Proposed Rule2024-14608
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
July 3, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, and 747SR series airplanes. This proposed AD was prompted by a report indicating cracks at eight fastener hole locations in the fuselage skin lap splice between certain stations (STAs) at certain stringers. This proposed AD would require repetitive inspections of the upper fastener row of the fuselage skin lap splice in a certain area for any crack, 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 89 Issue 128 (Wednesday, July 3, 2024)</title>
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[Federal Register Volume 89, Number 128 (Wednesday, July 3, 2024)]
[Proposed Rules]
[Pages 55128-55130]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-14608]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-1882; Project Identifier AD-2024-00227-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 747-100, 747-100B, 747-100B SUD,
747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F,
747SP, and 747SR series airplanes. This proposed AD was prompted by a
report indicating cracks at eight fastener hole locations in the
fuselage skin lap splice between certain stations (STAs) at certain
stringers. This proposed AD would require repetitive inspections of the
upper fastener row of the fuselage skin lap splice in a certain area
for any crack, 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 August 19,
2024.
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-2024-1882; or in person at
[[Page 55129]]
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 the material, 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-2024-1882.
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#c89bbcadaea9a6a1ade686e69aa7adbba4a188aea9a9e6afa7be"><span class="__cf_email__" data-cfemail="4a193e2f2c2b24232f64046418252f3926230a2c2b2b642d253c">[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-2024-1882;
Project Identifier AD-2024-00227-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#7b280f1e1d1a15121e55355529141e0817123b1d1a1a551c140d"><span class="__cf_email__" data-cfemail="e7b493828186898e82c9a9c9b58882948b8ea7818686c9808891">[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 has received a report that cracking was found at eight
fastener hole locations in the fuselage skin lap splice between STAs
1450 and 1470 at stringers S-23L and S-23R on a Boeing Model 747-400
series airplane that had completed 128,792 flight hours and 25,581
flight cycles when the cracks were discovered. The maximum crack length
discovered was 0.946 inch. After this report was received, the Boeing
Company did a high frequency eddy current inspection on the Boeing
Model 747-100 fatigue test airplane and found cracks on the countersink
area of the fastener holes on the lap splice between STAs 1416 and 1480
at stringers S-23L and S-23R. The maximum crack length discovered was
0.10 inch. The Boeing Model 747-100 fatigue test airplane had completed
the equivalent of 45,000 flight cycles. Cracking in the fuselage skin
lap splice, if not addressed, could result in an in-flight rapid
decompression and a loss of structural integrity of the fuselage.
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.
Related Material Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 747-53A2912 RB,
dated April 5, 2024. This material specifies procedures for repetitive
external surface high frequency eddy current inspections of the upper
fastener row of the fuselage skin lap splice between STAs 1350 and 1480
at stringers S-23L and S-23R for any crack, and applicable on-condition
actions. On-condition actions include obtaining and following repair
instructions.
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-2024-1882.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 170 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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Inspections...................... 8 work-hours x $85 $0 $680 per inspection $115,600 per
per hour = $680 cycle. inspection cycle
per inspection
cycle.
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The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions specified in this proposed AD.
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.
[[Page 55130]]
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:
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-2024-1882; Project Identifier AD-
2024-00227-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by August 19, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-100, 747-100B,
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, 747SP, and 747SR series airplanes, certificated in
any category, as identified in Boeing Alert Requirements Bulletin
747-53A2912 RB, dated April 5, 2024.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report indicating cracks at eight
fastener hole locations in the fuselage skin lap splice between
stations (STAs) 1450 and 1470 at stringers S-23L and S-23R. The FAA
is issuing this AD to detect and correct cracking of the upper
fastener row of the fuselage skin lap splice between STAs 1350 and
1480 at stringers S-23L and S-23R. The unsafe condition, if not
addressed, could result in an in-flight rapid decompression and a
loss of structural integrity of the fuselage.
(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 747-53A2912 RB, dated April 5, 2024, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
747-53A2912 RB, dated April 5, 2024.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
747-53A2912, dated April 5, 2024, which is referred to in Boeing
Alert Requirements Bulletin 747-53A2912 RB, dated April 5, 2024.
(h) Exceptions to Service Information Specifications
(1) Where the Condition and Boeing Recommended Compliance Time
columns of the tables in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 747-53A2912 RB, dated April 5, 2024,
refer to ``the Original Issue date of the Requirements Bulletin 747-
53A2912 RB,'' this AD requires using the effective date of this AD.
(2) Where Boeing Alert Requirements Bulletin 747-53A2912 RB,
dated April 5, 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
(i) of this AD.
(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#f0b1bdbfb3b0969191de979f86"><span class="__cf_email__" data-cfemail="b2f3fffdf1f2d4d3d39cd5ddc4">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, 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#80d3f4e5e6e1eee9e5aeceaed2efe5f3ece9c0e6e1e1aee7eff6"><span class="__cf_email__" data-cfemail="ffac8b9a999e91969ad1b1d1ad909a8c9396bf999e9ed1989089">[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 (IBR) 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 747-53A2912 RB, dated
April 5, 2024.
(ii) [Reserved]
(3) For Boeing material, 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#e78195c98e8994978284938e8889a789869586c9808891"><span class="__cf_email__" data-cfemail="0d6b7f2364637e7d686e796462634d636c7f6c236a627b">[email protected]</span></a>.
Issued on June 27, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-14608 Filed 7-2-24; 8:45 am]
BILLING CODE 4910-13-P
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