# Boeing Alert Service Bulletin 767-57A0076: Revision 3

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2012-0108; AD 2015-15-06 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 767-57A0076](https://openairdocs.org/service-documents/boeing/767-57a0076.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin 767-57A0076-03
- Pages: 46
- PDF: https://openairdocs.org/files/sha256/b4/e2/b4e2617974fe05c0169a08ff61cfee49fc030e2d461cfbac1465fb810bcc4c96
- Page: https://openairdocs.org/service-documents/boeing/767-57a0076/file/b4e2617974fe

## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-57A0076
Original Issue: October 26, 2000
Revision 3: April 04, 2012
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting
Assembly Inspection and Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). 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 © 2000 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
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, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the
Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in
connection with this document unless provided in writing by Boeing.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 9
1. PLANNING INFORMATION ........................................ 1 3
A. Effectivity ............................................... 1 3
1. Airplanes ............................................ 1 3
2. Spares Affected ........................................ 1 8
B. Concurrent Requirements ...................................... 1 8
C. Reason ................................................ 1 8
D. Description .............................................. 1 9
E. Compliance .............................................. 2 0
F. Approval ............................................... 2 0
G. Manpower .............................................. 2 1
H. Weight and Balance Changes .................................... 2 2
I. Electrical Load Data ......................................... 2 2
J. References .............................................. 2 2
1. Existing Data: ......................................... 2 2
2. Data supplied with this Service Bulletin: ........................... 2 2
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 2
K. Publications Affected ........................................ 2 3
L. Interchangeability and Intermixability of Parts ........................... 2 3
2. MATERIAL INFORMATION ........................................ 2 5
A. Material - Price and Availability ................................... 2 5
B. Industry Support Information .................................... 2 5
C. Parts Necessary For Each Airplane ................................. 2 5
1. Kits/Parts: ........................................... 2 5
2. Parts and Materials Supplied by the Operator: ........................ 2 5
3. Parts Modified and Reidentified: ............................... 2 6
4. Parts Removed and Not Replaced: .............................. 2 7
D. Parts Necessary to Change Spares ................................. 2 7
E. Special Tooling - Price and Availability ............................... 2 8
F. Special Tooling Necessary to do this Service Bulletin ....................... 2 8
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 2 9
A. GENERAL INFORMATION ..................................... 2 9
B. WORK INSTRUCTIONS ....................................... 3 0
FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES ....... 3 3
FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION ................. 3 4
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION .... 3 8
FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT ...................... 4 3
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767-57A0076Revision 3: April 04, 2012
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ALERTALERT
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 767-57A0076Original Issue: October 26, 2000
Revision 3: April 04, 2012
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting
Assembly Inspection and Replacement
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01 is related to this service bulletin.
No more work is necessary on airplanes which previously accomplished Part 3 - Terminating Action of this
service bulletin.
No more work is necessary on airplanes that have been previously inspected in accordance with the original
issue, Revision 1, or Revision 2 that have hinge fittings with the tool runout.
No more work is necessary on airplanes that have been previously inspected in accordance with the original
issue, Revision 1, or Revision 2 that have hinge fittings without the tool runout but continued inspections are
required at reduced intervals as follows:
1. Airplanes that were last inspected in accordance with Part 1 - Detailed Inspection: Repeat Part 1 - Detailed
Inspection or Do Part 2 - Detailed and Eddy Current Inspection within 300 flight-cycles of the last Part 1 -
Detailed Inspection.
2. Airplanes that were last inspected in accordance with Part 2 - Detailed and Eddy Current Inspection: Repeat
Part 2 - Detailed and Eddy Current Inspection or Do Part 1 - Detailed Inspection within 750 flight-cycles,
from the last Part 2 - Detailed and Eddy Current Inspection or before 300 flight-cycles after the Revision 3
date of this service bulletin, whichever is later, but not to exceed 1,500 flight cycles.
Do continued inspections and actions in accordance with Paragraph 1.E., Compliance.
REASON FOR REVISION
This revision is sent to reduce the compliance time for the repeat inspection interval of the inboard trailing edge
main flap outboard hinge fittings and change the area and limit to the outboard half only. Subsequent to the
release of Revision 2 of this service bulletin, one operator reported finding a fractured hinge fitting assembly.
The fracture occurred on a hinge fitting assembly, that did not have the runout option, at approximately 780
flight-cycles after its last inspection, which was a significant number of flight-cycles before the next scheduled
repeat Part 2 inspection. As a result, the repeat inspection interval for Part 2 Inspection is reduced from 1500
flight-cycles to 750 flight-cycles. An examination of the fractured hinge fitting assembly showed that the crack
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started at the edge of the current inspection area. The service bulletin illustrations have been updated to clearly
show the expected crack location and direction. A new Boeing Service Related Problem (SRP) 767-SRP-57-0251
was initiated as a result of this in service report. This service bulletin also corrects the existing warranty date to
show remedies are available for airplanes in warranty as of March 8, 2000 instead of August 3, 2000. The latest
service bulletin format standards have also been updated where applicable.
Terminology has been changed in the Work Instructions to agree with the terminology defined in Paragraph
3.A., General Information - Notes.
These sections are changed:
1. Service Bulletin Title updated.
2. Summary - Background - Reference to Boeing Service Related Problem (SRP) 767-SRP-57-0251 added.
3. Summary - Industry Support Information - Warranty date updated.
4. Summary - Illustration - Illustration updated to show the expected crack location and direction.
5. Paragraph 1.C., Reason - Reference to Boeing Service Related Problem (SRP) 767-SRP-57-0251 added.
6. Paragraph 1.D., Description - Affected Maintenance Zone Table added.
7. Paragraph 1.G., Manpower - Table updated.
8. Paragraph 1.J.1., Existing Data - Reference to Boeing Service Related Problem (SRP) 767-SRP-57-0251
added.
9. Paragraph 1.K.1, Publications - Table updated.
10. Paragraph 1.K.2., Damage Tolerance Based Structural Inspections - Damage Tolerance Inspections (DTI)
statement added.
11. Paragraph 2.B., Industry Support Information - Warranty date updated.
12. Paragraph 3.A., General Information - General notes updated.
13. Paragraph 3.B., Work Instructions - Titles updated and the latest service bulletin format standards have
also been updated where applicable.
14. Figure 1 - Compliance information in the logic table updated.
15. Figure 2 - Illustrations and step table updated to incorporate the new inspection requirements.
16. Figure 3 - Illustrations and step table updated to incorporate the new inspection requirements.
The data given in Information Notice 767-57A0076 IN 01 is included in this revision.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
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REVISION HISTORY
October 26, 2000Original Issue:
March 29, 2001Revision 1:
November 22, 2006Revision 2:
April 04, 2012Revision 3:
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767-57A0076Revision 3: April 04, 2012
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ALERTALERT
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-57A0076Original Issue: October 26, 2000
Revision 3: April 04, 2012
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting
Assembly 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 detect cracks, prevent fractures and ensure the structural integrity
of the inboard trailing edge main flap outboard hinge fittings. Fracture of the hinge fitting assemblies could result
in the inboard aft flap becoming unrestrained potentially striking the aircraft upon departure, resulting in significant
damage to the surrounding structure and cause potential personal injury.
One operator reported lug fractures on both the inboard and outboard hinge fittings of the outboard hinge
assembly mounted to the main flap. The hinge assembly provides one of two primary attachment points of the
inboard trailing edge aft flap. The outboard hinge fitting was fractured just above the lug hole. The fractured
hinge fittings were found during a routine maintenance inspection. The airplane had accumulated 9,598 flight-hours
and 5,393 flight-cycles.
During root cause analysis of the fractured hinge fitting it was discovered that an optional tool runout was not
present on the damaged fitting assembly. The tool runout option allows the part to be machined thicker within
the area reported to be fractured. Boeing has received no reports of cracks or fractures on fittings that have the
optional tool runout.
Replacement of the hinge fittings without the tool runout option will ensure the structural integrity of the aft flap,
prevent damage to the surrounding structure and the potential for personal injury.
Subsequent to the release of Revision 2 of this service bulletin, one operator reported finding a fractured hinge
fitting assembly. The fracture occurred on a hinge fitting assembly, that did not have the runout option, at
approximately 780 flight-cycles after its last inspection, which was a significant number of flight-cycles before
the next scheduled repeat Part 2 inspection. The service bulletin illustrations have been updated to clearly show
the expected crack location and direction. A new Boeing Service Related Problem (SRP) 767-SRP-57-0251
was initiated as a result of this in service report.
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Boeing Service Related Problem (SRP) 767-SRP-57-0119 and 767-SRP-57-0251 are related to this service
bulletin.
ACTION
Inspect the inboard trailing edge main flap outboard hinge fittings of the left and right wing for cracks, fractures
and tool runout option. If any cracks or fractures are found, complete terminating action. If fittings have the tool
runout option and no cracks or fractures are found, no further action is required. If fittings do not have the tool
runout option and no cracks or fractures are found, repeat inspections until terminating action is completed.
EFFECTIVITY
767-200/300/300F Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the list of affected airplanes.
COMPLIANCE
Refer to FIGURE 1 Logic Diagram for Inspection and Maintenance Alternatives.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01 is related to this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are available for airplanes in warranty as of March 8, 2000. Please refer to Paragraph
2.B., Industry Support Information.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Operator Supplied Parts/Materials.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
SEE A
HINGE FITTING
ASSEMBLY
FWD
INBOARD FLAP - OUTBOARD LINKAGE
INSPECT OUTBOARD HINGE
FITTING FOR CRACKS OR
FRACTURES. IF CRACKS OR
FRACTURES ARE FOUND REPLACE
HINGE FITTING ASSEMBLY
LOCATION OF FATIGUE
FWD<  CRACKS AND FRACTURES
RIGHT WING SIMILAR  LEFT WING SHOWN  V37977
Original Issue: October 26, 2000
Revision 3: April 04, 2012  767-57A0076
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767-57A0076Revision 3: April 04, 2012
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-57A0076
Original Issue: October 26, 2000
Revision 3: April 04, 2012
ATA System: 5750
SUBJECT: WINGS - Trailing Edge and Trailing Edge Devices - Inboard Main Flap - Hinge Fitting
Assembly 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 Document 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 numbers 1 - 825.-1
Airplane Models:
767-200, 767-300, 767-300F
GroupVariable Number
1VA001 - VA020
1VA301 - VA315
1VA501 - VA530
1VA701 - VA719
1VA801 - VA810
1VB001 - VB002
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GroupVariable Number
1VB051 - VB055
1VB101 - VB125
1VB201 - VB202
1VB251 - VB253
1VB281 - VB284
1VB301 - VB302
1VB321 - VB332
1VB371 - VB373
1VB401
1VB441 - VB444
1VE001 - VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE069
1VE083 - VE086
1VE101 - VE104
1VE116 - VE118
1VE121 - VE126
1VE141 - VE152
1VE171 - VE172
1VF001 - VF002
1VF041 - VF042
1VF051
1VF061 - VF062
1VF071 - VF072
1VF091 - VF093
1VF101 - VF102
1VF161 - VF162
1VF171 - VF172
1VF180 - VF184
1VF251
1VK001 - VK016
1VK021 - VK022
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GroupVariable Number
1VK031 - VK056
1VK081 - VK113
1VK131 - VK133
1VK141 - VK148
1VK161 - VK164
1VK171
1VK181
1VK186
1VL001 - VL006
1VL011
1VL701 - VL703
1VL751 - VL755
1VL806 - VL807
1VL871 - VL873
1VL891 - VL900
1VL911 - VL914
1VL931 - VL932
1VL941
1VN001 - VN041
1VN051 - VN064
1VN081 - VN099
1VN111 - VN127
1VN130 - VN137
1VN151 - VN158
1VN163 - VN168
1VN171 - VN174
1VN191 - VN198
1VN211 - VN212
1VN221 - VN225
1VN231 - VN234
1VN241 - VN243
1VN251 - VN276
1VN291 - VN293
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GroupVariable Number
1VN301 - VN314
1VN371 - VN372
1VN376
1VN381 - VN388
1VN421 - VN427
1VN436
1VN471 - VN472
1VN491 - VN513
1VN531 - VN532
1VN536 - VN537
1VN541 - VN542
1VN546 - VN547
1VN551
1VN556 - VN557
1VN561 - VN562
1VN631 - VN638
1VN651 - VN658
1VN671 - VN672
1VN676
1VN681 - VN691
1VN731 - VN732
1VN751 - VN753
1VN791 - VN792
1VN811 - VN813
1VN921 - VN922
1VN931 - VN936
1VN951 - VN953
1VN966 - VN972
1VR051 - VR055
1VR201 - VR209
1VR251
1VR256 - VR257
1VR401
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GroupVariable Number
1VR421 - VR422
1VR426
1VR441
1VR461
1VR471 - VR472
1VS051 - VS056
1VS061
1VS066 - VS070
1VS073 - VS078
1VS091 - VS102
1VS111 - VS113
1VS131 - VS133
1VS136 - VS137
1VS176 - VS177
1VS186 - VS187
1VS196 - VS203
1VS206 - VS208
1VS211
1VS216 - VS217
1VS246 - VS248
1VS261 - VS262
1VS266 - VS274
1VS291
1VS301 - VS303
1VS306 - VS308
1VS316
1VS321 - VS324
1VS366 - VS367
1VS381 - VS382
1VS391 - VS392
1VS401
1VS466 - VS470
1VS486
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GroupVariable Number
1VS496 - VS497
1VS506 - VS507
1VW701 - VW721
1VW851
2. Spares Affected
Examine your inboard trailing edge main flap spares supply for the outboard hinge fitting assemblies
without the tool runout as identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any
parts are found, refer to Paragraph 2.C. for the recommended use.
B. Concurrent Requirements
None.
C. Reason
Accomplishment of this service bulletin will detect cracks, prevent fractures and ensure the structural
integrity of the inboard trailing edge main flap outboard hinge fittings. Fracture of the hinge fittings could
result in the inboard aft flap becoming unrestrained potentially striking the aircraft upon departure,
resulting in significant damage to the surrounding structure and cause potential personal injury.
One operator reported lug fractures on both the inboard and outboard hinge fittings of the outboard
hinge assembly mounted to the main flap. The hinge assembly provides one of two primary attachment
points of the inboard trailing edge aft flap. The outboard hinge fitting was fractured just above the lug
hole. The fractured hinge fittings were found during a routine maintenance inspection. The airplane
had accumulated 9,598 flight-hours and 5,393 flight-cycles.
During root cause analysis of the fractured hinge fitting it was discovered that an optional tool runout
was not present on the damaged fitting assembly. The tool runout option allows the part to be machined
thicker within the area reported to be fractured. Boeing has received no reports of cracks or fractures
on fittings that have the optional tool runout.
Replacement of the hinge fittings without the tool runout option will ensure the structural integrity of
the aft flap, prevent damage to the surrounding structure and the potential for personal injury.
Subsequent to the release of Revision 2 of this service bulletin, one operator reported finding a fractured
hinge fitting assembly. The fracture occurred on a hinge fitting assembly, that did not have the runout
option, at approximately 780 flight-cycles after its last inspection, which was a significant number of
flight-cycles before the next scheduled repeat Part 2 inspection. The service bulletin illustrations have
been updated to clearly show the expected crack location and direction. A new Boeing Service Related
Problem (SRP) 767-SRP-57-0251 was initiated as a result of this in service report.
Revision 1 was sent to inform operators of the following changes:
1. Revise Figure 2 and 3 to add an isometric view to further clarify the tool runout inspections.
2. Revise Figure 2 and 3 to add allowable surface mismatch tolerances for the inboard and outboard
hinge fitting assemblies.
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3. Revise industry support information to add warranty remedies.
4. Revise effectivity to limit airplanes to all 767-200, 767-300 and 767-300F line numbers 1 through
825.
Revision 2 was sent to add optional parts for the replacement outboard hinge fitting assemblies. The
optional parts are the same as the existing replacement parts except the production handling holes
are omitted.
Revision 2 makes the following changes to the service bulletin:
— Revised the warranty date in the Summary and Material Information section.
— Add optional parts for the replacement outboard hinge fittings in the Material Information section
and in Figure 4.
— Added note to the Material Information section and Figure 4 that the replacement hinge fitting may
require different length installation bolts due to variations in the thickness of the installation stack-up.
— Revise the Accomplishment Instructions, Part 3, Step 3 and 5 to show the correct access panels
555JT and 655JT.
— Revise the Accomplishment Instructions to clarify that the work is accomplished on both the left
and right wing.
— Add reference to the related FAA Airworthiness Directive (AD).
Revision 3 is sent to reduce the compliance time for the repeat inspection interval of the inboard trailing
edge main flap outboard hinge fittings and change the area and limit to the outboard half only.
Subsequent to the release of Revision 2 of this service bulletin, one operator reported finding a fractured
hinge fitting assembly. The fracture occurred on a hinge fitting assembly, that did not have the runout
option, at approximately 780 flight-cycles after its last inspection, which was a significant number of
flight-cycles before the next scheduled repeat Part 2 inspection. As a result, the repeat inspection
interval for Part 2 Inspection is reduced from 1500 flight-cycles to 750 flight-cycles. An examination of
the fractured hinge fitting assembly showed that the crack started at the edge of the current inspection
area. The service bulletin illustrations have been updated to clearly show the expected crack location
and direction. A new Boeing Service Related Problem (SRP) 767-SRP-57-0251 was initiated as a result
of this in service report. This service bulletin also corrects the existing warranty date to show remedies
are available for airplanes in warranty as of March 8, 2000 instead of August 3, 2000. The latest service
bulletin format standards have also been updated where applicable.
Boeing Service Related Problem (SRP) 767-SRP-57-0119 and 767-SRP-57-0251 are related to this
service bulletin.
D. Description
Inspect the inboard trailing edge main flap outboard hinge fittings of the left and right wing for cracks,
fractures and tool runout option. If any cracks or fractures are found, complete terminating action. If
fittings have the tool runout option and no cracks or fractures are found, no further action is required.
If fittings do not have the tool runout option and no cracks or fractures are found, repeat inspections
until terminating action is completed.
Revision 1 - No more work was necessary on airplanes changed as shown in the original issue of this
service bulletin.
Revision 2 - No more work was necessary on airplanes changed as shown in the original issue or
Revision 1 of this service bulletin.
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Revision 3 - No more work is necessary on airplanes which previously accomplished Part 3 - Terminating
Action of this service bulletin.
No more work is necessary on airplanes that have been previously inspected in accordance with the
original issue, Revision 1, or Revision 2 that have hinge fittings with the tool runout.
No more work is necessary on airplanes that have been previously inspected in accordance with the
original issue, Revision 1, or Revision 2 that have hinge fittings without the tool runout but continued
inspections are required at reduced intervals as follows:
1. Airplanes that were last inspected in accordance with Part 1 - Detailed Inspection: Repeat Part 1
- Detailed Inspection or Do Part 2 - Detailed and Eddy Current Inspection within 300 flight-cycles
of the last Part 1 - Detailed Inspection.
2. Airplanes that were last inspected in accordance with Part 2 - Detailed and Eddy Current Inspection:
Repeat Part 2 - Detailed and Eddy Current Inspection or Do Part 1 - Detailed Inspection within
750 flight-cycles, from the last Part 2 - Detailed and Eddy Current Inspection or before 300
flight-cycles after the Revision 3 date of this service bulletin, whichever is later, but not to exceed
1,500 flight cycles.
Do continued inspections and actions in accordance with Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
571, 671767-200, 767-300, 767-300F
E. Compliance
Refer to FIGURE 1 Logic Diagram for Inspection and Maintenance Alternatives.
Federal Aviation Administration (FAA) Airworthiness Directive AD 2003-13-01 is related to this service
bulletin.
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.
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This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft
Certification Office approves the Inspections and Terminating Action defined in this service bulletin as
an alternative method of compliance to the requirements of paragraph (a), (b) and (f) of AD 2003-13-01.
All provisions of AD 2003-13-01 that are not specifically referenced in the above statement remain fully
applicable and must be complied with.
G. Manpower
The table below shows an estimate of the man-hours necessary to do the fitting inspections and
replacement for each airplane. This estimate is for direct labor only, done by an experienced crew.
Adjust the estimate with operator man-hour data if necessary. The estimate does not include lost time.
These are some examples of lost time:
— Time to adjust to the workplace
— Time to schedule the work
— Time to examine the work
— Time to cure the materials
— Time to make the parts
— Time to find the tools.
Part 1 - Detailed Inspection
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
1.02.02Open Access
1.01.01Detailed Inspec-
tion
1.02.02Close Access
3.05.0TOTAL FOR EACH WING
6.010.0TOTAL FOR EACH AIRPLANE
Part 2 - Detailed and Eddy Current Inspection
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
1.02.02Open Access
1.01.01Detailed Inspec-
tion
1.51.51Eddy Current In-
spection
1.02.02Close Access
(a)(a)TOTAL FOR EACH WING
(a)(a)TOTAL FOR EACH AIRPLANE
(a) The total task hours and elapsed hours are not given as the work necessary for
each wing and airplane is variable.
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Part 3 - Terminating Action
Elapsed Time (Hours)Man-HoursNumber of PersonsTask
1.02.02Open Access
6.012.02Replace Fitting
1.02.02Close Access
8.016.0TOTAL FOR EACH WING
16.032.0TOTAL FOR EACH AIRPLANE
H. Weight and Balance Changes
None
I. Electrical Load Data
Not changed
J. References
1. Existing Data:
a. Boeing Service Related Problem (SRP) 767-SRP-57-0119, 767-SRP-57-0251
b. Component Maintenance Manual (CMM) 57-53-27
c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2003-13-01
d. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-50-10, 20-50-19
e. 767 Aircraft Maintenance Manual (AMM) 06-44-00, 27-51-00
f. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-19
2. Data supplied with this Service Bulletin:
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin:
TitleDrawing Number
FLAP INSTL - INBD T.E. FLAP113T2101
FLAP INSTL - INBD T.E. FLAP113T2000
MAIN FLAP INSTL - INBD T.E. FLAP113T2201
These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
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K. Publications Affected
1. Publications:
Chapter-SectionPublication
27-51767 Illustrated Parts Catalog
57-53Component Maintenance Manual
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
Refer to Paragraph 2.C., Parts Necessary for Each Airplane, for interchangeability and intermixability
information.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary for Each
Airplane, and Paragraph 2.D., Parts Necessary to Change Spares. As an alternative, operators can
purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and
supply data.
B. Industry Support Information
Boeing warranty remedies are available for 767 airplanes in warranty as of March 08, 2000. For
inspection task hour reimbursement for airplanes in warranty as of that date, send a warranty claim to
Boeing Commercial Airplanes Group - Warranties. If the condition described in this service bulletin is
found during the inspection for airplanes in warranty as of that date and additional task hours and parts
are required, send a warranty claim to Boeing Commercial Airplanes Group - Warranties. Please refer
to this service bulletin number and reference the airplane variable numbers in your purchase order.
C. Parts Necessary For Each Airplane
1. Kits/Parts:
None.
2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number / Specifica-
tion
(a)Outboard Hinge Fitting Assy - Left Wing1113T2271-43
113T2271Y43 (Optional)
(a)Outboard Hinge Fitting Assy - Right Wing1113T2271-44
113T2271Y44 (Optional)
(b) (e)Bolt4BACB30LE5K19
(b) (e)Bolt (Optional 1/64 Oversize)4BACB30LE5K19X
(b) (e)Bolt4BACB30LE5K20
(b) (e)Bolt (Optional 1/64 Oversize)4BACB30LE5K20X
(d)Shim4BACS40R015D015F
(d)Shim4BACS40R015D017F
(d)Washer8BACW10BP5CD
(d)Washer (Optional 1/64 Oversize)8BACW10BP51CD
(d)Washer8BACW10BP5DP
(d)Washer (Optional 1/64 Oversize)8BACW10BP51DP
(d)Nut8NAS1805-5L
(c)Sealant8
Ounces
BMS 5-95
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NotesNameQTYPart Number / Specifica-
tion
(c)Primer4
Ounces
BMS 10-11 Type I
(c)Grease4
Ounces
MIL-G-23827
(a) The 113T2271Y( ) optional part is identical to the 113T2271-( ) part except the optional
part omits the handling holes used in production.
(b) Refer to 767 Structural Repair Manual Chapter 51 for alternative fasteners.
(c) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for
supplier data.
(d) Use original shims located between the fitting assembly and the flap skin to maintain the
original hinge line geometry of the fittings. However if original shims are damaged, replace
shims. Maintain the thickness and location of the original shims.
(e) Due to variations in the hinge fitting installation stack-up thickness, it is possible that differ-
ent fastener lengths may be required. It is acceptable to install a different fastener length
of the same bolt type if required.
3. Parts Modified and Reidentified:
The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the
number of parts changed on each airplane.
NotesNew Part NumberNameQTYExisting Part
Number
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-13
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-14
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-23
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-24
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-29
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-30
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-33
(a) (b) (c) (d)-Hinge Fitting Assembly1113T2271-34
(a) Hinge Fitting Assemblies with tool runout found to have no cracks or fractures during inspec-
tions in accordance with this service bulletin.
(b) Make the change in accordance with this service bulletin.
(c) There is no equivalent Boeing part number for the changed part. Identify on the part that
the change in accordance with this service bulletin was made.
(d) You can use the existing part to replace the new or changed part. If you use the existing
part, you cancel the effect of the change given in this service bulletin.
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4. Parts Removed and Not Replaced:
None.
D. Parts Necessary to Change Spares
To get the parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NotesNameQTYPart Number
(d)Outboard Hinge Fitting Assy - Left Wing1113T2271-43
113T2271Y43 (Option-
al)
(d)Outboard Hinge Fitting Assy - Right Wing1113T2271-44
113T2271Y44 (Option-
al)
(a) (e)Bolt4BACB30LE5K19
(a) (e)Bolt (Optional 1/64 Oversize)4BACB30LE5K19X
(a) (e)Bolt4BACB30LE5K20
(a) (e)Bolt (Optional 1/64 Oversize)4BACB30LE5K20X
(c)Shim4BACS40R015D015F
(c)Shim4BACS40R015D017F
(c)Washer8BACW10BP5CD
(c)Washer (Optional 1/64 Oversize)8BACW10BP51CD
(c)Washer8BACW10BP5DP
(c)Washer (Optional 1/64 Oversize)8BACW10BP51DP
(c)Nut8NAS1805-5L
(b)Sealant8 ouncesBMS 5-95
(b)Primer4 ouncesBMS 10-11 Type I
(b)4 ouncesMIL-G-23827
(a) Refer to 767 Structural Repair Manual Chapter 51 for alternative fasteners.
(b) See the Qualified Products List at the end of the Boeing Material Specification
(BMS) for supplier data.
(c) Use original shims located between the fitting assembly and the flap skin to
maintain the original hinge line geometry of the fittings. However if original shims
are damaged, replace shims. Maintain the thickness and location of the original
shims.
(d) The 113T2271Y( ) optional part is identical to the 113T2271-( ) part except the
optional part omits the handling holes used in production.
(e) Due to variations in the hinge fitting installation stack-up thickness, it is possible
that different fastener lengths may be required. It is acceptable to install a different
fastener length of the same bolt type if required.
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E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
4. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
8. 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.
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9. 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.
10. 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.
11. This service bulletin includes functional test procedures for the systems changed by
this service bulletin. More functional tests can possibly be necessary in accordance
with standard maintenance practices because of interruption to other airplane systems.
12. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is
permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'
(dash) part number. Boeing Drawing 005W0900 contains more data.
B. WORK INSTRUCTIONS
Part 1 - Detailed Inspection
WARNING: TRAILING EDGE FLAPS ARE FAST ACTING. MAKE SURE THAT PERSONS AND
EQUIPMENT ARE CLEAR OF TRAILING EDGE FLAPS AND THE FLAP DRIVE
MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. ONCE THE
TRAILING FLAPS ARE DEPLOYED LOCKS MUST BE INSTALLED TO PREVENT
POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF THE FLAPS.
1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted
procedure.
2. Remove the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer
to 767 AMM 06-44-00 for location of these panels.
Right WingLeft Wing
671GL571GL
671GR571GR
3. On the left and right wing, do a detailed inspection of the inboard trailing edge main flap outboard
hinge fittings for cracks, fractures and tool runout option in accordance with FIGURE 2.
4. If cracked or fractured fittings are found, do Part 3 - Terminating Action.
5. If fittings have the tool runout option and no cracks or fractures are found, mark the incorporation
of this service bulletin on each hinge fitting assembly by rubber stamp or stencil method. No further
action is required. Refer to SOPM 20-50-10 as an accepted procedure.
6. If fittings do not have the tool runout option and no cracks or fractures are found, repeat the
inspections at the intervals shown in accordance with FIGURE 1 until terminating action is
completed.
7. Install the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to
767 AMM 06-44-00 for location of these panels.
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Right WingLeft Wing
671GL571GL
671GR571GR
8. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure.
9. Put the airplane back to a serviceable condition.
Part 2 - Detailed and Eddy Current Inspection
WARNING: TRAILING EDGE FLAPS ARE FAST ACTING. MAKE SURE THAT PERSONS AND
EQUIPMENT ARE CLEAR OF TRAILING EDGE FLAPS AND THE FLAP DRIVE
MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. ONCE THE
TRAILING FLAPS ARE DEPLOYED LOCKS MUST BE INSTALLED TO PREVENT
POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF THE FLAPS.
1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted
procedure.
2. Remove the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer
to 767 AMM 06-44-00 for location of these panels.
Right WingLeft Wing
671GL571GL
671GR571GR
3. On the left and right wing, do a detailed and eddy current inspection of the inboard trailing edge
main flap outboard hinge fittings for cracks, fractures and tool runout option in accordance with
FIGURE 3.
4. If cracked or fractured fittings are found, do Part 3 - Terminating Action.
5. If fittings have the tool runout option and no cracks or fractures are found, mark the incorporation
of this service bulletin on each hinge fitting assembly by rubber stamp or stencil method. No further
action is required. Refer to SOPM 20-50-10 as an accepted procedure.
6. If fittings do not have the tool runout option and no cracks or fractures are found, repeat the
inspections at the intervals in accordance with FIGURE 1 until terminating action is completed.
7. Install the number 3 and 6 trailing edge aft flap adjustment access panels listed below. Refer to
767 AMM 06-44-00 for location of these panels.
Right WingLeft Wing
671GL571GL
671GR571GR
8. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure.
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9. Put the airplane back to a serviceable condition.
Part 3 - Terminating Action
WARNING: TRAILING EDGE FLAPS ARE FAST ACTING. MAKE SURE THAT PERSONS AND
EQUIPMENT ARE CLEAR OF TRAILING EDGE FLAPS AND THE FLAP DRIVE
MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. ONCE THE
TRAILING FLAPS ARE DEPLOYED LOCKS MUST BE INSTALLED TO PREVENT
POSSIBLE INJURY DUE TO INADVERTENT OPERATION OF THE FLAPS.
1. Extend and deactivate the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted
procedure.
2. Remove the number 3 and 6 trailing edge main flap fairing mid sections listed below. Refer to 767
AMM 06-44-00 for location of these fairing sections.
Right WingLeft Wing
671DB571DB
3. Remove the number 3 and 6 trailing edge main flap upper skin access panels listed below. Refer
to 767 AMM 06-44-00 for location of these panels.
Right WingLeft Wing
655JT555JT
4. On the left and right wing, replace the inboard trailing edge main flap outboard hinge fittings in
accordance with FIGURE 4.
NOTE: The outboard hinge fitting and the inboard hinge fitting are attached together to make the
hinge fitting assembly. If cracks or fractures are found on the outboard hinge fitting, it is
necessary to change both (inboard and outboard) hinge fittings.
5. Install the number 3 and 6 trailing edge main flap upper skin access panels listed below. Refer to
767 AMM 06-44-00 for location of these panels.
Right WingLeft Wing
655JT555JT
6. Install the number 3 and 6 trailing edge main flap fairing mid sections listed below. Refer to 767
AMM 06-44-00 for location of these fairing sections.
Right WingLeft Wing
671DB571DB
7. Activate and retract the trailing edge flaps. Refer to 767 AMM 27-51-00 as an accepted procedure.
8. Put the airplane back to a serviceable condition.
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BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
WITHIN 90 DAYS AFTER RELEASE OF REVISION 1 OF THIS
SERVICE BULLETIN, OR BEFORE THE AIRCRAFT HAS
ACCUMULATED 2,700 FLIGHT-CYCLES, WHICHEVER IS LATER,
DO ONE OF THE FOLLOWING INSPECTIONS
PART 1 - DETAILED  PART 2 - DETAILED AND
INSPECTION  EDDY CURRENT INSPECTION
FITTINGS WITHOUT  FITTINGS WITH  FITTINGS WITHOUT
TOOL RUNOUT FOUND  TOOL RUNOUT FOUND  TOOL RUNOUT FOUND
CRACKS OR  CRACKS OR  NO CRACKS OR  CRACKS OR
FRACTURE FOUND  FRACTURE FOUND  FRACTURE FOUND  FRACTURE FOUND
DO PART 3  CONTACT BOEING AND  NO  FURTHER  DO PART 3
TERMINATING ACTION  DO PART 3  ACTION  TERMINATING ACTION
TERMINATING ACTION  REQUIRED
NO CRACKS OR  NO CRACKS OR
FRACTURE FOUND  FRACTURE FOUND
WITHIN  DO PART 3  WITHIN
300 FLIGHT-CYCLES  TERMINATING ACTION  750 FLIGHT-CYCLES
REPEAT  REPEAT
PART 1  PART 2
DETAILED INSPECTION  DETAILED AND
EDDY CURRENT INSPECTION
AS OF REVISION 3 DATE OF THIS SERVICE BULLETIN, DO THE NEXT PART 2 INSPECTION
WITHIN 750 FLIGHT CYCLES FROM THE LAST PART 2 INSPECTION OR BEFORE 300 FLIGHT
CYCLES AFTER THE REVISION 3 DATE OF THIS SERVICE BULLETIN, WHICHEVER IS LATER,  BUT NOT TO EXCEED 1,500 FLIGHT CYCLES.  V37985
FIGURE 1: LOGIC DIAGRAM OF INSPECTION AND MAINTENANCE ALTERNATIVES
(SHEET 1 OF 1)
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### Page 34 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
SEE A
HINGE FITTING
ASSEMBLY
FWDS
INBOARD FLAP - OUTBOARD LINKAGE
FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION
(SHEET 1 OF 4)
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### Page 35 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
INBOARD HINGE
FITTING
OUTBOARD HINGE
FITTING
FWDE
HINGE FITTING
ASSEMBLY
HINGE FITTING WITH
TOOL RUNOUT
TYPICAL LOCATION
OF FATIGUE CRACKS
AND FRACTURES
DETAILED
INSPECTION AREA
HINGE FITTING WITHOUT  V37999
TOOL RUNOUT
FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION
(SHEET 2 OF 4)
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### Page 36 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
5.68
5.62
0.81
0.75
FWD
0.37→
0.35
A-A
OUTBOARD HINGE FITTING
WITH TOOL RUNOUT
5.68
5.62
FWD
0.84
0.74
0.37
0.35
B-B
OUTBOARD HINGE FITTING  V48850
WITHOUT TOOL RUNOUT
FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION
(SHEET 3 OF 4)
Original Issue: October 26, 2000
Revision 3 April 04, 2012  BOEING PROPRIETARY -  767-57A0076
Copyright © Unpublished Work - See page 1 for details.  36 of 46

### Page 37

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 one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to remove loose dirt, grease and oil. Refer to SOPM
20-30-03 as an accepted procedure.
1113T2271-( )Outboard
Hinge Fit-
ting
Clean1
Do a Detailed Inspection for cracks or fractures as
indicated. (a)
1113T2271-( )Outboard
Hinge Fit-
ting
Inspect2
Do a Detailed Inspection to find out if the hinge fitting
configuration is machined with or without a tool runout.
Hinge fittings with the tool runout option will be thicker
in the lug area as indicated. (b)
1113T2271-( )Outboard
Hinge Fit-
ting
Inspect3
(a) On outboard hinge fitting only. Both faces on the outboard hinge fitting require inspection in the area
shown.
(b) This step is not required for the repeat inspections if the tool runout condition has previously been deter-
mined.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATAFLAG
NOTE
A (0.000 - 0.030) of an inch surface mismatch is allowable on the outboard fitting as indicated.1
FIGURE 2: OUTBOARD HINGE FITTING - DETAILED INSPECTION
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 26, 2000
767-57A0076Revision 3 April 04, 2012
37 of 46
BOEING SERVICE BULLETIN 767-57A0076
ALERTALERT

### Page 38 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
SEE A
HINGE FITTING
ASSEMBLY
FWDS
INBOARD FLAP - OUTBOARD LINKAGE
V38002
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION
(SHEET 1 OF 5)
Original Issue: October 26, 2000
Revision 3 April 04, 2012  767-57A0076
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  38 of 46

### Page 39 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
INBOARD HINGE
FITTING
OUTBOARD HINGE
FITTING
FWDE
HINGE FITTING
ASSEMBLY
HINGE FITTING WITH
TOOL RUNOUT
TYPICAL LOCATION
OF FATIGUE CRACKS
AND FRACTURES
SEE
DETAILED
INSPECTION AREA  HINGE FITTING WITHOUT  V38000
TOOL RUNOUT
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION
(SHEET 2 OF 5)
Original Issue: October 26, 2000
Revision 3 April 04, 2012  BOEING PROPRIETARY -  767-57A0076
Copyright © Unpublished Work - See page 1 for details.  39 of 46

### Page 40 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
5.68
5.62
0.81
0.75
FWD
0.37
0.35
A-A
OUTBOARD HINGE FITTING
WITH TOOL RUNOUT
5.68
5.62
FWD
0.84
0.74
0.37
0.35
B-B
OUTBOARD HINGE FITTING
WITHOUT TOOL RUNOUT  V48851
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION
(SHEET 3 OF 5)
Original Issue: October 26, 2000
Revision 3 April 04, 2012  BOEING PROPRIETARY -  767-57A0076
Copyright © Unpublished Work - See page 1 for details.  40 of 46

### Page 41 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
TYPICAL
LOCATION OF
FATIGUE
CRACKS AND
FRACTURES
1.00-1.50
0.25-0.50
OUTBOARD HINGE FITTING
1.00-1.50  WITHOUT TOOL RUNOUT
OUTBOARD HINGE
FITTING WITHOUT
TOOL RUNOUT
1.00-1.50
¡ EDDY CURRENT
INSPECTION AREA
VIEW C-C  2120055
INSPECTION AREA
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION
(SHEET 4 OF 5)
Original Issue: October 26, 2000
Revision 3 April 04, 2012  767-57A0076
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  41 of 46

### Page 42

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 one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
to remove loose dirt, grease and oil. Refer to SOPM
20-30-03 as an accepted procedure.
1113T2271-( )Out-
board
Hinge
Fitting
Clean1
Do a Detailed Inspection for cracks or fractures as
indicated. (a)
1113T2271-( )Out-
board
Hinge
Fitting
Inspect2
Do a Detailed Inspection to find out if the hinge fitting
configuration is machined with or without the tool
runout. Hinge fittings with the tool runout option will
be thicker in the lug area as indicated. (b)
113T2271-( )Out-
board
Hinge
Fitting
Inspect3
Do an Eddy Current inspection. Use a right angle
pencil probe with a maximum drop of 0.1 inch to in-
spect the area for cracks in accordance with 767 NDT
Part 6, 51-00-01 or 767 NDT Part 6, 51-00-19. (a) (c)
1113T2271-( )Out-
board
Hinge
Fitting
Inspect4
(a) On outboard hinge fitting only. Both faces on the outboard hinge fitting require inspection in the area
shown.
(b) This step is not required for the repeat inspections if the tool runout condition has previously been deter-
mined.
(c) This step is not necessary if the outboard hinge fitting has the tool runout option.
The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.
MORE DATAFLAG
NOTE
A (0.000 - 0.030) of an inch surface mismatch is allowable on the outboard fitting as indicated.1
FIGURE 3: OUTBOARD HINGE FITTING - DETAILED AND EDDY CURRENT INSPECTION
(SHEET 5 OF 5)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 26, 2000
767-57A0076Revision 3 April 04, 2012
42 of 46
BOEING SERVICE BULLETIN 767-57A0076
ALERTALERT

### Page 43 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
SEE
INBOARD FLAP - OUTBOARD LINKAGE
V39022
FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT
(SHEET 1 OF 4)
Original Issue: October 26, 2000
Revision 3 April 04, 2012  BOEING PROPRIETARY -  767-57A0076
Copyright © Unpublished Work - See page 1 for details.  43 of 46

### Page 44 (OCR)

BOEING SERVICE BULLETIN 767-57A0076
ALERT  ALERT
SHIM B 4  DO SHIM A
A DE (2 LOCATIONS)
(2 LOCATIONS) 25) B
FLAP SKIN
UP  SEE ®
FWD '
SHIM A 45
(2 LOCATIONS) (3)5  DO SHIM B
• FLAP SKIN
UP
→FWD
V39031
FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT
(SHEET 2 OF 4)
Original Issue: October 26, 2000
Revision 3 April 04, 2012  767-57A0076
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  44 of 46

### Page 45

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 one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Maintain fasteners location and stack-up
for later installation. Refer to CMM 57-53-
27 as an accepted procedure.
4-FastenersRemove /
Keep
1
4-FastenersRemove2
1113T2271-( )Hinge Fitting
Assembly
Remove3
Maintain original location of shims. If shims
are damaged, replace shims maintaining
the original thickness. Apply BMS 10-11
Type I primer to replacement shims and
any bare surfaces of the original shims.
Refer to SOPM 20-41-02 as an accepted
procedure.
2BACS40R015D015FShims "A"Remove /
Keep
4
2BACS40R015D017FShims "B"
(a) Locate and install hinge fitting with kept
or identical replacement shims in the same
location to maintain the original hinge line
geometry of the fitting. Refer to CMM 57-
53-27 as an accepted procedure. Fay seal
shims and install fasteners wet with BMS
5-95 common to fitting assembly and the
main flap. Refer to SOPM 20-50-19 as an
accepted procedure. Install kept fasteners
common to the flap linkage and hinge fit-
tings with MIL-G-23827 grease. Refer to
CMM 57-53-27 as an accepted procedure.
1113T2271-43 or
113T2271Y43 (Optional)
Hinge Fitting
Assembly
(Left)
Install
(New)
5
1113T2271-44 or
113T2271Y44 (Optional)
Hinge Fitting
Assembly
(Right)
2BACS40R015D015FShims "A"
(Kept)
2BACS40R015D017FShims "B"
(Kept)
4-Fasteners
(New)
4-Fasteners
(Kept)
the incorporation of this service bulletin on
each hinge fitting assembly. Refer to
SOPM 20-50-10 as an accepted proce-
dure.
--Rubber Stamp
or Stencil
Identify6
(a) The 113T2271Y( ) optional part is identical to the 113T2271-( ) part except the optional part omits the
handling holes used in production.
FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT
(SHEET 3 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 26, 2000
767-57A0076Revision 3 April 04, 2012
45 of 46
BOEING SERVICE BULLETIN 767-57A0076
ALERTALERT

### Page 46

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.
MORE DATAIDENTIFICATIONNAMECODE
(a) Install bolts wet with BMS 5-95
Sealant. Refer to SOPM 20-50-19 as an
accepted procedure.
BACB30LE5K19NominalBoltA
BACB30LE5K19XOptional 1/64 Oversize
BACW10BP5CDNominalWasher
BACW10BP51CDOptional 1/64 Oversize
BACW10BP5DPNominalWasher
BACW10BP51DPOptional 1/64 Oversize
NAS1805-5LNut
(a) Install bolts wet with BMS 5-95
Sealant. Refer to SOPM 20-50-19 as an
accepted procedure.
BACB30LE5K20NominalBoltB
BACB30LE5K20XOptional 1/64 Oversize
BACW10BP5CDNominalWasher
BACW10BP51CDOptional 1/64 Oversize
BACW10BP5DPNominalWasher
BACW10BP51DPOptional 1/64 Oversize
NAS1805-5LNut
(a) Due to variations in the hinge fitting installation stack-up thickness, it is possible that different fastener
lengths may be required. It is acceptable to install a different fastener length of the same bolt type if re-
quired.
FIGURE 4: HINGE FITTING ASSEMBLY - REPLACEMENT
(SHEET 4 OF 4)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 26, 2000
767-57A0076Revision 3 April 04, 2012
46 of 46
BOEING SERVICE BULLETIN 767-57A0076
ALERTALERT

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