# Boeing Alert Requirements Bulletin B787-81205-SB530076-00 RB

Copy: Revision 001 ("SB-787-53A0076-00_RB"), 42 pages: PDF https://openairdocs.org/files/sha256/73/43/73437b796d96f8d8184cfd80d34a2b91b7de26a90d84db6ae1e0aeb4280246b7; text https://openairdocs.org/service-documents/boeing/b787-81205-sb530076-00-rb/file/73437b796d96.md. Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2021-0332; AD 2021-23-20 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Boeing](https://openairdocs.org/service-documents/boeing.md)
- Type: Service bulletin (Alert Requirements Bulletin)
- Number: B787-81205-SB530076-00 RB
- Latest revision known: B787-81205-SB530076-00 RB, Issue 001, dated September 8, 2020 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/boeing/b787-81205-sb530076-00-rb

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2021-23-20](https://openairdocs.org/ad/2021-23-20.md), effective Jan 10, 2022: Revision 001

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/boeing/b787-81205-sb530076-00-rb/proposed.md).

## Text (42 pages)

Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2021-0332; AD 2021-23-20 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

Alert Requirements Bulletin B787-81205-SB530076-00 RB FUSELAGE -
Structure - STA 873 Front Spar Body Chord Inspection
Copyright © 2020 Boeing. Unpublished Work. All rights reserved.
Treatment of this data module and its content is governed by contract with Boeing. Rights to use this data module 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.
EXPORT CONTROLLED
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.
ECCN: 9E991
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3.0
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Table of Contents
Page
A. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4
B. CONCURRENT REQ UIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4
C. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4
D. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
E. ACCOMPLISHMENT INSTR UCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
1. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11
2. Work Instr uctions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12
TASK 1 – FRONT SPAR BODY CHORD HFEC INSPECTION  [Group 1] . . . . . . . . . . . . . . . . . . 19
TASK 2 – FRONT SPAR BODY CHORD DETAILED INSPECTION [Group 1] . . . . . . . . . . . . . . . 24
TASK 3 – FRONT SPAR BODY CHORD UT INSPECTION [Group 1] . . . . . . . . . . . . . . . . . . . . 29
TASK 4 – FRONT SPAR BODY CHORD HFEC INSPECTION  [Group 2] . . . . . . . . . . . . . . . . . . 34
TASK 5 – FRONT SPAR BODY CHORD DETAILED INSPECTION [Group 2] . . . . . . . . . . . . . . . 39
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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
Alert:
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.
A. EFFECTIVITY
1. Airplanes
This bulletin is applicable to 787-8, 787-9 Airplane(s), line number(s) 115-527, 529-547, 549-564,
566-598, 601, 603, 605, 607, 610, 612, 614, 619 in 2 Group(s).Where the effectivity is presented
with hyphens between line numbers, the airplane applicability means "through" and "inclusive",
e.g. line numbers 1-9 means line numbers 1 through 9 inclusive.
Table 1  
DESCRIPTIONCONFIGURATIONGROUP
787-8 Airplanes with potential shimming requirements not met at STA
873 Front Spar Body Chord structure joints.
-1
787-9 Airplanes with potential shimming requirements not met at STA
873 Front Spar Body Chord structure joints.
-2
Airplane Models: 787-8, 787-9
Table 2
GroupVariable Number
1ZA122 - ZA124
1ZA136 - ZA144
1ZA152 - ZA156
1ZA187 - ZA189
1ZA195 - ZA204
1ZA215 - ZA225
1ZA244 - ZA255
1ZA265 - ZA269
1ZA275 - ZA277
1ZA291 - ZA296
GroupVariable Number
1ZA321 - ZA324
1ZA327
1ZA334 - ZA335
1ZA341 - ZA342
1ZA387 - ZA389
1ZA435 - ZA439
1ZA445 - ZA448
1ZA453 - ZA457
1ZA468 - ZA489
1ZA515 - ZA516
GroupVariable Number
1ZA540 - ZA545
1ZA560 - ZA567
1ZA578 - ZA580
1ZA586
1ZA588 - ZA593
1ZA610 - ZA617
1ZA650 - ZA652
1ZA655 - ZA663
1ZA665 - ZA675
1ZA680 - ZA685
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GroupVariable Number
1ZA695 - ZA697
1ZA715 - ZA716
1ZA718 - ZA719
1ZA740 - ZA741
1ZA768 - ZA769
1ZA778 - ZA779
1ZA783 - ZA784
1ZA817 - ZA831
1ZA839
1ZA842
1ZA846 - ZA848
1ZA853 - ZA860
1ZA873 - ZA874
1ZA881 - ZA888
1ZA916 - ZA920
2ZB001 - ZB010
2ZB021 - ZB040
2ZB047 - ZB057
GroupVariable Number
2ZB077 - ZB081
2ZB097 - ZB107
2ZB127 - ZB132
2ZB167 - ZB187
2ZB197 - ZB198
2ZB217
2ZB224 - ZB229
2ZB234 - ZB242
2ZB246
2ZB251 - ZB253
2ZB261
2ZB299
2ZB302
2ZB332
2ZB362 - ZB377
2ZB407 - ZB418
2ZB422 - ZB424
2ZB446 - ZB457
GroupVariable Number
2ZB536 - ZB543
2ZB545 - ZB547
2ZB558 - ZB578
2ZB603 - ZB618
2ZB646 - ZB649
2ZB656 - ZB659
2ZB676 - ZB679
2ZB688 - ZB699
2ZB703 - ZB705
2ZB733
2ZB738 - ZB739
2ZB763 - ZB766
2ZB778 - ZB779
2ZB782 - ZB791
2ZB812 - ZB815
2ZB828
2ZB831
--
2. Spares Affected
None.
B. CONCURRENT REQUIREMENTS
None.
C. COMPLIANCE
The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Re-
quirements Bulletin B787-81205-SB530076-00 RB. The Airworthiness Directive will make the compliance
tasks and times given in Requirements Bulletin B787-81205-SB530076-00 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Table 5 and 6, in accordance with
Accomplishment Instructions.
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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 or an OPTION, do all of the ACTION numbers for that
CONDITION or OPTION.
Group 1:
Table 5  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection, Detailed Inspection and Ultra-
sonic (UT) Inspection
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 1,500 Flight
Cycles OR within 365
days after the Issue
001 date of the Re-
quirements Bulletin
B787-81205-
SB530076-00 RB,
whichever occurs first.
Before 101,250 Total
Flight Hours (TFH)
OR
Before 11,600 Total
Flight Cycles (TFC)
OR
Before the result of
12,450.80 -
(0.048897*TFH) -
TFC is less than or
equal to zero,
whichever occurs
first.
ACTION 1:
Do a HFEC inspection
along the entire forward
edge of the front spar body
chord in the area covered
by the body chord splice
angle at stringer S-25, left
and right side, and the
splice fitting at Buttock Line
(BL) 0, STA 873, for any
crack.
All Airplanes
ACTION 2:
Do a detailed inspection of
the front spar body chord
horizontal flange surface
between stringer S-26 to
stringer S-40 at STA 873,
left and right side, for any
crack.
ACTION 3:
Do an UT inspection of the
front spar body chord hori-
zontal flange along the up-
per and lower edges of the
end fittings at stringer S-
27, at STA 873, left and
right side, for any crack.
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Group 1:
Table 5  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection, Detailed Inspection and Ultra-
sonic (UT) Inspection
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.ACTION 1:CONDITION 1:
ANY CRACK
FOUND DURING
HFEC INSPEC-
TION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
12,000 Flight Cy-
cles
-ACTION 2:
Repeat the HFEC inspec-
tion along the entire for-
ward edge of the front spar
body chord in the area
covered by the body chord
splice angle at stringer S-
25, left and right side, and
the splice fitting at BL0,
STA 873, for any crack. *[2]
12,000 Flight Cy-
cles
-Repeat the HFEC inspec-
tion along the entire for-
ward edge of the front spar
body chord in the area
covered by the body chord
splice angle at stringer S-
25, left and right side, and
the splice fitting at BL0,
STA 873, for any crack. *[2]
CONDITION 2:
NO CRACK
FOUND DURING
HFEC INSPEC-
TION.
-Before further flight.ACTION 1:CONDITION 3:
ANY CRACK
FOUND DURING
DETAILED IN-
SPECTION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
12,000 Flight Cy-
cles
-ACTION 2:
Repeat the detailed inspec-
tion of the front spar body
chord horizontal flange
surface between stringer
S-26 to stringer S-40 at
STA 873, left and right
side, for any crack. *[2]
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Group 1:
Table 5  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection, Detailed Inspection and Ultra-
sonic (UT) Inspection
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
12,000 Flight Cy-
cles
-Repeat the detailed inspec-
tion of the front spar body
chord horizontal flange
surface between stringer
S-26 to stringer S-40 at
STA 873, left and right
side, for any crack. *[2]
CONDITION 4:
NO CRACK
FOUND DURING
DETAILED IN-
SPECTION.
-Before further flight.ACTION 1:CONDITION 5:
ANY CRACK
FOUND DURING
UT INSPECTION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
12,000 Flight Cy-
cles
-ACTION 2:
Repeat the UT inspection
of the front spar body
chord horizontal flange
along the upper and lower
edges of the end fittings at
stringer S-27, at STA 873,
left and right side, for any
crack. *[2]
12,000 Flight Cy-
cles
-Repeat the UT inspection
of the front spar body
chord horizontal flange
along the upper and lower
edges of the end fittings at
stringer S-27, at STA 873,
left and right side, for any
crack. *[2]
CONDITION 6:
NO CRACK
FOUND DURING
UT INSPECTION.
*[1]  If a repair is required due to a crack condition identified in accordance with this service bulletin, the repair will be related to Critical
Design Configuration Control Limitation (CDCCL) required by Special Compliance Items/Airworthiness Limitation (SCI/AWL) D011Z009-
03-04. Strict adherence to SCI/AWL is required.
*[2]  It is not required to do the inspections in accordance with Requirements Bulletin B787-81205-SB530076-00 RB in areas where a repair
covers the affected inspection area and meets the following conditions:
1.The repair is the corrective action to the crack condition identified in Requirements Bulletin B787-81205-SB530076-00 RB and installed
after the Issue 001 date of the Requirements Bulletin B787-81205-SB530076-00 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 which contains a
repeat inspection program for the subject area.
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Group 2:
Table 6  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection and Detailed Inspection
Repeat Interval (Not
to Exceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
-Within 1,500 Flight
Cycles OR within
365 days after the Is-
sue 001 date of the
Requirements Bul-
letin B787-81205-
SB530076-00 RB,
whichever occurs
first.
Before 76,950 Total
Flight Hours (TFH)
OR
Before 9,900 Total
Flight Cycles (TFC)
OR
Before the result of
10,904.30 -
(0.06763*TFH) - TFC
is less than or equal
to zero, whichever
occurs first.
ACTION 1:
Do a HFEC inspec-
tion along the entire
forward edge of the
front spar body chord
in the area covered
by the body chord
splice angle at
stringer S-25, left
and right side, and
the splice fitting at
Buttock Line (BL) 0,
STA 873, for any
crack.
All Airplanes
ACTION 2:
Do a detailed inspec-
tion of the front spar
body chord horizon-
tal flange surface be-
tween stringer S-26
to stringer S-40 at
STA 873, left and
right side, for any
crack.
-Before further flight.ACTION 1:CONDITION 7: ANY
CRACK FOUND
DURING HFEC IN-
SPECTION.
Contact The Boeing
Company for repair
instructions and do
the repair. *[1]
12,000 Flight Cycles-ACTION 2:
Repeat the HFEC in-
spection along the
entire forward edge
of the front spar body
chord in the area
covered by the body
chord splice angle at
stringer S-25, left
and right side, and
the splice fitting at
BL0, STA 873, for
any crack. *[2]
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### Page 9

Group 2:
Table 6  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection and Detailed Inspection
Repeat Interval (Not
to Exceed)
Compliance Time (Whichever Occurs
Later)
ActionCondition
12,000 Flight Cycles-Repeat the HFEC in-
spection along the
entire forward edge
of the front spar body
chord in the area
covered by the body
chord splice angle at
stringer S-25, left
and right side, and
the splice fitting at
BL0, STA 873, for
any crack. *[2]
CONDITION 8: NO
CRACK FOUND
DURING HFEC IN-
SPECTION.
-Before further flight.ACTION 1:CONDITION 9: ANY
CRACK FOUND
DURING DETAILED
INSPECTION.
Contact The Boeing
Company for repair
instructions and do
the repair. *[1]
12,000 Flight Cycles-ACTION 2:
Repeat the detailed
inspection of the
front spar body chord
horizontal flange sur-
face between
stringer S-26 to
stringer S-40 at STA
873, left and right
side, for any crack.
*[2]
12,000 Flight Cycles-Repeat the detailed
inspection of the
front spar body chord
horizontal flange sur-
face between
stringer S-26 to
stringer S-40 at STA
873, left and right
side, for any crack.
*[2]
CONDITION 10: NO
CRACK FOUND
DURING DETAILED
INSPECTION.
*[1]  If a repair is required due to a crack condition identified in accordance with this service bulletin, the repair will be related to Critical
Design Configuration Control Limitation (CDCCL) required by Special Compliance Items/Airworthiness Limitation (SCI/AWL) D011Z009-
03-04. Strict adherence to SCI/AWL is required.
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Group 2:
Table 6  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection and Detailed Inspection
*[2]  It is not required to do the inspections in accordance with Requirements Bulletin B787-81205-SB530076-00 RB in areas where a repair
covers the affected inspection area and meets the following conditions:
1.The repair is the corrective action to the crack condition identified in Requirements Bulletin B787-81205-SB530076-00 RB and installed
after the Issue 001 date of the Requirements Bulletin B787-81205-SB530076-00 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 which contains a
repeat inspection program for the subject area.
D. 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 Requirements 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 11

E.    ACCOMPLISHMENT INSTRUCTIONS
1. GENERAL INFORMATION
OBEY THE MANUFACTURER'S PROCEDURES WHEN YOU DO TASKS THAT
ARE RELATED TO AIRWORTHINESS LIMITATIONS (AWL). IF YOU DO NOT OBEY
THE PROCEDURES, IT CAN INCREASE THE RISK OF A SOURCE OF IGNITION.
INJURIES TO PERSONNEL, AND DAMAGE TO EQUIPMENT CAN OCCUR IF
THERE IS A FIRE OR EXPLOSION.
WARNING
NOTE: 1. 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.
2. 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.
3. 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.
4. The compliance times for the actions in the Work Instructions are in the Compliance
section.
5. 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.
6. The instructions in the Work Instructions 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 12

7. 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.
8. If a repair is required due to a crack condition identified in accordance with this bulletin,
the repair will be related to Critical Design Configuration Control Limitation (CDCCL) re-
quired by Special Compliance Items/Airworthiness Limitation (SCI/AWL) D011Z009-03-
04. Strict adherence to SCI/AWL is required.
9. Boeing Service Letter 787-SL-51-001, 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.
2. WORK INSTRUCTIONS
A. Actions Required for Compliance
(1) Requirements
B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN

### Page 13

Group 1:
Table 1  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection, Detailed Inspection and Ultra-
sonic (UT) Inspection
Refer to the listed proce-
dures in SB B787-81205-
SB530076-00 Issue 001
or later approved issues
as an accepted proce-
dure
Method of ComplianceActionCondition
PART 1: OPEN ACCESS--All Airplanes
-Task 1ACTION 1:
Do a HFEC inspection
along the entire forward
edge of the front spar body
chord in the area covered
by the body chord splice
angle at stringer S-25, left
and right side, and the
splice fitting at Buttock
Line (BL) 0, STA 873, for
any crack.
-Task 2ACTION 2:
Do a detailed inspection of
the front spar body chord
horizontal flange surface
between stringer S-26 to
stringer S-40 at STA 873,
left and right side, for any
crack.
-Task 3ACTION 3:
Do an UT inspection of the
front spar body chord hori-
zontal flange along the up-
per and lower edges of the
end fittings at stringer S-
27, at STA 873, left and
right side, for any crack.
B787-81205-SB530076-00 RB
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EXPORT CONTROLLED ECCN: 9E991
See title page for details.
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Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN

### Page 14

Group 1:
Table 1  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection, Detailed Inspection and Ultra-
sonic (UT) Inspection
Refer to the listed proce-
dures in SB B787-81205-
SB530076-00 Issue 001
or later approved issues
as an accepted proce-
dure
Method of ComplianceActionCondition
PART 2: CLOSE ACCESS-ACTION 1:CONDITION 1: ANY
CRACK FOUND DURING
HFEC INSPECTION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
PART 1: OPEN ACCESS-ACTION 2:
Repeat the HFEC inspec-
tion along the entire for-
ward edge of the front spar
body chord in the area
covered by the body chord
splice angle at stringer S-
25, left and right side, and
the splice fitting at BL0,
STA 873, for any crack. *[2]
-Task 1
PART 2: CLOSE ACCESS-
PART 1: OPEN ACCESS-Repeat the HFEC inspec-
tion along the entire for-
ward edge of the front spar
body chord in the area
covered by the body chord
splice angle at stringer S-
25, left and right side, and
the splice fitting at BL0,
STA 873, for any crack. *[2]
CONDITION 2: NO
CRACK FOUND DURING
HFEC INSPECTION. -Task 1
PART 2: CLOSE ACCESS-
PART 2: CLOSE ACCESS-ACTION 1:CONDITION 3: ANY
CRACK FOUND DURING
DETAILED INSPECTION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
PART 1: OPEN ACCESS-ACTION 2:
Repeat the detailed inspec-
tion of the front spar body
chord horizontal flange
surface between stringer
S-26 to stringer S-40 at
STA 873, left and right
side, for any crack. *[2]
-Task 2
PART 2: CLOSE ACCESS-
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EXPORT CONTROLLED ECCN: 9E991
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REQUIREMENTS BULLETIN

### Page 15

Group 1:
Table 1  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection, Detailed Inspection and Ultra-
sonic (UT) Inspection
Refer to the listed proce-
dures in SB B787-81205-
SB530076-00 Issue 001
or later approved issues
as an accepted proce-
dure
Method of ComplianceActionCondition
PART 1: OPEN ACCESS-Repeat the detailed inspec-
tion of the front spar body
chord horizontal flange
surface between stringer
S-26 to stringer S-40 at
STA 873, left and right
side, for any crack. *[2]
CONDITION 4: NO
CRACK FOUND DURING
DETAILED INSPECTION. -Task 2
PART 2: CLOSE ACCESS-
PART 2: CLOSE ACCESS-ACTION 1:CONDITION 5: ANY
CRACK FOUND DURING
UT INSPECTION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
PART 1: OPEN ACCESS-ACTION 2:
Repeat the UT inspection
of the front spar body
chord horizontal flange
along the upper and lower
edges of the end fittings at
stringer S-27, at STA 873,
left and right side, for any
crack. *[2]
-Task 3
PART 2: CLOSE ACCESS-
PART 1: OPEN ACCESS-Repeat the UT inspection
of the front spar body
chord horizontal flange
along the upper and lower
edges of the end fittings at
stringer S-27, at STA 873,
left and right side, for any
crack. *[2]
CONDITION 6: NO
CRACK FOUND DURING
UT INSPECTION. -Task 3
PART 2: CLOSE ACCESS-
*[1]  If a repair is required due to a crack condition identified in accordance with this service bulletin, the repair will be related to Critical
Design Configuration Control Limitation (CDCCL) required by Special Compliance Items/Airworthiness Limitation (SCI/AWL) D011Z009-
03-04. Strict adherence to SCI/AWL is required.
*[2]  It is not required to do the inspections in accordance with Requirements Bulletin B787-81205-SB530076-00 RB in areas where a repair
covers the affected inspection area and meets the following conditions:
1.The repair is the corrective action to the crack condition identified in Requirements Bulletin B787-81205-SB530076-00 RB and installed
after the Issue 001 date of the Requirements Bulletin B787-81205-SB530076-00 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 which contains a
repeat inspection program for the subject area.
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REQUIREMENTS BULLETIN

### Page 16

Group 2:
Table 2  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection and Detailed Inspection
Refer to the listed proce-
dures in SB B787-81205-
SB530076-00 Issue 001
or later approved issues
as an accepted proce-
dure
Method of ComplianceActionCondition
PART 1: OPEN ACCESS--All Airplanes
-Task 4ACTION 1:
Do a HFEC inspection
along the entire forward
edge of the front spar body
chord in the area covered
by the body chord splice
angle at stringer S-25, left
and right side, and the
splice fitting at Buttock
Line (BL) 0, STA 873, for
any crack.
-Task 5ACTION 2:
Do a detailed inspection of
the front spar body chord
horizontal flange surface
between stringer S-26 to
stringer S-40 at STA 873,
left and right side, for any
crack.
PART 2: CLOSE ACCESS-ACTION 1:CONDITION 7: ANY
CRACK FOUND DURING
HFEC INSPECTION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
PART 1: OPEN ACCESS-ACTION 2:
Repeat the HFEC inspec-
tion along the entire for-
ward edge of the front spar
body chord in the area
covered by the body chord
splice angle at stringer S-
25, left and right side, and
the splice fitting at BL 0,
STA 873, for any crack. *[2]
-Task 4
PART 2: CLOSE ACCESS-
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REQUIREMENTS BULLETIN

### Page 17

Group 2:
Table 2  Front Spar Body Chord High Frequency Eddy Current (HFEC) Inspection and Detailed Inspection
Refer to the listed proce-
dures in SB B787-81205-
SB530076-00 Issue 001
or later approved issues
as an accepted proce-
dure
Method of ComplianceActionCondition
PART 1: OPEN ACCESS-Repeat the HFEC inspec-
tion along the entire for-
ward edge of the front spar
body chord in the area
covered by the body chord
splice angle at stringer S-
25, left and right side, and
the splice fitting at BL 0,
STA 873, for any crack. *[2]
CONDITION 8: NO
CRACK FOUND DURING
HFEC INSPECTION. -Task 4
PART 2: CLOSE ACCESS-
PART 2: CLOSE ACCESS-ACTION 1:CONDITION 9: ANY
CRACK FOUND DURING
DETAILED INSPECTION.
Contact The Boeing Com-
pany for repair instructions
and do the repair. *[1]
PART 1: OPEN ACCESS-ACTION 2:
Repeat the detailed inspec-
tion of the front spar body
chord horizontal flange
surface between stringer
S-26 to stringer S-40 at
STA 873, left and right
side, for any crack. *[2]
-Task 5
PART 2: CLOSE ACCESS-
PART 1: OPEN ACCESS-Repeat the detailed inspec-
tion of the front spar body
chord horizontal flange
surface between stringer
S-26 to stringer S-40 at
STA 873, left and right
side, for any crack. *[2]
CONDITION 10: NO
CRACK FOUND DURING
DETAILED INSPECTION. -Task 5
PART 2: CLOSE ACCESS-
*[1]  If a repair is required due to a crack condition identified in accordance with this service bulletin, the repair will be related to Critical
Design Configuration Control Limitation (CDCCL) required by Special Compliance Items/Airworthiness Limitation (SCI/AWL) D011Z009-
03-04. Strict adherence to SCI/AWL is required.
*[2]  It is not required to do the inspections in accordance with Requirements Bulletin B787-81205-SB530076-00 RB in areas where a repair
covers the affected inspection area and meets the following conditions:
1.The repair is the corrective action to the crack condition identified in Requirements Bulletin B787-81205-SB530076-00 RB and installed
after the Issue 001 date of the Requirements Bulletin B787-81205-SB530076-00 RB.
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an FAA Form 8100-9 which contains a
repeat inspection program for the subject area.
B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN

### Page 18

Task 1 – FRONT SPAR BODY CHORD HFEC INSPECTION [Group 1: ]
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
Alert:
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.
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REQUIREMENTS BULLETIN

### Page 19 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN
Procedure
This Task applies only to: Group 1.
STA 873
BL
S-25R-  - S-25L
FORWARD CARGO COMPARTMENT
(VIEW LOOKING AFT, STA 873)
ICN-B787-A-000061-A-81205-17622-A-01-1
Figure 1
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### Page 20 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN
FRONT SPAR BODY
CHORD SPLICE ANGLE
FRONT SPAR
BODY CHORD
S-25L
FRONT SPAR BODY
CHORD SPLICE ANGLE
S-25R
- FRONT SPAR
BODY CHORD
\ INSPECTIONAREA  2913913
ICN-B787-A-000061-A-81205-17623-A-01-1
Figure 2
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### Page 21 (OCR)

A BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
BL
S-40R  BODY CHORD  FRONT SPAR  BODY CHORD  FRONT SPAR  S-40L
SPLICE FITTING
FORWARD CARGO COMPARTMENT
(VIEW LOOKING AFT, STA 873)
• INSPECTION AREA  2914279
ICN-B787-A-000061-A-81205-17624-A-01-1
Figure 3
1. The step numbers shown below agree with the numbers shown in the circle symbols in the Task. The QTY
numbers shown below are the number of parts necessary for this task.
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### Page 22

Table 1  
More DataQtyIdentificationNameActionStep
*[1]--FRONT SPAR BODY
CHORD
Inspect1
*[2]--FRONT SPAR BODY
CHORD
Inspect2
*[1]  Do a surface HFEC inspection along the entire forward edge of the front spar body chord in the area covered by the front spar body
chord splice angle at stringer S-25, left and right side, for any crack in accordance with 787 NDT Manual Part 6, 53-20-07 Temporary
Revision (TR) 06-1019 dated Feb 25/2020, or 787 NDT Manual Part 6, 53-20-07 that incorporates 787 NDT Manual Part 6, 53-20-07
TR 06-1019 dated Feb 25/2020 or later Boeing approved revisions.
*[2]  Do a surface HFEC inspection along the entire forward edge of the front spar body chord in the area covered by the front spar body
chord splice fitting at BL0, left and right side, for any crack in accordance with 787 NDT Manual Part 6, 53-20-11 TR 06-1009 dated
Feb 20/2020, or 787 NDT Manual Part 6, 53-20-11 that incorporates 787 NDT Manual Part 6, 53-20-11 TR 06-1009 dated Feb 20/2020
or later Boeing approved revisions.
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See title page for details.
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REQUIREMENTS BULLETIN

### Page 23

Task 2 – FRONT SPAR BODY CHORD DETAILED INSPECTION [Group 1:
]
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
Alert:
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.
B787-81205-SB530076-00 RB
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See title page for details.
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REQUIREMENTS BULLETIN

### Page 24 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
Procedure
This Task applies only to: Group 1.
STA 873
BL
FORWARD CARGO COMPARTMENT
(VIEW LOOKING AFT, STA 873)
ICN-B787-A-000061-A-81205-17625-A-01-1
Figure 1
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### Page 25 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN
FRONT SPAR
BODY CHORD
SPLICE ANGLE
- S-25L
FRONT SPAR  - S-31L
BODY CHORD
FRONT SPAR BODY
CHORD SPLICE FITTING
STA 873-  S-40L
BL O
LEFT SIDE BODY CHORD
\ INSPECTION AREA  13950
ICN-B787-A-000061-A-81205-17626-A-01-1
Figure 2
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### Page 26 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
FRONT SPAR
BODY CHORD
SPLICE ANGLE
S-25R -
S-31R  FRONT SPAR
BODY CHORD
FRONT SPAR BODY
CHORD SPLICE FITTING
S-40R
BLO  STA 873
RIGHT SIDE BODY CHORD
/ INSPECTION AREA
ICN-B787-A-000061-A-81205-17627-A-01-1
Figure 3
1. The step numbers shown below agree with the numbers shown in the circle symbols in the Task. The QTY
numbers shown below are the number of parts necessary for this task.
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See title page for details.

### Page 27

Table 1  
More DataQtyIdentificationNameActionStep
*[1]*[2]--FRONT SPAR BODY
CHORD
Inspect1
*[1]  If access is limited to the front spar body chord, an inspection aid may be used.
*[2]  Do a detailed inspection of the front spar body chord horizontal flange surface between stringer S-26 to stringer S-40, left and right
side, for any crack in accordance with 787-8 SRM 51-00-06.
B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN

### Page 28

Task 3 – FRONT SPAR BODY CHORD UT INSPECTION [Group 1: ]
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
Alert:
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.
B787-81205-SB530076-00 RB
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See title page for details.
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### Page 29 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
Procedure
This Task applies only to: Group 1.
STA 873
BL
S-25R-  - S-25L
FORWARD CARGO COMPARTMENT
(VIEW LOOKING AFT, STA 873)
ICN-B787-A-000061-A-81205-17628-A-01-1
Figure 1
B787-81205-SB530076-00 RB
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### Page 30 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN
FRONT SPAR
• BODY CHORD
UPPER END
FITTING
FRONT SPAR
BODY CHORD
S-27L  UPPER END
FITTING
LOWER END
FITTING
FWD
- S-27L
INBD  LOWER END  FITTING
/ INSPECTION AREA  C  2914067
ICN-B787-A-000061-A-81205-17720-A-01-1
Figure 2
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### Page 31 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN
FRONT SPAI
BODY CHORI
JPPER EN
FITTING
FRONT SPAR
BODY CHORD
S-27R
UPPER END
FITTING
LOWER ENL
FITTING
FWD
S-27R
LOWER END
FITTING  INBD
• INSPECTION AREA
ICN-B787-A-000061-A-81205-17721-A-01-1
Figure 3
1. The step numbers shown below agree with the numbers shown in the circle symbols in the Task. The QTY
numbers shown below are the number of parts necessary for this task.
B787-81205-SB530076-00 RB
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### Page 32

Table 1  
More DataQtyIdentificationNameActionStep
*[1]--FRONT SPAR BODY
CHORD
Inspect1
*[1]  Do an UT inspection of the front spar body chord horizontal flange along the upper and lower edges of the end fittings at stringer S-
27, left and right side, for any crack in accordance with 787 NDT Manual Part 4, 53-20-01 Temporary Revision (TR) 04-1005 dated
Mar 12/2020, or 787 NDT Manual Part 4, 53-20-01 that incorporates 787 NDT Manual Part 4, 53-20-01 TR 04-1005 dated Mar 12/2020
or later Boeing approved revisions.
B787-81205-SB530076-00 RB
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See title page for details.
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REQUIREMENTS BULLETIN

### Page 33

Task 4 – FRONT SPAR BODY CHORD HFEC INSPECTION [Group 2: ]
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
Alert:
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.
B787-81205-SB530076-00 RB
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Page 33 of 42
EXPORT CONTROLLED ECCN: 9E991
See title page for details.
B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN

### Page 34 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
Procedure
This Task applies only to: Group 2.
STA 873
BL
S-25R  - S-25L
FORWARD CARGO COMPARTMENT
(VIEW LOOKING AFT, STA 873)
ICN-B787-A-000061-A-81205-17722-A-01-1
Figure 1
B787-81205-SB530076-00 RB
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### Page 35 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
FRONT SPAR BODY
CHORD SPLICE ANGLE
FRONT SPAR
BODY CHORD
79Z-S
S-25R
• FRONT SPAR
BODY CHORD
\ INSPECTION AREA
ICN-B787-A-000061-A-81205-17723-A-01-1
Figure 2
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### Page 36 (OCR)

_BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
FRONT SPAR  S-40R  S-40L  FRONT SPAR
BODY CHORD  BODY CHORD
SPLICE FITTING
FORWARD CARGO COMPARTMENT
(VIEW LOOKING AFT, STA 873)
• INSPECTION AREA  D  4406
ICN-B787-A-000061-A-81205-17724-A-01-1
Figure 3
1. The step numbers shown below agree with the numbers shown in the circle symbols in the Task. The QTY
numbers shown below are the number of parts necessary for this task.
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### Page 37

Table 1  
More DataQtyIdentificationNameActionStep
*[1]--FRONT SPAR BODY
CHORD
Inspect1
*[2]--FRONT SPAR BODY
CHORD
Inspect2
*[1]  Do a surface HFEC inspection along the entire forward edge of the front spar body chord in the area covered by the body chord splice
angle at stringer S-25, left and right side, for any crack in accordance with 787 NDT Manual Part 6, 53-20-08 Temporary Revision
(TR) 06-1015 dated Feb 24/2020, or 787 NDT Manual Part 6, 53-20-08 that incorporates 787 NDT Manual Part 6, 53-20-08 TR 06-
1015 dated Feb 24/2020 or later Boeing approved revisions.
*[2]  Do a surface HFEC inspection along the entire forward edge of the front spar body chord in the area covered by the front spar body
chord splice fitting at BL0, left and right side, for any crack in accordance with 787 NDT Manual Part 6, 53-20-12 Temporary Revision
(TR) 06-1010 dated Feb 20/2020, or 787 NDT Manual Part 6, 53-20-12 that incorporates 787 NDT Manual Part 6, 53-20-12 TR 06-
1010 dated Feb 20/2020 or later Boeing approved revisions.
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REQUIREMENTS BULLETIN

### Page 38

Task 5 – FRONT SPAR BODY CHORD DETAILED INSPECTION [Group 2:
]
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
Alert:
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.
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REQUIREMENTS BULLETIN

### Page 39 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
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REQUIREMENTS BULLETIN
Procedure
This Task applies only to: Group 2.
STA 873
FORWARD CARGO COMPARTMENT
(VIEW LOOKING AFT, STA 873)
ICN-B787-A-000061-A-81205-17725-A-01-1
Figure 1
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### Page 40 (OCR)

BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
FRONT SPAR
BODY CHORD
SPLICE ANGLE
- S-25L
FRONT SPAR  - S-31L
BODY CHORD
FRONT SPAR BODY
CHORD SPLICE FITTING
STA 873-  - S-40L
* BL O
LEFT SIDE BODY CHORD
35
\ INSPECTION AREA
ICN-B787-A-000061-A-81205-17726-A-01-1
Figure 2
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### Page 41 (OCR)

@ BOEING  B787-81205-SB530076-00 RB
Issue 001, 08 Sep 2020 8:58:27 AM
REQUIREMENTS BULLETIN
FRONT SPAR
BODY CHORD
SPLICE ANGLE
S-25R -
S-31R -  FRONT SPAR
BODY CHORD
FRONT SPAR BODY
CHORD SPLICE FITTING
S-40R -
BL O-  STA 873
RIGHT SIDE BODY CHORD
• INSPECTION AREA
ICN-B787-A-000061-A-81205-17727-A-01-1
Figure 3
1. The step numbers shown below agree with the numbers shown in the circle symbols in the Task. The QTY
numbers shown below are the number of parts necessary for this task.
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EXPORT CONTROLLED ECCN: 9E991
See title page for details.

### Page 42

Table 1  
More DataQtyIdentificationNameActionStep
*[1]*[2]--FRONT SPAR BODY
CHORD
Inspect1
*[1]  If access is limited to the front spar body chord, an inspection aid may be used.
*[2]  Do a detailed inspection of the front spar body chord horizontal flange surface between stringer S-26 to stringer S-40, left and right
side, for any crack in accordance with 787-9 SRM 51-00-06.
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REQUIREMENTS BULLETIN

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