Airworthiness Directives; The Boeing Company Airplanes, 97494-97497 [2024-28782]
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97494
Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations
(i) No Reporting Requirement
Although the material referenced in EASA
AD 2024–0049 specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
(j) Additional AD Provisions
(k) Additional Information
For more information about this AD,
contact Shahram Daneshmandi, Aviation
Safety Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
206–231–3220; email
shahram.daneshmandi@faa.gov.
ddrumheller on DSK120RN23PROD with RULES1
(l) 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 this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2024–0049, dated February 20,
2024.
(ii) [Reserved]
(3) For EASA AD 2024–0049, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; website
easa.europa.eu. You may find this EASA AD
on the EASA website at ad.easa.europa.eu.
(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 www.archives.gov/federal-register/cfr/
ibr-locationsoremailfr.inspection@nara.gov.
15:13 Dec 06, 2024
[FR Doc. 2024–28787 Filed 12–6–24; 8:45 am]
BILLING CODE 4910–13–P
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Validation 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 International Validation
Branch, mail it to the address identified in
paragraph (k) of this AD. Information may be
emailed to: AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Validation
Branch, FAA; or EASA; or Airbus Defense
and Space S.A.’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
VerDate Sep<11>2014
Issued on November 21, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
Jkt 265001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1053; Project
Identifier AD–2023–00164–T; Amendment
39–22891; AD 2024–24–01]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 757–200,
–200CB, and –200PF series airplanes.
This AD was prompted by a crack
growth analysis, which indicated that
current inspections are not adequate to
detect cracks in certain sections of the
upper frame at the frame splice between
certain stringers before a single frame
fails. This AD requires an inspection or
records review for existing repairs,
repetitive inspections for cracks of the
upper frame at the frame splices
between certain stringers in certain
sections, and applicable on-condition
actions. The FAA is issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective January 13,
2025.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 13, 2025.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–1053, 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 final rule, any comments
received, and other information. The
address for Docket Operations is U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
Material Incorporated by Reference:
• For Boeing material identified in
this AD, contact Boeing Commercial
DATES:
PO 00000
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Fmt 4700
Sfmt 4700
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740–5600; telephone 562–797–1717;
website myboeingfleet.com.
• 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 regulations.gov
under Docket No. FAA–2023–1053.
FOR FURTHER INFORMATION CONTACT:
Wayne Ha, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: 562–627–
5238; email: wayne.ha@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 757–200, –200CB, and –200PF
series airplanes. The NPRM published
in the Federal Register on July 24, 2023
(88 FR 47402). The NPRM was
prompted by a crack growth analysis,
which indicated that current
inspections are not adequate to detect
cracks in certain sections of the upper
frame at the frame splice between
certain stringers before a single frame
fails. In the NPRM, the FAA proposed
to require an inspection or records
review for existing repairs, repetitive
inspections for cracks of the upper
frame at the frame splices between
certain stringers in certain sections, and
applicable on-condition actions.
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to certain The
Boeing Company Model 757–200,
–200CB, and –200PF series airplanes.
The SNPRM published in the Federal
Register on April 22, 2024 (89 FR
29274). The SNPRM was prompted by a
determination that the repetitive
inspection intervals for airplanes that
were modified by Aviation Partners
Boeing (APB) supplemental type
certificate (STC) ST01518SE needed to
be revised. The SNPRM proposed to
require the actions specified in the
NPRM, with certain revised compliance
times.
The FAA is issuing this AD to address
cracking at the upper frames common to
the splice at stringers S–13 to S–14,
which could interact with fuselage skin
cracking at the stringer S–14 lap splice.
This unsafe condition, if not addressed,
could result in the inability of a
principal structural element to sustain
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Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations
with its requirements. For those
airplanes, the FAA has added paragraph
(h)(4) of this AD to provide an exception
to the actions specified in Boeing Alert
Requirements Bulletin 757–53A0115,
dated January 25, 2022.
limit loads, and could adversely affect
the structural integrity of the airplane.
Discussion of Final Airworthiness
Directive
Comments
The FAA received a comment from
Boeing who supported the SNPRM
without change.
The FAA received additional
comments from FedEx Express, United
Airlines (United), and European Air
Transport Leipzig GmbH (EATL). The
following presents the comments
received on the SNPRM and the FAA’s
response to each comment.
Request To Use Different Figures
FedEx Express noted that its 757 fleet
has been modified by VT MAE STC
ST03562AT, passenger-to-freighter
modification for Model 757–200 series
airplanes, which adds a main deck cargo
door to the airplane. After consultation
with the STC holder, FedEx Express
requested modifications for Groups 1, 2,
and 3 of Boeing Alert Requirements
Bulletin 757–53A0115, dated January
25, 2022, for airplanes modified by VT
MAE STC ST03562AT. FedEx Express
requested using the different figures
from the requirements bulletin for the
factory freighter airplanes along with
shorter repeat intervals associated with
those figures. FedEx Express stated that
all other figures along with the method
of inspections called out in the
requirements bulletin will be complied
with according to their respective
effectivity.
The FAA finds no justification for
airplanes modified by VT MAE STC
ST03562AT to utilize the inspections,
methods, and intervals in Groups 1, 2,
and 3 of Boeing Alert Requirements
Bulletin 757–53A0115, dated January
25, 2022. FedEx did not provide
sufficient justification and data for
airplanes modified by VT MAE STC
ST03562AT to support a revision to this
AD. Operators must request approval of
an alternative method of compliance
(AMOC) for airplanes modified by VT
MAE STC ST03562AT to address the
unsafe condition of this AD and comply
Comment Regarding Compliance Time
United stated that the proposed
requirement to divide the applicable
compliance times and repeat intervals
specified in Boeing Alert Requirements
Bulletin 757–53A0115, dated January
25, 2022, by a factor of two is excessive
and could create an undue burden on
the operators. United added that the
FAA did not provide details regarding
how it determined requiring a reduction
in compliance by a factor of two. United
understood that a reduction is necessary
because APB does not yet have an
approved service bulletin to provide its
compliance requirements. However,
United believed the reduction required
by APB will likely show a factor of two
is not an accurate determination.
EATL stated the proposed exception
in paragraph (h)(3) of the proposed AD
includes strong penalties for airplanes
equipped with winglets, as modified by
APB STC ST01518SE. EATL noted
Boeing and APB usually work closely
together to align impacts generated by
installation of winglets, which is then
included in the compliance tables of the
requirements bulletin. EATL added that
Boeing Alert Requirements Bulletin
757–53A0115, dated January 25, 2022,
does not include such penalties or any
indication that installation of winglets
affects the compliance times.
EATL stated the proposed exception
in paragraph (h)(3) of the proposed AD
would prevent airplanes equipped with
winglets, as modified by APB STC
ST01518SE, from scheduling the
inspections required by this AD during
base maintenance events. EATL
requested that the FAA re-evaluate
halving the applicable compliance times
and repeat intervals specified in Boeing
Alert Requirements Bulletin 757–
53A0115, dated January 25, 2022.
The FAA stated the reduction in
compliance by a factor of two is to allow
97495
for APB to complete its evaluation of
airplanes with APB STC ST01518SE
installed. The FAA determined this is a
conservative and appropriate
compliance time for this AD. No
changes have been made to this AD in
this regard.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, and any other changes
described previously, this AD is
adopted as proposed in the SNPRM.
None of the changes will increase the
economic burden on any operator.
Material Incorporated by Reference
Under 1 CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 757–53A0115
RB, dated January 25, 2022. This
material specifies procedures for a
general visual inspection (GVI) or
records review between stringers S–13
and S–14 in Sections 43 and 46 for
existing repairs. This material also
describes procedures, depending on the
configuration, for repetitive high
frequency eddy current (HFEC) and low
frequency eddy current (LFEC)
inspections for cracking of the upper
frames and splice doublers at the frame
splices between stringers S–13 and S–
14, left- and right-hand sides, in
Sections 43 and 46; and applicable oncondition actions. On-condition actions
include repair.
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.
Costs of Compliance
The FAA estimates that this AD
affects 456 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
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ESTIMATED COSTS
Parts
cost
Action
Labor cost
GVI ..............................................
2 work-hours × $85 per hour =
$170 per inspection cycle.
Up to 267 work-hours × $85 per
hour = Up to $22,695 per inspection cycle.
Repetitive Inspections .................
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15:13 Dec 06, 2024
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$0
0
Cost on U.S.
operators
Cost per product
$170 per inspection cycle .........
$77,520 per inspection cycle.
Up to $22,695 per inspection
cycle.
Up to $10,348,920 per inspection cycle.
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97496
Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition repairs specified in
this 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.
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
This AD will not have federalism
implications under Executive Order
13132. This AD will 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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will 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.
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The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
VerDate Sep<11>2014
15:13 Dec 06, 2024
Jkt 265001
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2024–24–01 The Boeing Company:
Amendment 39–22891; Docket No.
FAA–2023–1053; Project Identifier AD–
2023–00164–T.
(a) Effective Date
This airworthiness directive (AD) is
effective January 13, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 757–200, –200CB, and –200PF series
airplanes, certificated in any category, as
identified in Boeing Alert Requirements
Bulletin 757–53A0115 RB, dated January 25,
2022.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a crack growth
analysis, which indicated that current
inspections are not adequate to detect cracks
in the Sections 43 and 46 upper frame at the
frame splice between stringers S–13 and S–
14 before a single frame fails. The FAA is
issuing this AD to address cracking at the
upper frames common to the splice at
stringers S–13 to S–14, which could interact
with fuselage skin cracking at the stringer S–
14 lap splice. The unsafe condition, if not
addressed, could result in the inability of a
principal structural element to sustain limit
loads, and could adversely affect 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 757–53A0115 RB,
dated January 25, 2022, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 757–53A0115
RB, dated January 25, 2022.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 757–53A0115, dated January 25,
2022, which is referred to in Boeing Alert
Requirements Bulletin 757–53A0115 RB,
dated January 25, 2022.
(h) Exceptions to Service Information
Specifications
(1) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
of Boeing Alert Requirements Bulletin 757–
53A0115 RB, dated January 25, 2022, use the
phrase ‘‘the original issue date of
Requirements Bulletin 757–53A0115 RB,’’
PO 00000
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Fmt 4700
Sfmt 4700
this AD requires using the effective date of
this AD.
(2) Where Boeing Alert Requirements
Bulletin 757–53A0115 RB, dated January 25,
2022, specifies contacting Boeing for repair
instructions or for alternative inspections:
This AD requires doing the repair and doing
the alternative inspections and applicable oncondition actions using a method approved
in accordance with the procedures specified
in paragraph (i) of this AD.
(3) For airplanes on which winglet
structural provisions (original equipment
manufacturer (OEM) wingtips) or Aviation
Partners Boeing (APB) winglets have been
installed in accordance with APB
Supplemental Type Certificate (STC)
ST01518SE: This AD requires dividing the
applicable compliance times and repeat
intervals specified in the ‘‘Compliance’’
paragraph of Boeing Requirements Bulletin
757–53A0115 RB, dated January 25, 2022, by
a factor of two.
(4) For airplanes modified by VT MAE STC
ST03562AT: Where paragraph (g) of this AD
requires doing ‘‘all applicable actions
identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Requirements Bulletin 757–53A0115 RB,
dated January 25, 2022,’’ this AD requires
obtaining inspection instructions and
applicable repair instructions in accordance
with the procedures specified in paragraph
(i) of this AD at the later of the compliance
times specified in paragraphs (h)(4)(i) and (ii)
of this AD. Comply with all applicable
instructions at the time specified in the
instructions.
(i) Before 50,000 total flight cycles.
(ii) Within 2,500 flight cycles after the
effective date 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: AMOC@
faa.gov.
(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, 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 Wayne Ha, Aviation Safety Engineer,
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Federal Register / Vol. 89, No. 236 / Monday, December 9, 2024 / Rules and Regulations
Continued Operational Safety Branch, FAA,
2200 South 216th Street, Des Moines, WA
98198; phone: 562–627–5238; email:
wayne.ha@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the address specified in
paragraph (k)(3) of this AD.
AGENCY:
by multiple occurrences of pilot and copilot seats locking in a fore-aft position
due to the seat fore-aft adjustment
mechanism disconnecting, caused by a
broken cotter pin in the seat base egress
linkage. This AD requires modifying the
pilot and co-pilot seats by replacing the
hardware of the seat base egress linkage,
as specified in a Transport Canada AD,
which is incorporated by reference. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 13,
2025.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 13, 2025.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–0468; 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 final rule, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The address for
Docket Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
Material Incorporated by Reference:
• For Transport Canada material
identified in this AD, contact Transport
Canada, Transport Canada National
Aircraft Certification, 159 Cleopatra
Drive, Nepean, Ontario K1A 0N5,
Canada; telephone 888–663–3639; email
TC.AirworthinessDirectivesConsignesdenavigabilite.TC@tc.gc.ca.
You may find this material on the
Transport Canada website at
tc.canada.ca/en/aviation.
• 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 regulations.gov
under Docket No. FAA–2024–0468.
FOR FURTHER INFORMATION CONTACT:
Fatin Saumik, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone 516–228–
7300; email fatin.r.saumik@faa.gov.
SUPPLEMENTARY INFORMATION:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Canada Limited Partnership
Model BD–500–1A10 and BD–500–
1A11 airplanes. This AD was prompted
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Limited
Partnership Model BD–500–1A10 and
BD–500–1A11 airplanes. The NPRM
(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
757–53A0115 RB, dated January 25, 2022.
(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 myboeingfleet.com.
(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 www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
Issued on November 19, 2024.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2024–28782 Filed 12–6–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0468; Project
Identifier MCAI–2023–00762–T; Amendment
39–22898; AD 2024–24–08]
RIN 2120–AA64
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Airworthiness Directives; Airbus
Canada Limited Partnership (Type
Certificate Previously Held by C Series
Aircraft Limited Partnership (CSALP);
Bombardier, Inc.) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY:
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15:13 Dec 06, 2024
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97497
published in the Federal Register on
March 21, 2024 (89 FR 20144). The
NPRM was prompted by AD CF–2023–
40, dated June 13, 2023, issued by
Transport Canada, which is the aviation
authority for Canada (Transport Canada
AD CF–2023–40) (also referred to as the
MCAI). The MCAI states that there have
been in-service occurrences of pilot and
co-pilot seats becoming locked in a foreaft position due to disconnection of the
seat fore-aft adjustment mechanism
caused by a broken cotter pin in the seat
base egress linkage.
In the NPRM, the FAA proposed to
require modifying the pilot and co-pilot
seats by replacing the hardware of the
seat base egress, as specified in
Transport Canada AD CF–2023–40. The
FAA is issuing this AD to address the
disconnection of the seat fore-aft
adjustment mechanism caused by a
broken cotter pin in the seat base egress
linkage. The unsafe condition, if not
addressed, could result in a significant
increase in crew workload for continued
safe flight and landing.
You may examine the MCAI in the
AD docket at regulations.gov under
Docket No. FAA–2024–0468.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
two commenters, including Collins
Aerospace and Delta Airlines (Delta).
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request for Later-Approved Service
Information
Collins Aerospace and Delta
requested that the FAA edit paragraph
(h)(3) of the proposed AD so that it
would allow the use of later service
information. Paragraph (h)(3) of the
proposed AD would mandate Goodrich
Interiors Service Bulletin 1430–25–003,
Revision C, dated November 22, 2022.
The FAA disagrees with the request.
Transport Canada AD CF–2023–40,
dated June 13, 2023, refers to ‘‘Airbus
Canada Service Bulletin (SB) BD500–
251006, Issue 001, dated 05 April 2023,
or later revisions approved by the Chief,
Continuing Airworthiness, Transport
Canada,’’ but does not specifically allow
later-approved revisions of any service
information cited in that Airbus Canada
service bulletin. The FAA has not
changed this AD as a result of this
comment.
Request for Clarification of Paragraph
(h)(3) of Proposed AD
Delta requested clarification of the
wording in (h)(3) of the proposed AD
E:\FR\FM\09DER1.SGM
09DER1
]]>Agencies
[Federal Register Volume 89, Number 236 (Monday, December 9, 2024)]
[Rules and Regulations]
[Pages 97494-97497]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-28782]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1053; Project Identifier AD-2023-00164-T;
Amendment 39-22891; AD 2024-24-01]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain The Boeing Company Model 757-200, -200CB, and -200PF series
airplanes. This AD was prompted by a crack growth analysis, which
indicated that current inspections are not adequate to detect cracks in
certain sections of the upper frame at the frame splice between certain
stringers before a single frame fails. This AD requires an inspection
or records review for existing repairs, repetitive inspections for
cracks of the upper frame at the frame splices between certain
stringers in certain sections, and applicable on-condition actions. The
FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective January 13, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 13,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-1053, 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 final rule, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
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 myboeingfleet.com.
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 regulations.gov under
Docket No. FAA-2023-1053.
FOR FURTHER INFORMATION CONTACT: Wayne Ha, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: 562-627-
5238; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 757-200, -200CB, and -200PF series airplanes. The NPRM
published in the Federal Register on July 24, 2023 (88 FR 47402). The
NPRM was prompted by a crack growth analysis, which indicated that
current inspections are not adequate to detect cracks in certain
sections of the upper frame at the frame splice between certain
stringers before a single frame fails. In the NPRM, the FAA proposed to
require an inspection or records review for existing repairs,
repetitive inspections for cracks of the upper frame at the frame
splices between certain stringers in certain sections, and applicable
on-condition actions.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to certain The
Boeing Company Model 757-200, -200CB, and -200PF series airplanes. The
SNPRM published in the Federal Register on April 22, 2024 (89 FR
29274). The SNPRM was prompted by a determination that the repetitive
inspection intervals for airplanes that were modified by Aviation
Partners Boeing (APB) supplemental type certificate (STC) ST01518SE
needed to be revised. The SNPRM proposed to require the actions
specified in the NPRM, with certain revised compliance times.
The FAA is issuing this AD to address cracking at the upper frames
common to the splice at stringers S-13 to S-14, which could interact
with fuselage skin cracking at the stringer S-14 lap splice. This
unsafe condition, if not addressed, could result in the inability of a
principal structural element to sustain
[[Page 97495]]
limit loads, and could adversely affect the structural integrity of the
airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from Boeing who supported the SNPRM
without change.
The FAA received additional comments from FedEx Express, United
Airlines (United), and European Air Transport Leipzig GmbH (EATL). The
following presents the comments received on the SNPRM and the FAA's
response to each comment.
Request To Use Different Figures
FedEx Express noted that its 757 fleet has been modified by VT MAE
STC ST03562AT, passenger-to-freighter modification for Model 757-200
series airplanes, which adds a main deck cargo door to the airplane.
After consultation with the STC holder, FedEx Express requested
modifications for Groups 1, 2, and 3 of Boeing Alert Requirements
Bulletin 757-53A0115, dated January 25, 2022, for airplanes modified by
VT MAE STC ST03562AT. FedEx Express requested using the different
figures from the requirements bulletin for the factory freighter
airplanes along with shorter repeat intervals associated with those
figures. FedEx Express stated that all other figures along with the
method of inspections called out in the requirements bulletin will be
complied with according to their respective effectivity.
The FAA finds no justification for airplanes modified by VT MAE STC
ST03562AT to utilize the inspections, methods, and intervals in Groups
1, 2, and 3 of Boeing Alert Requirements Bulletin 757-53A0115, dated
January 25, 2022. FedEx did not provide sufficient justification and
data for airplanes modified by VT MAE STC ST03562AT to support a
revision to this AD. Operators must request approval of an alternative
method of compliance (AMOC) for airplanes modified by VT MAE STC
ST03562AT to address the unsafe condition of this AD and comply with
its requirements. For those airplanes, the FAA has added paragraph
(h)(4) of this AD to provide an exception to the actions specified in
Boeing Alert Requirements Bulletin 757-53A0115, dated January 25, 2022.
Comment Regarding Compliance Time
United stated that the proposed requirement to divide the
applicable compliance times and repeat intervals specified in Boeing
Alert Requirements Bulletin 757-53A0115, dated January 25, 2022, by a
factor of two is excessive and could create an undue burden on the
operators. United added that the FAA did not provide details regarding
how it determined requiring a reduction in compliance by a factor of
two. United understood that a reduction is necessary because APB does
not yet have an approved service bulletin to provide its compliance
requirements. However, United believed the reduction required by APB
will likely show a factor of two is not an accurate determination.
EATL stated the proposed exception in paragraph (h)(3) of the
proposed AD includes strong penalties for airplanes equipped with
winglets, as modified by APB STC ST01518SE. EATL noted Boeing and APB
usually work closely together to align impacts generated by
installation of winglets, which is then included in the compliance
tables of the requirements bulletin. EATL added that Boeing Alert
Requirements Bulletin 757-53A0115, dated January 25, 2022, does not
include such penalties or any indication that installation of winglets
affects the compliance times.
EATL stated the proposed exception in paragraph (h)(3) of the
proposed AD would prevent airplanes equipped with winglets, as modified
by APB STC ST01518SE, from scheduling the inspections required by this
AD during base maintenance events. EATL requested that the FAA re-
evaluate halving the applicable compliance times and repeat intervals
specified in Boeing Alert Requirements Bulletin 757-53A0115, dated
January 25, 2022.
The FAA stated the reduction in compliance by a factor of two is to
allow for APB to complete its evaluation of airplanes with APB STC
ST01518SE installed. The FAA determined this is a conservative and
appropriate compliance time for this AD. No changes have been made to
this AD in this regard.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the SNPRM. None of the changes will increase the economic burden on
any operator.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 757-53A0115 RB,
dated January 25, 2022. This material specifies procedures for a
general visual inspection (GVI) or records review between stringers S-
13 and S-14 in Sections 43 and 46 for existing repairs. This material
also describes procedures, depending on the configuration, for
repetitive high frequency eddy current (HFEC) and low frequency eddy
current (LFEC) inspections for cracking of the upper frames and splice
doublers at the frame splices between stringers S-13 and S-14, left-
and right-hand sides, in Sections 43 and 46; and applicable on-
condition actions. On-condition actions include repair.
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.
Costs of Compliance
The FAA estimates that this AD affects 456 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
GVI................................ 2 work-hours x $85 $0 $170 per inspection $77,520 per
per hour = $170 per cycle. inspection cycle.
inspection cycle.
Repetitive Inspections............. Up to 267 work-hours 0 Up to $22,695 per Up to $10,348,920 per
x $85 per hour = Up inspection cycle. inspection cycle.
to $22,695 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
[[Page 97496]]
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this 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.
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
This AD will not have federalism implications under Executive Order
13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will 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 Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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:
2024-24-01 The Boeing Company: Amendment 39-22891; Docket No. FAA-
2023-1053; Project Identifier AD-2023-00164-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 13, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 757-200, -200CB, and
-200PF series airplanes, certificated in any category, as identified
in Boeing Alert Requirements Bulletin 757-53A0115 RB, dated January
25, 2022.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a crack growth analysis, which indicated
that current inspections are not adequate to detect cracks in the
Sections 43 and 46 upper frame at the frame splice between stringers
S-13 and S-14 before a single frame fails. The FAA is issuing this
AD to address cracking at the upper frames common to the splice at
stringers S-13 to S-14, which could interact with fuselage skin
cracking at the stringer S-14 lap splice. The unsafe condition, if
not addressed, could result in the inability of a principal
structural element to sustain limit loads, and could adversely
affect 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 757-53A0115 RB, dated January 25, 2022,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
757-53A0115 RB, dated January 25, 2022.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
757-53A0115, dated January 25, 2022, which is referred to in Boeing
Alert Requirements Bulletin 757-53A0115 RB, dated January 25, 2022.
(h) Exceptions to Service Information Specifications
(1) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-
53A0115 RB, dated January 25, 2022, use the phrase ``the original
issue date of Requirements Bulletin 757-53A0115 RB,'' this AD
requires using the effective date of this AD.
(2) Where Boeing Alert Requirements Bulletin 757-53A0115 RB,
dated January 25, 2022, specifies contacting Boeing for repair
instructions or for alternative inspections: This AD requires doing
the repair and doing the alternative inspections and applicable on-
condition actions using a method approved in accordance with the
procedures specified in paragraph (i) of this AD.
(3) For airplanes on which winglet structural provisions
(original equipment manufacturer (OEM) wingtips) or Aviation
Partners Boeing (APB) winglets have been installed in accordance
with APB Supplemental Type Certificate (STC) ST01518SE: This AD
requires dividing the applicable compliance times and repeat
intervals specified in the ``Compliance'' paragraph of Boeing
Requirements Bulletin 757-53A0115 RB, dated January 25, 2022, by a
factor of two.
(4) For airplanes modified by VT MAE STC ST03562AT: Where
paragraph (g) of this AD requires doing ``all applicable actions
identified in, and in accordance with, the Accomplishment
Instructions of Boeing Alert Requirements Bulletin 757-53A0115 RB,
dated January 25, 2022,'' this AD requires obtaining inspection
instructions and applicable repair instructions in accordance with
the procedures specified in paragraph (i) of this AD at the later of
the compliance times specified in paragraphs (h)(4)(i) and (ii) of
this AD. Comply with all applicable instructions at the time
specified in the instructions.
(i) Before 50,000 total flight cycles.
(ii) Within 2,500 flight cycles after the effective date 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: [email protected].
(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, 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 Wayne Ha,
Aviation Safety Engineer,
[[Page 97497]]
Continued Operational Safety Branch, FAA, 2200 South 216th Street,
Des Moines, WA 98198; phone: 562-627-5238; email: [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the address specified in
paragraph (k)(3) of 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 757-53A0115 RB, dated
January 25, 2022.
(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 myboeingfleet.com.
(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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on November 19, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-28782 Filed 12-6-24; 8:45 am]
BILLING CODE 4910-13-P
