Proposed Rule2024-29620
Airworthiness Directives; Airbus SAS Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
December 17, 2024
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2015-02-14, which applies 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, -213, -231, and -232 airplanes. AD 2015-02-14 requires 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 proposed AD would continue to require the actions specified in AD 2015-02-14, add an optional terminating action, and revise the applicability, as specified in a European Union Aviation Safety Agency (EASA) AD, which is proposed for incorporation by reference (IBR). The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 89 Issue 242 (Tuesday, December 17, 2024)</title>
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[Federal Register Volume 89, Number 242 (Tuesday, December 17, 2024)]
[Proposed Rules]
[Pages 102016-102019]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-29620]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 89, No. 242 / Tuesday, December 17, 2024 /
Proposed Rules
[[Page 102016]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2661; Project Identifier MCAI-2024-00269-T]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2015-02-14, which applies 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, -213, -231, and -232 airplanes. AD
2015-02-14 requires 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 proposed AD would continue to require the actions
specified in AD 2015-02-14, add an optional terminating action, and
revise the applicability, as specified in a European Union Aviation
Safety Agency (EASA) AD, which is proposed for incorporation by
reference (IBR). The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this proposed AD by January 31,
2025.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2661; 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 NPRM, the mandatory continuing airworthiness
information (MCAI), any comments received, and other information. The
street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For EASA material identified in this proposed AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email <a href="/cdn-cgi/l/email-protection#6d2c291e2d080c1e0c4308181f021d0c430818"><span class="__cf_email__" data-cfemail="7031340330151103115e1505021f00115e1505">[email protected]</span></a>; website easa.europa.eu. You may
find this material on the EASA website at ad.easa.europa.eu.
<bullet> You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call 206-231-3195.
FOR FURTHER INFORMATION CONTACT: Tim Dowling, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 206-
231-3667; email: <a href="/cdn-cgi/l/email-protection#abdfc2c6c4dfc3d285db85cfc4dcc7c2c5ccebcdcaca85ccc4dd"><span class="__cf_email__" data-cfemail="d7a3bebab8a3bfaef9a7f9b3b8a0bbbeb9b097b1b6b6f9b0b8a1">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2024-2661;
Project Identifier MCAI-2024-00269-T'' at the beginning of your
comments. The most helpful comments reference a specific portion of the
proposal, explain the reason for any recommended change, and include
supporting data. The FAA will consider all comments received by the
closing date and may amend the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Tim
Dowling, Aviation Safety Engineer, FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 206-231-3667; email:
<a href="/cdn-cgi/l/email-protection#c6b2afaba9b2aebfe8b6e8a2a9b1aaafa8a186a0a7a7e8a1a9b0"><span class="__cf_email__" data-cfemail="285c4145475c40510658064c475f4441464f684e4949064f475e">[email protected]</span></a>. Any commentary that the FAA receives which
is not specifically designated as CBI will be placed in the public
docket for this rulemaking.
Background
The FAA issued AD 2015-02-14, Amendment 39-18081 (80 FR 11096,
March 2, 2015) (AD 2015-02-14), for 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, -213, -231, and -232 series
airplanes. AD 2015-02-14 was prompted by MCAI originated by the
European Union Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union. EASA issued AD 2012-
0118, dated July 4, 2012 (EASA AD 2012-0118) (which corresponds to FAA
AD
[[Page 102017]]
2015-02-14), to correct an unsafe condition.
AD 2015-02-14 requires 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. 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.
Actions Since AD 2015-02-14 Was Issued
Since the FAA issued AD 2015-02-14, EASA superseded AD 2012-0118,
dated July 4, 2012, and issued EASA AD 2024-0097R2, dated July 12, 2024
(EASA AD 2024-0097R2) (referred to after this as the MCAI) to correct
an unsafe condition on certain Airbus SAS Model A318-111, -112, -121, -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, -
133, -151N, -153N, and -171N airplanes; Model A320-211, -212, -214, -
215, -216, -231, -232, -233, -251N, -252N, -253N, -271N, -272N, and -
273N airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231,
-232, -251N, -251NX, -252N, -252NX, -253N, -253NX, -271N, -271NX, -
272N, and -272NX airplanes. Model A320-215 airplanes are not
certificated by the FAA and are not included on the U.S. type
certificate data sheet; this proposed AD therefore does not include
those airplanes in the applicability.
The MCAI states that Airbus SAS Model A318-111, A318-112, A318-121,
A318-122; Model A319-111, A319-112, A319-113, A319-114, A319-115, A319-
131, A319-132, A319-133; Model A320-211, A320-212, A320-214, A320-215,
A320-216, A320-231, A320-232, A320-233; Model A321-111, A321-112, A321-
131, A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes are
commercially known as current engine option (CEO) airplanes.
The MCAI states that Airbus SAS Model A319-151N, A319-153N, A319-
171N; Model A320-251N, A320-252N, A320-253N, A320-271N, A320-272N,
A320-273N; Model A321-251N, A321-251NX, A321-252N, A321-252NX, A321-
253N, A321-253NX, A321-271N, A321-271NX, A321-272N, and A321-272NX
airplanes are commercially known as new engine option (NEO) airplanes.
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 in-service embodiment through Airbus mod 165315 for CEO
airplanes. The MCAI states that the applicability is expanded to
include the NEO airplanes, which are subject to the same unsafe
condition.
The FAA is proposing 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 an 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 <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-2661.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2015-02-14, this proposed AD would retain all the
requirements of AD 2015-02-14. Those requirements are referenced in
EASA AD 2024-0097R2, which, in turn, is referenced in paragraph (g) of
this proposed AD. Paragraph (i) of this proposed AD does restate the
requirement of paragraph (k) of AD 2015-02-14, as EASA AD 2024-0097R2
only cancels 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. However, it does not require removal from the
maintenance or inspection program for certain airplanes. This proposed
AD would require removal of this task.
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. Corrective actions
include replacement of the affected MLG door actuator fitting, and
repair of the bush migration, the wear marks underneath bolt head, and
other damages on left and right sides of the airplane.
EASA AD 2024-0097R2 specifies procedures for repetitive detailed
visual and HFEC inspections of the MLG door hinge fittings on the keel
beam. Corrective actions include replacement of the MLG door hinge
fitting, and repair of the bush migration, wear marks underneath bolt
head, and other damages 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.
FAA's Determination
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 and
material referenced above. The FAA is issuing this NPRM after
determining that the unsafe condition described previously is likely to
exist or develop on other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would retain all requirements of AD 2015-02-14,
add an optional terminating action, and revise the applicability by
adding NEO airplanes and removing airplanes with a certain
modification. This proposed AD would also require accomplishing the
actions specified in the material described previously.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 1,766 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
[[Page 102018]]
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections.................... 20 work-hours x $85 per $0 $1,700, per $3,002,200, per
hour = $1,700, per inspection cycle. inspection
inspection cycle. cycle.
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Modify the actuator and hinge fittings at 82 work-hours x $85 per hour = $52,000 $58,970
MLG door. $6,970.
----------------------------------------------------------------------------------------------------------------
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
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
38 work-hours x $85 per hour = $3,230. $6,742 $9,972
------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the repairs specified in this proposed AD.
According to the manufacturer, some or all of the costs of this
proposed 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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
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:
Airbus SAS: Docket No. FAA-2024-2661; Project Identifier MCAI-2024-
00269-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by January 31, 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 (4) 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
[[Page 102019]]
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 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, International
Validation Branch, FAA; or the European Union Aviation Safety Agency
(EASA); or 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.
(i) Retained Maintenance or Inspection Program Revision, With Added
Airplanes and Compliance Time
This paragraph restates the requirements of paragraph (k) of AD
2015-02-14 with added airplanes and compliance time. At the
applicable time specified in paragraph (i)(1) or (2) 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.
(1) For airplanes identified in paragraphs (c)(1), (2), (4), and
(6) of this AD: After the effective date of AD 2015-02-14 and before
further flight after doing the initial inspections required by
paragraph (g) of this AD.
(2) For airplanes identified in paragraphs (c)(3), (5), and (7)
of this AD: After the effective date of this AD and before further
flight after doing the initial inspections required by paragraph (g)
of this AD.
(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,
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, send it to the attention of the
person identified in paragraph (l) of this AD and email to:
<a href="/cdn-cgi/l/email-protection#c1808c8e8281a7a0a0efa6aeb7"><span class="__cf_email__" data-cfemail="2a6b6765696a4c4b4b044d455c">[email protected]</span></a>.
(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 2012-0118 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, International
Validation Branch, FAA; or the European Union Aviation Safety Agency
(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 (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, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 206-231-3667; email:
<a href="/cdn-cgi/l/email-protection#73071a1e1c071b0a5d035d171c041f1a1d14331512125d141c05"><span class="__cf_email__" data-cfemail="76021f1b19021e0f5806581219011a1f18113610171758111900">[email protected]</span></a>.
(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.
(3) The following material was approved for IBR on [DATE 35 DAYS
AFTER PUBLICATION OF THE FINAL RULE].
(i) European Union Aviation Safety Agency (EASA) AD 2024-0097R2,
dated July 12, 2024.
(ii) [Reserved]
(4) For EASA AD 2024-0097R2 identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
8999 000; email <a href="/cdn-cgi/l/email-protection#d29396a192b7b3a1b3fcb7a7a0bda2b3fcb7a7"><span class="__cf_email__" data-cfemail="cb8a8fb88baeaab8aae5aebeb9a4bbaae5aebe">[email protected]</span></a>; website easa.europa.eu. You may
find this material on the EASA website at ad.easa.europa.eu.
(5) 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.
(6) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#a9cfdb87c0c7dad9cccaddc0c6c7e9c7c8dbc887cec6df"><span class="__cf_email__" data-cfemail="4325316d2a2d30332620372a2c2d032d2231226d242c35">[email protected]</span></a>.
Issued on December 11, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-29620 Filed 12-16-24; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on December 17, 2024.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.