Proposed Rule2025-06061
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
April 10, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This proposed AD was prompted by discovery of a crack at one of the forward lower fastener holes, outside of the underwing longeron (UWL) following replacement of a cracked UWL fitting. This proposed AD would require performing an open hole high frequency eddy current (HFEC) inspection for cracks of the fastener holes common to the UWL fitting, upper drag splice angle, and lower drag splice angle, and applicable on-condition actions. 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 68 (Thursday, April 10, 2025)</title>
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[Federal Register Volume 90, Number 68 (Thursday, April 10, 2025)]
[Proposed Rules]
[Pages 15318-15321]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-06061]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 90, No. 68 / Thursday, April 10, 2025 /
Proposed Rules
[[Page 15318]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0618; Project Identifier AD-2024-00637-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 adopt a new airworthiness directive (AD)
for certain The Boeing Company Model 767-200, -300, -300F, and -400ER
series airplanes. This proposed AD was prompted by discovery of a crack
at one of the forward lower fastener holes, outside of the underwing
longeron (UWL) following replacement of a cracked UWL fitting. This
proposed AD would require performing an open hole high frequency eddy
current (HFEC) inspection for cracks of the fastener holes common to
the UWL fitting, upper drag splice angle, and lower drag splice angle,
and applicable on-condition actions. 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 May 27,
2025.
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-2025-0618; 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 identified 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-2025-0618.
FOR FURTHER INFORMATION CONTACT: Stefanie Roesli, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3964; email: <a href="/cdn-cgi/l/email-protection#6f3c1b0a090e01060a4121413d000a1c03062f090e0e41080019"><span class="__cf_email__" data-cfemail="6c3f18090a0d0205094222423e03091f00052c0a0d0d420b031a">[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 to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2025-0618;
Project Identifier AD-2024-00637-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 this 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 NPRM.
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
Stefanie Roesli, Aviation Safety Engineer, FAA, 2200 South 216th St.,
Des Moines, WA 98198; phone: 206-231-3964; email:
<a href="/cdn-cgi/l/email-protection#8eddfaebe8efe0e7eba0c0a0dce1ebfde2e7cee8efefa0e9e1f8"><span class="__cf_email__" data-cfemail="1447607172757a7d713a5a3a467b7167787d547275753a737b62">[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
During an inspection of the UWL fitting in accordance with Boeing
Service Bulletin 767-57A0126, Revision 5, dated April 7, 2016, an
operator replaced the left side UWL fitting due to a crack found at the
flange radius. Subsequent non-destructive inspection of the removed UWL
fitting revealed a crack at one of the forward lower fastener holes,
outside the inspection area of Service Bulletin 767-57A0126. The crack
was 0.30 inch long and 0.37 inch deep. The airplane had accumulated
80,955 total flight hours and 22,620 total flight cycles at the time of
the report. An analysis of the cracked fitting found that the crack was
caused by fatigue. There is no requirement to inspect the forward lower
fastener holes in Service Bulletin 767-57A026 or in the baseline
fatigue inspection program per the Boeing 767 Maintenance Planning Data
(MPD) Document. A crack in the UWL fitting, if not addressed, could
result in loss of the primary load path between the fuselage
[[Page 15319]]
and the wing box, adversely affecting the structural integrity of the
airplane.
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 Requirements Bulletin 767-57A0148 RB,
dated October 10, 2024. This material specifies procedures for
performing an open hole HFEC inspection for cracks of the fastener
holes common to the UWL fitting, upper drag splice angle, and lower
drag splice angle, and applicable on-condition actions. On-condition
actions include crack repair (e.g., hole oversize repair), an open hole
HFEC inspection of the fitting and angles for any crack at hole
oversize repair locations, an open hole HFEC inspection of the entire
fastener stack-up common to the tension bolt hole and a surface HFEC
inspection of the front spar lower chord for any crack, replacement of
the underwing longeron fitting with new underwing longeron fitting,
underwing longeron fitting hole repair, tension bolt fastener stack-up
repair, front spar lower chord repair, and subsequent repetitive open
hole HFEC inspections for cracks of the fastener holes common to the
UWL fitting, upper drag splice angle, and lower drag splice angle.
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> under Docket No. FAA-2025-0618.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 600 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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HFEC inspection of fastener holes.... 170 work-hours x $85 per $0 $14,450 $8,670,000
hour = $14,450.
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The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of the
proposed inspection. The agency has no way of determining the number of
aircraft that might need these repairs:
On-Condition Costs *
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Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement............................. 19 work-hours x $85 per $15,270 $16,885.
hour = $1,615.
Inspections of the fitting and angles, Up to 6 work-hours x $85 = 0 Up to $510.
the entire fastener stack-up common to Up to $510.
the tension bolt hole, and the front
spar lower chord for any crack.
Repetitive HFEC inspection of fastener 170 work-hours x $85 per 0 $14,450.
holes. hour = $14,450.
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* The FAA has received no definitive data on which to base the cost estimates for time and work for the repairs
specified in this proposed AD, as the work necessary is variable.
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 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 this 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:
[[Page 15320]]
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 adding the following new airworthiness
directive:
The Boeing Company: Docket No. FAA-2025-0618; Project Identifier AD-
2024-00637-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by May 27, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category, as
identified in Boeing Alert Requirements Bulletin 767-57A0148 RB,
dated October 10, 2024.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted discovery of a crack at one of the forward
lower fastener holes, outside of the underwing longeron (UWL)
following replacement of a cracked UWL fitting. The FAA is issuing
this AD to ensure that any crack in the forward lower fastener holes
at the UWL fitting is found and repaired before reaching a critical
length. Such cracking, if not addressed, could result in loss in the
primary load path between the fuselage and the wing box, adversely
affecting the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
767-57A0148 RB, dated October 10, 2024.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
767-57A0148, dated October 10, 2024, which is referred to in Boeing
Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024.
(h) Exceptions to Requirements Bulletin Specifications
(1) Where the Compliance Time column of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 767-
57A0148 RB, dated October 10, 2024, refers to the original issue
date of Requirements Bulletin 767-57A0148 RB, this AD requires using
the effective date of this AD.
(2) Where Boeing Alert Requirements Bulletin 767-57A0148 RB,
dated October 10, 2024, specifies contacting Boeing for repair
instructions: This AD requires doing the repair using a method
approved in accordance with the procedures specified in paragraph
(g) of this AD.
(3) During application of any cap seal to a fastener, fastener
head, and fastener threads and collars, as required by this AD, the
cap seal must be applied with a thickness equal to or greater than
the dimensions specified in figure 1 to paragraph (h)(3) of this AD.
[GRAPHIC] [TIFF OMITTED] TP10AP25.000
(i) 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
(j)(1) of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#c2838f8d8182a4a3a3eca5adb4"><span class="__cf_email__" data-cfemail="13525e5c50537572723d747c65">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector,
[[Page 15321]]
or lacking a principal inspector, the manager of the responsible
Flight Standards Office.
(3) 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.
(j) Related Information
(1) For more information about this AD, contact Stefanie Roesli,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3964; email: <a href="/cdn-cgi/l/email-protection#bdeec9d8dbdcd3d4d893f393efd2d8ced1d4fddbdcdc93dad2cb"><span class="__cf_email__" data-cfemail="edbe99888b8c838488c3a3c3bf82889e8184ad8b8c8cc38a829b">[email protected]</span></a>.
(2) Material identified in this AD that is not incorporated by
reference is available at the address specified in paragraph (k)(3)
this AD.
(k) 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 Requirements Bulletin 767-57A0148 RB, dated
October 10, 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#177165397e7964677274637e7879577976657639707861"><span class="__cf_email__" data-cfemail="a4c2d68acdcad7d4c1c7d0cdcbcae4cac5d6c58ac3cbd2">[email protected]</span></a>.
Issued on April 3, 2025.
Victor Wicklund,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-06061 Filed 4-9-25; 8:45 am]
BILLING CODE 4910-13-P
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