# Boeing Alert Service Bulletin 767-57A0117: Revision 1

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- Document: [Boeing Alert Service Bulletin 767-57A0117](https://openairdocs.org/service-documents/boeing/767-57a0117.md)
- Title as filed: U.S.DOT/FAA- Service Bulletin
- Pages: 113
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-57A0117
Original Issue: October 01, 2009
Revision 1: March 02, 2011
ATA System: 5700
SUBJECT: WINGS - Skins - Upper Wing Skin Panel at Front Spar Pitch Load Fitting Attachment
- Inspection and Repair
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 © 2009 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Unpublished Work - All Rights Reserved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 ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 8
B. Concurrent Requirements ...................................... 1 8
C. Reason ................................................ 1 9
D. Description .............................................. 1 9
E. Compliance .............................................. 2 0
F. Approval ............................................... 6 9
G. Manpower .............................................. 7 0
H. Weight and Balance Changes .................................... 7 1
I. Electrical Load Data ......................................... 7 1
J. References .............................................. 7 1
1. Existing Data .......................................... 7 1
2. Data supplied with this Service Bulletin ............................ 7 1
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 7 1
K. Publications Affected ........................................ 7 2
L. Interchangeability and Intermixability of Parts ........................... 7 2
2. MATERIAL INFORMATION ........................................ 7 3
A. Material - Price and Availability ................................... 7 3
B. Industry Support Information .................................... 7 4
C. Parts Necessary For Each Airplane ................................. 7 4
1. Kits/Parts ............................................ 7 4
2. Parts and Materials Supplied by the Operator ........................ 7 5
3. Parts Modified and Reidentified ................................ 7 6
4. Parts Removed and Not Replaced .............................. 7 6
D. Parts Necessary to Change Spares ................................. 7 6
E. Special Tooling - Price and Availability ............................... 7 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 7 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 7 7
A. GENERAL INFORMATION ..................................... 7 7
B. WORK INSTRUCTIONS ....................................... 7 8
FIGURE 1: ULTRASONIC INSPECTION OF THE UPPER WING SKIN AT THE FRONT SPAR PITCH LOAD
FITTING OF THE LEFT WING ................................ 8 2
FIGURE 2: ULTRASONIC INSPECTION OF THE UPPER WING SKIN AT THE FRONT SPAR PITCH LOAD
FITTING OF THE RIGHT WING ................................ 8 4
FIGURE 3: HFEC INSPECTION OF THE UPPER WING SKIN FASTENER HOLES AT THE FRONT SPAR
PITCH LOAD FITTING OF THE LEFT WING ......................... 8 6
FIGURE 4: HFEC INSPECTION OF THE UPPER WING SKIN FASTENER HOLES AT THE FRONT SPAR
PITCH LOAD FITTING OF THE RIGHT WING ........................ 8 8
FIGURE 5: HOLE REPAIR ......................................... 9 0
FIGURE 6: FREEZE PLUG REPAIR .................................... 9 3
FIGURE 7: FASTENER REPLACEMENT, LEFT WING [Group 1-2, 4-5, 8] ............... 9 5
FIGURE 8: FASTENER REPLACEMENT, RIGHT WING [Group 1-2, 4-5, 8] ............. 1 0 0
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FIGURE 9: FASTENER REPLACEMENT, LEFT WING [Group 3, 6-7, 9] ............... 1 0 5
FIGURE 10: FASTENER REPLACEMENT, RIGHT WING [Group 3, 6-7, 9] ............... 1 0 9
APPENDIX A: SUPPLEMENTAL FASTENER REPLACEMENT (EXAMPLE) ............... 1 1 3
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Revision Transmittal SheetNumber: 767-57A0117Original Issue: October 01, 2009
Revision 1: March 02, 2011
ATA System: 5700
SUBJECT: WINGS - Skins - Upper Wing Skin Panel at Front Spar Pitch Load Fitting Attachment
- Inspection and Repair
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplane(s) inspected or changed in accordance with the original issue of this
service bulletin. However, the initial inspection threshold grace period for airplanes that have not accomplished
the inspection in accordance with this service bulletin have been reduced and may require earlier inspections.
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-217-AD, is related to
this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directives AD 2000-19-09 and AD 2004-16-12 are related
to this service bulletin.
REASON FOR REVISION
This revision is sent to revise the Compliance Tables to reduce the inspection grace period times due to inspection
findings in the fleet.
These sections were changed:
1. In Summary, Background, added information about fleet inspection findings.
2. In Summary, Compliance, added NPRM and AD information.
3. In Paragraph 1.C., Reason, added information about fleet inspection findings.
4. In Paragraph 1.E., Compliance, added NPRM and AD information.
5. In Paragraph 1.E., Compliance, revised the compliance information in Table 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11,
12, 13 and 14.
6. In Paragraph 1.E., Compliance, revised the description of the conditions in Table 1, 2, 3, 4, 5, 6, 7, 8, 9,
10, 11, 12, 13 and 14.
7. In Paragraph 1.F., Approval, added Alternate Method of Compliance statement.
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8. In Paragraph 2.A., Material - Price and Availability, changed the table to apply effectivity.
9. In Paragraph 3.A., General Information, added notes about access and tool use.
10. In Paragraph 3.B., Accomplishment Instructions, revised the position of the slats.
11. In Paragraph 3.B., Accomplishment Instructions, revised the description of the conditions.
12. In Paragraph 3.B., Accomplishment Instructions, Figure 3, revised the reference for titanium fittings.
13. In Paragraph 3.B., Accomplishment Instructions, Figure 3, added a footnote about fastener removal.
14. In Paragraph 3.B., Accomplishment Instructions, Figure 4, revised the reference for titanium fittings.
15. In Paragraph 3.B., Accomplishment Instructions, Figure 4, added a footnote about fastener removal.
16. In Paragraph 3.B., Accomplishment Instructions, Figure 5, revised the 'Inspect' More Data column.
17. In Paragraph 3.B., Accomplishment Instructions, Figure 5, revised the 'Ream' More Data column.
18. In Paragraph 3.B., Accomplishment Instructions, Figure 5, revised footnote (a).
19. In Paragraph 3.B., Accomplishment Instructions, Figure 5, added a footnote (c) about fastener removal.
20. In Paragraph 3.B., Accomplishment Instructions, Figure 5, revised Table 1 and Table 2.
21. In Paragraph 3.B., Accomplishment Instructions, Figure 6, revised the 'Inspect' More Data column.
The data given in Information Notices 767-57A0117 IN-01, IN-02 and IN-03 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.
REVISION HISTORY
October 01, 2009Original Issue:
March 02, 2011Revision 1:
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-57A0117Original Issue: October 01, 2009
Revision 1: March 02, 2011
ATA System: 5700
SUBJECT: WINGS - Skins - Upper Wing Skin Panel at Front Spar Pitch Load Fitting Attachment
- Inspection and Repair
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
Accomplishment of this service bulletin will find possible cracks in the upper wing skin at the fastener holes
common to the inboard and outboard front spar pitch load fittings. Undetected upper wing skin cracks at the
fastener holes common to the inboard and outboard front spar pitch load fittings could result in the loss of the
strut-to-wing upper link load path and possible separation of a strut and engine from the airplane during flight.
Multiple operators have reported a total of 36 cracks in the upper wing skin at the fastener holes common to the
inboard and outboard front spar pitch load fittings. The reported airplanes had accumulated between 11,700
and 39,900 total flight-cycles and 28,700 and 83,100 total flight-hours. The reported crack lengths were between
0.016 and 0.140 inch. All cracks were found during accomplishment of the open hole high frequency eddy current
(HFEC) inspections given in strut improvement service bulletins 767-54-0080, 767-54-0081 or 767-54-0082.
Further Boeing analysis has determined the cracks to be a result of fatigue due to higher than predicted fastener
load and skin stress peaking along the aft fastener row.
Subsequent to the original issue of this service bulletin, one operator accomplishing this service bulletin reported
finding a fastener hole with significant crack sizes of 0.53 inches and 0.31 inches on either side of the hole. The
subject airplane had accumulated 18,900 flight cycles and 89,500 flight hours at the time of the inspection.
This service bulletin provides instructions to inspect the upper wing skin at the fastener holes common to the
inboard and outboard front spar pitch load fittings for cracks and repair the holes if cracks are found. Inspection
and repair will prevent undetected upper wing skin cracks at the fastener holes common to the inboard and
outboard front spar pitch load fittings that could result in the loss of the strut-to-wing upper link load path and
possible separation of a strut and engine from the airplane during flight.
Boeing Service Related Problem 767-SRP-57-0206 is related to this service bulletin.
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ACTION
Get access to the upper wing skin at the front spar pitch load fitting. Do a detailed and ultrasonic inspection or
do a HFEC open hole inspection of the fastener holes common to the front spar pitch load fitting and wing skin
for cracks. If any crack is found, repair the hole by oversizing the hole or installing a freeze plug. If no crack is
found, continue to perform repeat inspections. If the crack is too large to repair, contact Boeing for repair
instructions.
EFFECTIVITY
All 767-200, -300, -300F and -400ER Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected
airplanes.
COMPLIANCE
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-217-AD, is related to
this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directives AD 2000-19-09 and AD 2004-16-12 are related
to this service bulletin.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection,and/or repair procedures given in this service
bulletin.
MANPOWER
For detailed Manhour estimates, refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Boeing Supplied Kits/Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-57A0117
ALERT  ALERT
LEFT WING SHOWN
(RIGHT WING OPPOSITE)
10 80
DO A DETAILED AND ULTRASONIC INSPECTION OR
DO A HFEC OPEN HOLE INSPEC  •TION OF THE
FASTENER HOL  JES  COMMON  O THE FRONT SPAR
PITCH LOAD FI  ING AND WING SKIN FOR CRACKS
UPPER
SKIN
UPPER
LINK
FRONT SPAR PITCH
LOAD FITTINGS
FWD  1539002
Original Issue: October 01, 2009
Revision 1: March 02, 2011  767-57A0117
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-57A0117
Original Issue: October 01, 2009
Revision 1: March 02, 2011
ATA System: 5700
SUBJECT: WINGS - Skins - Upper Wing Skin Panel at Front Spar Pitch Load Fitting Attachment
- Inspection and Repair
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplanes shown below.
Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
NOTE: This service bulletin is for the airplanes identified below. The effectivity list shown below
is complete for airplanes through line number 1009. At least one airplane after line number
1009 is also affected by this service bulletin, and these airplanes are in Group(s) 3,6,7,9.
These airplanes will be added to the service bulletin's MyBoeingFleet.com (MBF) \"get
effectivity\" result when they are added to the MBF Fleet Profile Page.
DESCRIPTIONCONFIGURATIONGROUP
767-200, -300 and -300F Airplanes with Pratt and Whitney JT9D
engines with line numbers 1-663.
-1
Airplanes that have not accomplished SB 767-54-0080.1
Airplanes that have accomplished SB 767-54-0080.2
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DESCRIPTIONCONFIGURATIONGROUP
767-200, -300 and -300F Airplanes with Pratt and Whitney PW4000
engines with line numbers 1-663.
-2
Airplanes that have not accomplished SB 767-54-0080.1
Airplanes that have accomplished SB 767-54-0080.2
767-200, -300 and -300F Airplanes with Pratt and Whitney engines
with line numbers 664 and on.
-3
767 Airplanes with General Electric CF6-80A engines with line
numbers 1-663.
-4
Airplanes that have not accomplished SB 767-54-0081.1
Airplanes that have accomplished SB 767-54-0081.2
767-200, -300 and -300F Airplanes with General Electric CF6-80C2
engines with line numbers 1-663.
-5
Airplanes that have not accomplished SB 767-54-0081.1
Airplanes that have accomplished SB 767-54-0081.2
767-200, -300 and -300F Airplanes with General Electric engines
with line numbers 664 and on.
-6
767-400ER Airplanes with General Electric engines.-7
767-200, -300 and -300F Airplanes with Rolls Royce engines with
line numbers 1-663.
-8
Airplanes that have not accomplished SB 767-54-0082.1
Airplanes that have accomplished SB 767-54-0082.2
767-200, -300 and -300F Airplanes with Rolls Royce engines with
line numbers 664 and on.
-9
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
1VA001 - VA020
4VA301 - VA315
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GroupVariable Number
4VA501 - VA530
1VA701 - VA719
1VA801 - VA810
1VB001 - VB002
4VB051 - VB055
4VB101 - VB125
1VB201 - VB202
4VB251 - VB253
1VB281 - VB284
1VB301 - VB302
4VB321 - VB330
5VB331 - VB332
1VB371 - VB373
4VB401
5VB441 - VB444
1VE001 - VE003
1VE021 - VE023
1VE041 - VE043
1VE061 - VE069
1VE083 - VE084
2VE085 - VE086
4VE101 - VE104
4VE116 - VE118
5VE121 - VE126
5VE141 - VE152
2VE171 - VE172
5VF001 - VF002
5VF041 - VF042
5VF051
2VF061 - VF062
2VF071 - VF072
2VF091 - VF093
2VF101 - VF102
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GroupVariable Number
2VF161 - VF162
5VF171 - VF172
5VF180 - VF184
5VF251
1VK001 - VK011
5VK012 - VK015
6VK016
1VK021 - VK022
4VK031 - VK054
2VK055 - VK056
5VK081 - VK112
6VK113
5VK131 - VK133
5VK141 - VK147
6VK148
2VK161 - VK164
2VK171
6VK181
6VK186
5VL001 - VL006
2VL011
5VL701 - VL703
5VL751 - VL755
2VL806 - VL807
8VL871 - VL873
5VL891 - VL900
5VL911 - VL914
2VL931 - VL932
5VL941
5VN001 - VN041
5VN051 - VN064
5VN081 - VN098
6VN099
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GroupVariable Number
8VN111 - VN127
8VN130 - VN137
2VN151 - VN158
2VN163 - VN168
2VN171 - VN174
5VN191 - VN198
2VN211 - VN212
2VN221 - VN225
5VN231 - VN234
2VN241 - VN243
2VN251 - VN271
3VN272 - VN276
5VN291 - VN293
5VN301 - VN314
2VN371 - VN372
2VN376
2VN381 - VN388
5VN421 - VN427
5VN436
5VN471 - VN472
2VN491 - VN513
2VN531 - VN532
2VN536 - VN537
2VN541 - VN542
5VN546 - VN547
2VN551
2VN556 - VN557
2VN561 - VN562
2VN631 - VN633
5VN634 - VN638
5VN651 - VN657
6VN658
2VN671 - VN672
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GroupVariable Number
5VN676
2VN681 - VN691
5VN731 - VN732
5VN751 - VN753
5VN791 - VN792
5VN811 - VN813
5VN921 - VN922
2VN931 - VN936
5VN951 - VN953
2VN966 - VN967
5VN968 - VN969
6VN970
2VN971 - VN972
7VQ001 - VQ021
7VQ071 - VQ086
7VQ111
6VR051 - VR060
6VR081
6VR084
6VR086 - VR089
6VR106 - VR109
6VR201 - VR211
6VR251
6VR256 - VR260
6VR266 - VR277
6VR401
3VR421 - VR423
6VR426
6VR441
6VR461
3VR471 - VR472
6VS051 - VS056
3VS061
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GroupVariable Number
3VS066 - VS070
6VS073 - VS078
3VS091 - VS104
6VS111 - VS113
6VS131 - VS133
6VS136 - VS137
6VS176 - VS177
6VS186 - VS187
6VS196 - VS203
3VS206 - VS208
3VS211
6VS216 - VS217
6VS231
9VS246 - VS248
6VS261 - VS263
6VS266 - VS274
6VS291 - VS293
3VS301 - VS303
3VS306 - VS311
6VS316
6VS321 - VS324
6VS331 - VS333
6VS336 - VS337
6VS366 - VS367
6VS381 - VS382
6VS391 - VS392
6VS401
3VS426 - VS428
6VS466 - VS472
6VS486
3VS496 - VS497
3VS506 - VS507
6VS526
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GroupVariable Number
6VS546 - VS549
6VS701 - VS736
6VS751 - VS759
3VS821 - VS825
3VS841 - VS844
6VS861
3VS881 - VS883
6VS891
3VS896
6VS901 - VS910
3VS911 - VS912
3VS916
6VS921 - VS925
6VS931 - VS933
6VS941
6VS951 - VS954
6VS961 - VS965
6VS971 - VS972
6VS976
6VT501
6VT511 - VT513
6VT521 - VT523
6VT531 - VT533
6VT541 - VT543
5VW701 - VW716
6VW717 - VW721
5VW851
2. Spares Affected
None.
B. Concurrent Requirements
None.
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C. Reason
Accomplishment of this service bulletin will find possible cracks in the upper wing skin at the fastener
holes common to the inboard and outboard front spar pitch load fittings. Undetected upper wing skin
cracks at the fastener holes common to the inboard and outboard front spar pitch load fittings could
result in the loss of the strut-to-wing upper link load path and possible separation of a strut and engine
from the airplane during flight.
Multiple operators have reported a total of 36 cracks in the upper wing skin at the fastener holes common
to the inboard and outboard front spar pitch load fittings. The reported airplanes had accumulated
between 11,700 and 39,900 total flight-cycles and 28,700 and 83,100 total flight-hours. The reported
crack lengths were between 0.016 and 0.140 inch. All cracks were found during accomplishment of
the open hole high frequency eddy current (HFEC) inspections given in strut improvement service
bulletins 767-54-0080, 767-54-0081 or 767-54-0082. Further Boeing analysis has determined the cracks
to be a result of fatigue due to higher than predicted fastener load and skin stress peaking along the
aft fastener row.
Subsequent to the original issue of this service bulletin, one operator accomplishing this service bulletin
reported finding a fastener hole with significant crack sizes of 0.53 inches and 0.31 inches on either
side of the hole. The subject airplane had accumulated 18,900 flight cycles and 89,500 flight hours at
the time of the inspection.
This service bulletin provides instructions to inspect the upper wing skin at the fastener holes common
to the inboard and outboard front spar pitch load fittings for cracks and repair the holes if cracks are
found. Inspection and repair will prevent undetected upper wing skin cracks at the fastener holes
common to the inboard and outboard front spar pitch load fittings that could result in the loss of the
strut-to-wing upper link load path and possible separation of a strut and engine from the airplane during
flight.
Boeing Service Related Problem 767-SRP-57-0206 is related to this service bulletin.
Revision 1 is sent to revise the Compliance Tables to reduce the inspection grace period times due to
inspection findings in the fleet.
D. Description
Get access to the upper wing skin at the front spar pitch load fitting. Do a detailed and ultrasonic
inspection or do a HFEC open hole inspection of the fastener holes common to the front spar pitch
load fitting and wing skin for cracks. If any crack is found, repair the hole by oversizing the hole or
installing a freeze plug. If no crack is found, continue to perform repeat inspections. If the crack is too
large to repair, contact Boeing for repair instructions.
Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of
this service bulletin. However, the initial inspection threshold grace period for airplanes that have not
accomplished the inspection in accordance with this service bulletin have been reduced and may
require earlier inspections.
The work in this service bulletin is done in the maintenance zone(s) given below.
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ALERTALERT

### Page 20

Group 1-2, 4:
Affected Maintenance Zones
ZoneModel
511, 611767-200, 767-300
Group 3, 8-9:
Affected Maintenance Zones
ZoneModel
511, 611767-300
Group 5-6:
Affected Maintenance Zones
ZoneModel
511, 611767-200, 767-300, 767-300F
Group 7:
Affected Maintenance Zones
ZoneModel
511, 611767-400ER
E. Compliance
Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2009-NM-217-AD, is
related to this service bulletin.
Federal Aviation Administration (FAA) Airworthiness Directives AD 2000-19-09 and AD 2004-16-12
are related to this service bulletin.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
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BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 21

Group 1, Configuration 1:
Table 1: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 18,000
Total Flight Cy-
cles or 54,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
21 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 22

Group 1, Configuration 1:
Table 1: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
22 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 23

Group 1, Configuration 1:
Table 1: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
5,000 Flight Cycles
or 15,000 Flight
Hours (whichever
occurs first)
-Within 5,000
Flight Cycles or
15,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
23 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 24

Group 1, Configuration 1:
Table 1: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
Group 1, Configuration 2:
Table 2: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Within 11,000
Flight Cycles or
33,000 Flight
Hours After
Completing Ser-
vice Bulletin
767-54-0080
(whichever oc-
curs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
BOEING PROPRIETARY -
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Original Issue: October 01, 2009
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24 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 25

Group 1, Configuration 2:
Table 2: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
25 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 26

Group 1, Configuration 2:
Table 2: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
26 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 27

Group 1, Configuration 2:
Table 2: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
5,000 Flight Cycles
or 15,000 Flight
Hours (whichever
occurs first)
-Within 5,000
Flight Cycles or
15,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
27 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 28

Group 2, Configuration 1:
Table 3: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 12,000
Total Flight Cy-
cles or 36,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
28 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 29

Group 2, Configuration 1:
Table 3: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
29 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 30

Group 2, Configuration 1:
Table 3: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
5,000 Flight Cycles
or 15,000 Flight
Hours (whichever
occurs first)
-Within 5,000
Flight Cycles or
15,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
30 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 31

Group 2, Configuration 1:
Table 3: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
Group 2, Configuration 2:
Table 4: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Within 12,000
Flight Cycles or
36,000 Flight
Hours After
Completing Ser-
vice Bulletin
767-54-0080
(whichever oc-
curs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
31 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 32

Group 2, Configuration 2:
Table 4: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
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Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
32 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 33

Group 2, Configuration 2:
Table 4: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
33 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 34

Group 2, Configuration 2:
Table 4: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
5,000 Flight Cycles
or 15,000 Flight
Hours (whichever
occurs first)
-Within 5,000
Flight Cycles or
15,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
34 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 35

Group 3:
Table 5: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 12,000
Total Flight Cy-
cles or 36,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
7,000 Flight Cycles
or 21,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 7,000
Flight Cycles or
21,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
7,000 Flight Cycles
or 21,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 7,000
Flight Cycles or
21,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
35 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 36

Group 3:
Table 5: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to 0.469
inches.
-AND-
7,000 Flight Cycles
or 21,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 7,000
Flight Cycles or
21,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
36 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 37

Group 3:
Table 5: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.469 inches
and less than or equal to
0.477 inches. -AND-
7,000 Flight Cycles
or 21,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 7,000
Flight Cycles or
21,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.477 inches
and less than or equal to
0.540 inches.
-AND-
5,000 Flight Cycles
or 15,000 Flight
Hours (whichever
occurs first)
-Within 5,000
Flight Cycles or
15,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
37 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 38

Group 3:
Table 5: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
Group 4, Configuration 1:
Table 6: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 25,000
Total Flight Cy-
cles or 75,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
38 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 39

Group 4, Configuration 1:
Table 6: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
39 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 40

Group 4, Configuration 1:
Table 6: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
40 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 41

Group 4, Configuration 1:
Table 6: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
41 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 42

Group 4, Configuration 2:
Table 7: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Within 17,000
Flight Cycles or
51,000 Flight
Hours After
Completing Ser-
vice Bulletin
767-54-0081
(whichever oc-
curs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
42 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 43

Group 4, Configuration 2:
Table 7: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
43 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 44

Group 4, Configuration 2:
Table 7: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 17,000 Flight Cy-
cles or 51,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 17,000
Flight Cycles or
51,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
44 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 45

Group 4, Configuration 2:
Table 7: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
Group 5, Configuration 1:
Table 8: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 18,000
Total Flight Cy-
cles or 54,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
45 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 46

Group 5, Configuration 1:
Table 8: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
46 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 47

Group 5, Configuration 1:
Table 8: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
47 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 48

Group 5, Configuration 1:
Table 8: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
6,000 Flight Cycles
or 18,000 Flight
Hours (whichever
occurs first)
-Within 6,000
Flight Cycles or
18,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
48 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 49

Group 5, Configuration 2:
Table 9: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Within 15,000
Flight Cycles or
45,000 Flight
Hours After
Completing Ser-
vice Bulletin
767-54-0081
(whichever oc-
curs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
49 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 50

Group 5, Configuration 2:
Table 9: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to
0.4042 inches.
-AND-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
50 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 51

Group 5, Configuration 2:
Table 9: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.4042 inches
and less than or equal to
0.453 inches. -AND-
10,000 Flight Cy-
cles or 30,000
Flight Hours
(whichever occurs
first) (a) (c)
-Within 10,000
Flight Cycles or
30,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e) -OR-
-OR--OR- 15,000 Flight Cy-
cles or 45,000
Flight Hours
(whichever occurs
first) (b) (c)
Within 15,000
Flight Cycles or
45,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.453 inches
and less than or equal to
0.540 inches.
-AND-
6,000 Flight Cycles
or 18,000 Flight
Hours (whichever
occurs first)
-Within 6,000
Flight Cycles or
18,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
51 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 52

Group 5, Configuration 2:
Table 9: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
Group 6:
Table 10: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 18,000
Total Flight Cy-
cles or 54,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
52 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 53

Group 6:
Table 10: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
9,000 Flight Cycles
or 27,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 9,000
Flight Cycles or
27,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
9,000 Flight Cycles
or 27,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 9,000
Flight Cycles or
27,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
53 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 54

Group 6:
Table 10: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to 0.469
inches.
-AND-
9,000 Flight Cycles
or 27,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 9,000
Flight Cycles or
27,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.469 inches
and less than or equal to
0.477 inches. -AND-
9,000 Flight Cycles
or 27,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 9,000
Flight Cycles or
27,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
12,000 Flight Cy-
cles or 36,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 12,000
Flight Cycles or
36,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
54 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 55

Group 6:
Table 10: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.477 inches
and less than or equal to
0.540 inches.
-AND-
6,000 Flight Cycles
or 18,000 Flight
Hours (whichever
occurs first)
-Within 6,000
Flight Cycles or
18,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
55 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 56

Group 7:
Table 11: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 18,000
Total Flight Cy-
cles or 54,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
56 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 57

Group 7:
Table 11: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions. (f)
Condition 2A: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
less than or equal to 0.469
inches.
-AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
57 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 58

Group 7:
Table 11: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Do Part 4 - Fastener In-
stallation as given in
Paragraph 3.B., Work In-
structions and replace
adjacent fasteners as
given in APPENDIX A. (f)
Condition 2B: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.469 inches
and less than or equal to
0.477 inches. -AND-
8,000 Flight Cycles
or 24,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 8,000
Flight Cycles or
24,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
11,000 Flight Cy-
cles or 33,000
Flight Hours
(whichever occurs
first) (b) (c)
-OR-
Within 11,000
Flight Cycles or
33,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Do Part 3 - Freeze Plug
Repair as given in Para-
graph 3.B., Work Instruc-
tions and Do Part 4 -
Fastener Installation as
given in Paragraph 3.B.,
Work Instructions and re-
place adjacent fasteners
as given in APPENDIX A.
(f)
Condition 2C: Any crack
found in one or more of the
affected fastener locations
that can be removed with
a repaired hole diameter
greater than 0.477 inches
and less than or equal to
0.540 inches.
-AND-
6,000 Flight Cycles
or 18,000 Flight
Hours (whichever
occurs first)
-Within 6,000
Flight Cycles or
18,000 Flight
Hours (whichev-
er occurs first)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
58 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 59

Group 7:
Table 11: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
--Before further
flight.
Contact Boeing for addi-
tional instructions and do
the repair.
Condition 2D: Any crack
found in one or more of the
affected fastener hole loca-
tions that can not be re-
moved with a repaired hole
diameter of less than or
equal to 0.540 inches.
(a) If Part 1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections was previously done.
(b) If Part 2 - Open Hole HFEC Inspection was previously done.
(c) If freeze plug repairs are installed at one or more of the affected fastener locations, refer to Condition 2C
for Compliance and Repeat Interval times.
(d) If a freeze plug is installed in any one of the wing skin holes common to the pitch load fitting, only Part
1 - Upper Wing Skin Surface Detailed and Ultrasonic Inspections can be accomplished for that side of
the airplane.
(e) Action is on a per wing basis.
(f) Action is on a per hole basis.
Group 8, Configuration 1:
Table 12: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
-Within 2,000
Flight Cycles or
6,000 Flight
Hours After the
Original Issue
Date of this Ser-
vice Bulletin
(whichever oc-
curs first).
Before 12,000
Total Flight Cy-
cles or 36,000
Total Flight
Hours (whichev-
er occurs first).
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
All Airplanes
NOTE: The following conditions, times and intervals are on a per wing basis.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
59 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

### Page 60

Group 8, Configuration 1:
Table 12: Upper Wing Skin at the Front Spar Pitch Load Fitting Attachment Inspection
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
Action (d)Condition
6,000 Flight Cycles
or 18,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 6,000
Flight Cycles or
18,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
Condition 1 for airplanes
on which Part 1 Inspections
were done: No crack(s)
found at any hole location.
-OR-
9,000 Flight Cycles
or 27,000 Flight
Hours (whichever
occurs first) (b) (c)
-OR-
Within 9,000
Flight Cycles or
27,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Oversize the hole as giv-
en in Paragraph
3.B.4.a.(1) and install a
new fastener as given in
Paragraph 3.B.4.a.(2) .
Condition 1 for airplanes
on which Part 2 Inspection
was done: No crack(s)
found at any hole location.
-AND-
6,000 Flight Cycles
or 18,000 Flight
Hours (whichever
occurs first) (a) (c)
-Within 6,000
Flight Cycles or
18,000 Flight
Hours (whichev-
er occurs first)
(a) (c)
Do Part 1 - Upper Wing
Skin Surface Detailed
and Ultrasonic Inspec-
tions as given in Para-
graph 3.B., Work Instruc-
tions. (e)
-OR-
9,000 Flight Cycles
or 27,000 Flight
Hours (whichever
occurs first) (b) (c)
-OR-
Within 9,000
Flight Cycles or
27,000 Flight
Hours (whichev-
er occurs first)
(b) (c)
-OR-
Do Part 2 - Open Hole
HFEC Inspection as giv-
en in Paragraph 3.B.,
Work Instructions. (e)
--Before further
flight.
Remove the crack as giv-
en in Paragraph
3.B.4.b.(2) and do the
actions given in Condi-
tions 2A, 2B, 2C or 2D
based on repaired hole
diameter. (f)
Condition 2: Any crack
found
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: October 01, 2009
767-57A0117Revision 1: March 02, 2011
60 of 113
BOEING SERVICE BULLETIN 767-57A0117
ALERTALERT

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