Airworthiness Directives; Airbus Helicopters, 13972-13975 [2021-05142]
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
more protective of public health than
TSA’s mandatory measures.
II. TSOB Ratification
The Aviation and Transportation
Security Act (the Act) establishes the
TSOB and provides that the TSOB shall
‘‘review and ratify or disapprove’’
security directives issued by TSA under
49 U.S.C. 114(l)(2).7 The Act further
states that such directives ‘‘shall remain
effective for a period not to exceed 90
days unless ratified or disapproved by
the Board or rescinded by the
Administrator.’’ 8
Pursuant to these authorities, the
Senior Official Performing the Duties of
the Deputy Secretary of Homeland
Security, in his capacity as chairman of
the TSOB, requested TSOB review of
the SD.9 On February 28, 2021, the
TSOB ratified TSA Security Directive
1582/84–21–01. As part of this
ratification, the TSOB also ratified any
extension of the SD for a period no
longer than the period of time that the
Secretary’s national emergency
determination and the CDC Order
remain in effect should the TSA
Administrator determine that such an
extension is warranted to support
implementation of the Executive Order,
the national emergency determination,
and the CDC order.
The SD is available in the docket for
this notice at https://
www.regulations.gov/.
David P. Pekoske,
Senior Official Performing the Duties of
Deputy Secretary of Homeland Security &
Chairman of the Transportation Security
Oversight Board, U.S. Department of
Homeland Security.
[FR Doc. 2021–05241 Filed 3–10–21; 4:15 pm]
BILLING CODE 9110–9M–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–1123; Project
Identifier MCAI–2020–01294–R; Amendment
39–21448; AD 2021–05–05]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
7 49
U.S.C. 115(a) and (c)(1).
114(l)(2)(B).
9 DHS Delegation No. 7071.1, Delegation to the
Deputy Secretary to Chair the Transportation
Security Oversight Board (Apr. 2, 2007).
8 Id.
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The FAA is superseding
Airworthiness Directive (AD) 2016–23–
05, which applied to certain Airbus
Helicopters Model SA–365N1, AS–
365N2, AS 365 N3, SA–366G1, EC 155B,
and EC155B1 helicopters. AD 2016–23–
05 required repetitive checks of the oil
level of the tail rotor gearbox and, if
necessary, filling the oil to the
maximum level; and replacement of a
certain control rod double bearing
(bearing) with a new bearing. This AD
retains the requirements of AD 2016–
23–05 and also requires modifying the
helicopter by replacing the tail gearbox
(TGB) control shaft guide bushes;
repetitive inspections of the TGB
magnetic plug and corrective actions if
necessary; repetitive replacements of the
bearing; and modifying the helicopter
by replacing the TGB; as specified in a
European Aviation Safety Agency (now
European Union Aviation Safety
Agency) (EASA) AD, which is
incorporated by reference. This AD also
adds helicopters to the applicability.
This AD was prompted by reports of
occurrences of loss of yaw control due
to failure of the TGB bearing. 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,
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–2020–1123.
SUMMARY:
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–
1123; 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
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Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Aviation Safety
Engineer, Large Aircraft Section,
International Validation Branch, FAA,
2200 South 216th St., Des Moines, WA
98198; telephone and fax 206–231–
3218; email kathleen.arrigotti@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2017–0125, dated July 21, 2017 (EASA
AD 2017–0125) (also referred to as the
Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an
unsafe condition for all Airbus
Helicopters Model SA 365 N1, AS 365
N2, AS 365 N3, SA 366 G1, EC 155 B,
and EC 155 B1 helicopters. EASA AD
2017–0125 supersedes EASA AD 2017–
0007, dated January 13, 2017, which
superseded EASA AD 2016–0097R1,
dated May 25, 2016 (which corresponds
to FAA AD 2016–23–05). EASA AD
2017–0125 adds helicopters to the
applicability, adds repetitive
inspections of the magnetic plug after
bearing replacement, requires the use of
the revised Airbus Helicopters Alert
Service Bulletin (ASB) instructions, and
requires replacement of the TGB with a
modified unit, which terminates the
repetitive inspections.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–23–05,
Amendment 39–18712 (81 FR 85126,
November 25, 2016) (AD 2016–23–05).
AD 2016–23–05 applied to certain
Airbus Helicopters Model SA–365N1,
AS–365N2, AS 365 N3, SA–366G1, EC
155B, and EC155B1 helicopters. The
NPRM published in the Federal
Register on December 14, 2020 (85 FR
80689). The NPRM was prompted by a
determination that additional
inspections, replacements, and
modifications are necessary to address
the unsafe condition. The NPRM
proposed to retain the requirements of
AD 2016–23–05 and also require
modifying the helicopter by replacing
the TGB control shaft guide bushes;
repetitive inspections of the TGB
magnetic plug and corrective actions if
necessary; repetitive replacements of the
bearing; and modifying the helicopter
by replacing the TGB; as specified in an
EASA AD. The NPRM also proposed to
add helicopters to the applicability.
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
and replacing the bearing), repetitive
replacements of the bearing; and
modifying the helicopter by replacing
the TGB.
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.
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.
The FAA is issuing this AD to address
damage to the bearing, which could
result in end play, loss of tail rotor pitch
control, and subsequent loss of control
of the helicopter. See the MCAI for
additional background information.
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.
Related Service Information Under 1
CFR Part 51
Update to the Costs of Compliance
The FAA has updated the costs for the
new required actions and on-condition
actions based on data received since the
NPRM was issued.
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
Explanation of Retained Requirements
EASA AD 2017–0125 describes
procedures for modifying the helicopter
by replacing TGB control shaft guide
bushes, repetitive inspections (checks)
of the oil level of the tail rotor gearbox
and, if necessary, filling the oil to the
maximum level, repetitive inspections
of the TGB magnetic plug for the
presence of particles and corrective
actions if necessary (corrective actions
include removing the TGB, complying
with certain work cards to address
particles and other conditions such as
abrasions, scales, flakes, and splinters,
Although this AD does not explicitly
restate the requirements of AD 2016–
23–05, this AD retains certain
requirements of AD 2016–23–05. Those
requirements are referenced in
paragraphs (2) and (5) of EASA AD
2017–0125, which, in turn, is referenced
in paragraph (g) of this AD.
Costs of Compliance
The FAA estimates that this AD
affects 52 helicopters of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
Retained actions from
AD 2016–23–05.
New actions ...............
17 work-hours × $85 per hour = $1,445 ........
$1,125 ........................
$2,570 ........................
$133,640.
71 work-hours × $85 per hour = $6,035 ........
Up to $155,300 ..........
Up to $161,335 ..........
Up to $8,389,420.
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Labor cost
Parts cost
Cost per
product
Up to 8 work-hours × $85 per hour = $680 ............................................................................................................
$0
$680
Labor cost
Parts cost
Cost per
product
Up to 4 work-hours × $85 per hour = $340 ............................................................................................................
Up to $1,395
Up to $1,735
ESTIMATED COSTS OF ON-CONDITION ACTIONS
According to the manufacturer, some
or all of the costs of this AD may be
covered under warranty, thereby
reducing the cost impact on affected
operators. The FAA does not control
warranty coverage for affected operators.
As a result, the FAA has included all
known costs in this cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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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
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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.
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
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
removing Airworthiness Directive (AD)
2016–23–05, Amendment 39–18712 (81
FR 85126, November 25, 2016), and
adding the following new AD:
■
2021–05–05 Airbus Helicopters:
Amendment 39–21448 Docket No. FAA–
2020–1123; Project Identifier MCAI–
2020–01294–R.
(a) Effective Date
This airworthiness directive (AD) is
effective April 16, 2021.
(b) Affected ADs
This AD replaces AD 2016–23–05,
Amendment 39–18712 (81 FR 85126,
November 25, 2016) (AD 2016–23–05).
(c) Applicability
This AD applies to Airbus Helicopters
Model SA–365N1, AS–365N2, AS 365 N3,
SA–366G1, EC 155B, and EC155B1
helicopters, certificated in any category, all
serial numbers.
(d) Subject
Joint Aircraft System Component (JASC)
Code 65, Tail Rotor.
(e) Reason
This AD was prompted by reports of
occurrences of loss of yaw control due to
failure of the tail gearbox (TGB) control rod
double bearing (bearing). This AD was also
prompted by the determination that
additional inspections, replacements, and
modifications are necessary to address the
unsafe condition. The FAA is issuing this AD
to address damage to the bearing, which
could result in end play, loss of tail rotor
pitch 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, European Aviation Safety
Agency (now European Union Aviation
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Safety Agency) (EASA) AD 2017–0125, dated
July 21, 2017 (EASA AD 2017–0125).
(h) Exceptions to EASA AD 2017–0125
(1) Where EASA AD 2017–0125 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where EASA AD 2017–0125 refers to
June 4, 2011 (the effective date of EASA AD
2011–0105), this AD requires using the
effective date of this AD.
(3) Where EASA AD 2017–0125 refers to
May 25, 2016 (the effective date of EASA AD
2016–0197R1), this AD requires using the
effective date of this AD.
(4) The ‘‘Remarks’’ section of EASA AD
2017–0125 does not apply to this AD.
(5) Where paragraph (2) of EASA AD 2017–
0125 requires inspections (checks) to be done
‘‘in accordance with the instructions of
Paragraph 3.B.1 of the applicable inspection
ASB,’’ for this AD, those instructions are for
reference only and are not required for the
actions in paragraph (2) of EASA AD 2017–
0125. The inspections (checks) required by
paragraph (2) of EASA AD 2017–0125 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.
(6) Where paragraph (5) of EASA AD 2017–
0125 specifies to ‘‘accomplish the applicable
corrective action(s) in accordance with the
instructions of Paragraph 3.B.1 of the
applicable inspection ASB,’’ for this AD, a
qualified mechanic must add oil to the TGB
to the ‘‘max’’ level if the oil level is not at
maximum. The instructions are for reference
only and are not required for the actions in
paragraph (5) of EASA AD 2017–0125.
(7) Where EASA AD 2017–0125 refers to
flight hours (FH), this AD requires using
hours time-in-service.
(8) Where EASA AD 2017–0125 requires
action after the last flight of the day or
‘‘ALF,’’ this AD requires those actions before
the first flight of the day.
(9) Where the service information referred
to in EASA AD 2017–0125 specifies to
perform a metallurgical analysis and contact
the manufacturer if collected particles are not
clearly characterized, this AD does not
require contacting the manufacturer to
determine the characterization of the
particles collected.
(10) Although service information
referenced in EASA AD 2017–0125 specifies
to scrap parts, this AD does not include that
requirement.
(11) Although service information
referenced in EASA AD 2017–0125 specifies
reporting information to Airbus Helicopters
and filling in a ‘‘particle detection’’ followup sheet, this AD does not include those
requirements.
(12) Although service information
referenced in EASA AD 2017–0125 specifies
returning certain parts to an approved
workshop, this AD does not include that
requirement.
(13) Where paragraph (6) of EASA AD
2017–0125 refers to ‘‘any discrepancy,’’ for
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this AD, discrepancies include the presence
of particles and other conditions such as
abrasions, scales, flakes, and splinters.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Strategic Policy
Rotorcraft Section, 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 Strategic Policy
Rotorcraft Section, send it to: Manager,
Strategic Policy Rotorcraft Section, FAA,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110. Information
may be emailed to: 9-ASW-FTW-AMOCRequests@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 Kathleen Arrigotti, Aviation Safety
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218; email
kathleen.arrigotti@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 Aviation Safety Agency
(EASA) AD 2017–0125, dated July 21, 2017.
(ii) [Reserved].
(3) For EASA AD 2017–0125, 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–2020–1123.
(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.
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Federal Register / Vol. 86, No. 47 / Friday, March 12, 2021 / Rules and Regulations
Issued on February 17, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
availability of this material at the FAA,
call 817–222–5110.
[FR Doc. 2021–05142 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–2015–4497; Project
Identifier 2016–SW–011–AD; Amendment
39–21450; AD 2021–05–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters Deutschland GmbH (Type
Certificate Previously Held by
Eurocopter Deutschland GmbH)
Helicopters
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for Airbus
Helicopters Deutschland GmbH (Airbus
Helicopters) Model BO–105A, BO–
105C, BO–105S, MBB–BK 117 A–1,
MBB–BK 117 A–3, MBB–BK 117 A–4,
MBB–BK 117 B–1, MBB–BK 117 B–2,
and MBB–BK 117 C–1 helicopters. This
AD was prompted by a report of a loss
of electrical ground between the startergenerator and the generator voltage
regulator (regulator). This AD requires
inspecting the starter-generator
electrical ground connection, retrofitting
the starter-generator wire harness, and
depending on model, revising the
existing Rotorcraft Flight Manual (RFM)
for your helicopter. 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 certain publications listed in this AD
as of April 16, 2021.
ADDRESSES: For Eurocopter service
information identified in this final rule,
contact Airbus Helicopters, 2701 N
Forum Drive, Grand Prairie, TX 75052;
telephone 972–641–0000 or 800–232–
0323; fax 972–641–3775; or at https://
www.airbus.com/helicopters/services/
technical-support.html. You may view
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
SUMMARY:
VerDate Sep<11>2014
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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–2015–
4497; 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 street 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:
Ronnea L. Derby, Aerospace Engineer,
Denver ACO Branch, FAA, 26805 East
68th Ave., Room 214, Denver, CO
80249; telephone 303–342–1093; email
ronnea.l.derby.@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(now European Union Aviation Safety
Agency) (EASA), which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2015–0098, dated June 2, 2015 (EASA
AD 2015–0098), and EASA AD 2015–
0220, dated November 9, 2015 (EASA
AD 2015–0220) (also referred to as the
Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an
unsafe condition for all Airbus
Helicopters Model MBB–BK117 A–1,
MBB–BK117 A–3, MBB–BK117 A–4,
MBB–BK117 B–1, MBB–BK117 B–2,
and MBB–BK117 C–1 helicopters; and
Airbus Helicopters Model BO105 A,
BO105 C, BO105 D and BO105 S
helicopters with certain part-numbered
voltage regulators.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Helicopters
Model BO–105A, BO–105C, and BO–
105S helicopters; and all Airbus
Helicopters Model MBB–BK 117 A–1,
MBB–BK 117 A–3, MBB–BK 117 A–4,
MBB–BK 117 B–1, MBB–BK 117 B–2,
and MBB–BK 117 C–1 helicopters. The
NPRM published in the Federal
Register on July 16, 2020 (85 FR 43153).
The NPRM was prompted by a report of
a loss of electrical ground between the
starter-generator and the regulator. The
NPRM proposed to require inspecting
the starter-generator electrical ground
connection, retrofitting the startergenerator wire harness, and depending
on model, revising the existing RFM for
your helicopter.
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13975
The FAA is issuing this AD to address
the loss of electrical ground between the
starter-generator and the regulator. This
condition could result in an overvoltage
of electrical power, damage to electronic
equipment, 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
Eurocopter (now Airbus Helicopters)
issued Alert Service Bulletin ASB–
MBB–BK117–90–118, Revision 2, dated
May 4, 2009, for certain Model MBB–
BK117 helicopters and Alert Service
Bulletin ASB BO105–90–103, Revision
4, dated June 21, 2010, for certain Model
BO105 helicopters. This service
information specifies a visual inspection
for damage, corrosion, and cracks and
measuring the resistance of the left-hand
and right-hand electrical ground
connections between each startergenerator and the regulator. If there is
damage or suspected damage, or if the
resistance is out of tolerance, this
service information specifies replacing
the wire terminal. This service
information also specifies performing
the visual inspection and resistance
measurement each time the starter
generator is removed or the wiring is
disconnected until a retrofit ground
connection is installed. These
documents are distinct since they apply
to different models.
Eurocopter also issued Eurocopter
Flight Manual BK117 A–3 Temporary
Revision 9, Eurocopter Flight Manual
BK117 A–4 Temporary Revision 5,
Eurocopter Flight Manual BK117 B–1
Temporary Revision 6, Eurocopter
Flight Manual BK 117 B–2 Temporary
Revision 1, and Eurocopter Flight
Manual BK 117 C–1 Temporary
Revision 2, all dated September 22,
2006, to provide updated procedures in
the event of a generator failure. These
E:\FR\FM\12MRR1.SGM
12MRR1
]]>Agencies
[Federal Register Volume 86, Number 47 (Friday, March 12, 2021)]
[Rules and Regulations]
[Pages 13972-13975]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-05142]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-1123; Project Identifier MCAI-2020-01294-R;
Amendment 39-21448; AD 2021-05-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2016-23-
05, which applied to certain Airbus Helicopters Model SA-365N1, AS-
365N2, AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters. AD 2016-
23-05 required repetitive checks of the oil level of the tail rotor
gearbox and, if necessary, filling the oil to the maximum level; and
replacement of a certain control rod double bearing (bearing) with a
new bearing. This AD retains the requirements of AD 2016-23-05 and also
requires modifying the helicopter by replacing the tail gearbox (TGB)
control shaft guide bushes; repetitive inspections of the TGB magnetic
plug and corrective actions if necessary; repetitive replacements of
the bearing; and modifying the helicopter by replacing the TGB; as
specified in a European Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD, which is incorporated by reference.
This AD also adds helicopters to the applicability. This AD was
prompted by reports of occurrences of loss of yaw control due to
failure of the TGB bearing. 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, 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-2020-1123.
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-
1123; 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: Kathleen Arrigotti, Aviation Safety
Engineer, Large Aircraft Section, International Validation Branch, FAA,
2200 South 216th St., Des Moines, WA 98198; telephone and fax 206-231-
3218; 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 2017-0125, dated July 21, 2017 (EASA
AD 2017-0125) (also referred to as the Mandatory Continuing
Airworthiness Information, or the MCAI), to correct an unsafe condition
for all Airbus Helicopters Model SA 365 N1, AS 365 N2, AS 365 N3, SA
366 G1, EC 155 B, and EC 155 B1 helicopters. EASA AD 2017-0125
supersedes EASA AD 2017-0007, dated January 13, 2017, which superseded
EASA AD 2016-0097R1, dated May 25, 2016 (which corresponds to FAA AD
2016-23-05). EASA AD 2017-0125 adds helicopters to the applicability,
adds repetitive inspections of the magnetic plug after bearing
replacement, requires the use of the revised Airbus Helicopters Alert
Service Bulletin (ASB) instructions, and requires replacement of the
TGB with a modified unit, which terminates the repetitive inspections.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2016-23-05, Amendment 39-18712 (81 FR
85126, November 25, 2016) (AD 2016-23-05). AD 2016-23-05 applied to
certain Airbus Helicopters Model SA-365N1, AS-365N2, AS 365 N3, SA-
366G1, EC 155B, and EC155B1 helicopters. The NPRM published in the
Federal Register on December 14, 2020 (85 FR 80689). The NPRM was
prompted by a determination that additional inspections, replacements,
and modifications are necessary to address the unsafe condition. The
NPRM proposed to retain the requirements of AD 2016-23-05 and also
require modifying the helicopter by replacing the TGB control shaft
guide bushes; repetitive inspections of the TGB magnetic plug and
corrective actions if necessary; repetitive replacements of the
bearing; and modifying the helicopter by replacing the TGB; as
specified in an EASA AD. The NPRM also proposed to add helicopters to
the applicability.
[[Page 13973]]
The FAA is issuing this AD to address damage to the bearing, which
could result in end play, loss of tail rotor pitch control, and
subsequent loss of control of the helicopter. See the MCAI for
additional background information.
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.
Update to the Costs of Compliance
The FAA has updated the costs for the new required actions and on-
condition actions based on data received since the NPRM was issued.
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 2017-0125 describes procedures for modifying the helicopter
by replacing TGB control shaft guide bushes, repetitive inspections
(checks) of the oil level of the tail rotor gearbox and, if necessary,
filling the oil to the maximum level, repetitive inspections of the TGB
magnetic plug for the presence of particles and corrective actions if
necessary (corrective actions include removing the TGB, complying with
certain work cards to address particles and other conditions such as
abrasions, scales, flakes, and splinters, and replacing the bearing),
repetitive replacements of the bearing; and modifying the helicopter by
replacing the TGB.
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.
Explanation of Retained Requirements
Although this AD does not explicitly restate the requirements of AD
2016-23-05, this AD retains certain requirements of AD 2016-23-05.
Those requirements are referenced in paragraphs (2) and (5) of EASA AD
2017-0125, which, in turn, is referenced in paragraph (g) of this AD.
Costs of Compliance
The FAA estimates that this AD affects 52 helicopters of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2016- 17 work-hours x $85 $1,125........... $2,570........... $133,640.
23-05. per hour = $1,445.
New actions.................... 71 work-hours x $85 Up to $155,300... Up to $161,335... Up to $8,389,420.
per hour = $6,035.
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Estimated Costs for Optional Actions
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Cost per
Labor cost Parts cost product
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Up to 8 work-hours x $85 per hour = $0 $680
$680.................................
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Estimated Costs of On-Condition Actions
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Cost per
Labor cost Parts cost product
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Up to 4 work-hours x $85 per hour = Up to $1,395 Up to $1,735
$340.................................
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According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators. The FAA does not control warranty coverage for
affected operators. As a result, the FAA has included all known costs
in this cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
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.
[[Page 13974]]
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 removing Airworthiness Directive (AD)
2016-23-05, Amendment 39-18712 (81 FR 85126, November 25, 2016), and
adding the following new AD:
2021-05-05 Airbus Helicopters: Amendment 39-21448 Docket No. FAA-
2020-1123; Project Identifier MCAI-2020-01294-R.
(a) Effective Date
This airworthiness directive (AD) is effective April 16, 2021.
(b) Affected ADs
This AD replaces AD 2016-23-05, Amendment 39-18712 (81 FR 85126,
November 25, 2016) (AD 2016-23-05).
(c) Applicability
This AD applies to Airbus Helicopters Model SA-365N1, AS-365N2,
AS 365 N3, SA-366G1, EC 155B, and EC155B1 helicopters, certificated
in any category, all serial numbers.
(d) Subject
Joint Aircraft System Component (JASC) Code 65, Tail Rotor.
(e) Reason
This AD was prompted by reports of occurrences of loss of yaw
control due to failure of the tail gearbox (TGB) control rod double
bearing (bearing). This AD was also prompted by the determination
that additional inspections, replacements, and modifications are
necessary to address the unsafe condition. The FAA is issuing this
AD to address damage to the bearing, which could result in end play,
loss of tail rotor pitch 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, European Aviation Safety Agency (now European Union
Aviation Safety Agency) (EASA) AD 2017-0125, dated July 21, 2017
(EASA AD 2017-0125).
(h) Exceptions to EASA AD 2017-0125
(1) Where EASA AD 2017-0125 refers to its effective date, this
AD requires using the effective date of this AD.
(2) Where EASA AD 2017-0125 refers to June 4, 2011 (the
effective date of EASA AD 2011-0105), this AD requires using the
effective date of this AD.
(3) Where EASA AD 2017-0125 refers to May 25, 2016 (the
effective date of EASA AD 2016-0197R1), this AD requires using the
effective date of this AD.
(4) The ``Remarks'' section of EASA AD 2017-0125 does not apply
to this AD.
(5) Where paragraph (2) of EASA AD 2017-0125 requires
inspections (checks) to be done ``in accordance with the
instructions of Paragraph 3.B.1 of the applicable inspection ASB,''
for this AD, those instructions are for reference only and are not
required for the actions in paragraph (2) of EASA AD 2017-0125. The
inspections (checks) required by paragraph (2) of EASA AD 2017-0125
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.
(6) Where paragraph (5) of EASA AD 2017-0125 specifies to
``accomplish the applicable corrective action(s) in accordance with
the instructions of Paragraph 3.B.1 of the applicable inspection
ASB,'' for this AD, a qualified mechanic must add oil to the TGB to
the ``max'' level if the oil level is not at maximum. The
instructions are for reference only and are not required for the
actions in paragraph (5) of EASA AD 2017-0125.
(7) Where EASA AD 2017-0125 refers to flight hours (FH), this AD
requires using hours time-in-service.
(8) Where EASA AD 2017-0125 requires action after the last
flight of the day or ``ALF,'' this AD requires those actions before
the first flight of the day.
(9) Where the service information referred to in EASA AD 2017-
0125 specifies to perform a metallurgical analysis and contact the
manufacturer if collected particles are not clearly characterized,
this AD does not require contacting the manufacturer to determine
the characterization of the particles collected.
(10) Although service information referenced in EASA AD 2017-
0125 specifies to scrap parts, this AD does not include that
requirement.
(11) Although service information referenced in EASA AD 2017-
0125 specifies reporting information to Airbus Helicopters and
filling in a ``particle detection'' follow-up sheet, this AD does
not include those requirements.
(12) Although service information referenced in EASA AD 2017-
0125 specifies returning certain parts to an approved workshop, this
AD does not include that requirement.
(13) Where paragraph (6) of EASA AD 2017-0125 refers to ``any
discrepancy,'' for this AD, discrepancies include the presence of
particles and other conditions such as abrasions, scales, flakes,
and splinters.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Strategic Policy Rotorcraft Section, 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 Strategic Policy Rotorcraft Section,
send it to: Manager, Strategic Policy Rotorcraft Section, FAA, 10101
Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110.
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 Kathleen Arrigotti,
Aviation Safety Engineer, Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax 206-231-3218; 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 Aviation Safety Agency (EASA) AD 2017-0125, dated
July 21, 2017.
(ii) [Reserved].
(3) For EASA AD 2017-0125, 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-
2020-1123.
(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.
[[Page 13975]]
Issued on February 17, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-05142 Filed 3-11-21; 8:45 am]
BILLING CODE 4910-13-P
