Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-57A0131

Original Issue: October 30, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Outboard Flap Support Rib Nut

Fracture Inspection

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 © 2012 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Unpublished Work.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, DreamlinerTM,

BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, 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. BOEING is a trademark of Boeing Management

Company.

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ALERT ALERT

BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 21

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 25

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 28

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1 . . . . . . . . . . . . . . . 35

FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2 . . . . . . . . . . . . . . . 37

FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7 . . . . . . . . . . . . . . . 39

FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8 . . . . . . . . . . . . . . . 41

FIGURE 5: FASTENER DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1 . . . . . . . . . . . . . . . . . . 44

FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2 . . . . . . . . . . . . . . . . . . 48

FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7 . . . . . . . . . . . . . . . . . . 52

FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8 . . . . . . . . . . . . . . . . . . 56

FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE [Group 2] . . . . . . . . . . . . . . . . . . 60

FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE [Group 2-3] . . . . . . . . . . . . . . . . . 62

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ALERT ALERT
APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER . . . . . . . . . . . . 64

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Commercial 

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-57A0131

Original Issue: October 30, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Outboard Flap Support Rib Nut

Fracture Inspection

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

Accomplishment of this service bulletin will find and replace any cracked, corroded or incorrect nuts and bolts

on the #1, #2, #7 and #8 outboard flap support ribs. Cracked, corroded or incorrect nuts and bolts could lead to

additional nut and bolt damage in the joint which could result in loss of the outboard flap. Continued safe flight

and landing could be affected after the departure of a flap during takeoff or landing.

An operator reported two fractured and corroded nuts on the outboard flap, support rib #2 on an airplane with

54,953 hours and 49,519 cycles. It was found that the incorrect nuts (QTY 8) were installed on support ribs #2

and #7. The correct nuts for this installation are BACN10HR12 nuts while NAS1804-12 nuts were found to have

been installed. The torque for the BACN10HR12 nuts is 3300 to 4300 in-lbs while the torque for the NAS1804-12

nuts is 2400 to 3500 in-lbs. Overtorqued NAS1804-12 nuts are at risk of fracture. Fractured nuts may create a

breach in the cap seal and allow moisture to contact the nuts, resulting in corrosion. Nut fractures could lead to

additional nut or bolt fractures within that support rib. Additional fractures can cause the joint to be compromised.

This service bulletin provides instructions to inspect the nuts and bolts common to the #1, #2, #7 and #8 outboard

flap support ribs and replaces any cracked, corroded or incorrect nuts and/or bolts that are found.

Boeing Fleet Team Digest (FTD) 767 FTD 57-12003 is related to this service bulletin.

Boeing Service Related Problem (SRP) 767-SRP-57-0257 is related to this service bulletin.

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

information.

Planning Data Affected Reference

Spares Affected No Paragraph 1.A.2., Spares Affected

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Planning Data Affected Reference

Paragraph 1.E., Compliance and Paragraph

1.F., Approval

AD Related Yes

Weight and Balance Change No Paragraph 1.H., Weight and Balance Changes

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

Publications Affected No Paragraph 1.K., Publications Affected

Airplane Flight Operations Affected (Flight Crew No 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

Group 1:

Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7 and #8.

Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and corrosion. If any cracked

or corroded fasteners are found, replace all four fasteners on that Support Rib. Repeat the Detailed Inspection.

Install new bolts, washers and nuts.

Group 2-3:

Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7 and #8.

Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and corrosion. If any

corroded fasteners are found, replace that fastener. If any cracked fasteners are found, replace all four fasteners

on that Support Rib. Repeat the Detailed Inspection. Make sure the correct nuts are installed. If any incorrect

nuts are found, replace the nut, bolt and washers.

EFFECTIVITY

767-200, -300, -300F and -400ER airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.

COMPLIANCE

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

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

mandatory.

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of May 29, 2012. Please refer to Paragraph

2.B., Industry Support Information.

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ALERT ALERT
MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

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ALERT ALERT
Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-57A0131

Original Issue: October 30, 2012

ATA System: 5750

SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Outboard Flap Support Rib Nut

Fracture Inspection

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 D624T001 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

GROUP CONFIGURATION DESCRIPTION

767-200 and-300 Airplanes that have a line number 1 through 200.

These airplanes were delivered with H-11 bolts installed in the

Outboard Flap Support Ribs.

1 -

767-200, -300 and -300F Airplanes that have a line number 201

through 920. These airplanes were delivered with BACB30US* bolts

installed in the Outboard Flap Support Ribs.

2 -

767-400ER Airplanes that have a line number 758 through 878. These

airplanes were delivered with BACB30US* bolts installed in the

Outboard Flap Support Ribs.

3 -

Airplane Models:

767-200, 767-300, 767-300F, 767-400ER

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Variable Number Group

VA001 - VA020 1

VA301 - VA315 1

VA501 - VA530 1

VA701 - VA712 1

VA713 - VA719 2

VA801 - VA810 1

VB001 - VB002 1

VB051 - VB055 1

VB101 - VB125 1

VB201 - VB202 1

VB251 - VB253 1

VB281 - VB284 1

VB301 - VB302 1

VB321 - VB325 1

VB326 - VB332 2

VB371 - VB373 1

VB401 1

VB441 - VB444 2

VE001 - VE003 1

VE021 - VE023 1

VE041 - VE043 1

VE061 - VE069 1

VE083 - VE084 1

VE085 - VE086 2

VE101 - VE103 1

VE104 2

VE116 - VE117 1

VE118 2

VE121 - VE126 1

VE141 - VE145 1

VE146 - VE152 2

VE171 - VE172 2

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ALERT ALERT
Variable Number Group

VF001 - VF002 2

VF041 - VF042 2

VF051 2

VF061 - VF062 2

VF071 - VF072 2

VF091 - VF093 2

VF101 - VF102 2

VF161 - VF162 2

VF171 - VF172 2

VF180 - VF184 2

VF251 2

VK001 - VK006 1

VK007 - VK016 2

VK021 - VK022 1

VK031 - VK040 1

VK041 - VK056 2

VK081 - VK085 1

VK086 - VK113 2

VK131 - VK133 2

VK141 - VK148 2

VK161 - VK164 2

VK171 2

VK181 2

VK186 2

VL001 1

VL002 - VL006 2

VL011 1

VL701 - VL703 2

VL751 - VL755 2

VL806 - VL807 2

VL871 - VL873 2

VL891 - VL900 2

VL911 - VL914 2

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ALERT ALERT
Variable Number Group

VL931 - VL932 2

VL941 2

VN001 - VN041 2

VN051 - VN064 2

VN081 - VN099 2

VN111 - VN127 2

VN130 - VN137 2

VN151 - VN158 2

VN163 - VN168 2

VN171 - VN174 2

VN191 - VN198 2

VN211 - VN212 2

VN221 - VN225 2

VN231 - VN234 2

VN241 - VN243 2

VN251 - VN276 2

VN291 - VN293 2

VN301 - VN314 2

VN371 - VN372 2

VN376 2

VN381 - VN388 2

VN421 - VN427 2

VN436 2

VN471 - VN472 2

VN491 - VN513 2

VN531 - VN532 2

VN536 - VN537 2

VN541 - VN542 2

VN546 - VN547 2

VN551 2

VN556 - VN557 2

VN561 - VN562 2

VN631 - VN638 2

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Variable Number Group

VN651 - VN658 2

VN671 - VN672 2

VN676 2

VN681 - VN691 2

VN731 - VN732 2

VN751 - VN753 2

VN791 - VN792 2

VN811 - VN813 2

VN921 - VN922 2

VN931 - VN936 2

VN951 - VN953 2

VN966 - VN972 2

VQ001 - VQ021 3

VQ071 - VQ086 3

VR051 - VR060 2

VR081 2

VR084 2

VR086 2

VR201 - VR211 2

VR251 2

VR256 - VR260 2

VR401 2

VR421 - VR423 2

VR426 2

VR441 2

VR461 2

VR471 - VR472 2

VS051 - VS056 2

VS061 2

VS066 - VS070 2

VS073 - VS078 2

VS091 - VS104 2

VS111 - VS113 2

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ALERT ALERT
Variable Number Group

VS131 - VS133 2

VS136 - VS137 2

VS176 - VS177 2

VS186 - VS187 2

VS196 - VS203 2

VS206 - VS208 2

VS211 2

VS216 - VS217 2

VS231 2

VS246 - VS248 2

VS261 - VS263 2

VS266 - VS274 2

VS291 - VS293 2

VS301 - VS303 2

VS306 - VS311 2

VS316 2

VS321 - VS324 2

VS331 - VS333 2

VS336 - VS337 2

VS366 - VS367 2

VS381 - VS382 2

VS391 - VS392 2

VS401 2

VS426 - VS428 2

VS466 - VS472 2

VS486 2

VS496 - VS497 2

VS506 - VS507 2

VS526 2

VS546 - VS549 2

VS701 - VS708 2

VS721 - VS730 2

VS751 - VS759 2

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Variable Number Group

VS821 - VS825 2

VS841 - VS844 2

VS861 2

VS881 2

VT501 2

VW701 - VW721 2

VW851 2

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Accomplishment of this service bulletin will find and replace any cracked, corroded or incorrect nuts

and bolts on the #1, #2, #7 and #8 outboard flap support ribs. Cracked, corroded or incorrect nuts and

bolts could lead to additional nut and bolt damage in the joint which could result in loss of the outboard

flap. Continued safe flight and landing could be affected after the departure of a flap during takeoff or

landing.

An operator reported two fractured and corroded nuts on the outboard flap, support rib #2 on an airplane

with 54,953 hours and 49,519 cycles. It was found that the incorrect nuts (QTY 8) were installed on

support ribs #2 and #7. The correct nuts for this installation are BACN10HR12 nuts while NAS1804-12

nuts were found to have been installed. The torque for the BACN10HR12 nuts is 3300 to 4300 in-lbs

while the torque for the NAS1804-12 nuts is 2400 to 3500 in-lbs. Overtorqued NAS1804-12 nuts are

at risk of fracture. Fractured nuts may create a breach in the cap seal and allow moisture to contact

the nuts, resulting in corrosion. Nut fractures could lead to additional nut or bolt fractures within that

support rib. Additional fractures can cause the joint to be compromised.

This service bulletin provides instructions to inspect the nuts and bolts common to the #1, #2, #7 and

#8 outboard flap support ribs and replaces any cracked, corroded or incorrect nuts and/or bolts that

are found.

Boeing Fleet Team Digest (FTD) 767 FTD 57-12003 is related to this service bulletin.

Boeing Service Related Problem (SRP) 767-SRP-57-0257 is related to this service bulletin.

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ALERT ALERT
D. Description

Group 1:

Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7

and #8. Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and

corrosion. If any cracked or corroded fasteners are found, replace all four fasteners on that Support

Rib. Repeat the Detailed Inspection. Install new bolts, washers and nuts.

Group 2-3:

Do a Detailed Inspection of the sealant on the nuts common to Outboard Flap Support Ribs #1, #2, #7

and #8. Remove sealant if damaged and do a Detailed Inspection of the fasteners for cracks and

corrosion. If any corroded fasteners are found, replace that fastener. If any cracked fasteners are found,

replace all four fasteners on that Support Rib. Repeat the Detailed Inspection. Make sure the correct

nuts are installed. If any incorrect nuts are found, replace the nut, bolt and washers.

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

Group 1:

Affected Maintenance Zones

Model Zone

767-200, 767-300 572, 573, 672, 673

Group 2:

Affected Maintenance Zones

Model Zone

767-200, 767-300, 767-300F 572, 573, 672, 673

Group 3:

Affected Maintenance Zones

Model Zone

767-400ER 572, 573, 672, 673

E. Compliance

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

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

service bulletin mandatory.

Accomplish the required actions, based on the applicable conditions, in Tables 1 and 2, in accordance

with Paragraph 3. Accomplishment Instructions.

Evaluate the condition of each fastener of the #1, #2, #7 and #8 Support Ribs separately in Parts 1, 2

and 4. The conditions shown are for each fastener.

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ALERT ALERT
Group 1:

Table 1: Outboard Flap Support Rib Fastener Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 12 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 1 - Cap Seal Detailed Inspection

-ORDo Part 3 - All Fastener

Replacement within a

Support Rib for #1, #2, #7

and #8 Support Ribs (a)

All Airplanes

Do Part 2 - Fastener De- Before further flight -

tailed Inspection

Part 1, Condition 1: Damaged sealant found

Repeat Part 1 - Cap Seal - 12 Months (b)

Detailed Inspection

Part 1, Condition 2: No

damaged sealant found

-ANDWithin 36 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 3 - All Fastener

Replacement within a

Support Rib (b)

Do Part 3 - All Fastener Before further flight -

Replacement within a

Support Rib where the

cracked nut, bolt or

washer was found (b)

Part 2, Condition 3:

Cracked nut, bolt or washer

found

Do Part 3 - All Fastener Before further flight -

Replacement within a

Support Rib where the

corroded nut, bolt or

washer was found (b)

Part 2, Condition 4: Corrosion is found on the nut,

bolt or washers and no

crack found

Cap Seal Nut with BMS Before further flight -

5-95

Part 2, Condition 5: No

cracks or corrosion on the

nut, bolt or washers is

found -ANDRepeat Part 1 - Cap Seal - 12 Months (b)

Detailed Inspection

-ANDWithin 36 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 3 - All Fastener

Replacement within a

Support Rib (b)

(a) Terminating Action is complete once Part 3 has been done on each Support Rib.

(b) Terminating Action to the Part 1 inspections of each Support Rib is accomplishment of

Part 3 on each Support Rib.

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ALERT ALERT
Group 2-3:

Table 2: Outboard Flap Support Rib Fastener Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 12 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 1 - Cap Seal Detailed InspectionAll Airplanes

Do Part 2 - Fastener De- Before further flight -

tailed Inspection

Part 1, Condition 1: Damaged sealant found

Repeat Part 1 - Cap Seal - 12 Months (a)

Detailed Inspection

Part 1, Condition 2: No

damaged sealant found

-ANDWithin 48 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 4 - Detailed Inspection for Nut Type (a)

Do Part 3 - All Fastener Before further flight -

Replacement within a

Support Rib where the

cracked nut, bolt or

washer was found (b)

Part 2, Condition 3:

Cracked nut, bolt or washer

found

Do Part 5 - Singular Fas- Before further flight -

tener Replacement at the

fastener location where

the corrosion was found

Part 2, Condition 4: Corrosion is found on the nut,

bolt or washers and no

crack found

-ANDDo Part 4 - Detailed Inspection for Nut Type on

all other fasteners within

the affected Support Rib

(c)

Cap Seal Nut with BMS Before further flight -

5-95

Part 2, Condition 5: No

cracks or corrosion on the

nut, bolt or washers is

found -ANDRepeat Part 1 - Cap Seal - 12 Months (a)

Detailed Inspection

-ANDWithin 48 Months -

after the Original

Issue Date of this

Service Bulletin

Do Part 4 - Detailed Inspection for Nut Type (a)

Do Part 5 - Singular Fas- Before further flight -

tener Replacement

Part 4, Condition 6: Incorrect nut installed

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ALERT ALERT
Group 2-3:

Table 2: Outboard Flap Support Rib Fastener Inspection and Replacement

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Cap Seal Nut with BMS Before further flight -

5-95

Part 4, Condition 7: Correct

nut installed

(a) Terminating Action to the Part 1 inspections of each Support Rib is accomplishment of

Part 3 on each Support Rib or accomplishment of Part 4 and its follow on actions from

Condition 6 or Condition 7, as applicable, on each Support Rib.

(b) Terminating Action for affected Support Rib.

(c) Terminating Action for affected Support Rib requires accomplishment of Part 5 at affected

fastener locations and accomplishment of Part 4 and its follow on actions from Condition

6 or Condition 7, as applicable, at all other locations.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved, as well as European

Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved

airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on

the airplane in its original Boeing delivery configuration or as modified by other approved Boeing

changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Group 1:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Part 1: FIGURE 1 1 0.40 0.40

Part 1: FIGURE 2 1 0.40 0.40

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Group 1:

Task Number of Persons Task Hours Elapsed Hours

Part 1: FIGURE 3 1 0.40 0.40

Part 1: FIGURE 4 1 0.40 0.40

Part 2: FIGURE 5 1 0.15 0.15

Part 3: FIGURE 6 1 1.80 (a) 1.80 (a)

Part 3: FIGURE 7 1 1.80 (a) 1.80 (a)

Part 3: FIGURE 8 1 1.80 (a) 1.80 (a)

Part 3: FIGURE 9 1 1.80 (a) 1.80 (a)

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 2.75 2.75

(a) Add time to total if repairs are required.

Group 2-3:

Task Number of Persons Task Hours Elapsed Hours

Open Access 1 0.50 0.50

Part 1: FIGURE 1 1 0.40 0.40

Part 1: FIGURE 2 1 0.40 0.40

Part 1: FIGURE 3 1 0.40 0.40

Part 1: FIGURE 4 1 0.40 0.40

Part 2: FIGURE 5 1 0.15 0.15

Part 4: FIGURE 10 1 0.05 0.05

Part 4: FIGURE 11 1 0.05 0.05

Part 5: FIGURE 6 1 0.30 (a) 0.30 (a)

Part 5: FIGURE 7 1 0.30 (a) 0.30 (a)

Part 5: FIGURE 8 1 0.30 (a) 0.30 (a)

Part 5: FIGURE 9 1 0.30 (a) 0.30 (a)

Close Access 1 0.50 0.50

TOTAL FOR EACH AIRPLANE 2.85 2.85

(a) Add time to total if repairs are required.

H. Weight and Balance Changes

None.

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ALERT ALERT
I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Letter 767-SL-51-036

b. Boeing Service Related Problem (SRP) 767-SRP-57-0257

c. Service Bulletin Index D624T001

d. Standard Overhaul Practices Manual (SOPM) 20-50-19

e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19

f. 767 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-27, 28-11-00, 28-26-00

g. 767 Fleet Team Digest (FTD) 57-12003

h. 767 Non-Destructive Testing (NDT) Manual Part 6, Subject 51-00-04, Part 6, Subject 51-00-11,

Part 6, Subject 51-00-16

i. 767-400 Aircraft Maintenance Manual (AMM) 27-51-00, 27-51-27, 28-11-00, 28-26-00

2. Data Supplied with this Service Bulletin:

None.

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

None.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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ALERT ALERT
M. Software Accomplishment Summary

Not affected.

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in the kits in Paragraph 2.C., Parts Necessary

for Each Airplane . As an alternative, operators can purchase the parts from Boeing Spares. The Boeing

price data shown below is given for planning purposes. Supply data can be given if requested. The

parts are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.

Prices are in United States Dollars. Terms: Net 30 days

Reference this service bulletin and submit your purchase order by one of these methods:

1. Order on-line via ATA Spec 2000 or The Boeing PART Page

2. Fax to (206) 662-7145

Group 1-2:

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 original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

August 30, 1 149 $2,553.00

2012

TOP KIT - 767 Wing

Flap Support Nut Fracture

015T1882-1

February 6, 48

2013

Group 3:

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 original issue

date of this Service Bulletin (US

Dollars)

ROLT as of the

original issue

date of this Service Bulletin (Calendar Days)

Kit Number Name Date QTY

August 30, 1 149 $2,553.00

2012

TOP KIT - 767 Wing

Flap Support Nut Fracture

015T1882-3

B. Industry Support Information

Boeing warranty remedies are available for 767airplanes in warranty as of May 29, 2012. For task hour

reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Commercial

Airplanes Group - Warranties. The kits for airplanes in warranty as of that date will be supplied at no

charge. Send a purchase order for the kits to Boeing Spares. Please refer to this service bulletin number

and reference the airplane variable numbers in your purchase order.

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
C. Parts Necessary for Each Airplane

1. Kits/Parts

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

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

ALL

Kit 015T1882

Existing Part Notes

Number

New Part Number Qty Name

-1 -3

TOP KIT - 767

Wing Flap Support

Nut Fracture

015T1882-1 - .

TOP KIT - 767

Wing Flap Support

Nut Fracture

015T1882-3 . -

BOLT, 12 PT

HEAD

BACB30US10K47 2 .

BOLT, 12 PT

HEAD

BACB30US10K48 4 .

BOLT, 12 PT

HEAD

BACB30US10K50 2 .

BACB30US12K46 . 2 BOLT

BOLT, 12 PT

HEAD

BACB30US12K47 . 4

BOLT, 12 PT

HEAD

BACB30US12K48 . 2

BOLT, 12 PT

HEAD

BACB30US12K49 2 2

BOLT, 12 PT

HEAD

BACB30US12K50 2 2

BOLT, 12 PT

HEAD

BACB30US12K51 4 4

BACN10HR10CD 8 . NUT

SELF-LOCKING

NUT

BACN10HR12CD 8 16

BACW10BP10DP 8 . WASHER

BACW10BP12DP 8 8 WASHER, PLAIN

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ALERT ALERT
ALL

Kit 015T1882

Existing Part Notes

Number

New Part Number Qty Name

-1 -3

WASHER, SELFALIGNBACW10CA10CCS 8 .

WASHER, SELFALIGNBACW10CA10CVS 8 .

WASHER, SELFALIGNBACW10CA12CCS 8 16

WASHER, SELFALIGNBACW10CA12CVS 8 16

(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.

2. Parts and Materials Supplied by the Operator

The following parts or materials are necessary to do the change in this service bulletin. Parts and

materials in the manuals given in Paragraph 1.J., References, can also be necessary. Examine

operator part and material supply to make sure all necessary parts and materials are available.

Group 1-2:

Part Number / QTY Name Notes

Specification

BACB30US10K47 2 BOLT, 12 POINT HEAD (c)

BACB30US10K47X 2 BOLT, 12 POINT HEAD (a)

BACB30US10K47Y 1 BOLT, 12 POINT HEAD (a)

BACB30US10K48 4 BOLT, 12 POINT HEAD (c)

BACB30US10K48X 4 BOLT, 12 POINT HEAD (a)

BACB30US10K48Y 2 BOLT, 12 POINT HEAD (a)

BACB30US10K50 2 BOLT, 12 POINT HEAD (c)

BACB30US10K50X 2 BOLT, 12 POINT HEAD (a)

BACB30US10K50Y 1 BOLT, 12 POINT HEAD (a)

BACW10CA10CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA101CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA102CVS 6 WASHER, SELF-ALIGNING (a)

BACW10CA10CCS 8 WASHER, SELF-ALIGNING (c)

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ALERT ALERT
Group 1-2:

Part Number / QTY Name Notes

Specification

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP10DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP101DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP102DP 6

BACN10HR10CD 8 NUT, SELF-LOCKING (c)

BACB30US12K49 2 BOLT, 12 POINT HEAD (c)

BACB30US12K49X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K49Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K50 2 BOLT, 12 POINT HEAD (c)

BACB30US12K50X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K50Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K51 4 BOLT, 12 POINT HEAD (c)

BACB30US12K51X 4 BOLT, 12 POINT HEAD (a)

BACB30US12K51Y 2 BOLT, 12 POINT HEAD (a)

BACW10CA12CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA121CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA122CVS 6 WASHER, SELF-ALIGNING (a)

BACW10CA12CCS 8 WASHER, SELF-ALIGNING (c)

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP12DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP121DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP122DP 6

BACN10HR12CD 8 NUT, SELF-LOCKING (c)

BMS 5-95 - Sealant (b)

BMS 5-45 (BMS 5- - Fuel Tank Sealant (b)

26 optional)

(a) Refer to 767 Structural Repair Manual Chapter 51 for alternate fasteners.

(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

(c) Part is in kit.

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ALERT ALERT
Group 3:

Part Number / QTY Name Notes

Specification

BACB30US12K46 2 BOLT, 12 POINT HEAD (c)

BACB30US12K46X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K46Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K47 4 BOLT, 12 POINT HEAD (c)

BACB30US12K47X 4 BOLT, 12 POINT HEAD (a)

BACB30US12K47Y 2 BOLT, 12 POINT HEAD (a)

BACB30US12K48 2 BOLT, 12 POINT HEAD (c)

BACB30US12K48X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K48Y 1 BOLT, 12 POINT HEAD (a)

BACW10CA12CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA121CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA122CVS 6 WASHER, SELF-ALIGNING (a)

BACW10CA12CCS 8 WASHER, SELF-ALIGNING (c)

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP12DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP121DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP122DP 6

BACN10HR12CD 8 NUT, SELF-LOCKING (c)

BACB30US12K49 2 BOLT, 12 POINT HEAD (c)

BACB30US12K49X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K49Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K50 2 BOLT, 12 POINT HEAD (c)

BACB30US12K50X 2 BOLT, 12 POINT HEAD (a)

BACB30US12K50Y 1 BOLT, 12 POINT HEAD (a)

BACB30US12K51 4 BOLT, 12 POINT HEAD (c)

BACB30US12K51X 4 BOLT, 12 POINT HEAD (a)

BACB30US12K51Y 2 BOLT, 12 POINT HEAD (a)

BACW10CA12CVS 8 WASHER, SELF-ALIGNING (c)

BACW10CA121CVS 8 WASHER, SELF-ALIGNING (a)

BACW10CA122CVS 6 WASHER, SELF-ALIGNING (a)

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ALERT ALERT
Group 3:

Part Number / QTY Name Notes

Specification

BACW10CA12CCS 8 WASHER, SELF-ALIGNING (c)

WASHER, PLAIN AND COUNTER- (c)

SUNK

BACW10BP12DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP121DP 8

WASHER, PLAIN AND COUNTER- (a)

SUNK

BACW10BP122DP 6

BACN10HR12CD 8 NUT, SELF-LOCKING (c)

BMS 5-95 - Sealant (b)

BMS 5-45 (BMS 5- - Fuel Tank Sealant (b)

26 optional)

(a) Refer to 767 Structural Repair Manual Chapter 51 for alternate fasteners.

(b) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS)

for supplier data.

(c) Part is in kit.

3. Parts Modified and Reidentified

None.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

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

definition of the acronyms.

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

3. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in Structural Repair

Manual (SRM) Chapter 51

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

4. Use the approved fastener and process material substitutions in accordance with

SRM Chapter 51.

5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures,

and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

6. The necessary conditions for selection of clamp type and size are included in SWPM

20-10-12. If any wire bundle support clamp specified in this service bulletin does not

make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted

procedure to select a clamp that fits correctly.

7. 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.

8. 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.

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ALERT ALERT
9. 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.

10. Boeing Service Letter 767-SL-51-036 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.

11. Refer to Appendix A for Applicable Part Numbers and Quantities.

12. 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.

13. 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.

14. 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.

15. Shaded areas in Figures are reference only. Shaded areas in Figures may look

different than your airplane.

16. The term "fastener" used in this service bulletin is defined as the combination of a

bolt, two washers and a nut.

17. Evaluate the condition of each fastener of the #1, #2, #7 and #8 Support Ribs

separately in Parts 1, 2 and 4. The conditions shown are for each fastener.

Terminating Action applies to each Support Rib separately.

B. WORK INSTRUCTIONS

1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 or 767-400 AMM

27-51-00 as an accepted procedure, as applicable.

2. Do Part 1 - Cap Seal Detailed Inspection.

a. Condition 1: Damaged sealant found

(1) Do Part 2 - Fastener Detailed Inspection.

(a) Condition 3: Cracked nut, bolt or washer found

1) Do Part 3 - All Fastener Replacement within a Support Rib on the Support Rib

where the cracked nut, bolt or washer was found. (Terminating Action for affected

Support Rib)

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ALERT ALERT
(b) Condition 4: Corrosion is found on the nut, bolt or washers and no crack found

1) Group 1:

Do Part 3 - All Fastener Replacement within a Support Rib on the Support Rib

where the corroded nut, bolt or washer was found. (Terminating Action for

affected Support Rib)

2) Group 2-3:

Do Part 5 - Singular Fastener Replacement at the fastener location where the

corrosion was found.

AND

Do Part 4 - Detailed Inspection for Nut Type on all other fasteners within the

Support Rib.

a) Condition 6: Incorrect nut installed

{1} Do Part 5 - Singular Fastener Replacement. (Terminating Action to

Part 1 Inspection for affected fastener location)

b) Condition 7: Correct nut installed

{1} Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an

accepted procedure. (Terminating Action to Part 1 Inspection for

affected fastener location)

NOTE: Terminating Action for affected Support Rib requires

accomplishment of Part 5 at affected fastener locations and

accomplishment of Part 4 and its follow on actions from

Condition 6 or Condition 7, as applicable, at all other locations.

(c) Condition 5: No cracks or corrosion on the nut, bolt or washers is found

1) Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an accepted

procedure.

2) Repeat Part 1 - Cap Seal Detailed Inspection at the time given in Paragraph

1.E., Compliance.

3) Group 1:

Do Part 3 - All Fastener Replacement within a Support Rib at the time given in

Paragraph 1.E., Compliance. (Terminating Action for affected Support Rib)

4) Group 2-3:

Do Part 4 - Detailed Inspection for Nut Type at the time given in Paragraph 1.E.,

Compliance.

a) Condition 6: Incorrect nut installed

{1} Do Part 5 - Singular Fastener Replacement. (Terminating Action to

Part 1 Inspection for affected fastener location)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
b) Condition 7: Correct nut installed

{1} Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an

accepted procedure. (Terminating Action to Part 1 Inspection for

affected fastener location)

NOTE: Terminating Action for affected Support Rib requires

accomplishment of Terminating Action for every fastener

location within the Support Rib.

b. Condition 2: No damaged sealant found

(1) Repeat Part 1 - Cap Seal Detailed Inspection at the time given in Paragraph 1.E.,

Compliance.

(2) Group 1:

Do Part 3 - All Fastener Replacement within a Support Rib at the time given in Paragraph

1.E., Compliance. (Terminating Action for affected Support Rib)

(3) Group 2-3:

Do Part 4 - Detailed Inspection for Nut Type at the time given in Paragraph 1.E.,

Compliance.

(a) Condition 6: Incorrect nut installed

1) Do Part 5 - Singular Fastener Replacement. (Terminating Action to Part 1

Inspection for affected fastener location)

(b) Condition 7: Correct nut installed

1) Cap seal the nut with BMS 5-95. Refer to SOPM 20-50-19 as an accepted

procedure. (Terminating Action to Part 1 Inspection for affected fastener location)

NOTE: Terminating Action for affected Support Rib requires accomplishment of

Terminating Action for every fastener location within the Support Rib.

3. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 or 767-400 AMM 27-51-00

as an accepted procedure, as applicable.

4. Put the airplane in serviceable condition.

Part 1 - Cap Seal Detailed Inspection

1. Do a Detailed Inspection of the cap seal on the nuts common to the Outboard Flap Support Ribs

by support rib number for damaged sealant in accordance with the figures below:

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 1 FIGURE 2 FIGURE 3 FIGURE 4

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Part 2 - Fastener Detailed Inspection

1. Do a Detailed Inspection of the affected fastener for cracks and corrosion in accordance with

FIGURE 5.

Part 3 - All Fastener Replacement within a Support Rib

1. Defuel and Purge fuel tank as required for entry. Refer to 767 AMM 28-26-00 and 767 AMM

28-11-00 or 767-400 AMM 28-26-00 and 767-400 AMM 28-11-00 as accepted procedures, as

applicable.

2. Remove the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an

accepted procedure, as applicable.

NOTE: The outboard flaps do not need to be removed if only one fastener at a time is removed

and replaced.

3. Replace all four fasteners for the affected Support Rib in accordance with the figures below, as

applicable (Terminating Action for affected Support Rib):

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 6 FIGURE 7 FIGURE 8 FIGURE 9

4. Install the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an accepted

procedure, as applicable.

Group 2-3:

Part 4 - Detailed Inspection for Nut Type

1. Measure the dimensions of the nut for the correct type in accordance with the figures below, as

applicable:

Group 2:

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 10 FIGURE 11 FIGURE 11 FIGURE 10

Group 3:

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 11 FIGURE 11 FIGURE 11 FIGURE 11

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Part 5 - Singular Fastener Replacement

1. Defuel and Purge fuel tank as required for entry. Refer to 767 AMM 28-26-00 and 767 AMM

28-11-00 or 767-400 AMM 28-26-00 and 767-400 AMM 28-11-00 as accepted procedures, as

applicable.

2. Remove the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an

accepted procedure, as applicable.

NOTE: The outboard flaps do not need to be removed if only one fastener at a time is removed

and replaced.

3. Replace the affected fastener in accordance with the figures below, as applicable:

Left Wing Right Wing

Support Rib #1 Support Rib #2 Support Rib #7 Support Rib #8

FIGURE 6 FIGURE 7 FIGURE 8 FIGURE 9

4. Install the Outboards Flaps. Refer to 767 AMM 27-51-27 or 767-400 AMM 27-51-27 as an accepted

procedure, as applicable.

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1

(SHEET 1 OF 2)

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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 this figure.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.

FIGURE 1: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 1

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131

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 this figure.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.

FIGURE 2: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 2

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131

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 this figure.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.

FIGURE 3: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 7

(SHEET 2 OF 2)

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ALERT ALERT
FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131

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 this figure.

Step Task Name Identification Qty More Data

Do a Detailed Inspection of the sealant

around the nut for

damage. (a)

1 Inspect Cap Seal - 4

(a) Damaged sealant includes sealant that is cracked, missing, wrinkled, loose or separated.

FIGURE 4: CAP SEAL DETAILED INSPECTION FOR SUPPORT RIB # 8

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131

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 for one fastener location. The QTY may vary from 1 to 4 on each support rib depending

on the condition of each fastener location.

Step Task Name Identification Qty More Data

only from fastener

locations where

damaged sealant

was found.

1 Remove Cap Seal - 1

Do a Detailed Inspection for corrosion

and cracks on the

nut, bolt and washers.

2 Inspect Fastener - 1

FIGURE 5: FASTENER DETAILED INSPECTION

(SHEET 1 OF 1)

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ALERT ALERT
FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

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 for one fastener location. The QTY may vary from 1 to 4 on each support rib depending

on the condition of each fastener location.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection of the fastener hole for cracks

and corrosion in accordance with 767

NDT Manual Part 6,

Subject 51-00-04,

767 NDT Part 6,

Subject 51-00-11 or

767 NDT Part 6,

Subject 51-00-16.

2 Inspect Fastener Hole - 4

to remove cracks

and corrosion. If no

cracks and corrosion

found, ream hole to

next available fastener hole size as

shown in APPENDIX

A. Contact Boeing if

cracks and corrosion

cannot be removed

within the allowable

hole sizes and do

the repair.

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance with 767 NDT

Manual Part 6, Subject 51-00-04, 767

NDT Part 6, Subject

51-00-11 or 767

NDT Part 6, Subject

51-00-16.

Inspect Fastener Hole - 4

FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

FIGURE 6: FASTENER REPLACEMENTS FOR SUPPORT RIB # 1

(SHEET 4 OF 4)

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ALERT ALERT
FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

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 for one fastener location. The QTY may vary from 1 to 4 on each support rib depending

on the condition of each fastener location.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection on the fastener hole for cracks

and corrosion in accordance with 767

NDT Manual Part 6,

Subject 51-00-04,

767 NDT Part 6,

Subject 51-00-11 or

767 NDT Part 6,

Subject 51-00-16.

2 Inspect Fastener Hole - 4

to remove cracks

and corrosion. If no

cracks and corrosion

found, ream hole to

next available fastener hole size as

shown in APPENDIX

A. Contact Boeing if

cracks and corrosion

cannot be removed

within the allowable

hole sizes and do

the repair.

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance with 767 NDT

Manual Part 6, Subject 51-00-04, 767

NDT Part 6, Subject

51-00-11 or 767

NDT Part 6, Subject

51-00-16.

Inspect Fastener Hole - 4

FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

FIGURE 7: FASTENER REPLACEMENTS FOR SUPPORT RIB # 2

(SHEET 4 OF 4)

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ALERT ALERT
FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

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 for one fastener location. The QTY may vary from 1 to 4 on each support rib depending

on the condition of each fastener location.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection on the fastener hole for cracks

and corrosion in accordance with 767

NDT Manual Part 6,

Subject 51-00-04,

767 NDT Part 6,

Subject 51-00-11 or

767 NDT Part 6,

Subject 51-00-16.

2 Inspect Fastener Hole - 4

to remove cracks

and corrosion. If no

cracks and corrosion

found, ream hole to

next available fastener hole size as

shown in APPENDIX

A. Contact Boeing if

cracks and corrosion

cannot be removed

within the allowable

hole sizes and do

the repair.

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance with 767 NDT

Manual Part 6, Subject 51-00-04, 767

NDT Part 6, Subject

51-00-11 or 767

NDT Part 6, Subject

51-00-16.

Inspect Fastener Hole - 4

FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

FIGURE 8: FASTENER REPLACEMENTS FOR SUPPORT RIB # 7

(SHEET 4 OF 4)

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ALERT ALERT
FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

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 for one fastener location. The QTY may vary from 1 to 4 on each support rib depending

on the condition of each fastener location.

Step Task Name Identification Qty More Data

1 Remove Fastener - 4

FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
Step Task Name Identification Qty More Data

Do a High Frequency Eddy Current Inspection on the fastener hole for cracks

and corrosion in accordance with 767

NDT Manual Part 6,

Subject 51-00-04,

767 NDT Part 6,

Subject 51-00-11 or

767 NDT Part 6,

Subject 51-00-16.

2 Inspect Fastener Hole - 4

to remove cracks

and corrosion. If no

cracks and corrosion

found, ream hole to

next available fastener hole size as

shown in APPENDIX

A. Contact Boeing if

cracks and corrosion

cannot be removed

within the allowable

hole sizes and do

the repair.

3 Ream Fastener Hole - 4

Do a High Frequency Eddy Current Inspection of the fastener hole to make

sure all cracks and

corrosion has been

removed in accordance with 767 NDT

Manual Part 6, Subject 51-00-04, 767

NDT Part 6, Subject

51-00-11 or 767

NDT Part 6, Subject

51-00-16.

Inspect Fastener Hole - 4

FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 3 OF 4)

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ALERT ALERT
Step Task Name Identification Qty More Data

wet with BMS 5-95

sealant. Refer to

APPENDIX A for applicable bolt part

numbers.

4 Install (New) Bolt - 4

Refer to APPENDIX

A for washer quantities and applicable

part numbers.

Install (New) Washer - -

Refer to APPENDIX

A for applicable nut

part numbers.

Install (New) Nut - 4

Cap seal nuts external to the wing fuel

tank. Refer to SOPM

20-50-19 as an accepted procedure.

5 Apply Sealant BMS 5-95 4

Cap seal bolt heads

internal to the wing

fuel tank. Refer to

SOPM 20-50-19 as

an accepted procedure.

BMS 5-45 (BMS 5-26 4

optional)

Apply Sealant

FIGURE 9: FASTENER REPLACEMENTS FOR SUPPORT RIB # 8

(SHEET 4 OF 4)

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ALERT ALERT
This Figure applies only to: Group 2.

FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131

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 for one fastener location. The QTY may vary from 1 to 4 on each support rib depending

on the condition of each fastener location.

Step Task Name Identification Qty More Data

and compare to examples above to find

if correct or incorrect

nut is installed.

1 Measure Nut - 1

FIGURE 10: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 2 OF 2)

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ALERT ALERT
This Figure applies only to: Group 2-3.

FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-57A0131

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 for one fastener location. The QTY may vary from 1 to 4 on each support rib depending

on the condition of each fastener location.

Step Task Name Identification Qty More Data

and compare to examples above to find

if correct or incorrect

nut is installed.

1 Measure Nut - 1

FIGURE 11: NUT MEASUREMENT FOR CORRECT TYPE

(SHEET 2 OF 2)

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767-57A0131

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
GROUP 1-2: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia More Data

0.6245 -

0.6255

A BACB30US10K47 1 BOLT, 12 POINT HEAD

0.6401 - Optional.

0.6411

BACB30US10K47X 1 BOLT, 12 POINT HEAD

0.6557 - Optional.

0.6567

BACB30US10K47Y 1 BOLT, 12 POINT HEAD

0.6245 -

0.6255

B BACB30US10K48 2 BOLT, 12 POINT HEAD

0.6401 - Optional.

0.6411

BACB30US10K48X 2 BOLT, 12 POINT HEAD

0.6557 - Optional.

0.6567

BACB30US10K48Y 1 BOLT, 12 POINT HEAD

0.6245 -

0.6255

C BACB30US10K50 1 BOLT, 12 POINT HEAD

0.6401 - Optional.

0.6411

BACB30US10K50X 1 BOLT, 12 POINT HEAD

0.6557 - Optional.

0.6567

BACB30US10K50Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US10K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA10CVS 4

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 1 OF 6)

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767-57A0131

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
GROUP 1-2: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia More Data

Use with BACB30US10K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA101CVS 4

Use with BACB30US10K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA102CVS 3

Use with any

BACB30US10K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA10CCS 4

Use with BACB30US10K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP10DP 4

Use with BACB30US10K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP101DP 4

Use with BACB30US10K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP102DP 3

Use with any

BACB30US10K bolt.

Torque to 1900 - 2300 inlbs.

BACN10HR10CD 4 NUT, SELF-LOCKING -

GROUP 1-2: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia More Data

0.7495 -

0.7505

A BACB30US12K49 1 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K49X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K49Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

B BACB30US12K50 1 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K50X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K50Y 1 BOLT, 12 POINT HEAD

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 2 OF 6)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
GROUP 1-2: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia More Data

0.7495 -

0.7505

C BACB30US12K51 2 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K51X 2 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K51Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US12K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CVS 4

Use with BACB30US12K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA121CVS 4

Use with BACB30US12K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA122CVS 3

Use with any

BACB30US12K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CCS 4

Use with BACB30US12K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP12DP 4

Use with BACB30US12K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP121DP 4

Use with BACB30US12K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP122DP 3

Use with any

BACB30US12K bolt.

Torque to 3300 - 4300 inlbs.

BACN10HR12CD 4 NUT, SELF-LOCKING -

GROUP 3: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia More Data

0.7495 -

0.7505

A BACB30US12K46 1 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K46X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K46Y 1 BOLT, 12 POINT HEAD

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 3 OF 6)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
GROUP 3: Support Rib # 1 and # 8

CODE Identification QTY Name Hole Dia More Data

0.7495 -

0.7505

B BACB30US12K47 2 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K47X 2 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K47Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

C BACB30US12K48 1 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K48X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K48Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US12K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CVS 4

Use with BACB30US12K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA121CVS 4

Use with BACB30US12K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA122CVS 3

Use with any

BACB30US12K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CCS 4

Use with BACB30US12K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP12DP 4

Use with BACB30US12K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP121DP 4

Use with BACB30US12K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP122DP 3

Use with any

BACB30US12K bolt.

Torque to 3300 - 4300 inlbs.

BACN10HR12CD 4 NUT, SELF-LOCKING -

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 4 OF 6)

Export Controlled ECCN: 9E991 - BOEING

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
GROUP 3: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia More Data

0.7495 -

0.7505

A BACB30US12K49 1 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K49X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K49Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

B BACB30US12K50 1 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K50X 1 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K50Y 1 BOLT, 12 POINT HEAD

0.7495 -

0.7505

C BACB30US12K51 2 BOLT, 12 POINT HEAD

0.7654 - Optional.

0.7661

BACB30US12K51X 2 BOLT, 12 POINT HEAD

0.7807 - Optional.

0.7817

BACB30US12K51Y 1 BOLT, 12 POINT HEAD

MATING WASHERS AND NUTS

Use with BACB30US12K*

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CVS 4

Use with BACB30US12K*X

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA121CVS 4

Use with BACB30US12K*Y

bolt. Install under head of

bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA122CVS 3

Use with any

BACB30US12K bolt. Install

under head of bolt.

WASHER, SELF-ALIGN- -

ING

BACW10CA12CCS 4

Use with BACB30US12K*

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP12DP 4

Use with BACB30US12K*X

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP121DP 4

Use with BACB30US12K*Y

bolt. Install under nut.

WASHER, PLAIN AND -

COUNTERSUNK

BACW10BP122DP 3

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 5 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

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Original Issue: October 30, 2012

767-57A0131

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT
GROUP 3: Support Rib # 2 and # 7

CODE Identification QTY Name Hole Dia More Data

Use with any

BACB30US12K bolt.

Torque to 3300 - 4300 inlbs.

BACN10HR12CD 4 NUT, SELF-LOCKING -

APPENDIX A: PART NUMBERS AND QUANTITIES BY SUPPORT RIB NUMBER

(SHEET 6 OF 6)

Export Controlled ECCN: 9E991 - BOEING

PROPRIETARY - Copyright © Unpublished

Work - See page 1 for details.

Original Issue: October 30, 2012

767-57A0131

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BOEING SERVICE BULLETIN 767-57A0131

ALERT ALERT