Airworthiness Directives; Airbus SAS Airplanes, 56195-56198 [2024-14868]
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Federal Register / Vol. 89, No. 131 / Tuesday, July 9, 2024 / Rules and Regulations
Bulletin (SB) CFE738–72–A8082, dated July
4, 2023 (CFE738–72–A8082).
Moines, WA 98198; phone: (781) 238–7178;
email: alexei.t.marqueen@faa.gov.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7250, Turbine Section.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as
applicable to do the actions required by this
AD, unless the AD specifies otherwise.
(i) CFE Service Bulletin CFE738–72–
A8082, dated July 4, 2023.
(ii) [Reserved]
(3) For CFE material, contact CFE
Company, 111 S 34th Street, Phoenix, AZ
85034; phone: (800) 601–3099; email:
CFE738DataCenter@honeywell.com; website:
aerospace.honeywell.com.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on
the availability of this material at the FAA,
call (817) 222–5110.
(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.
(e) Unsafe Condition
This AD was prompted by a manufacturer
investigation that revealed certain HPT stage
1 disks and HPT stage 2 disks were
manufactured from powder metal material
suspected to contain iron inclusion. The FAA
is issuing this AD to prevent premature
fracture and consequent uncontained failure.
The unsafe condition, if not addressed, could
result in uncontained debris release, damage
to the engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
At the applicable times specified in
paragraphs (g)(1) and (2) of this AD, remove
each affected HPT stage 1 disk and HPT stage
2 disk from service and replace with a part
eligible for installation, in accordance with
steps (1) through (9) in paragraph B. of the
Accomplishment Instructions of CFE738–72–
A8082.
(1) For affected HPT stage 1 disks, at the
next piece-part exposure or before exceeding
2,450 cycles since new (CSN), whichever
occurs first.
(2) For affected HPT stage 2 disks, at the
next piece-part exposure or before exceeding
2,930 CSN, whichever occurs first.
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(h) Definition
For the purpose of this AD:
(1) A ‘‘part eligible for installation’’ is any
HPT stage 1 disk or HPT stage 2 disk with
a P/N and S/N that is not identified in
Section 1. Planning Information, paragraph E.
Compliance, Tables 2 and 3 of CFE738–72–
A8082.
(2) ‘‘Piece-part exposure’’ is when the
affected part is removed from the engine.
(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 local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the AIR–520 Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (j) of this AD and email to: ANEAD-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(j) Related Information
For more information about this AD,
contact Alexei Marqueen, Aviation Safety
Engineer, FAA, 2200 South 216th Steet, Des
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Issued on June 11, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2024–14939 Filed 7–8–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0757; Project
Identifier MCAI–2023–01205–T; Amendment
39–22765; AD 2024–12–01]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2022–14–
10, which applied to certain Airbus SAS
Model A318 series airplanes; Model
A319–111, –112, –113, –114, –115,
–131, –132, and –133 airplanes; Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes; and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. AD
2022–14–10 required repetitive
inspections for cracking of the radius of
the front spar vertical stringers and the
horizontal floor beam on a certain frame
SUMMARY:
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56195
(FR), repetitive inspections for cracking
of the fastener holes of the front spar
vertical stringers on that frame, and
repair if necessary. AD 2022–14–10 also
provided, for certain airplanes, a
modification of the center wing box area
that terminates the repetitive
inspections under certain conditions.
Since the FAA issued AD 2022–14–10,
an additional airplane model has been
identified that is also subject to the
unsafe condition. This AD continues to
require the actions in AD 2022–14–10
and adds Model A321–271N airplanes
to the applicability, as specified in a
European Union Aviation Safety Agency
(EASA) AD, which is incorporated by
reference (IBR). The FAA is issuing this
AD to address the unsafe condition on
these products.
This AD is effective August 13,
2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 13, 2024.
DATES:
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–0757; 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 EASA material, 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 material on the EASA website at
ad.easa.europa.eu.
• 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–2024–0757.
FOR FURTHER INFORMATION CONTACT:
Timothy Dowling, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590;
telephone 206–231–3667; email
timothy.p.dowling@faa.gov.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 89, No. 131 / Tuesday, July 9, 2024 / Rules and Regulations
2022–14–10 and add Model A321–271N
airplanes to the applicability, as
specified in EASA AD 2023–0205. The
FAA is issuing this AD to address the
unsafe condition on these products.
You may examine the MCAI in the
AD docket at regulations.gov under
Docket No. FAA–2024–0757.
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2022–14–10,
Amendment 39–22115 (87 FR 42315,
July 15, 2022), (AD 2022–14–10). AD
2022–14–10 applied to certain Airbus
SAS Model A318 series airplanes;
Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes;
Model A320–211, –212, –214, –216,
–231, –232, and –233 airplanes; and
Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
AD 2022–14–10 required repetitive
inspections for cracking of the radius of
the front spar vertical stringers and the
horizontal floor beam on FR 36,
repetitive inspections for cracking of the
fastener holes of the front spar vertical
stringers on FR 36, and repair if
necessary, and, for certain airplanes, a
potential terminating action
modification of the center wing box
area. The FAA issued AD 2022–14–10 to
address fatigue cracking of the front spar
vertical stringers on the wings, which, if
not corrected, could result in reduced
structural integrity of the airplane.
The NPRM published in the Federal
Register on March 22, 2024 (89 FR
20364). The NPRM was prompted by
AD 2023–0205, dated November 21,
2023 (EASA AD 2023–0205) (also
referred to as the MCAI), issued by
EASA, which is the Technical Agent for
the Member States of the European
Union. The MCAI states that analysis of
the full-scale certification fatigue testing
findings indicated that Model A321–
271N airplanes are also subject to the
unsafe condition. Fatigue cracking of
the front spar vertical stringers on the
wings, if not detected and corrected,
could lead to crack propagation,
possibly resulting in reduced structural
integrity of the airplane.
In the NPRM, the FAA proposed to
continue to require the actions in AD
Discussion of Final Airworthiness
Directive
Comments
The FAA received a comment from
United Airlines who supported the
NPRM without change.
Additional Changes Made to This AD
The FAA added paragraphs (h)(5) and
(6) of this AD to clarify who can provide
approval instructions for certain actions.
These paragraphs correspond to actions
retained from AD 2022–14–10 and were
inadvertently omitted from the
proposed AD.
detailed inspections for cracking of the
radius of the front spar vertical
stringers, horizontal floor beam radius
and fastener holes of the front spear
vertical stringers on FR 36, and for
installing new fasteners. EASA AD
2023–0205 further describes procedures
for repetitive high frequency eddy
current (HFEC) inspections for cracking
of the horizontal floor beam, repetitive
HFEC inspections for cracking of the
fastener holes of the front spar vertical
stringers on FR 36, repetitive rototest
inspections of the fastener holes of the
spar vertical stringers, and repair. EASA
AD 2023–0205 also describes
procedures for the modification of the
center wing box area. The modification
is required for airplanes in configuration
1, 2 or 3; and for airplanes in
configuration 5, 6, or 7, the modification
is optional and is a terminating action
for the repetitive inspections when done
within a specified time frame. The
modification includes related
investigative and corrective actions.
Related investigative actions include an
HFEC inspection on the radius of the rib
flanges, a rototest inspection of the
fastener holes, detailed and HFEC
inspections for cracking on the cut
edges, detailed and rototest inspections
on all open fastener holes, and an
inspection to determine if secondary
structure brackets are installed.
Corrective actions include rework of the
secondary structure bracket and repair.
This service information 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.
Conclusion
This product has been approved by
the aviation authority of another
country and is approved for operation in
the United States. Pursuant to the FAA’s
bilateral agreement with this State of
Design Authority, it has notified the
FAA of the unsafe condition described
in the MCAI referenced above. The FAA
reviewed the relevant data, considered
the comment 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 this product. 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.
Costs of Compliance
Related Service Information Under 1
CFR Part 51
EASA AD 2023–0205 specifies
procedures for repetitive special
The FAA estimates that this AD
affects 1,755 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Inspection, per inspection
cycle.
Labor cost
25 work-hours × $85 per
hour = $2,125.
Parts cost
Cost per product
Up to $100 ........................
Up to $2,225 .....................
Cost on U.S. operators
Up to $3,904,875.
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ESTIMATED COSTS FOR OPTIONAL ACTIONS
Labor cost
Parts cost
Up to 409 work-hours × $85 per hour = Up to $34,765 .........................
Up to $66,050 ................................
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition actions specified in
this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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Cost per product
Up to $100,815.
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
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Federal Register / Vol. 89, No. 131 / Tuesday, July 9, 2024 / Rules and Regulations
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
The FAA determined that this 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
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) 2022–14–10, Amendment 39–
22115 (87 FR 42315, July 15, 2022); and
■ b. Adding the following new AD:
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■
■
2024–12–01 Airbus SAS: Amendment 39–
22765; Docket No. FAA–2024–0757;
Project Identifier MCAI–2023–01205–T.
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(a) Effective Date
This airworthiness directive (AD) is
effective August 13, 2024.
(b) Affected ADs
This AD replaces AD 2022–14–10,
Amendment 39–22115 (87 FR 42315, July 15,
2022) (AD 2022–14–10).
(c) Applicability
This AD applies to the Airbus SAS
airplanes identified in paragraphs (c)(1)
through (4) of this AD, certificated in any
category, as identified in European Union
Aviation Safety Agency (EASA) AD 2023–
0205, dated November 21, 2023 (EASA AD
2023–0205).
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –216,
–231, –232, and –233 airplanes.
(4) Model A321–111, –112, –131, –211,
–212, –213, –231, –232, and –271N airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report that,
during a center fuselage certification fullscale fatigue test, cracks were found on the
front spar vertical stringer at a certain frame.
This AD was also prompted by a
determination that Model A321 airplanes
that have incorporated modification 160021
are also subject to the unsafe condition. The
FAA is issuing this AD to address fatigue
cracking of the front spar vertical stringers on
the wings. The unsafe condition, if not
addressed, could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2023–0205.
(h) Exceptions to EASA AD 2023–0205
(1) Where EASA AD 2023–0205 refers to
‘‘22 November 2021 [the effective date of
EASA AD 2021–0241],’’ this AD requires
using August 19, 2022 (the effective date of
AD 2022–14–10).
(2) Where EASA AD 2023–0205 refers to its
effective date, this AD requires using the
effective date of this AD.
(3) This AD does not adopt the ‘‘Remarks’’
section of EASA AD 2023–0205.
(4) Where paragraph (5) of EASA AD 2023–
0205 specifies ‘‘if any crack is found, before
next flight, contact Airbus for approved
corrective action instructions and accomplish
those instructions accordingly,’’ this AD
requires replacing that text with ‘‘if any crack
is found, the crack must be repaired before
further flight using a method approved by the
Manager, International Validation Branch,
FAA; or EASA; or Airbus SAS’s EASA
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56197
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.’’
(5) Where paragraph (4) of EASA AD 2023–
0205 specifies actions for airplanes repaired
‘‘in accordance with instructions approved
by EASA or approved under the authority of
Airbus Design Organization Approval (DOA)
privileges,’’ this AD requires replacing that
text with ‘‘using a method approved by the
Manager, International Validation Branch,
FAA; or EASA; or Airbus SAS’s EASA DOA.
If approved by the DOA, the approval must
include the DOA-authorized signature.’’
(6) Where paragraph (9) of EASA AD 2023–
0205 specifies approval ‘‘by Airbus DOA,’’
this AD requires replacing that text with ‘‘by
the Manager, International Validation
Branch, FAA; or EASA; or Airbus SAS’s
EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized
signature.’’
(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2023–0205 specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
(j) Additional AD Provisions
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: 9-AVS-AIR-730-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 SAS’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (j)(2) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
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Federal Register / Vol. 89, No. 131 / Tuesday, July 9, 2024 / Rules and Regulations
(k) Additional Information
For more information about this AD,
contact Timothy Dowling, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone 206–
231–3667; email timothy.p.dowling@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2023–0205, dated November 21,
2023.
(ii) [Reserved]
(3) For EASA AD 2023–0205, 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 service information
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 June 5, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2024–14868 Filed 7–8–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–1640; Project
Identifier AD–2022–00283–E; Amendment
39–22768; AD 2024–12–04]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
lotter on DSK11XQN23PROD with RULES1
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all Pratt
& Whitney (PW) Model PW2037,
PW2037M, and PW2040 engines with a
certain high-pressure turbine (HPT) 2nd
stage blade assembly installed. This AD
was prompted by an in-flight shutdown
SUMMARY:
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15:55 Jul 08, 2024
Jkt 262001
(IFSD) caused by the fracture of HPT
2nd stage turbine hub assembly lugs,
which resulted in blade liberation and
a titanium fire in the high-pressure
compressor (HPC). This AD requires a
visual inspection of the HPT 2nd stage
blade assemblies for missing contact
marks, a dimensional shadowgraph
inspection of the HPT 2nd stage blade
assemblies for blade root profile
dimensional deviations, and an eddy
current inspection (ECI) of the HPT 2nd
stage turbine hub assembly for
conforming slot flatness. This AD also
requires removal from service and
replacement of any HPT 2nd stage
turbine hub assembly or HPT 2nd stage
blade assembly that does not pass any
inspection. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective August 13,
2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 13, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–1640; 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 service information, contact
Pratt & Whitney, 400 Main Street, East
Hartford, CT 06118; phone: (860) 565–
0140; email: help24@pw.utc.com;
website: connect.prattwhitney.com.
• You may view this service
information at the FAA, Airworthiness
Products Section, 1200 District Avenue,
Burlington, MA 01803. 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–2023–1640.
FOR FURTHER INFORMATION CONTACT:
Carol Nguyen, Aviation Safety Engineer,
FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–
7655; email: carol.nguyen@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 all PW Model PW2037,
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PW2037M, and PW2040 engines with a
certain HPT 2nd stage blade assembly
installed. The NPRM published in the
Federal Register on August 25, 2023 (88
FR 58114). The NPRM was prompted by
an IFSD caused by the fracture of HPT
2nd stage turbine hub assembly lugs,
which resulted in blade liberation and
a titanium fire in the HPC.
In the NPRM, the FAA proposed to
require a visual inspection of the HPT
2nd stage blade assemblies for missing
contact marks, a dimensional
shadowgraph inspection of the HPT 2nd
stage blade assemblies for blade root
profile dimensional deviations, and an
ECI of the HPT 2nd stage turbine hub
assembly for conforming slot flatness.
The NPRM also proposed to require
removal from service and replacement
of any HPT 2nd stage turbine hub
assembly or HPT 2nd stage blade
assembly that does not pass any
inspection. The FAA is issuing this AD
to address the unsafe condition on these
products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from six
commenters. The commenters were The
Boeing Company (Boeing), Delta Air
Lines (Delta), European Air Transport
(EAT), FedEx Express (FedEx), MTU
Maintenance Hannover GmbH (MTU),
and United Parcel Service (UPS). Boeing
supported the NPRM without change.
The following presents the comments
received from Delta, EAT, FedEx, MTU,
and UPS on the NPRM and the FAA’s
response to each comment.
Request To Exempt Certain Hubs From
NPRM Cycle Limit
Delta requested that the FAA allow
hubs with an ECI performed on 25% of
the blade slots to be inspected in
accordance with the updated
dimensional ECI procedure at the next
piece part exposure of the HPT 2nd
stage turbine hub assembly, rather than
being inspected within the cycle limit of
the NPRM. Delta noted that Method 2,
Step 4 in PW Alert Service Bulletin
PW2000 A72–777, Initial Issue, dated
September 29, 2021 (PW2000 A72–777,
Initial Issue) requires that HPT 2nd
stage turbine hub assemblies be
installed that have passed the HPT 2nd
stage turbine hub assembly ECI
inspection specified in PW2000 Engine
Manual, Task 72–52–16–200–006, but
does not provide guidance on the
required amount of slots to be
inspected. Delta also noted that in the
beginning of the HPT Field Management
Program for this unsafe condition and
E:\FR\FM\09JYR1.SGM
09JYR1
]]>Agencies
[Federal Register Volume 89, Number 131 (Tuesday, July 9, 2024)]
[Rules and Regulations]
[Pages 56195-56198]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-14868]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0757; Project Identifier MCAI-2023-01205-T;
Amendment 39-22765; AD 2024-12-01]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2022-14-
10, which applied to certain Airbus SAS Model A318 series airplanes;
Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes;
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
AD 2022-14-10 required repetitive inspections for cracking of the
radius of the front spar vertical stringers and the horizontal floor
beam on a certain frame (FR), repetitive inspections for cracking of
the fastener holes of the front spar vertical stringers on that frame,
and repair if necessary. AD 2022-14-10 also provided, for certain
airplanes, a modification of the center wing box area that terminates
the repetitive inspections under certain conditions. Since the FAA
issued AD 2022-14-10, an additional airplane model has been identified
that is also subject to the unsafe condition. This AD continues to
require the actions in AD 2022-14-10 and adds Model A321-271N airplanes
to the applicability, as specified in a European Union Aviation Safety
Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective August 13, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 13,
2024.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2024-0757; 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 EASA material, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; website easa.europa.eu. You may find this material
on the EASA website at ad.easa.europa.eu.
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-2024-0757.
FOR FURTHER INFORMATION CONTACT: Timothy Dowling, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 206-231-3667; email [email protected].
SUPPLEMENTARY INFORMATION:
[[Page 56196]]
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2022-14-10, Amendment 39-22115 (87 FR
42315, July 15, 2022), (AD 2022-14-10). AD 2022-14-10 applied to
certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, -
113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212,
-214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. AD 2022-14-10 required
repetitive inspections for cracking of the radius of the front spar
vertical stringers and the horizontal floor beam on FR 36, repetitive
inspections for cracking of the fastener holes of the front spar
vertical stringers on FR 36, and repair if necessary, and, for certain
airplanes, a potential terminating action modification of the center
wing box area. The FAA issued AD 2022-14-10 to address fatigue cracking
of the front spar vertical stringers on the wings, which, if not
corrected, could result in reduced structural integrity of the
airplane.
The NPRM published in the Federal Register on March 22, 2024 (89 FR
20364). The NPRM was prompted by AD 2023-0205, dated November 21, 2023
(EASA AD 2023-0205) (also referred to as the MCAI), issued by EASA,
which is the Technical Agent for the Member States of the European
Union. The MCAI states that analysis of the full-scale certification
fatigue testing findings indicated that Model A321-271N airplanes are
also subject to the unsafe condition. Fatigue cracking of the front
spar vertical stringers on the wings, if not detected and corrected,
could lead to crack propagation, possibly resulting in reduced
structural integrity of the airplane.
In the NPRM, the FAA proposed to continue to require the actions in
AD 2022-14-10 and add Model A321-271N airplanes to the applicability,
as specified in EASA AD 2023-0205. The FAA is issuing this AD to
address the unsafe condition on these products.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2024-0757.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comment from United Airlines who supported the
NPRM without change.
Additional Changes Made to This AD
The FAA added paragraphs (h)(5) and (6) of this AD to clarify who
can provide approval instructions for certain actions. These paragraphs
correspond to actions retained from AD 2022-14-10 and were
inadvertently omitted from the proposed AD.
Conclusion
This product has been approved by the aviation authority of another
country and is approved for operation in the United States. Pursuant to
the FAA's bilateral agreement with this State of Design Authority, it
has notified the FAA of the unsafe condition described in the MCAI
referenced above. The FAA reviewed the relevant data, considered the
comment 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 this product. 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.
Related Service Information Under 1 CFR Part 51
EASA AD 2023-0205 specifies procedures for repetitive special
detailed inspections for cracking of the radius of the front spar
vertical stringers, horizontal floor beam radius and fastener holes of
the front spear vertical stringers on FR 36, and for installing new
fasteners. EASA AD 2023-0205 further describes procedures for
repetitive high frequency eddy current (HFEC) inspections for cracking
of the horizontal floor beam, repetitive HFEC inspections for cracking
of the fastener holes of the front spar vertical stringers on FR 36,
repetitive rototest inspections of the fastener holes of the spar
vertical stringers, and repair. EASA AD 2023-0205 also describes
procedures for the modification of the center wing box area. The
modification is required for airplanes in configuration 1, 2 or 3; and
for airplanes in configuration 5, 6, or 7, the modification is optional
and is a terminating action for the repetitive inspections when done
within a specified time frame. The modification includes related
investigative and corrective actions. Related investigative actions
include an HFEC inspection on the radius of the rib flanges, a rototest
inspection of the fastener holes, detailed and HFEC inspections for
cracking on the cut edges, detailed and rototest inspections on all
open fastener holes, and an inspection to determine if secondary
structure brackets are installed. Corrective actions include rework of
the secondary structure bracket and repair.
This service information 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 1,755 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection, per inspection cycle 25 work-hours x Up to $100........ Up to $2,225...... Up to $3,904,875.
$85 per hour =
$2,125.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
------------------------------------------------------------------------
Up to 409 work-hours x $85 per Up to $66,050..... Up to $100,815.
hour = Up to $34,765.
------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions 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
[[Page 56197]]
detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this 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) 2022-14-10, Amendment 39-22115
(87 FR 42315, July 15, 2022); and
0
b. Adding the following new AD:
2024-12-01 Airbus SAS: Amendment 39-22765; Docket No. FAA-2024-0757;
Project Identifier MCAI-2023-01205-T.
(a) Effective Date
This airworthiness directive (AD) is effective August 13, 2024.
(b) Affected ADs
This AD replaces AD 2022-14-10, Amendment 39-22115 (87 FR 42315,
July 15, 2022) (AD 2022-14-10).
(c) Applicability
This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (4) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2023-0205, dated November 21, 2023 (EASA AD 2023-0205).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, -232,
and -271N airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report that, during a center fuselage
certification full-scale fatigue test, cracks were found on the
front spar vertical stringer at a certain frame. This AD was also
prompted by a determination that Model A321 airplanes that have
incorporated modification 160021 are also subject to the unsafe
condition. The FAA is issuing this AD to address fatigue cracking of
the front spar vertical stringers on the wings. The unsafe
condition, if not addressed, could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2023-0205.
(h) Exceptions to EASA AD 2023-0205
(1) Where EASA AD 2023-0205 refers to ``22 November 2021 [the
effective date of EASA AD 2021-0241],'' this AD requires using
August 19, 2022 (the effective date of AD 2022-14-10).
(2) Where EASA AD 2023-0205 refers to its effective date, this
AD requires using the effective date of this AD.
(3) This AD does not adopt the ``Remarks'' section of EASA AD
2023-0205.
(4) Where paragraph (5) of EASA AD 2023-0205 specifies ``if any
crack is found, before next flight, contact Airbus for approved
corrective action instructions and accomplish those instructions
accordingly,'' this AD requires replacing that text with ``if any
crack is found, the crack must be repaired before further flight
using a method approved by the Manager, International Validation
Branch, FAA; or EASA; or Airbus SAS's EASA Design Organization
Approval (DOA). If approved by the DOA, the approval must include
the DOA-authorized signature.''
(5) Where paragraph (4) of EASA AD 2023-0205 specifies actions
for airplanes repaired ``in accordance with instructions approved by
EASA or approved under the authority of Airbus Design Organization
Approval (DOA) privileges,'' this AD requires replacing that text
with ``using a method approved by the Manager, International
Validation Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.''
(6) Where paragraph (9) of EASA AD 2023-0205 specifies approval
``by Airbus DOA,'' this AD requires replacing that text with ``by
the Manager, International Validation Branch, FAA; or EASA; or
Airbus SAS's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.''
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2023-0205
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
(j) Additional AD Provisions
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: [email protected]. 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 SAS's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (j)(2) of this AD, if any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
[[Page 56198]]
(k) Additional Information
For more information about this AD, contact Timothy Dowling,
Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 206-231-3667; email
[email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2023-0205,
dated November 21, 2023.
(ii) [Reserved]
(3) For EASA AD 2023-0205, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; website easa.europa.eu. You may find this EASA
AD on the EASA website at ad.easa.europa.eu.
(4) You may view this service information 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 June 5, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-14868 Filed 7-8-24; 8:45 am]
BILLING CODE 4910-13-P
