# Boeing Alert Service Bulletin 767-53A0261: No revision named

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- Document: [Boeing Alert Service Bulletin 767-53A0261](https://openairdocs.org/service-documents/boeing/767-53a0261.md)
- Title as filed: SB-767-53A0261-00
- Pages: 40
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## Text

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### Page 1

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.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2014 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
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3.0

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### Page 3

Table of Contents
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 0
B. Concurrent Requirements ...................................... 1 0
C. Reason ................................................ 1 1
D. Description .............................................. 1 1
E. Compliance .............................................. 1 2
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 5
I. Electrical Load Data ......................................... 1 5
J. References .............................................. 1 5
1. Existing Data: ......................................... 1 5
2. Data Supplied with this Service Bulletin: ........................... 1 6
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 1 6
K. Publications Affected ........................................ 1 6
L. Interchangeability and Intermixability of Parts ........................... 1 6
M. Software Accomplishment Summary ................................ 1 6
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary for Each Airplane ................................. 1 7
1. Kits/Parts: ........................................... 1 7
2. Parts and Materials Supplied by the Operator: ........................ 1 8
3. Parts Modified and Reidentified: ............................... 1 9
4. Parts Removed and Not Replaced: .............................. 1 9
D. Parts Necessary to Change Spares ................................. 1 9
E. Special Tooling - Price and Availability ............................... 1 9
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 9
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 1
A. GENERAL INFORMATION ..................................... 2 1
B. WORK INSTRUCTIONS ....................................... 2 3
FIGURE 1: ACCESS ............................................ 2 6
FIGURE 2: INTERNAL AND EXTERNAL DETAILED INSPECTION ................... 2 7
FIGURE 3: TORQUE CHECK ....................................... 2 9
FIGURE 4: MAGNETIC CHECK ...................................... 3 1
FIGURE 5: BARREL NUT REPLACEMENT ................................ 3 3
APPENDIX A: COMPLIANCE TASKS AND COMPLIANCE TIMES LOGIC DIAGRAM ........... 3 9
APPENDIX B: INPUT SURVEY ........................................ 4 0
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-53A0261Original 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.
ReferenceAffectedPlanning Data
Paragraph 1.A.2., Spares AffectedNoSpares Affected
Paragraph 1.E., Compliance and Paragraph
1.F., Approval
YesAD Related
Paragraph 1.H., Weight and Balance ChangesNoWeight and Balance Change
Paragraph 1.I., Electrical Load DataNoElectrical Load Changed
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### Page 6

ReferenceAffectedPlanning Data
Paragraph 1.K., Publications AffectedYesPublications Affected
Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew
Operations Manual and/or FAA Approved Air-
plane Flight Manual)
Paragraph 2.C.1., Kits/PartsYesKits/Parts Required
Paragraph 2.C.2., Parts and Materials Supplied
by the Operator
YesOperator Supplied Parts/Material
Paragraph 2.F., Special Tooling Necessary to
do this Service Bulletin
NoSpecial Tooling Required
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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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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### Page 8 (OCR)

BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
STRINGER  BODY/FIN  REAR SPAR
FITTING  TENSION  ACCESS  HOLE  FITTING  TENSION
FRONT SPAR
TENSION
FITTING
VERTICAL
FIN
STA
1725
STA
STA  1702
STA 16/8
EWD  VERTICAL FIN  ATTACH FASTENERS  1654  DO INTERNAL AND EXTERNAL
(16 LOCATIONS)  DETAILED INSPECTIONS AND TORQUE
CHECK TO FIND CORRODED OR
DAMAGED H-11 STEEL BARREL NUTS.
IF CORRODED OR DAMAGED BARREL
NUTS ARE FOUND, REPLACE THEM
WITH INCONEL BARREL NUTS.
2307584
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### Page 9

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.
DESCRIPTIONCONFIGURATIONGROUP
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
GroupVariable Number
1VF182 - VF184
1VF251
1VK015 - VK016
1VK113
1VK144 - VK148
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### Page 10

GroupVariable Number
1VK181
1VK186
1VL754 - VL755
1VL806 - VL807
1VL871 - VL873
1VL891 - VL900
1VL911 - VL914
1VL931 - VL932
1VL941
1VN096 - VN099
1VN136 - VN137
1VN174
1VN197 - VN198
1VN225
1VN265 - VN276
1VN292 - VN293
1VN388
1VN424 - VN427
1VN436
1VN637 - VN638
1VN657 - VN658
1VN932 - VN936
1VN953
1VN966 - VN972
1VW701 - VW721
1VW851
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
ZoneModel
311, 312, 313, 314, 322, 323, 324, 325767-200, 767-300, 767-300F
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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)
ActionCondition
-Within 36
months after the
last Torque
Check inspec-
tion in accor-
dance with 767
MPD Section 2,
Task 53-734-00.
Within 24
months after the
Original Issue
date of this Ser-
vice Bulletin.
OPTION 1:
Do PART 2: INTERNAL
AND EXTERNAL DE-
TAILED INSPECTION of
the barrel nut holes and
sealant for signs of corro-
sion.
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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### Page 13

Table 1: Vertical Stabilizer Attachment Barrel Nut Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
18 months.--CONDITION 1 (ACTION
1): Repeat
CONDITION 1: No signs of
corrosion AND no loose
bolt found during any OP-
TION 1 inspection.
(b)
PART 2: INTERNAL AND
EXTERNAL DETAILED
INSPECTION of the bar-
rel 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)
-Before further flight.Do PART 5: BARREL
NUT REPLACEMENT.
CONDITION 2: Corrosion
OR any loose bolt found
during any OPTION 1 in-
spection.
(b)
---No further action is re-
quired.
CONDITION 3: No H-11
steel barrel nut found dur-
ing any OPTION 2 inspec-
tion.
-Before further flight.Do PART 2: INTERNAL
AND EXTERNAL DE-
TAILED INSPECTION of
the barrel nut holes and
sealant for signs of corro-
sion.
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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### Page 14

Table 1: Vertical Stabilizer Attachment Barrel Nut Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
18 months.--CONDITION 5 (ACTION
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 bar-
rel 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)
-Before further flight.Do PART 5: BARREL
NUT REPLACEMENT.
CONDITION 6: H-11 steel
barrel nut found during any
OPTION 2 inspection. Cor-
rosion 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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### Page 15

 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.
Elapsed HoursTask HoursNumber of PersonsTask
0.751.502OPEN ACCESS
1.601.601FIGURE 2 - INTERNAL AND EXTERNAL
DETAILED INSPECTION
1.601.601FIGURE 3 - TORQUE CHECK
2.004.002FIGURE 4 - MAGNETIC CHECK
(a)
0.750.751FIGURE 5 - BARREL NUT REPLACEMENT
(b)
0.751.502CLOSE ACCESS
4.706.20TOTAL FOR EACH AIRPLANE
(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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### Page 16

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:
TitleDrawing Number
SECTION 48/72 INTEGRATION100T3480
SEALANT APPLICATION - SECTION 48 INTEGRATION140T4800
PROTECTIVE FINISH INSTL140T5000
CORROSION INHIBITING COMPOUND INSTL - FUSELAGE140T6000
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:
Chapter-SectionPublication
55-30767 Aircraft Maintenance Manual
55-00, 55-30767 Corrosion Prevention Manual
53-80767 Illustrated Parts Catalog
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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### Page 17

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 Ser-
vice Bulletin (US
Dollars)
ROLT as of the
original issue
date of this Ser-
vice Bulletin (Cal-
endar Days)
NameKit Number
Kit - Barrel Nut Replacement015T1900-1
Kit - Bolt Replacement015T1900-2
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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ALL
Kit 015T1900
NotesExisting Part
Number
NameQtyNew Part Number
-2-1
(a)Kit - Barrel Nut Re-
placement
.-015T1900-1
(a)Kit - Bolt Replace-
ment
-.015T1900-2
BOLT, 12 PT
HEAD
4.BACB30US16K47
BOLT, 12 PT
HEAD
4.BACB30US16K48
BOLT, 12 PT
HEAD
2.BACB30US16K50
BOLT, 12 PT
HEAD
2.BACB30US16K51
BOLT, 12 PT
HEAD
4.BACB30US18K52
BARREL NUT.12BACN11B16CS
BARREL NUT.4BACN11B18CS
RETAINER, BAR-
REL NUT
.12BACR10AL16B
RETAINER, BAR-
REL NUT
.4BACR10AL18B
WASHER, PLAIN.12BACW10BP16CD
WASHER, PLAIN.4BACW10BP18CD
WASHER.12NAS1149E1632P
WASHER.4NAS1149E1832P
(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.
NotesNameQtyPart Number/ Specification
(a)Corrosion Inhibiting Compound8 OzBMS 3-23, TYPE II
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NotesNameQtyPart Number/ Specification
(a)Sealant8 OzBMS 5-142, TYPE II  (BMS 5-
95 optional)
(a)Sealant1 PtBMS 5-95, TYPE I, CLASS B
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 ser-
vice bulletin (US
Dollars)
NameTool Kit Number
$209,767.00PLATFORM ASSEMBLYPME148T0010
$272,554.00TORQUE MULTIPLIER AND
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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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.
NameTool Kit Number
PLATFORM ASSEMBLYPME148T0010
TORQUE MULTIPLIER AND
ADAPTER
2MIT100T3480
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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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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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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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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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### Page 25

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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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.
More DataQtyIdentificationNameTaskStep
-2-Access DoorOpen1
FIGURE 1: ACCESS
(SHEET 1 OF 1)
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### Page 27 (OCR)

BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
STRINGER  FITTING  TENSION  HOLE  BODY/FIN  ACCESS  REAR SPAR  TENSION  FITTING
FRONT SPAR
TENSION
FITTING
VERTICAL
FIN
8 LOCATIONS
STA
1725
STA
STA  1702
STA  1678
1654
2307540
FIGURE 2: INTERNAL AND EXTERNAL DETAILED INSPECTION
(SHEET 1 OF 2)
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### Page 28

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.
More DataQtyIdentificationNameTaskStep
(a)--Barrel Nut Hole and SealantInspect1
(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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BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
STRINGER  FITTIN  TENSION  HOLE  BODY/FIN  ACCESS  REAR SPAR  TENSION  FITTING
FRONT SPAR
TENSION
FITTING
VERTICAL
FIN
8 LOCATIONS
STA
1725
STA
STA  1702
STA  1678
1654
FIGURE 3: TORQUE CHECK
(SHEET 1 OF 2)
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### Page 30

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.
More DataQtyIdentificationNameTaskStep
(a)--TorqueApply1
(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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### Page 31 (OCR)

BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
STRINGER  FITTIN  TENSION  HOLE  BODY/FIN  ACCESS  REAR SPAR  TENSION  FITTING
FRONT SPAR
TENSION
FITTING
VERTICAL
FIN
8 LOCATIONS
STA
1725
STA
STA  1702
STA  1678
1654
FIGURE 4: MAGNETIC CHECK
(SHEET 1 OF 2)
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### Page 32

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.
More DataQtyIdentificationNameTaskStep
(a)--SealantRemove1
(b)--Barrel NutInspect2
(c)-BMS 5-142, TYPE II
(BMS 5-95 optional)
SealantApply3
(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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BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
" 48
STA
^ 48  1702
STA
1678
STA
1654
8 LOCATIONS  2307565
FIGURE 5: BARREL NUT REPLACEMENT
(SHEET 1 OF 6)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
25) IF NECESSARY FOR
-WD  GRIP LENGTH
ADJUSTMENT
BULKHEAD
FITTING
IF NECESSARY FOR
GRIP LENGTH
ADJUSTMENT
7
FIN TO BODY ATTACH LOCATION
(8 LOCATIONS)
FIGURE 5: BARREL NUT REPLACEMENT
(SHEET 2 OF 6)
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### Page 35

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.
More DataQtyIdentificationNameTaskStep
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.
(a)1-BoltRemove / Keep1
-2-WasherRemove2
-1-RetainerRemove
-1-Barrel NutRemove
(b)-BMS 5-95, TYPE I,
CLASS B OR C
SealantApply3
FIGURE 5: BARREL NUT REPLACEMENT
(SHEET 3 OF 6)
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More DataQtyIdentificationNameTaskStep
(d) (f)1-Barrel NutInstall (New)4
(d)1-RetainerInstall (New)
(d)1-WasherInstall (New)5
(d)1-WasherInstall (New)6
(d)1-BoltInstall (Kept)7
(c)-BMS 5-142, TYPE II
(BMS 5-95 optional)
SealantApply8
(e)--FinishApply9
--BMS 3-23, TYPE IICorrosion Inhibiting
Compound
Apply10
(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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### Page 37

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.
More DataHole DiaQtyIdentificationNameCode
7,800 - 8,800 in-lbs
torque.
-4BACB30US16K47BOLT, 12 PT HEADA
7,800 - 8,800 in-lbs
torque.
-4BACB30US16K48BOLT, 12 PT HEAD
7,800 - 8,800 in-lbs
torque.
-2BACB30US16K50BOLT, 12 PT HEAD
7,800 - 8,800 in-lbs
torque.
-2BACB30US16K51BOLT, 12 PT HEAD
Under bolt head.-12BACW10BP16CDWASHER, PLAIN
If necessary for grip length
adjustment.
-12NAS1149E1632PWASHER
--12BACN11B16CSBARREL NUT
--12BACR10AL16BRETAINER, BARREL
NUT
FIGURE 5: BARREL NUT REPLACEMENT
(SHEET 5 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 12, 2014
767-53A0261
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BOEING SERVICE BULLETIN 767-53A0261
ALERTALERT

### Page 38

More DataHole DiaQtyIdentificationNameCode
10,450 - 11,500 in-lbs
torque.
-4BACB30US18K52BOLT, 12 PT HEADB
Under bolt head.-4BACW10BP18CDWASHER, PLAIN
If necessary for grip length
adjustment.
-4NAS1149E1832PWASHER
--4BACN11B18CSBARREL NUT
--4BACR10AL18BRETAINER, BARREL
NUT
FIGURE 5: BARREL NUT REPLACEMENT
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: August 12, 2014
767-53A0261
38 of 40
BOEING SERVICE BULLETIN 767-53A0261
ALERTALERT

### Page 39 (OCR)

BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
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.
All Airplanes. Each
attachment point.
OPTION 1:
-DO PART 2: INTERNAL AND EXTERNAL
DETAILED INSPECTION for signs of corrosion.
-Do PART 3: TORQUE CHECK for loose bolt.
Within 24 months after the Original Issue date of this
Service Bulletin or within 36 months after the last
Torque Check in accordance with 767 MPD Section
2, Task 53-734-00, whichever occurs later. (a)
OPTION 2:
-Do PART 4: MAGNETIC CHECK to identify H-11
steel barrel nut.
Within 24 months after the Original Issue date of
this Service Bulletin or within 36 months after the
last Torque Check in accordance with 767 MPD
Section 2, Task 53-734-00, whichever occurs later.
Yes  No
-DO PART 2: INTERNAL AND EXTERNAL
DETAILED INSPECTION for signs of corrosion.
-Do PART 3: TORQUE CHECK for loose bolt.
Before further flight. (a) (b)
Corrosion
AND/OR  Yes
Loose bolt?
No
ACTION 1: Repeat PART 2:
INTERNAL AND EXTERNAL
DETAILED INSPECTION and
PART 3: TORQUE CHECK, not  Do PART 5: BARREL
to exceed 18 months. (b)  NUT REPLACEMENT
before further flight. (b)
ACTION 2: Do PART 5:
BARREL NUT REPLACEMENT
within 36 months after the
Original Issue date of this
Service Bulletin. (b)
No turther action is
required
(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.
APPENDIX A: COMPLIANCE TASKS AND COMPLIANCE TIMES LOGIC DIAGRAM
(SHEET 1 OF 1)
Original Issue: August 12, 2014
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0261
Work - See page 1 for details.  39 of 40

### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-53A0261
ALERT  ALERT
Boeing Service Bulletin Input Survey
After review of this service bulletin, Boeing asks that the primary engineer fill out this survey to help Boeing
predict the quantity and timing of Boeing supplied kits. This survey is only to help schedule kit/part availability
based on a preliminary review and is not a commitment to order.
Airline:
Contact Name:
Date:
Contact E-mail:
• Yes  • No Have/will you recommend to your airline to accomplish this service bulletin?
_ Yes  No Would issuance of an NPRM change this decision?
_ Yes  No Would issuance of an AD change this decision?
When would you likely be starting this SB incorporation? Month/ Year
How many airplanes per month do you plan to accomplish? Airplane/Month
How many total airplanes do you plan to complete? Total Airplanes
For inspection Service Bulletins, are you planning to replace on condition, or a fleet campaign to replace on
all airplanes regardless of condition?
• On Condition  _ Campaign
If you are not incorporating this Service Bulletin at this time will you please help us understand the reason/s
why? Your input will help us provide better customer support.
• Cost Prohibitive  - Continue Inspections  • Other
Operator Comments:
Within 45 days of the SB issue, or as soon after as possible, please scan and send this to:
sbsolutions@boeing.com
Disclaimer: The data provided in this survey will be used for planning purposes only and does not
consitute a commitment on any part of the airlines to purchase the parts in question, nor does it consitute a  2285062
commitment on the part of Boeing to deliver the parts in question.  This survey is a projection to help
Boeing forecast demand levels and timing to better support the customers schedule.
APPENDIX B: INPUT SURVEY
(SHEET 1 OF 1)
Original Issue: August 12, 2014
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0261
Work - See page 1 for details.  40 of 40

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