# Boeing Alert Requirements Bulletin 737-53A1371 RB: No revision named

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### Page 1

Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1371 RB
Original Issue: January 19, 2018
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Fuselage Frame Webs at Overwing Emergency
Exits Between Stringer-7 and Stringer-8, Left and Right Side - Inspection
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:
Copyright © 2018 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Unpublished Work.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,
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connection with this document unless provided in writing by Boeing.
Original Issue: January 19, 2018
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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 ................................................. 9
5. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 1
A. General Information ......................................... 1 1
B. Work Instructions ........................................... 1 2
FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE [Group 2, Configuration 1] ............................ 1 6
FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET
INSTALLATION - LEFT SIDE [Group 2, Configuration 2] .................. 2 1
FIGURE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- RIGHT SIDE [Group 2, Configuration 1] ........................... 2 5
FIGURE 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET
INSTALLATION - RIGHT SIDE [Group 2, Configuration 2] .................. 3 0
FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE [Group 3, Configuration 1] ............................ 3 4
FIGURE 6: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET
INSTALLATION - LEFT SIDE [Group 3, Configuration 2] .................. 4 0
FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- RIGHT SIDE [Group 3, Configuration 1] ........................... 4 4
FIGURE 8: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET
INSTALLATION - RIGHT SIDE [Group 3, Configuration 2] .................. 5 0
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET
INSTALLATION - LEFT SIDE [Group 4, Configuration 1] .................. 5 4
FIGURE 10: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT
BRACKET INSTALLATION - LEFT SIDE [Group 4, Configuration 2] ............ 6 2
FIGURE 11: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET
INSTALLATION - RIGHT SIDE [Group 4, Configuration 1] .................. 6 8
FIGURE 12: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME
WEBS AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT
BRACKET INSTALLATION - RIGHT SIDE [Group 4, Configuration 2] ........... 7 6
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Commercial 
Airplanes
737
Requirements Bulletin
ALERT
Number: 737-53A1371 RB
Original Issue: January 19, 2018
ATA System: 5311
SUBJECT: FUSELAGE - Frames and Bulkheads - Fuselage Frame Webs at Overwing Emergency
Exits Between Stringer-7 and Stringer-8, Left and Right Side - Inspection
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
This bulletin is applicable to all 737-100/-200/-200C/-300/-400/-500 airplanes. The Variable Numbers
and Group Information for the applicable airplanes are given below.
DESCRIPTIONCONFIGURATIONGROUP
737-100/-200/-200C airplanes. Line numbers 1-291.-1
737-200/-200C airplanes.-2
737-200/-200C airplanes on which a support bracket between S-7
and S-8 for stowage bins was installed.
1
737-200/-200C airplanes on which a support bracket between S-7
and S-8 for stowage bins was not installed.
2
737-300/-500 airplanes.-3
737-300/-500 airplanes on which a support bracket between S-7 and
S-8 for stowage bins was installed.
1
737-300/-500 airplanes on which a support bracket between S-7 and
S-8 for stowage bins was not installed.
2
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DESCRIPTIONCONFIGURATIONGROUP
737-400 airplanes.-4
737-400 airplanes on which a support bracket between S-7 and S-8
for stowage bins was installed.
1
737-400 airplanes on which a support bracket between S-7 and S-8
for stowage bins was not installed.
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 737-53A1371 RB. The Airworthiness Directive will make the compliance tasks and
times given in Requirements Bulletin 737-53A1371 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 3, in accordance
with the Accomplishment Instructions.
When more than one ACTION is given for a CONDITION number, do all of the ACTION numbers for that
CONDITION number.
Group 1:
The Boeing Company endorses the FAA rules related to Limit of Validity (LOV) and recommends immediate
and permanent removal from service of any airplanes upon reaching the LOV, whether or not it is operated
under FAA jurisdiction. As such, The Boeing Company no longer provides maintenance instructions for
airplanes that have accumulated flight cycles beyond the LOV. Airplanes in Group 1 (line number 1-291)
have accumulated flight cycles beyond the LOV of the maintenance program. 14 CFR 121.1115 and 129.115
prohibit operation of an airplane beyond its LOV.
Group 2:
Table 1: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and
STA 639 Between S-7 and S-8, Left and Right Side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of Requirements
Bulletin 737-
53A1371 RB.
Before 12,000 total
flight cycles.
Do an HFEC inspection of the
fuselage frame webs at STA
616 and STA 639 between S-7
and S-8, left and right side for
any crack. (a)
All airplanes.
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Group 2:
Table 1: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and
STA 639 Between S-7 and S-8, Left and Right Side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company
for repair instructions and do
the repair.
ANY CRACK
FOUND.
6,000 flight cycles.-CONDITION 1 (ACTION 2):
Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
6,000 flight cycles.-Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
CONDITION 2:
NO CRACK
FOUND.
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas
where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed
after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9.
Group 3:
Table 2: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and
STA 639 Between S-7 and S-8, Left and Right Side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of Requirements
Bulletin 737-
53A1371 RB.
Before 12,000 total
flight cycles.
Do an HFEC inspection of the
fuselage frame webs at STA
616 and STA 639 between S-7
and S-8, left and right side for
any crack. (a)
All airplanes.
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Group 3:
Table 2: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and
STA 639 Between S-7 and S-8, Left and Right Side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company
for repair instructions and do
the repair.
ANY CRACK
FOUND.
9,000 flight cycles.-CONDITION 1 (ACTION 2):
Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
9,000 flight cycles.-Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
CONDITION 2:
NO CRACK
FOUND.
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas
where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed
after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9.
Group 4:
Table 3: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 578, STA
601, STA 616 and STA 639 Between S-7 and S-8, Left and Right Side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Within 6,000 flight
cycles after the
original issue date
of Requirements
Bulletin 737-
53A1371 RB.
Before 12,000 total
flight cycles.
Do an HFEC inspection of the
fuselage frame webs at STA
578, STA 601, STA 616 and
STA 639 between S-7 and S-8,
left and right side for any crack.
(a)
All airplanes.
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Group 4:
Table 3: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 578, STA
601, STA 616 and STA 639 Between S-7 and S-8, Left and Right Side
Repeat Interval
(Not to Exceed)
Compliance Time
(Whichever Occurs Later)
ActionCondition
-Before further flight.CONDITION 1 (ACTION 1):CONDITION 1:
Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND.
9,000 flight cycles.-CONDITION 1 (ACTION 2):
Repeat an HFEC inspection of
the fuselage frame webs at STA
578, STA 601, STA 616 and
STA 639 between S-7 and S-8,
left and right side for any crack.
(a)
9,000 flight cycles.-Repeat an HFEC inspection of
the fuselage frame webs at STA
578, STA 601, STA 616 and
STA 639 between S-7 and S-8,
left and right side for any crack.
(a)
CONDITION 2:
NO CRACK
FOUND.
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas
where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed
after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9.
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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5.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
NOTE: 1. 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 737 Structural Repair Manual,
Chapter 51.
– Values for airframe maintenance tasks are included in Chapter 20 of 737
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 737
Aircraft Maintenance Manual (AMM).
– Non-standard torque values for maintenance tasks are included in the
applicable installation step.
2. 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.
3. Boeing Service Letter 737-SL-51-042, 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.
4. The instructions in 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.
5. 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.
6. When more than one ACTION is given for a CONDITION number, do all of the
ACTION numbers for that CONDITION number.
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7. 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.
8. 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.
9. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
B. WORK INSTRUCTIONS
Actions Required for Compliance:
1. Requirements
Group 1:
The Boeing Company endorses the FAA rules related to Limit of Validity (LOV) and recommends
immediate and permanent removal from service of any airplanes upon reaching the LOV, whether
or not it is operated under FAA jurisdiction. As such, The Boeing Company no longer provides
maintenance instructions for airplanes that have accumulated flight cycles beyond the LOV.
Airplanes in Group 1 (line number 1-291) have accumulated flight cycles beyond the LOV of the
maintenance program. 14 CFR 121.1115 and 129.115 prohibit operation of an airplane beyond
its LOV.
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### Page 13

Group 2:
Table 1: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and
STA 639 Between S-7 and S-8, Left and Right Side
Refer to the listed
procedures in SB
737-53A1371 Origi-
nal Issue or later
approved revi-
sions as an accept-
ed procedure:
Method of ComplianceActionCondition
PART 1:-Do an HFEC inspection of the
fuselage frame webs at STA
616 and STA 639 between S-7
and S-8, left and right side for
any crack. (a)
All airplanes.
GET ACCESS.
-FIGURE 1 AND
FIGURE 3
Group 2,
Configuration 1
-FIGURE 2 ANDGroup 2,
FIGURE 4Configuration 2
PART 2:-CONDITION 1 (ACTION 1):CONDITION 1:
CLOSE ACCESS.Contact The Boeing Company
for repair instructions and do
the repair.
ANY CRACK
FOUND.
PART 1:-CONDITION 1 (ACTION 2):
GET ACCESS.Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
-FIGURE 1 AND
FIGURE 3
Group 2,
Configuration 1
-FIGURE 2 ANDGroup 2,
FIGURE 4Configuration 2
PART 2:--CONDITION 2:
CLOSE ACCESS.NO CRACK
FOUND. PART 1:-Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
GET ACCESS.
-FIGURE 1 AND
FIGURE 3
Group 2,
Configuration 1
-FIGURE 2 ANDGroup 2,
FIGURE 4Configuration 2
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas
where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed
after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9.
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### Page 14

Group 3:
Table 2: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 616 and
STA 639 Between S-7 and S-8, Left and Right Side
Refer to the listed
procedures in SB
737-53A1371 Origi-
nal Issue or later
approved revi-
sions as an accept-
ed procedure:
Method of ComplianceActionCondition
PART 1:-Do an HFEC inspection of the
fuselage frame webs at STA
616 and STA 639 between S-7
and S-8, left and right side for
any crack. (a)
All airplanes.
GET ACCESS.
-FIGURE 5 AND
FIGURE 7
Group 3,
Configuration 1
-FIGURE 6 ANDGroup 3,
FIGURE 8Configuration 2
PART 2:-CONDITION 1 (ACTION 1):CONDITION 1:
CLOSE ACCESS.Contact The Boeing Company
for repair instructions and do
the repair.
ANY CRACK
FOUND.
PART 1:-CONDITION 1 (ACTION 2):
GET ACCESS.Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
-FIGURE 5 AND
FIGURE 7
Group 3,
Configuration 1
-FIGURE 6 ANDGroup 3,
FIGURE 8Configuration 2
PART 2:--CONDITION 2:
CLOSE ACCESS.NO CRACK
FOUND. PART 1:-Repeat an HFEC inspection of
the fuselage frame webs at
STA 616 and STA 639 between
S-7 and S-8, left and right side
for any crack. (a)
GET ACCESS.
-FIGURE 5 AND
FIGURE 7
Group 3,
Configuration 1
-FIGURE 6 ANDGroup 3,
FIGURE 8Configuration 2
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas
where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed
after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9.
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### Page 15

Group 4:
Table 3: High Frequency Eddy Current (HFEC) Inspection of the Fuselage Frame Webs at STA 578, STA
601, STA 616 and STA 639 Between S-7 and S-8, Left and Right Side
Refer to the listed
procedures in SB
737-53A1371 Origi-
nal Issue or later
approved revisions
as an accepted pro-
cedure:
Method of ComplianceActionCondition
PART 1:-Do an HFEC inspection of the
fuselage frame webs at STA
578, STA 601, STA 616 and
STA 639 between S-7 and S-8,
left and right side for any crack.
(a)
All airplanes.
GET ACCESS.
-FIGURE 9 AND
FIGURE 11
Group 4,
Configuration 1
-FIGURE 10 ANDGroup 4,
FIGURE 12Configuration 2
PART 2:-CONDITION 1 (ACTION 1):CONDITION 1:
CLOSE ACCESS.Contact The Boeing Company
for repair instructions and do the
repair.
ANY CRACK
FOUND.
PART 1:-CONDITION 1 (ACTION 2):
GET ACCESS.Repeat an HFEC inspection of
the fuselage frame webs at STA
578, STA 601, STA 616 and
STA 639 between S-7 and S-8,
left and right side for any crack.
(a)
-FIGURE 9 AND
FIGURE 11
Group 4,
Configuration 1
-FIGURE 10 AND
FIGURE 12
Group 4,
Configuration 2
PART 2:--CONDITION 2:
CLOSE ACCESS.NO CRACK
FOUND. PART 1:-Repeat an HFEC inspection of
the fuselage frame webs at STA
578, STA 601, STA 616 and
STA 639 between S-7 and S-8,
left and right side for any crack.
(a)
GET ACCESS.
-FIGURE 9 AND
FIGURE 11
Group 4,
Configuration 1
-FIGURE 10 ANDGroup 4,
FIGURE 12Configuration 2
(a) It is not required to do the inspections in accordance with Requirements Bulletin 737-53A1371 RB in areas
where an existing repair covers the inspection area and meets the following criteria:
1. The repair is the corrective action to the crack condition identified in this bulletin and installed
after the original issue date of requirements bulletin 737-53A1371 RB.
AND
2. The repair was approved by the Boeing Organization Designation Authorization (ODA) via an
FAA Form 8100-9.
Export Controlled ECCN: 9E991
Copyright © Unpublished
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Original Issue: January 19, 2018
737-53A1371 RB
15 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 16 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 1.
S-7L
S-8L
D
- S-9L
OVERWING
EMERGENCY
EXIT
STA 616
STA 639  2748963
FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 1 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  16 of 81

### Page 17 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
S-8L
SHEAR TIE
•BRACKET
STA 616
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2752629
FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 2 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  17 of 81

### Page 18 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
FRAME  BRACKET
STA
616
SHEAR TIE  D
B-B
SHEAR TIE
0.1
(MINIMUM)  S-8L
FRAME
BRACKET-
NBD
STA 616
HFEC INSPECTION  VIEW LOOKING AFT  C-C  2767997
FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 3 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  18 of 81

### Page 19 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
S-8L
SHEAR TIE
STA 639
VIEW LOOKING AFT
D-D
HFEC INSPECTION
2768011
FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 4 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  19 of 81

### Page 20

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(b)--Fuselage frame webInspect2
(c)--Fuselage frame webInspect3
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(b) Do an HFEC inspection of the fuselage frame web along the outboard edge of the bracket for any crack
in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(c) Do an HFEC inspection of the fuselage frame web along the edge of the shear tie for any crack in accor-
dance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 1: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
20 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 21 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 2.
S-7L
_S-8L
_ S-9L
OVERWING
EMERGENCY-
EXIT
STA 616
STA 639  2768015
FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 1 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  21 of 81

### Page 22 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
SHEAR TIE
INED
STA 616
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2768016
FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 2 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  22 of 81

### Page 23 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
S-8L
SHEAR TIE
STA 639
VIEW LOOKING AFT
B-B
HFEC INSPECTION
2768020
FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 3 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  23 of 81

### Page 24

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 2: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
24 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 25 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 1.
S-9R
OVERWING
EMERGENCY
EXIT
STA 616
STA 639  2768024
FIGURE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 1 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  25 of 81

### Page 26 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
S-8R
SHEAR TIE
BRACKET
STA 616
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2775395
FIGURE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 2 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  26 of 81

### Page 27 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
BRACKET  _FRAME
STA
616
SHEAR TIE
B-B
SHEAR TIE
S-8R  (MINIMUM)
• FRAME
• BRACKET
NBD
STA 616
HFEC INSPECTION  VIEW LOOKING AFT  C-C  2775399
FIGURE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 3 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  27 of 81

### Page 28 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
SHEAR TIE
NBD
STA 639
VIEW LOOKING AFT
D-D
HFEC INSPECTION
2775403
FIGURE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 4 OF 5)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  28 of 81

### Page 29

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(b)--Fuselage frame webInspect2
(c)--Fuselage frame webInspect3
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(b) Do an HFEC inspection of the fuselage frame web along the outboard edge of the bracket for any crack
in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(c) Do an HFEC inspection of the fuselage frame web along the edge of the shear tie for any crack in accor-
dance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 3: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 5 OF 5)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
29 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 30 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 2, Configuration 2.
S-TR
S-8R
S-9R
OVERWING
EMERGENCY
EXIT
STA 616
STA 639  2775405
FIGURE 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 1 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  30 of 81

### Page 31 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
S-8R
SHEAR TIE
STA 616
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2775411
FIGURE 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 2 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  31 of 81

### Page 32 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
S-8R
SHEAR TIE
NBD
STA 639
VIEW LOOKING AFT
B-B
HFEC INSPECTION
2775412
FIGURE 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 3 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  32 of 81

### Page 33

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 4: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
33 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 34 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 3, Configuration 1.
S-7L
S-BL
- S-9L
OVERWING
EMERGENCY
EXIT
STA 616
STA 639  2775413
FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 1 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  34 of 81

### Page 35 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
STRAP
SHEAR TIE
-BRACKET
INBD
STA 616
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2775414
FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 2 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  35 of 81

### Page 36 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
FRAME  BRACKET
STA
616
SHEAR TIE  D  STRAP
B-B
SHEAR TIE
FRAME
(MININ  S-8L
STRAP
BRACKET-
NBD
STA 616
HFEC INSPECTION  VIEW LOOKING AFT  C-C  2775415
FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 3 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  36 of 81

### Page 37 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
STRAP
SHEAR TIE
S-8
BRACKET -
STA 639
VIEW LOOKING AFT
D-D
VIII HFEC INSPECTION
2775420
FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 4 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  37 of 81

### Page 38 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
BRACKET  _ FRAME
— STA
639
STRAp  SHEAR TIE
E-E
SHEAR TIE
FRAME
MINIMUM)
- STRAP
- BRACKET
INBD
STA 639
HFEC INSPECTION  VIEW LOOKING FORWARD  F-F  2775441
FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 5 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  38 of 81

### Page 39

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(b)--Fuselage frame webInspect2
(c)--Fuselage frame webInspect3
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(b) Do an HFEC inspection of the fuselage frame web along the outboard edge of the bracket for any crack
in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(c) Do an HFEC inspection of the fuselage frame web along the edge of the shear tie for any crack in accor-
dance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 5: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - LEFT SIDE
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
39 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 40 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 3, Configuration 2.
S-7L
S-8L
_S-9L
OVERWING
EMERGENCY
EXIT
STA 616
STA 639  2775446
FIGURE 6: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 1 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  40 of 81

### Page 41 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
*STRAP
S-81
SHEAR TIE
INBD
STA 616
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2775449
FIGURE 6: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 2 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  41 of 81

### Page 42 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
STRAP
S-8L
SHEAR TIE
STA 639
VIEW LOOKING AFT
B-B
HFEC INSPECTION
2775452
FIGURE 6: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 3 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  42 of 81

### Page 43

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 6: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - LEFT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
43 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 44 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 3, Configuration 1.
S-8R
S-9F -
OVERWING
• EMERGENCY
EXIT
STA 616
STA 639  2775456
FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 1 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
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### Page 45 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
B
SHEAR TIE
_S-8R
BRACKET
STA 616
VIEW LOOKING FORWARD
A-A
VIII HFEC INSPECTION
2775458
FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 2 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  45 of 81

### Page 46 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
BRACKET  FRAME
STA
616
STRAP  SHEAR TIE
B-B
SHEAR TIE
FRAME
S-8R  MINIMUM)
- STRAP
• BRACKET
INBD
STA 616
VIEW LOOKING AFT
HFEC INSPECTION  C-C  2775461
FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 3 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
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### Page 47 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
"STRAP
S-8R  SHEAR TIE
— BRACKET
NBD
STA 639
VIEW LOOKING AFT
D-D
HFEC INSPECTION
2775693
FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 4 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  47 of 81

### Page 48 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
FRAME  BRACKET
STA.
639
SHEAR TIE  STRAP
E-E
SHEAR TIE
FRAME
(MINIMUM)  S-8R
STRAP
BRACKET-
INBD
STA 639
HFEC INSPECTION  VIEW LOOKING FORWARD  F-F  2775698
FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 5 OF 6)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  48 of 81

### Page 49

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(b)--Fuselage frame webInspect2
(c)--Fuselage frame webInspect3
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(b) Do an HFEC inspection of the fuselage frame web along the outboard edge of the bracket for any crack
in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
(c) Do an HFEC inspection of the fuselage frame web along the edge of the shear tie for any crack in accor-
dance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 7: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION - RIGHT SIDE
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
49 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 50 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 3, Configuration 2.
S-8R
S-9R
OVERWING
EMERGENCY
EXIT
STA 616
STA 639  2775703
FIGURE 8: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 1 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  50 of 81

### Page 51 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
STRAP
S-8R
SHEAR TIE
STA 616
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2775704
FIGURE 8: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 2 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  51 of 81

### Page 52 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7R
FRAME
STRAP
SHEAR TIE
STA 639
VIEW LOOKING AFT
B-B
HFEC INSPECTION
2775705
FIGURE 8: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 3 OF 4)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  52 of 81

### Page 53

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.
More DataQtyIdentificationNameTaskStep
(a)--Fuselage frame webInspect1
(a) Do an HFEC inspection of the fuselage frame web around the indicated fasteners common to the shear
tie for any crack in accordance with 737 NDT Manual Part 6, 51-00-00 Procedure 4 or Procedure 23.
FIGURE 8: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITHOUT BRACKET INSTALLATION - RIGHT SIDE
(SHEET 4 OF 4)
Export Controlled ECCN: 9E991
Copyright © Unpublished
Work - See page 1 for details.
Original Issue: January 19, 2018
737-53A1371 RB
53 of 81
REQUIREMENTS BULLETIN 737-53A1371
ALERTALERT

### Page 54 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
This Figure applies only to: Group 4, Configuration 1.
—S-7L
S-8L
B
_ S-9L
G
OVERWING
EMERGENCY
EXIT
STA
578
STA
601
STA
616
STA  2775710
639
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE
(SHEET 1 OF 8)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  54 of 81

### Page 55 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
*STRAP
S-8I
SHEAR TIE
NBC
STA 578
VIEW LOOKING FORWARD
A-A
HFEC INSPECTION
2775719
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE
(SHEET 2 OF 8)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  55 of 81

### Page 56 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
STRAP
S-8L
SHEAR TIE
BRACKET
STA 601
VIEW LOOKING AFT
B-B
HFEC INSPECTION
2775723
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE
(SHEET 3 OF 8)
Original issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  56 of 81

### Page 57 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT
_FRAME
STA
601
SHEAR TIE
C-C
SHEAR TIE
FRAME
S-8L
- STRAP
• BRACKET
INBD
STA 601
| HFEC INSPECTION  VIEW LOOKING FORWARD  D-D  2775731
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE
(SHEET 4 OF 8)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  737-53A1371 RB
Copyright © Unpublished
Work - See page 1 for details.  57 of 81

### Page 58 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
*STRAP
SHEAR TIE
BRACKET
STA 616
VIEW LOOKING FORWARD
E-E
HFEC INSPECTION
2775744
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE
(SHEET 5 OF 8)
Original issue: January 19, 2018
Export Controlled ECCN: 9E991  Work - See page 1 for details.  Copyright © Unpublished  737-53A1371 RB  58 of 81

### Page 59 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
FRAME  BRACKET
STA _
616
SHEAR TIE  * STRAP
F-F
SHEAR TIE
FRAME
S-8L
STRAP
BRACKET -
INBD
STA 616
VIEW LOOKING AFT
HFEC INSPECTION  G-G  2775896
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE
(SHEET 6 OF 8)
Original Issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  59 of 81

### Page 60 (OCR)

REQUIREMENTS BULLETIN 737-53A1371
ALERT  ALERT
S-7L
FRAME
STRAP
S-8L
SHEAR TIE
STA 639
VIEW LOOKING AFT
H-H
HFEC INSPECTION
2775912
FIGURE 9: HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE FUSELAGE FRAME WEBS
AT STA 578, STA 601, STA 616 AND STA 639 BETWEEN S-7 AND S-8 WITH BRACKET INSTALLATION
- LEFT SIDE
(SHEET 7 OF 8)
Original issue: January 19, 2018
Export Controlled ECCN: 9E991  Copyright © Unpublished  737-53A1371 RB
Work - See page 1 for details.  60 of 81

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