midspar fittings

with new fittings.

3) If no crack is found in a vacated torque bulkhead or midspar chord fastener hole,

install new inboard and outboard midspar fittings and the existing torque bulkhead

in accordance with Boeing drawing number 65C13839 Sheet 1, zones 1 thru

17 for 707-100B LONG BODY, -100B SHORT BODY, -300B, -300C and 720B

turbofan airplanes, and Zones 20 thru 32 for 707-200 and 300 turbojet airplanes.

NOTE: On installation of new midspar fitting use the optional lug bore tooling

and match drill with existing fastener holes in the midspar and torque

bulkhead installations. Make sure fastener Edge Distance (ED) is not

less than 1D + 0.050 inch.

(2) If any crack in the inboard or outboard midspar fitting is equal to or larger than 0.3 inch,

do the Part 6 - Overwing Support Fitting - Inspection and accomplish the remaining Part

5 inspections.

(3) If every crack found is less than 0.3 inch, or if no crack is found, in the inboard or outboard

midspar fitting, continue with the Part 5 inspections.

d. Do an open hole High Frequency Eddy Current (HFEC) inspection of the drag fitting attachment

holes in accordance with FIGURE 8.

(1) If any crack is found in a drag fitting attachment hole contact Boeing for repair instructions

and do the repair instructed by Boeing.

(2) If no crack is found in the drag fitting attachment holes, install new operator supplied

bushings in accordance with FIGURE 8. Refer to APPENDIX C for bushing dimensions.

e. Make sure the corner radius or chamfer at the forward inside edges of the left and right wing

forward drag fitting will clear the larger shoulder radius of the mating surface of the new midspar

fitting. If the drag fitting will not clear the larger shoulder radius of the mating surface of the

new midspar fitting, chamfer the drag fittings in accordance with APPENDIX B.

(1) If required, re-identify all trimmed drag fittings to indicate incorporation of this service

bulletin. Apply stencil markings (service bulletin number) to a visible area of the drag

fitting. Refer to SOPM 20-50-10 as an accepted procedure. Make sure that trimmed

fittings are used for all subsequent fitting replacements.

f. Do an open hole High Frequency Eddy Current (HFEC) inspection of the front spar support

attachment holes in accordance with FIGURE 8.

(1) If any crack is found in the front spar support attachment holes, install a new front spar

support in accordance with Boeing service bulletin 3366 (707-3366).

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
g. Do a surface High Frequency Eddy Current (HFEC) inspection of the front spar support in

accordance with FIGURE 8.

(1) If any crack is found in the front spar support, install a new front spar support in accordance

with Boeing service bulletin 3366 (707-3366).

h. Apply sealant to the midspar area in accordance with Boeing drawing number 65C13839

Sheet 1.

i. Apply Corrosion Inhibiting Compound (CIC) BMS 3-23, TYPE II, CLASS 2 to the midspar

fitting areas. Refer to SOPM 20-43-03 as an accepted procedure.

NOTE: Each operator should evaluate his airplanes environment, the inhibitor used, and

the application schedule to ensure adequate corrosion protection. Although Boeing

has developed BMS 3-23 as a standard for organic corrosion inhibitors compound

and recommends its use, other water displacing corrosion preventive compounds

can be satisfactory, based on operator evaluation and experience.

j. Install the nacelle strut # 1 and # 4 to the airplane. Refer to 707 Aircraft Maintenance Manual

54-01-0 as an accepted procedure.

NOTE: On installation of nacelle strut to the airplane, make sure to install new lug shims (if

and as required) to reduce lug-to-clevis gap below 0.002 inch.

k. Install the engine # 1 and # 4 to the airplane. Refer to 707 Aircraft Maintenance Manual 71-5-0

as an accepted procedure.

l. Put the airplane back to a serviceable condition.

6. Part 6 - Overwing Support Fitting - Inspection

a. Do an open hole High Frequency Eddy Current (HFEC) inspection in the two forward most

fastener holes common to the inboard side of the nacelle strut overwing support fitting and

the wing front spar upper chord for any crack in accordance with FIGURE 11.

(1) If no cracks are found, oversize the holes to remove fatigued metal and install oversize

fasteners in accordance with FIGURE 12.

(2) If any crack is found in the two forward most fastener holes common to the inboard side

of the nacelle strut overwing support fitting and the wing front spar upper chord, do an

open hole HFEC inspection for any crack in the two forward most fastener holes common

to the outboard side of the nacelle strut overwing support fitting and the wing front spar

upper chord in accordance with FIGURE 12.

(a) If no cracks are found, oversize the holes to remove fatigued metal and install oversize

fasteners in accordance with FIGURE 13.

(3) If any crack is found in any of the four fastener holes common to the nacelle strut overwing

support fitting and the wing front spar upper chord, contact Boeing for repair instructions

and do the repair instructed by Boeing or install a new overwing support fitting in

accordance with Boeing service bulletin 3173 (707-3173).

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ALERT ALERT
FIGURE 1: THIS FIGURE IS DELETED

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 2: THIS FIGURE IS DELETED

(SHEET 1 OF 1)

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ALERT ALERT
FIGURE 3: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 3: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Remove Sealant - - (a) (b)

2 Remove Sealant - - (c)

Clean Midspar Fitting - 2 (d)

3 Inspect Midspar Fitting - 2 (e)

4 Inspect Midspar Fitting - 2 (f)

(a) Remove sealant from the area around the bushing lug bores of the inboard and outboard midspar fittings.

Use tools made from plastic or hardwood material. Do not use metal tools.

(b) Bushing removal is not required.

(c) Remove all surface sealant from the areas covering the inboard and outboard midspar fitting. Refer to

SOPM 20-50-19 as an accepted procedure. Make sure all the surface areas of the midspar fitting are

clearly visible before inspection.

(d) Clean all areas of the inboard and outboard midspar fittings. Refer to 707 Maintenance Manual Subject

12-3-1 or SOPM 20-30-03 as an accepted procedure.

(e) Do a detailed inspection of the inboard and outboard midspar fittings for any crack.

(f) Do a surface High Frequency Eddy Current (HFEC) inspection of the inboard and outboard midspar fittings

for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 13 or Figure 24.

FIGURE 3: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

(SHEET 3 OF 3)

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ALERT ALERT
FIGURE 4: NACELLE STRUT # 2 AND # 3 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

(SHEET 1 OF 3)

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ALERT ALERT
FIGURE 4: NACELLE STRUT # 2 AND # 3 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Inspect Midspar Chord - - (a)

2 Inspect Torque Bulkhead - - (b)

(a) Do an open hole High Frequency Eddy Current (HFEC) inspection at all opened holes in the midspar

chords for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16, using a 0.03 notch

calibration.

(b) Do an open hole High Frequency Eddy Current (HFEC) inspection at all opened holes in the torque

bulkhead for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16, using a 0.03 notch

calibration.

FIGURE 4: NACELLE STRUT # 2 AND # 3 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

(SHEET 3 OF 3)

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ALERT ALERT
FIGURE 5: NACELLE STRUT # 2 AND # 3 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 1 OF 5)

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ALERT ALERT
FIGURE 5: NACELLE STRUT # 2 AND # 3 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 2 OF 5)

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ALERT ALERT
FIGURE 5: NACELLE STRUT # 2 AND # 3 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Remove Bushing - 2 (a) (b)

Measure Bushing - 2 (b) (c)

Clean Drag Fitting Hole - 2 (d)

2 Inspect Drag Fitting Hole - 2 (e)

3 Remove / Keep Fastener - 2 (f)

4 Inspect Drag Fitting Hole - 2 (e)

Front Spar Support - 2 (g)

Hole

5 Inspect

6 Inspect Front Spar Support - - (h)

7 Install (Kept) Fastener - 2 -

8 Hone Drag Fitting Hole - 2 (i)

Measure Drag Fitting Hole - 2 (j)

Chemical Conversion TYPE 2, CLASS A - (k)

Coating

9 Apply

10 Apply Sealant BMS 5-95 - (l)

Install (New) Bushing - 2 (b) (m)

Ream Bushing - 2 (n)

(a) Remove bushing from the drag fitting attachment hole. Refer to SOPM 20-50-03 as an accepted procedure.

(b) Bushings are operator supplied parts. Refer to APPENDIX C to fabricate bushings.

(c) Measure the Internal Diameter (ID), Outer Diameter (OD), and flange thickness to determine the appropriate replacement bushing.

(d) Clean drag fitting hole. Refer to 707 Maintenance Manual Subject 12-3-1 or SOPM 20-30-03 as an accepted procedure.

(e) Do an open hole High Frequency Eddy Current (HFEC) inspection of the drag fitting attachment hole for

any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16.

(f) Remove the fasteners common to the drag fitting and front spar support.

(g) Do an open hole High Frequency Eddy Current (HFEC) inspection of the front spar support attachment

holes for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16.

(h) Do a surface High Frequency Eddy Current (HFEC) inspection of the front spar support for any crack in

accordance with 707, 720 NDT Part 6, 51-00-00, Figure 4 or Figure 23 or 707, 720 NDT Part 6, 57-40-

07, Figure 2.

(i) Lightly hone the drag fitting hole as required to restore the surface finish of 63 microinches AA.

FIGURE 5: NACELLE STRUT # 2 AND # 3 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Step Task Name Identification Qty More Data

(j) Measure the drag fitting hole to make sure the drag fitting hole is within tolerance. Refer to APPENDIX

C for drag fitting hole diameter dimensions. If the drag fitting hole is not within tolerance contact Boeing

for repair instructions and do the repair.

(k) Apply chemical conversion coating to the drag fitting hole. Refer to SOPM 20-43-03 as an accepted procedure.

(l) Apply sealant to all mating surfaces of the bushing and drag fitting hole. Refer to SOPM 20-50-19 as an

accepted procedure.

(m) Use the shrink fit procedure to install the bushing to the drag fitting attachment hole. Refer to SOPM 20-

50-03 as an accepted procedure.

(n) Ream bushing bore holes to final diameter in accordance with Boeing Engineering Drawing 65C13873.

FIGURE 5: NACELLE STRUT # 2 AND # 3 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 6: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 6: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Remove Sealant - - (a) (b)

2 Remove Sealant - - (c)

Clean Midspar Fitting - 2 (d)

3 Inspect Midspar Fitting - 2 (e)

4 Inspect Midspar Fitting - 2 (f)

(a) Remove sealant from the area around the bushing lug bores of the inboard and outboard midspar fittings.

Use tools made from plastic or hardwood material. Do not use metal tools.

(b) Bushing removal is not required.

(c) Remove all surface sealant from the areas covering the inboard and outboard midspar fitting. Refer to

SOPM 20-50-19 as an accepted procedure. Make sure all the surface areas of the midspar fitting are

clearly visible before inspection.

(d) Clean all areas of the inboard and outboard midspar fittings. Refer to 707 Maintenance Manual Subject

12-3-1 or SOPM 20-30-03 as an accepted procedure.

(e) Do a detailed inspection of the inboard and outboard midspar fittings for any crack.

(f) Do a surface High Frequency Eddy Current (HFEC) inspection of the inboard and outboard midspar fittings

for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 13 or Figure 24.

FIGURE 6: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE LIMIT PROGRAM

(SHEET 3 OF 3)

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ALERT ALERT
FIGURE 7: NACELLE STRUT # 1 AND # 4 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 7: NACELLE STRUT # 1 AND # 4 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Inspect Midspar Chord - - (a)

2 Inspect Torque Bulkhead - - (b)

(a) Do an open hole High Frequency Eddy Current (HFEC) inspection at all opened holes in the midspar

chords for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16, using a 0.03 notch

calibration.

(b) Do an open hole High Frequency Eddy Current (HFEC) inspection at all opened holes in the torque

bulkhead for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16, using a 0.03 notch

calibration.

FIGURE 7: NACELLE STRUT # 1 AND # 4 TORQUE BULKHEAD AND MIDSPAR CHORD INSPECTIONS

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 8: NACELLE STRUT # 1 AND # 4 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 1 OF 5)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 8: NACELLE STRUT # 1 AND # 4 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 8: NACELLE STRUT # 1 AND # 4 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 3 OF 5)

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83 of 106

BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Remove Bushing - 2 (a) (b)

Measure Bushing - 2 (b) (c)

Clean Drag Fitting Hole - 2 (d)

2 Inspect Drag Fitting Hole - 2 (e)

3 Remove Fastener - 1 (f)

4 Inspect Drag Fitting Hole - 1 (e)

Front Spar Support - 1 (g)

Hole

5 Inspect

6 Inspect Front Spar Support - - (h)

7 Install (Kept) Fastener - 1 -

8 Hone Drag Fitting Hole - 2 (i)

Measure Drag Fitting Hole - 2 (j)

Chemical Conversion TYPE 2, CLASS A - (k)

Coating

9 Apply

10 Apply Sealant BMS 5-95 - (l)

Install (New) Bushing - 2 (b) (m)

Ream Bushing - 2 (n)

(a) Remove bushing from the drag fitting attachment hole. Refer to SOPM 20-50-03 as an accepted procedure.

(b) Bushings are operator supplied parts. Refer to APPENDIX C to fabricate bushings.

(c) Measure the Internal Diameter (ID), Outer Diameter (OD), and flange thickness to determine the appropriate replacement bushing.

(d) Clean drag fitting hole. Refer to 707 Maintenance Manual Subject 12-3-1 or SOPM 20-30-03 as an accepted procedure.

(e) Do an open hole High Frequency Eddy Current (HFEC) inspection of the drag fitting attachment hole for

any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16.

(f) Remove the fasteners common to the drag fitting and front spar support.

(g) Do an open hole High Frequency Eddy Current (HFEC) inspection of the front spar support attachment

holes for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16.

(h) Do a surface High Frequency Eddy Current (HFEC) inspection of the front spar support for any crack in

accordance with 707, 720 NDT Part 6, 51-00-00, Figure 4 or Figure 23 or 707, 720 NDT Part 6, 57-40-

07, Figure 2.

(i) Lightly hone the drag fitting hole as required to restore the surface finish of 63 microinches AA.

FIGURE 8: NACELLE STRUT # 1 AND # 4 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 4 OF 5)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Step Task Name Identification Qty More Data

(j) Measure the drag fitting hole to make sure the drag fitting hole is within tolerance. Refer to APPENDIX

C for drag fitting hole diameter dimensions. If the drag fitting hole is not within tolerance contact Boeing

for repair instructions and do the repair.

(k) Apply chemical conversion coating to the drag fitting hole. Refer to SOPM 20-43-03 as an accepted procedure.

(l) Apply sealant to all mating surfaces of the bushing and drag fitting hole. Refer to SOPM 20-50-19 as an

accepted procedure.

(m) Use the shrink fit procedure to install the bushing to the drag fitting attachment hole. Refer to SOPM 20-

50-03 as an accepted procedure.

(n) Ream bushing bore holes to final diameter in accordance with Boeing Engineering Drawing 65C13839.

FIGURE 8: NACELLE STRUT # 1 AND # 4 DRAG FITTING AND FRONT SPAR SUPPORT INSPECTIONS

(SHEET 5 OF 5)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 9: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM - MID

INTERVAL INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 9: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM - MID

INTERVAL INSPECTION

(SHEET 2 OF 3)

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87 of 106

BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Remove Sealant - - (a) (b)

2 Remove Sealant - - (c)

Clean Midspar Fitting - 2 (d)

3 Inspect Midspar Fitting - 2 (e)

4 Inspect Midspar Fitting - 2 (f)

(a) Remove sealant from the area around the bushing lug bores of the inboard and outboard midspar fittings.

Use tools made from plastic or hardwood material. Do not use metal tools.

(b) Bushing removal is not required.

(c) Remove all surface sealant from the areas covering the inboard and outboard midspar fitting. Refer to

SOPM 20-50-19 as an accepted procedure. Make sure all the surface areas of the midspar fitting are

clearly visible before inspection.

(d) Clean all visible areas of the inboard and outboard midspar fittings. Refer to 707 Maintenance Manual

Subject 12-3-1 or SOPM 20-30-03 as an accepted procedure.

(e) Do a detailed inspection of all visible areas of the inboard and outboard midspar fittings for any crack.

(f) Do a surface High Frequency Eddy Current (HFEC) inspection of all visible areas of the inboard and

outboard midspar fittings for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 13 or

Figure 24.

FIGURE 9: NACELLE STRUT # 2 AND # 3 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM - MID

INTERVAL INSPECTION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 10: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM -

MID INTERVAL INSPECTION

(SHEET 1 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 10: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM -

MID INTERVAL INSPECTION

(SHEET 2 OF 3)

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90 of 106

BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Remove Sealant - - (a) (b)

2 Remove Sealant - - (c)

Clean Midspar Fitting - 2 (d)

3 Inspect Midspar Fitting - 2 (e)

4 Inspect Midspar Fitting - 2 (f)

(a) Remove sealant from the area around the bushing lug bores of the inboard and outboard midspar fittings.

Use tools made from plastic or hardwood material. Do not use metal tools.

(b) Bushing removal is not required.

(c) Remove all surface sealant from the areas covering the inboard and outboard midspar fitting. Refer to

SOPM 20-50-19 as an accepted procedure. Make sure all the surface areas of the midspar fitting are

clearly visible before inspection.

(d) Clean all visible areas of the inboard and outboard midspar fittings. Refer to 707 Maintenance Manual

Subject 12-3-1 or SOPM 20-30-03 as an accepted procedure.

(e) Do a detailed inspection of all visible areas of the inboard and outboard midspar fittings for any crack.

(f) Do a surface High Frequency Eddy Current (HFEC) inspection of all visible areas of the inboard and

outboard midspar fittings for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 13 or

Figure 24.

FIGURE 10: NACELLE STRUT # 1 AND # 4 MIDSPAR FITTING INSPECTION - LIFE-LIMIT PROGRAM -

MID INTERVAL INSPECTION

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 11: NACELLE STRUT # 1, # 2, # 3 AND # 4 INBOARD SIDE OVERWING SUPPORT FITTING

INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Remove Fastener - 2 (a)

2 Inspect Hole - 2 (b)

(a) Remove the two forward most fasteners attaching the inboard side of the nacelle strut overwing support

fitting to the wing front spar upper chord.

(b) Do an open hole High Frequency Eddy Current (HFEC) inspection of the holes in the chord, skin, and,

overwing support fitting for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16.

FIGURE 11: NACELLE STRUT # 1, # 2, # 3 AND # 4 INBOARD SIDE OVERWING SUPPORT FITTING

INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 12: NACELLE STRUT # 1, # 2, # 3 AND # 4 OUTBOARD SIDE OVERWING SUPPORT FITTING

INSPECTION

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Drill / Ream Hole - 2 (a)

2 Install (New) Bolt BACB30MB12-10 2 (b)

Install (New) Collar BACC30BH12 2 -

3 Remove Fastener - 2 (c)

4 Inspect Hole - 2 (d)

(a) Oversize the holes to 0.371 - 0.375 inch diameter to remove fatigued metal in accordance with 707-

100/200 SRM 51-2-5 or 707-300/400 SRM 51-2-5.

(b) Install the fasteners common to the inboard side of the nacelle strut overwing support fitting and the wing

front spar upper chord.

(c) Remove the two fasteners attaching the outboard side of the nacelle strut overwing support fitting to the

wing front spar upper chord.

(d) Do an open hole High Frequency Eddy Current (HFEC) inspection of the holes in the chord, skin, and,

overwing support fitting for any crack in accordance with 707, 720 NDT Part 6, 51-00-00, Figure 16.

FIGURE 12: NACELLE STRUT # 1, # 2, # 3 AND # 4 OUTBOARD SIDE OVERWING SUPPORT FITTING

INSPECTION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
FIGURE 13: NACELLE STRUT # 1, # 2, # 3 AND # 4 OUTBOARD SIDE OVERWING FASTENER

INSTALLATION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY

numbers shown below are the number of parts necessary for each nacelle strut.

Step Task Name Identification Qty More Data

1 Drill / Ream Hole - 2 (a)

2 Install (New) Bolt BACB30MB12-10 2 (b)

Install (New) Collar BACC30BH12 2 -

(a) Oversize the holes to 0.371 - 0.375 inch diameter to remove fatigued metal in accordance with 707-

100/200 SRM 51-2-5 or 707-300/400 SRM 51-2-5.

(b) Install the fasteners common to the outboard side of the overwing support fitting and the wing front spar

upper chord.

FIGURE 13: NACELLE STRUT # 1, # 2, # 3 AND # 4 OUTBOARD SIDE OVERWING FASTENER

INSTALLATION

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
The parts shown below are changed by this service bulletin. The Quantity is the number of parts changed on

each airplane. Components or sub-assembly parts are indented. The Quantity of the indented part is the number

of parts used on the next higher assembly.

Existing Part Number RUC Name Quantity New Part Number PNC RC

50-8227-1 thru -10, -13 R, S C

thru -20, -23 thru -28, -31

, -32, -3001, -3002, -3007

thru -3010

Strut Assembly - 1 each

Equipped

50-8227-1 thru -10, -13 RWK

thru -20, -23 thru -28, -31

, -32, -3001, -3002, -3007

thru -3010

65-2510-1, -2, -3001 thru R, S C

-3016, -3019 thru -3030,

-3033, -3034, -3037 thru

-3042, -3049 thru -3056,

-3059 thru -3110

Strut Assembly - 1 each

Equipped

65-2510-1, -2, -3001 thru RWK

-3016, -3019 thru -3030,

-3033, -3034, -3037 thru

-3042, -3049 thru -3056,

-3059 thru -3110

.5-85617-3000 thru - R, S C

3002, -3008, -3009, -

3011, -3014

Strut Assembly - 1 each

Structure

.5-85617-3000 thru - RWK

3002, -3008, -3009, -

3011, -3014

Strut Assembly - 1 each 65-2516, -1 R, S C

Structure

.65-2516, -1 RWK

65-2516-3000, -3026, - R, S C

3027, -3030

Strut Assembly - 1 each

Structure

.65-2516-3000, -3026, - RWK

3027, -3030

..5-85658-3001 DIS Midspar Fitting 1 65-2536-15 or -25 S C

..5-85658-3002 DIS Midspar Fitting 1 65-2536-16 or -26 S C

..5-85658-3017 DIS Midspar Fitting 1 65-2536-15 or -25 S C

..5-85658-3018 DIS Midspar Fitting 1 65-2536-16 or -26 S C

.. 65-2536-1 DIS Midspar Fitting 1 65-2536-15 or -25 S C

.. 65-2536-2 DIS Midspar Fitting 1 65-2536-16 or -26 S C

.. 65-2536-4 DIS Midspar Fitting 1 65-2536-15 or -25 S C

.. 65-2536-5 DIS Midspar Fitting 1 65-2536-16 or -26 S C

.. 65-2536-7 DIS Midspar Fitting 1 65-2536-19 or -27 S C

.. 65-2536-8 DIS Midspar Fitting 1 65-2536-20 or -28 S C

Midspar Fitting As- 1 65-2536-15 or -25 S C

sembly

.. 65-2536-9 DIS

Midspar Fitting As- 1 65-2536-16 or -26 S C

sembly

.. 65-2536-10 DIS

Bushing - Standard 1 each 65-27303-32 S A

Size

... 65-27303-27, -28, -29 DIS

Bushing - Under- 1 each 65-27303-32 S C

size I.D.

... 65-99744-427, -428, - DIS

429

APPENDIX A: EXISTING PARTS ACCOUNTABILITY

(SHEET 1 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Existing Part Number RUC Name Quantity New Part Number PNC RC

66-1044 DIS Lug Shim - 0.001 8 66-1044-6 S C

66-1044-1 DIS Lug Shim - 0.003 4 66-1044-7 S C

66-1044-2 DIS Lug Shim - 0.006 4 66-1044-8 S C

66-1044-3 DIS Lug Shim - 0.010 4 66-1044-9 S C

66-1044-4 DIS Lug Shim - 0.016 4 66-1044-10 S C

66-1044-5 DIS Lug Shim - 0.025 4 66-1044-11 S C

Existing Part Number RUC Name Quantity New Part Number PNC RC

50-8228-1 thru -12, -15 R, S C

thru -32, -3001, -3002, -

3007 thru -3014

Strut Assembly - 1 each

Equipped

50-8228-1 thru -12, -15 RWK

thru -32, -3001, -3002, -

3007 thru -3014

65-2488-1, -2, -3001 thru R, S C

-3016, -3019 thru -3030,

-3033 thru -3042, -3049

thru 3128, -501, -502

Strut Assembly - 1 each

Equipped

65-2488-1, -2, -3001 thru RWK

-3016, -3019 thru -3030,

-3033 thru -3042, -3049

thru 3128, -501, -502

5-85627-3000, -3002, - R, S C

3003, -3009, -3010, -

3012, -3013, -3014, -

3015,

Strut Assembly - 1 each

Structure

5-85627-3000, -3002, - RWK

3003, -3009, -3010, -

3012, -3013, -3014, -

3015,

Strut Assembly - 1 each 65-2494, -1, -3016 R, S C

Structure

65-2494, -1, -3016 RWK

65-2494-3000, -3015, - R, S C

3019, -501

Strut Assembly - 1 each

Structure

65-2494-3000, -3015, - RWK

3019, -501

5-84467-3001 DIS Midspar Fitting 1 65-02534-21 S C

5-84467-3002 DIS Midspar Fitting 1 65-02534-22 S C

5-84467-3003 DIS Midspar Fitting 1 65-02534-21 S C

5-84467-3004 DIS Midspar Fitting 1 65-02534-22 S C

65-02534-1 DIS Midspar Fitting 1 65-02534-21 S C

65-02534-2 DIS Midspar Fitting 1 65-02534-22 S C

65-02534-4 DIS Midspar Fitting 1 65-02534-21 S C

65-02534-5 DIS Midspar Fitting 1 65-02534-22 S C

65-02534-7 DIS Midspar Fitting 1 65-02534-19 S C

65-02534-8 DIS Midspar Fitting 1 65-02534-20 S C

Midspar Fitting As- 1 65-02534-21 S C

sembly

65-02534-9 DIS

APPENDIX A: EXISTING PARTS ACCOUNTABILITY

(SHEET 2 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: June 27, 1975

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Existing Part Number RUC Name Quantity New Part Number PNC RC

Midspar Fitting As- 1 65-02534-22 S C

sembly

65-02534-10 DIS

Bushing - Standard 1 each 65-27303-33 S A

Size

65-27303-26 DIS

66-1051 DIS Lug Shim - 0.001 8 66-1051-6 S C

66-1051-1 DIS Lug Shim - 0.003 4 66-1051-7 S C

66-1051-2 DIS Lug Shim - 0.006 4 66-1051-8 S C

66-1051-3 DIS Lug Shim - 0.010 4 66-1051-9 S C

66-1051-4 DIS Lug Shim - 0.016 4 66-1051-10 S C

66-1051-5 DIS Lug Shim - 0.025 4 66-1051-11 S C

RUC Recommended Use Code

DIS Discard the part.

RWK Make the change as specified in this service bulletin.

PNC Part Number Code

R This is the part number after the change.

S This is the new equivalent or replacement part number.

RC Replacement Code

A Replacement not permitted. Do not replace a new part with an existing part.

Replacement permitted. However, if the existing part is used, it will cancel the effect of the change

specified in this service bulletin

C

APPENDIX A: EXISTING PARTS ACCOUNTABILITY

(SHEET 3 OF 3)

Export Controlled ECCN: 9E991 - BOEING

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Original Issue: June 27, 1975

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
APPENDIX B: NACELLE STRUT # 1 AND # 4 - DRAG FITTING - CHAMFER / RADIUS INSPECTION

(SHEET 1 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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Work - See page 1 for details.

Original Issue: June 27, 1975

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
APPENDIX B: NACELLE STRUT # 1 AND # 4 - DRAG FITTING - CHAMFER / RADIUS INSPECTION

(SHEET 2 OF 2)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Inboard Strut - Drag Fitting - Straight Bushing - Non Plated

Part Number Drag Fitting Hole Diameter A B C

0.77

0.78

1.160 0.77

1.189

1.3145 1.186

1.3165

69-2860-1 1.3125 - 1.3126 1.3145

(a)

0.79

0.80

1.160 0.79

1.189

1.3145 1.186

1.3165

69-2860-2 1.3125 - 1.3126 1.3145

(a)

(a) This part is required with Top Kit 65C13873-2.

APPENDIX C: BUSHING DIMENSIONS FOR DRAG FITTING ATTACHMENT HOLES

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Inboard Strut - Drag Fitting - Straight Bushing - Part Number - Plated (a)

Drag Fitting Hole A (Before Plate) A (After Plate) B C

Diameter

Part Number

0.79

0.80

1.192 0.79

1.221

1.3461 1.218

1.3470

1.3457 1.3461

1.3462

69-2860-50 1.3445 - 1.3446 1.3457

(b)

0.92

0.93

1.192 0.92

1.221

1.3461 1.218

1.3470

1.3457 1.3461

1.3462

69-2860-51 1.3445 - 1.3446 1.3457

(b)

0.97

0.98

1.192 0.97

1.221

1.3461 1.218

1.3470

1.3457 1.3461

1.3462

69-2860-59 1.3445 - 1.3446 1.3457

(b)

(a) Cadmium plate in accordance with AMS-QQ-P-416, Type 1, Class 2. Plating optional on ID.

(b) This part is required with Top Kit 65C13873-1.

Outboard Strut - Drag Fitting - Straight Bushing - Non Plated

Part Number Drag Fitting Hole Diameter A B C

0.80

0.81

1.090 0.80

1.127

1.2520 1.124

1.2540

69-2860-3 1.2500 - 1.2510 1.2520

(a)

0.79

0.80

1.090 0.79

1.127

1.2520 1.124

1.2540

69-2860-4 1.2500 - 1.2510 1.2520

(a)

(a) This part is required with Top Kit 65C13839-2.

Outboard Strut - Drag Fitting - Straight Bushing - Plated (a)

Drag Fitting Hole A (Before Plate) A (After Plate) B C

Diameter

Part Number

0.80

0.81

1.122 0.80

1.159

1.2836 1.156

1.2845

1.2832 1.2836

1.2837

69-2860-52 1.2820 - 1.2830 1.2832

(b)

0.92

0.93

1.122 0.92

1.159

1.2836 1.156

1.2845

1.2832 1.2836

1.2837

69-2860-53 1.2820 - 1.2830 1.2832

(b)

(a) Cadmium plate in accordance with AMS-QQ-P-416, Type 1, Class 2. Plating optional on ID.

(b) This part is required with Top Kit 65C13839-1.

APPENDIX C: BUSHING DIMENSIONS FOR DRAG FITTING ATTACHMENT HOLES

(SHEET 2 OF 4)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: June 27, 1975

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BOEING SERVICE BULLETIN A3183

ALERT ALERT
Outboard Strut - Drag Fitting - Flanged Bushing - Plated (a)

G

+0.010

-0.000

F

+/-

0.005

Drag Fitting D (Before Plate) D (After Plate) E

Hole Diameter

Part Number

1.122 0.855 0.09

1.159

1.2836 1.156

1.2845

1.2832 1.2836

1.2837

69-42475-5 1.2820 - 1.2830 1.2832

(b)

1.122 0.935 0.09

1.159

1.2836 1.156

1.2845

1.2832 1.2836

1.2837

69-42475-6 1.2820 - 1.2830 1.2832

(b)

1.192 0.905 0.09

1.221

1.3461 1.218

1.3470

1.3457 1.3461

1.3462

69-42475-9 1.2820 - 1.2830 1.3457

(c)

APPENDIX C: BUSHING DIMENSIONS FOR DRAG FITTING ATTACHMENT HOLES

(SHEET 3 OF 4)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: June 27, 1975

Revision 6 February 07, 2014 A3183

105 of 106

BOEING SERVICE BULLETIN A3183

ALERT ALERT
Outboard Strut - Drag Fitting - Flanged Bushing - Plated (a)

G

+0.010

-0.000

F

+/-

0.005

Drag Fitting D (Before Plate) D (After Plate) E

Hole Diameter

Part Number

1.192 0.906 0.09

1.221

1.3461 1.218

1.3470

1.3457 1.3461

1.3462

69-42475-10 1.2820 - 1.2830 1.3457

(c)

1.192 0.835 0.09

1.221

1.3461 1.218

1.3470

1.3457 1.3461

1.3462

69-42475-15 1.2820 - 1.2830 1.3457

(c)

1.122 0.855 0.06

1.159

1.2836 1.156

1.2845

1.2832 1.2836

1.2837

69-42475-18 1.2820 - 1.2830 1.2832

(b)

(a) Cadmium plate in accordance with AMS-QQ-P-416, Type 1, Class 2. Plating optional on ID.

(b) This part is required with Top Kit 65C13839-1.

(c) This part is required with Top Kit 65C13873-1.

APPENDIX C: BUSHING DIMENSIONS FOR DRAG FITTING ATTACHMENT HOLES

(SHEET 4 OF 4)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: June 27, 1975

Revision 6 February 07, 2014 A3183

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BOEING SERVICE BULLETIN A3183

ALERT ALERT