# Boeing Alert Service Bulletin 767-57A0126: U.S. DOT/FAA - Boeing Service Bulletin 767-57A0126

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- Document: [Boeing Alert Service Bulletin 767-57A0126](https://openairdocs.org/service-documents/boeing/767-57a0126.md)
- Title as filed: U.S. DOT/FAA - Boeing Service Bulletin 767-57A0126
- Pages: 115
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## Text

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### Page 1

Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-57A0126
Original Issue: August 12, 2011
ATA System: 5710 5350
SUBJECT: Wing - Center Wing - Lower Underwing Longeron Fitting at FWD Intersection of
Fuselage and Wing Skin - Inspection and Replacement
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2011 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Unpublished Work - All Rights Reserved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
Summary ...................................................... 5
1. PLANNING INFORMATION ........................................ 9
A. Effectivity ................................................ 9
1. Airplanes ............................................. 9
2. Spares Affected ........................................ 1 6
B. Concurrent Requirements ...................................... 1 6
C. Reason ................................................ 1 6
D. Description .............................................. 1 6
E. Compliance .............................................. 1 7
F. Approval ............................................... 2 0
G. Manpower .............................................. 2 0
H. Weight and Balance Changes .................................... 2 5
I. Electrical Load Data ......................................... 2 5
J. References .............................................. 2 5
1. Existing Data .......................................... 2 5
2. Data supplied with this Service Bulletin ............................ 2 5
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 2 5
K. Publications Affected ........................................ 2 6
L. Interchangeability and Intermixability of Parts ........................... 2 6
2. MATERIAL INFORMATION ........................................ 2 7
A. Material - Price and Availability ................................... 2 7
B. Industry Support Information .................................... 2 7
C. Parts Necessary For Each Airplane ................................. 2 8
1. Kits/Parts ............................................ 2 8
2. Parts and Materials Supplied by the Operator ........................ 3 2
3. Parts Modified and Reidentified ................................ 3 3
4. Parts Removed and Not Replaced .............................. 3 3
D. Parts Necessary to Change Spares ................................. 3 3
E. Special Tooling - Price and Availability ............................... 3 3
F. Special Tooling Necessary to do this Service Bulletin ....................... 3 3
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 5
A. GENERAL INFORMATION ..................................... 3 5
B. WORK INSTRUCTIONS ....................................... 3 6
FIGURE 1: UNDERWING LONGERON FITTING INSPECTION, LH ................... 4 2
FIGURE 2: UNDERWING LONGERON FITTING INSPECTION, RH .................. 4 5
FIGURE 3: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH [Group 1, 3-4]
.................................................. 4 8
FIGURE 4: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH [Group 1, 3-4]
.................................................. 5 4
FIGURE 5: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH [Group 2] . 60
FIGURE 6: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH [Group 2] . 66
FIGURE 7: TENSION BOLT, INTERNAL BATHTUB FITTING AND UNDERWING LONGERON FITTING
INSTALL - LH [Group 1, 3-4] .................................. 7 2
FIGURE 8: TENSION BOLT, INTERNAL BATHTUB FITTING AND UNDERWING LONGERON FITTING
INSTALL, RH [Group 1, 3-4] .................................. 8 0
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FIGURE 9: TENSION BOLT, INTERNAL BATHTUB FITTING AND UNDERWING LONGERON FITTING
INSTALL, LH [Group 2] .................................... 8 8
FIGURE 10: TENSION BOLT, INTERNAL BATHTUB FITTING AND UNDERWING LONGERON FITTING
INSTALL, RH [Group 2] .................................... 9 6
FIGURE 11: SEAL RETAINER REMOVAL, LH [Group 1-2; Group 4, Configuration 1] ......... 1 0 4
FIGURE 12: SEAL RETAINER REMOVAL, RH [Group 1-2; Group 4, Configuration 1] ......... 1 0 6
FIGURE 13: SEAL RETAINER INSTALL, LH [Group 1-2; Group 4, Configuration 1] .......... 1 0 8
FIGURE 14: SEAL RETAINER INSTALL, RH [Group 1-2; Group 4, Configuration 1] .......... 1 1 1
APPENDIX A: ................................................. 1 1 4
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Commercial 
Airplanes
767
Service Bulletin
ALERT
SummaryNumber: 767-57A0126Original Issue: August 12, 2011
ATA System: 5710 5350
SUBJECT: Wing - Center Wing - Lower Underwing Longeron Fitting at FWD Intersection of
Fuselage and Wing Skin - Inspection and Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
CONCURRENT REQUIREMENTS
None.
BACKGROUND
The underwing longeron fittings must be inspected by High Frequency Eddy Current (HFEC) inspection to detect
cracks in each underwing longeron fitting. If any crack is found in an underwing longeron fitting, that fitting must
be replaced, and the tension bolt hole and the front spar lower chord adjacent to the underwing longeron fitting
must be inspected for cracks. Further repair may be required. The underwing longeron fittings must be inspected
periodically for cracks over the service life of the airplane. If you do not do this service bulletin, then cracks in
the underwing longeron fitting could go undetected, potentially leading to a loss of the primary load path between
the fuselage and the wing box. The loss of the primary load path could result in catastrophic damage to the wing
box.
An operator reported finding cracks in the left and right wing center section underwing longeron fittings. The
cracks found were in the same location on both fittings and appeared to run through the entire thickness of the
forward edge of the fitting at the radius corner of the vertical/horizontal flange. The lengths of cracks were
approximately 0.300 to 0.375 inches long. The airplane had accumulated 37,000 flight-cycles.
Similar cracks were found on a fatigue test airplane at these locations. Boeing estimates that it would take 25,000
cycles for the cracks to grow from 0.375 inches to 1.8 inches.
Another operator reported finding a crack in the left wing center section underwing longeron fitting during normal
maintenance. The length of crack was approximately one inch long and started from the radius of the fitting
flange. The airplane had accumulated 16,655 flight-cycles.
If you do this service bulletin you will prevent a possible loss of a primary load path due to the subject mode of
crack development.
Boeing Service Related Problem (SRP) 767-SRP-57-0240 is related to this service bulletin.
BOEING PROPRIETARY -
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This area is the subject of Maintenance Planning Document (MPD) 767 MPD 8 53-622-00 and 767 MPD 8
53-632-00.
ACTION
Part 1 - UNDERWING LONGERON FITTING INSPECTION
– Do a HFEC inspection of the underwing longeron fitting for any crack.
– If no crack is detected, repeat Part 1 within the compliance time in accordance with Paragraph 1.E.,
Compliance.
– If any crack is detected, do Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION
AND UNDERWING LONGERON FITTING REPLACEMENT.
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING LONGERON
FITTING REPLACEMENT.
– Do a HFEC inspection of the tension bolt hole and the front spar lower chord for any crack.
– If no crack is detected in the tension bolt hole or in the front spar lower chord, install the new underwing
longeron fitting.
– If any crack is detected in the tension bolt hole or in the front spar lower chord, contact The Boeing Company
for repair instructions and do the repair.
– Repeat Part 1 UNDERWING LONGERON FITTING INSPECTION within the compliance time in accordance
with Paragraph 1.E., Compliance.
EFFECTIVITY
All 767-200/ -300/ -300F/ -400ER airplanes. Refer to Paragraph 1.A., Effectivity.
COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service
bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin
mandatory.
Refer to Paragraph 1.E., Compliance.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the inspection,and/or repair procedures given in this service
bulletin.
MANPOWER
Refer to Paragraph 1.G., Manpower.
MATERIAL INFORMATION
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
JACK PAD
(193EL-LEF I SIDE)
(194ER-RIGHT SIDE)  (193KL-LEFT SIDE)
(194KR-RIGHT SIDE)
STA
783.04  BODY
UPPER DRAG  SKIN  FRONT SPAR
SPLICE ANGLE
LOWER DRAG  оббо  UNDERWING
SPLICE ANGLE  LONGERON
FORWARD FASTENERS
(3 LOCATIONS) LEFT SIDE
(3 LOCATIONS) RIGHT SIDE
PART 1:
DO A HFEC INSPECTION OF
THE UNDERWING LONGERON
FITTING FOR ANY CRACK
PART 2:  DO A HFEC INSPECTION OF  FWD
THE TENSION BOLT HOLE AND  UNDERWING LONGERON
THE FRONT SPAR LOWER  (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE)
CHORD FOR ANY CRACK, AND  2029426
REPLACE THE UNDERWING
LONGERON FITTING
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Commercial 
Airplanes
767
Service Bulletin
ALERT
Number: 767-57A0126
Original Issue: August 12, 2011
ATA System: 5710 5350
SUBJECT: Wing - Center Wing - Lower Underwing Longeron Fitting at FWD Intersection of
Fuselage and Wing Skin - Inspection and Replacement
THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH
1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO
THE NEW OWNER.
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
This service bulletin is for the airplane(s) 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 1020. At least one airplane after line number
1020 is also affected by this service bulletin, and these airplanes are in Group(s) 1,2.
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
All 767-200/-300/-300F airplanes with production seal retainer.-1
All 767-400ER airplanes with production seal retainer.-2
All 767-200/-300/-300F airplanes without production seal retainer.-3
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DESCRIPTIONCONFIGURATIONGROUP
All 767-200/-300 airplanes with post-production seal retainer: service
bulletin 767-57-0026.
-4
All 767-200/-300 airplanes: incorporated service bulletin 767-57-0026.1
All 767-200/-300 airplanes: did not incorporate service bulletin
767-57-0026.
2
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
3VA001 - VA020
3VA301 - VA315
3VA501 - VA530
3VA701 - VA719
3VA801 - VA810
3VB001 - VB002
3VB051 - VB055
3VB101 - VB125
3VB201 - VB202
3VB251 - VB253
3VB281 - VB284
3VB301 - VB302
3VB321 - VB332
3VB371 - VB373
3VB401
3VB441 - VB444
3VE001 - VE003
3VE021 - VE023
3VE041 - VE043
3VE061 - VE069
3VE083 - VE086
3VE101 - VE104
3VE116 - VE118
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GroupVariable Number
3VE121 - VE126
3VE141 - VE152
3VE171 - VE172
4VF001 - VF002
4VF041
1VF042
1VF051
1VF061 - VF062
1VF071 - VF072
1VF091 - VF093
1VF101 - VF102
1VF161 - VF162
1VF171 - VF172
1VF180 - VF184
1VF251
3VK001 - VK008
1VK009 - VK016
3VK021 - VK022
3VK031 - VK045
1VK046 - VK056
3VK081 - VK091
1VK092 - VK113
1VK131 - VK133
1VK141 - VK148
1VK161 - VK164
1VK171
1VK181
1VK186
4VL001 - VL003
1VL004 - VL006
4VL011
1VL701 - VL703
1VL751 - VL755
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GroupVariable Number
1VL806 - VL807
1VL871 - VL873
1VL891 - VL900
1VL911 - VL914
1VL931 - VL932
1VL941
4VN001 - VN015
1VN016 - VN041
4VN051 - VN058
1VN059 - VN064
4VN081 - VN084
1VN085 - VN099
1VN111 - VN127
1VN130 - VN137
4VN151
1VN152 - VN158
1VN163 - VN168
4VN171 - VN172
1VN173 - VN174
1VN191 - VN198
1VN211 - VN212
1VN221 - VN225
1VN231 - VN234
1VN241 - VN243
1VN251 - VN276
1VN291 - VN293
1VN301 - VN314
1VN371 - VN372
1VN376
1VN381 - VN388
1VN421 - VN427
1VN436
1VN471 - VN472
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GroupVariable Number
1VN491 - VN513
1VN531 - VN532
1VN536 - VN537
1VN541 - VN542
1VN546 - VN547
1VN551
1VN556 - VN557
1VN561 - VN562
1VN631 - VN638
1VN651 - VN658
1VN671 - VN672
1VN676
1VN681 - VN691
1VN731 - VN732
1VN751 - VN753
1VN791 - VN792
1VN811 - VN813
1VN921 - VN922
1VN931 - VN936
1VN951 - VN953
1VN966 - VN972
2VQ001 - VQ021
2VQ071 - VQ086
2VQ111
1VR051 - VR060
1VR081
1VR084
1VR086 - VR089
1VR106 - VR109
1VR201 - VR211
1VR251
1VR256 - VR260
1VR266 - VR278
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GroupVariable Number
1VR401
1VR421 - VR423
1VR426
1VR441
1VR461
1VR471 - VR472
1VS051 - VS056
1VS061
1VS066 - VS070
1VS073 - VS078
1VS091 - VS104
1VS111 - VS113
1VS131 - VS133
1VS136 - VS137
1VS176 - VS177
1VS186 - VS187
1VS196 - VS203
1VS206 - VS208
1VS211
1VS216 - VS217
1VS231
1VS246 - VS248
1VS261 - VS263
1VS266 - VS274
1VS291 - VS293
1VS301 - VS303
1VS306 - VS311
1VS316
1VS321 - VS324
1VS331 - VS333
1VS336 - VS337
1VS366 - VS367
1VS381 - VS382
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GroupVariable Number
1VS391 - VS392
1VS401
1VS426 - VS428
1VS466 - VS472
1VS486
1VS496 - VS497
1VS506 - VS507
1VS526
1VS546 - VS549
1VS701 - VS736
1VS751 - VS759
1VS821 - VS825
1VS841 - VS844
1VS861
1VS881 - VS883
1VS891
1VS896
1VS901 - VS912
1VS916
1VS921 - VS927
1VS931 - VS933
1VS941
1VS951 - VS954
1VS961 - VS967
1VS971 - VS973
1VS976
1VT501
1VT511 - VT513
1VT521 - VT523
1VT531 - VT533
1VT541 - VT543
1VV001
1VW701 - VW721
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GroupVariable Number
1VW851
2. Spares Affected
None.
B. Concurrent Requirements
None.
C. Reason
The underwing longeron fittings must be inspected by High Frequency Eddy Current (HFEC) inspection
to detect cracks in each underwing longeron fitting. If any crack is found in an underwing longeron
fitting, that fitting must be replaced, and the tension bolt hole and the front spar lower chord adjacent
to the underwing longeron fitting must be inspected for cracks. Further repair may be required. The
underwing longeron fittings must be inspected periodically for cracks over the service life of the airplane.
If you do not do this service bulletin, then cracks in the underwing longeron fitting could go undetected,
potentially leading to a loss of the primary load path between the fuselage and the wing box. The loss
of the primary load path could result in catastrophic damage to the wing box.
An operator reported finding cracks in the left and right wing center section underwing longeron fittings.
The cracks found were in the same location on both fittings and appeared to run through the entire
thickness of the forward edge of the fitting at the radius corner of the vertical/horizontal flange. The
lengths of cracks were approximately 0.300 to 0.375 inches long. The airplane had accumulated 37,000
flight-cycles.
Similar cracks were found on a fatigue test airplane at these locations. Boeing estimates that it would
take 25,000 cycles for the cracks to grow from 0.375 inches to 1.8 inches.
Another operator reported finding a crack in the left wing center section underwing longeron fitting
during normal maintenance. The length of crack was approximately one inch long and started from the
radius of the fitting flange. The airplane had accumulated 16,655 flight-cycles.
If you do this service bulletin you will prevent a possible loss of a primary load path due to the subject
mode of crack development.
Boeing Service Related Problem (SRP) 767-SRP-57-0240 is related to this service bulletin.
This area is the subject of Maintenance Planning Document (MPD) 767 MPD 8 53-622-00 and 767
MPD 8 53-632-00.
D. Description
Part 1 - UNDERWING LONGERON FITTING INSPECTION
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– Do a HFEC inspection of the underwing longeron fitting for any crack.
– If no crack is detected, repeat Part 1 within the compliance time in accordance with Paragraph
1.E., Compliance.
– If any crack is detected, do Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD
INSPECTION AND UNDERWING LONGERON FITTING REPLACEMENT.
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT
– Do a HFEC inspection of the tension bolt hole and the front spar lower chord for any crack.
– If no crack is detected in the tension bolt hole or in the front spar lower chord, install the new
underwing longeron fitting.
– If any crack is found in the tension bolt hole or in the front spar lower chord, contact The Boeing
Company for repair instructions and do the repair.
– Repeat Part 1 UNDERWING LONGERON FITTING INSPECTION within the compliance time in
accordance with Paragraph 1.E., Compliance.
The work in this service bulletin is done in the maintenance zone(s) given below.
Group 1:
Affected Maintenance Zones
ZoneModel
193, 194767-200, 767-300, 767-300F
Group 2:
Affected Maintenance Zones
ZoneModel
193, 194767-400ER
Group 3-4:
Affected Maintenance Zones
ZoneModel
193, 194767-200, 767-300
E. Compliance
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this
service bulletin mandatory.
Accomplish Part 1 and Part 2 as required in Table 1- LOWER UNDERWING LONGERON FITTING
INSPECTION AND REPLACEMENT in accordance with Paragraph 3. Accomplishment Instructions.
Evaluate the conditions and actions for each underwing longeron fitting separately.
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TABLE 1 - LOWER UNDERWING LONGERON FITTING INSPECTION AND REPLACEMENT.
Repeat Interval (Not
to Exceed)
Compliance Time (Whichever occurs
Later)
ActionCondition
-Within 6,000 flight-
cycles or 14,000
flight-hours,
whichever occurs
first, after the original
issue date of this
service bulletin.
Before 16,000 total
flight-cycles or
35,000 total flight-
hours, whichever oc-
curs first.
Do a High Frequency
Eddy Current
(HFEC) inspection of
the underwing
longeron fitting for
any crack in accor-
dance with Part 1 -
UNDERWING
LONGERON FIT-
TING INSPECTION.
Airplanes that have
less than 35,000 total
flight-cycles and less
than 70,000 total
flight-hours as of the
original issue date of
this service bulletin.
-Within 3,000 flight-
cycles or 7,000 flight-
hours, whichever oc-
curs first, after the
original issue date of
this service bulletin.
-Do a HFEC inspec-
tion of the underwing
longeron fitting for
any crack in accor-
dance with Part 1 -
UNDERWING
LONGERON FIT-
TING INSPECTION.
Airplanes that have
35,000 or more total
flight-cycles, or
70,000 or more total
flight-hours as of the
original issue date of
this service bulletin.
12,000 flight-cycles
or 28,000 flight-
hours, whichever oc-
curs first.
--Repeat the HFEC in-
spection of the under-
wing longeron fitting
for any crack in accor-
dance with Part 1 -
UNDERWING
LONGERON FIT-
TING INSPECTION.
Condition 1:
No crack found.
--Before further flight.Do a HFEC inspec-
tion of the tension
bolt hole and the
front spar lower
chord for any crack
in accordance with
Part 2 - TENSION
BOLT HOLE,
FRONT SPAR LOW-
ER CHORD INSPEC-
TION AND UNDER-
WING LONGERON
FITTING REPLACE-
MENT.
Condition 2:
Any crack found.
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TABLE 1 - LOWER UNDERWING LONGERON FITTING INSPECTION AND REPLACEMENT.
Repeat Interval (Not
to Exceed)
Compliance Time (Whichever occurs
Later)
ActionCondition
--Before further flight.Replace the under-
wing longeron fitting
in accordance with
Part 2 - TENSION
BOLT HOLE,
FRONT SPAR LOW-
ER CHORD INSPEC-
TION AND UNDER-
WING LONGERON
FITTING REPLACE-
MENT.
Condition 2A:
No crack found in the
tension bolt hole or
the front spar lower
chord.
and
(a)-Within 16,000 flight-
cycles or 35,000
flight-hours,
whichever occurs
first after the fitting is
replaced.
Do a HFEC inspec-
tion of the underwing
longeron fitting for
any crack in accor-
dance with Part 1 -
UNDERWING
LONGERON FIT-
TING INSPECTION.
See Condition 1 or
Condition 2 as appli-
cable.
--Before further flight.Contact The Boeing
Company for repair
instructions and do
the repair.
Condition 2B:
Any crack found in
the tension bolt hole
or the front spar low-
er chord. and
(a)-Within 16,000 flight-
cycles or 35,000
flight-hours,
whichever occurs
first after the repair is
accomplished and
the fitting is replaced.
Do a HFEC inspec-
tion of the underwing
longeron fitting for
any crack in accor-
dance with Part 1 -
UNDERWING
LONGERON FIT-
TING INSPECTION.
See Condition 1 or
Condition 2 as appli-
cable.
(a) The longeron fitting replacement does not terminate the continued inspection requirements of this service
bulletin.
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F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this Inspection and replacement
for each wing. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate
with operator task hour data if necessary. The estimate does not include lost time. These are some
examples of lost time:
 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Part 1 - UNDERWING LONGERON FITTING INSPECTION
Elapsed HoursTask HoursNumber of PersonsTask
0.250.502Open access -
longeron fitting
0.800.801FIGURE 1 - UNDER-
WING LONGERON
FITTING INSPEC-
TION, LH
0.800.801FIGURE 2 - UNDER-
WING LONGERON
FITTING INSPEC-
TION, RH
0.500.502Close access -
longeron fitting
2.352.60TOTAL FOR EACH AIRPLANE
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Group 1; Group 4, Configuration 1:
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
8.0032.004Defuel airplane,
purge and fuel tank
entry
2.5012.505Jack airplane
0.250.502Open access - FWD
cargo compartment
0.250.502Open access -
longeron fitting
0.200.201FIGURE 11 SEAL
RETAINER RE-
MOVAL, LH
0.200.201FIGURE 12 SEAL
RETAINER RE-
MOVAL, RH
2.655.302FIGURE 3 - TEN-
SION BOLT HOLE
AND FRONT SPAR
LOWER CHORD IN-
SPECTION, LH
2.655.302FIGURE 4 - TEN-
SION BOLT HOLE
AND FRONT SPAR
LOWER CHORD IN-
SPECTION, RH
6.2512.502FIGURE 7 - TEN-
SION BOLT, INTER-
NAL BATHTUB FIT-
TING AND UNDER-
WING LONGERON
FITTING INSTALL,
LH
6.2512.502FIGURE 8 - TEN-
SION BOLT, INTER-
NAL BATHTUB FIT-
TING AND UNDER-
WING LONGERON
FITTING INSTALL,
RH
0.500.501FIGURE 13 - SEAL
RETAINER IN-
STALL, LH
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Group 1; Group 4, Configuration 1:
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
0.500.501FIGURE 14 - SEAL
RETAINER IN-
STALL, RH
4.008.002Close access - fuel
tank
2.5012.505De-jack airplane
0.250.502Close access - FWD
cargo compartment
0.250.502Close access -
longeron
37.10104.00TOTAL FOR EACH AIRPLANE
Group 2:
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
8.0032.004Defuel airplane,
purge and fuel tank
entry
2.5012.505Jack airplane
0.250.502Open access - FWD
cargo compartment
0.250.502Open access -
longeron fitting
0.200.201FIGURE 11 SEAL
RETAINER RE-
MOVAL, LH
0.200.201FIGURE 12 SEAL
RETAINER RE-
MOVAL, RH
2.655.302FIGURE 5 - TEN-
SION BOLT HOLE
AND FRONT SPAR
LOWER CHORD IN-
SPECTION, LH
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Group 2:
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
2.655.302FIGURE 6 - TEN-
SION BOLT HOLE
AND FRONT SPAR
LOWER CHORD IN-
SPECTION, RH
6.2512.502FIGURE 9 - TEN-
SION BOLT, INTER-
NAL BATHTUB FIT-
TING AND UNDER-
WING LONGERON
FITTING INSTALL,
LH
6.2512.502FIGURE 10 - TEN-
SION BOLT, INTER-
NAL BATHTUB FIT-
TING AND UNDER-
WING LONGERON
FITTING INSTALL,
RH
0.500.501FIGURE 13 - SEAL
RETAINER IN-
STALL, LH
0.500.501FIGURE 14 - SEAL
RETAINER IN-
STALL, RH
4.008.002Close access - fuel
tank
2.5012.505De-jack airplane
0.250.502Close access - FWD
cargo compartment
0.250.502Close access -
longeron
37.10104.00TOTAL FOR EACH AIRPLANE
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Group 3; Group 4, Configuration 2:
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT
Elapsed HoursTask HoursNumber of PersonsTask
8.0032.004Defuel airplane,
purge and fuel tank
entry
2.5012.505Jack airplane
0.250.502Open access - FWD
cargo compartment
0.250.502Open access -
longeron fitting
2.655.302FIGURE 3 - TEN-
SION BOLT HOLE
AND FRONT SPAR
LOWER CHORD IN-
SPECTION, LH
2.655.302FIGURE 4 - TEN-
SION BOLT HOLE
AND FRONT SPAR
LOWER CHORD IN-
SPECTION, RH
6.2512.502FIGURE 7 - TEN-
SION BOLT, INTER-
NAL BATHTUB FIT-
TING AND UNDER-
WING LONGERON
FITTING INSTALL,
LH
6.2512.502FIGURE 8 - TEN-
SION BOLT, INTER-
NAL BATHTUB FIT-
TING AND UNDER-
WING LONGERON
FITTING INSTALL,
RH
4.008.002Close access - fuel
tank
2.5012.505De-jack airplane
0.250.502Close access - FWD
cargo compartment
0.250.502Close access -
longeron
35.70102.60TOTAL FOR EACH AIRPLANE
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H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+284.0+0.4767-200/-300/-
300F/-400ER
I. Electrical Load Data
Not changed.
J. References
1. Existing Data
a. Service Related Problem (SRP) 767-SRP-57-0240
b. Standard Overhaul Practices Manual (SOPM) 20-30-03
c. 767 Aircraft Maintenance Manual (AMM) 07-11-01, 07-11-03, 25-52-03, 28-11-00, 28-26-00,
53-52-01
d. 767 Maintenance Planning Data (MPD) 853-622-00, 853-632-00
e. 767 Non-Destructive Testing (NDT) Manual Part 6, 51-00-01, Part 6, 51-00-04, Part 6, 51-00-11,
Part 6, 51-00-16, Part 6, 51-00-19
f. 767-400 Aircraft Maintenance Manual (AMM) 07-11-01, 07-11-03, 25-52-03, 28-11-00,
28-26-00, 53-52-01
g. Boeing Parts Standards Document D-590
h. Boeing Drawing 767 012W6100
i. Structural Repair Manual (SRM) 767-200 SRM 51-40-09, or 767-200SF SRM 51-40-09, or
767-300 SRM 51-40-09, or 767-300BCF SRM51-40-09, or 767-300F SRM 51-40-09, or
767-400 SRM 51-40-09
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
TitleDrawing Number
LONGERON INSTL-AFT UNDER WING111T4022
MONOCOQUE INTEGRATION SECTION 43 TO 45140T0120
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These drawings were used to prepare this service bulletin. These drawings are not necessary to
make the specified changes, and are not supplied with this service bulletin. These drawings may
not be applicable to all airplane configurations or operators.
K. Publications Affected
1. Publications:
None.
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected
are contained in Paragraph 1.E., Compliance of this service bulletin.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary for Each Airplane. Operators
are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin.
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
Prices are in United States Dollars. Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of these methods:
1. Order on-line via ATA Spec 2000 or The Boeing PART Page
2. Fax to (206) 662-7145
Group 1, 3-4:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original date
of this Service
Bulletin (US Dol-
lars)
ROLT as of the
original date of
this Service Bul-
letin (Calendar
Days)
NameKit Number
$1,623.00515TOP KIT - UNDERWING LONGERON -
REPLACEMENT
015T1859-1
$4,406.00149FITTING, UNDERWING LONGERON, LH111T4020U7
$4,406.00149FITTING, UNDERWING LONGERON, RH111T4020U8
Group 2:
REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER
AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION
Unit Price as of
the original date
of this Service
Bulletin (US Dol-
lars)
ROLT as of the
original date of
this Service Bul-
letin (Calendar
Days)
NameKit Number
$2,739.00515TOP KIT - UNDERWING LONGERON -
REPLACEMENT
015T1859-2
$4,406.00149FITTING, UNDERWING LONGERON, LH111T4020U9
$4,406.00149FITTING, UNDERWING LONGERON, RH111T4020U10
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes inspection, and/or repair
procedures given in this service bulletin.
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C. Parts Necessary For Each Airplane
1. Kits/Parts
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each wing.
Kit 015T1859
NotesExisting Part
Number
NameQTYNew Part Number
-2-1
Top Kit - Under-
wing Longeron -
Replacement
.-015T1859-1
Top Kit - Under-
wing Longeron -
Replacement
-.015T1859-2
(a)(b)BOLT33BACB30MR10A26X
(a)(b)BOLT, PROTRUD-
ING HD
.2BACB30NX10K12X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX10K12Y
(a)(b)BOLT, PROTRUD-
ING HD
.2BACB30NX10K13X
(a)(b)BOLT, PROTRUD-
ING HD
.2BACB30NX10K14X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX10K14Y
(a)(b)BOLT, PROTRUD-
ING HD
.2BACB30NX10K17X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX10K17Y
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX10K18X
(a)(b)BOLT, PROTRUD-
ING HD
11BACB30NX10K19X
(a)(b)BOLT, PROTRUD-
ING HD
11BACB30NX10K20X
(a)(b)BOLT, PROTRUD-
ING HD
11BACB30NX10K20Y
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX10K21X
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Kit 015T1859
NotesExisting Part
Number
NameQTYNew Part Number
-2-1
(a)(b)BOLT, PROTRUD-
ING HD
11BACB30NX10K21Y
(a)(b)BOLT, PROTRUD-
ING HD
.4BACB30NX10K9X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX10K9Y
(a)(b)BOLT, PROTRUD-
ING HD
2.BACB30NX12K10X
(a)(b)BOLT, PROTRUD-
ING HD
1.BACB30NX12K10Y
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX12K14X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX12K14Y
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX12K17X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX12K19X
(a)(b)BOLT, HEX-DRIVE.1BACB30NX12K19Y
(a)(b)BOLT, HEX DRIVE2.BACB30NX12K9X
(a)(b)BOLT, PROTRUD-
ING HD
1.BACB30NX14K14X
(a)(b)BOLT TITANIUM
O/S
1.BACB30NX14K15X
(a)(b)BOLT, HEX DRIVE1.BACB30NX14K15Y
(a)(b)BOLT, PROTRUD-
ING HD
1.BACB30NX14K18X
(a)(b)BOLT, PROTRUD-
ING HD
21BACB30NX14K19X
(a)(b)BOLT, HEX-DRIVE11BACB30NX14K19Y
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX14K22X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX14K22Y
(a)(b)BOLT, PROTRUD-
ING HD
22BACB30NX8K10X
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Kit 015T1859
NotesExisting Part
Number
NameQTYNew Part Number
-2-1
(a)(b)BOLT, PROTRUD-
ING HD
11BACB30NX8K10Y
(a)(b)BOLT, PROTRUD-
ING HD
44BACB30NX8K12X
(a)(b)BOLT, PROTRUD-
ING HD
11BACB30NX8K12Y
(a)(b)BOLT, PROTRUD-
ING HD
.2BACB30NX8K14X
(a)(b)BOLT, PROTRUD-
ING HD
.1BACB30NX8K14Y
(a)(b)BOLT, PROTRUD-
ING HD
.2BACB30NX8K16X
(a)(b)BOLT, PROTRUD-
ING HD
2220BACB30NX8K8X
(a)(b)BOLT, PROTRUD-
ING HD
22BACB30NX8K8Y
(a)(b)BOLT, PROTRUD-
ING HD
24BACB30NX8K9X
(a)(b)BOLT1.BACB30US10K39X
(a)(b)BOLT, 12 PT
HEAD
11BACB30US5K25X
(a)(b)BOLT, 12 PT
HEAD
11BACB30US5K27X
(BACB30US5K28X
optional)
(a)(b)BOLT, 12 PT
HEAD
.1BACB30US9K35X
(a)(b)BOLT, HEX DRIVE1.BACB30YK12K14X
(a)(b)BOLT1.BACB30YK12K14Y
(a)(b)BOLT, HEX DRIVE1.BACB30YK12K18X
(a)(b)BOLT, HEX DRIVE1.BACB30YK12K20X
(a)(b)BOLT1.BACB30YK12K20Y
(a)COLLAR16BACC30AC10
(a)COLLAR12BACC30AC12
(a)COLLAR22BACC30AC14
(a)COLLAR55BACC30AC8
(a)COLLAR216BACC30BH10
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Kit 015T1859
NotesExisting Part
Number
NameQTYNew Part Number
-2-1
(a)COLLAR43BACC30BH12
(a)COLLAR,
PRELOAD
52BACC30BH14
(a)COLLAR3034BACC30BH8
(a)COLLAR,
PRELOAD
3.BACC30CP12C
(a)COLLAR,
PRELOAD
2.BACC30CP12CY
(a)NUT1.BACN10HR10CD
(a)NUT22BACN10HR5CD
(a)NUT.1BACN10HR9CD
(a)NUT33BACN11Z10CD
SHIM - LAMINAT-
ED
11BACS40R014C022F
SHIM, LAMINAT-
ED
.1BACS40R016B018F
SHIM, LAMINAT-
ED
1.BACS40R018B022F
SHIM ,LAMINAT-
ED
.1BACS40R020C032F
SHIM - LAMINAT-
ED
1.BACS40R021C037F
SHIM, LAMINAT-
ED
22BACS40R025C063F
(a)WASHER, PLAIN33BACW10BP101CD
(a)WASHER, PLAIN79BACW10BP101DP
(a)WASHER, PLAIN16BACW10BP102DP
(a)WASHER, PLAIN32BACW10BP121DP
(a)WASHER, PLAIN32BACW10BP122DP
(a)WASHER, PLAIN22BACW10BP141DP
(a)WASHER, PLAIN22BACW10BP142DP
(a)WASHER, PLAIN22BACW10BP51CD
(a)WASHER, PLAIN66BACW10BP51DP
(a)WASHER, PLAIN45BACW10BP81DP
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Kit 015T1859
NotesExisting Part
Number
NameQTYNew Part Number
-2-1
(a)WASHER, PLAIN45BACW10BP82DP
(a)WASHER, PLAIN.1BACW10BP91C
(a)WASHER, PLAIN.2BACW10BP91DP
(a)WASHER, SELF-
ALIGN
1.BACW10CA101CVS
(a)WASHER, SELF-
ALIGN
.1BACW10CA10CCS
(a)WASHER, SELF-
ALIGN
1.BACW10CA12CCS
(a)WASHER, SELF-
ALIGN
.1BACW10CA91CVS
(a) There are more parts than are necessary
(b) If grip length shown is not available at Boeing, fasteners supplied in the kits
may be one grip length longer than indicated. Also, if any fasteners part numbers
listed are not available or have been superseded, substitute fasteners may be
supplied in the kits. Boeing Document D-590 and Boeing Drawing 012W6100
are used to determine the part numbers used as substitutes.
2. Parts and Materials Supplied by the Operator
To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by
the Operator, are necessary for each wing.
Group 1, 3-4:
NotesExisting Part NumberNameQTYPart Number /
Specification
(a)PRESSURE AND ENVIRONMEN-
TAL SEALANT-CHROMATE TYPE
70 Oz.BMS5-95
(a)FUEL TANK SEALANT30 Oz.BMS5-45 (BMS5-
26 optional)
FITTING, UNDERWING
LONGERON, LH
1111T4020U7
FITTING, UNDERWING
LONGERON, RH
1111T4020U8
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
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### Page 33

Group 2:
NotesExisting Part NumberNameQTYPart Number /
Specification
(a)PRESSURE AND ENVIRONMEN-
TAL SEALANT-CHROMATE TYPE
70 Oz.BMS5-95
(a)FUEL TANK SEALANT30 Oz.BMS5-45 (BMS5-
26 optional)
FITTING, UNDERWING
LONGERON, LH
1111T4020U9
FITTING, UNDERWING
LONGERON, RH
1111T4020U10
(a) Refer to the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier
data.
3. Parts Modified and Reidentified
None.
4. Parts Removed and Not Replaced
None.
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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BLANK PAGE

### Page 35

3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions and the Figure(s)
give the recommended sequence of steps. The sequence of steps to do this service
bulletin can be changed.
2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
3. Obey all of the warnings and cautions given in the specified manual sections.
4. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets are in Structural Repair Manual (SRM)
Chapter 51
– Torque limits to tighten nuts and bolts are in SRM Chapter 51
5. Use the approved fastener and process material substitutions in accordance with
SRM Chapter 51. Alternate fasteners are listed in SRM Chapter 51 and Boeing
Drawing 767 012W6100.
6. If the length of any fastener specified in this service bulletin does not meet installation
standards given in SRM Chapter 51, then a fastener of the same specification, or
an approved substitute, with a length which meets the installation standards given
in SRM Chapter 51 may be used. In addition, washers may be installed for fastener
grip length in accordance with SRM Chapter 51.
7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
8. Boeing Service Letter 767-SL-51-036, Damage Reporting and Repair Plan/Design
Guidelines, is an acceptable procedure to request information from Boeing for
additional structural repair instructions. The Service Letter describes what information
must be provided to Boeing before a structural repair can be provided.
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9. The instructions in Paragraph 3.B., Work Instructions and the figures can include
operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated
Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing
Index contain data on versions of the tools or test equipment that you can use. It is
permitted to use replaced tools. It is not permitted to use superseded tools.
10. If it is necessary to remove more parts for access, you can remove those parts. If
you can get access without removing identified parts, it is not necessary to remove
all of the identified parts. Jacking and shoring limitations must be observed.
11. Where the work instructions include installation of a kept part, a new or serviceable
part with the same part number can be installed as an alternative to the kept part.
The removed part can be discarded if a new or serviceable part is installed.
12. Some Boeing parts are supplied in a temporary configuration. Those parts are
identified with a 'U', 'W', or 'Y' in place of the '-' (dash) in the part number. It is
permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '-'
(dash) part number. Boeing Drawing 005W0900 contains more data.
B. WORK INSTRUCTIONS
1. Do a High Frequency Eddy Current (HFEC) inspection of the underwing longeron fitting for any
crack in accordance with Part 1 - UNDERWING LONGERON FITTING INSPECTION within the
compliance time in Paragraph 1.E., Compliance.
a. Condition 1 - No crack is found:
(1) Repeat the HFEC inspection of the underwing longeron fitting for any crack in accordance
with Part 1 - UNDERWING LONGERON FITTING INSPECTION within the compliance
time in Paragraph 1.E., Compliance.
b. Condition 2 - Any crack found:
(1) Do a HFEC inspection of the tension bolt hole and the front spar lower chord for any
crack in accordance with Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD
INSPECTION AND UNDERWING LONGERON FITTING REPLACEMENT.
(a) Condition 2A - No crack is found in the tension bolt hole or the front spar lower chord:
1) Replace the underwing longeron fitting in accordance with Part 2 - TENSION
BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT.
2) Do a HFEC inspection of the underwing longeron fitting for any crack in
accordance with Part 1 - UNDERWING LONGERON FITTING INSPECTION
within the compliance time in Paragraph 1.E., Compliance.
(b) Condition 2B - Any crack found in the tension bolt hole or the front spar lower chord:
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1) Contact The Boeing Company for repair instructions and do the repair.
2) Do a HFEC inspection of the underwing longeron fitting for any crack in
accordance with Part 1 - UNDERWING LONGERON FITTING INSPECTION
within the compliance time in Paragraph 1.E., Compliance.
PART 1 - UNDERWING LONGERON FITTING INSPECTION
1. Remove the wing-to-body access panel to open access to the longeron fitting. Refer to 767 AMM
53-52-01 or 767-400 AMM 53-52-01 as an accepted procedure.
RightLeft
194KR193KL
2. Do a HFEC inspection of the underwing longeron fitting for any crack in accordance with the figures
below:
RightLeft
FIGURE 2FIGURE 1
3. Install the wing-to-body access panel to close access to the longeron fitting. Refer to 767 AMM
53-52-01 or 767-400 AMM 53-52-01 as an accepted procedure.
RightLeft
194KR193KL
Part 2 - TENSION BOLT HOLE, FRONT SPAR LOWER CHORD INSPECTION AND UNDERWING
LONGERON FITTING REPLACEMENT
1. Defuel the airplane. Refer to 767 AMM 28-26-00 or 767-400 AMM 28-26-00 as an accepted
procedure.
2. Do a purge and fuel tank entry to open access to the tension bolt. Refer to 767 AMM 28-11-00 or
767-400 AMM 28-11-00 as an accepted procedure.
3. Jack the airplane:
NOTE: Only one underwing longeron fitting is to be removed and replaced at a time. Each side
may need separate jacking loads.
a. Make sure the airplane is indoors for the jacking procedure.
b. Make sure the airplane is at operational empty weight (OEW) with or without engines installed.
Refer to 767 AMM 07-11-03 or 767-400 AMM 07-11-03 as an accepted procedure.
c. Deflate all gear struts. Service all gear struts with the specified hydraulic fluid. Make sure that
a minimum of one (1) inch of chrome is exposed on the gear strut cylinder. Refer to 767 AMM
12-15-01 and 767 AMM 12-15-02 or, 767-400 AMM 12-15-01 and 767-400 AMM 12-15-02
as an accepted procedure.
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NOTE: The gear strut must be filled with hydraulic fluid until there are no bubbles in the
hydraulic fluid that comes out of the air valve at the top of the gear strut. When there
are no bubbles in the Hydraulic fluid, the air valve must be closed and additional
hydraulic fluid must be pumped into the gear strut until one (1) inch of chrome is
exposed.
CAUTION: MAKE SURE NOT TO LOCATE AND JACK THE AIRPLANE ON THE AUXILIARY
NOSE JACKING POINT D.
d. Locate and level the airplane on the main gear axle jacks and nose gear axle jacks. Refer to
767 AMM 07-11-01, 767-400 AMM 07-11-01, 767 AMM 07-11-03 and 767-400 AMM 07-11-03
as accepted procedures.
e. If the airplane is at OEW with engines installed, load the airplane on the jacking points in
accordance with the table titled: Jacking Loads at OEW with Engines Installed. Refer to 767
AMM 07-11-01 or 767-400 AMM 07-11-01 as an accepted procedure.
Jacking Loads at OEW with Engines Installed
Tail Jacking Point C
Load (Pounds)
Auxiliary Wing Jacking
Points E and F Load
(Pounds)
Nose Gear Axle Jacking
Point Load (Pounds) (b)
Minor Model (a)
7,80014,50027,400767-200 Airplanes
13,60015,00030,500767-300 Airplanes
4,10015,00029,000767-300F Airplanes
14,00016,50031,800767-400ER Airplanes
(a) All loads are +/- 5 percent.
(b) Load on main gear axle jacks is not monitored.
CAUTION: AIRPLANE ENGINE STRUTS MUST BE INSTALLED ON THE AIRPLANE.
f. If the airplane is at OEW with engines removed, load the airplane on the jacking points in
accordance with the table titled: Jacking Loads at OEW Engines Removed (engine struts
installed). Refer to 767 AMM 07-11-01 or 767-400 AMM 07-11-01 as an accepted procedure.
Jacking Loads at OEW with Engines Removed (engine struts installed)
Tail Jacking Point C
Load (Pounds)
Auxiliary Wing Jacking
Points E and F Load
(Pounds)
Nose Gear Axle Jacking
Point Load (Pounds) (b)
Minor Model (a)
17,30010,50027,400767-200 Airplanes
21,60011,00030,500767-300 Airplanes
12,30011,00029,000767-300F Airplanes
20,90013,00031,800767-400ER Airplanes
(a) All loads are +/- 5 percent.
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Jacking Loads at OEW with Engines Removed (engine struts installed)
Tail Jacking Point C
Load (Pounds)
Auxiliary Wing Jacking
Points E and F Load
(Pounds)
Nose Gear Axle Jacking
Point Load (Pounds) (b)
Minor Model (a)
(b) Load on main gear axle jacks is not monitored.
g. Mechanically lock all the jacks. Refer to 767 AMM 07-11-01 or 767-400 AMM 07-11-01 as an
accepted procedure.
h. Make sure all three (3) forward fasteners common to the vertical flange of the underwing
longeron fitting are unloaded and free to rotate under minimal torque load. If not, then do the
following:
NOTE: See FIGURE 3 and FIGURE 4 for the location of the three forward fasteners common
to the vertical flange of the underwing longeron fitting.
(1) Mechanically unlock the nose gear axle jack only. Refer to 767 AMM 07-11-01 or 767-400
AMM 07-11-01 as an accepted procedure.
(2) Adjust the jacking loads by doing either actions A or B, or both actions A and B, until all
three (3) forward fasteners are unloaded and free to rotate under minimal torque load as
given in the table titled: Actions to Adjust the Airplane Jacking Loads. Refer to 767 AMM
07-11-01 or 767-400 AMM 07-11-01 as an accepted procedure.
NOTE: Only one underwing longeron fitting is to be removed and replaced at a time.
The jacking loads may require separate adjustment for the removal of each
underwing longeron fitting.
Actions to Adjust the Airplane Jacking Loads
DescriptionAction
Change the nose gear axle jack load by +/- 10 percent of the target load as given
in one of the applicable tables titled either:
A
Jacking Loads at OEW with Engines Installed
<or>
Jacking Loads at OEW with Engines Removed (engine struts installed).
Load the primary body jacking points A and B between 0 to 10,000 lbs.B
The jacking loads on jacking points A and B must always be kept within 1,000 lbs
of each other.
(3) Mechanically lock all the jacks. Refer to 767 AMM 07-11-01 or 767-400 AMM 07-11-01
as an accepted procedure.
4. Remove the insulation blanket(s) to gain access to the work area at the lower lobe inside the FWD
cargo compartment. Refer to 767 AMM 25-52-03 or 767-400 AMM 25-52-03 as an accepted
procedure.
5. Remove the wing-to-body access panel to open access to the longeron fitting. Refer to 767 AMM
53-52-01 or 767-400 AMM 53-52-01 as an accepted procedure.
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RightLeft
194KR193KL
6. Group 1-2; Group 4, Configuration 1:
Remove the retainer seal in accordance with the figures below:
RightLeft
FIGURE 12FIGURE 11
7. Remove the underwing longeron fitting, the tension bolt and the internal bathtub fitting, and do a
HFEC inspect of the tension bolt hole and the front spar lower chord for any crack in accordance
with the figures below:
Group 1, 3-4:
RightLeft
FIGURE 4FIGURE 3
Group 2:
RightLeft
FIGURE 6FIGURE 5
8. Install the underwing longeron fitting, the tension bolt and the internal bathtub fitting in accordance
with the figures below:
Group 1, 3-4:
RightLeft
FIGURE 8FIGURE 7
Group 2:
RightLeft
FIGURE 10FIGURE 9
9. Group 1-2; Group 4, Configuration 1:
Install the retainer seal in accordance with the figures below:
RightLeft
FIGURE 14FIGURE 13
10. Close access to the fuel tank. Refer to 767 AMM 28-11-00 or 767-400 AMM 28-11-00 as an
accepted procedure.
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11. De-jack the airplane. Refer to 767 AMM 07-11-01 or 767-400 AMM 07-11-01 as an accepted
procedure.
12. Install the insulation blanket(s) to close access to the work area at the lower lobe inside the FWD
cargo compartment. Refer to 767 AMM 25-52-03 or 767-400 AMM 25-52-03 as an accepted
procedure.
13. Install the wing-to-body access panel to close access to the longeron fitting. Refer to 767 AMM
53-52-01 or 767-400 AMM 53-52-01 as an accepted procedure.
RightLeft
194KR193KL
14. Return the airplane to a serviceable condition.
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### Page 42 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
JACK PAD
(193EL)  (193KL)
STA
783.04  BODY
UPPER DRAG  SKIN  FRONT SPAR
SPLICE ANGLE
UNDERWING
LONGERON
LOWER DRAG
SPLICE ANGLE
UNDERWING LONGERON
2026714
FIGURE 1: UNDERWING LONGERON FITTING INSPECTION, LH
(SHEET 1 OF 3)
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### Page 43 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
0.5→
1.0
1.5
0.8
1.0
INBD
A-A  2028198
FIGURE 1: UNDERWING LONGERON FITTING INSPECTION, LH
(SHEET 2 OF 3)
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### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a HFEC inspection for any crack in
the area indicated in accordance with
767 NDT Part 6, 51-00-01 or 767 NDT
Part 6, 51-00-19. Dimensions are mini-
mum.
1-FITTING, LOWER -
UNDERWING,
LONGERON, LH
Inspect1
FIGURE 1: UNDERWING LONGERON FITTING INSPECTION, LH
(SHEET 3 OF 3)
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### Page 45 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
JACK PAD
(194KR)  (194ER)
STA
BODY 783.04
FRONT SPAR  SKIN  UPPER DRAG
SPLICE ANGLE
UNDERWING
LONGERON
LOWER DRAG
SPLICE ANGLE
UNDERWING LONGERON
2026909
FIGURE 2: UNDERWING LONGERON FITTING INSPECTION, RH
(SHEET 1 OF 3)
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### Page 46 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
• 0.5→
†
1.0
1.5
0.8
0.8 →
1.0
INBD
A-A  2028226
FIGURE 2: UNDERWING LONGERON FITTING INSPECTION, RH
(SHEET 2 OF 3)
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### Page 47

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
Do a HFEC inspection for any crack in
the area indicated in accordance with
767 NDT Part 6, 51-00-01 or 767 NDT
Part 6, 51-00-19. Dimensions are mini-
mum.
1-FITTING, LOWER -
UNDERWING,
LONGERON, RH
Inspect1
FIGURE 2: UNDERWING LONGERON FITTING INSPECTION, RH
(SHEET 3 OF 3)
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### Page 48 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
This Figure applies only to: Group 1, 3-4.
JACK PAD
(193EL)  (193KL)
STA
783.04  BODY
UPPER DRAG  SKIN  FRONT SPAR
SPLICE ANGLE
UNDERWING
LONGERON
LOWER DRAG
SPLICE ANGLE
FORWARD FASTENERS
(3 LOCATIONS)
UNDERWING LONGERON
2028233
FIGURE 3: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH
(SHEET 1 OF 6)
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### Page 49 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
SEAL RETAINER
(REFERENCE ONLY)
6 ) SHIM "B"
FRONT
SPAR
SHIM "A" (6  6 FITTING  BATHTUB
(1X  ) SHIM "C"
STA
776.21
C
3) 45 LOCATIONS
FWD
UNDERWING LONGERON
A-A
4)RADIUS  'FILLER "A"
4 RADIUS  - LLER "B  RADIUS
SHIM "D"  'FILLER "C"
(2 LOCATIONS)
RADIUS
FILLER "D
++5
+ +
RADIUS  FILLER "E" '  RADIUS  FILLER "p" 4  / FILLER "G"  ¡ RADIUS  RADIUS 4
FILLER "H"
FWD  B-B  2028554
FIGURE 3: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH
(SHEET 2 OF 6)
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### Page 50 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
4) FILLER "I"  RADIUS  4) RADIUS  / FILLER "J"  4 RADIUS  'FILLER "K"  4) RADIUS  / FILLER "L"
RADIUS
/FILLER "P"
4 RADE  FILLER "N  FWD
RADIUS
→ FILLER I"M"
C-C
_ 1.0
FRONT SPAR WEB
INSPECTION AREA
INTERNAL BATHTUB
FITTING LOCATION
WING
LOWER
SKIN
2028574
FIGURE 3: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH
(SHEET 3 OF 6)
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### Page 51

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-NUTRemove /
Keep
1
CONCAVE1-WASHER, SELF-
ALIGN
Remove /
Keep
CONVEX1-WASHER SELF-ALIGNRemove /
Keep
1-WASHERRemove /
Keep
TENSION BOLT1-BOLT, 12 PT HEADRemove /
Keep
Refer to SOPM 20-30-03 as an accepted
procedure as required.
1-HOLEClean2
Do a HFEC inspection for any crack on
the entire joint thickness, including the
fuselage ring doubler, fuselage bathtub
fitting and wing bathtub fitting in accor-
dance with 767 NDT Part 6, 51-00-04,
or 767 NDT Part 6, 51-00-11, or 767
NDT Part 6, 51-00-16.
1-HOLEInspect
45-FASTENERSRemove3
FIGURE 3: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH
(SHEET 4 OF 6)
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### Page 52

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER ARemove /
Keep
4
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER BRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER CRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER DRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER ERemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER FRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER GRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER HRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER IRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER JRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER KRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER LRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER MRemove /
Keep
1-RADIUS FILLER NRemove /
Keep
FIGURE 3: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH
(SHEET 5 OF 6)
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### Page 53

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER ORemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER PRemove /
Keep
1-FITTING, UNDER-
WING LONGERON, LH
Remove5
1-FITTING, INTERNAL
BATHTUB
Remove /
Keep
6
SHIM A1-SHIM, LAMINATEDRemove
SHIM B1-SHIM, LAMINATEDRemove
SHIM C1-SHIM, LAMINATEDRemove
SHIM D2-SHIM, LAMINATEDRemove
Refer to SOPM 20-30-03 as an accepted
procedure as required.
--FRONT SPAR LOWER
CHORD
Clean7
Do a HFEC inspection for any crack in
accordance with 767 NDT Part 6, 51-00-
01 or 767 NDT Part 6, 51-00-19.
--FRONT SPAR LOWER
CHORD
Inspect8
FIGURE 3: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH
(SHEET 6 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 12, 2011
767-57A0126
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ALERTALERT

### Page 54 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
This Figure applies only to: Group 1, 3-4.
JACK PAD
(194KR) (194ER)
STA
BODY /83.02
FRONT SPAR  SKIN  UPPER DRAG
SPLICE ANGLE
UNDERWING
LONGERON
LOWER DRAG
SPLICE ANGLE
FORWARD FASTENERS
(3 LOCATIONS)
UNDERWING LONGERON
2028593
FIGURE 4: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH
(SHEET 1 OF 6)
Original Issue: August 12, 2011
767-57A0126
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  54 of 115

### Page 55 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
SEAL RETAINER
(REFERENCE ONLY)
SHIM "B"
FRONT
B  BATHTUB  SPAR  B
FITTING
SHIM "A"
SHIM "C"  STA
776.21
45 LOCATIONS 3
FWD
UNDERWING LONGERON
A-A
4) RADIUS  'FILLER "A"
RADIUS  FILLER "B"'  RADIUS 4
FILLER "C"  SHIM "D"
(2 LOCATIONS)
4) FILLER "D"  RADIUS
RADIUS  RADIUS
FILLER "H"  RADIUS  / FILLER "G"  RADIUS  FILLER "F"  FILLER "E"
B-B  2028673
FIGURE 4: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH
(SHEET 2 OF 6)
Original Issue: August 12, 2011
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Copyright © Unpublished Work - See page 1 for details.  55 of 115

### Page 56 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
FILLER "L" (4)  RADIUS  RADIUS
FILLER "K"  RADIUS  FILLER "J"  FILLER "I" 4  RADIUS
RADIUS  RADIUS
FILLER "p"  FILLER "O"
FWD
RADIUS
FILLER "N"
FILLER "M"  RADIUS
C-C
1.0
FRONT SPAR WEB
1.0
INSPECTION AREA  FRONT SPAR (7) 8
INTERNAL BATHTUB
FITTING LOCATION
WING
LOWER
SKIN
2028676
FIGURE 4: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH
(SHEET 3 OF 6)
Original Issue: August 12, 2011
767-57A0126
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.  56 of 115

### Page 57

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for one side of the airplane.
MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
1-NUTRemove /
Keep
1
CONCAVE1-WASHER, SELF-
ALIGN
Remove /
Keep
CONVEX2-WASHER SELF-ALIGNRemove /
Keep
1-WASHERRemove /
Keep
TENSION BOLT1-BOLT, 12 PT HEADRemove /
Keep
Refer to SOPM 20-30-03 as an accepted
procedure as required.
1-HOLEClean2
Do a HFEC inspection for any crack on
the entire joint thickness, including the
fuselage ring doubler, fuselage bathtub
fitting and wing bathtub fitting in accor-
dance with 767 NDT Part 6, 51-00-04,
or 767 NDT Part 6, 51-00-11, or 767
NDT Part 6, 51-00-16.
1-HOLEInspect
45-FASTENERSRemove3
FIGURE 4: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH
(SHEET 4 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 12, 2011
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BOEING SERVICE BULLETIN 767-57A0126
ALERTALERT

### Page 58

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER ARemove /
Keep
4
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER BRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER CRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER DRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER ERemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER FRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER GRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER HRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER IRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER JRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER KRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER LRemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER MRemove /
Keep
1-RADIUS FILLER NRemove /
Keep
FIGURE 4: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH
(SHEET 5 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 12, 2011
767-57A0126
58 of 115
BOEING SERVICE BULLETIN 767-57A0126
ALERTALERT

### Page 59

MORE DATAQTYIDENTIFICATIONNAMETASKSTEP
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER ORemove /
Keep
If you remove a RADIUS FILLER at this
location, note the orientation for re-in-
stall.
1-RADIUS FILLER PRemove /
Keep
1-FITTING, UNDER-
WING LONGERON, LH
Remove5
1-FITTING, INTERNAL
BATHTUB
Remove /
Keep
6
SHIM A1-SHIM, LAMINATEDRemove
SHIM B1-SHIM, LAMINATEDRemove
SHIM C1-SHIM, LAMINATEDRemove
SHIM D2-SHIM, LAMINATEDRemove
Refer to SOPM 20-30-03 as an accepted
procedure as required.
--FRONT SPAR LOWER
CHORD
Clean7
Do a HFEC inspection for any crack in
accordance with 767 NDT Part 6, 51-00-
01 or 767 NDT Part 6, 51-00-19.
--FRONT SPAR LOWER
CHORD
Inspect8
FIGURE 4: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, RH
(SHEET 6 OF 6)
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: August 12, 2011
767-57A0126
59 of 115
BOEING SERVICE BULLETIN 767-57A0126
ALERTALERT

### Page 60 (OCR)

BOEING SERVICE BULLETIN 767-57A0126
ALERT  ALERT
This Figure applies only to: Group 2.
JACK PAD
(193EL)  (193KL)
STA
783.04  BODY
UPPER DRAG  SKIN  FRONT SPAR
SPLICE ANGLE
50800000  UNDERWING
LONGERON
LOWER DRAG
SPLICE ANGLE
UNDERWING LONGERON
2028742
FIGURE 5: TENSION BOLT HOLE AND FRONT SPAR LOWER CHORD INSPECTION, LH
(SHEET 1 OF 6)
Original Issue: August 12, 2011
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Copyright © Unpublished Work - See page 1 for details.  60 of 115

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