[Federal Register Volume 85, Number 236 (Tuesday, December 8, 2020)]
[Rules and Regulations]
[Pages 78954-78957]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-26867]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0570; Product Identifier 2019-SW-121-AD; Amendment
39-21337; AD 2020-24-07]
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) 2018-26-02
for Airbus Helicopters (previously Eurocopter France) Model AS350B3,
EC130B4, and EC130T2 helicopters. AD 2018-26-02 required inspecting the
pilot's and co-pilot's throttle twist for proper operation. This new AD
retains the requirements of AD 2018-26-02 and adds calendar time
compliance times for the required actions. This AD was prompted by a
public comment that prompted additional review. The actions of this AD
are intended to address an unsafe condition on these products.
DATES: This AD is effective January 12, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 2,
2017 (81 FR 95854, December 29, 2016), and January 30, 2019 (83 FR
66093, December 26, 2018).
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 the view this 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-2020-0570.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov in Docket No. FAA-2020-0570; 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 Aviation
Safety Agency (now 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: George Schwab, Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
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 to remove AD 2018-26-02, Amendment 39-19532 (83 FR 66093,
December 26, 2018) (AD 2018-26-02), and add a new AD. AD 2018-26-02
applied to Airbus Helicopters Model AS350B3 and EC130B4 helicopters
with an ARRIEL 2B1 engine with the two-channel Full Authority Digital
Engine Control (FADEC) and with new twist grip modification (MOD)
073254 (for Model AS350B3 helicopters) or MOD
[[Page 78955]]
073773 (for Model EC130B4 helicopters) installed, and Model AS350B3 and
EC130T2 helicopters with an ARRIEL 2D engine installed. The NPRM
published in the Federal Register on June 11, 2020 (85 FR 35604). The
NPRM proposed to retain the inspection requirements of AD 2018-26-02
and include inspecting the wiring, performing an insulation test,
inspecting the pilot and copilot throttle twist grip controls, and
testing the pilot and copilot throttle twist grip controls for proper
functioning. The NPRM also proposed to include calendar compliance
times for the repetitive inspections at intervals depending on
operating conditions.
AD 2018-26-02 was prompted by EASA AD No. 2017-0059, dated April 6,
2017, issued by EASA, which is the Technical Agent for the Member
States of the European Union. EASA advised that the switches in the
engine ``IDLE'' or ``FLIGHT'' control system could be affected by the
corrosive effects of a salt-laden atmosphere, which could lead to
engine power loss. EASA advised that this condition, if not detected
and corrected, could, in case of failure of the other switch, prevent
the pilot from switching from ``IDLE'' to ``FLIGHT'' mode during
training of autorotation landing, making aborting the autorotation
impossible, resulting in unintended touchdown.
Actions Since AD 2018-26-02 Was Issued
After AD 2018-26-02 was issued, the FAA received comments from one
commenter requesting the FAA clarify why the compliance time for the
repetitive inspections required in AD 2018-26-02 was given in terms of
hours time-in-service (TIS) without also requiring calendar compliance
times. The commenter stated that a lot of operators do not operate
their aircraft 660 hours TIS in a year and asked whether the FAA is
concerned with calendar time. The FAA agreed; since the unsafe
condition involves corrosion, which has a direct relationship between
calendar time and airworthiness, it is necessary to add calendar time
compliance times for all required actions including the repetitive
inspections.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule, but the FAA did not receive any comments on
the NPRM or on the determination of the cost to the public.
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 of the information provided by EASA and determining the
unsafe condition exists and is likely to exist or develop on other
helicopters of the same type designs and that air safety and the public
interest require adopting the AD requirements as proposed.
Interim Action
The FAA considers this AD to be an interim action. If final action
is later identified, the FAA might consider further rulemaking then.
Differences Between This AD and the EASA AD
The EASA AD requires the initial inspections within 10 flight hours
or 7 days; this AD requires compliance before the next autorotation
training flight, 100 hours TIS, or 6 months, whichever occurs earlier,
as the unsafe condition only occurs when transitioning the throttle in-
flight from flight to idle and back to flight, such as during a
practice autorotation.
Additionally, the EASA AD requires installing Airbus Helicopters
MOD 074263; this AD does not as it does not correct the unsafe
condition.
Related Service Information Under 1 CFR Part 51
The FAA reviewed one document that co-publishes three Airbus
Helicopters Emergency Alert Service Bulletin (EASB) identification
numbers: No. 05.00.61, Revision 3, dated June 15, 2015, for Model
AS350B3 helicopters; No. 05.00.41, Revision 2, dated June 15, 2015, for
the non-FAA type certificated Model AS550C3 helicopter; and No. 05A009,
Revision 3, dated June 15, 2015, for Model EC130B4 helicopters. EASB
Nos. 05.00.61 and 05A009 are incorporated by reference in AD 2018-26-02
and are retained for the requirements of this AD. EASB No. 05.00.41 is
not incorporated by reference in AD 2018-26-02 and is not incorporated
by reference in this AD. This service information applies to
helicopters with an ARRIEL 2B1 engine installed and describes
procedures for a functional check and installation of protection for
micro-contacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT mode).
The FAA also reviewed one document that co-publishes three Airbus
Helicopters EASB identification numbers: No. 05.00.77, Revision 1,
dated June 15, 2015, for Model AS350B3 helicopters; No. 05.00.52,
Revision 1, dated June 15, 2015, for the non-FAA type certificated
Model AS550C3 helicopter; and No. 05A014, Revision 1, dated June 15,
2015, for Model EC130T2 helicopters. EASB Nos. 05.00.77 and 05A014 are
incorporated by reference in AD 2018-26-02 and are retained for the
requirements of this AD. EASB No. 05.00.52 is not incorporated by
reference in AD 2018-26-02 and is not incorporated by reference in this
AD. This service information applies to helicopters with an ARRIEL 2D
engine installed and describes procedures for a check of the protection
for micro-contacts (microswitches) 53Ka, 53Kb, and 65K (IDLE/FLIGHT
mode).
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.
Costs of Compliance
The FAA estimates that this AD affects 617 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.
Inspecting the wiring, performing an insulation test, inspecting
the pilot and copilot throttle twist grip controls, and testing the
pilot and copilot throttle twist grip controls takes about 4 work-
hours, for an estimated cost of $340 per helicopter and $209,780 for
the U.S. fleet per inspection cycle.
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.
[[Page 78956]]
Regulatory Findings
The FAA has determined that 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) 2018-26-02, Amendment 39-19532
(83 FR 66093, December 26, 2018); and
0
b. Adding the following new AD:
2020-24-07 Airbus Helicopters: Amendment 39-21337; Docket No. FAA-
2020-0570; Product Identifier 2019-SW-121-AD.
(a) Applicability
This airworthiness directive (AD) applies to the following
Airbus Helicopters, certificated in any category:
(1) Model AS350B3 helicopters with an ARRIEL 2B1 engine with the
two-channel Full Authority Digital Engine Control (FADEC) and with
new twist grip modification (MOD) 073254 or with an ARRIEL 2D engine
installed;
(2) Model EC130B4 helicopters with an ARRIEL 2B1 engine with the
two-channel FADEC and with new twist grip MOD 073773 installed; and
(3) Model EC130T2 helicopters with an ARRIEL 2D engine
installed.
(b) Unsafe Condition
This AD defines the unsafe condition as failure of one of the
two contactors, 53Ka or 53Kb, which can prevent switching from
``IDLE'' mode to ``FLIGHT'' mode during autorotation training making
it impossible to recover from a practice autorotation and compelling
the pilot to continue the autorotation to the ground. This condition
could result in unintended touchdown to the ground at a flight-idle
power setting during a practice autorotation, damage to the
helicopter, and injury to occupants.
(c) Affected ADs
This AD replaces AD 2018-26-02, Amendment 39-19532 (83 FR 66093,
December 26, 2018).
(d) Effective Date
This AD becomes effective January 12, 2021.
(e) 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.
(f) Required Actions
(1) Before the next practice autorotation, within 100 hours
time-in-service (TIS), or 6 months, whichever occurs first, inspect
the wiring, perform an insulation test, inspect the pilot and
copilot throttle twist grip controls, and test the pilot and copilot
throttle twist grip controls for proper functioning by following the
Accomplishment Instructions, paragraph 3.B.1 through 3.B.6, of
Airbus Helicopters Emergency Alert Service Bulletin (EASB) No.
05.00.61, Revision 3, dated June 15, 2015, for Model AS350B3
helicopters with an ARRIEL 2B1 engine; EASB No. 05.00.77, Revision
1, dated June 15, 2015, for Model AS350B3 helicopters with an ARRIEL
2D engine; EASB No. 05A009, Revision 3, dated June 15, 2015, for
Model EC130B4 helicopters; or EASB No. 05A014, Revision 1, dated
June 15, 2015, for Model EC130T2 helicopters, as appropriate for
your model helicopter.
(2) Repeat the inspections in paragraph (f)(1) of this AD at
intervals not to exceed the following compliance times. For purposes
of this AD, salt laden conditions exist when a helicopter performs a
flight from a takeoff and landing area, heliport, or airport less
than 0.5 statute mile from salt water or performs a flight within
0.5 statute mile from salt water below an altitude of 1,000 ft.
above ground or sea level.
(i) For helicopters that have operated in salt laden conditions
since the previous inspection required by this AD, at intervals not
to exceed 330 hours TIS or 6 months, whichever occurs first.
(ii) For helicopters that have not operated in salt laden
conditions since the previous inspection required by this AD, at
intervals not to exceed 660 hours TIS or 12 months, whichever occurs
first.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Rotorcraft Standards Branch, FAA, may approve
AMOCs for this AD. Send your proposal to: George Schwab, Aviation
Safety Engineer, Safety Management Section, Rotorcraft Standards
Branch, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 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.
(h) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (now European Union Aviation Safety Agency) AD No. 2017-0059,
dated April 6, 2017. You may view the EASA AD on the internet at
https://www.regulations.gov in Docket No. FAA-2020-0570.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 7697, Engine
Control System Wiring.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
February 2, 2017 (81 FR 95854, December 29, 2016).
(i) Airbus Helicopters Emergency Alert Service Bulletin (EASB)
No. 05.00.61, Revision 3, dated June 15, 2015.
(ii) Airbus Helicopters EASB No. 05A009, Revision 3, dated June
15, 2015.
Note 1 to paragraph (j)(3): Airbus Helicopters EASB Nos.
05.00.61 and 05A009, both Revision 3 and dated June 15, 2015, are
co-published as one document along with Airbus Helicopters EASB No.
05.00.41, Revision 2, dated June 15, 2015, which is not incorporated
by reference in this AD.
(4) The following service information was approved for IBR on
January 30, 2019 (83 FR 66093, December 26, 2018).
(i) Airbus Helicopters EASB No. 05.00.77, Revision 1, dated June
15, 2015.
(ii) Airbus Helicopters EASB No. 05A014, Revision 1, dated June
15, 2015.
Note 2 to paragraph (j)(4): Airbus Helicopters EASB Nos.
05.00.77 and 05A014, both Revision 1 and dated June 15, 2015, are
co-published as one document along with Airbus Helicopters EASB No.
05.00.52, Revision 1, dated June 15, 2015, which is not incorporated
by reference in this AD.
(5) 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.
(6) 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.
[[Page 78957]]
(7) 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 [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on November 17, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-26867 Filed 12-7-20; 8:45 am]
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