Airworthiness Directives; Airbus Helicopters, 13989-13992 [2021-05145]
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) For all helicopters, except Model A109S
having S/N 22705 or S/N 22706 and Model
AW109SP having S/N 22384, before further
flight:
(i) Install a placard with the information in
Figure 5 of Leonardo Helicopters Emergency
Alert Service Bulletin (EASB) No. 109S–079
(EASB 109S–079), or Leonardo Helicopters
EASB No. 109SP–120 (EASB 109SP–120),
each Revision A, and each dated June 4,
2018, as applicable to your helicopter model,
in the baggage compartment on the internal
side of the baggage door D8.
(ii) Revise the existing Rotorcraft Flight
Manual (RFM) for your helicopter by cutting
along the dashed line of Figure 6 of EASB
109S–079 or EASB 109SP–120, as applicable
to your model helicopter, and inserting the
cutout to replace page 1–28 or 1–3, as
applicable to your model helicopter, of the
existing RFM for your helicopter.
(2) For all helicopters, except Model A109S
having S/N 22705 or S/N 22706 and Model
AW109SP having S/N 22384, within 5 hours
time-in-service (TIS):
(i) Visually inspect the installation of the
terminal lugs to determine whether the
installation is consistent with Figure 2 of
EASB 109SP–120 or EASB 109S–079, as
applicable to your model helicopter. If the
installation is not consistent with Figure 2 of
EASB 109SP–120 or EASB 109S–079, as
applicable to your model helicopter, restore
the installation to be consistent with Figure
2 of EASB 109SP–120 or EASB 109S–079, as
applicable to your model helicopter.
(ii) Shim the installation of the baggage
fairing assembly (fwd up) part number (P/N)
109–0344–31–101 to move it away from the
circuit breaker panel, and install a silicon
rubber protection over the blind rivets of the
hinge in accordance with the
Accomplishment Instructions, Part II, steps 3
through 8 of EASB 109S–079 or EASB
109SP–120, as applicable to your model
helicopter.
(3) Performing the steps as described in
paragraph (e)(2) of this AD allows the RFM
revision described in paragraph (e)(1) of this
AD to be removed from the existing RFM for
your helicopter and the placard described in
paragraph (e)(1) of this AD to be removed
from the helicopter.
(4) For all helicopters, within 10 hours TIS
and thereafter at intervals not to exceed 25
hours TIS, remove the baggage fairing
assembly (fwd up) P/N 109–0344–31–101,
remove the rubber protections P/N 109–
0746–52–105 and P/N 109–0746–52–107,
and inspect the cable assemblies routing of
both circuit breaker panels for damage. For
the purposes of this inspection, damage may
be indicated by chafing. If there is any
damage, repair or replace the cables in
accordance with FAA accepted procedures
and protect the cables by installing Nomex
sleeve P/N EN6049–006.
(5) For all helicopters, within 200 hours
TIS, modify the helicopter’s baggage
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compartment by adding the protective
coverings in accordance with the
Accomplishment Instructions, Part II, steps 3
through 14 of Leonardo Helicopters EASB
No. 109SP–122, dated July 5, 2018, or
Leonardo Helicopters EASB No. 109S–081,
dated July 5, 2018, as applicable to your
model helicopter. Completion of this
modification is a terminating action for the
25 hour TIS repetitive inspections of
paragraph (e)(4) of this AD.
(f) 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: Kristin
Bradley, Aerospace Engineer, General
Aviation & Rotorcraft Section, International
Validation Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; telephone
817–222–5110; email 9-AVS-AIR-730AMOC@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.
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (now
European Union Aviation Safety Agency)
(EASA) AD No. 2018–0149–E, dated July 13,
2018. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2020–1139.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 5397, Fuselage Wiring, Baggage
Fairings Modification.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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.
(i) Leonardo Helicopters Emergency Alert
Service Bulletin (EASB) No. 109S–079,
Revision A, dated June 4, 2018.
(ii) Leonardo Helicopters EASB 109SP–
120, Revision A, dated June 4, 2018.
(iii) Leonardo Helicopters EASB No.
109SP–122, dated July 5, 2018.
(iv) Leonardo Helicopters EASB No. 109S–
081, dated July 5, 2018.
(3) For service information identified in
this AD, contact Leonardo S.p.A. Helicopters,
Emanuele Bufano, Head of Airworthiness,
Viale G. Agusta 520, 21017 C. Costa di
Samarate (Va) Italy; telephone +39–0331–
225074; fax +39–0331–229046; or at https://
www.leonardocompany.com/en/home.
(4) You may view this service information
at the FAA, Office of the Regional Counsel,
PO 00000
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13989
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177. For
information on the availability of this
material at the FAA, call 817–222–5110.
(5) You may view this 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/ibrlocations.html.
Issued on February 17, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–05147 Filed 3–11–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–1132; Project
Identifier MCAI–2020–01386–R; Amendment
39–21452; AD 2021–05–09]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2018–15–
02, which applied to certain Airbus
Helicopters Model AS350B, AS350B1,
AS350B2, AS350B3, AS350BA, AS355E,
AS355F, AS355F1, AS355F2, AS355N,
and AS355NP helicopters. AD 2018–15–
02 required repetitively inspecting the
tail rotor (TR) pitch rod for a damaged
elastomeric ball joint, and corrective
action if necessary. This AD continues
to require the repetitive inspections and
allows the repetitive inspection interval
to be extended under certain conditions,
as specified in a European Union
Aviation Safety Agency (EASA) AD,
which is incorporated by reference. This
AD was prompted by a report of several
cases of damaged TR pitch rod ball
joints. The FAA is issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective April 16,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 16, 2021.
ADDRESSES: For material incorporated
by reference (IBR) in this AD, contact
the EASA, Konrad-Adenauer-Ufer 3,
SUMMARY:
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
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–2020–1132.
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–2020–
1132; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
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:
Katherine Venegas, Aviation Safety
Engineer, Cabin Safety, Mechanical and
Environmental Systems Section, Los
Angeles ACO Branch, FAA, 3960
Paramount Boulevard, Lakewood, CA
90712–4137; phone: 562–627–5353; fax:
562–627–5210; email:
Katherine.Venegas@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2017–0020R1, dated May 22, 2019
(EASA AD 2017–0020R1) (also referred
to as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for certain Airbus Helicopters Model
AS350B, AS350BA, AS350BB,
AS350B1, AS350B2, AS350B3, AS355E,
AS355F, AS355F1, AS355F2, AS355N
and AS355NP helicopters. Model
AS350BB helicopters are not certificated
by the FAA and are not included on the
U.S. type certificate data sheet; this AD
therefore does not include those
helicopters in the applicability.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2018–15–02,
Amendment 39–19334 (83 FR 34029,
July 19, 2018) (AD 2018–15–02). AD
2018–15–02 applied to certain Airbus
Helicopters Model AS350B, AS350B1,
AS350B2, AS350B3, AS350BA, AS355E,
AS355F, AS355F1, AS355F2, AS355N,
and AS355NP helicopters. The NPRM
published in the Federal Register on
December 16, 2020 (85 FR 81427). The
NPRM was prompted by a report of
several cases of damaged TR pitch rod
ball joints. The NPRM proposed to
continue to require the repetitive
inspections of the TR pitch rod for a
damaged elastomeric ball joint, as
specified in an EASA AD. The NPRM
also proposed to allow the repetitive
inspection intervals specified in AD
2018–15–02 to be extended to
correspond with the intervals for the
inspection of the TR pitch rod specified
in the airworthiness limitation section
of the applicable helicopter
maintenance manual, as specified in an
EASA AD. The FAA is issuing this AD
to address damage to the elastomeric
ball joint on the TR pitch change rod.
This condition could result in failure of
the TR pitch change rod and subsequent
loss of control of the helicopter.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data
and determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. The FAA has
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
EASA AD 2017–0020R1 describes
procedures for repetitively inspecting
the TR pitch rod for a damaged
(debonding, extrusion, or cracking)
elastomeric ball joint and corrective
action. The corrective action includes
replacing an affected TR pitch rod with
a serviceable TR pitch rod. This material
is reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 955 helicopters of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Retained actions from AD 2018–15–02 .........
0.5 work-hour × $85 per hour = $42.50 .........
This new AD adds no new costs to
affected operators.
The FAA estimates the following
costs to do any necessary on-condition
Cost per
product
Parts cost
actions that would be required based on
the results of any required actions. The
FAA has no way of determining the
$0
$42.50
Cost on U.S.
operators
$40,587.50
number of helicopters that might need
these on-condition actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per
product
1 work-hour × $85 per hour = $85 ..........................................................................................................................
$3,358
$3,443
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of 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:
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a. removing Airworthiness Directive
(AD) 2018–15–02, Amendment 39–
19334 (83 FR 34029, July 19, 2018); and
■ b. adding the following new AD:
■
2021–05–09 Airbus Helicopters:
Amendment 39–21452; Docket No.
FAA–2020–1132; Project Identifier
MCAI–2020–01386–R.
(a) Effective Date
This airworthiness directive (AD) is
effective April 16, 2021.
(b) Affected ADs
This AD replaces AD 2018–15–02,
Amendment 39–19334 (83 FR 34029, July 19,
2018) (AD 2018–15–02).
(c) Applicability
This AD applies to Airbus Helicopters
Model AS350B, AS350B1, AS350B2,
AS350B3, AS350BA, AS355E, AS355F,
AS355F1, AS355F2, AS355N, and AS355NP
helicopters, certificated in any category, as
identified in European Union Aviation Safety
Agency (EASA) AD 2017–0020R1, dated May
22, 2019 (EASA AD 2017–0020R1).
(d) Subject
Joint Aircraft System Component (JASC)
Code 6720, Tail Rotor Control System.
(e) Reason
This AD was prompted by a report of
several cases of damaged tail rotor (TR) pitch
rod ball joints. The FAA is issuing this AD
to address damage to the elastomeric ball
joint on the TR pitch change rod. This
condition could result in failure of the TR
pitch change rod and subsequent loss of
control of the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) New 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 2017–0020R1.
(h) Exceptions to EASA AD 2017–0020R1
(1) Where EASA AD 2017–0020R1 refers to
its effective date, this AD requires using the
effective date of this AD.
(2) Where EASA AD 2017–0020R1 refers to
February 9, 2017 (the effective date of EASA
AD 2017–0020–E, dated February 9, 2017),
this AD requires using August 3, 2018 (the
effective date of AD 2018–15–02).
(3) The ‘‘Remarks’’ section of EASA AD
2017–0020R1 does not apply to this AD.
(4) Although the service information
referenced in EASA AD 2017–0020R1
specifies to discard certain parts, this AD
does not include that requirement.
(5) Where EASA AD 2017–0020R1 refers to
flight hours (FH), this AD requires using
hours time-in-service (TIS).
(6) Where paragraph (1) of EASA AD 2017–
0020R1 specifies an initial compliance time
of ‘‘Before exceeding 50 FH [flight hours]
since the last inspection per ALS
[airworthiness limitations] chapter 04–20–00,
PO 00000
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13991
or within 10 FH or 7 days, whichever occurs
first,’’ for this AD, the initial compliance time
is within 10 hours TIS.
(7) For the inspections specified in
paragraph (1) of EASA AD 2017–0020R1:
Accomplishing the actions specified in
paragraphs (h)(7)(i) and (ii) of this AD before
the effective date of this AD are acceptable
for compliance with the inspections specified
in in paragraph (1) of EASA AD 2017–
0020R1. On or after the effective date of this
AD, comply with the inspections as specified
in paragraph (1) of EASA AD 2017–0020R1.
(i) Manually induce a flapping movement
in the TR blade until the pitch change rod
rotates a minimum of 10 degrees.
(ii) Inspect both faces of the blade side of
the ball joint elastomer for debonding,
extrusion, and cracks.
(8) Although the service information
referenced in EASA AD 2017–0020R1
permits certain actions to be performed by a
mechanical engineering technician or pilot,
this AD requires that the actions be
performed by a qualified mechanic.
(i) 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 International Validation Branch, send
it to the attention of the person identified in
paragraph (j) of this AD. Information may be
emailed to: 9-AVS-AIR-730-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.
(j) Related Information
For more information about this AD,
contact Katherine Venegas, Aviation Safety
Engineer, Cabin Safety, Mechanical and
Environmental Systems Section, Los Angeles
ACO Branch, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5353; fax: 562–627–5210;
email: Katherine.Venegas@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 this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2017–0020R1, dated May 22,
2019.
(ii) [Reserved]
(3) For EASA AD 2017–0020R1, 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.
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
(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–2020–1132.
(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 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–05145 Filed 3–11–21; 8:45 am]
BILLING CODE 4910–13–P
Points, and subsequent amendments can
be viewed online at https://
www.faa.gov/air_traffic/publications/.
For further information, you can contact
the Airspace Policy Group, Federal
Aviation Administration, 800
Independence Avenue SW, Washington,
DC 20591; telephone: (202) 267–8783.
The Order is also available for
inspection at the National Archives and
Records Administration (NARA). For
information on the availability of FAA
Order 7400.11E at NARA, email:
fedreg.legal@nara.gov or go to https://
www.archives.gov/federal-register/cfr/
ibr-locations.html.
FOR FURTHER INFORMATION CONTACT:
Rebecca Shelby, Federal Aviation
Administration, Operations Support
Group, Central Service Center, 10101
Hillwood Parkway, Fort Worth, TX
76177; telephone (817) 222–5857.
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
Authority for This Rulemaking
Federal Aviation Administration
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it revokes the
Class E airspace extending upward from
700 feet above the surface at Orange City
Municipal, Orange City, IA and amends
the Class E airspace at Le Mars
Municipal Airport, Le Mars, IA, to
support instrument flight rule
operations at this airport.
14 CFR Part 71
[Docket No. FAA–2020–0664; Airspace
Docket No. 20–ACE–15]
RIN 2120–AA66
Revocation and Amendment of Class E
Airspace; Orange City and Le Mars, IA
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action removes the Class
E airspace extending upward from 700
feet above the surface at Orange City
Municipal Airport, Orange City, IA and
amends the Class E airspace extending
upward from 700 feet above the surface
at the Le Mars Municipal Airport, Le
Mars, IA. This action is the result of an
airspace review caused by the
decommissioning of Orange City (ORC)
non-directional beacon (NDB), and the
Automated Weather Observing System
(AWOS) navigation aids, and the
closure of the Orange City Municipal
Airport. Additionally, the geographical
coordinates for the Le Mars Municipal
Airport, Le Mars, IA, have been updated
to coincide with the FAA’s aeronautical
database.
DATES: Effective 0901 UTC, June 17,
2021. The Director of the Federal
Register approves this incorporation by
reference action under 1 CFR part 51,
subject to the annual revision of FAA
Order 7400.11 and publication of
conforming amendments.
ADDRESSES: FAA Order 7400.11E,
Airspace Designations and Reporting
SUMMARY:
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History
The FAA published a notice of
proposed rulemaking in the Federal
Register (85 FR 62269; October 2, 2020)
for Docket No. FAA–2020–0664 to
remove the Class E airspace extending
upward from 700 feet above the surface
at Orange City Municipal Airport,
Orange City, IA, and amend the Class E
airspace extending upward from 700
feet above the surface at Le Mars
Municipal Airport, Le Mars, IA.
Interested parties were invited to
participate in this rulemaking effort by
submitting written comments on the
proposal to the FAA. One comment
received supporting the proposed
action. No response is provided.
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Class E airspace designations are
published in paragraph 6005 of FAA
Order 7400.11E, dated July 21, 2020,
and effective September 15, 2020, which
is incorporated by reference in 14 CFR
71.1. The Class E airspace designations
listed in this document will be
published subsequently in the Order.
Availability and Summary of
Documents for Incorporation by
Reference
This document amends FAA Order
7400.11E, Airspace Designations and
Reporting Points, dated July 21, 2020,
and effective September 15, 2020. FAA
Order 7400.11E is publicly available as
listed in the ADDRESSES section of this
document. FAA Order 7400.11E lists
Class A, B, C, D, and E airspace areas,
air traffic service routes, and reporting
points.
The Rule
This amendment to 14 CFR part 71
revokes the Class E airspace extending
upward from 700 feet above the surface
at Orange City Municipal Airport,
Orange City, IA, as the instrument
procedures at this airport have been
cancelled and the airport closed, so the
airspace is no longer required.
Amends the Class E airspace
extending upward from 700 feet above
the surface to within 6.4-mile
(decreased from 7.5-mile) radius of Le
Mars Municipal Airport, Le Mars, IA
and removes the Orange City Municipal
Airport; exclusionary language from the
Le Mars Municipal Airport, Le Mars, IA,
airspace legal description; and updates
the geographic coordinates of the airport
to coincide with the FAA’s aeronautical
database.
This action is due to an airspace
review caused by the decommissioning
of the Orange City NDB, and the
Automated Weather Observing System
(AWOS) navigation aids which
provided navigational information to
the instrument procedures at this
airport.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
Regulatory Notices and Analyses
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current, is non-controversial and
unlikely to result in adverse or negative
comments. It, therefore: (1) Is not a
‘‘significant regulatory action’’ under
Executive Order 12866; (2) is not a
‘‘significant rule’’ under DOT
E:\FR\FM\12MRR1.SGM
12MRR1
]]>Agencies
[Federal Register Volume 86, Number 47 (Friday, March 12, 2021)]
[Rules and Regulations]
[Pages 13989-13992]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05145]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1132; Project Identifier MCAI-2020-01386-R;
Amendment 39-21452; AD 2021-05-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2018-15-
02, which applied to certain Airbus Helicopters Model AS350B, AS350B1,
AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N,
and AS355NP helicopters. AD 2018-15-02 required repetitively inspecting
the tail rotor (TR) pitch rod for a damaged elastomeric ball joint, and
corrective action if necessary. This AD continues to require the
repetitive inspections and allows the repetitive inspection interval to
be extended under certain conditions, as specified in a European Union
Aviation Safety Agency (EASA) AD, which is incorporated by reference.
This AD was prompted by a report of several cases of damaged TR pitch
rod ball joints. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective April 16, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 16,
2021.
ADDRESSES: For material incorporated by reference (IBR) in this AD,
contact the EASA, Konrad-Adenauer-Ufer 3,
[[Page 13990]]
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-2020-1132.
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-2020-
1132; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, 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: Katherine Venegas, Aviation Safety
Engineer, Cabin Safety, Mechanical and Environmental Systems Section,
Los Angeles ACO Branch, FAA, 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5353; fax: 562-627-5210; 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 2017-0020R1, dated May 22, 2019
(EASA AD 2017-0020R1) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for certain Airbus Helicopters Model AS350B, AS350BA, AS350BB, AS350B1,
AS350B2, AS350B3, AS355E, AS355F, AS355F1, AS355F2, AS355N and AS355NP
helicopters. Model AS350BB helicopters are not certificated by the FAA
and are not included on the U.S. type certificate data sheet; this AD
therefore does not include those helicopters in the applicability.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2018-15-02, Amendment 39-19334 (83 FR
34029, July 19, 2018) (AD 2018-15-02). AD 2018-15-02 applied to certain
Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA,
AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. The
NPRM published in the Federal Register on December 16, 2020 (85 FR
81427). The NPRM was prompted by a report of several cases of damaged
TR pitch rod ball joints. The NPRM proposed to continue to require the
repetitive inspections of the TR pitch rod for a damaged elastomeric
ball joint, as specified in an EASA AD. The NPRM also proposed to allow
the repetitive inspection intervals specified in AD 2018-15-02 to be
extended to correspond with the intervals for the inspection of the TR
pitch rod specified in the airworthiness limitation section of the
applicable helicopter maintenance manual, as specified in an EASA AD.
The FAA is issuing this AD to address damage to the elastomeric ball
joint on the TR pitch change rod. This condition could result in
failure of the TR pitch change rod and subsequent loss of control of
the helicopter.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA received no comments on the NPRM or
on the determination of the cost to the public.
Conclusion
The FAA reviewed the relevant data and determined that air safety
and the public interest require adopting this final rule as proposed,
except for minor editorial changes. The FAA has determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
EASA AD 2017-0020R1 describes procedures for repetitively
inspecting the TR pitch rod for a damaged (debonding, extrusion, or
cracking) elastomeric ball joint and corrective action. The corrective
action includes replacing an affected TR pitch rod with a serviceable
TR pitch rod. This material is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 955 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2018-15-02... 0.5 work-hour x $85 per $0 $42.50 $40,587.50
hour = $42.50.
----------------------------------------------------------------------------------------------------------------
This new AD adds no new costs to affected operators.
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 Actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
1 work-hour x $85 per hour = $85...... $3,358 $3,443
------------------------------------------------------------------------
[[Page 13991]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. removing Airworthiness Directive (AD) 2018-15-02, Amendment 39-19334
(83 FR 34029, July 19, 2018); and
0
b. adding the following new AD:
2021-05-09 Airbus Helicopters: Amendment 39-21452; Docket No. FAA-
2020-1132; Project Identifier MCAI-2020-01386-R.
(a) Effective Date
This airworthiness directive (AD) is effective April 16, 2021.
(b) Affected ADs
This AD replaces AD 2018-15-02, Amendment 39-19334 (83 FR 34029,
July 19, 2018) (AD 2018-15-02).
(c) Applicability
This AD applies to Airbus Helicopters Model AS350B, AS350B1,
AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N,
and AS355NP helicopters, certificated in any category, as identified
in European Union Aviation Safety Agency (EASA) AD 2017-0020R1,
dated May 22, 2019 (EASA AD 2017-0020R1).
(d) Subject
Joint Aircraft System Component (JASC) Code 6720, Tail Rotor
Control System.
(e) Reason
This AD was prompted by a report of several cases of damaged
tail rotor (TR) pitch rod ball joints. The FAA is issuing this AD to
address damage to the elastomeric ball joint on the TR pitch change
rod. This condition could result in failure of the TR pitch change
rod and subsequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) New 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 2017-0020R1.
(h) Exceptions to EASA AD 2017-0020R1
(1) Where EASA AD 2017-0020R1 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2017-0020R1 refers to February 9, 2017 (the
effective date of EASA AD 2017-0020-E, dated February 9, 2017), this
AD requires using August 3, 2018 (the effective date of AD 2018-15-
02).
(3) The ``Remarks'' section of EASA AD 2017-0020R1 does not
apply to this AD.
(4) Although the service information referenced in EASA AD 2017-
0020R1 specifies to discard certain parts, this AD does not include
that requirement.
(5) Where EASA AD 2017-0020R1 refers to flight hours (FH), this
AD requires using hours time-in-service (TIS).
(6) Where paragraph (1) of EASA AD 2017-0020R1 specifies an
initial compliance time of ``Before exceeding 50 FH [flight hours]
since the last inspection per ALS [airworthiness limitations]
chapter 04-20-00, or within 10 FH or 7 days, whichever occurs
first,'' for this AD, the initial compliance time is within 10 hours
TIS.
(7) For the inspections specified in paragraph (1) of EASA AD
2017-0020R1: Accomplishing the actions specified in paragraphs
(h)(7)(i) and (ii) of this AD before the effective date of this AD
are acceptable for compliance with the inspections specified in in
paragraph (1) of EASA AD 2017-0020R1. On or after the effective date
of this AD, comply with the inspections as specified in paragraph
(1) of EASA AD 2017-0020R1.
(i) Manually induce a flapping movement in the TR blade until
the pitch change rod rotates a minimum of 10 degrees.
(ii) Inspect both faces of the blade side of the ball joint
elastomer for debonding, extrusion, and cracks.
(8) Although the service information referenced in EASA AD 2017-
0020R1 permits certain actions to be performed by a mechanical
engineering technician or pilot, this AD requires that the actions
be performed by a qualified mechanic.
(i) 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 International Validation Branch, send it to the
attention of the person identified in paragraph (j) 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.
(j) Related Information
For more information about this AD, contact Katherine Venegas,
Aviation Safety Engineer, Cabin Safety, Mechanical and Environmental
Systems Section, Los Angeles ACO Branch, FAA, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5353; fax: 562-
627-5210; email: [email protected].
(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 this AD specifies otherwise.
(i) European Union Aviation Safety Agency (EASA) AD 2017-0020R1,
dated May 22, 2019.
(ii) [Reserved]
(3) For EASA AD 2017-0020R1, 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.
[[Page 13992]]
(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-
2020-1132.
(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 19, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-05145 Filed 3-11-21; 8:45 am]
BILLING CODE 4910-13-P
