Airworthiness Directives; Airbus Helicopters, 13159-13162 [2021-04803]
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Federal Register / Vol. 86, No. 43 / Monday, March 8, 2021 / Rules and Regulations
(3) If all 48 fasteners were replaced before
the effective date of this AD by following the
instructions in paragraph (g)(2) of this AD,
then the initial and recurring inspections
detailed in paragraph (g)(1) of this AD are not
required provided you report the information
required by paragraph (h) of this AD.
208B5344, 208B5346 through 208B5350,
208B5353, 208B5354, 208B5356 through
208B5359, 208B5362 through 208B5366,
208B5401, 208B5403, 208B5404, and
208B5408; certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)
Code: 5520, Elevator Structure.
(e) Unsafe Condition
This AD was prompted by reports of loose
elevator torque tube attach fasteners. The
FAA is issuing this AD to detect and correct
loosening and eventual failure of the elevator
torque tube attach fasteners. The unsafe
condition, if not addressed, could result in
loss of elevator control, resulting in loss of
control of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection and Fastener Replacement
(1) At the following compliance times,
inspect each inboard and outboard elevator
torque tube attach fastener for looseness and
fretting by following sections 2.C. and 2.D. of
Task 27–30–00–290, Left and Right Elevator
Torque Tube Attach Points (Borescope)
Special Detailed Inspection, dated October 1,
2018, of the Cessna Model 208 Maintenance
Manual. You must also inspect for
incorrectly installed fasteners.
(i) For airplanes that have accumulated less
than 800 hours time-in-service (TIS) as of the
effective date of this AD, complete the initial
inspection before the airplane accumulates
800 hours TIS or within 200 hours TIS after
the effective date of the AD, whichever
occurs later. Thereafter, repeat the visual
inspection at intervals not to exceed 200
hours TIS until the airplane has accumulated
4,000 hours TIS or until all 48 elevator torque
tube attach fasteners are replaced, whichever
occurs first.
(ii) For airplanes that have accumulated
800 or more hours TIS but less than 4,000
hours TIS as of the effective date of this AD,
complete the initial inspection within 200
hours TIS after the effective date of the AD.
Thereafter, repeat the visual inspection at
intervals not to exceed 200 hours TIS until
the airplane has accumulated 4,000 hours
TIS or until all 48 elevator torque tube attach
fasteners are replaced, whichever occurs first.
(iii) For airplanes that have accumulated
4,000 or more hours TIS as of the effective
date of this AD, complete a one-time visual
inspection within 200 hours TIS after the
effective date of the AD. No repetitive
inspections are required after completion of
the one-time visual inspection.
(2) If there are any loose, fretting, or
incorrectly installed fasteners, remove the
elevator and replace all 48 elevator torque
tube attach fasteners (24 per side, with 12
each on the inboard and outboard elevator
torque tube attach point) before further flight.
Maintain proper alignment by marking each
part prior to removal and by replacing one
fastener at a time. Replacing all 48 fasteners
is terminating action for the repetitive
inspections required by paragraphs (g)(1)(i)
and (ii) of this AD.
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(h) Reporting Requirement
Within 30 days after doing the initial
inspection (regardless if loose, fretting, or
incorrectly installed fasteners were found) or
within 30 days after the effective date of this
AD, whichever occurs later, and then within
30 days after each inspection where loose,
fretting, or incorrectly installed fasteners
were found, report the following information
to the FAA at Wichita-COS@faa.gov:
(1) Name and address of owner.
(2) Date of the inspection.
(3) Name, address, phone number, and
email address of person submitting the
report.
(4) Airplane serial number, registration
number, and total hours TIS on the airplane
at the time of the inspection.
(5) If an earlier inspection identified loose,
fretting, or incorrectly installed fasteners,
identify the hours TIS on the airplane and
which fasteners were replaced, if known, or
if all fasteners were replaced.
(6) If loose, fretting, or incorrectly installed
fasteners were found, detailed information
including a sketch or picture showing the
location of the loose, fretting, or incorrectly
installed fasteners and identification of any
installed supplemental type certificates
(STCs), alterations, repairs, or field approvals
affecting the area of concern.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita ACO 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 the Related
Information section of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(j) Related Information
For more information about this AD,
contact Bobbie Kroetch, Aviation Safety
Engineer, Wichita ACO Branch, FAA, 1801
Airport Road, Wichita, KS 67209; phone:
316–946–4155; fax: 316–946–4107; email:
bobbie.kroetch@faa.gov or Wichita-COS@
faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
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13159
(i) Task 27–30–00–290, Left and Right
Elevator Torque Tube Attach Points
(Borescope) Special Detailed Inspection,
dated October 1, 2018, of the Cessna Model
208 Maintenance Manual.
(ii) [Reserved]
(3) For Textron Aviation, Inc. service
information identified in this AD, contact
Textron Aviation Inc., One Cessna
Boulevard, Wichita, KS 67215; phone: 316–
517–5800; email: teamturbopropsupport@
txtav.com; website: https://
support.cessna.com.
(4) You may view this service information
at FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust St.,
Kansas City, MO 64106. For information on
the availability of this material at the FAA,
call 816–329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email: fedreg.legal@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Issued on February 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–03478 Filed 3–5–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0095; Project
Identifier MCAI–2020–01658–R; Amendment
39–21439; AD 2021–04–17]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Helicopters Model AS350B,
AS350BA, AS350B1, AS350B2,
AS350D, AS355E, AS355F, AS355F1,
AS355F2, and AS355N helicopters. This
AD was prompted by two reports of
debonding of the tail rotor (T/R) blade
leading edge protection shields. This
AD requires repetitively inspecting
certain T/R blades and depending on
the inspection results, replacing the T/
R blade, as specified in a European
Union Aviation Safety Agency (EASA)
AD, which is incorporated by reference
(IBR). This AD also prohibits installing
certain T/R blades. The FAA is issuing
SUMMARY:
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this AD to address the unsafe condition
on these products.
DATES: This AD becomes effective
March 23, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 23, 2021.
The FAA must receive comments on
this AD by April 22, 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 IBR material in this AD, contact
the 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 this
material on the EASA website at https://
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. It is also
available in the AD docket on the
internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0095.
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Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0095; 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 AD, 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:
Kristi Bradley, Aviation Safety Engineer,
General Aviation & Rotorcraft Section,
International Validation Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
kristin.bradley@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
Requirements of This AD
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2020–0224R1, dated November 11, 2020
(EASA AD 2020–0224R1), to correct an
unsafe condition for all Airbus
Helicopters Model AS 350 B, AS 350
BA, AS 350 BB, AS 350 B1, AS350 B2,
AS 350 D, AS 355 E, AS 355 F, AS 355
F1, AS 355 F2, and AS 355 N
helicopters. EASA AD 2020–0224R1
revises EASA AD 2020–0224–E, dated
October 16, 2020, to expand the list of
serviceable parts (post-mod 075580).
This AD was prompted by two reports
of large debonding of the T/R blade
leading edge protection shields.
According to EASA, the design and
assembly procedure of the affected part
(pre-mod 075580) is such that rapid
debonding can occur if humidity/liquid
water reaches the bonding surface
between the leading edge and blade
spar. The FAA is issuing this AD to
prevent failure of the T/R blade, which
could result in loss of tail rotor control
and subsequent loss of control of the
helicopter. See the EASA AD for
additional background information.
This AD requires accomplishing the
actions specified in EASA AD 2020–
0224R1, 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 AD and the EASA AD.’’
Additionally, the owner/operator (pilot)
may perform the required visual checks
but must enter compliance with the
applicable paragraph of this AD in the
helicopter maintenance records in
accordance with 14 CFR 43.9(a)(1)
through (4) and 91.417(a)(2)(v). A pilot
may perform these checks because they
only involve visually checking affected
T/R blade leading edge protection
shields and bonding strips. This action
can be performed equally well by a pilot
or a mechanic. This check is an
exception to the FAA’s standard
maintenance regulations.
Related IBR Material Under 1 CFR Part
51
EASA AD 2020–0224R1 specifies
repetitively visually inspecting each T/
R blade leading edge protection shield
and repetitively tap inspecting each T/
R blade leading edge. EASA AD 2020–
0224R1 also prohibits the installation of
an affected part and specifies a longerterm modification to replace each
affected part with a serviceable part.
EASA AD 2020–0224R1 states that
replacing all affected parts with
serviceable parts on a helicopter
constitutes terminating action for the
repetitive visual and tap inspections.
This material is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
FAA’s Determination
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.
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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. The FAA has since
coordinated with other manufacturers
and civil aviation authorities (CAAs) to
use this process. As a result, EASA AD
2020–0224R1 will be incorporated by
reference in the FAA final rule. This AD
would, therefore, require compliance
with EASA AD 2020–0224R1 in its
entirety, through that incorporation,
except for any differences identified as
exceptions in the regulatory text of this
AD. Using common terms that are the
same as the heading of a particular
section in the EASA AD 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 the EASA AD. Service
information specified in EASA AD
2020–0224R1 that is required for
compliance with EASA AD 2020–
0224R1 is available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0095.
Differences Between This AD and the
EASA AD
The EASA AD applies to all Model
AS 350 B, AS 350 BA, AS 350 BB, AS
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350 B1, AS350 B2, AS 350 D, AS 355
E, AS 355 F, AS 355 F1, AS 355 F2, and
AS 355 N helicopters, whereas this AD
applies to Model AS350B, AS350BA,
AS350B1, AS350B2, AS350D, AS355E,
AS355F, AS355F1, AS355F2, and
AS355N helicopters with certain partnumbered T/R blades installed instead.
This AD does not apply to Model AS
350 BB because this model is not FAA
type-certificated. The EASA AD requires
visually inspecting each T/R blade
leading edge protection shield. This AD
requires visually checking each T/R
blade leading edge protection shield and
bonding strip instead and allows a pilot
to accomplish these visual checks. The
EASA AD requires a longer-term
modification of replacing each affected
part with a serviceable part, whereas
this AD does not. The FAA plans to
publish a notice of proposed rulemaking
to give the public an opportunity to
comment on this longer-term
requirement.
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FAA’s Justification and Determination
of the Effective Date
Section 553(b)(3)(B) of the
Administrative Procedure Act (5 U.S.C.)
authorizes agencies to dispense with
notice and comment procedures for
rules when the agency, for ‘‘good cause’’
finds that those procedures are
‘‘impracticable, unnecessary, or contrary
to the public interest.’’ Under this
section, an agency, upon finding good
cause, may issue a final rule without
seeking comment prior to the
rulemaking.
An unsafe condition exists that
requires the immediate adoption of this
AD without providing an opportunity
for public comments prior to adoption.
The FAA has found that the risk to the
flying public justifies waiving notice
and comment prior to adoption of this
rule because the visual repetitive checks
must be done before each flight and the
initial instance of the repetitive tap
inspections must be done within 30
hours time-in-service, a time period of
up to about 1.5 months based on the
average flight-hour utilization rate of
these helicopters. Accordingly, the
compliance time for the required actions
is shorter than the time necessary for the
public to comment and for publication
of the final rule. Therefore, notice and
opportunity for prior public comment
are impracticable and contrary to public
interest pursuant to 5 U.S.C.
553(b)(3)(B). In addition, for the reasons
stated above, the FAA finds that good
cause exists pursuant to 5 U.S.C. 553(d)
for making this amendment effective in
less than 30 days.
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Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2021–0095; Project Identifier MCAI–
2020–01658–R’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the AD,
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 AD 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 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 AD 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 AD,
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 AD. Submissions containing CBI
should be sent to Kristi Bradley,
Aviation Safety Engineer, General
Aviation & Rotorcraft Section,
International Validation Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
kristin.bradley@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.
Regulatory Flexibility Act (RFA)
The requirements of the RFA do not
apply when an agency finds good cause
pursuant to 5 U.S.C. 553 to adopt a rule
without prior notice and comment.
Because the FAA has determined that it
has good cause to adopt this rule
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without notice and comment, RFA
analysis is not required.
Costs of Compliance
The FAA estimates that this AD
affects 450 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 AD.
Visually checking the T/R blades
takes about 0.25 work-hour for an
estimated cost of $21 per helicopter and
$9,450 for the U.S. fleet, per inspection
cycle. Tap inspecting the T/R blades
takes about 0.5 work-hour for an
estimated cost of $43 per helicopter and
$19,350 for the U.S. fleet, per inspection
cycle. Replacing a T/R blade takes about
12 work-hours and parts cost about
$10,000 for an estimated cost of $11,020
per T/R blade.
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 AD
would not have federalism implications
under Executive Order 13132. This 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 regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
and
(2) Will not affect intrastate aviation
in Alaska.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
2021–04–17 Airbus Helicopters:
Amendment 39–21439; Docket No.
FAA–2021–0095; Project Identifier
MCAI–2020–01658–R.
(a) Effective Date
This airworthiness directive (AD) becomes
effective March 23, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters
Model AS350B, AS350BA, AS350B1,
AS350B2, AS350D, AS355E, AS355F,
AS355F1, AS355F2, and AS355N
helicopters, certificated in any category, with
a tail rotor (T/R) blade part number (P/N)
listed in Appendix 1, Table 1, of European
Union Aviation Safety Agency (EASA) AD
2020–0224R1, dated November 11, 2020
(EASA AD 2020–0224R1) (pre-mod 075580).
(d) Subject
Joint Aircraft System Component (JASC)
Code 6410, Tail Rotor Blades.
(e) Reason
This AD was prompted by two reports of
debonding of the T/R blade leading edge
protection shields. The FAA is issuing this
AD to prevent failure of the T/R blade, which
could result in loss of tail rotor control and
subsequent loss of control of the helicopter.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2020–0224R1.
(h) Exceptions to EASA AD EASA AD 2020–
0224R1
(1) Where EASA AD 2020–0224R1 refers to
flight hours (FH), this AD requires using
hours time-in-service.
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(2) Where EASA AD 2020–0224R1 refers to
October 20, 2020 (the effective date of the
original issuance of its AD (EASA AD 2020–
0224–E, dated October 16, 2020)) and its
effective date, this AD requires using the
effective date of this AD.
(3) Where paragraph (1) of EASA AD 2020–
0224R1 specifies visually inspecting each T/
R blade leading edge protection shield with
instructions in the service information, this
AD requires visually checking each T/R blade
leading edge protection shield and bonding
strip for a distortion, dent, and scratch;
visually checking the area surrounding each
T/R blade leading edge protection along the
skin length for a gap; and visually checking
the area surrounding the bonding strip for a
crack. These visual checks may be performed
by the owner/operator (pilot) holding at least
a private pilot certificate and must be entered
into the aircraft records showing compliance
with this AD in accordance with 14
CFR 43.9(a)(1) through (4) and 14 CFR
91.417(a)(2)(v). The record must be
maintained as required by 14 CFR 91.417,
121.380, or 135.439.
(4) Where paragraph (5) of EASA AD 2020–
0224R1 specifies the modification of
replacing each affected part with a
serviceable part, this AD does not require this
modification.
(5) The ‘‘Remarks’’ section of EASA AD
2020–0224R1 does not apply to this AD.
(i) Parts Installation Prohibition
As of the effective date of this AD, do not
install a T/R blade identified in paragraph (c)
of this AD on any helicopter.
(j) Special Flight Permit
Special flight permits are prohibited if an
installed T/R blade does not pass the visual
or tap inspections.
(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)(1) 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.
(l) Related Information
(1) For more information about this AD,
contact Kristi Bradley, Aviation Safety
Engineer, General Aviation & Rotorcraft
Section, International Validation Branch,
FAA, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone (817) 222–5110; email
kristin.bradley@faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0224R1, dated November
11, 2020.
(ii) [Reserved]
(3) For EASA AD 2020–0224R1, contact the
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 this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) 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.
This material may be found in the AD docket
on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2021–0095.
(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email fedreg.legal@
nara.gov, or go to https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued on February 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–04803 Filed 3–4–21; 11:15 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0682; Product
Identifier 2017–SW–028–AD; Amendment
39–21433; AD 2021–04–12]
RIN 2120–AA64
Airworthiness Directives; Robinson
Helicopter Company Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for
Robinson Helicopter Company
(Robinson) Model R66 helicopters. This
AD was prompted by reports of tail rotor
(T/R) drive shaft forward hanger bearing
failures. This AD requires installing a
certain part numbered kit and removing
parts from service or replacing a certain
part-numbered T/R drive shaft
assembly. This AD also prohibits the
installation of certain parts. The FAA is
SUMMARY:
E:\FR\FM\08MRR1.SGM
08MRR1
]]>Agencies
[Federal Register Volume 86, Number 43 (Monday, March 8, 2021)]
[Rules and Regulations]
[Pages 13159-13162]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-04803]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0095; Project Identifier MCAI-2020-01658-R;
Amendment 39-21439; AD 2021-04-17]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2,
AS350D, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. This
AD was prompted by two reports of debonding of the tail rotor (T/R)
blade leading edge protection shields. This AD requires repetitively
inspecting certain T/R blades and depending on the inspection results,
replacing the T/R blade, as specified in a European Union Aviation
Safety Agency (EASA) AD, which is incorporated by reference (IBR). This
AD also prohibits installing certain T/R blades. The FAA is issuing
[[Page 13160]]
this AD to address the unsafe condition on these products.
DATES: This AD becomes effective March 23, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 23,
2021.
The FAA must receive comments on this AD by April 22, 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 IBR material in this AD, contact the EASA, Konrad-Adenauer-Ufer
3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.easa.europa.eu. You may find this
material on the EASA website at https://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. It is also available in the AD docket on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2021-0095.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0095; 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 AD, 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: Kristi Bradley, Aviation Safety
Engineer, General Aviation & Rotorcraft Section, International
Validation Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222-5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2020-0224R1, dated November 11, 2020
(EASA AD 2020-0224R1), to correct an unsafe condition for all Airbus
Helicopters Model AS 350 B, AS 350 BA, AS 350 BB, AS 350 B1, AS350 B2,
AS 350 D, AS 355 E, AS 355 F, AS 355 F1, AS 355 F2, and AS 355 N
helicopters. EASA AD 2020-0224R1 revises EASA AD 2020-0224-E, dated
October 16, 2020, to expand the list of serviceable parts (post-mod
075580).
This AD was prompted by two reports of large debonding of the T/R
blade leading edge protection shields. According to EASA, the design
and assembly procedure of the affected part (pre-mod 075580) is such
that rapid debonding can occur if humidity/liquid water reaches the
bonding surface between the leading edge and blade spar. The FAA is
issuing this AD to prevent failure of the T/R blade, which could result
in loss of tail rotor control and subsequent loss of control of the
helicopter. See the EASA AD for additional background information.
Related IBR Material Under 1 CFR Part 51
EASA AD 2020-0224R1 specifies repetitively visually inspecting each
T/R blade leading edge protection shield and repetitively tap
inspecting each T/R blade leading edge. EASA AD 2020-0224R1 also
prohibits the installation of an affected part and specifies a longer-
term modification to replace each affected part with a serviceable
part. EASA AD 2020-0224R1 states that replacing all affected parts with
serviceable parts on a helicopter constitutes terminating action for
the repetitive visual and tap inspections.
This material is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section.
FAA's Determination
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.
Requirements of This AD
This AD requires accomplishing the actions specified in EASA AD
2020-0224R1, 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 AD and
the EASA AD.'' Additionally, the owner/operator (pilot) may perform the
required visual checks but must enter compliance with the applicable
paragraph of this AD in the helicopter maintenance records in
accordance with 14 CFR 43.9(a)(1) through (4) and 91.417(a)(2)(v). A
pilot may perform these checks because they only involve visually
checking affected T/R blade leading edge protection shields and bonding
strips. This action can be performed equally well by a pilot or a
mechanic. This check is an exception to the FAA's standard maintenance
regulations.
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. The FAA has
since coordinated with other manufacturers and civil aviation
authorities (CAAs) to use this process. As a result, EASA AD 2020-
0224R1 will be incorporated by reference in the FAA final rule. This AD
would, therefore, require compliance with EASA AD 2020-0224R1 in its
entirety, through that incorporation, except for any differences
identified as exceptions in the regulatory text of this AD. Using
common terms that are the same as the heading of a particular section
in the EASA AD 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 the EASA AD. Service information specified in EASA AD
2020-0224R1 that is required for compliance with EASA AD 2020-0224R1 is
available on the internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2021-0095.
Differences Between This AD and the EASA AD
The EASA AD applies to all Model AS 350 B, AS 350 BA, AS 350 BB, AS
[[Page 13161]]
350 B1, AS350 B2, AS 350 D, AS 355 E, AS 355 F, AS 355 F1, AS 355 F2,
and AS 355 N helicopters, whereas this AD applies to Model AS350B,
AS350BA, AS350B1, AS350B2, AS350D, AS355E, AS355F, AS355F1, AS355F2,
and AS355N helicopters with certain part-numbered T/R blades installed
instead. This AD does not apply to Model AS 350 BB because this model
is not FAA type-certificated. The EASA AD requires visually inspecting
each T/R blade leading edge protection shield. This AD requires
visually checking each T/R blade leading edge protection shield and
bonding strip instead and allows a pilot to accomplish these visual
checks. The EASA AD requires a longer-term modification of replacing
each affected part with a serviceable part, whereas this AD does not.
The FAA plans to publish a notice of proposed rulemaking to give the
public an opportunity to comment on this longer-term requirement.
FAA's Justification and Determination of the Effective Date
Section 553(b)(3)(B) of the Administrative Procedure Act (5 U.S.C.)
authorizes agencies to dispense with notice and comment procedures for
rules when the agency, for ``good cause'' finds that those procedures
are ``impracticable, unnecessary, or contrary to the public interest.''
Under this section, an agency, upon finding good cause, may issue a
final rule without seeking comment prior to the rulemaking.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule
because the visual repetitive checks must be done before each flight
and the initial instance of the repetitive tap inspections must be done
within 30 hours time-in-service, a time period of up to about 1.5
months based on the average flight-hour utilization rate of these
helicopters. Accordingly, the compliance time for the required actions
is shorter than the time necessary for the public to comment and for
publication of the final rule. Therefore, notice and opportunity for
prior public comment are impracticable and contrary to public interest
pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the reasons stated
above, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d)
for making this amendment effective in less than 30 days.
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
ADDRESSES. Include ``Docket No. FAA-2021-0095; Project Identifier MCAI-
2020-01658-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the AD, 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
AD 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 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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to Kristi
Bradley, Aviation Safety Engineer, General Aviation & Rotorcraft
Section, International Validation Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone (817) 222-5110; 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.
Regulatory Flexibility Act (RFA)
The requirements of the RFA do not apply when an agency finds good
cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and
comment. Because the FAA has determined that it has good cause to adopt
this rule without notice and comment, RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 450 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 AD.
Visually checking the T/R blades takes about 0.25 work-hour for an
estimated cost of $21 per helicopter and $9,450 for the U.S. fleet, per
inspection cycle. Tap inspecting the T/R blades takes about 0.5 work-
hour for an estimated cost of $43 per helicopter and $19,350 for the
U.S. fleet, per inspection cycle. Replacing a T/R blade takes about 12
work-hours and parts cost about $10,000 for an estimated cost of
$11,020 per T/R blade.
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 AD would not have federalism
implications under Executive Order 13132. This 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 regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
(2) Will not affect intrastate aviation in Alaska.
[[Page 13162]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2021-04-17 Airbus Helicopters: Amendment 39-21439; Docket No. FAA-
2021-0095; Project Identifier MCAI-2020-01658-R.
(a) Effective Date
This airworthiness directive (AD) becomes effective March 23,
2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Helicopters Model AS350B, AS350BA,
AS350B1, AS350B2, AS350D, AS355E, AS355F, AS355F1, AS355F2, and
AS355N helicopters, certificated in any category, with a tail rotor
(T/R) blade part number (P/N) listed in Appendix 1, Table 1, of
European Union Aviation Safety Agency (EASA) AD 2020-0224R1, dated
November 11, 2020 (EASA AD 2020-0224R1) (pre-mod 075580).
(d) Subject
Joint Aircraft System Component (JASC) Code 6410, Tail Rotor
Blades.
(e) Reason
This AD was prompted by two reports of debonding of the T/R
blade leading edge protection shields. The FAA is issuing this AD to
prevent failure of the T/R blade, which could result in loss of tail
rotor control 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, EASA AD 2020-0224R1.
(h) Exceptions to EASA AD EASA AD 2020-0224R1
(1) Where EASA AD 2020-0224R1 refers to flight hours (FH), this
AD requires using hours time-in-service.
(2) Where EASA AD 2020-0224R1 refers to October 20, 2020 (the
effective date of the original issuance of its AD (EASA AD 2020-
0224-E, dated October 16, 2020)) and its effective date, this AD
requires using the effective date of this AD.
(3) Where paragraph (1) of EASA AD 2020-0224R1 specifies
visually inspecting each T/R blade leading edge protection shield
with instructions in the service information, this AD requires
visually checking each T/R blade leading edge protection shield and
bonding strip for a distortion, dent, and scratch; visually checking
the area surrounding each T/R blade leading edge protection along
the skin length for a gap; and visually checking the area
surrounding the bonding strip for a crack. These visual checks may
be performed by the owner/operator (pilot) holding at least a
private pilot certificate and must be entered into the aircraft
records showing compliance with this AD in accordance with 14 CFR
43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must
be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
(4) Where paragraph (5) of EASA AD 2020-0224R1 specifies the
modification of replacing each affected part with a serviceable
part, this AD does not require this modification.
(5) The ``Remarks'' section of EASA AD 2020-0224R1 does not
apply to this AD.
(i) Parts Installation Prohibition
As of the effective date of this AD, do not install a T/R blade
identified in paragraph (c) of this AD on any helicopter.
(j) Special Flight Permit
Special flight permits are prohibited if an installed T/R blade
does not pass the visual or tap inspections.
(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)(1) 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
(1) For more information about this AD, contact Kristi Bradley,
Aviation Safety Engineer, General Aviation & Rotorcraft Section,
International Validation Branch, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; telephone (817) 222-5110; email
[email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2020-0224R1,
dated November 11, 2020.
(ii) [Reserved]
(3) For EASA AD 2020-0224R1, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
[email protected]; internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
(4) 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. This material may be
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2021-0095.
(5) You may view this material that is incorporated by reference
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, email
[email protected], or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on February 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-04803 Filed 3-4-21; 11:15 am]
BILLING CODE 4910-13-P
