Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France), 24556-24560 [2021-08897]
Download as PDF
<![CDATA[
24556
Federal Register / Vol. 86, No. 87 / Friday, May 7, 2021 / Proposed Rules
the FADEC MN4 microprocessor solder ball.
The unsafe condition, if not addressed, could
result in loss of engine thrust control and
reduced control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within the following compliance times
after the effective date of this AD, replace the
full authority digital engine control (FADEC)
integrated circuit (MN4) microprocessor
using an approved overhaul procedure:
(i) For a FADEC MN4 microprocessor with
10,500 or more cycles since new (CSN),
replace the FADEC MN4 microprocessor
before accumulating 500 additional cycles on
the FADEC MN4 microprocessor.
(ii) For a FADEC MN4 microprocessor with
5,000 CSN or more, but fewer than 10,500
CSN, replace the FADEC MN4
microprocessor at the next FADEC
component shop visit or before accumulating
11,000 CSN on the FADEC MN4
microprocessor, whichever occurs first.
(2) Thereafter, repeat the replacement of
the FADEC MN4 microprocessor at the first
FADEC component shop visit after
accumulating 5,000 CSN since the last
replacement but before accumulating 11,000
CSN since the last replacement.
(h) Installation Prohibition
After the effective date of this AD, do not
install onto any engine any FADEC with a
main channel board that was subject to more
than three replacements of the FADEC MN4
microprocessor.
(i) Definition
(1) For the purpose of this AD, an
‘‘approved overhaul procedure’’ is one of the
following:
(i) Replacement of the FADEC MN4
microprocessor using FADEC Internationalapproved maintenance procedures; or
(ii) Replacement of the FADEC MN4
microprocessor using the Accomplishment
Instructions, paragraph 3.A., of GE GE90–100
Service Bulletin 73–0118, Revision 01, dated
April 27, 2021.
(2) For the purpose of this AD, a ‘‘FADEC
component shop visit’’ is the induction of the
FADEC into a repair facility to perform
internal maintenance on the FADEC.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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 certification office,
send it to the attention of the person
identified in Related Information. You may
email your request to: ANE-AD-AMOC@
faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
VerDate Sep<11>2014
17:32 May 06, 2021
Jkt 253001
of the local flight standards district office/
certificate holding district office.
(k) Related Information
(1) For more information about this AD,
contact Stephen Elwin, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone: (781)
238–7236; fax: (781) 238–7199; email:
stephen.l.elwin@faa.gov.
(2) For service information identified in
this AD, contact General Electric Company,
1 Neumann Way, Cincinnati, OH 45215;
phone: (513) 552–3272; email:
aviation.fleetsupport@ae.ge.com; website:
www.ge.com. You may view this referenced
service information at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on
the availability of this material at the FAA,
call (781) 238–7759.
Issued on April 28, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–09291 Filed 5–6–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0175; Project
Identifier 2001–SW–33–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Type Certificate
Previously Held by Eurocopter France)
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
AGENCY:
The FAA is revising a SNPRM
for all Eurocopter France (now Airbus
Helicopters) Model SA–365N, SA–
365N1, AS–365N2, AS 365 N3, and SA–
366G1 helicopters. The SNPRM retained
the proposed requirements in the notice
of proposed rulemaking (NPRM) and
added recurring inspections and
references to an engineering report that
lists approved U.S. alternative fasteners
and materials that may be used in any
required repairs. The FAA is reopening
the comment period because a
significant amount of time has elapsed
since the SNPRM was published. This
proposed AD would require measuring
the 9-degree frame flange (frame) for the
correct edge distance of the four
attachment holes for the stretcher
support and inspecting for cracks, and
repairing the frame, if necessary, as
SUMMARY:
PO 00000
Frm 00044
Fmt 4702
Sfmt 4702
specified in two Direction Ge´ne´rale de
l’Aviation Civile (DGAC) ADs, which
are proposed for incorporation by
reference (IBR). This action also revises
the SNPRM by updating the type
certificate holder’s name and estimated
cost information. The FAA is proposing
this airworthiness directive (AD) to
address the unsafe condition on these
products. Since these actions would
impose an additional burden over those
in the SNPRM, the agency is requesting
comments on this SNPRM.
DATES: The comment period for the
SNPRM published in the Federal
Register on March 11, 2004 (69 FR
11556), is reopened.
The FAA must receive comments on
this SNPRM by June 21, 2021.
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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• 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.
For DGAC material that is proposed
for IBR in this AD, contact the European
Union Aviation Safety Agency (EASA),
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find the DGAC material on the EASA
website at https://ad.easa.europa.eu.
For American Eurocopter material,
contact Airbus Helicopters, 2701 N
Forum Drive, Grand Prairie, TX 75052;
telephone 972–641–0000 or 800–232–
0323; fax 972–641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may view
the DGAC and American Eurocopter
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 DGAC
material is also available in the AD
docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0175–AD.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
E:\FR\FM\07MYP1.SGM
07MYP1
Federal Register / Vol. 86, No. 87 / Friday, May 7, 2021 / Proposed Rules
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0175; 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 SNPRM,
any comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems
Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division,
3960 Paramount Blvd., Lakewood, CA
90712; telephone 562–627–5371; email
blaine.williams@faa.gov.
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–2021–0175; Project Identifier
2001–SW–33–AD’’ 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 https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this proposal.
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 SNPRM
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 SNPRM, 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
VerDate Sep<11>2014
17:32 May 06, 2021
Jkt 253001
will not be placed in the public docket
of this SNPRM. Submissions containing
CBI should be sent to Blaine Williams,
Aerospace Engineer, Cabin Safety &
Environmental Systems Section, Los
Angeles ACO Branch, Compliance &
Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone 562–627–5371; email
blaine.williams@faa.gov. Any
commentary that the FAA receives that
is not specifically designated as CBI will
be placed in the public docket for this
rulemaking.
Background
The DGAC, which was the Technical
Agent for France, issued DGAC AD
2001–061–053(A), dated February 21,
2001 (DGAC AD 2001–061–053(A)) for
certain Model SA–365N, SA–365N1,
AS–365N2, and AS 365 N3 helicopters;
and DGAC AD 2001–283–025(A), dated
July 11, 2001 (DGAC AD 2001–283–
025(A)) for all Model SA–366G1
helicopters (also referred to as the
Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an
unsafe condition for those helicopters.
The FAA issued a SNPRM to amend
14 CFR part 39 by adding an AD that
would apply to all Eurocopter France
Model SA–365N, SA–365N1, AS–
365N2, AS 365 N3, and SA–366G1
helicopters. The FAA preceded the
SNPRM with an NPRM that published
in the Federal Register on December 18,
2002 (67 FR 77444). The NPRM
proposed to require inspecting the frame
for the correct edge distance of the four
attachment holes of the stretcher
support and for a crack, and repairing
the frame, if necessary. The NPRM was
prompted by a quality control check
that revealed some stretcher attachment
holes were improperly located on the
frame where there was insufficient edge
distance.
The first SNPRM published in the
Federal Register on March 11, 2004 (69
FR 11556). The first SNPRM retained
the proposed requirements of the NPRM
and added recurring inspections and
references to an engineering report that
lists approved U.S. alternative fasteners
and materials that may be used in any
required repairs. Additionally, the first
SNPRM stated that the FAA determined
that it is unnecessary to require
installation of a reinforcing angle and
instead will require a 550-hour
repetitive inspection for those
helicopters that have an edge distance
on the frame of less than 5 millimeters
(mm), are not cracked, and have not
been repaired.
PO 00000
Frm 00045
Fmt 4702
Sfmt 4702
24557
Actions Since the SNPRM Was Issued
Since the FAA issued the first
SNPRM, a significant amount of time
elapsed requiring the FAA to reopen the
comment period to allow the public a
chance to comment on the proposed
actions.
Additionally, since the FAA issued
the first SNPRM, Eurocopter France has
changed its name to Airbus Helicopters.
The FAA has revised references to the
manufacturer’s name specified
throughout this SNPRM to identify the
manufacturer’s name as published in
the most recent type certificate data
sheet for the affected models and
updates the contact information to
obtain service documentation. This
SNPRM also updates the estimated cost
information.
Furthermore, since the FAA issued
the first SNPRM, EASA has become the
Technical Agent for the Member States
of the European Union, which includes
France. EASA is now the State of Design
Authority for the affected helicopter
models.
The FAA’s Aircraft Certification
Service has also changed its
organizational structure. The new
structure replaces product directorates
with functional divisions. The FAA
revised some of the office titles and
nomenclature throughout this proposed
AD to reflect the new organizational
changes. Additional information about
the new structure can be found in the
Notice published on July 25, 2017 (82
FR 34564).
Clarification of Requirement To Install
a Reinforcing Angle
The preamble of the first SNPRM
stated that it was unnecessary to require
the installation of a reinforcing angle
but that action was included as a
requirement in the body of the first
SNPRM. This second SNPRM retains
that installation requirement, which
corresponds with the requirements of
the DGAC ADs and addresses the
identified unsafe condition.
Docket Number Change
For transparency and as part of the
FAA’s on-going docket management
consolidation efforts, the FAA is
transferring the docket for this SNPRM
to the Federal Docket Management
System (FDMS). The new Docket
Number (No.) is FAA–2021–0175. The
old Docket No., which is 2001–SW–33–
AD, became the Project Identifier.
Related Service Information Under 1
CFR Part 51
DGAC AD 2001–061–053(A) and
DGAC AD 2001–283–025(A) describe
procedures for measuring the edge
E:\FR\FM\07MYP1.SGM
07MYP1
24558
Federal Register / Vol. 86, No. 87 / Friday, May 7, 2021 / Proposed Rules
information and determining the unsafe
condition described previously is likely
to exist or develop in other products of
these same type designs.
Certain changes described above
expand the scope of the SNPRM. As a
result, the FAA has determined that it
is necessary to reopen the comment
period to provide additional
opportunity for the public to comment
on this SNPRM.
distance of the webs at the four
attachment holes of the stretcher
support on the left and right sides of the
9-degree frame, and additional actions
depending on the findings. The
additional actions include repetitively
inspecting the frame for cracking, repair
if necessary, and installation of a
reinforcement plate (reinforcing angle)
on the frame. These documents are
distinct since they refer to different
helicopter models.
American Eurocopter Engineering
Report No. AEC/03R–E–005,
‘‘Addendum ASB 53.00.42 and 53.00.43
AS365’’, dated January 29, 2003,
specifies U.S. and European rivet
equivalent part numbers, U.S. rivet part
numbers with acceptable substitute
materials with greater strength
properties, and 5 rivet, 6 rivet, and pin
Hi-lok alternatives.
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.
Proposed AD Requirements
This proposed AD would require
accomplishing the actions specified in
DGAC AD 2001–061–053(A) and DGAC
AD 2001–283–025(A), described
previously, as incorporated by
reference, except for any differences
identified as exceptions in the
regulatory text of this AD and except as
discussed under ‘‘Differences Between
this Proposed AD and the MCAI.’’
Comments
The FAA gave the public the
opportunity to participate in developing
this proposed AD. The FAA received no
comments on the first SNPRM or on the
determination of the cost to the public.
FAA’s Determination and Requirements
of This SNPRM
These products have been approved
by the aviation authority of another
country, and are approved for operation
in the United States. Pursuant to the
bilateral agreement with the State of
Design Authority, the FAA has been
notified of the unsafe condition
described in the MCAI referenced
above. The FAA is proposing this AD
after evaluating all the relevant
Explanation of Required Compliance
Information
In the FAA’s ongoing efforts to
improve the efficiency of the AD
process, the FAA initially worked with
Airbus and EASA to develop a process
to use certain EASA ADs as the primary
source of information for compliance
with requirements for corresponding
FAA ADs. As mentioned previously,
when the SNPRM was published the
DGAC was the Technical Agent for
France. Since that time EASA has
become the Technical Agent for the
Member States of the European Union,
which includes France. The FAA has
since coordinated with other
manufacturers and civil aviation
authorities (CAAs) to use this process.
As a result, DGAC AD 2001–061–053(A)
and DGAC AD 2001–283–025(A) will be
incorporated by reference in the FAA
final rule. This proposed AD would,
therefore, require compliance with
DGAC AD 2001–061–053(A) and DGAC
AD 2001–283–025(A) in their 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 the DGAC ADs does not mean
that operators need comply only with
that section. Service information
specified in DGAC AD 2001–061–
053(A) and DGAC AD 2001–283–025(A)
that is required for compliance with
DGAC AD 2001–061–053(A) and DGAC
AD 2001–283–025(A) will be available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0175 after the FAA final rule is
published.
Differences Between This Proposed AD
and the MCAI
The FAA has determined that
acceptable U.S. alternatives to the
fasteners and materials needed to
perform repairs or modifications are
listed in American Eurocopter
Engineering Report No. AEC/03R–E–005
‘‘Addendum ASB 53.00.42 and
53.00.043 AS365’’, dated January 29,
2003.
Where DGAC AD 2001–061–053(A)
exempts helicopters that were delivered
after January 31, 2001, from the
applicability, this proposed AD does not
exempt those helicopters.
Costs of Compliance
The FAA estimates that this proposed
AD affects 31 helicopters of U.S.
registry. The FAA estimates the
following costs to comply with this
proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
3 work-hours × $85 per hour = $255 ..........................................................................................
$100
$355
$11,005
The FAA estimates the following
costs to do any necessary on-condition
actions that would be required based on
the results of any required actions. The
FAA has no way of determining the
number of helicopters that might need
these on-condition actions:
ESTIMATED COSTS OF ON-CONDITION ACTION
Labor cost
Parts cost
Cost per product
Up to 8 work-hours × $85 per hour = $680 ......................................................................................................
$250
Up to $930
VerDate Sep<11>2014
17:32 May 06, 2021
Jkt 253001
PO 00000
Frm 00046
Fmt 4702
Sfmt 4702
E:\FR\FM\07MYP1.SGM
07MYP1
Federal Register / Vol. 86, No. 87 / Friday, May 7, 2021 / Proposed Rules
§ 39.13
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
VerDate Sep<11>2014
17:32 May 06, 2021
Jkt 253001
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France):
Docket No. FAA–2021–0175; Project
Identifier 2001–SW–33–AD.
(a) Comments Due Date
The FAA must receive comments by June
21, 2021.
(b) Affected Airworthiness Directives (ADs)
None.
(c) Applicability
This AD applies to all Airbus Helicopters
(type certificate previously held by
Eurocopter France) Model SA–365N, SA–
365N1, AS–365N2, AS 365 N3, and SA–
366G1 helicopters, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)
Code 5311, Fuselage Main, Frame.
(e) Reason
This AD was prompted by a quality control
check that revealed some stretcher
attachment holes were improperly located on
the frame where there was insufficient edge
distance. The FAA is issuing this AD to
address failure of the 9-degree frame flange
(frame) due to a crack at the stretcher support
attachment holes, which could result in loss
of a passenger door, damage to the rotor
system, and subsequent 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 paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with the applicable Direction
Ge´ne´rale de l’Aviation Civile (DGAC) ADs
specified in paragraphs (g)(1) and (2) of this
AD.
(1) For Model SA–365N, SA–365N1, AS–
365N2, and AS 365 N3 helicopters: DGAC
AD 2001–061–053(A), dated February 21,
2001, (DGAC AD 2001–061–053(A)).
(2) For Model SA–366G1 helicopters:
DGAC AD 2001–283–025(A), dated July 11,
2001 (DGAC AD 2001–283–025(A)).
(h) Exceptions to DGAC AD 2001–061–
053(A) and DGAC AD 2001–283–025(A)
(1) Where paragraph 3.1 of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies an initial compliance time to
do the measurement, for this AD, do the
measurement within 50 hours time-in-service
(TIS) after the effective date of this AD.
(2) Where paragraph 3.1. of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies to do a measurement, for
this AD, do an inspection of the area around
the attachment holes for cracks concurrently
with the measurement.
PO 00000
Frm 00047
Fmt 4702
Sfmt 4702
24559
(3) Where paragraph 3.2.1.a) of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies ‘‘every 550 flight hours,
check that there is no crack in the flange,’’
for this AD, inspect (check) the area around
the attachment holes for cracks at intervals
not to exceed 550 hours TIS.
(4) Where paragraph 3.2.1.b) of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) requires installation of a
reinforcement plate (reinforcing angle) on the
flange for certain helicopters, do the
installation within 550 hours TIS after
accomplishment of the measurement
specified in paragraph 3.1. of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A).
(5) Where the service information referred
to in DGAC AD 2001–061–053(A) and DGAC
AD 2001–283–025(A) specifies to perform a
dye penetrant crack inspection ‘‘if in doubt,’’
this AD requires performing a dye penetrant
inspection.
(6) Where paragraph 3.2.2. of DGAC AD
2001–061–053(A) and DGAC AD 2001–283–
025(A) specifies to do various actions
specified in paragraphs 3.2.2.(a), (b), and (c)
of those ADs, for this AD, if any frame is
cracked, before further flight, repair the
frame. Acceptable U.S. alternatives to the
fasteners and materials needed to perform
repairs or modifications are listed in
American Eurocopter Engineering Report No.
AEC/03R–E–005, ‘‘Addendum ASB 53.00.42
and 53.00.43 AS365’’, dated January 29,
2003.
(7) Where the Note in paragraph 3.2.2. of
DGAC AD 2001–061–053(A) and DGAC AD
2001–283–025(A) specifies the instructions
are no longer applicable after a customized
repair has been carried out, for this AD,
modifying or repairing the frame constitutes
terminating action for the requirements of
this AD.
(i) Special Flight Permit
Special flight permits, as described in 14
CFR 21.197 and 21.199, are prohibited.
(j) 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 (k)(2) 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.
(k) Related Information
(1) For DGAC AD 2001–061–053(A) and
DGAC AD 2001–283–025(A), contact the
European Union Aviation Safety Agency
(EASA), Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
E:\FR\FM\07MYP1.SGM
07MYP1
24560
Federal Register / Vol. 86, No. 87 / Friday, May 7, 2021 / Proposed Rules
www.easa.europa.eu. You may find the
DGAC material on the EASA website at
https://ad.easa.europa.eu. For American
Eurocopter material, contact Airbus
Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone 972–641–0000
or 800–232–0323; fax 972–641–3775; or at
https://www.airbus.com/helicopters/services/
technical-support.html. You may view the
DGAC and American Eurocopter 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
DGAC material may also be found in the AD
docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2021–0175.
(2) For more information about this AD,
contact Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems
Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712;
telephone 562–627–5371; email
blaine.williams@faa.gov.
Issued on April 22, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–08897 Filed 5–6–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0865; Project
Identifier 2010–SW–061–AD]
RIN 2120–AA64
Airworthiness Directives; Bell Textron
Canada Limited (Type Certificate
Previously Held by Bell Helicopter
Textron Canada Limited)
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM).
AGENCY:
The FAA is revising a notice
of proposed rulemaking (NPRM) that
applied to certain Bell Helicopter
Textron Canada Limited (now Bell
Textron Canada Limited) Model 206A,
206B, 206L, 206L–1, 206L–3, and 206L–
4 helicopters. This action revises the
NPRM by revising the format,
rearranging certain paragraphs,
converting a certain table to paragraph
format, and removing certain language.
The FAA is proposing this
airworthiness directive (AD) to address
the unsafe condition on these products.
Since the NPRM was issued, a
significant amount of time has elapsed
requiring the FAA to reopen the
SUMMARY:
VerDate Sep<11>2014
17:32 May 06, 2021
Jkt 253001
comment period to allow the public a
chance to comment on the proposed
actions.
DATES: The FAA must receive comments
on this SNPRM by June 21, 2021.
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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• 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 between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays.
For service information identified in
this SNPRM, contact Bell Helicopter
Textron Canada Limited, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J1R4;
phone: 450–437–2862 or 800–363–8023;
fax: (450) 433–0272; internet: https://
www.bellcustomer.com. You may view
this service information 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.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2010–0865; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains the
NPRM, this SNPRM, 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.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Program Manager,
Large Aircraft Section, International
Validation Branch, Compliance &
Airworthiness Division, FAA, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: (206) 231–3218; email:
kathleen.arrigotti@faa.gov.
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
PO 00000
Frm 00048
Fmt 4702
Sfmt 4702
under ADDRESSES. Include ‘‘Docket No.
FAA–2010–0865; Project Identifier
2010–SW–061–AD’’ 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 again revise 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 https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this proposed
AD.
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 SNPRM
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 SNPRM, 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 SNPRM. Submissions containing
CBI should be sent to Kathleen Arrigotti,
Program Manager, Large Aircraft
Section, International Validation
Branch, Compliance & Airworthiness
Division, FAA, 2200 South 216th St.,
Des Moines, WA 98198; phone and fax:
(206) 231–3218; email:
kathleen.arrigotti@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
The FAA issued an NPRM to amend
14 CFR part 39 by adding an AD that
would apply to certain Bell Helicopter
Textron Canada Limited (now Bell
Textron Canada Limited) Model 206A,
206B, 206L, 206L–1, 206L–3, and 206L–
4 helicopters. The NPRM published in
the Federal Register on August 30, 2010
(75 FR 52914). In the NPRM, the FAA
proposed to require determining if an
E:\FR\FM\07MYP1.SGM
07MYP1
]]>Agencies
[Federal Register Volume 86, Number 87 (Friday, May 7, 2021)]
[Proposed Rules]
[Pages 24556-24560]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-08897]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0175; Project Identifier 2001-SW-33-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.
-----------------------------------------------------------------------
SUMMARY: The FAA is revising a SNPRM for all Eurocopter France (now
Airbus Helicopters) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, and
SA-366G1 helicopters. The SNPRM retained the proposed requirements in
the notice of proposed rulemaking (NPRM) and added recurring
inspections and references to an engineering report that lists approved
U.S. alternative fasteners and materials that may be used in any
required repairs. The FAA is reopening the comment period because a
significant amount of time has elapsed since the SNPRM was published.
This proposed AD would require measuring the 9-degree frame flange
(frame) for the correct edge distance of the four attachment holes for
the stretcher support and inspecting for cracks, and repairing the
frame, if necessary, as specified in two Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) ADs, which are
proposed for incorporation by reference (IBR). This action also revises
the SNPRM by updating the type certificate holder's name and estimated
cost information. The FAA is proposing this airworthiness directive
(AD) to address the unsafe condition on these products. Since these
actions would impose an additional burden over those in the SNPRM, the
agency is requesting comments on this SNPRM.
DATES: The comment period for the SNPRM published in the Federal
Register on March 11, 2004 (69 FR 11556), is reopened.
The FAA must receive comments on this SNPRM by June 21, 2021.
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 https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
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.
For DGAC material that is proposed for IBR in this AD, contact the
European Union Aviation Safety Agency (EASA), Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.easa.europa.eu. You may find the DGAC
material on the EASA website at https://ad.easa.europa.eu. For American
Eurocopter material, contact Airbus Helicopters, 2701 N Forum Drive,
Grand Prairie, TX 75052; telephone 972-641-0000 or 800-232-0323; fax
972-641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may view the DGAC and American Eurocopter
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 DGAC material is also available in the AD docket on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2021-0175-AD.
Examining the AD Docket
You may examine the AD docket on the internet at https://
[[Page 24557]]
www.regulations.gov by searching for and locating Docket No. FAA-2021-
0175; 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 SNPRM, any comments received, and other information. The street
address for Docket Operations is listed above. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer,
Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch,
Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA
90712; telephone 562-627-5371; 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-2021-0175; Project Identifier
2001-SW-33-AD'' 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
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposal.
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 SNPRM 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 SNPRM, 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 SNPRM. Submissions containing CBI should
be sent to Blaine Williams, Aerospace Engineer, Cabin Safety &
Environmental Systems Section, Los Angeles ACO Branch, Compliance &
Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 90712;
telephone 562-627-5371; email [email protected]. Any commentary
that the FAA receives that is not specifically designated as CBI will
be placed in the public docket for this rulemaking.
Background
The DGAC, which was the Technical Agent for France, issued DGAC AD
2001-061-053(A), dated February 21, 2001 (DGAC AD 2001-061-053(A)) for
certain Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters;
and DGAC AD 2001-283-025(A), dated July 11, 2001 (DGAC AD 2001-283-
025(A)) for all Model SA-366G1 helicopters (also referred to as the
Mandatory Continuing Airworthiness Information, or the MCAI), to
correct an unsafe condition for those helicopters.
The FAA issued a SNPRM to amend 14 CFR part 39 by adding an AD that
would apply to all Eurocopter France Model SA-365N, SA-365N1, AS-365N2,
AS 365 N3, and SA-366G1 helicopters. The FAA preceded the SNPRM with an
NPRM that published in the Federal Register on December 18, 2002 (67 FR
77444). The NPRM proposed to require inspecting the frame for the
correct edge distance of the four attachment holes of the stretcher
support and for a crack, and repairing the frame, if necessary. The
NPRM was prompted by a quality control check that revealed some
stretcher attachment holes were improperly located on the frame where
there was insufficient edge distance.
The first SNPRM published in the Federal Register on March 11, 2004
(69 FR 11556). The first SNPRM retained the proposed requirements of
the NPRM and added recurring inspections and references to an
engineering report that lists approved U.S. alternative fasteners and
materials that may be used in any required repairs. Additionally, the
first SNPRM stated that the FAA determined that it is unnecessary to
require installation of a reinforcing angle and instead will require a
550-hour repetitive inspection for those helicopters that have an edge
distance on the frame of less than 5 millimeters (mm), are not cracked,
and have not been repaired.
Actions Since the SNPRM Was Issued
Since the FAA issued the first SNPRM, a significant amount of time
elapsed requiring the FAA to reopen the comment period to allow the
public a chance to comment on the proposed actions.
Additionally, since the FAA issued the first SNPRM, Eurocopter
France has changed its name to Airbus Helicopters. The FAA has revised
references to the manufacturer's name specified throughout this SNPRM
to identify the manufacturer's name as published in the most recent
type certificate data sheet for the affected models and updates the
contact information to obtain service documentation. This SNPRM also
updates the estimated cost information.
Furthermore, since the FAA issued the first SNPRM, EASA has become
the Technical Agent for the Member States of the European Union, which
includes France. EASA is now the State of Design Authority for the
affected helicopter models.
The FAA's Aircraft Certification Service has also changed its
organizational structure. The new structure replaces product
directorates with functional divisions. The FAA revised some of the
office titles and nomenclature throughout this proposed AD to reflect
the new organizational changes. Additional information about the new
structure can be found in the Notice published on July 25, 2017 (82 FR
34564).
Clarification of Requirement To Install a Reinforcing Angle
The preamble of the first SNPRM stated that it was unnecessary to
require the installation of a reinforcing angle but that action was
included as a requirement in the body of the first SNPRM. This second
SNPRM retains that installation requirement, which corresponds with the
requirements of the DGAC ADs and addresses the identified unsafe
condition.
Docket Number Change
For transparency and as part of the FAA's on-going docket
management consolidation efforts, the FAA is transferring the docket
for this SNPRM to the Federal Docket Management System (FDMS). The new
Docket Number (No.) is FAA-2021-0175. The old Docket No., which is
2001-SW-33-AD, became the Project Identifier.
Related Service Information Under 1 CFR Part 51
DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) describe
procedures for measuring the edge
[[Page 24558]]
distance of the webs at the four attachment holes of the stretcher
support on the left and right sides of the 9-degree frame, and
additional actions depending on the findings. The additional actions
include repetitively inspecting the frame for cracking, repair if
necessary, and installation of a reinforcement plate (reinforcing
angle) on the frame. These documents are distinct since they refer to
different helicopter models.
American Eurocopter Engineering Report No. AEC/03R-E-005,
``Addendum ASB 53.00.42 and 53.00.43 AS365'', dated January 29, 2003,
specifies U.S. and European rivet equivalent part numbers, U.S. rivet
part numbers with acceptable substitute materials with greater strength
properties, and 5 rivet, 6 rivet, and pin Hi-lok alternatives.
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.
Comments
The FAA gave the public the opportunity to participate in
developing this proposed AD. The FAA received no comments on the first
SNPRM or on the determination of the cost to the public.
FAA's Determination and Requirements of This SNPRM
These products have been approved by the aviation authority of
another country, and are approved for operation in the United States.
Pursuant to the bilateral agreement with the State of Design Authority,
the FAA has been notified of the unsafe condition described in the MCAI
referenced above. The FAA is proposing this AD after evaluating all the
relevant information and determining the unsafe condition described
previously is likely to exist or develop in other products of these
same type designs.
Certain changes described above expand the scope of the SNPRM. As a
result, the FAA has determined that it is necessary to reopen the
comment period to provide additional opportunity for the public to
comment on this SNPRM.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A), described
previously, as incorporated by reference, except for any differences
identified as exceptions in the regulatory text of this AD and except
as discussed under ``Differences Between this Proposed AD and the
MCAI.''
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA initially worked with Airbus and EASA to develop a
process to use certain EASA ADs as the primary source of information
for compliance with requirements for corresponding FAA ADs. As
mentioned previously, when the SNPRM was published the DGAC was the
Technical Agent for France. Since that time EASA has become the
Technical Agent for the Member States of the European Union, which
includes France. The FAA has since coordinated with other manufacturers
and civil aviation authorities (CAAs) to use this process. As a result,
DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) will be
incorporated by reference in the FAA final rule. This proposed AD
would, therefore, require compliance with DGAC AD 2001-061-053(A) and
DGAC AD 2001-283-025(A) in their 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 the DGAC ADs does not mean that
operators need comply only with that section. Service information
specified in DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A) that
is required for compliance with DGAC AD 2001-061-053(A) and DGAC AD
2001-283-025(A) will be available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0175 after the FAA final rule is published.
Differences Between This Proposed AD and the MCAI
The FAA has determined that acceptable U.S. alternatives to the
fasteners and materials needed to perform repairs or modifications are
listed in American Eurocopter Engineering Report No. AEC/03R-E-005
``Addendum ASB 53.00.42 and 53.00.043 AS365'', dated January 29, 2003.
Where DGAC AD 2001-061-053(A) exempts helicopters that were
delivered after January 31, 2001, from the applicability, this proposed
AD does not exempt those helicopters.
Costs of Compliance
The FAA estimates that this proposed AD affects 31 helicopters of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255........................... $100 $355 $11,005
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
helicopters that might need these on-condition actions:
Estimated Costs of On-Condition Action
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
------------------------------------------------------------------------
Up to 8 work-hours x $85 per hour = $250 Up to $930
$680..............................
------------------------------------------------------------------------
[[Page 24559]]
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 adding the following new airworthiness
directive:
Airbus Helicopters (Type Certificate Previously Held by Eurocopter
France): Docket No. FAA-2021-0175; Project Identifier 2001-SW-33-AD.
(a) Comments Due Date
The FAA must receive comments by June 21, 2021.
(b) Affected Airworthiness Directives (ADs)
None.
(c) Applicability
This AD applies to all Airbus Helicopters (type certificate
previously held by Eurocopter France) Model SA-365N, SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 helicopters, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC) Code 5311, Fuselage Main,
Frame.
(e) Reason
This AD was prompted by a quality control check that revealed
some stretcher attachment holes were improperly located on the frame
where there was insufficient edge distance. The FAA is issuing this
AD to address failure of the 9-degree frame flange (frame) due to a
crack at the stretcher support attachment holes, which could result
in loss of a passenger door, damage to the rotor system, and
subsequent 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 paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with the applicable Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC) ADs specified in paragraphs (g)(1) and (2)
of this AD.
(1) For Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3
helicopters: DGAC AD 2001-061-053(A), dated February 21, 2001, (DGAC
AD 2001-061-053(A)).
(2) For Model SA-366G1 helicopters: DGAC AD 2001-283-025(A),
dated July 11, 2001 (DGAC AD 2001-283-025(A)).
(h) Exceptions to DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A)
(1) Where paragraph 3.1 of DGAC AD 2001-061-053(A) and DGAC AD
2001-283-025(A) specifies an initial compliance time to do the
measurement, for this AD, do the measurement within 50 hours time-
in-service (TIS) after the effective date of this AD.
(2) Where paragraph 3.1. of DGAC AD 2001-061-053(A) and DGAC AD
2001-283-025(A) specifies to do a measurement, for this AD, do an
inspection of the area around the attachment holes for cracks
concurrently with the measurement.
(3) Where paragraph 3.2.1.a) of DGAC AD 2001-061-053(A) and DGAC
AD 2001-283-025(A) specifies ``every 550 flight hours, check that
there is no crack in the flange,'' for this AD, inspect (check) the
area around the attachment holes for cracks at intervals not to
exceed 550 hours TIS.
(4) Where paragraph 3.2.1.b) of DGAC AD 2001-061-053(A) and DGAC
AD 2001-283-025(A) requires installation of a reinforcement plate
(reinforcing angle) on the flange for certain helicopters, do the
installation within 550 hours TIS after accomplishment of the
measurement specified in paragraph 3.1. of DGAC AD 2001-061-053(A)
and DGAC AD 2001-283-025(A).
(5) Where the service information referred to in DGAC AD 2001-
061-053(A) and DGAC AD 2001-283-025(A) specifies to perform a dye
penetrant crack inspection ``if in doubt,'' this AD requires
performing a dye penetrant inspection.
(6) Where paragraph 3.2.2. of DGAC AD 2001-061-053(A) and DGAC
AD 2001-283-025(A) specifies to do various actions specified in
paragraphs 3.2.2.(a), (b), and (c) of those ADs, for this AD, if any
frame is cracked, before further flight, repair the frame.
Acceptable U.S. alternatives to the fasteners and materials needed
to perform repairs or modifications are listed in American
Eurocopter Engineering Report No. AEC/03R-E-005, ``Addendum ASB
53.00.42 and 53.00.43 AS365'', dated January 29, 2003.
(7) Where the Note in paragraph 3.2.2. of DGAC AD 2001-061-
053(A) and DGAC AD 2001-283-025(A) specifies the instructions are no
longer applicable after a customized repair has been carried out,
for this AD, modifying or repairing the frame constitutes
terminating action for the requirements of this AD.
(i) Special Flight Permit
Special flight permits, as described in 14 CFR 21.197 and
21.199, are prohibited.
(j) 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 (k)(2) 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.
(k) Related Information
(1) For DGAC AD 2001-061-053(A) and DGAC AD 2001-283-025(A),
contact the European Union Aviation Safety Agency (EASA), Konrad-
Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000;
email [email protected]; internet
[[Page 24560]]
www.easa.europa.eu. You may find the DGAC material on the EASA
website at https://ad.easa.europa.eu. For American Eurocopter
material, contact Airbus Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone 972-641-0000 or 800-232-0323; fax 972-
641-3775; or at https://www.airbus.com/helicopters/services/technical-support.html. You may view the DGAC and American
Eurocopter 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 DGAC material may also be found in the
AD docket on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0175.
(2) For more information about this AD, contact Blaine Williams,
Aerospace Engineer, Cabin Safety & Environmental Systems Section,
Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960
Paramount Blvd., Lakewood, CA 90712; telephone 562-627-5371; email
[email protected].
Issued on April 22, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-08897 Filed 5-6-21; 8:45 am]
BILLING CODE 4910-13-P
