# Boeing Alert Requirements Bulletin 767-53A0278 RB: No revision named

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- Title as filed: ARB 767-53A0278RB
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### Page 1

Commercial 
Airplanes
767
Requirements Bulletin
ALERT
Number: 767-53A0278 RB
Original Issue: June 30, 2017
ATA System: 5350
SUBJECT: FUSELAGE - Section 45 - Overwing Hatch Door Surround Structure - Edge Frame
Inner Chord Inspection Above Stub Beam Fitting
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 300-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET
Copyright © 2017 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document
are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The
Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and
Boeing liveries 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.
Original Issue: June 30, 2017
767-53A0278 RB
1 of 48
2.0

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Table of Contents
1 . E F F E C T I V I T Y  ................................................ 5
A. Airplanes ................................................ 5
B . S p a r e s  A f f e c t e d  ............................................ 6
2. CONCURRENT REQUIREMENTS ..................................... 6
3 . C O M P L I A N C E  ................................................ 6
4. APPROVAL ................................................ 1 2
5. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 3
A. General Information ......................................... 1 3
B. Work Instructions ........................................... 1 4
FIGURE 1: LEFT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group 1] . 19
FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM
FITTING AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group
2 ]  ................................................ 2 4
FIGURE 3: RIGHT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group 1] . 30
FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM
FITTING AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group
2 ]  ................................................ 3 5
FIGURE 5: LEFT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB
FILLER - FRAME INNER CHORD - SURFACE HFEC INSPECTION ............ 4 1
FIGURE 6: RIGHT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB
FILLER - FRAME INNER CHORD - SURFACE HFEC INSPECTION ............ 4 5
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Commercial 
Airplanes
767
Requirements Bulletin
ALERT
Number: 767-53A0278 RB
Original Issue: June 30, 2017
ATA System: 5350
SUBJECT: FUSELAGE - Section 45 - Overwing Hatch Door Surround Structure - Edge Frame
Inner Chord Inspection Above Stub Beam Fitting
THIS DOCUMENT 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 DOCUMENT
TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE
NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN
(RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL
TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB
WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. EFFECTIVITY
A. Airplanes
Service Bulletin 767-53A0278 and Requirements Bulletin 767-53A0278 RB are applicable to 767-200
and 767-300 Airplanes, line numbers 1-120, 272, 569, 602, 617-618, 642, 668, 834, 843, and 882, in
2 Groups.
DESCRIPTIONCONFIGURATIONGROUP
767-200 and 767-300 airplanes, line numbers 1-70, 72-78, 80, 82-100,
102-106, 108-112, 114-120, 272, 569, 618 and 642 delivered with
one Type III overwing exit door.
-1
767-200 and 767-300 airplanes.1
767-200 airplane changed to the 767-200SF (Special Freighter)
configuration and 767-300 airplane changed to the 767-300BCF
(Boeing Converted Freighter) configuration.
2
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DESCRIPTIONCONFIGURATIONGROUP
767-200 and 767-300 airplanes, line numbers 71, 79, 81, 101, 107,
113, 602, 617, 668, 834, 843 and 882 delivered with two Type III
overwing exit door.
-2
767-200 and 767-300 airplanes.1
767-300 airplanes changed to the 767-300BCF (Boeing Converted
Freighter) configuration.
2
B. Spares Affected
None.
2. CONCURRENT REQUIREMENTS
None.
3. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to
Requirements Bulletin 767-53A0278 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 767-53A0278 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 4, in accordance
with the Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When
more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION
numbers for that CONDITION number or OPTION number.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A,
APPENDIX B, APPENDIX C and APPENDIX D of Service Bulletin 767-53A0278.
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Group 1, Configuration 1:
Table 1: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler
installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current
(HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner
chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 24
months or 3,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 767-
53A0278 RB,
whichever oc-
curs first.
Before 37,500
total flight cy-
cles.
Do a detailed inspection
for any MRB filler in-
stalled in the area from
the frame web to the stub
beam fitting on the left
and right side at STA
859.5 and 883.5. (a)
All Airplanes.
--No further action required
at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO
STUB BEAM JOINT.
-Before further flight.Do a surface HFEC in-
spection around the end
fastener common to each
MRB filler for any crack
in the frame inner chord.
(b)
CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM
JOINT.
-Before further flight.ACTION 1: Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3: ANY
CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the
surface HFEC inspection
around the end fastener
for any crack in the frame
inner chord, at each unre-
paired frame location
common to a MRB filler.
(b)
6,000 flight cycles.-Repeat the surface HFEC
inspection around the end
fastener for any crack in
the frame inner chord, at
each frame location com-
mon to a MRB filler. (b)
CONDITION 4: NO
CRACK FOUND.
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### Page 8

Group 1, Configuration 1:
Table 1: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler
installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current
(HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner
chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches
by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767-
53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Autho-
rization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209
covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing
repairs must continue. Inspection outside each repaired region must continue as instructed in accordance
with Requirements Bulletin 767-53A0278 RB.
Group 1, Configuration 2:
Table 2: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler
installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current
(HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner
chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 24
months or 3,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 767-
53A0278 RB,
whichever oc-
curs first.
Before 30,000
total flight cy-
cles.
Do a detailed inspection
for any MRB filler in-
stalled in the area from
the frame web to the stub
beam fitting on the left
and right side at STA
859.5 and 883.5. (a)
All Airplanes.
--No further action required
at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO
STUB BEAM JOINT.
-Before further flight.Do a surface HFEC in-
spection around the end
fastener common to each
MRB filler for any crack
in the frame inner chord.
(b)
CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM
JOINT.
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### Page 9

Group 1, Configuration 2:
Table 2: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler
installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current
(HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner
chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.ACTION 1: Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3: ANY
CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the
surface HFEC inspection
around the end fastener
for any crack in the frame
inner chord, at each unre-
paired frame location
common to a MRB filler.
(b)
6,000 flight cycles.-Repeat the surface HFEC
inspection around the end
fastener for any crack in
the frame inner chord, at
each frame location com-
mon to a MRB filler. (b)
CONDITION 4: NO
CRACK FOUND.
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches
by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767-
53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Autho-
rization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209
covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing
repairs must continue. Inspection outside each repaired region must continue as instructed in accordance
with Requirements Bulletin 767-53A0278 RB.
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ALERTALERT

### Page 10

Group 2, Configuration 1:
Table 3: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB)
filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy
Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the
frame inner chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 24
months or 3,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 767-
53A0278 RB,
whichever oc-
curs first.
Before 37,500
total flight cy-
cles.
Do a detailed inspection
for any MRB filler in-
stalled in the area from
the frame web to the stub
beam fitting on the left
and right side at STA
859.5, 883.5 and 903.5.
(a)
All Airplanes.
--No further action required
at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO
STUB BEAM JOINT.
-Before further flight.Do a surface HFEC in-
spection around the end
fastener common to each
MRB filler for any crack
in the frame inner chord.
(b)
CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM
JOINT.
-Before further flight.ACTION 1: Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3: ANY
CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the
surface HFEC inspection
around the end fastener
for any crack in the frame
inner chord, at each unre-
paired frame location
common to a MRB filler.
(b)
6,000 flight cycles.-Repeat the surface HFEC
inspection around the end
fastener for any crack in
the frame inner chord, at
each frame location com-
mon to a MRB filler. (b)
CONDITION 4: NO
CRACK FOUND.
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### Page 11

Group 2, Configuration 1:
Table 3: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB)
filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy
Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the
frame inner chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches
by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767-
53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Autho-
rization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209
covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing
repairs must continue. Inspection outside each repaired region must continue as instructed in accordance
with Requirements Bulletin 767-53A0278 RB.
Group 2, Configuration 2:
Table 4: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB)
filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy
Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the
frame inner chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Within 24
months or 3,000
flight cycles af-
ter the original
issue date of
Requirements
Bulletin 767-
53A0278 RB,
whichever oc-
curs first.
Before 30,000
total flight cy-
cles.
Do a detailed inspection
for any MRB filler in in-
stalled the area from the
frame web to the stub
beam fitting on the left
and right side at STA
859.5, 883.5 and 903.5.
(a)
All Airplanes.
--No further action required
at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO
STUB BEAM JOINT.
-Before further flight.Do a surface HFEC in-
spection around the end
fastener common to each
MRB filler for any crack
in the frame inner chord.
(b)
CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM
JOINT.
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### Page 12

Group 2, Configuration 2:
Table 4: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB)
filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy
Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the
frame inner chord
Repeat Interval
(Not to Exceed)
Compliance Time (Whichever
Occurs Later)
ActionCondition
-Before further flight.ACTION 1: Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3: ANY
CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the
surface HFEC inspection
around the end fastener
for any crack in the frame
inner chord, at each unre-
paired frame location
common to a MRB filler.
(b)
6,000 flight cycles.-Repeat the surface HFEC
inspection around the end
fastener for any crack in
the frame inner chord, at
each frame location com-
mon to a MRB filler. (b)
CONDITION 4: NO
CRACK FOUND.
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches
by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767-
53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Autho-
rization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209
covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing
repairs must continue. Inspection outside each repaired region must continue as instructed in accordance
with Requirements Bulletin 767-53A0278 RB.
4. APPROVAL
This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes
specified in this document 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 document and its approval were based on the airplane
in its original Boeing delivery configuration or as modified by other Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by
this Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this Requirements Bulletin.
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### Page 13

5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 4. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches
– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus
or minus 0.03 inch
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch
– Angular tolerance is plus or minus 2 degrees
– Hole dimensions for standard solid rivets and fasteners are in Structural Repair
Manual (SRM) Chapter 51
– Torque Values:
— Values for structural fasteners are given in 767 Structural Repair Manual,
Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 767
Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of
Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 767
Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the
applicable installation step.
5. Use the approved fastener, process and material substitutions in accordance with
SRM Chapter 51.
6. A Detailed Inspection is defined as: An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or irregularity. Available lighting
is normally supplemented with a direct source of good lighting at an intensity deemed
appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be required.
7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative
procedure, the accepted alternative procedure can be used. When the words "in
accordance with" are included in the instruction, the procedure in the Boeing document
must be used.
8. 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.
10. The Work Instructions and the figures can include operation of tools or test equipment.
Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and
the Special Tool and Ground Handling Drawing Index contain data on versions of
the tools or test equipment that you can use. It is permitted to use replaced tools. It
is not permitted to use superseded tools.
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### Page 14

11. 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.
12. 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.
13. When more than one OPTION is given for a CONDITION, do only one of the OPTION
numbers. When more than one ACTION is given for a CONDITION number or an
OPTION number, do all of the ACTION numbers for that CONDITION number or
OPTION number.
14. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
15. This is an Enhanced Required for Compliance document. There will be a separate
Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated
by an Airworthiness Directive (AD), then all applicable requirements specified in the
RB must be done. For the related SB, some locations are marked RC Start and RC
End to identify the requirements that are restated from the RB. For the related SB,
the areas between RC Start and RC End, including sub-steps and any figures
identified between RC Start and RC End, must be done to comply with the AD.
Therefore, an Alternative Method of Compliance (AMOC) is required for any deviations
to steps between RC Start and RC End, including substeps and identified figures.
For the related SB, the steps not between RC Start and RC End may be deviated
from using accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC; this is provided that the
steps between RC Start and RC End, including sub-steps and identified figures, can
still be done as specified, and the airplane can be put back in an airworthy condition.
Figures not required for compliance are omitted from the RB.
16. This is an Enhanced Required for Compliance document. The Boeing processes
used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure
that the information between "RC Start" and "RC End" in the SB are identical to the
information in the same sections (Compliance, Work Instructions...) of the RB which
the SB refers to as the related document.
B. WORK INSTRUCTIONS
Actions Required for Compliance:
1. Requirements
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
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14 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 15

Group 1:
Table 1: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler
installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current
(HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner
chord
Refer to the listed
procedures in SB
767-53A0278
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure:
Method of ComplianceActionCondition
PART 1: OPEN
ACCESS
-Do a detailed inspection
for any MRB filler in-
stalled in the area from
the frame web to the stub
beam fitting on the left
and right side at STA
859.5 and 883.5. (a)
All Airplanes.
-FIGURE 1
and
FIGURE 3
PART 2: CLOSE
ACCESS
-
--No further action required
at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO
STUB BEAM JOINT.
-FIGURE 5Do a surface HFEC in-
spection around the end
fastener common to each
MRB filler for any crack
in the frame inner chord.
(b)
CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM
JOINT.
and
FIGURE 6
--ACTION 1: Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3: ANY
CRACK FOUND.
PART 1: OPEN
ACCESS
-ACTION 2: Repeat the
surface HFEC inspection
around the end fastener
for any crack in the frame
inner chord, at each unre-
paired frame location
common to a MRB filler.
(b)
-FIGURE 5
and
FIGURE 6
PART 2: CLOSE
ACCESS
-
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
15 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 16

Group 1:
Table 1: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler
installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current
(HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner
chord
Refer to the listed
procedures in SB
767-53A0278
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure:
Method of ComplianceActionCondition
PART 1: OPEN
ACCESS
-Repeat the surface HFEC
inspection around the end
fastener for any crack in
the frame inner chord, at
each frame location com-
mon to a MRB filler. (b)
CONDITION 4: NO
CRACK FOUND.
-FIGURE 5
and
FIGURE 6
PART 2: CLOSE
ACCESS
-
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches
by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767-
53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Autho-
rization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209
covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing
repairs must continue. Inspection outside each repaired region must continue as instructed in accordance
with Requirements Bulletin 767-53A0278 RB.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
16 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 17

Group 2:
Table 2: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB)
filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy
Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the
frame inner chord
Refer to the listed
procedures in SB
767-53A0278
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure:
Method of ComplianceActionCondition
PART 1: OPEN
ACCESS
-Do a detailed inspection
for any MRB filler in-
stalled in the area from
the frame web to the stub
beam fitting on the left
and right side at STA
859.5, 883.5 and 903.5.
(a)
All Airplanes.
-FIGURE 2
and
FIGURE 4
PART 2: CLOSE
ACCESS
-
--No further action required
at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO
STUB BEAM JOINT.
-FIGURE 5Do a surface HFEC in-
spection around the end
fastener common to each
MRB filler for any crack
in the frame inner chord.
(b)
CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM
JOINT.
and
FIGURE 6
--ACTION 1: Contact The
Boeing Company for re-
pair instructions and do
the repair.
CONDITION 3: ANY
CRACK FOUND.
PART 1: OPEN
ACCESS
-ACTION 2: Repeat the
surface HFEC inspection
around the end fastener
for any crack in the frame
inner chord, at each unre-
paired frame location
common to a MRB filler.
(b)
-FIGURE 5
and
FIGURE 6
PART 2: CLOSE
ACCESS
-
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
17 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 18

Group 2:
Table 2: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB)
filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy
Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the
frame inner chord
Refer to the listed
procedures in SB
767-53A0278
Original Issue or
later approved re-
visions as an ac-
cepted proce-
dure:
Method of ComplianceActionCondition
PART 1: OPEN
ACCESS
-Repeat the surface HFEC
inspection around the end
fastener for any crack in
the frame inner chord, at
each frame location com-
mon to a MRB filler. (b)
CONDITION 4: NO
CRACK FOUND.
-FIGURE 5
and
FIGURE 6
PART 2: CLOSE
ACCESS
-
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap from the frame web to the stub beam support fitting could not be filled to within 0.005 inches by the
shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767-
53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Autho-
rization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209
covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing
repairs must continue. Inspection outside each repaired region must continue as instructed in accordance
with Requirements Bulletin 767-53A0278 RB.
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
18 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 19 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
This Figure applies only to: Group 1.
STA
859.5
STA
883.5
LEFT SIDE OVERWING HATCH SURROUND
STRUCTURE FRAME SEGMENTS AND STUB BEAMS -
STA 859.5 AND 883.5
2573944
FIGURE 1: LEFT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND
ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 1 OF 5)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  19 of 48

### Page 20 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
- A
— STA  859.5
STUB BEAM
FITTING
- STA  883.5
2573945
FIGURE 1: LEFT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND
ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 2 OF 5)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  20 of 48

### Page 21 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
- FRAME
SEGMENT
EDGE OF
MRB FILLER
(TYPICAL)
S-20L -
B  - STUB BEAN
FITTING
INBD
LEFT SIDE STA 859.:
FRAME SEGMENT AND STUB BEAN
A-A
FRAME
WEB
STA
• 859.5
BEAM  STUB  B-B  BD  2573950
FITTING
FIGURE 1: LEFT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND
ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 3 OF 5)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  21 of 48

### Page 22 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
• FRAME
SEGMENT
• EDGE OF
MRB FILLER
(TYPICAL)
S-20L
D  D
STUB BEAM
FITTING
LEFT SIDE STA 883.5 FRAME SEGMENT AND
STUB BEAM
STA 889 FITTINGS NOT SHOWN FOR CLARITY
STUB  C-C
BEAM
FITTING  (2)
STA
• 883.5
FRAME  D-D  IBD  2573951
WEB
FIGURE 1: LEFT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND
ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 4 OF 5)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0278 RB
Work - See page 1 for details.  22 of 48

### Page 23

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect1
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect2
(a) Do a detailed inspection for any Material Review Board (MRB) filler installed in the area from the frame
web to the stub beam fitting that extends above the frame to stub beam joint.
(b) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches
by the shim installation.
FIGURE 1: LEFT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND
ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
23 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 24 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
This Figure applies only to: Group 2.
STA
859.5
STA
883.5
STA
903.5
LEFT SIDE OVERWING HATCH SURROUND
STRUCTURE FRAME SEGMENTS AND STUB BEAMS -
STA 859.5, 883.5 AND 903.5
2573142
FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 1 OF 6)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  24 of 48

### Page 25 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
* STA
859.5
STA  883.5
- STA  903.5  STUB BEAM
FITTING
FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 2 OF 6)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  25 of 48

### Page 26 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
• FRAME
SEGMENT
- EDGE OF
MRB FILLER
(TYPICAL)
S-20L -
B  B  - STUB BEAN
FITTING
INBD
LEFT SIDE STA 859.5
FRAME SEGMENT AND STUB BEAM
A-A
FRAME
WEB
STA
- 859.5
STUB  BEAM  B-B  INBD  2573036
FITTING
FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 3 OF 6)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  26 of 48

### Page 27 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
EDGE OF
MRB FILLER
(TYPICAL)
S-20L
D  ID  STUB BEAM
FITTING
LEFT SIDE STA 883.5
FRAME SEGMENT AND STUB BEAM
C-C
STUB
BEAM
FITTING
STA
883.5
FRAME  D-D  IBD  2573054
WEB
FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 4 OF 6)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  27 of 48

### Page 28 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
• FRAME
SEGMENT
EDGE OF
MRB FILLER
(TYPICAL)
S-20L
• STUB BEAM
FITTING
LEFT SIDE STA 903.5
FRAME SEGMENT AND STUB BEAM
E-E
FRAME
WEB
STA
- 903.5
STUB  NBD  2573028
BEAM  F-F
FITTING
FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 5 OF 6)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  28 of 48

### Page 29

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect1
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect2
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect3
(a) Do a detailed inspection for any Material Review Board (MRB) filler installed in the area from the frame
web to the stub beam fitting.
(b) A structural Material Review Board (MRB) filler is installed during production integration in addition to a
laminated shim when the gap from the frame web to the stub beam support fitting could not be filled to
within 0.005 inches by the shim installation.
FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
29 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 30 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
This Figure applies only to: Group 1.
D
D
STA
859.5
STA
883.5
RIGHT SIDE OVERWING HATCH SURROUND
STRUCTURE FRAME SEGMENTS AND STUB BEAMS -
STA 859.5 AND 883.5
2575217
FIGURE 3: RIGHT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 1 OF 5)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  30 of 48

### Page 31 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
, FRAME
SEGMENT
859.5  STA
STUB BEAM
FITTING
STA
883.5
2575221
FIGURE 3: RIGHT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 2 OF 5)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  31 of 48

### Page 32 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
EDGE OF
MRB FILLER
(TYPICAL)
- S-20R
STYINGEAM  B
INBD
RIGHT SIDE STA 859.5
FRAME SEGMENT AND STUB BEAM
A-A
FRAME
WEB
STA
859.5
INBD  B-B  STUB  2575222
BEAM
FITTING
FIGURE 3: RIGHT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 3 OF 5)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0278 RB
Work - See page 1 for details.  32 of 48

### Page 33 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
EDGE OF
MRB FILLER
(TYPICAL)
S-20R
STUB BEAM  D
FITTING
RIGHT SIDE STA 883.5 FRAME SEGMENT AND
STUB BEAM
STA 889 FITTINGS NOT SHOWN FOR CLARITY
C-C  STUB
BEAM
FITTING
STA
883.5
D-D  FRAME
INBD  WEB  2575223
FIGURE 3: RIGHT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 4 OF 5)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  33 of 48

### Page 34

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect1
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect2
(a) Do a detailed inspection for any Material Review Board (MRB) filler installed in the area from the frame
web to the stub beam fitting that extends above the frame to stub beam joint.
(b) A structural MRB filler is installed during production integration in addition to a laminated shim when the
gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches
by the shim installation.
FIGURE 3: RIGHT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
34 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 35 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
This Figure applies only to: Group 2.
STA
859.5
STA
883.5
STA
903.5
RIGHT SIDE OVERWING HATCH SURROUND
STRUCTURE FRAME SEGMENTS AND STUB BEAMS -
STA 859.5, 883.5 AND 903.5
FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 1 OF 6)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  35 of 48

### Page 36 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
STA
859.5
883.5  STA-
STUB BEAM  903.5  STA
FITTING
2575231
FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5-AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 2 OF 6)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  36 of 48

### Page 37 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
EDGE OF
MRB FILLER -
(TYPICAL)
• S-20R
FITTING  STING AM
NBD
RIGHT SIDE STA 859.5
FRAME SEGMENT AND STUB BEAM
A-A
FRAME
WEB
STA
859.5-
INBD  B-B  STUB  2575234
BEAM
FITTING
FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 3 OF 6)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  37 of 48

### Page 38 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
EDGE OF
MRB FILLER
(TYPICAL)
S-20R 1
STUB BEAM  D
FITTING
RIGHT SIDE STA 883.5
FRAME SEGMENT AND STUB BEAM
C-C
STUB
BEAM
FITTING
STA
883.5
INBD  D-D  FRAME  WEB  2575235
FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5-AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 4 OF 6)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0278 RB
Work - See page 1 for details.  38 of 48

### Page 39 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
EDGE OF
MRB FILLER
(TYPICAL)
- S-20R
STUB BEAM
FITTING
RIGHT SIDE STA 903.5
FRAME SEGMENT AND STUB BEAM
E-E
FRAME
WEB
STA
903.5
INBD  STUB  BEAM  2575237
F-F  FITTING
FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 5 OF 6)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  39 of 48

### Page 40

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect1
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect2
(a)(b)--AREA FROM FRAME
WEB TO STUB BEAM
FITTING
Inspect3
(a) Do a detailed inspection for any Material Review Board (MRB) filler installed in the area from the frame
web to the stub beam fitting.
(b) A structural Material Review Board (MRB) filler is installed during production integration in addition to a
laminated shim when the gap from the frame web to the stub beam support fitting could not be filled to
within 0.005 inches by the shim installation.
FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING
AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
40 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 41 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
STA
TYPICAL
LEFT SIDE OVERWING HATCH SURROUND
STRUCTURE FRAME SEGMENTS AND STUB BEAMS
2574226
FIGURE 5: LEFT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 1 OF 4)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  PROPRIETARY - Copyright © Unpublished  767-53A0278 RB
Work - See page 1 for details.  41 of 48

### Page 42 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
STUB BEAM
FITTING
* STA
TYPICAL
FRAME
SEGMENT
2574227
FIGURE 5: LEFT SIDE -AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 2 OF 4)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  42 of 48

### Page 43 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
© INNER
CHORD
- EDGE OF
MRB FILLER
(TYPICAL)
STUB BEAM
S-20L-  FITTING
INBD
LEFT SIDE TYPICAL FRAME SEGMENT AND STUB BEAM
AFT FITTINGS NOT SHOWN FOR CLARITY
A-A  2574229
FIGURE 5: LEFT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 3 OF 4)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  43 of 48

### Page 44

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--INNER CHORDInspect1
(a) Do a surface high frequency eddy current (HFEC) inspection for any crack in the frame inner chord around
the end fastener common to the MRB filler in accordance with 767 NDT Manual Part 6, 51-00-19.
FIGURE 5: LEFT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
44 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

### Page 45 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
D
STA
TYPICAL
RIGHT SIDE OVERWING HATCH SURROUND
STRUCTURE FRAME SEGMENTS AND STUB BEAMS
2574231
FIGURE 6: RIGHT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 1 OF 4)
Original Issue: June 30, 2017
Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.  45 of 48

### Page 46 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
STUB BEAM
FITTING
STA
TYPICAL
FRAME
SEGMENT
2574233
FIGURE 6: RIGHT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 2 OF 4)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  46 of 48

### Page 47 (OCR)

REQUIREMENTS BULLETIN 767-53A0278
ALERT  ALERT
FRAME
SEGMENT
CHORD Q  INNER
EDGE OF
MRB FILLER
(TYPICAL)
S-20R
STUB BEAM
FITTING
RIGHT SIDE TYPICAL FRAME SEGMENT AND STUB BEAM
AFT FITTINGS NOT SHOWN FOR CLARITY
A-A  2574234
FIGURE 6: RIGHT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 3 OF 4)
Original Issue: June 30, 2017
PROPRIETARY - Copyright © Unpublished  Export Controlled ECCN: 9E991 - BOEING  767-53A0278 RB
Work - See page 1 for details.  47 of 48

### Page 48

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--INNER CHORDInspect1
(a) Do a surface high frequency eddy current (HFEC) inspection for any crack in the frame inner chord around
the end fastener common to the MRB filler in accordance with 767 NDT Manual Part 6, 51-00-19.
FIGURE 6: RIGHT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER
- FRAME INNER CHORD - SURFACE HFEC INSPECTION
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991 - BOEING
PROPRIETARY - Copyright © Unpublished
Work - See page 1 for details.
Original Issue: June 30, 2017
767-53A0278 RB
48 of 48
REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT

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