[Federal Register Volume 90, Number 98 (Thursday, May 22, 2025)]
[Rules and Regulations]
[Pages 21841-21845]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-09222]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2661; Project Identifier MCAI-2024-00269-T;
Amendment 39-23041; AD 2025-10-07]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2015-02-
14, which applied to all Airbus SAS Model A318 series airplanes; A319-
111, -112, -113, -114, -115, -131, -132, and -133 airplanes; A320-211,
-212, -214, -231, -232, and -233 airplanes; and A321-111, -112, -131, -
211, -212,
[[Page 21842]]
-213, -231, and -232 airplanes. AD 2015-02-14 required repetitive
inspections for cracking, damage, correct installation, and correct
adjustment of the main landing gear (MLG) door hinge and actuator
fittings on the keel beam, corrective actions if necessary, and
revision of the existing maintenance or inspection program, as
applicable. Since the FAA issued AD 2015-02-14, a new design of the MLG
door keel beam hinge and actuator fitting was developed. This AD
continues to require the actions specified in AD 2015-02-14, adds an
optional terminating action, and revises the applicability, 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 June 26, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 26,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. 2024-2661; 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 identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999
000; email [email protected]. 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-2024-2661.
FOR FURTHER INFORMATION CONTACT: Tim Dowling, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-231-3667;
email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2015-02-14, Amendment 39-18081 (80 FR
11096, March 2, 2015) (AD 2015-02-14). AD 2015-02-14 applied to all
Airbus SAS Model A318 series airplanes; Model A319-111, -112, -113, -
114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214,
-231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. AD 2015-02-14 required repetitive
inspections for cracking, damage, correct installation, and correct
adjustment of the MLG door hinge and actuator fittings on the keel
beam; corrective actions if necessary; and revision of the existing
maintenance or inspection program, as applicable. The FAA issued AD
2015-02-14 to detect and correct cracking on the MLG door hinge fitting
and actuator fitting on the keel beam, which could lead to in-flight
detachment of an MLG door, possibly resulting in injury to persons on
the ground and/or damage to the airplane.
The NPRM was published in the Federal Register on December 17, 2024
(89 FR 102016). The NPRM was prompted by AD 2024-0097R2, dated July 12,
2024 (EASA AD 2024-0097R2) (also referred to as the MCAI), which
superseded EASA AD 2012-0118, dated July 4, 2012 (which corresponds to
FAA AD 2015-02-14), issued by EASA, which is the Technical Agent for
the Member States of the European Union. The MCAI states that after
EASA AD 2012-0118 was issued, a new design of the MLG door keel beam
hinge and actuator fitting was certified for current engine option
(CEO) airplanes (Model A318-111, A318-112, A318-121, A318-122; A319-
111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A319-
133; A320-211, A320-212, A320-214, A320-215, A320-216, A320-231, A320-
232, A320-233; and A321-111, A321-112, A321-131, A321-211, A321-212,
A321-213, A321-231, and A321-232 airplanes) and new engine option (NEO)
airplanes (Model A319-151N, A319-153N, A319-171N; A320-251N, A320-252N,
A320-253N, A320-271N, A320-272N, A320-273N; A321-251N, A321-251NX,
A321-252N, A321-252NX, A321-253N, A321-253NX, A321-271N, A321-271NX,
A321-272N, and A321-272NX airplanes). The MCAI states that the
applicability is expanded to include the NEO airplanes which are
subject to the same unsafe condition. Model A320-215 airplanes are not
certificated by the FAA and are not included on the U.S. type
certificate data sheet; this AD therefore does not include those
airplanes in the applicability.
In the NPRM, the FAA proposed to continue to require the actions
specified in AD 2015-02-14, add an optional terminating action, and
revise the applicability, as specified in EASA AD 2024-0097R2. The FAA
is issuing this AD to detect and correct cracking on the MLG door hinge
fitting and actuator fitting on the keel beam, which could lead to in-
flight detachment of a MLG door, possibly resulting in injury to
persons on the ground and/or damage to the airplane.
You may examine the MCAI in the AD docket at regulations.gov under
Docket No. FAA-2024-2661.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from the Air Line Pilots Association,
International (ALPA) and United Airlines, who supported the NPRM
without change.
The FAA received additional comments from American Airlines (AA),
Delta Air Lines (Delta), and Spirit Airlines. The following presents
the comments received on the NPRM and the FAA's response to each
comment.
Request To Correct a Typographical Error
AA and Delta requested the FAA revise paragraph (k)(1)(ii) of the
proposed AD to read ``AMOCs approved previously for FAA AD 2015-02-14
are approved as AMOCs for the corresponding provisions of EASA AD 2024-
0097R2 that are required by paragraph (g) of this AD.'' (Paragraph
(k)(1)(ii) of the proposed AD inadvertently referenced EASA AD 2012-
0118, instead of EASA AD 2024-0097R2.)
The FAA agrees and has revised paragraph (k)(1)(ii) of this AD
accordingly.
Request To Clarify Superseding Relationship Between Airworthiness
Limitations Tasks and Airbus Service Bulletins
Spirit Airlines requested that when the FAA issues an AD to
incorporate Airworthiness Limitations Section (ALS) Part 2, Revision 11
(which is scheduled for release November 2024), it include a caveat or
clarification detailing the superseding relationship between
Airworthiness Limitations (ALI) tasks 533154-10-1 and 533154-03-2, and
Airbus Service Bulletin A320-53-1195, Airbus Service Bulletin A320-53-
1325, Airbus Service Bulletin
[[Page 21843]]
A320-53-1196, and Airbus Service Bulletin A320-53-1326. Spirit Airlines
stated that it will not be able to incorporate ALI tasks 533154-10-1
and 533154-03-2 and Airbus Service Bulletin A320-53-1195, Airbus
Service Bulletin A320-53-1325, Airbus Service Bulletin A320-53-1196,
and Airbus Service Bulletin A320-53-1326 simultaneously, and a clear
explanation will help avoid any confusion or conflicts when
implementing the updated AD.
The FAA does not agree with the request. Airbus will update the ALS
as needed to address the superseding relationship between ALI tasks
533154-10-1 and 533154-03-2, and Airbus Service Bulletin A320-53-1195,
Airbus Service Bulletin A320-53-1325, Airbus Service Bulletin A320-53-
1196, and Airbus Service Bulletin A320-53-1326. The FAA has not changed
this AD in this regard.
Request for a Grace Period
Delta requested the FAA allow a 3-month grace period to comply with
the initial inspection requirements in paragraphs (1) and (2) of EASA
AD 2024-0097R2 for NEO airplanes. Delta requested this grace period to
continue to use ALI task 533154-03-2 in lieu of Airbus Service Bulletin
A320-53-1325, as referenced in paragraph (1) of EASA AD 2024-0097R2;
and to continue to use ALI task 533154-04-2 or ALI task 533154-10-1 in
lieu of Airbus Service Bulletin A320-53-1326 referenced in paragraph
(2) of EASA AD 2024-0097R2. Delta noted that ALI tasks are mandatory
inspections; therefore, until the final rule is issued, U.S. operators
would have no authority to use those service bulletins in lieu of those
ALI inspections. Delta stated that the current language in the proposed
AD would require, from the effective date of the AD, that operators
immediately switch from the ALI tasks to the Airbus service bulletins.
Delta added that this could be logistically very difficult, especially
if the ALI inspection is being performed on several airplanes on the
AD's effective date.
The FAA agrees to include a grace period for the transition for NEO
airplanes only. CEO airplanes have been subject to the compliance times
specified in AD 2015-02-14 and therefore do not need a grace period.
The FAA has added paragraphs (h)(6) and (7) to this AD accordingly.
Request To Remove Ultrasonic Inspection
AA requested the FAA revise paragraph (g) of the proposed AD to
require operators to also comply with the changes detailed in Airbus
Service Bulletin Information Transmission/Operators Information
Transmission (SBIT/OIT) 23-0074, Revision 01, dated June 7, 2024.
Airbus SBIT/OIT 23-0074 removes the ``ultrasonic'' inspection wording
from Airbus Service Bulletin A320-53-1196 and Airbus Service Bulletin
A320-53-1326. AA stated that the Non-Destructive Testing Manual (NTM)
referenced in the Airbus service bulletins does not contain ultrasonic
inspection instructions.
The FAA agrees that the ultrasonic inspection is not necessary and
has added paragraph (h)(8) of this AD to clarify the requirement
accordingly.
Additional Changes to This AD
The FAA revised paragraph (i) of this AD, including removing
paragraphs (i)(1) and (2) of the proposed AD. The FAA determined that
the actions specified in paragraph (i) of this AD are only applicable
to the CEO airplanes, since the NEO airplanes are not in the ALI
documents specified in paragraph (i) of this AD.
Conclusion
These products have been approved by the civil aviation authority
of another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, that authority has notified the FAA of the unsafe condition
described in the MCAI referenced above. 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 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.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2024-0097R2 specifies procedures for repetitive detailed
visual, high frequency eddy current (HFEC), and ultrasonic inspections
of the MLG door actuator fittings on the keel beam for discrepancies
(cracks, wear marks, migration of the plain bush, loose flanged bush,
and other damage). Corrective actions include replacement of the
affected MLG door actuator fitting, modification of the actuator and
hinge fittings at the MLG door, and repair of any cracks, loose flanged
bush axial, bush migration, wear marks underneath the bolt head, and
other damage on the left and right sides of the airplane.
EASA AD 2024-0097R2 also specifies procedures for repetitive
detailed visual and HFEC inspections of the MLG door hinge fittings on
the keel beam for discrepancies (cracks, migration of the plain bush,
wear marks, and other damage). Corrective actions include replacement
of the MLG door hinge fitting, modification of the actuator and hinge
fittings at the MLG door, and repair of any bush migration, wear marks
underneath the bolt head, and other damage on the left and right sides
of the airplane.
EASA AD 2024-0097R2 also specifies procedures for modifying the
actuator and hinge fittings at the MLG door for the following parts:
MLG actuator fittings, hinge fittings, and connecting plates between
frame (FR) 42 and FR 43; accomplishment of this modification terminates
the repetitive inspections.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 1,766 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspections............................ 20 work-hours x $85 per $0 $1,700 $3,002,200
hour = $1,700.
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[[Page 21844]]
Estimated Costs for Optional Actions
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Cost per
Action Labor cost Parts cost product
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Modify the actuator and hinge fittings at MLG 82 work-hours x $85 per hour = $52,000 $58,970
door. $6,970.
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The FAA estimates the following costs to do any fitting replacement
that would be required based on the results of any required actions.
The FAA has no way of determining the number of aircraft that might
need a fitting replacement:
Estimated Costs of On-Condition Actions
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Labor cost Parts cost Cost per product
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38 work-hours x $85 per hour = $6,742 $9,972
$3,230.........................
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The FAA has received no definitive data on which to base the cost
estimates for the repairs specified in this AD.
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all known costs
in the cost estimate.
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) 2015-02-14, Amendment 39-18081
(80 FR 11096, March 2, 2015); and
0
b. Adding the following new AD:
2025-10-07 Airbus SAS: Amendment 39-23041; Docket No. FAA-2024-2661;
Project Identifier MCAI-2024 00269-T.
(a) Effective Date
This airworthiness directive (AD) is effective June 26, 2025.
(b) Affected ADs
This AD replaces AD 2015-02-14, Amendment 39-18081 (80 FR 11096,
March 2, 2015) (AD 2015-02-14).
(c) Applicability
This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (7) of this AD, certificated in any
category, as identified in European Union Aviation Safety Agency
(EASA) AD 2024-0097R2, dated July 12, 2024 (EASA AD 2024-0097R2).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A319-151N, -153N, and -171N airplanes.
(4) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(5) Model A320-251N, -252N, -253N, -271N, -272N, and -273N
airplanes.
(6) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(7) Model A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -
271N, -271NX, -272N, and -272NX airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks on the main landing
gear (MLG) door hinge fitting and actuator fitting on the keel beam.
The FAA is issuing this AD to detect and correct cracking on the MLG
door hinge fitting and actuator fitting on the keel beam. The unsafe
condition, if not addressed, could lead to in-flight detachment of
an MLG door, possibly resulting in injury to persons on the ground
and/or damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (j) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, EASA AD 2024-0097R2.
(h) Exceptions to EASA AD 2024-0097R2
(1) Where EASA AD 2024-0097R2 refers to ``16 May 2024 [the
effective date of the original issue of this AD],'' this AD requires
using the effective date of this AD.
(2) Where EASA AD 2024-0097R2 refers to ``18 July 2012 [the
effective date of EASA AD
[[Page 21845]]
2012-0118],'' this AD requires using April 6, 2015 (the effective
date of AD 2015-02-14).
(3) Where EASA AD 2024-0097R2 specifies to ``contact Airbus for
approved repair instructions and, within the compliance time
specified therein, accomplish those instructions accordingly'',
replace that text with ``all repairs must be done before further
flight using a method approved by the Manager, AIR-520, Continued
Operational Safety 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''.
(4) Where paragraph (6) of EASA AD 2024-0097R2 describes an
airplane that has been inspected per ``ALI task 533154-03-2, 533154-
04-2 or 533154-10-1, or in accordance with the instructions of
inspection SB 1 (at any Revision) or inspection SB 2 (at any
Revision)'', replace that text with ``ALI task 533154-03-2, 533154-
04-2 or 533154-10-1, or in accordance with the instructions of
Airbus SB A320-53-1195 or SB A320-53-1325 at any Revision, as
applicable, or Airbus SB A320-53-1196 or SB A320-53-1326 at any
Revision, as applicable''.
(5) This AD does not adopt the ``Remarks'' section of EASA AD
2024-0097R2.
(6) For airplanes identified in paragraphs (c)(3), (5), and (7)
of this AD: Where paragraph (1) of EASA AD 2024-0097R2 specifies
accomplishing inspection ``in accordance with the instructions of
the inspection SB 1, as applicable'', this AD requires replacing
that text with ``in accordance with the instructions of the
inspection SB 1, as applicable, or Airworthiness Limitations task
533154-03-2. As of 3 months after the effective date of FAA AD 2025-
10-07, only the inspection SB 1, as applicable, may be used''.
(7) For airplanes identified in paragraphs (c)(3), (5), and (7)
of this AD: Where paragraph (2) of EASA AD 2024-0097R2 specifies
accomplishing inspection ``in accordance with the instructions of
the inspection SB 2, as applicable'', this AD requires replacing
that text with ``in accordance with the instructions of the
inspection SB 2, as applicable, or Airworthiness Limitations task
533154-04-2 or task 533154-10-1. As of 3 months after the effective
date of FAA AD 2025-10-07, only the inspection SB 2, as applicable,
may be used''.
(8) Where the ``Inspection SB 2'' as defined in EASA AD 2024-
0097R2 specifies to do an ultrasonic inspection in addition to a
high frequency eddy current (HFEC) inspection, this AD does not
require an ultrasonic inspection.
(i) Retained Maintenance or Inspection Program Revision, With No
Changes
This paragraph restates the requirements of paragraph (k) of AD
2015-02-14 with no changes. For airplanes identified in paragraphs
(c)(1), (2), (4), and (6) of this AD: After April 6, 2015 (the
effective date of AD 2015-02-14) and before further flight after
doing the initial inspections required by paragraph (g) of this AD:
Revise the maintenance or inspection program, as applicable, to
remove Task 533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part
2-Damage Tolerant Airworthiness Limitations Items (DT ALI), Revision
01, dated April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated
October 2009; or Airbus A318/A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE-M4/95A.0252/96, Issue 11, dated September
2010. The actions required by this AD take precedence over Task
533154-02-1 of the Airbus A318/A319/A320/A321 ALS Part 2 Damage
Tolerant Airworthiness Limitation Items (DT ALI), Revision 01, dated
April 4, 2012; Airbus A318/A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009;
and Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 11, dated September 2010.
(j) No Reporting Requirement
Although the material referenced in EASA AD 2024-0097R2
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
(k) Additional AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager, AIR-
520, Continued Operational Safety Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or responsible Flight Standards Office,
as appropriate. If sending information directly to the manager of
the Continued Operational Safety Branch, send it to the attention of
the person identified in paragraph (l) of this AD and email to:
[email protected].
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(ii) AMOCs approved previously for AD 2015-02-14 are approved as
AMOCs for the corresponding provisions of EASA AD 2024-0097R2 that
are required by paragraph (g) of this AD.
(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, AIR-520,
Continued Operational Safety Branch, FAA; or EASA; or Airbus SAS's
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (k)(2) of this AD, if any material 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.
(l) Additional Information
For more information about this AD, contact Tim Dowling,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; phone: 206-231-3667; email: [email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the material listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2024-0097R2,
dated July 12, 2024.
(ii) [Reserved]
(3) For EASA material identified in this AD, 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.
(4) You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St.,
Des Moines, WA. For information on the availability of this material
at the FAA, call 206-231-3195.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on May 12, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-09222 Filed 5-21-25; 8:45 am]
BILLING CODE 4910-13-P