Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-53A0261

Original Issue: August 12, 2014

ATA System: 5300 5380 5530

SUBJECT: FUSELAGE - Section 48 - Vertical Stabilizer Attachment Barrel Nut 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 © 2014 Boeing.

Unpublished Work. All Rights Reserved.

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are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The

Boeing Company.

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BLANK PAGE
Table of Contents

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 16

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

M. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 19

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE 1: ACCESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

FIGURE 2: INTERNAL AND EXTERNAL DETAILED INSPECTION . . . . . . . . . . . . . . . . . . . 27

FIGURE 3: TORQUE CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

FIGURE 4: MAGNETIC CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 5: BARREL NUT REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

APPENDIX A: COMPLIANCE TASKS AND COMPLIANCE TIMES LOGIC DIAGRAM . . . . . . . . . . . 39

APPENDIX B: INPUT SURVEY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40

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BLANK PAGE
Commercial 

Airplanes 767

Service Bulletin

ALERT

Summary Number: 767-53A0261

Original Issue: August 12, 2014

ATA System: 5300 5380 5530

SUBJECT: FUSELAGE - Section 48 - Vertical Stabilizer Attachment Barrel Nut 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

Accomplishment of this service bulletin will make sure H-11 steel barrel nuts that attach the vertical stabilizer

to body section 48 are found and replaced. If H-11 steel barrel nuts are not found and replaced, galvanic corrosion

can occur if moisture is present. Corroded H-11 steel barrel nuts could fail due to stress corrosion cracking which

can cause departure of the vertical stabilizer and the loss of rudder control.

During a C-check, an operator reported finding of H-11 steel barrel nuts installed on an airplane not included in

the effectivity of the Service Bulletin SB 767-53A0085. The SB 767-53A0085 provides instructions to inspect

and replace H-11 steel barrel nuts at the Vertical Fin, Section 48, attachment points with Inconel barrel nuts.

Further investigation has discovered that airplanes with line numbers 575 to 681, allowed an optional installation

of H-11 steel or Inconel barrel nuts at the 16 vertical fin attachment points.

Production incorporation of only Inconel barrel nuts begins with line number 682 and on.

Boeing Service Related Problem (SRP) 767-SRP-53-0453 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

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

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Planning Data Affected Reference

Publications Affected Yes 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 Parts/Material Yes

Paragraph 2.F., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

ACTION

Get internal and external access to Section 48 and to the area of the vertical fin attachment joint. Do the following

steps for each of the 16 attachment points. Do Internal and External Detailed Inspection of the barrel nut holes

and sealant for cracked/damaged sealant, corrosion, or cracked/broken barrel nut.

If cracked/damaged sealant, corrosion, or cracked/broken barrel nut is found, consider the barrel nut to be

corroded. Replace the barrel nut with a new Inconel barrel nut.

If no cracked/damaged sealant, corrosion, or cracked/broken barrel nut is found, do a Torque Check on each

affected vertical fin attachment bolt.

If the Torque Check finds that a bolt can be turned, consider the barrel nut to be damaged. Replace the barrel

nut with a new Inconel barrel nut.

If the Torque Check does not find that a bolt can be turned, put the airplane back to a serviceable condition.

Continue to do Internal and External Detailed Inspection, and Torque Check on each affected vertical fin

attachment bolt unless the correct nut type is installed.

As an alternative, do the Magnetic Check to identify H-11 steel barrel nuts. If H-11 steel barrel nut is found,

replace the barrel nut with a new Inconel barrel nut. If no H-11 steel barrel nut is found, no further action is

required.

Put the airplane back to a serviceable condition.

EFFECTIVITY

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

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of September 11, 1997. Please refer to

Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years from the original

issue date of this service bulletin.

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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.

Operators are encouraged to complete the survey provided in the Appendix of this service bulletin to help Boeing

predict the quantity and timing of the Boeing Supplied Kits/Parts.

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Commercial 

Airplanes 767

Service Bulletin

ALERT

Number: 767-53A0261

Original Issue: August 12, 2014

ATA System: 5300 5380 5530

SUBJECT: FUSELAGE - Section 48 - Vertical Stabilizer Attachment Barrel Nut 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

Refer to Service Bulletin Index D624T001 Part 3 for Airplane Variable Number, Line Number, and

Serial Number data.

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

767-200/-300/-300F Airplanes. Line number 575 through 681, which

have optional H-11 steel or Inconel barrel nuts installed at the vertical

stabilizer attachment points.

1 -

Airplane Models:

767-200, 767-300, 767-300F

Variable Number Group

VF182 - VF184 1

VF251 1

VK015 - VK016 1

VK113 1

VK144 - VK148 1

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Variable Number Group

VK181 1

VK186 1

VL754 - VL755 1

VL806 - VL807 1

VL871 - VL873 1

VL891 - VL900 1

VL911 - VL914 1

VL931 - VL932 1

VL941 1

VN096 - VN099 1

VN136 - VN137 1

VN174 1

VN197 - VN198 1

VN225 1

VN265 - VN276 1

VN292 - VN293 1

VN388 1

VN424 - VN427 1

VN436 1

VN637 - VN638 1

VN657 - VN658 1

VN932 - VN936 1

VN953 1

VN966 - VN972 1

VW701 - VW721 1

VW851 1

2. Spares Affected

None.

B. Concurrent Requirements

None.

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C. Reason

Accomplishment of this service bulletin will make sure H-11 steel barrel nuts that attach the vertical

stabilizer to body section 48 are found and replaced. If H-11 steel barrel nuts are not found and replaced,

galvanic corrosion can occur if moisture is present. Corroded H-11 steel barrel nuts could fail due to

stress corrosion cracking which can cause departure of the vertical stabilizer and the loss of rudder

control.

During a C-check, an operator reported finding of H-11 steel barrel nuts installed on an airplane not

included in the effectivity of the Service Bulletin SB 767-53A0085. The SB 767-53A0085 provides

instructions to inspect and replace H-11 steel barrel nuts at the Vertical Fin, Section 48, attachment

points with Inconel barrel nuts. Further investigation has discovered that airplanes with line numbers

575 to 681, allowed an optional installation of H-11 steel or Inconel barrel nuts at the 16 vertical fin

attachment points.

Production incorporation of only Inconel barrel nuts begins with line number 682 and on.

Boeing Service Related Problem (SRP) 767-SRP-53-0453 is related to this service bulletin.

D. Description

Get internal and external access to Section 48 and to the area of the vertical fin attachment joint. Do

the following steps for each of the 16 attachment points. Do Internal and External Detailed Inspection

of the barrel nut holes and sealant for cracked/damaged sealant, corrosion, or cracked/broken barrel

nut.

If cracked/damaged sealant, corrosion, or cracked/broken barrel nut is found, consider the barrel nut

to be corroded. Replace the barrel nut with a new Inconel barrel nut.

If no cracked/damaged sealant, corrosion, or cracked/broken barrel nut is found, do a Torque Check

on each affected vertical fin attachment bolt.

If the Torque Check finds that a bolt can be turned, consider the barrel nut to be damaged. Replace

the barrel nut with a new Inconel barrel nut.

If the Torque Check does not find that a bolt can be turned, put the airplane back to a serviceable

condition. Continue to do Internal and External Detailed Inspection, and Torque Check on each affected

vertical fin attachment bolt unless the correct nut type is installed.

As an alternative, do the Magnetic Check to identify H-11 steel barrel nuts. If H-11 steel barrel nut is

found, replace the barrel nut with a new Inconel barrel nut. If no H-11 steel barrel nut is found, no further

action is required.

Put the airplane back to a serviceable condition.

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

Affected Maintenance Zones

Model Zone

767-200, 767-300, 767-300F 311, 312, 313, 314, 322, 323, 324, 325

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ALERT ALERT
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.

1. Compliance Time Exceptions:

If a vertical stabilizer attachment barrel nut has been inspected and no H-11 steel barrel nut found,

and/or replaced, and meets 1 of the requirements shown below, then no further action is required

at that attachment point location. The inspections and/or H-11 steel barrel nut replacement of the

non-repaired attachment points do not change.

a. Previously installed H-11 barrel nut was replaced with drawing configuration barrel nut made

from alternate material to H-11 steel.

b. Previously installed H-11 barrel nut was replaced with barrel nut approved by FAA or by a

Boeing Company Authorized Representative. The replacement barrel nut is made from alternate

material to H-11 steel.

Do the required actions in accordance with Paragraph 3. Accomplishment Instructions.

When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When

more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION

numbers for that CONDITION number or OPTION number.

A logic diagram showing compliance tasks and compliance times is included as an aid in APPENDIX

A.

Table 1: Vertical Stabilizer Attachment Barrel Nut Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

Within 36 -

months after the

last Torque

Check inspection in accordance with 767

MPD Section 2,

Task 53-734-00.

Within 24

months after the

Original Issue

date of this Service Bulletin.

OPTION 1:

Do PART 2: INTERNAL

AND EXTERNAL DETAILED INSPECTION of

the barrel nut holes and

sealant for signs of corrosion.

Do PART 3: TORQUE

CHECK for any loose bolt

(e.g., the bolt can be

turned).

All Airplanes.

(a)

OPTION 2:

Do PART 4: MAGNETIC

CHECK to identify H-11

steel barrel nuts.

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ALERT ALERT
Table 1: Vertical Stabilizer Attachment Barrel Nut Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

CONDITION 1 (ACTION - - 18 months.

1): Repeat

CONDITION 1: No signs of

corrosion AND no loose

bolt found during any OPTION 1 inspection.

(b)

PART 2: INTERNAL AND

EXTERNAL DETAILED

INSPECTION of the barrel nut holes and sealant

for signs of corrosion.

PART 3: TORQUE

CHECK for any loose bolt

(e.g., the bolt can be

turned).

Within 36 months after the Original -

Issue date of this Service Bulletin.

CONDITION 1 (ACTION

2): Do PART 5: BARREL

NUT REPLACEMENT.

(b)

Do PART 5: BARREL Before further flight. -

NUT REPLACEMENT.

CONDITION 2: Corrosion

OR any loose bolt found

during any OPTION 1 inspection.(b)

No further action is re- - - -

quired.

CONDITION 3: No H-11

steel barrel nut found during any OPTION 2 inspection.

Do PART 2: INTERNAL Before further flight. -

AND EXTERNAL DETAILED INSPECTION of

the barrel nut holes and

sealant for signs of corrosion.

CONDITION 4: H-11 steel

barrel nut found during any

OPTION 2 inspection.

Do PART 3: TORQUE

CHECK for any loose bolt

(e.g., the bolt can be

turned).

(a) (b)

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ALERT ALERT
Table 1: Vertical Stabilizer Attachment Barrel Nut Inspection

Repeat Interval

(Not to Exceed)

Compliance Time (Whichever

Occurs Later)

Condition Action

CONDITION 5 (ACTION - - 18 months.

1): Repeat

CONDITION 5: H-11 steel

barrel nut found during any

OPTION 2 inspection. No

signs of corrosion AND no

loose bolt found during any

OPTION 2 inspection.

(b)

PART 2: INTERNAL AND

EXTERNAL DETAILED

INSPECTION of the barrel nut holes and sealant

for signs of corrosion.

PART 3: TORQUE

CHECK for any loose bolt

(e.g., the bolt can be

turned).

Within 36 months after the Original -

Issue date of this Service Bulletin.

CONDITION 5 (ACTION

2): Do PART 5: BARREL

NUT REPLACEMENT.

(b)

Do PART 5: BARREL Before further flight. -

NUT REPLACEMENT.

CONDITION 6: H-11 steel

barrel nut found during any

OPTION 2 inspection. Corrosion OR any loose bolt

found during any OPTION

2 inspection.

(b)

(a) Signs of corrosion include but not limited to sealant cracks, sealant bulging and powder residue.

(b) Accomplishment of PART 5: BARREL NUT REPLACEMENT is terminating action to the repeat inspection

at that attachment point location only.

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 and replacement

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:

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ALERT ALERT
• 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.

Task Number of Persons Task Hours Elapsed Hours

OPEN ACCESS 2 1.50 0.75

FIGURE 2 - INTERNAL AND EXTERNAL 1 1.60 1.60

DETAILED INSPECTION

FIGURE 3 - TORQUE CHECK 1 1.60 1.60

FIGURE 4 - MAGNETIC CHECK 2 4.00 2.00

(a)

FIGURE 5 - BARREL NUT REPLACEMENT 1 0.75 0.75

(b)

CLOSE ACCESS 2 1.50 0.75

TOTAL FOR EACH AIRPLANE 6.20 4.70

(a) Add labor estimates to total as required if optional inspection is accomplished in accordance with

Paragraph 3.B., Work Instructions - PART 4: MAGNETIC CHECK.

(b) Labor estimates are for one (1) barrel nut replacement. Multiply the number of barrel nut replacement

and add labor estimates to total as required if barrel nut replacement is accomplished in accordance

with Paragraph 3.B., Work Instructions - PART 5: BARREL NUT REPLACEMENT.

NOTE: If Boeing tools PME148T0010 (PLATFORM ASSEMBLY) and 2MIT100T3480 (TORQUE

MULTIPLIER AND ADAPTER) are used, further removal of equipment will be necessary for

access. The time required for the removal and reinstallation of equipment has not been

accounted for in this estimate of man-hours.

H. Weight and Balance Changes

None.

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Boeing Service Bulletin 767-53A0085

b. Boeing Service Related Problem (SRP) 767-SRP-53-0453

c. Service Bulletin Index D624T001

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ALERT ALERT
d. Standard Overhaul Practices Manual (SOPM) 20-50-01

e. 767 Aircraft Maintenance Manual (AMM) 24-22-00, 29-11-00, 55-31-03, 55-30-03

f. 767 Illustrated Parts Catalog (IPC) 53-80-52

g. 767 Maintenance Planning Data (MPD) Section 2, Task 53-734-00

2. Data Supplied with this Service Bulletin:

None.

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

Drawing Number Title

100T3480 SECTION 48/72 INTEGRATION

140T4800 SEALANT APPLICATION - SECTION 48 INTEGRATION

140T5000 PROTECTIVE FINISH INSTL

140T6000 CORROSION INHIBITING COMPOUND INSTL - FUSELAGE

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

1. Publications:

Publication Chapter-Section

767 Aircraft Maintenance Manual 55-30

767 Corrosion Prevention Manual 55-00, 55-30

767 Illustrated Parts Catalog 53-80

2. Damage Tolerance Based Structural Inspections:

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

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

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

L. Interchangeability and Intermixability of Parts

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

M. Software Accomplishment Summary

Not affected.

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ALERT ALERT
2. MATERIAL INFORMATION

A. Material - Price and Availability

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

are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.

The kits/parts are subject to the terms and conditions of the Boeing standard purchase order

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

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

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

2. Fax to (206) 662-7145

REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER

AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION

Unit Price as of

the 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

015T1900-1 Kit - Barrel Nut Replacement

015T1900-2 Kit - Bolt Replacement

Operators are encouraged to complete the survey provided in the APPENDIX of this service bulletin

to help Boeing predict the quantity and timing of the Boeing Supplied Kits/Parts.

B. Industry Support Information

Boeing warranty remedies are available for airplanes in warranty as of September 11, 1997. Please

refer to Paragraph 2.B., Industry Support Information. The warranty remedies will expire eight years

from the original issue date of this service bulletin.

C. Parts Necessary for Each Airplane

1. Kits/Parts:

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

NOTE: A barrel nut replacement kit 015T1900-1 and the items shown in Paragraph 2.C.2., Parts

and Materials Supplied by the Operator, are necessary for each airplane. If the fin

attachment bolts that exist are found to be damaged, a bolt replacement kit 015T1900-2

would also be necessary and should also be ordered.

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

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ALERT ALERT
ALL

Kit 015T1900

Existing Part Notes

Number

New Part Number Qty Name

-1 -2

Kit - Barrel Nut Re- (a)

placement

015T1900-1 - .

Kit - Bolt Replace- (a)

ment

015T1900-2 . -

BOLT, 12 PT

HEAD

BACB30US16K47 . 4

BOLT, 12 PT

HEAD

BACB30US16K48 . 4

BOLT, 12 PT

HEAD

BACB30US16K50 . 2

BOLT, 12 PT

HEAD

BACB30US16K51 . 2

BOLT, 12 PT

HEAD

BACB30US18K52 . 4

BACN11B16CS 12 . BARREL NUT

BACN11B18CS 4 . BARREL NUT

RETAINER, BARREL NUTBACR10AL16B 12 .

RETAINER, BARREL NUTBACR10AL18B 4 .

BACW10BP16CD 12 . WASHER, PLAIN

BACW10BP18CD 4 . WASHER, PLAIN

NAS1149E1632P 12 . WASHER

NAS1149E1832P 4 . WASHER

(a) The kit may have more parts than are necessary for installation. Discard parts

that are not used or keep the parts for spares.

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.

Part Number/ Specification Qty Name Notes

BMS 3-23, TYPE II 8 Oz Corrosion Inhibiting Compound (a)

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ALERT ALERT
Part Number/ Specification Qty Name Notes

BMS 5-142, TYPE II (BMS 5- 8 Oz Sealant (a)

95 optional)

BMS 5-95, TYPE I, CLASS B 1 Pt Sealant (a)

OR C

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

for supplier data.

3. Parts Modified and Reidentified:

None.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None

E. Special Tooling - Price and Availability

Boeing can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service

Bulletin. Operators are encouraged to share schedule requirements with Boeing for incorporation of

the service bulletin by e-mail to ServiceBulletinRentalLoanTools@boeing.com. The tools are subject

to the terms and conditions of the Boeing standard purchase order acknowledgement. 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 Boeing Part Page

2. Fax to (425) 965-8237

Rental Data:

Daily Price as of

the Original Issue

date of this service bulletin (US

Dollars)

Tool Kit Number Name

PME148T0010 PLATFORM ASSEMBLY $209,767.00

TORQUE MULTIPLIER AND $272,554.00

ADAPTER

2MIT100T3480

F. Special Tooling Necessary to do this Service Bulletin

The tools referred to below can be used to improve access to the vertical fin attachment bolts and for

removal and replacement of the same bolts.

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ALERT ALERT
To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability.

Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be

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

Tool Kit Number Name

PME148T0010 PLATFORM ASSEMBLY

TORQUE MULTIPLIER AND

ADAPTER

2MIT100T3480

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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. The work instructions are divided into work packages. Task Hours and Elapsed Hours

for each package are given in Paragraph 1.G., Manpower. You can do each work

package independently.

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

– Linear dimensions are in inches

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

or minus 0.03 inch

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

– Angular tolerance is plus or minus 2 degrees

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

Manual (SRM) Chapter 51

– Torque Values:

— Values for structural fasteners are given in 767 Structural Repair Manual,

Chapter 51.

— Non-standard torque values for maintenance tasks are included in the

applicable installation step.

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

SRM Chapter 51.

6. If the length of any fastener specified in this service bulletin does not meet installation

standards given in SRM Chapter 51, then a fastener of the same specification, or

an approved substitute, with a length which meets the installation standards given

in SRM Chapter 51 may be used. In addition, washers may be installed for fastener

grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate

full threaded fasteners (screws) needed for installation in this service bulletin.

7. 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
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.

9. Refer to APPENDIX A for logic diagram(s). Logic diagrams are provided as an aid

only. Information contained in Paragraph 1.E., Compliance is the primary source for

compliance times. Information in Paragraph 3.B., Work Instructions is the primary

source for tasks required for compliance.

10. Refer to APPENDIX B for INPUT SURVEY. Operators are encouraged to complete

the survey provided in the Appendix of this service bulletin to help Boeing predict

the quantity and timing of the Boeing Supplied Kits/Parts.

11. 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.

12. 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.

13. 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.

14. Use of colors in Figures is based on guidance from the ATA e-Business Program

(ATA) iSpec 2200.

15. When more than one OPTION is given for a CONDITION, do only one of the OPTION

numbers. When more than one ACTION is given for a CONDITION number or an

OPTION number, do all of the ACTION numbers for that CONDITION number or

OPTION number.

16. The compliance times for the actions in Paragraph 3.B., WORK INSTRUCTIONS

are in Paragraph 1.E., Compliance.

17. Some steps in the Work Instructions are identified as Required for Compliance (RC).

If this service bulletin is mandated by an Airworthiness Directive (AD), then the steps

identified as RC must be done to comply with the AD. Alternative procedures for

steps not identified with RC can be used if the RC steps can still be done as specified,

and the airplane can be put back in a serviceable condition. An Alternative Method

of Compliance (AMOC) is not necessary for deviations to steps that are not identified

as RC.

18. Boeing recommends that PLATFORM ASSEMBLY PME148T0010 or a similar

suitable work platform be installed for access to the vertical fin attachment bolts. If

this tool is used, fasteners from the frames at body station (BS) 1629 and BS 1654

must be removed to allow access. Install new fasteners of the same type and size

after the PLATFORM ASSEMBLY is removed.

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ALERT ALERT
19. Boeing TORQUE MULTIPLIER AND ADAPTER Tool 2MIT100T3480 is a tool used

by Boeing during production to apply installation torque to the bolts that attach the

vertical fin to the fuselage. If an operator wishes to use this tool or a similar tool,

several pieces of equipment such as pulley brackets, fairlead brackets and hydraulic

lines will need to be removed in order to attach the tool to BS 1654.5 and BS 1725.5

frames. Details of this equipment removal and subsequent installation are not shown

in this service bulletin.

20. Compliance Time Exceptions:

If a vertical stabilizer attachment barrel nut has been inspected and no H-11 steel

barrel nut found, and/or replaced, and meets 1 of the requirements shown below,

then no further action is required at that attachment point location. The inspections

and/or H-11 steel barrel nut replacement of the non-repaired attachment points do

not change.

– Previously installed H-11 barrel nut was replaced with drawing configuration

barrel nut made from alternate material to H-11 steel.

– Previously installed H-11 barrel nut was replaced with barrel nut approved by

FAA or by a Boeing Company Authorized Representative. The replacement

barrel nut is made from alternate material to H-11 steel.

B. WORK INSTRUCTIONS

1. Do PART 1: OPEN ACCESS.

2. OPTION 1: Do PART 2: INTERNAL AND EXTERNAL DETAILED INSPECTION for signs of

corrosion. Do PART 3: TORQUE CHECK for any loose bolt (e.g., the bolt can be turned).

NOTE: Signs of corrosion includes but not limited to sealant cracks, sealant bulging and powder

residue.

CONDITION 1: No signs of corrosion AND no loose bolt found.

a. ACTION 1: Repeat PART 2: INTERNAL AND EXTERNAL DETAILED INSPECTION and

PART 3: TORQUE CHECK.

b. ACTION 2: Do PART 5: BARREL NUT REPLACEMENT.

CONDITION 2: Corrosion OR any loose bolt found.

a. Do PART 5: BARREL NUT REPLACEMENT.

3. OPTION 2: Do PART 4: MAGNETIC CHECK to identify H-11 steel barrel nuts.

CONDITION 3: No H-11 steel barrel nut found.

a. No further action is required.

CONDITION 4: H-11 steel barrel nut found.

a. Do PART 2: INTERNAL AND EXTERNAL DETAILED INSPECTION for signs of corrosion.

Do PART 3: TORQUE CHECK for any loose bolt (e.g., the bolt can be turned).

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ALERT ALERT
NOTE: Signs of corrosion includes but not limited to sealant cracks, sealant bulging and

powder residue.

CONDITION 5: H-11 steel barrel nut found. No signs of corrosion AND no loose bolt

found.

(1) ACTION 1: Repeat PART 2: INTERNAL AND EXTERNAL DETAILED INSPECTION and

PART 3: TORQUE CHECK.

(2) ACTION 2: Do PART 5: BARREL NUT REPLACEMENT.

CONDITION 6: H-11 steel barrel nut found. Corrosion OR any loose bolt found.

(1) Do PART 5: BARREL NUT REPLACEMENT.

4. Do PART 6: CLOSE ACCESS.

PART 1: OPEN ACCESS

WARNING: BEFORE ENTERING SECTION 48, DEACTIVATE AND PLACARD THE HORIZONTAL

STABILIZER TRIM CONTROLS WITH DO-NOT-OPERATE IDENTIFIERS. DO THIS TO

PREVENT INADVERTENT STABILIZER OPERATION WHICH CAN CAUSE INJURY

TO PERSONNEL AND DAMAGE TO EQUIPMENT.

1. Do the steps that follow to deactivate the horizontal stabilizer. Refer to 767 AMM 55-31-03 as an

accepted procedure.

a. Pressurize the center hydraulic system. Refer to 767 AMM 29-11-00 as an accepted procedure.

b. Place the horizontal stabilizer at neutral (2 units of trim on position indicator) using the STAB

TRIM levers.

c. Depressurize the center and left hydraulic systems. Refer to 767 AMM 29-11-00 as an accepted

procedure.

d. Position LEFT and CENTER STAB TRIM SHUTOFF switches on control stand P10 to CUTOUT.

e. Open SHUT OFF VALVE,STAB TRIM,LEFT (11C12), and SHUT OFF VALVE, STAB TRIM,C

(11C13) circuit breakers on the P11 overhead circuit breaker panel and attach DO-NOT-CLOSE

identifiers.

2. Do the steps that follow to deactivate the rudder. Refer to 767 AMM 55-31-03 as an accepted

procedure.

a. Supply electrical power. Refer to 767 AMM 24-22-00 as an accepted procedure.

b. Move the FLT CONTROL SHUTOFF TAIL L, R, and C switches on the P61 right side panel

to OFF. Make sure that the switch position lights come on. Attach DO-NOT-CLOSE identifiers.

c. Open RUDDER RATIO (11G10), TAIL, L-FLT CONT SHUTOFF (11H17), TAIL, C-FLT CONT

SHUTOFF (11H18), and TAIL, R-FLT CONT SHUTOFF (11H27) circuit breakers on the P11

overhead circuit breaker panel and attach DO-NOT-CLOSE identifiers.

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ALERT ALERT
3. Get external access to the base of the vertical fin. Get internal access as shown in FIGURE 1.

PART 2: INTERNAL AND EXTERNAL DETAILED INSPECTION

1. RC - Do Internal and External Detailed Inspection of the barrel nut holes and sealant for

cracked/damaged sealant, corrosion, or cracked/broken barrel nuts in accordance with FIGURE

2.

NOTE: Signs of corrosion include but not limited to sealant cracks, sealant bulging and powder

residue.

PART 3: TORQUE CHECK

1. RC - Do a Torque Check of the Vertical Stabilizer attachment bolts for any loose bolt (e.g., the

bolt can be turned) in accordance with FIGURE 3.

NOTE: Boeing recommends that Platform Assembly PME148T0010 or a similar suitable work

platform be installed to allow access to the vertical fin attachment bolts.

PART 4: MAGNETIC CHECK

1. RC - Do a Magnetic Check to identify H-11 steel barrel nuts in accordance with FIGURE 4.

PART 5: BARREL NUT REPLACEMENT

WARNING: DO NOT REMOVE TWO ADJACENT BOLTS AT THE SAME TIME. ALSO, DO NOT

REMOVE MORE THAN FOUR BOLTS FROM EACH SIDE OF THE FIN AT ONE TIME.

DO THIS TO PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

1. RC - Do barrel nut replacement in accordance with FIGURE 5.

PART 6: CLOSE ACCESS

1. Close the access doors that were opened for access as shown in FIGURE 1.

2. Remove the DO-NOT close identifiers and close SHUT OFF VALVE,STAB TRIM,LEFT (11C12),

and SHUT OFF VALVE, STAB TRIM,C (11C13) circuit breakers on the P11 overhead circuit

breaker panel.

3. Remove the DO-NOT close identifiers and close RUDDER RATIO (11G10), TAIL, L-FLT CONT

SHUTOFF (11H17), TAIL, C-FLT CONT SHUTOFF (11H18), and TAIL, R-FLT CONT SHUTOFF

(11H27) circuit breakers on the P11 overhead circuit breaker panel.

4. Put the airplane back to a serviceable condition.

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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 each airplane.

Step Task Name Identification Qty More Data

1 Open Access Door - 2 -

FIGURE 1: ACCESS

(SHEET 1 OF 1)

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ALERT ALERT
FIGURE 2: INTERNAL AND EXTERNAL DETAILED INSPECTION

(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 each airplane.

Step Task Name Identification Qty More Data

1 Inspect Barrel Nut Hole and Sealant - - (a)

(a) Do Internal and External Detailed Inspection of the barrel nut holes and sealant for cracked/damaged

sealant, corrosion, or cracked/broken barrel nuts. Signs of corrosion includes but not limited to sealant

cracks, sealant bulging and powder residue.

FIGURE 2: INTERNAL AND EXTERNAL DETAILED INSPECTION

(SHEET 2 OF 2)

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FIGURE 3: TORQUE CHECK

(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 each airplane.

Step Task Name Identification Qty More Data

1 Apply Torque - - (a)

(a) Torque bolt to 3,700 - 4,100 in-lbs for the torque check for any loose bolt (e.g., the bolt can be turned).

FIGURE 3: TORQUE CHECK

(SHEET 2 OF 2)

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FIGURE 4: MAGNETIC CHECK

(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 each airplane.

Step Task Name Identification Qty More Data

1 Remove Sealant - - (a)

2 Inspect Barrel Nut - - (b)

BMS 5-142, TYPE II - (c)

(BMS 5-95 optional)

3 Apply Sealant

(a) Remove sealant from the barrel nut hole to expose the nut.

(b) Do a magnetic check to identify H-11 steel barrel nuts. If the magnet is attracted to the nut, the nut is

considered an H-11 steel nut. Doing an inspection to determine the part number is acceptable in lieu of

the magnetic check if the part number of the barrel nut can be conclusively determined from that inspection.

H-11 steel barrel nuts are identified with part number marking 113LH7940T or LH7940T. The part marking

can be stamped or etched on either side of the barrel nut cradle.

(c) Apply sealant to fill the entire barrel nut hole.

FIGURE 4: MAGNETIC CHECK

(SHEET 2 OF 2)

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FIGURE 5: BARREL NUT REPLACEMENT

(SHEET 1 OF 6)

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FIGURE 5: BARREL NUT REPLACEMENT

(SHEET 2 OF 6)

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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

WARNING: DO NOT REMOVE TWO ADJACENT BOLTS AT THE SAME TIME. ALSO, DO NOT REMOVE

MORE THAN FOUR BOLTS FROM EACH SIDE OF THE FIN AT ONE TIME. DO THIS TO

PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

1 Remove / Keep Bolt - 1 (a)

2 Remove Washer - 2 -

Remove Retainer - 1 -

Remove Barrel Nut - 1 -

BMS 5-95, TYPE I, - (b)

CLASS B OR C

3 Apply Sealant

FIGURE 5: BARREL NUT REPLACEMENT

(SHEET 3 OF 6)

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Step Task Name Identification Qty More Data

4 Install (New) Barrel Nut - 1 (d) (f)

Install (New) Retainer - 1 (d)

5 Install (New) Washer - 1 (d)

6 Install (New) Washer - 1 (d)

7 Install (Kept) Bolt - 1 (d)

BMS 5-142, TYPE II - (c)

(BMS 5-95 optional)

8 Apply Sealant

9 Apply Finish - - (e)

Corrosion Inhibiting BMS 3-23, TYPE II - -

Compound

10 Apply

(a) Remove sealant from bolts. An Inconel bolt can be reinstalled if no corrosion, cracks, thread damage, or

shank damage is found. If bolt corrosion, cracks, or damage is found, replace the bolt with new Inconel

bolt.

(b) To the areas that follow:

- Bolt threads, shank and under bolt head.

- Barrel nut areas that contact the vertical fin structure.

- Washer mating surfaces.

(c) Apply sealant to fill the entire barrel nut hole.

(d) Refer to fastener table for fastener codes and torque values.

(e) To bare aluminum to match adjacent structure.

(f) Verify that the barrel nut locking feature is present on the new barrel nuts. Visually inspect for oval shaped

threads on the upper end of the barrel nut or hand thread the matting attach fastener and verify that the

bolt cannot be threaded all the way through the barrel nut by hand force. One operator has reported that

new barrel nuts did not have the locking feature present on one set of barrel nuts supplied for one airplane.

FIGURE 5: BARREL NUT REPLACEMENT

(SHEET 4 OF 6)

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BOEING SERVICE BULLETIN 767-53A0261

ALERT ALERT
The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure.

A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the

number of fasteners necessary for this figure.

Code Name Identification Qty Hole Dia More Data

7,800 - 8,800 in-lbs

torque.

A BOLT, 12 PT HEAD BACB30US16K47 4 -

7,800 - 8,800 in-lbs

torque.

BOLT, 12 PT HEAD BACB30US16K48 4 -

7,800 - 8,800 in-lbs

torque.

BOLT, 12 PT HEAD BACB30US16K50 2 -

7,800 - 8,800 in-lbs

torque.

BOLT, 12 PT HEAD BACB30US16K51 2 -

WASHER, PLAIN BACW10BP16CD 12 - Under bolt head.

If necessary for grip length

adjustment.

WASHER NAS1149E1632P 12 -

BARREL NUT BACN11B16CS 12 - -

RETAINER, BARREL BACR10AL16B 12 - -

NUT

FIGURE 5: BARREL NUT REPLACEMENT

(SHEET 5 OF 6)

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BOEING SERVICE BULLETIN 767-53A0261

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Code Name Identification Qty Hole Dia More Data

10,450 - 11,500 in-lbs

torque.

B BOLT, 12 PT HEAD BACB30US18K52 4 -

WASHER, PLAIN BACW10BP18CD 4 - Under bolt head.

If necessary for grip length

adjustment.

WASHER NAS1149E1832P 4 -

BARREL NUT BACN11B18CS 4 - -

RETAINER, BARREL BACR10AL18B 4 - -

NUT

FIGURE 5: BARREL NUT REPLACEMENT

(SHEET 6 OF 6)

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BOEING SERVICE BULLETIN 767-53A0261

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Logic diagrams are provided as an aid only. Information contained in Paragraph 1.E., Compliance is the primary

source for compliance times. Information in Paragraph 3.B., Work Instructions is the primary source for tasks

required for compliance.

APPENDIX A: COMPLIANCE TASKS AND COMPLIANCE TIMES LOGIC DIAGRAM

(SHEET 1 OF 1)

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APPENDIX B: INPUT SURVEY

(SHEET 1 OF 1)

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