Airworthiness Directives; The Boeing Company Airplanes, 81320-81324 [2024-23116]
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Federal Register / Vol. 89, No. 195 / Tuesday, October 8, 2024 / Rules and Regulations
(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.
DEPARTMENT OF TRANSPORTATION
(k) Related Information
The FAA is superseding
Airworthiness Directive (AD) 2009–01–
02, which applied to certain Boeing
Model 737–600, –700, –700C, –800, and
–900 series airplanes. AD 2009–01–02
required an inspection of frames
between body station (BS) 360 and BS
907 to determine if certain support
brackets of the air conditioning (A/C)
outlet extrusions are installed,
inspections for cracking of the frames
around the attachment holes of the
subject brackets, and repair if necessary.
AD 2009–01–02 also requires installing
new, improved fittings for all support
brackets of the A/C outlet extrusions
between BS 360 and BS 907. This AD
was prompted by numerous reports of
multiple cracks in the frame around the
attachment holes of the support bracket
of the A/C outlet extrusion, and the
determination that certain repairs might
develop fatigue cracks that could result
in the inability of the frame to sustain
limit load and therefore must be
inspected. This AD would continue to
require the actions specified in AD
2009–01–02 and would also require
repetitive inspections for cracking of
certain repairs, and repair if necessary.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective November
12, 2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 12, 2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of February 27, 2009 (74 FR
4117, January 23, 2009).
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–1886; 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
(l) Material Incorporated by Reference
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(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
777–53A0100 RB, dated March 16, 2023.
(ii) Boeing Multi Operator Message MOM–
MOM–24–0054–01B, dated January 26, 2024.
(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 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 August 1, 2024.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2024–23117 Filed 10–7–24; 8:45 am]
BILLING CODE 4910–13–P
16:13 Oct 07, 2024
14 CFR Part 39
[Docket No. FAA–2023–1886; Project
Identifier AD–2023–00429–T; Amendment
39–22841; AD 2024–18–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY:
(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: luis.a.cortez-muniz@faa.gov.
(2) Material identified in this AD that is not
incorporated by reference is available at the
address specified in paragraph (l)(3) of this
AD.
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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–2023–1886.
FOR FURTHER INFORMATION CONTACT:
Owen F. Bley-Male, Aviation Safety
Engineer, FAA, 2200 South 216th Street,
Des Moines, WA 98198; phone: 206–
231–3992; email: Owen.F.Bley-Male@
faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009–01–02,
Amendment 39–15780 (74 FR 4117,
January 23, 2009) (AD 2009–01–02). AD
2009–01–02 applied to certain Boeing
Model 737–600, –700, –700C, –800, and
–900 series airplanes. The NPRM
published in the Federal Register on
September 25, 2023 (88 FR 65637). The
NPRM was prompted by numerous
reports of multiple cracks in the frame
around the attachment holes of the
support bracket of the A/C outlet
extrusion and the determination that
certain repairs might develop fatigue
cracks that could result in the inability
of the frame to sustain limit load and
therefore must be inspected. In the
NPRM, the FAA proposed to continue to
require a one-time general visual
inspection of frames between BS 360
and BS 907 to determine if certain
support brackets of the A/C outlet
extrusions are installed; medium- and
high-frequency eddy current inspections
for cracking of the frames around the
attachment holes of the subject brackets;
repair if necessary; and installation of
new, improved fittings for all support
brackets of the A/C outlet extrusions
between BS 360 and BS 907. The NPRM
also proposed to require repetitive
inspections for cracking of certain
repairs, and repair if necessary. The
FAA is issuing this AD to prevent frame
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Federal Register / Vol. 89, No. 195 / Tuesday, October 8, 2024 / Rules and Regulations
cracking, which, if not corrected, could
lead to a severed frame that, combined
with cracking of the chemically milled
steps in the skin above the Stringer 10
lap splice, could result in rapid
decompression of the airplane.
Discussion of Final Airworthiness
Directive
Comments
The FAA received a comment from an
individual who supported the NPRM
without change.
The FAA received additional
comments from Aviation Partners
Boeing, The Boeing Company (Boeing),
Southwest Airlines (SWA), United
Airlines (UAL), and an individual. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Determine Estimated Cost
An individual commented that the
NPRM stated that there is no definitive
data on which to estimate the labor cost
(for the repairs), so the basis for this
estimated cost is unclear. The
commenter suggested an estimate using
cost data for operations similar to those
required by this AD, making estimates
more robust.
The FAA cannot pre-determine oncondition actions before the inspections
required by this AD are actually
completed. The work-hours to complete
repairs will be unique to each airplane.
For the other actions required by this
AD, the FAA used estimated costs that
were provided by the design approval
holder. No changes have been made to
this AD in this regard.
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Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
incorporation of Supplemental Type
Certificate (STC) ST00830SE for
installation of blended or split scimitar
winglets does not affect the
accomplishment of the manufacturer’s
service instructions.
The FAA agrees with the commenter
that STC ST00830SE does not affect the
accomplishment of the manufacturer’s
service instructions. Therefore, the
installation of STC ST00830SE does not
affect the ability to accomplish the
actions required by this AD. The FAA
has not changed this AD in this regard.
Request for Correction of the Skin Lap
Splice Location
Boeing stated that the NPRM
incorrectly identified the location of the
skin lap splice. The NPRM referred to
‘‘cracking of the skin lap splice above
stringer 10.’’ Boeing requested that
language be corrected to ‘‘cracking of
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the chemically milled steps in the skin
above Stringer 10 lap splice’’ to match
the language in Boeing Alert Service
Bulletin 737–25A1544, Revision 4,
dated February 15, 2022.
The FAA agrees with the request and
has revised the ‘‘Background’’ section of
this final rule and the ‘‘Unsafe
Condition’’ in paragraph (e) of this AD
accordingly.
Request To Add a General Visual
Inspection for Cracks
Boeing noted that Boeing Alert
Service Bulletin 737–25A1544, Revision
4, dated February 15, 2022, requires a
general visual inspection (GVI) to detect
cracks, not just to determine if certain
support brackets of the A/C outlet
extrusions are installed at certain
frames. Boeing requested that a GVI be
required to also detect cracks.
The FAA agrees with the request. The
inspections specified in Part 2 of Boeing
Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022,
include a GVI to detect cracks. The
‘‘Material Incorporated by Reference
under 1 CFR part 51’’ section of this
final rule and paragraph (g)(2) of this
AD have been revised to include a GVI
as an inspection method.
Request To Revise the Applicability
Statement
Boeing stated that paragraph (c),
‘‘Applicability,’’ of the proposed AD
incorrectly identified the referenced
service information as Boeing ‘‘Special
Attention’’ Service Bulletin 737–
25A1544, Revision 4, dated February 15,
2022, and explained that Revision 4 of
this service information is an ‘‘alert’’
service bulletin. The correct reference is
Boeing Alert Service Bulletin 737–
25A1544, Revision 4, dated February 15,
2022.
The FAA agrees and has revised
paragraph (c) of this AD accordingly.
Request To Correct Special Attention
Service Bulletin
Boeing stated that a certain Boeing
special attention service bulletin is
incorrectly identified under ‘‘Actions
Since AD 2009–01–02 Was Issued’’ of
the NPRM. Boeing pointed out that the
NPRM incorrectly identified the service
bulletin number as ‘‘737–25A1544.’’
The correct service bulletin number is
‘‘737–25–1544.’’
The FAA partially agrees. The FAA
agrees that the specified service bulletin
number was stated incorrectly in the
NPRM. However, since that section of
the NPRM is not restated in this final
rule, no change is necessary in this
regard.
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Request To Revise AMOC Provisions
SWA stated that paragraph (j) of the
proposed AD requires inspection of
repairs installed on the BS 907 frame at
the compliance times given in Table 2
of Boeing Alert Service Bulletin 737–
25A1544, Revision 4, dated February 15,
2022. SWA mentioned that Table 2
requires post-repair inspections for
repairs that were installed per Boeing
Special Attention Service Bulletin 737–
25–1544, Revision 3, dated May 16,
2016; or Boeing Alert Service Bulletin
737–25A1544, Revision 4, dated
February 15, 2022; and does not address
repairs that were installed by any other
means. SWA proposed revising
paragraph (m)(4) of the proposed AD to
extend alternative method of
compliance (AMOC) approval to
paragraph (j) of the proposed AD,
provided the AMOC approval contains
a damage tolerance evaluation. SWA
believes that individually approved
repairs that contain an AMOC to AD
2009–01–02, with a damage tolerance
analysis as a Category A or Category B
repair (as defined in Boeing SRM 51–
00–06), provide an equivalent level of
safety.
The FAA disagrees with the request.
Only repairs installed per Boeing
Special Attention Service Bulletin 737–
25–1544, Revision 3, dated May 16,
2016; or Boeing Alert Service Bulletin
737–25A1544, Revision 4, dated
February 15, 2022; are subject to the
requirements of paragraph (j) of this AD.
Repairs installed by any other means are
not subject to the requirements of
paragraph (j) of this AD, so the proposed
AMOC to paragraph (j) would not be
applicable. The FAA has not changed
this AD in this regard.
Request To Clarify Airplanes Affected
by New Requirements
UAL supported the NPRM, and
requested clarification of the airplanes
affected by paragraph (j) of the proposed
AD. UAL stated that some airplanes had
repairs to the STA 907 frame performed
before release of Boeing Special
Attention Service Bulletin 737–25–
1544, Revision 3, dated May 16, 2016.
UAL added that these repairs were
coordinated with Boeing and received
Form 8100–9 approvals as AMOCs to
paragraph (g) of AD 2009–01–02 and are
considered Category B damage tolerance
repairs that also require additional
inspections as defined in the 8100–9
approval. UAL stated that Table 2 of the
‘‘Compliance’’ paragraph of Boeing
Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022 (as
specified in paragraph (j) of the
proposed AD), applies only to airplanes
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on which a frame repair has been done
at STA 907 in accordance with Boeing
Special Attention Service Bulletin 737–
25–1544, Revision 3, dated May 16,
2016; or Boeing Alert Service Bulletin
737–25–1544, Revision 4, dated
February 15, 2022. UAL therefore stated
that Category B repairs via Form 8100–
9 should be excluded from paragraph (j)
of the proposed AD.
The FAA provides the following
clarification. As stated previously, only
repairs installed per Boeing Special
Attention Service Bulletin 737–25–
1544, Revision 3, dated May 16, 2016;
or Boeing Alert Service Bulletin 747–
25A1544, Revision 4, dated February 15,
2022; are subject to the requirements of
paragraph (j) of this AD. Repairs
installed by any other means are not
subject to the requirements of paragraph
(j) of this AD. Therefore, no change to
this AD is necessary.
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 NPRM.
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
Service Bulletin 737–25A1544, Revision
4, dated February 15, 2022. This
material specifies procedures for a onetime general visual inspection of frames
between BS 360 and BS 907 to
determine if certain support brackets of
the A/C outlet extrusions are installed;
a general visual inspection and low-,
medium-, and high-frequency eddy
current inspections for cracking of the
frames around the attachment holes of
the subject brackets, and repair if
necessary; and installation of new,
improved fittings for all support
brackets of the A/C outlet extrusions
between BS 360 and BS 907. This
material also specifies procedures for
repetitive detailed and high-frequency
eddy current inspections for cracking of
certain repairs at BS 907 and repair if
necessary.
This AD also requires Boeing Special
Attention Service Bulletin 737–25–
1544, Revision 1, dated January 16,
2008, which the Director of the Federal
Register approved for incorporation by
reference as of February 27, 2009 (74 FR
4117, January 23, 2009).
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 ADDRESSES.
Costs of Compliance
The FAA estimates that this AD
affects 738 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
General visual inspection (retained actions from AD 2009-01-02).
Eddy current inspections (retained actions from AD 2009-01-02).
Replace support fittings (retained actions from AD 2009–01–02).
Post-repair inspections (new action) ....
1 work-hour × $85 per hour = $85 .......
$0 ......................
$85 .........................
$62,730.
Up to 216 work-hours × $85 per hour
= Up to $18,360.
Up to 346 work-hours × $85 per hour
= Up to $29,410.
42 work-hours × $85 per hour =
$3,570 per inspection cycle.
$0 ......................
Up to $18,360 ........
Up to $13,549,680.
Up to $28,789 ...
Up to $58,199 ........
Up to $42,950,862.
$0 ......................
$3,570 per inspection cycle.
$2,634,660 per inspection cycle.
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition repairs that would
be required based on the results of the
inspections specified in this AD.
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
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
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.
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Regulatory Findings
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Cost on U.S.
operators
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2009–01–02, Amendment 39–
15780 (74 FR 4117, January 23, 2009);
and
■ b. Adding the following new AD:
■
■
2024–18–07 The Boeing Company:
Amendment 39–22841; Docket No.
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FAA–2023–1886; Project Identifier AD–
2023–00429–T.
(a) Effective Date
This airworthiness directive (AD) is
effective November 12, 2024.
(b) Affected ADs
This AD replaces AD 2009–01–02,
Amendment 39–15780 (74 FR 4117, January
23, 2009) (AD 2009–01–02).
(c) Applicability
This AD applies to Boeing Model 737–600,
–700, –700C, –800, and –900 series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishing.
(e) Unsafe Condition
This AD was prompted by numerous
reports of multiple cracks in the frame
around the attachment holes of the support
bracket of the air conditioning (A/C) outlet
extrusion. Also, the FAA determined that
certain repairs done to comply with AD
2009–01–02 might develop fatigue cracks
that could result in the inability of the frame
to sustain limit load and must be inspected.
The FAA is issuing this AD to address frame
cracking, which, if not corrected, could lead
to a severed frame that, combined with
cracking of the chemically milled steps in the
skin above the Stringer 10 lap splice, could
result in rapid decompression of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection, With New Material
This paragraph restates the requirements of
paragraph (f) of AD 2009–01–02, with new
material. Before the accumulation of 36,000
total flight cycles, or within 72 months after
February 27, 2009 (the effective date of AD
2009–01–02), whichever occurs later, except
as required by paragraph (i) of this AD: Do
a general visual inspection to determine if
the support brackets of the A/C outlet
extrusions between body station (BS) 360 and
BS 907 have two-rivet attachment fittings in
accordance with Part 2 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–25–
1544, Revision 1, dated January 16, 2008, or
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022; except
at the locations identified in the notes of Step
3.B.1 of Part 1 of the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–25–1544, Revision 1,
dated January 16, 2008, or Boeing Alert
Service Bulletin 737–25A1544, Revision 4,
dated February 15, 2022. As of the effective
date of this AD, only use Boeing Alert
Service Bulletin 737–25A1544, Revision 4,
dated February 15, 2022, for the actions
required by paragraph (g) of this AD.
(1) For any support bracket attached with
three or more rivets: No further action is
required by paragraph (g) of this AD.
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(2) For any subject support bracket having
a two-rivet attachment fitting: Before the
accumulation of 36,000 total flight cycles, or
within 72 months after February 27, 2009
(the effective date of AD 2009–01–02),
whichever occurs later, except as required by
paragraph (i) of this AD, do general visual,
medium- and high-frequency eddy current
inspections for cracking of the frame around
the attachment holes of the support bracket,
in accordance with Part 2 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–25–
1544, Revision 1, dated January 16, 2008, or
do general visual, low-, medium- and highfrequency eddy current inspections for
cracking of the frame around the attachment
holes of the support bracket, in accordance
with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–25A1544, Revision 4, dated February 15,
2022. If any cracking is discovered, before
further flight, repair the cracking in
accordance with Part 3 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–25–
1544, Revision 1, dated January 16, 2008, or
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022, except
as required by paragraph (k)(2) of this AD. As
of the effective date of this AD, only use
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022, for the
actions required by paragraph (g)(2) of this
AD.
81323
(j) New Requirements of This AD
For Groups 1 through 4 and Group 6 as
identified in Boeing Alert Service Bulletin
737–25A1544, Revision 4, dated February 15,
2022: Except as specified in paragraph (k) of
this AD: At the applicable time specified in
Table 2 of the ‘‘Compliance’’ paragraph of
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022, do a
detailed inspection and a high-frequency
eddy current inspection for cracking of the
repaired area at frame BS 907, and do all
applicable repairs before further flight, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–25A1544, Revision 4, dated February 15,
2022. Repeat the inspections thereafter at the
applicable time specified in Table 2 of the
‘‘Compliance’’ paragraph of Boeing Alert
Service Bulletin 737–25A1544, Revision 4,
dated February 15, 2022.
(i) Retained Compliance Time for Certain
Airplanes, With No Changes
(k) Exceptions to Service Bulletin
Specifications
(1) Where the Compliance Time column of
Table 2 in the ‘‘Compliance’’ paragraph of
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022, uses the
phrase ‘‘the Revision 4 date of this Service
Bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(2) Where Boeing Alert Service Bulletin
737–25A1544, Revision 4, dated February 15,
2022, specifies contacting Boeing, this AD
requires repair before further flight using a
method approved in accordance with the
procedures specified in paragraph (m) of this
AD.
(3) For airplanes on which BBJ Lower
Cabin Altitude STC ST01697SE (drs.faa.gov/
browse/excelExternalWindow/
0812969A86AF879B86257664
00600105.0001) has been incorporated, the
flight-cycle related compliance times for the
inspections required by paragraph (j) of this
AD are different from those specified in
Table 2 of the ‘‘Compliance’’ paragraph in
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022. All
initial compliance times specified in total
flight cycles or flight cycles must be reduced
to half of those specified in Table 2 of the
‘‘Compliance’’ paragraph in Boeing Alert
Service Bulletin 737–25A1544, Revision 4,
dated February 15, 2022. All repetitive
interval compliance times specified in flight
cycles must be reduced to one-quarter of
those specified in Table 2 of the
‘‘Compliance’’ paragraph in Boeing Alert
Service Bulletin 737–25A1544, Revision 4,
dated February 15, 2022.
This paragraph restates the compliance
time specified in paragraph (h) of AD 2009–
01–02, with no changes. For airplanes on
which Boeing Business Jet (BBJ) lower cabin
altitude modification is incorporated in
accordance with Supplemental Type
Certificate (STC) ST01697SE (6,500 feet
maximum cabin altitude in lieu of 8,000
feet): Before the accumulation of 18,000 total
flight cycles, or within 72 months after
February 27, 2009 (the effective date of AD
2009–01–02), whichever occurs later, do the
actions specified in paragraphs (g) and (h) of
this AD.
(l) Credit for Previous Actions
(1) This paragraph provides credit for the
actions specified in paragraphs (g) and (h) of
this AD, if those actions were performed
before February 27, 2009 (the effective date
of AD 2009–01–02), using Boeing Special
Attention Service Bulletin 737–25–1544,
dated October 4, 2006.
(2) This paragraph provides credit for the
actions specified in paragraphs (g) and (h) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Special Attention Service Bulletin
737–25–1544, Revision 2, dated March 23,
(h) Retained Modification, With New
Material
This paragraph restates the requirements of
paragraph (g) of AD 2009–01–02, with new
material. Except as required by paragraph (i)
of this AD: Before the accumulation of 36,000
total flight cycles, or within 72 months after
February 27, 2009 (the effective date of AD
2009–01–02), whichever occurs later, replace
the support fittings of all A/C outlet
extrusions between BS 360 and BS 907 with
new, improved support fittings, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–25–
1544, Revision 1, dated January 16, 2008, or
Boeing Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022. As of
the effective date of this AD, only use Boeing
Alert Service Bulletin 737–25A1544,
Revision 4, dated February 15, 2022, for the
actions required by paragraph (h) of this AD.
PO 00000
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81324
Federal Register / Vol. 89, No. 195 / Tuesday, October 8, 2024 / Rules and Regulations
2011; or Boeing Special Attention Service
Bulletin 737–25–1544, Revision 3, dated May
16, 2016.
(m) 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 AIR–520, Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (n)(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, 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.
(4) AMOCs approved for AD 2009–01–02
are approved as AMOCs for the
corresponding provisions of this AD.
ddrumheller on DSK120RN23PROD with RULES1
(n) Related Information
(1) For more information about this AD,
contact Owen F. Bley-Male, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: 206–231–3992;
email: Owen.F.Bley-Male@faa.gov.
(2) Material identified in this AD that is not
incorporated by reference is available at the
address specified in paragraph (o)(5) of this
AD.
(o) 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.
(3) The following material was approved
for IBR on November 12, 2024.
(i) Boeing Alert Service Bulletin 737–
25A1544, Revision 4, dated February 15,
2022.
(ii) [Reserved]
(4) The following material was approved
for IBR on February 27, 2009 (74 FR 4117,
January 23, 2009).
(i) Boeing Special Attention Service
Bulletin 737–25–1544, Revision 1, dated
January 16, 2008.
(ii) [Reserved]
(5) For Boeing material identified in this
AD, contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110–
VerDate Sep<11>2014
16:13 Oct 07, 2024
Jkt 265001
SK57, Seal Beach, CA 90740–5600; telephone
562–797–1717; website myboeingfleet.com.
(6) 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.
(7) 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 September 6, 2024.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2024–23116 Filed 10–7–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–1686; Project
Identifier MCAI–2023–00595–R; Amendment
39–22839; AD 2024–18–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Helicopters Model AS332C,
AS332C1, AS332L, AS332L1, and
SA330J helicopters. This AD was
prompted by the installation of
unapproved main gearbox (MGB)
forward and rear suspension bar
attachment plates. This AD requires
inspecting or measuring the MGB
forward and rear suspension bar
attachment plates and, depending on
the results, taking corrective action, as
specified in a European Union Aviation
Safety Agency (EASA) 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 November
12, 2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 12, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–1686; or in person at
Docket Operations between 9 a.m. and
SUMMARY:
PO 00000
Frm 00032
Fmt 4700
Sfmt 4700
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, the EASA AD,
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 EASA material identified in this
AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; phone:
+49 221 8999 000; email: ADs@
easa.europa.eu; website:
easa.europa.eu. You may find the EASA
material on the EASA website at
ad.easa.europa.eu.
• You may view this material at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. For information on the
availability of this material at the FAA,
call (817) 222–5110. It is also available
at regulations.gov under Docket No.
FAA–2024–1686.
Other Related Material: For Airbus
Helicopters material identified in this
AD, contact Airbus Helicopters, 2701
North Forum Drive, Grand Prairie, TX
75052; phone: (972) 641–0000 or (800)
232–0323; fax: (972) 641–3775; or at
airbus.com/en/products-services/
helicopters/hcare-services/airbusworld.
FOR FURTHER INFORMATION CONTACT: Hye
Yoon Jang, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (206) 231–
3758; email: hye.yoon.jang@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 Airbus Helicopters Model
AS332C, AS332C1, AS332L, AS332L1,
and SA330J helicopters. The NPRM
published in the Federal Register on
June 18, 2024 (89 FR 51468). The NPRM
was prompted by a series of ADs, the
most recent being EASA AD 2023–0076,
dated April 11, 2023 (EASA AD 2023–
0076), issued by EASA, which is the
Technical Agent for the Member States
of the European Union, to correct an
unsafe condition on Airbus Helicopters
Model SA 330 J, AS 332 C, AS 332 C1,
AS 332 L, and AS 332 L1 helicopters.
In the NPRM, the FAA proposed to
require inspecting or measuring the
MGB forward and rear suspension bar
attachment plates and, depending on
the results, taking corrective action. The
FAA is issuing this AD to address the
unsafe condition on these products.
E:\FR\FM\08OCR1.SGM
08OCR1
]]>Agencies
[Federal Register Volume 89, Number 195 (Tuesday, October 8, 2024)]
[Rules and Regulations]
[Pages 81320-81324]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-23116]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-1886; Project Identifier AD-2023-00429-T;
Amendment 39-22841; AD 2024-18-07]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2009-01-
02, which applied to certain Boeing Model 737-600, -700, -700C, -800,
and -900 series airplanes. AD 2009-01-02 required an inspection of
frames between body station (BS) 360 and BS 907 to determine if certain
support brackets of the air conditioning (A/C) outlet extrusions are
installed, inspections for cracking of the frames around the attachment
holes of the subject brackets, and repair if necessary. AD 2009-01-02
also requires installing new, improved fittings for all support
brackets of the A/C outlet extrusions between BS 360 and BS 907. This
AD was prompted by numerous reports of multiple cracks in the frame
around the attachment holes of the support bracket of the A/C outlet
extrusion, and the determination that certain repairs might develop
fatigue cracks that could result in the inability of the frame to
sustain limit load and therefore must be inspected. This AD would
continue to require the actions specified in AD 2009-01-02 and would
also require repetitive inspections for cracking of certain repairs,
and repair if necessary. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective November 12, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 12,
2024.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 27, 2009 (74 FR 4117, January 23, 2009).
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-1886; 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-2023-1886.
FOR FURTHER INFORMATION CONTACT: Owen F. Bley-Male, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
206-231-3992; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2009-01-02, Amendment 39-15780 (74 FR 4117,
January 23, 2009) (AD 2009-01-02). AD 2009-01-02 applied to certain
Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. The
NPRM published in the Federal Register on September 25, 2023 (88 FR
65637). The NPRM was prompted by numerous reports of multiple cracks in
the frame around the attachment holes of the support bracket of the A/C
outlet extrusion and the determination that certain repairs might
develop fatigue cracks that could result in the inability of the frame
to sustain limit load and therefore must be inspected. In the NPRM, the
FAA proposed to continue to require a one-time general visual
inspection of frames between BS 360 and BS 907 to determine if certain
support brackets of the A/C outlet extrusions are installed; medium-
and high-frequency eddy current inspections for cracking of the frames
around the attachment holes of the subject brackets; repair if
necessary; and installation of new, improved fittings for all support
brackets of the A/C outlet extrusions between BS 360 and BS 907. The
NPRM also proposed to require repetitive inspections for cracking of
certain repairs, and repair if necessary. The FAA is issuing this AD to
prevent frame
[[Page 81321]]
cracking, which, if not corrected, could lead to a severed frame that,
combined with cracking of the chemically milled steps in the skin above
the Stringer 10 lap splice, could result in rapid decompression of the
airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from an individual who supported the
NPRM without change.
The FAA received additional comments from Aviation Partners Boeing,
The Boeing Company (Boeing), Southwest Airlines (SWA), United Airlines
(UAL), and an individual. The following presents the comments received
on the NPRM and the FAA's response to each comment.
Request To Determine Estimated Cost
An individual commented that the NPRM stated that there is no
definitive data on which to estimate the labor cost (for the repairs),
so the basis for this estimated cost is unclear. The commenter
suggested an estimate using cost data for operations similar to those
required by this AD, making estimates more robust.
The FAA cannot pre-determine on-condition actions before the
inspections required by this AD are actually completed. The work-hours
to complete repairs will be unique to each airplane. For the other
actions required by this AD, the FAA used estimated costs that were
provided by the design approval holder. No changes have been made to
this AD in this regard.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that incorporation of Supplemental
Type Certificate (STC) ST00830SE for installation of blended or split
scimitar winglets does not affect the accomplishment of the
manufacturer's service instructions.
The FAA agrees with the commenter that STC ST00830SE does not
affect the accomplishment of the manufacturer's service instructions.
Therefore, the installation of STC ST00830SE does not affect the
ability to accomplish the actions required by this AD. The FAA has not
changed this AD in this regard.
Request for Correction of the Skin Lap Splice Location
Boeing stated that the NPRM incorrectly identified the location of
the skin lap splice. The NPRM referred to ``cracking of the skin lap
splice above stringer 10.'' Boeing requested that language be corrected
to ``cracking of the chemically milled steps in the skin above Stringer
10 lap splice'' to match the language in Boeing Alert Service Bulletin
737-25A1544, Revision 4, dated February 15, 2022.
The FAA agrees with the request and has revised the ``Background''
section of this final rule and the ``Unsafe Condition'' in paragraph
(e) of this AD accordingly.
Request To Add a General Visual Inspection for Cracks
Boeing noted that Boeing Alert Service Bulletin 737-25A1544,
Revision 4, dated February 15, 2022, requires a general visual
inspection (GVI) to detect cracks, not just to determine if certain
support brackets of the A/C outlet extrusions are installed at certain
frames. Boeing requested that a GVI be required to also detect cracks.
The FAA agrees with the request. The inspections specified in Part
2 of Boeing Alert Service Bulletin 737-25A1544, Revision 4, dated
February 15, 2022, include a GVI to detect cracks. The ``Material
Incorporated by Reference under 1 CFR part 51'' section of this final
rule and paragraph (g)(2) of this AD have been revised to include a GVI
as an inspection method.
Request To Revise the Applicability Statement
Boeing stated that paragraph (c), ``Applicability,'' of the
proposed AD incorrectly identified the referenced service information
as Boeing ``Special Attention'' Service Bulletin 737-25A1544, Revision
4, dated February 15, 2022, and explained that Revision 4 of this
service information is an ``alert'' service bulletin. The correct
reference is Boeing Alert Service Bulletin 737-25A1544, Revision 4,
dated February 15, 2022.
The FAA agrees and has revised paragraph (c) of this AD
accordingly.
Request To Correct Special Attention Service Bulletin
Boeing stated that a certain Boeing special attention service
bulletin is incorrectly identified under ``Actions Since AD 2009-01-02
Was Issued'' of the NPRM. Boeing pointed out that the NPRM incorrectly
identified the service bulletin number as ``737-25A1544.'' The correct
service bulletin number is ``737-25-1544.''
The FAA partially agrees. The FAA agrees that the specified service
bulletin number was stated incorrectly in the NPRM. However, since that
section of the NPRM is not restated in this final rule, no change is
necessary in this regard.
Request To Revise AMOC Provisions
SWA stated that paragraph (j) of the proposed AD requires
inspection of repairs installed on the BS 907 frame at the compliance
times given in Table 2 of Boeing Alert Service Bulletin 737-25A1544,
Revision 4, dated February 15, 2022. SWA mentioned that Table 2
requires post-repair inspections for repairs that were installed per
Boeing Special Attention Service Bulletin 737-25-1544, Revision 3,
dated May 16, 2016; or Boeing Alert Service Bulletin 737-25A1544,
Revision 4, dated February 15, 2022; and does not address repairs that
were installed by any other means. SWA proposed revising paragraph
(m)(4) of the proposed AD to extend alternative method of compliance
(AMOC) approval to paragraph (j) of the proposed AD, provided the AMOC
approval contains a damage tolerance evaluation. SWA believes that
individually approved repairs that contain an AMOC to AD 2009-01-02,
with a damage tolerance analysis as a Category A or Category B repair
(as defined in Boeing SRM 51-00-06), provide an equivalent level of
safety.
The FAA disagrees with the request. Only repairs installed per
Boeing Special Attention Service Bulletin 737-25-1544, Revision 3,
dated May 16, 2016; or Boeing Alert Service Bulletin 737-25A1544,
Revision 4, dated February 15, 2022; are subject to the requirements of
paragraph (j) of this AD. Repairs installed by any other means are not
subject to the requirements of paragraph (j) of this AD, so the
proposed AMOC to paragraph (j) would not be applicable. The FAA has not
changed this AD in this regard.
Request To Clarify Airplanes Affected by New Requirements
UAL supported the NPRM, and requested clarification of the
airplanes affected by paragraph (j) of the proposed AD. UAL stated that
some airplanes had repairs to the STA 907 frame performed before
release of Boeing Special Attention Service Bulletin 737-25-1544,
Revision 3, dated May 16, 2016. UAL added that these repairs were
coordinated with Boeing and received Form 8100-9 approvals as AMOCs to
paragraph (g) of AD 2009-01-02 and are considered Category B damage
tolerance repairs that also require additional inspections as defined
in the 8100-9 approval. UAL stated that Table 2 of the ``Compliance''
paragraph of Boeing Alert Service Bulletin 737-25A1544, Revision 4,
dated February 15, 2022 (as specified in paragraph (j) of the proposed
AD), applies only to airplanes
[[Page 81322]]
on which a frame repair has been done at STA 907 in accordance with
Boeing Special Attention Service Bulletin 737-25-1544, Revision 3,
dated May 16, 2016; or Boeing Alert Service Bulletin 737-25-1544,
Revision 4, dated February 15, 2022. UAL therefore stated that Category
B repairs via Form 8100-9 should be excluded from paragraph (j) of the
proposed AD.
The FAA provides the following clarification. As stated previously,
only repairs installed per Boeing Special Attention Service Bulletin
737-25-1544, Revision 3, dated May 16, 2016; or Boeing Alert Service
Bulletin 747-25A1544, Revision 4, dated February 15, 2022; are subject
to the requirements of paragraph (j) of this AD. Repairs installed by
any other means are not subject to the requirements of paragraph (j) of
this AD. Therefore, no change to this AD is necessary.
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 NPRM. 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 Service Bulletin 737-25A1544,
Revision 4, dated February 15, 2022. This material specifies procedures
for a one-time general visual inspection of frames between BS 360 and
BS 907 to determine if certain support brackets of the A/C outlet
extrusions are installed; a general visual inspection and low-, medium-
, and high-frequency eddy current inspections for cracking of the
frames around the attachment holes of the subject brackets, and repair
if necessary; and installation of new, improved fittings for all
support brackets of the A/C outlet extrusions between BS 360 and BS
907. This material also specifies procedures for repetitive detailed
and high-frequency eddy current inspections for cracking of certain
repairs at BS 907 and repair if necessary.
This AD also requires Boeing Special Attention Service Bulletin
737-25-1544, Revision 1, dated January 16, 2008, which the Director of
the Federal Register approved for incorporation by reference as of
February 27, 2009 (74 FR 4117, January 23, 2009).
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 ADDRESSES.
Costs of Compliance
The FAA estimates that this AD affects 738 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
General visual inspection (retained 1 work-hour x $85 per $0......................... $85........................... $62,730.
actions from AD hour = $85.
2009[dash]01[dash]02).
Eddy current inspections (retained Up to 216 work-hours x $0......................... Up to $18,360................. Up to $13,549,680.
actions from AD $85 per hour = Up to
2009[dash]01[dash]02). $18,360.
Replace support fittings (retained Up to 346 work-hours x Up to $28,789.............. Up to $58,199................. Up to $42,950,862.
actions from AD 2009-01-02). $85 per hour = Up to
$29,410.
Post-repair inspections (new 42 work-hours x $85 $0......................... $3,570 per inspection cycle... $2,634,660 per inspection
action). per hour = $3,570 per cycle.
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs that would be required based on
the results of the inspections 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:
0
a. Removing Airworthiness Directive (AD) 2009-01-02, Amendment 39-15780
(74 FR 4117, January 23, 2009); and
0
b. Adding the following new AD:
2024-18-07 The Boeing Company: Amendment 39-22841; Docket No.
[[Page 81323]]
FAA-2023-1886; Project Identifier AD-2023-00429-T.
(a) Effective Date
This airworthiness directive (AD) is effective November 12,
2024.
(b) Affected ADs
This AD replaces AD 2009-01-02, Amendment 39-15780 (74 FR 4117,
January 23, 2009) (AD 2009-01-02).
(c) Applicability
This AD applies to Boeing Model 737-600, -700, -700C, -800, and
-900 series airplanes, certificated in any category, as identified
in Boeing Alert Service Bulletin 737-25A1544, Revision 4, dated
February 15, 2022.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
Furnishing.
(e) Unsafe Condition
This AD was prompted by numerous reports of multiple cracks in
the frame around the attachment holes of the support bracket of the
air conditioning (A/C) outlet extrusion. Also, the FAA determined
that certain repairs done to comply with AD 2009-01-02 might develop
fatigue cracks that could result in the inability of the frame to
sustain limit load and must be inspected. The FAA is issuing this AD
to address frame cracking, which, if not corrected, could lead to a
severed frame that, combined with cracking of the chemically milled
steps in the skin above the Stringer 10 lap splice, could result in
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection, With New Material
This paragraph restates the requirements of paragraph (f) of AD
2009-01-02, with new material. Before the accumulation of 36,000
total flight cycles, or within 72 months after February 27, 2009
(the effective date of AD 2009-01-02), whichever occurs later,
except as required by paragraph (i) of this AD: Do a general visual
inspection to determine if the support brackets of the A/C outlet
extrusions between body station (BS) 360 and BS 907 have two-rivet
attachment fittings in accordance with Part 2 of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 737-25-
1544, Revision 1, dated January 16, 2008, or Boeing Alert Service
Bulletin 737-25A1544, Revision 4, dated February 15, 2022; except at
the locations identified in the notes of Step 3.B.1 of Part 1 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-25-1544, Revision 1, dated January 16, 2008, or Boeing
Alert Service Bulletin 737-25A1544, Revision 4, dated February 15,
2022. As of the effective date of this AD, only use Boeing Alert
Service Bulletin 737-25A1544, Revision 4, dated February 15, 2022,
for the actions required by paragraph (g) of this AD.
(1) For any support bracket attached with three or more rivets:
No further action is required by paragraph (g) of this AD.
(2) For any subject support bracket having a two-rivet
attachment fitting: Before the accumulation of 36,000 total flight
cycles, or within 72 months after February 27, 2009 (the effective
date of AD 2009-01-02), whichever occurs later, except as required
by paragraph (i) of this AD, do general visual, medium- and high-
frequency eddy current inspections for cracking of the frame around
the attachment holes of the support bracket, in accordance with Part
2 of the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 737-25-1544, Revision 1, dated January 16, 2008, or
do general visual, low-, medium- and high-frequency eddy current
inspections for cracking of the frame around the attachment holes of
the support bracket, in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-25A1544, Revision
4, dated February 15, 2022. If any cracking is discovered, before
further flight, repair the cracking in accordance with Part 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-25-1544, Revision 1, dated January 16, 2008, or Boeing
Alert Service Bulletin 737-25A1544, Revision 4, dated February 15,
2022, except as required by paragraph (k)(2) of this AD. As of the
effective date of this AD, only use Boeing Alert Service Bulletin
737-25A1544, Revision 4, dated February 15, 2022, for the actions
required by paragraph (g)(2) of this AD.
(h) Retained Modification, With New Material
This paragraph restates the requirements of paragraph (g) of AD
2009-01-02, with new material. Except as required by paragraph (i)
of this AD: Before the accumulation of 36,000 total flight cycles,
or within 72 months after February 27, 2009 (the effective date of
AD 2009-01-02), whichever occurs later, replace the support fittings
of all A/C outlet extrusions between BS 360 and BS 907 with new,
improved support fittings, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-25-1544, Revision 1, dated January 16, 2008, or Boeing
Alert Service Bulletin 737-25A1544, Revision 4, dated February 15,
2022. As of the effective date of this AD, only use Boeing Alert
Service Bulletin 737-25A1544, Revision 4, dated February 15, 2022,
for the actions required by paragraph (h) of this AD.
(i) Retained Compliance Time for Certain Airplanes, With No Changes
This paragraph restates the compliance time specified in
paragraph (h) of AD 2009-01-02, with no changes. For airplanes on
which Boeing Business Jet (BBJ) lower cabin altitude modification is
incorporated in accordance with Supplemental Type Certificate (STC)
ST01697SE (6,500 feet maximum cabin altitude in lieu of 8,000 feet):
Before the accumulation of 18,000 total flight cycles, or within 72
months after February 27, 2009 (the effective date of AD 2009-01-
02), whichever occurs later, do the actions specified in paragraphs
(g) and (h) of this AD.
(j) New Requirements of This AD
For Groups 1 through 4 and Group 6 as identified in Boeing Alert
Service Bulletin 737-25A1544, Revision 4, dated February 15, 2022:
Except as specified in paragraph (k) of this AD: At the applicable
time specified in Table 2 of the ``Compliance'' paragraph of Boeing
Alert Service Bulletin 737-25A1544, Revision 4, dated February 15,
2022, do a detailed inspection and a high-frequency eddy current
inspection for cracking of the repaired area at frame BS 907, and do
all applicable repairs before further flight, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
25A1544, Revision 4, dated February 15, 2022. Repeat the inspections
thereafter at the applicable time specified in Table 2 of the
``Compliance'' paragraph of Boeing Alert Service Bulletin 737-
25A1544, Revision 4, dated February 15, 2022.
(k) Exceptions to Service Bulletin Specifications
(1) Where the Compliance Time column of Table 2 in the
``Compliance'' paragraph of Boeing Alert Service Bulletin 737-
25A1544, Revision 4, dated February 15, 2022, uses the phrase ``the
Revision 4 date of this Service Bulletin,'' this AD requires using
``the effective date of this AD.''
(2) Where Boeing Alert Service Bulletin 737-25A1544, Revision 4,
dated February 15, 2022, specifies contacting Boeing, this AD
requires repair before further flight using a method approved in
accordance with the procedures specified in paragraph (m) of this
AD.
(3) For airplanes on which BBJ Lower Cabin Altitude STC
ST01697SE (drs.faa.gov/browse/excelExternalWindow/0812969A86AF879B8625766400600105.0001) has been incorporated, the
flight-cycle related compliance times for the inspections required
by paragraph (j) of this AD are different from those specified in
Table 2 of the ``Compliance'' paragraph in Boeing Alert Service
Bulletin 737-25A1544, Revision 4, dated February 15, 2022. All
initial compliance times specified in total flight cycles or flight
cycles must be reduced to half of those specified in Table 2 of the
``Compliance'' paragraph in Boeing Alert Service Bulletin 737-
25A1544, Revision 4, dated February 15, 2022. All repetitive
interval compliance times specified in flight cycles must be reduced
to one-quarter of those specified in Table 2 of the ``Compliance''
paragraph in Boeing Alert Service Bulletin 737-25A1544, Revision 4,
dated February 15, 2022.
(l) Credit for Previous Actions
(1) This paragraph provides credit for the actions specified in
paragraphs (g) and (h) of this AD, if those actions were performed
before February 27, 2009 (the effective date of AD 2009-01-02),
using Boeing Special Attention Service Bulletin 737-25-1544, dated
October 4, 2006.
(2) This paragraph provides credit for the actions specified in
paragraphs (g) and (h) of this AD, if those actions were performed
before the effective date of this AD using Boeing Special Attention
Service Bulletin 737-25-1544, Revision 2, dated March 23,
[[Page 81324]]
2011; or Boeing Special Attention Service Bulletin 737-25-1544,
Revision 3, dated May 16, 2016.
(m) 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 AIR-520, Continued
Operational Safety Branch, send it to the attention of the person
identified in paragraph (n)(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, 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.
(4) AMOCs approved for AD 2009-01-02 are approved as AMOCs for
the corresponding provisions of this AD.
(n) Related Information
(1) For more information about this AD, contact Owen F. Bley-
Male, Aviation Safety Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: 206-231-3992; email: [email protected].
(2) Material identified in this AD that is not incorporated by
reference is available at the address specified in paragraph (o)(5)
of this AD.
(o) 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.
(3) The following material was approved for IBR on November 12,
2024.
(i) Boeing Alert Service Bulletin 737-25A1544, Revision 4, dated
February 15, 2022.
(ii) [Reserved]
(4) The following material was approved for IBR on February 27,
2009 (74 FR 4117, January 23, 2009).
(i) Boeing Special Attention Service Bulletin 737-25-1544,
Revision 1, dated January 16, 2008.
(ii) [Reserved]
(5) 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.
(6) 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.
(7) 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 September 6, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-23116 Filed 10-7-24; 8:45 am]
BILLING CODE 4910-13-P
