Proposed Rule2025-20061
Airworthiness Directives; The Boeing Company Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
November 18, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2017-19-26, which applies to certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. AD 2017-19-26 requires repetitive inspections for cracks along the chem-milled steps of the fuselage skin and missing or loose fasteners in the area of the preventive modification or repairs; replacement of the time-limited repair with a permanent repair, if applicable; and applicable corrective actions that end certain repetitive inspections. AD 2017-19- 26 also requires repetitive inspections for modified airplanes. Since the FAA issued AD 2017-19-26, the FAA has determined that the compliance times are not adequate. This proposed AD would continue to require certain actions in AD 2017-19-26 but at reduced compliance times. This proposed AD would also revise instructions for the preventative modification and remove instructions for the permanent and time-limited repairs. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 90 Issue 220 (Tuesday, November 18, 2025)</title>
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[Federal Register Volume 90, Number 220 (Tuesday, November 18, 2025)]
[Proposed Rules]
[Pages 51592-51596]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-20061]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-3429; Project Identifier AD-2024-00722-T]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2017-19-26, which applies to certain The Boeing Company Model 737-600,
-700, -700C, -800, and -900 series airplanes. AD 2017-19-26 requires
repetitive inspections for cracks along the chem-milled steps of the
fuselage skin and missing or loose fasteners in the area of the
preventive modification or repairs; replacement of the time-limited
repair with a permanent repair, if applicable; and applicable
corrective actions that end certain repetitive inspections. AD 2017-19-
26 also requires repetitive inspections for modified airplanes. Since
the FAA issued AD 2017-19-26, the FAA has determined that the
compliance times are not adequate. This proposed AD would continue to
require certain actions in AD 2017-19-26 but at reduced compliance
times. This proposed AD would also revise instructions for the
preventative modification and remove instructions
[[Page 51593]]
for the permanent and time-limited repairs. The FAA is proposing this
AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by January 2,
2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-3429; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this NPRM, any comments received, and other
information. The street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For Boeing material in this proposed AD, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110 SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; website <a href="http://myboeingfleet.com">myboeingfleet.com</a>.
<bullet> You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call 206-231-3195. It is also available at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2025-3429.
FOR FURTHER INFORMATION CONTACT: Luis Cortez-Muniz, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3958; email: <a href="/cdn-cgi/l/email-protection#1f736a766c317e317c706d6b7a6532726a7176655f797e7e31787069"><span class="__cf_email__" data-cfemail="aec2dbc7dd80cf80cdc1dcdacbd483c3dbc0c7d4eec8cfcf80c9c1d8">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under the ADDRESSES section. Include ``Docket No. FAA-2025-3429;
Project Identifier AD-2024-00722-T'' at the beginning of your comments.
The most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. The FAA will consider all comments received by the closing date
and may amend the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this proposed AD.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Luis
Cortez-Muniz, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 206-231-3958; email: <a href="/cdn-cgi/l/email-protection#fd9188948ed39cd39e928f899887d09088939487bd9b9c9cd39a928b"><span class="__cf_email__" data-cfemail="563a233f2578377835392422332c7b3b23383f2c1630373778313920">[email protected]</span></a>. Any commentary that the FAA receives that is not
specifically designated as CBI will be placed in the public docket for
this rulemaking.
Background
The FAA issued AD 2017-19-26, Amendment 39-19056 (82 FR 44504,
September 25, 2017) (AD 2017-19-26), for The Boeing Company Model 737-
600, -700, -700C, -800, and -900 series airplanes with certain line
numbers. AD 2017-19-26 was prompted by a fatigue test that revealed
numerous cracks in the upper skin panel at the chem-milled step above
the lap joint, followed by an evaluation by the design approval holder
(DAH) that indicated that the upper skin panel at the chem-milled step
above the lap joint is subject to widespread fatigue damage (WFD) if
the preventative modification was installed after 30,000 total flight
cycles. AD 2017-19-26 requires repetitive inspections for cracks along
the chem-milled steps of the fuselage skin and missing or loose
fasteners in the area of the preventive modification or repairs;
replacement of the time-limited repair with a permanent repair, if
applicable; and applicable corrective actions which would end certain
repetitive inspections. AD 2017-19-26 also requires repetitive
inspections for modified airplanes. The FAA issued AD 2017-19-26 to
detect and correct cracking of the upper skin panel at the chem-milled
step above the lap joint, which could result in reduced structural
integrity of the airplane.
Actions Since AD 2017-19-26 Was Issued
Since the FAA issued AD 2017-19-26, the FAA received reports of
five chemically milled skin cracks in an area just above the S-4 lap
joint on airplanes with 38,000 and 53,000 total flight cycles. One of
the cracks was found before the airplane reached the next repeat
interval specified in Boeing Alert Service Bulletin 737-53A1232,
Revision 3, dated July 27, 2015. As a result of these findings, the FAA
has determined that reduced inspection intervals for the chem-mill
areas and post-modification inspections (for airplanes on which the
optional preventative modification is accomplished), as well as revised
instructions for the preventative modification and removal of the
instructions for the permanent and time-limited repairs, are now
necessary to address the unsafe condition.
In addition, the FAA has determined that the end-level effect for
the unsafe condition is rapid decompression of the airplane. The FAA
has revised this NPRM accordingly.
The FAA is considering superseding similar ADs for Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes common to different
locations, which have crown skin panels that are of a similar design as
those on Model 737-600, -700, -700C, -800, and -900 series airplanes
addressed by this proposed AD and may be subject to the same unsafe
condition.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Boeing Alert Service Bulletin 737-53A1232,
Revision 4, dated May 22, 2024. This material specifies procedures for
repetitive external detailed inspections and either (1) external medium
frequency eddy
[[Page 51594]]
current (MFEC), magneto optic imager (MOI), or C-scan inspections or
(2) external ultrasonic phased array (UTPA) inspections for cracks in
the fuselage skin at chem-milled steps and pockets at certain
locations, and repairing any cracks, as well as repetitive post-
permanent repair inspections, and post-time-limited repair inspections.
This material specifies that accomplishment of the preventative
modification terminates the repetitive inspections. The preventative
modification includes an external eddy current inspection of the skin
and fastener holes for any crack and installation of a doubler. This
material is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
Proposed AD Requirements in This NPRM
This proposed AD would require accomplishing the actions specified
in the material already described, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
For information on the procedures and compliance times, see this
material at <a href="http://regulations.gov">regulations.gov</a> by searching for and locating Docket No.
FAA-2025-3429.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 307 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspections............... Up to 25 work-hours x $85 $0 Up to $2,125 per Up to $652,375 per
per hour = $2,125 per inspection cycle. inspection cycle.
inspection cycle.
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Estimated Costs for Optional Actions
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Action Labor cost Parts cost Cost per product
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Preventative Modification.......... Up to 956 work-hours x $85 Minimal................ $81,260.
per hour = $81,260.
Post-modification inspections...... Up to 92 work-hours x $85 $0..................... 7,820 per inspection
per hour = $7,820 per cycle.
inspection cycle.
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The extent of cracking found during the inspections could vary
significantly from airplane to airplane. The FAA has no way of
determining which conditions may be found on each airplane, the cost to
correct or repair each airplane, or the number of airplanes that may
require repair.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA has determined that this proposed AD would not have
federalism implications under Executive Order 13132. This proposed AD
would not have a substantial direct effect on the States, on the
relationship between the national government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-19-26, Amendment 39-19056
(82 FR 44504, September 25, 2017), and
0
b. Adding the following new AD:
The Boeing Company: Docket No. FAA-2025-3429; Project Identifier AD-
2024-00722-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 2, 2026.
(b) Affected ADs
This AD replaces AD 2017-19-26, Amendment 39-19056 (82 FR 44504,
September 25, 2017) (AD 2017-19-26).
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, and -900 series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin 737-53A1232, Revision
4, dated May 22, 2024.
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST00830SE
is installed, a ``change in product'' alternative method of
compliance (AMOC) approval request is not necessary to comply with
the requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
[[Page 51595]]
(e) Unsafe Condition
This AD was prompted by a fatigue test that revealed numerous
cracks in the upper skin panel at the chem-milled step above the lap
joint, followed by an evaluation by the design approval holder (DAH)
that indicated that location is subject to widespread fatigue damage
(WFD) on airplanes on which the preventative modification was
installed after 30,000 total flight cycles, and by reports of
fuselage fatigue cracks just above the S-4 lap joint. The FAA is
issuing this AD to detect and correct fatigue cracking of the upper
skin panel at the chem-milled step above the lap joint. The unsafe
condition, if not addressed, could result in rapid decompression of
the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections of the Upper Skin Panel at Chem-Milled Steps and
Pockets
At the applicable times specified in tables 1, 2, and 3 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1232, Revision 4, dated May 22, 2024, except as required by
paragraph (h) of this AD: Do an external detailed inspection and an
external nondestructive inspection (a medium frequency eddy current
(MFEC), magneto optic imager (MOI), C-scan, or ultrasonic phased
array (UTPA) inspection) for any crack in the fuselage skin at the
chem-milled steps, post-permanent repair inspections, and post-time-
limited repair inspections, at certain locations specified in, and
in accordance with, paragraphs 3.B.1, 3.B.3., and 3.B.4, as
applicable, of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1232, Revision 4, dated May 22, 2024. Repeat
the inspections thereafter at the applicable time specified in
tables 1, 2, and 3 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1232, Revision 4, dated May 22, 2024.
(h) Exceptions to Service Information Specifications
(1) Where ACTION 2 of Part IV and ACTION 2 of Part VII of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1232, Revision 4, dated May 22, 2024, specifies to contact Boeing
for work instructions or replacement instructions, this AD requires
doing the instructions using a method approved in accordance with
the procedures specified in paragraph (n) of this AD.
(2) Where the Compliance Time column in the tables under the
``Compliance'' paragraph of Boeing Alert Service Bulletin 737-
53A1232, Revision 4, dated May 22, 2024, refers to the Revision 4
date of this service bulletin, this AD requires using the effective
date of this AD.
(3) For airplanes on which the actions specified in paragraph
(g) of this AD are required: Inspections specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1232, Revision 4, dated May 22, 2024, are not required in
areas that are spanned by an FAA-approved repair that has a minimum
of 3 rows of fasteners above and below the chem-milled step,
provided that the repair was installed before October 30, 2017 (the
effective date of AD 2017-19-26). Operators must accomplish post-
repair inspections at the applicable time specified in table 2 of
paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 737-
53A1232, Revision 4, dated May 22, 2024, except as required by
paragraph (h)(5) of this AD.
(4) For any airplane that has an external doubler covering the
chem-milled step, but the doubler does not span the step by a
minimum of 3 rows of fasteners above and below the chem-milled step
and the doubler was installed before October 30, 2017 (the effective
date of AD 2017-19-26): One method of compliance with the inspection
requirement of paragraph (g) of this AD for the inspections
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1232, Revision 4, dated May 22, 2024,
is to inspect all chem-milled steps covered by the repair using non-
destructive test (NDT) methods approved in accordance with the
procedures specified in paragraph (n) of this AD. These repairs are
to be considered time-limited and are subject to the post-repair
supplemental inspections and replacement at the times specified in
table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1232, Revision 4, dated May 22, 2024, except as
required by paragraph (h)(5) of this AD.
Note 1 to paragraph (h)(4): Guidance for the procedures for the
alternative inspection specified in paragraph (h)(4) of this AD can
be found in the Boeing 737 NDT Manual, Part 6, Subject 53-30-20.
(5) For airplanes on which Supplemental Type Certificate (STC)
ST01697SE has been incorporated, all initial compliance times
(thresholds) specified in flight cycles must be reduced to \1/2\ and
all repeat interval compliance times specified in flight cycles must
be reduced to \1/4\ of those specified in Boeing Alert Service
Bulletin 737-53A1232, Revision 4, dated May 22, 2024.
(i) Repair
If any cracking is found during any inspection required by
paragraph (g) or (h) of this AD, before further flight, repair the
cracking using a method approved in accordance with the procedures
specified in paragraph (n) of this AD.
(j) Additional Actions for Modified Airplanes
For airplanes which have installed STC ST01697SE and the
preventive modification has been installed after 15,000 total flight
cycles: Before the accumulation of 25,000 total flight cycles, do
all applicable investigative and corrective actions using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD.
(k) Optional Terminating Action
For airplanes that have accumulated 30,000 total flight cycles
or fewer, or for airplanes on which STC ST0l697SE was installed and
that have accumulated 15,000 total flight cycles or fewer:
Accomplishment of the actions in paragraphs (k)(1) through (3) of
this AD terminates the repetitive inspections required by paragraph
(g) of this AD that are specified in table 1 of paragraph 1.E.,
Compliance, of Boeing Alert Service Bulletin 737-53A1232, Revision
4, dated May 22, 2024, for the modified area only.
(1) Do the preventive modification, including inspections for
cracking, specified in Part V of Boeing Alert Service Bulletin 737-
53A1232, Revision 4, dated May 22, 2024.
(2) If any cracking is found during any inspection required by
paragraph (k)(1) or (3) of this AD, before further flight, repair
the cracking found using a method approved in accordance with the
procedures specified in paragraph (n) of this AD.
(3) Do the post-modification repetitive inspections specified in
table 1a and table 1b of paragraph 1.E., Compliance, and in
accordance with Part VII of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1232, Revision 4, dated May 22,
2024, except as required by paragraphs (h)(1) and (2) of this AD.
The inspections must be performed and repeated at the applicable
times specified in table 1a and table 1b of paragraph 1.E.,
Compliance, of Boeing Alert Service Bulletin 737-53A1232, Revision
4, dated May 22, 2024. For airplanes on which STC ST01697SE has been
incorporated, all initial compliance times (thresholds) specified in
flight cycles must be reduced to \1/2\ and all repeat interval
compliance times specified in flight cycles must be reduced to \1/4\
of those specified in Boeing Alert Service Bulletin 737-53A1232,
Revision 4, dated May 22, 2024.
(l) Installation Limitations of Preventive Modification
As of October 30, 2017 (the effective date of AD 2017-19-26),
installation of the preventive modification specified in Boeing
Service Bulletin 737-53A1232 is prohibited on the airplanes
identified in paragraphs (l)(1) and (2) of this AD.
(1) Airplanes that have accumulated more than 30,000 total
flight cycles.
(2) Airplanes which have installed STC ST01697SE and that have
accumulated more than 15,000 total flight cycles.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the optional actions in
paragraph (k)(1) of this AD, if those actions were performed before
the effective date of this AD using Boeing Alert Service Bulletin
737-53A1232, Revision 3, dated July 27, 2015.
(2) This paragraph provides credit for the optional actions in
paragraph (k) of this AD, if those actions were performed before
October 30, 2017 (the effective date of AD 2017-19-26) using the
service information identified in paragraph (m)(2)(i) through (iii)
of this AD.
(i) Boeing Special Attention Service Bulletin 737-53A1232, dated
April 2, 2007.
(ii) Boeing Special Attention Service Bulletin 737-53A1232,
Revision 1, dated May 18, 2012.
(iii) Boeing Special Attention Service Bulletin 737-53A1232,
Revision 2, dated July 26, 2013.
[[Page 51596]]
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, AIR-520, Continued Operational Safety Branch,
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or
responsible Flight Standards Office, as appropriate. If sending
information directly to the manager of the certification office,
send it to the attention of the person identified in paragraph
(o)(1) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#0f4e42404c4f696e6e21686079"><span class="__cf_email__" data-cfemail="3a7b7775797a5c5b5b145d554c">[email protected]</span></a>.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
responsible Flight Standards Office.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, AIR-
520, Continued Operational Safety Branch, FAA, to make those
findings. To be approved, the repair method, modification deviation,
or alteration deviation must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.
(3) AMOCs approved for AD 2017-19-26 are not approved as AMOCs
for the corresponding provisions of this AD.
(o) Related Information
(1) For more information about this AD, contact Luis Cortez-
Muniz, Aviation Safety Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 206-231-3958; email: <a href="/cdn-cgi/l/email-protection#d3bfa6baa0fdb2fdb0bca1a7b6a9febea6bdbaa993b5b2b2fdb4bca5"><span class="__cf_email__" data-cfemail="93ffe6fae0bdf2bdf0fce1e7f6e9befee6fdfae9d3f5f2f2bdf4fce5">[email protected]</span></a>.
(2) Material identified in this AD that is not incorporated by
reference is available at the address specified in paragraph (p)(3)
of this AD.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737-53A1232, Revision 4, dated
May 22, 2024.
(ii) [Reserved]
(3) For Boeing material identified in this AD, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; website <a href="http://myboeingfleet.com">myboeingfleet.com</a>.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St.,
Des Moines, WA. For information on the availability of this material
at the FAA, call 206-231-3195.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#d7b1a5f9beb9a4a7b2b4a3beb8b997b9b6a5b6f9b0b8a1"><span class="__cf_email__" data-cfemail="e88e9ac681869b988d8b9c818786a886899a89c68f879e">[email protected]</span></a>.
Issued on October 3, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-20061 Filed 11-17-25; 8:45 am]
BILLING CODE 4910-13-P
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