Airworthiness Directives; Airbus Helicopters, 63440-63443 [2020-22241]
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Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations
(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 adding
the following new airworthiness
directive (AD):
■
2020–20–15 Airbus SAS: Amendment 39–
21271; Docket No. FAA–2020–0348;
Product Identifier 2020–NM–054–AD.
(a) Effective Date
This AD is effective November 12, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus SAS
airplanes specified in paragraphs (c)(1)
through (7) of this AD, certificated in any
category, as identified in European Union
Aviation Safety Agency (EASA) AD 2020–
0083, dated April 3, 2020 (‘‘EASA AD 2020–
0083’’).
(1) Model A330–202, –203, –223, and –243
airplanes.
(2) Model A330–223F and –243F airplanes.
(3) Model A330–302, –303, –323, and –343
airplanes.
(4) Model A330–941 airplanes.
(5) Model A340–313 airplanes.
(6) Model A340–541 airplanes.
(7) Model A340–642 airplanes.
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(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishings.
(e) Reason
This AD was prompted by the results of
laboratory tests on non-rechargeable lithium
batteries installed in emergency locator
transmitters (ELTs), which highlighted a lack
of protection against currents of 28 volts DC
or 115 volts AC that could lead to thermal
runaway and a battery fire. The FAA is
issuing this AD to address local (temporary)
fires in non-rechargeable lithium batteries
installed in ELTs, which could result in
damage to the airplane and injury to
occupants.
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16:24 Oct 07, 2020
Jkt 253001
(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 2020–0083.
(h) Exceptions to EASA AD 2020–0083
(1) Where EASA AD 2020–0083 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2020–0083 does not apply to this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, 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 Large Aircraft
Section, 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-AIR730-AMOC@faa.gov. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Airbus SAS’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2020–0083 that contains RC procedures and
tests: Except as required by paragraph (i)(2)
of this AD, RC procedures and tests must be
done to comply with this AD; any procedures
or tests that are not identified as RC are
recommended. Those procedures and tests
that are not identified as RC may be deviated
from using accepted methods in accordance
with the operator’s maintenance or
inspection program without obtaining
approval of an AMOC, provided the
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(j) Related Information
For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, Large Aircraft Section,
International Validation Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
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telephone and fax 206–231–3229; email
vladimir.ulyanov@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 2020–0083, dated April 3, 2020.
(ii) [Reserved]
(3) For information about EASA AD 2020–
0083, contact the EASA, Konrad-AdenauerUfer 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 material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. 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–2020–0348.
(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 September 24, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–22235 Filed 10–7–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0410; Product
Identifier 2019–SW–030–AD; Amendment
39–21274; AD 2020–21–01]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Helicopters Model AS–365N2,
AS 365N3, EC 155B, EC155B1, and SA–
365N1 helicopters. This AD requires
modifying the main gearbox (MGB) tail
rotor (T/R) drive flange installation.
SUMMARY:
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Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations
This AD was prompted by several
reported occurrences of loss of
tightening torque of the Shur-Lok nut,
which serves as a retainer of the T/R
drive flange. The actions of this AD are
intended to address an unsafe condition
on these products.
DATES: This AD is effective November
12, 2020.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of November 12, 2020.
ADDRESSES: For 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
the referenced service information at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX
76177. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0410.
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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–2020–
0410; 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, the
European Union Aviation Safety Agency
(EASA) AD, any service information
that is incorporated by reference, 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: Matt
Fuller, AD Program Manager,
Airworthiness Products Section,
General Aviation and Rotorcraft Unit,
10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110; email
Matthew.Fuller@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Airbus Helicopters Model AS–
365N2, AS 365N3, EC 155B, EC155B1,
and SA–365N1 helicopters with
modification 0763B64 installed, except
those with modification 0763C81. The
NPRM published in the Federal
VerDate Sep<11>2014
16:24 Oct 07, 2020
Jkt 253001
Register on April 23, 2020, (85 FR
22688). The NPRM proposed to require
within 600 hours time-in-service,
modifying the MGB T/R drive flange
installation by removing the sliding
flange from the flexible coupling and
installing the sliding flange with aft
output stop part number 365A32–7836–
20 added, as per helicopter model and
configuration. The NPRM also proposed
to require removing from service certain
washers, degreasing the bolt threads,
applying a sealant between the interlay
mating surfaces, and applying torque to
the nuts. The proposed requirements
were intended to prevent loosening and
disengagement of the Shur-Lok nut
threads, possibly resulting in reduction
of T/R drive control, rear transmission
vibrations, and subsequent loss of
control of the helicopter.
The NPRM was prompted by EASA
AD No. 2019–0046, dated March 11,
2019 (EASA AD 2019–0046), issued by
EASA, which is the Technical Agent for
the Member States of the European
Union, to correct an unsafe condition
for Airbus Helicopters (formerly
Eurocopter, Eurocopter France,
Aerospatiale) Model SA 365 N1, AS 365
N2, AS 365 N3, EC 155 B, and EC 155
B1 helicopters, all serial numbers, with
modification 0763B64 installed, except
those with 07 63C81 installed. EASA
advises of reported occurrences of loss
of tightening torque of the Shur-Lok nut,
which serves as a retainer of the T/R
drive flange of the MGB. EASA also
advises of subsequent investigation that
determined that these occurrences were
the result of failure of the Shur-Lok nut
locking function, which is normally
ensured by two anti-rotation tabs
engaged into two slots at the end of the
MGB output shaft pinion. EASA states
this condition could lead to the
loosening and disengagement of the
Shur-Lok nut threads, possibly resulting
in reduction of T/R drive control, rear
transmission vibrations, and subsequent
loss of control of the helicopter.
To address this unsafe condition,
EASA issued a series of ADs, initially
with EASA AD No. 2014–0165, dated
July 14, 2014 (EASA AD 2014–0165),
which required a one-time inspection of
the radial play inside the T/R drive
flange and the condition of the Shur-Lok
nut. Shortly after, EASA issued EASA
AD No. 2014–0179, dated July 25, 2014
(EASA AD 2014–0179) to supersede
EASA AD 2014–0165. EASA AD 2014–
0179 retained the requirements of EASA
AD 2014–0165 and expanded the
applicability of helicopters affected by
the unsafe condition. EASA later
revised EASA AD 2014–0179 to
Revision 1, dated July 29, 2014, to revise
the applicability and specify updated
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63441
related service information, and again to
Revision 2, dated April 11, 2016 (EASA
AD 2014–0179R2), to reduce the
applicability and specify additional
updated related service information.
Since EASA issued EASA AD 2014–
0179R2, another occurrence was
reported that involved an on-ground
loss of T/R synchronization, resulting
from disengagement of the Shur-Lok
nut. This additional occurrence
prompted EASA to issue EASA AD
2019–0046 to require installation of
modification 07 63C81, which consists
of installing a rear output stop with 5
spigots on the T/R shaft flexible
coupling. According to Airbus
Helicopters, the 5 spigots will come into
contact with the row of 5 bolt heads of
the front T/R shaft if the T/R drive
flange moves backwards. This contact
limits backward displacement of the T/
R drive flange and subsequently
prevents T/R drive flange
disengagement.
Comments
The FAA gave the public the
opportunity to participate in developing
this AD, but the FAA did not receive
any comments on the NPRM.
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 of the unsafe condition described
in its AD. The FAA is issuing this AD
after evaluating all information
provided by EASA and determining the
unsafe condition exists and is likely to
exist or develop on other products of the
same type designs and that air safety
and the public interest require adopting
the AD requirements as proposed.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Airbus Helicopters
Alert Service Bulletin (ASB) No.
AS365–63.00.19, for Model AS365N,
N1, N2, and N3 helicopters and non
FAA-type certificated military Model
AS365F, Fi, Fs, K, and K2 helicopters;
and Airbus Helicopters ASB No. EC155–
63A013 for Model EC155B and B1
helicopters, both Revision 1 and dated
January 31, 2019. This service
information specifies procedures for
modification 0763C81 to install a rear
(aft) output stop between the T/R drive
flange and T/R drive shaft.
This service information 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.
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Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations
Costs of Compliance
The FAA estimates that this AD
affects 46 helicopters of U.S. Registry.
The FAA estimates that operators may
incur the following costs in order to
comply with this AD. Labor costs are
estimated at $85 per work-hour.
Modifying the MGB T/R drive flange
installation takes about 14 work-hours
and parts cost about $2,704 for an
estimated cost of $3,894 per helicopter
and $179,124 for the U.S. fleet.
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 helicopters identified in this
rulemaking action.
Regulatory Findings
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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,
VerDate Sep<11>2014
16:24 Oct 07, 2020
Jkt 253001
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 (AD):
■
2020–21–01 Airbus Helicopters:
Amendment 39–21274; Docket No.
FAA–2020–0410; Product Identifier
2019–SW–030–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS–365N2, AS 365N3, EC 155B,
EC155B1, and SA–365N1 helicopters,
certificated in any category, with
modification 0763B64 installed, except those
with modification 0763C81.
(b) Unsafe Condition
This AD defines the unsafe condition as
loss of tightening torque of the Shur-Lok nut,
which serves as a retainer of the tail rotor (T/
R) drive flange of the main gearbox. This
condition could result in loss of the Shur-Lok
nut, possibly resulting in disengagement of
the T/R drive flange, reduction of T/R drive
control, rear transmission vibrations, and
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective November 12,
2020.
(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
Within 600 hours time-in-service:
(1) For Model AS–365N2, AS 365N3, and
SA–365N1 helicopters:
(i) Without removing the tail drive shaft
flange (a), remove the sliding flange (b) from
the flexible coupling (c) as shown in Detail
‘‘B’’ of Figure 1, PRE MOD, of Airbus
Helicopters Alert Service Bulletin (ASB) No.
AS365–63.00.19, Revision 1, dated January
31, 2019 (ASB AS365–63.00.19); replace the
3 bolts (d) and remove from service the 3
washers (e).
(ii) Install the sliding flange (b) with aft
output stop (1) part number (P/N) 365A32–
7836–20 as shown in Detail ‘‘B’’ of Figure 1,
POST MOD, of ASB AS365–63.00.19 and by
following the Accomplishment Instructions,
paragraph 3.B.2.b, of ASB AS365–63.00.19.
(2) For Model EC 155B and EC155B1
helicopters:
(i) Without removing the Shur-Lok nut (a),
remove the sliding flange (b) from the flexible
coupling (c) as shown in Detail ‘‘B’’ of Figure
1, PRE MOD, of Airbus Helicopters ASB No.
EC155–63A013, Revision 1, dated January 31,
2019 (ASB EC155–63A013); replace the 3
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bolts (d) and remove from service the 3
washers (e).
(ii) Install the sliding flange (b) with aft
output stop (1) P/N 365A32–7836–20 as
shown in Detail ‘‘B’’ of Figure 1, POST MOD,
of ASB EC155–63A013 and by following the
Accomplishment Instructions, paragraph
3.B.2.b, of ASB EC155–63A013.
Note 1 to paragraph (e)(2)(ii): ASB EC155–
63A013 refers to the ‘‘aft output stop’’ as
‘‘rear output stop.’’
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this
AD. Send your proposal to: Matt Fuller, AD
Program Manager, Airworthiness Products
Section, General Aviation and Rotorcraft
Unit, 10101 Hillwood Pkwy., Fort Worth, TX
76177; telephone 817–222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD No. 2019–0046, dated March 11,
2019. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA 2020–0410.
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6500, Tail Rotor Drive System.
(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) Airbus Helicopters Alert Service
Bulletin (ASB) No. AS365–63.00.19, Revision
1, dated January 31, 2019.
(ii) Airbus Helicopters ASB No. EC155–
63A013, Revision 1, dated January 31, 2019.
(3) For service information identified in
this AD, 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.
(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.
(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,
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Federal Register / Vol. 85, No. 196 / Thursday, October 8, 2020 / Rules and Regulations
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on September 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–22241 Filed 10–7–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0902; Project
Identifier AD–2020–01174–E; Amendment
39–21273; AD 2020–20–17]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
khammond on DSKJM1Z7X2PROD with RULES
Examining the AD Docket
The FAA is adopting a new
airworthiness directive (AD) for all
General Electric Company GE90–110B1
and GE90–115B model turbofan
engines. This AD was prompted by an
in-service occurrence of loss of engine
thrust control resulting in
uncommanded high thrust. This AD
prohibits dispatch of an airplane if
certain status messages are displayed on
the engine indicating and crew alerting
system (EICAS) and if certain conditions
are present per the manufacturer’s
service information. As a terminating
action, this AD requires revision of the
existing FAA-approved minimum
equipment list (MEL) by incorporating
into the MEL the dispatch restrictions
listed in this AD. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective October 23,
2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 23, 2020.
The FAA must receive comments on
this AD by November 23, 2020.
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–
SUMMARY:
VerDate Sep<11>2014
16:24 Oct 07, 2020
Jkt 253001
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this final rule, contact General Electric
Company, 1 Neumann Way, Cincinnati,
OH 45215; phone: 513–552–3272; email:
aviation.fleetsupport@ge.com; website:
www.ge.com. You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 1200 District Avenue,
Burlington, MA 01803. For information
on the availability of this material at the
FAA, call 781–238–7759. It is also
available on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0902.
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0902; 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 the
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Stephen Elwin, Aerospace Engineer,
ECO Branch, FAA, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7236; fax: 781–238–7199;
email: stephen.l.elwin@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA received a report from the
manufacturer of an in-service loss of
engine thrust control that occurred on
October 27, 2019, resulting in
uncommanded high thrust. Analysis by
the manufacturer found accumulated
thermal cycles of the MN4 integrated
circuit in the full authority digital
engine control (FADEC) through normal
operation causes the solder ball joints to
wear out and eventually fail over time.
The failure was preceded by an inbound
FADEC EICAS ‘‘ENG EEC C1’’ status
message one flight before the in-service
occurrence. This condition, if not
addressed, could result in loss of engine
thrust control and reduced control of
the airplane. The FAA is issuing this AD
to address the unsafe condition on these
products.
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Frm 00021
Fmt 4700
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63443
FAA’s Determination
The FAA is issuing this AD because
the agency evaluated all the relevant
information and determined the unsafe
condition described previously is likely
to exist or develop in other products of
the same type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed GE GE90–100
Service Bulletin (SB) 73–0117, R01,
dated August 5, 2020. The SB describes
procedures for checking for an inbound
FADEC EICAS ‘‘ENG EEC C1’’ status
message and corresponding conditions.
This service information 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.
AD Requirements
This AD prohibits dispatch of the
airplane if certain status messages are
displayed on the EICAS and if certain
conditions are present per the
manufacturer’s service information. As a
terminating action, this AD requires,
within 120 days of the effective date of
this AD, revision of the existing FAAapproved MEL by incorporating into the
MEL the dispatch restrictions listed in
paragraph (g) of this AD.
Interim Action
The FAA considers this AD interim
action. The manufacturer is still
reviewing the unsafe condition and the
FAA will consider further rulemaking.
Justification for Immediate Adoption
and Determination of the Effective Date
Section 553(b)(3)(B) of the
Administrative Procedure Act (APA) (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 issuance.
Further, Section 553(d) of the APA
authorizes agencies to make rules
effective in less than 30 days, upon a
finding of good cause.
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 foregoing notice
and comment prior to adoption of this
rule. On October 27, 2019, a Boeing
Company Model 777–300 airplane
powered by GE GE90–115B model
turbofan engines experienced an
E:\FR\FM\08OCR1.SGM
08OCR1
]]>Agencies
[Federal Register Volume 85, Number 196 (Thursday, October 8, 2020)]
[Rules and Regulations]
[Pages 63440-63443]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22241]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0410; Product Identifier 2019-SW-030-AD; Amendment
39-21274; AD 2020-21-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Helicopters Model AS-365N2, AS 365N3, EC 155B, EC155B1,
and SA-365N1 helicopters. This AD requires modifying the main gearbox
(MGB) tail rotor (T/R) drive flange installation.
[[Page 63441]]
This AD was prompted by several reported occurrences of loss of
tightening torque of the Shur-Lok nut, which serves as a retainer of
the T/R drive flange. The actions of this AD are intended to address an
unsafe condition on these products.
DATES: This AD is effective November 12, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of November 12,
2020.
ADDRESSES: For 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 the referenced service information at the FAA, Office of the
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321,
Fort Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0410.
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-
0410; 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, the European Union Aviation Safety Agency (EASA) AD, any
service information that is incorporated by reference, 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: Matt Fuller, AD Program Manager,
Airworthiness Products Section, General Aviation and Rotorcraft Unit,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to Airbus Helicopters
Model AS-365N2, AS 365N3, EC 155B, EC155B1, and SA-365N1 helicopters
with modification 0763B64 installed, except those with modification
0763C81. The NPRM published in the Federal Register on April 23, 2020,
(85 FR 22688). The NPRM proposed to require within 600 hours time-in-
service, modifying the MGB T/R drive flange installation by removing
the sliding flange from the flexible coupling and installing the
sliding flange with aft output stop part number 365A32-7836-20 added,
as per helicopter model and configuration. The NPRM also proposed to
require removing from service certain washers, degreasing the bolt
threads, applying a sealant between the interlay mating surfaces, and
applying torque to the nuts. The proposed requirements were intended to
prevent loosening and disengagement of the Shur-Lok nut threads,
possibly resulting in reduction of T/R drive control, rear transmission
vibrations, and subsequent loss of control of the helicopter.
The NPRM was prompted by EASA AD No. 2019-0046, dated March 11,
2019 (EASA AD 2019-0046), issued by EASA, which is the Technical Agent
for the Member States of the European Union, to correct an unsafe
condition for Airbus Helicopters (formerly Eurocopter, Eurocopter
France, Aerospatiale) Model SA 365 N1, AS 365 N2, AS 365 N3, EC 155 B,
and EC 155 B1 helicopters, all serial numbers, with modification
0763B64 installed, except those with 07 63C81 installed. EASA advises
of reported occurrences of loss of tightening torque of the Shur-Lok
nut, which serves as a retainer of the T/R drive flange of the MGB.
EASA also advises of subsequent investigation that determined that
these occurrences were the result of failure of the Shur-Lok nut
locking function, which is normally ensured by two anti-rotation tabs
engaged into two slots at the end of the MGB output shaft pinion. EASA
states this condition could lead to the loosening and disengagement of
the Shur-Lok nut threads, possibly resulting in reduction of T/R drive
control, rear transmission vibrations, and subsequent loss of control
of the helicopter.
To address this unsafe condition, EASA issued a series of ADs,
initially with EASA AD No. 2014-0165, dated July 14, 2014 (EASA AD
2014-0165), which required a one-time inspection of the radial play
inside the T/R drive flange and the condition of the Shur-Lok nut.
Shortly after, EASA issued EASA AD No. 2014-0179, dated July 25, 2014
(EASA AD 2014-0179) to supersede EASA AD 2014-0165. EASA AD 2014-0179
retained the requirements of EASA AD 2014-0165 and expanded the
applicability of helicopters affected by the unsafe condition. EASA
later revised EASA AD 2014-0179 to Revision 1, dated July 29, 2014, to
revise the applicability and specify updated related service
information, and again to Revision 2, dated April 11, 2016 (EASA AD
2014-0179R2), to reduce the applicability and specify additional
updated related service information. Since EASA issued EASA AD 2014-
0179R2, another occurrence was reported that involved an on-ground loss
of T/R synchronization, resulting from disengagement of the Shur-Lok
nut. This additional occurrence prompted EASA to issue EASA AD 2019-
0046 to require installation of modification 07 63C81, which consists
of installing a rear output stop with 5 spigots on the T/R shaft
flexible coupling. According to Airbus Helicopters, the 5 spigots will
come into contact with the row of 5 bolt heads of the front T/R shaft
if the T/R drive flange moves backwards. This contact limits backward
displacement of the T/R drive flange and subsequently prevents T/R
drive flange disengagement.
Comments
The FAA gave the public the opportunity to participate in
developing this AD, but the FAA did not receive any comments on the
NPRM.
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 of the
unsafe condition described in its AD. The FAA is issuing this AD after
evaluating all information provided by EASA and determining the unsafe
condition exists and is likely to exist or develop on other products of
the same type designs and that air safety and the public interest
require adopting the AD requirements as proposed.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB)
No. AS365-63.00.19, for Model AS365N, N1, N2, and N3 helicopters and
non FAA-type certificated military Model AS365F, Fi, Fs, K, and K2
helicopters; and Airbus Helicopters ASB No. EC155-63A013 for Model
EC155B and B1 helicopters, both Revision 1 and dated January 31, 2019.
This service information specifies procedures for modification 0763C81
to install a rear (aft) output stop between the T/R drive flange and T/
R drive shaft.
This service information 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.
[[Page 63442]]
Costs of Compliance
The FAA estimates that this AD affects 46 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour. Modifying the MGB T/R drive flange installation takes
about 14 work-hours and parts cost about $2,704 for an estimated cost
of $3,894 per helicopter and $179,124 for the U.S. fleet.
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 helicopters 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 adding the following new airworthiness
directive (AD):
2020-21-01 Airbus Helicopters: Amendment 39-21274; Docket No. FAA-
2020-0410; Product Identifier 2019-SW-030-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS-365N2, AS 365N3,
EC 155B, EC155B1, and SA-365N1 helicopters, certificated in any
category, with modification 0763B64 installed, except those with
modification 0763C81.
(b) Unsafe Condition
This AD defines the unsafe condition as loss of tightening
torque of the Shur-Lok nut, which serves as a retainer of the tail
rotor (T/R) drive flange of the main gearbox. This condition could
result in loss of the Shur-Lok nut, possibly resulting in
disengagement of the T/R drive flange, reduction of T/R drive
control, rear transmission vibrations, and subsequent loss of
control of the helicopter.
(c) Effective Date
This AD becomes effective November 12, 2020.
(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
Within 600 hours time-in-service:
(1) For Model AS-365N2, AS 365N3, and SA-365N1 helicopters:
(i) Without removing the tail drive shaft flange (a), remove the
sliding flange (b) from the flexible coupling (c) as shown in Detail
``B'' of Figure 1, PRE MOD, of Airbus Helicopters Alert Service
Bulletin (ASB) No. AS365-63.00.19, Revision 1, dated January 31,
2019 (ASB AS365-63.00.19); replace the 3 bolts (d) and remove from
service the 3 washers (e).
(ii) Install the sliding flange (b) with aft output stop (1)
part number (P/N) 365A32-7836-20 as shown in Detail ``B'' of Figure
1, POST MOD, of ASB AS365-63.00.19 and by following the
Accomplishment Instructions, paragraph 3.B.2.b, of ASB AS365-
63.00.19.
(2) For Model EC 155B and EC155B1 helicopters:
(i) Without removing the Shur-Lok nut (a), remove the sliding
flange (b) from the flexible coupling (c) as shown in Detail ``B''
of Figure 1, PRE MOD, of Airbus Helicopters ASB No. EC155-63A013,
Revision 1, dated January 31, 2019 (ASB EC155-63A013); replace the 3
bolts (d) and remove from service the 3 washers (e).
(ii) Install the sliding flange (b) with aft output stop (1) P/N
365A32-7836-20 as shown in Detail ``B'' of Figure 1, POST MOD, of
ASB EC155-63A013 and by following the Accomplishment Instructions,
paragraph 3.B.2.b, of ASB EC155-63A013.
Note 1 to paragraph (e)(2)(ii): ASB EC155-63A013 refers to the
``aft output stop'' as ``rear output stop.''
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Standards Branch, FAA, may approve
AMOCs for this AD. Send your proposal to: Matt Fuller, AD Program
Manager, Airworthiness Products Section, General Aviation and
Rotorcraft Unit, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
telephone 817-222-5110; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or certificate holding district office, before operating any
aircraft complying with this AD through an AMOC.
(g) Additional Information
The subject of this AD is addressed in European Union Aviation
Safety Agency (EASA) AD No. 2019-0046, dated March 11, 2019. You may
view the EASA AD on the internet at https://www.regulations.gov in
Docket No. FAA 2020-0410.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6500, Tail Rotor
Drive System.
(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) Airbus Helicopters Alert Service Bulletin (ASB) No. AS365-
63.00.19, Revision 1, dated January 31, 2019.
(ii) Airbus Helicopters ASB No. EC155-63A013, Revision 1, dated
January 31, 2019.
(3) For service information identified in this AD, 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.
(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.
(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,
[[Page 63443]]
email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on September 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-22241 Filed 10-7-20; 8:45 am]
BILLING CODE 4910-13-P
