Airworthiness Directives; Airbus Helicopters, 87821-87825 [2024-25615]
Download as PDF
<![CDATA[
87821
Federal Register / Vol. 89, No. 214 / Tuesday, November 5, 2024 / Proposed Rules
7.1.3 Absorbency. Perform AATCC Test
Method 79–2010, to confirm the absence of
ScotchguardTM or other water-repellent
finish. The time to absorb one drop must be
on the order of 1 second.
7.2 * * *
7.2.5 Calculate the coefficient of variation
(CV) of the nine average RMC values from
each sample load. The CV must be less than
or equal to 2.0% for the test cloth lot to be
considered acceptable and to perform the
standard extractor RMC testing.
8. * * *
8.5 Repeat sections 8.3 and 8.4 of this
appendix an additional two times, so that
three replications at each extractor condition
are performed. When this procedure is
performed in its entirety, a total of 60
extractor RMC test runs are required.
8.6 Calculate RMCcloth-avg for each
extractor test condition by averaging the
values of the 3 replications performed
specified in sections 8.3 and 8.4 of this
appendix.
8.7 Perform a linear least-squares fit to
determine coefficients A and B such that the
standard RMC values shown in table 8.7 of
this appendix (RMCstandard) are linearly
related to the RMCcloth-avg values calculated in
section 8.6 of this appendix:
RMCstandard ∼ A × RMCcloth-avg + B
where A and B are coefficients of the linear
least-squares fit.
TABLE 8.7—STANDARD RMC VALUES
RMC percentage
Warm soak
‘‘g Force’’
15 min. spin
(percent)
...................................................................................................................
...................................................................................................................
...................................................................................................................
...................................................................................................................
...................................................................................................................
8.8 Calculate the corrected RMC value for
each extractor test condition, RMCcloth-corr as
follows:
RMCcloth-corr = A × RMCcloth-avg + B
Where:
RMSE
I
Where:
RMCstandard_i = the RMCstandard value in table
8.7 of this appendix for the ith extractor
test condition, expressed as a decimal,
RMCcloth-corr_i = the corrected RMC value, as
calculated in section 8.8 of this appendix
for the ith extractor test condition,
expressed as a decimal, and
i = the 20 extractor test conditions listed in
table 8.7 of this appendix.
*
*
*
*
[FR Doc. 2024–25480 Filed 11–4–24; 8:45 am]
(RMCstandard
ddrumheller on DSK120RN23PROD with PROPOSALS1
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–2419; Project
Identifier MCAI–2023–00366–R]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
The FAA proposes to adopt a
new airworthiness directive (AD) for all
Airbus Helicopters (Airbus) Model
AS350B, AS350B1, AS350B2, AS350B3,
AS350BA, AS350D, AS355E, AS355F,
AS355F1, AS355F2, AS355N, AS355NP,
EC130B4, and EC130T2 helicopters.
This proposed AD was prompted by a
manufacturer assessment that
determined additional actions are
17:09 Nov 04, 2024
Jkt 265001
PO 00000
52.8
43.1
35.8
30.0
28.0
Frm 00021
i )'
20
SUMMARY:
VerDate Sep<11>2014
49.7
37.9
30.7
25.5
24.1
4 min. spin
(percent)
8.9 Calculate the root mean square error
of the linear fit, RMSE. The RMSE must be
less than or equal to 0.015 for the test cloth
lot to be considered acceptable. The RMSE is
calculated as follows:
RMCc1oth corr
i -
AGENCY:
BILLING CODE 6450–01–P
49.9
40.4
33.1
28.7
26.4
15 min. spin
(percent)
20
i=l
*
45.9
35.7
29.6
24.2
23.0
RMCcloth-avg = the average RMC value, as
calculated in section 8.6 of this appendix
for each extractor test condition,
expressed as a decimal, and
A and B are the coefficients of the linear least
squares fit as determined in section 8.7
of this appendix.
=
4 min. spin
(percent)
Fmt 4702
Sfmt 4702
necessary to improve particle detection
for main gearboxes (MGBs) with certain
planet gear bearings installed. This
proposed AD would require repetitively
inspecting the MGB bevel wheel for the
presence of particles, repetitively
inspecting the MGB magnetic plug for
particles, and prohibit installing an
affected MGB unless certain
requirements are met. These actions are
specified in a European Union Aviation
Safety Agency (EASA) AD, which is
proposed for incorporation by reference.
The FAA is proposing this AD to
address the unsafe condition on these
products.
The FAA must receive comments
on this NPRM by December 20, 2024.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
regulations.gov. Follow the instructions
for submitting comments.
• Fax: (202) 493–2251.
DATES:
E:\FR\FM\05NOP1.SGM
05NOP1
EP05NO24.001</GPH>
100
200
350
500
650
Cold soak
87822
Federal Register / Vol. 89, No. 214 / Tuesday, November 5, 2024 / Proposed Rules
• 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.
• 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 regulations.gov under Docket
No. FAA–2024–2419; 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 EASA AD, any
comments received, and other
information. The street address for
Docket Operations is listed above.
Material Incorporated by Reference:
• For EASA material identified in this
proposed AD, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; phone: +49 221 8999 000;
email: ADs@easa.europa.eu; website:
easa.europa.eu. You may find the EASA
material on the EASA website at
ad.easa.europa.eu.
• You may view this material at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. For information on the
availability of this material at the FAA,
call (817) 222–5110. The EASA material
is also available at regulations.gov under
Docket No. FAA–2024–2419.
Other Related Material: For Airbus
material identified in this proposed AD,
contact Airbus Helicopters, 2701 North
Forum Drive, Grand Prairie, TX 75052;
phone: (972) 641–0000 or (800) 232–
0323; fax: (972) 641–3775; or at
airbus.com/en/products-services/
helicopters/hcare-services/airbusworld.
FOR FURTHER INFORMATION CONTACT: Dan
McCully, Aviation Safety Engineer,
FAA, 1600 Stewart Ave., Suite 410,
Westbury, NY 11590; phone: (404) 474–
5548; email: william.mccully@faa.gov.
SUPPLEMENTARY INFORMATION:
ddrumheller on DSK120RN23PROD with PROPOSALS1
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 ADDRESSES. Include ‘‘Docket No.
FAA–2024–2419; Project Identifier
MCAI–2023–00366–R’’ 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 this proposal
because of those comments.
VerDate Sep<11>2014
17:09 Nov 04, 2024
Jkt 265001
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
regulations.gov, 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 Dan McCully,
Aviation Safety Engineer, FAA, 1600
Stewart Ave., Suite 410, Westbury, NY
11590; phone: (404) 474–5548; email:
william.mccully@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2023–0044,
dated February 28, 2023, (EASA AD
2023–0044) to correct an unsafe
condition on Airbus Model AS 350 B,
AS 350 D, AS 350 B1, AS 350 B2, AS
350 BA, AS 350 BB, AS 350 B3, EC 130
B4, EC 130 T2, AS 355 E, AS 355 F, AS
355 F1, AS 355 F2, AS355 N, and
AS355 NP helicopters. EASA advises
that after a fleet design review for
detection of particles in the MGB, it was
determined that additional maintenance
actions are necessary to improve
detection of particles in the MGB. The
FAA is proposing this AD to detect and
correct the presence of particles in the
MGB, which if not addressed, could
result in reduced or loss of control of
the helicopter.
You may examine EASA AD 2023–
0044 in the AD docket at regulations.gov
under Docket No. FAA–2024–2419.
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
Material Incorporated by Reference
Under 1 CFR Part 51
EASA AD 2023–0044 requires
repetitive borescope visual inspections
of the bevel wheel of the affected MGB
for particles, collecting and analyzing
any found particles, and depending on
the results, further actions,
accomplishing corrective action in
accordance with the ASB defined
within, or contacting AH [Airbus
Helicopters] for further corrective
action. EASA AD 2023–0044 also
requires accomplishing a borescope
visual inspection of the bevel wheel of
the affected MGB for particles following
the detection of any particles at the
MGB magnetic plug during
accomplishment of certain maintenance
tasks and depending on the results,
taking corrective action. Lastly, EASA
AD 2023–0044 prohibits installing an
affected MGB on any helicopter unless
it is a serviceable part as defined within
and certain requirements are met.
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.
Other Related Material
The FAA reviewed Airbus Alert
Service Bulletin No. AS350–05.01.04,
No. AS355–05.00.87, and No. EC130–
05A040, each Revision 0, and each
dated January 25, 2023. This material
specifies procedures for borescope
inspecting the MGB bevel wheel for
particles and, depending on the results,
replacing a damaged epicyclic module
or bevel reduction module with an
airworthy part, and collecting the
particles using a vacuum pump and
analyzing the particles.
FAA’s Determination
These helicopters have been approved
by EASA and are approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the
European Union, EASA has notified the
FAA about the unsafe condition
described in its AD. The FAA is
proposing this AD after evaluating all
known relevant information and
determining that the unsafe condition
described previously is likely to exist or
develop on other helicopters of these
same type designs.
Proposed AD Requirements in This
NPRM
This proposed AD would require
accomplishing the actions specified in
EASA AD 2023–0044, described
previously, as incorporated by
reference, except for any differences
identified as exceptions in the
E:\FR\FM\05NOP1.SGM
05NOP1
Federal Register / Vol. 89, No. 214 / Tuesday, November 5, 2024 / Proposed Rules
regulatory text of this proposed AD and
except as discussed under ‘‘Differences
Between this Proposed AD and EASA
AD 2023–0044.’’
This proposed AD would require
certain actions within compliance times
specified in certain material referenced
for compliance in EASA AD 2023–0044,
particularly for corrective actions for
scales, flakes, or splinters. Depending
on the measurements of the scales,
flakes, or splinters, corrective actions
include close monitoring, metallurgical
analysis within 50 hours time-inserivce, or removing each affected
module and additional actions when
certain criteria are exceeded.
ddrumheller on DSK120RN23PROD with PROPOSALS1
Explanation of Required Compliance
Information
In the FAA’s ongoing efforts to
improve the efficiency of the AD
process, the FAA developed a process to
use some civil aviation authority (CAA)
ADs as the primary source of
information for compliance with
requirements for corresponding FAA
ADs. The FAA has been coordinating
this process with manufacturers and
CAAs. As a result, the FAA proposes to
incorporate EASA AD 2023–0044 by
reference in the FAA final rule. This
proposed AD would, therefore, require
compliance with EASA AD 2023–0044
in its entirety through that
incorporation, except for any differences
identified as exceptions in the
regulatory text of this proposed AD.
Using common terms that are the same
as the heading of a particular section in
EASA AD 2023–0044 does not mean
that operators need comply only with
that section. For example, where the AD
requirement refers to ‘‘all required
actions and compliance times,’’
compliance with this AD requirement is
not limited to the section titled
‘‘Required Action(s) and Compliance
Time(s)’’ in EASA AD 2023–0044.
Material referenced in EASA AD 2023–
0044 for compliance will be available at
www.regulations.gov by searching for
and locating Docket No. FAA–2024–
2419 after the FAA final rule is
published.
Differences Between This Proposed AD
and EASA AD 2023–0044
EASA AD 2023–0044 applies to
Model AS350BB helicopters, whereas
this proposed AD would not because
that model is not FAA-type certificated.
Where Note 1 in the material
referenced in EASA AD 2023–0044
specifies the option of 1 mechanical
technician and 1 crew member, for this
proposed AD, the pilot is only permitted
to turn the tail rotor (b) because the
other actions specified in the note must
VerDate Sep<11>2014
17:09 Nov 04, 2024
Jkt 265001
be accomplished by persons authorized
under 14 CFR 43.3. Therefore, for the
purposes of this proposed AD, the
owner/operator (pilot) may turn the tail
rotor (b) and must enter compliance
with the applicable paragraph of this
proposed AD in the helicopter
maintenance records in accordance with
14 CFR 43.9(a) and 91.417(a)(2)(v). The
pilot may perform this action because it
only involves turning the tail rotor (b).
This action can be performed equally
well by a pilot or a mechanic. This
action is an exception to the FAA’s
standard maintenance regulations.
This proposed AD would not require
complying with paragraph (2) of EASA
AD 2023–0044. Instead, this proposed
AD would require repetitively
inspecting the MGB magnetic plug for
particles and, if there is any particle,
accomplishing a borescope visual
inspection, as specified in paragraphs
(h)(6)(i) and (ii) of this proposed AD.
Where the material referenced in
EASA AD 2023–0044 specifies
contacting Airbus Helicopters for a
certain action, this proposed AD would
require accomplishing action in
accordance with a method approved the
FAA, EASA, or Airbus Helicopters’
EASA Design Organization Approval.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 522
helicopters of U.S. Registry. Labor rates
are estimated at $85 per work-hour.
Based on these numbers, the FAA
estimates the following costs to comply
with this proposed AD.
A repetitive visual borescope
inspection of the MGB bevel wheel
would take 1 work-hour for an
estimated cost of $85 per helicopter and
$44,370 for the U.S. fleet, per inspection
cycle.
If necessary, collecting and
performing a metallurgical analysis of
the detected particles would take 6
work-hours for an estimated cost of
$510 per helicopter, per analysis.
Repetitively inspecting the magnetic
plugs of the MGB would take 1 workhour for an estimated cost of $85 per
helicopter and $44,370 for the U.S. fleet,
per inspection cycle.
If required, close monitoring would
take 2 work-hours for an estimated cost
of $170 per helicopter, per close
monitoring cycle.
Accomplishing a visual borescope
inspection of the MGB bevel wheel as a
result of an MGB magnetic plug
inspection would take 1 work-hour for
an estimated cost of $85 per helicopter.
If necessary, replacing an epicyclic
module would take 56 work-hours and
parts would cost $50,524 (overhauled)
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
87823
for an estimated cost of $55,284 per
module.
If necessary, replacing a bevel
reduction module would take 56 workhours and parts would cost $18,500
(overhaled) for an estimated cost of
$23,260 per module.
Certain corrective action could vary
significantly from helicopter to
helicopter. The FAA has no data to
determine the costs to accomplish the
corrective action.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
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,
E:\FR\FM\05NOP1.SGM
05NOP1
87824
Federal Register / Vol. 89, No. 214 / Tuesday, November 5, 2024 / Proposed Rules
the FAA proposes to amend 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 adding
the following new airworthiness
directive:
■
Airbus Helicopters: Docket No. FAA–2024–
2419; Project Identifier MCAI–2023–
00366–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by December 20,
2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Helicopters
Model AS350B, AS350B1, AS350B2,
AS350B3, AS350BA, AS350D, AS355E,
AS355F, AS355F1, AS355F2, AS355N,
AS355NP, EC130B4, and EC130T2
helicopters, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)
Code: 6320, Main Rotor Gearbox.
(e) Unsafe Condition
This AD was prompted by an assessment
performed by the manufacturer which
determined that additional actions are
necessary to improve particle detection for
main gearboxes (MGBs) with certain part-
numbered planet gear bearings installed. The
FAA is issuing this AD to detect and correct
particles in the MGB. The unsafe condition,
if not addressed, could result in reduced or
loss of control of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraphs (h) and
(i) of this AD: Comply with all required
actions and compliance times specified in,
and in accordance with, European Union
Aviation Safety Agency AD 2023–0044, dated
February 28, 2023 (EASA AD 2023–0044).
(h) Exceptions to EASA AD 2023–0044
(1) Where EASA AD 2023–0044 defines
‘‘serviceable MGB’’ as ‘‘An affected MGB
which has accumulated less than 330 flight
hours (FH) since new (first installation on a
helicopter), or since an overhaul, or since an
inspection in accordance with the
instructions of the ASB;’’ for this AD, replace
that text with ‘‘An affected MGB which has
accumulated less than 330 total hours timein-service since new (zero total hours timein-service), since last overhaul if an overhaul
has been accomplished, or since last
inspection and any specified corrective
action in accordance with the instructions of
the ASB if an inspection and any specified
corrective action by following the
instructions of the ASB have been
accomplished.’’
(2) Where EASA AD 2023–0044 requires
compliance in terms of flight hours, this AD
requires using hours time-in-service (TIS).
(3) Where EASA AD 2023–0044 refers to its
effective date, this AD requires using the
effective date of this AD.
(4) Where Note 1 in the material referenced
in paragraph (1) of EASA AD 2023–0044
specifies the option of 1 mechanical
technician and 1 crew member, for this AD,
the pilot is only permitted to turn the tail
rotor (b). The owner/operator (pilot) holding
at least a private pilot certificate may turn the
tail rotor (b) and must enter compliance with
paragraph (g) of this AD in the helicopter
maintenance records in accordance with 14
CFR 43.9(a) and 91.417(a)(2)(v). The record
must be maintained as required by 14 CFR
91.417, 121.380, or 135.43. All other actions
specified in Note 1 in the material referenced
in paragraph (1) of EASA AD 2023–0044
must be accomplished by persons authorized
under 14 CFR 43.3.
(5) Where Note 2 in the material referenced
in paragraph (1) of EASA AD 2023–0044
specifies contacting Airbus Helicopters for
further instructions if the bottom of the
radius (a6) of the bevel wheel (a3) or head
screws (a4) (see Figure 2) are not clearly
visible, this AD requires, before further flight,
accomplishing action in accordance with a
method approved by the FAA, EASA, or
Airbus Helicopters’ EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(6) Instead of complying with paragraph (2)
of EASA AD 2023–0044, comply with the
actions required by paragraphs (h)(6)(i) and
(ii) of this AD.
(i) After the effective date of this AD, and
within the compliance time intervals
specified table 1 to paragraph (h)(6)(i) of this
AD, visually inspect the MGB magnetic plug
for particles.
Note 1 to paragraph (h)(6)(i): Aircraft
Maintenance Manual (AMM) task 60–00–00,
6–2A, or AMM task 60–00–00, 6–2, or work
card 60–00–00–602, as applicable, provides
information regarding inspecting the MGB
magnetic plug.
TABLE 1 TO PARAGRAPH (h)(6)(i)—MGB MAGNETIC PLUG INSPECTIONS
Initial compliance times
(after the effective date
of this AD)
(hours TIS)
Helicopter model(s)
ddrumheller on DSK120RN23PROD with PROPOSALS1
AS350B, AS350B1, AS350BA, and AS350D ......................................................................
AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP .....................................
AS350B2 and AS350B3 ......................................................................................................
EC130B4 ..............................................................................................................................
EC130T2 ..............................................................................................................................
(ii) If there is any particle as a result of any
MGB magnetic plug inspection required by
paragraph (h)(6)(i) of this AD, before further
flight, borescope inspect the bevel wheel of
the affected MGB for particles as required by
paragraph (1) of EASA AD 2023–0044. If
there is any particle as a result of the
borescope inspection of the bevel wheel,
before further flight, collect and analyze the
particles as required by paragraph (3) of
EASA AD 2023–0044.
(7) Where paragraph (3) of EASA AD 2023–
0044 specifies ‘‘If, during any inspection as
required by paragraph (1) or (2) of this AD;’’
for this AD, replace that text with ‘‘If, during
VerDate Sep<11>2014
17:09 Nov 04, 2024
Jkt 265001
any inspection as required by paragraph (1)
of this AD.’’
(8) Where the material referenced in
paragraph (3) of EASA AD 2023–0044
specifies performing a metallurgical analysis
and contacting Airbus Helicopters if
collected particles cannot be characterized
with Work Card 20–08–01–601, this AD does
not require contacting Airbus Helicopter but
does require performing the metallurgical
analysis.
(9) This AD does not allow the ferry flight
provision specified in the material referenced
in paragraph (3) of EASA AD 2023–0044; for
this AD, refer to paragraph (j) of this AD.
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
5
5
10
5
5
Interval compliance times
(thereafter)
(hours TIS)
30
30
100
150
150
(10) Where the material referenced in
paragraph (3) of EASA AD 2023–0044
specifies contacting Airbus Helicopters if the
damaged module cannot be identified, this
AD requires, before further flight,
accomplishing action in accordance with a
method approved by the FAA, EASA, or
Airbus Helicopters’ EASA DOA. If approved
by the DOA, the approval must include the
DOA-authorized signature.
(11) Where paragraph (5) of EASA AD
2023–0044 states ‘‘to contact AH for
corrective action(s) instructions, and within
the compliance time specified therein, to
accomplish those instructions accordingly’’
for this AD, replace that text with
E:\FR\FM\05NOP1.SGM
05NOP1
Federal Register / Vol. 89, No. 214 / Tuesday, November 5, 2024 / Proposed Rules
‘‘accomplishing corrective actions in
accordance with a method approved by the
FAA, EASA, or Airbus Helicopters’ EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.’’
(12) Where paragraph (7) of EASA AD
2023–0044 states ‘‘since new (first
installation a helicopter), or since an
overhaul, or since an inspection in
accordance with the instructions of the ASB,
as applicable, and, thereafter, as required by
this AD;’’ for this AD, replace that text with
‘‘since new (zero total hours time-in-service),
or since last overhaul if an overhaul has been
accomplished, or since last inspection and
any specified corrective action in accordance
with the instructions of the ASB if an
inspection and any specified corrective
action by following the instructions of the
ASB have been accomplished, and thereafter
as required by this AD.’’.’’
(13) This AD does not adopt the ‘‘Remarks’’
section of EASA AD 2023–0044.
(i) No Reporting Requirement
Although the material referenced in EASA
AD 2023–0044 specifies to submit certain
information to the manufacturer, this AD
does not require that action.
(j) Special Flight Permit
A special flight permit may be issued in
accordance with 14 CFR 21.197 and 21.199
to permit a one-time, non-revenue flight to a
location where the actions required by this
AD can be accomplished. This flight must be
performed with only essential flight crew.
(k) Alternative Methods of Compliance
(AMOCs)
(1) 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 local
Flight Standards District 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.
Information may be emailed to: 9-AVS-AIR730-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.
ddrumheller on DSK120RN23PROD with PROPOSALS1
(l) Related Information
For more information about this AD,
contact Dan McCully, Aviation Safety
Engineer, FAA, 1600 Stewart Ave., Suite 410,
Westbury, NY 11590; phone: (404) 474–5548;
email: william.mccully@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the material listed in this paragraph under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as
applicable to do the actions required by this
AD, unless the AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2023–0044, dated February 28,
2023.
VerDate Sep<11>2014
17:09 Nov 04, 2024
Jkt 265001
(ii) [Reserved]
(3) For EASA material identified in this
AD, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; phone: +49 221
8999 000; email: ADs@easa.europa.eu;
website: easa.europa.eu. You may find the
EASA material on the EASA website at
ad.easa.europa.eu.
(4) You may view this material at the FAA,
Office of the Regional Counsel, Southwest
Region, 10101 Hillwood Pkwy., Room 6N–
321, Fort Worth, TX 76177. For information
on the availability of this material at the
FAA, call (817) 222–5110.
(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 October 29, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–25615 Filed 11–4–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
Bureau of Industry and Security
15 CFR Parts 734, 740, 742, 744, 746,
and 774
[Docket No. 241030–0286]
RIN 0694–XC109
Public Briefing on Revisions to SpaceRelated Export Controls Under Export
Administration Regulations and
International Traffic in Arms
Regulations
Bureau of Industry and
Security, U.S. Department of Commerce.
ACTION: Notification of public briefing
on regulatory actions.
AGENCY:
On October 23, 2024, the
Bureau of Industry and Security (BIS)
published in the Federal Register a
proposed rule, ‘‘Export Administration
Regulations: Revisions to Space-Related
Export Controls, including Addition of
License Exception Commercial Space
Activities (CSA).’’ On the same day, the
State Department’s Directorate of
Defense Trade Controls (DDTC)
published in the Federal Register a
proposed rule, ‘‘International Traffic in
Arms Regulations (ITAR): U.S.
Munitions List Categories IV and XV.’’
This document announces that, on
November 6, 2024, BIS will host a
public briefing on these proposed rules.
This document also provides details on
the procedures for participating in the
public briefing. Elsewhere in this issue
of the Federal Register, BIS is
SUMMARY:
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
87825
publishing notification of the public
briefing on related final rules.
DATES:
Public briefing: The public briefing
will be held on November 6, 2024. The
public briefing will begin at 1 p.m.
Eastern Standard Time (EST) and
conclude at 3 p.m. EST.
Deadline to register: Register no later
than November 1, 2024, to attend in
person. Register by November 5, 2024,
for virtual participation.
Deadline for submitting questions for
the public briefing: Questions for the
briefing must be received no later than
5 p.m. EST, November 4, 2024.
ADDRESSES:
In-Person: The public briefing will be
held at the Commerce Research Library
at the U.S. Department of Commerce,
1401 Constitution Avenue NW,
Washington, DC 20230. Register at:
space.commerce.gov/export24. Inperson attendance is limited to the
capacity of the room.
Virtual: To attend this event virtually,
register at space.commerce.gov/
export24.
Submitting questions: Submit
questions in writing through the
registration links at
space.commerce.gov/export24.
Recordkeeping: A summary of the
briefing and Q&A will be posted for the
record at space.commerce.gov/export24
and at regulations.gov.
FOR FURTHER INFORMATION CONTACT: For
questions, contact Joseph A. Cristofaro,
Director, Sensors, Aerospace and
Marine Division, Office of National
Security Controls, Bureau of Industry
and Security, U.S. Department of
Commerce, at (202) 482–2440 or by
email: Joseph.Cristofaro@bis.doc.gov.
SUPPLEMENTARY INFORMATION:
Background
On October 23, 2024, BIS published
the proposed rule ‘‘Export
Administration Regulations: Revisions
to Space-Related Export Controls,
including Addition of License
Exception Commercial Space Activities
(CSA)’’ (89 FR 84784), which proposed
changes to controls for spacecraft and
related items under the EAR that would
conform to proposed changes to the
International Traffic in Arms
Regulations related to U.S. Munitions
List Categories IV and XV. This rule also
proposed the addition of a new license
exception for certain Commercial Space
Activities (CSA). These proposed rules
are intended to better enable a globally
competitive U.S. space industrial base
while continuing to protect U.S.
national security and foreign policy
interests.
E:\FR\FM\05NOP1.SGM
05NOP1
]]>Agencies
[Federal Register Volume 89, Number 214 (Tuesday, November 5, 2024)]
[Proposed Rules]
[Pages 87821-87825]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-25615]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2419; Project Identifier MCAI-2023-00366-R]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Airbus Helicopters (Airbus) Model AS350B, AS350B1, AS350B2,
AS350B3, AS350BA, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N,
AS355NP, EC130B4, and EC130T2 helicopters. This proposed AD was
prompted by a manufacturer assessment that determined additional
actions are necessary to improve particle detection for main gearboxes
(MGBs) with certain planet gear bearings installed. This proposed AD
would require repetitively inspecting the MGB bevel wheel for the
presence of particles, repetitively inspecting the MGB magnetic plug
for particles, and prohibit installing an affected MGB unless certain
requirements are met. These actions are specified in a European Union
Aviation Safety Agency (EASA) AD, which is proposed for incorporation
by reference. The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this NPRM by December 20, 2024.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to regulations.gov. Follow
the instructions for submitting comments.
Fax: (202) 493-2251.
[[Page 87822]]
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.
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 regulations.gov under
Docket No. FAA-2024-2419; 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 EASA AD, any comments received, and
other information. The street address for Docket Operations is listed
above.
Material Incorporated by Reference:
For EASA material identified in this proposed AD, contact
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221
8999 000; email: [email protected]; website: easa.europa.eu. You may
find the EASA material on the EASA website at ad.easa.europa.eu.
You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177. For information on the availability of this
material at the FAA, call (817) 222-5110. The EASA material is also
available at regulations.gov under Docket No. FAA-2024-2419.
Other Related Material: For Airbus material identified in this
proposed AD, contact Airbus Helicopters, 2701 North Forum Drive, Grand
Prairie, TX 75052; phone: (972) 641-0000 or (800) 232-0323; fax: (972)
641-3775; or at airbus.com/en/products-services/helicopters/hcare-services/airbusworld.
FOR FURTHER INFORMATION CONTACT: Dan McCully, Aviation Safety Engineer,
FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; phone: (404)
474-5548; email: [email protected].
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 ADDRESSES. Include ``Docket No. FAA-2024-2419; Project Identifier
MCAI-2023-00366-R'' 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
this 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
regulations.gov, 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 Dan
McCully, Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 410,
Westbury, NY 11590; phone: (404) 474-5548; email:
[email protected]. Any commentary that the FAA receives which is
not specifically designated as CBI will be placed in the public docket
for this rulemaking.
Background
EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2023-0044, dated February 28, 2023,
(EASA AD 2023-0044) to correct an unsafe condition on Airbus Model AS
350 B, AS 350 D, AS 350 B1, AS 350 B2, AS 350 BA, AS 350 BB, AS 350 B3,
EC 130 B4, EC 130 T2, AS 355 E, AS 355 F, AS 355 F1, AS 355 F2, AS355
N, and AS355 NP helicopters. EASA advises that after a fleet design
review for detection of particles in the MGB, it was determined that
additional maintenance actions are necessary to improve detection of
particles in the MGB. The FAA is proposing this AD to detect and
correct the presence of particles in the MGB, which if not addressed,
could result in reduced or loss of control of the helicopter.
You may examine EASA AD 2023-0044 in the AD docket at
regulations.gov under Docket No. FAA-2024-2419.
Material Incorporated by Reference Under 1 CFR Part 51
EASA AD 2023-0044 requires repetitive borescope visual inspections
of the bevel wheel of the affected MGB for particles, collecting and
analyzing any found particles, and depending on the results, further
actions, accomplishing corrective action in accordance with the ASB
defined within, or contacting AH [Airbus Helicopters] for further
corrective action. EASA AD 2023-0044 also requires accomplishing a
borescope visual inspection of the bevel wheel of the affected MGB for
particles following the detection of any particles at the MGB magnetic
plug during accomplishment of certain maintenance tasks and depending
on the results, taking corrective action. Lastly, EASA AD 2023-0044
prohibits installing an affected MGB on any helicopter unless it is a
serviceable part as defined within and certain requirements are met.
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.
Other Related Material
The FAA reviewed Airbus Alert Service Bulletin No. AS350-05.01.04,
No. AS355-05.00.87, and No. EC130-05A040, each Revision 0, and each
dated January 25, 2023. This material specifies procedures for
borescope inspecting the MGB bevel wheel for particles and, depending
on the results, replacing a damaged epicyclic module or bevel reduction
module with an airworthy part, and collecting the particles using a
vacuum pump and analyzing the particles.
FAA's Determination
These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA about the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determining that
the unsafe condition described previously is likely to exist or develop
on other helicopters of these same type designs.
Proposed AD Requirements in This NPRM
This proposed AD would require accomplishing the actions specified
in EASA AD 2023-0044, described previously, as incorporated by
reference, except for any differences identified as exceptions in the
[[Page 87823]]
regulatory text of this proposed AD and except as discussed under
``Differences Between this Proposed AD and EASA AD 2023-0044.''
This proposed AD would require certain actions within compliance
times specified in certain material referenced for compliance in EASA
AD 2023-0044, particularly for corrective actions for scales, flakes,
or splinters. Depending on the measurements of the scales, flakes, or
splinters, corrective actions include close monitoring, metallurgical
analysis within 50 hours time-in-serivce, or removing each affected
module and additional actions when certain criteria are exceeded.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA developed a process to use some civil aviation
authority (CAA) ADs as the primary source of information for compliance
with requirements for corresponding FAA ADs. The FAA has been
coordinating this process with manufacturers and CAAs. As a result, the
FAA proposes to incorporate EASA AD 2023-0044 by reference in the FAA
final rule. This proposed AD would, therefore, require compliance with
EASA AD 2023-0044 in its entirety through that incorporation, except
for any differences identified as exceptions in the regulatory text of
this proposed AD. Using common terms that are the same as the heading
of a particular section in EASA AD 2023-0044 does not mean that
operators need comply only with that section. For example, where the AD
requirement refers to ``all required actions and compliance times,''
compliance with this AD requirement is not limited to the section
titled ``Required Action(s) and Compliance Time(s)'' in EASA AD 2023-
0044. Material referenced in EASA AD 2023-0044 for compliance will be
available at www.regulations.gov by searching for and locating Docket
No. FAA-2024-2419 after the FAA final rule is published.
Differences Between This Proposed AD and EASA AD 2023-0044
EASA AD 2023-0044 applies to Model AS350BB helicopters, whereas
this proposed AD would not because that model is not FAA-type
certificated.
Where Note 1 in the material referenced in EASA AD 2023-0044
specifies the option of 1 mechanical technician and 1 crew member, for
this proposed AD, the pilot is only permitted to turn the tail rotor
(b) because the other actions specified in the note must be
accomplished by persons authorized under 14 CFR 43.3. Therefore, for
the purposes of this proposed AD, the owner/operator (pilot) may turn
the tail rotor (b) and must enter compliance with the applicable
paragraph of this proposed AD in the helicopter maintenance records in
accordance with 14 CFR 43.9(a) and 91.417(a)(2)(v). The pilot may
perform this action because it only involves turning the tail rotor
(b). This action can be performed equally well by a pilot or a
mechanic. This action is an exception to the FAA's standard maintenance
regulations.
This proposed AD would not require complying with paragraph (2) of
EASA AD 2023-0044. Instead, this proposed AD would require repetitively
inspecting the MGB magnetic plug for particles and, if there is any
particle, accomplishing a borescope visual inspection, as specified in
paragraphs (h)(6)(i) and (ii) of this proposed AD.
Where the material referenced in EASA AD 2023-0044 specifies
contacting Airbus Helicopters for a certain action, this proposed AD
would require accomplishing action in accordance with a method approved
the FAA, EASA, or Airbus Helicopters' EASA Design Organization
Approval.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 522 helicopters of U.S. Registry. Labor rates are estimated at
$85 per work-hour. Based on these numbers, the FAA estimates the
following costs to comply with this proposed AD.
A repetitive visual borescope inspection of the MGB bevel wheel
would take 1 work-hour for an estimated cost of $85 per helicopter and
$44,370 for the U.S. fleet, per inspection cycle.
If necessary, collecting and performing a metallurgical analysis of
the detected particles would take 6 work-hours for an estimated cost of
$510 per helicopter, per analysis.
Repetitively inspecting the magnetic plugs of the MGB would take 1
work-hour for an estimated cost of $85 per helicopter and $44,370 for
the U.S. fleet, per inspection cycle.
If required, close monitoring would take 2 work-hours for an
estimated cost of $170 per helicopter, per close monitoring cycle.
Accomplishing a visual borescope inspection of the MGB bevel wheel
as a result of an MGB magnetic plug inspection would take 1 work-hour
for an estimated cost of $85 per helicopter.
If necessary, replacing an epicyclic module would take 56 work-
hours and parts would cost $50,524 (overhauled) for an estimated cost
of $55,284 per module.
If necessary, replacing a bevel reduction module would take 56
work-hours and parts would cost $18,500 (overhaled) for an estimated
cost of $23,260 per module.
Certain corrective action could vary significantly from helicopter
to helicopter. The FAA has no data to determine the costs to accomplish
the corrective action.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an 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,
[[Page 87824]]
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 adding the following new airworthiness
directive:
Airbus Helicopters: Docket No. FAA-2024-2419; Project Identifier
MCAI-2023-00366-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by December 20, 2024.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Helicopters Model AS350B, AS350B1,
AS350B2, AS350B3, AS350BA, AS350D, AS355E, AS355F, AS355F1, AS355F2,
AS355N, AS355NP, EC130B4, and EC130T2 helicopters, certificated in
any category.
(d) Subject
Joint Aircraft System Component (JASC) Code: 6320, Main Rotor
Gearbox.
(e) Unsafe Condition
This AD was prompted by an assessment performed by the
manufacturer which determined that additional actions are necessary
to improve particle detection for main gearboxes (MGBs) with certain
part-numbered planet gear bearings installed. The FAA is issuing
this AD to detect and correct particles in the MGB. The unsafe
condition, if not addressed, could result in reduced or loss of
control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraphs (h) and (i) of this AD: Comply
with all required actions and compliance times specified in, and in
accordance with, European Union Aviation Safety Agency AD 2023-0044,
dated February 28, 2023 (EASA AD 2023-0044).
(h) Exceptions to EASA AD 2023-0044
(1) Where EASA AD 2023-0044 defines ``serviceable MGB'' as ``An
affected MGB which has accumulated less than 330 flight hours (FH)
since new (first installation on a helicopter), or since an
overhaul, or since an inspection in accordance with the instructions
of the ASB;'' for this AD, replace that text with ``An affected MGB
which has accumulated less than 330 total hours time-in-service
since new (zero total hours time-in-service), since last overhaul if
an overhaul has been accomplished, or since last inspection and any
specified corrective action in accordance with the instructions of
the ASB if an inspection and any specified corrective action by
following the instructions of the ASB have been accomplished.''
(2) Where EASA AD 2023-0044 requires compliance in terms of
flight hours, this AD requires using hours time-in-service (TIS).
(3) Where EASA AD 2023-0044 refers to its effective date, this
AD requires using the effective date of this AD.
(4) Where Note 1 in the material referenced in paragraph (1) of
EASA AD 2023-0044 specifies the option of 1 mechanical technician
and 1 crew member, for this AD, the pilot is only permitted to turn
the tail rotor (b). The owner/operator (pilot) holding at least a
private pilot certificate may turn the tail rotor (b) and must enter
compliance with paragraph (g) of this AD in the helicopter
maintenance records in accordance with 14 CFR 43.9(a) and
91.417(a)(2)(v). The record must be maintained as required by 14 CFR
91.417, 121.380, or 135.43. All other actions specified in Note 1 in
the material referenced in paragraph (1) of EASA AD 2023-0044 must
be accomplished by persons authorized under 14 CFR 43.3.
(5) Where Note 2 in the material referenced in paragraph (1) of
EASA AD 2023-0044 specifies contacting Airbus Helicopters for
further instructions if the bottom of the radius (a6) of the bevel
wheel (a3) or head screws (a4) (see Figure 2) are not clearly
visible, this AD requires, before further flight, accomplishing
action in accordance with a method approved by the FAA, EASA, or
Airbus Helicopters' EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(6) Instead of complying with paragraph (2) of EASA AD 2023-
0044, comply with the actions required by paragraphs (h)(6)(i) and
(ii) of this AD.
(i) After the effective date of this AD, and within the
compliance time intervals specified table 1 to paragraph (h)(6)(i)
of this AD, visually inspect the MGB magnetic plug for particles.
Note 1 to paragraph (h)(6)(i): Aircraft Maintenance Manual (AMM)
task 60-00-00, 6-2A, or AMM task 60-00-00, 6-2, or work card 60-00-
00-602, as applicable, provides information regarding inspecting the
MGB magnetic plug.
Table 1 to Paragraph (h)(6)(i)--MGB Magnetic Plug Inspections
----------------------------------------------------------------------------------------------------------------
Initial compliance
times (after the Interval compliance times
Helicopter model(s) effective date of this (thereafter) (hours TIS)
AD) (hours TIS)
----------------------------------------------------------------------------------------------------------------
AS350B, AS350B1, AS350BA, and AS350D........................ 5 30
AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP....... 5 30
AS350B2 and AS350B3......................................... 10 100
EC130B4..................................................... 5 150
EC130T2..................................................... 5 150
----------------------------------------------------------------------------------------------------------------
(ii) If there is any particle as a result of any MGB magnetic
plug inspection required by paragraph (h)(6)(i) of this AD, before
further flight, borescope inspect the bevel wheel of the affected
MGB for particles as required by paragraph (1) of EASA AD 2023-0044.
If there is any particle as a result of the borescope inspection of
the bevel wheel, before further flight, collect and analyze the
particles as required by paragraph (3) of EASA AD 2023-0044.
(7) Where paragraph (3) of EASA AD 2023-0044 specifies ``If,
during any inspection as required by paragraph (1) or (2) of this
AD;'' for this AD, replace that text with ``If, during any
inspection as required by paragraph (1) of this AD.''
(8) Where the material referenced in paragraph (3) of EASA AD
2023-0044 specifies performing a metallurgical analysis and
contacting Airbus Helicopters if collected particles cannot be
characterized with Work Card 20-08-01-601, this AD does not require
contacting Airbus Helicopter but does require performing the
metallurgical analysis.
(9) This AD does not allow the ferry flight provision specified
in the material referenced in paragraph (3) of EASA AD 2023-0044;
for this AD, refer to paragraph (j) of this AD.
(10) Where the material referenced in paragraph (3) of EASA AD
2023-0044 specifies contacting Airbus Helicopters if the damaged
module cannot be identified, this AD requires, before further
flight, accomplishing action in accordance with a method approved by
the FAA, EASA, or Airbus Helicopters' EASA DOA. If approved by the
DOA, the approval must include the DOA-authorized signature.
(11) Where paragraph (5) of EASA AD 2023-0044 states ``to
contact AH for corrective action(s) instructions, and within the
compliance time specified therein, to accomplish those instructions
accordingly'' for this AD, replace that text with
[[Page 87825]]
``accomplishing corrective actions in accordance with a method
approved by the FAA, EASA, or Airbus Helicopters' EASA DOA. If
approved by the DOA, the approval must include the DOA-authorized
signature.''
(12) Where paragraph (7) of EASA AD 2023-0044 states ``since new
(first installation a helicopter), or since an overhaul, or since an
inspection in accordance with the instructions of the ASB, as
applicable, and, thereafter, as required by this AD;'' for this AD,
replace that text with ``since new (zero total hours time-in-
service), or since last overhaul if an overhaul has been
accomplished, or since last inspection and any specified corrective
action in accordance with the instructions of the ASB if an
inspection and any specified corrective action by following the
instructions of the ASB have been accomplished, and thereafter as
required by this AD.''.''
(13) This AD does not adopt the ``Remarks'' section of EASA AD
2023-0044.
(i) No Reporting Requirement
Although the material referenced in EASA AD 2023-0044 specifies
to submit certain information to the manufacturer, this AD does not
require that action.
(j) Special Flight Permit
A special flight permit may be issued in accordance with 14 CFR
21.197 and 21.199 to permit a one-time, non-revenue flight to a
location where the actions required by this AD can be accomplished.
This flight must be performed with only essential flight crew.
(k) Alternative Methods of Compliance (AMOCs)
(1) 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 local Flight
Standards District 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. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local Flight Standards District Office/certificate holding
district office.
(l) Related Information
For more information about this AD, contact Dan McCully,
Aviation Safety Engineer, FAA, 1600 Stewart Ave., Suite 410,
Westbury, NY 11590; phone: (404) 474-5548; email:
[email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2023-0044,
dated February 28, 2023.
(ii) [Reserved]
(3) For EASA material identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; phone: +49 221 8999
000; email: [email protected]; website: easa.europa.eu. You may
find the EASA material on the EASA website at ad.easa.europa.eu.
(4) You may view this material at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For information on the availability of
this material at the FAA, call (817) 222-5110.
(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 October 29, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-25615 Filed 11-4-24; 8:45 am]
BILLING CODE 4910-13-P
