[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]
BILLING CODE 4910-13-P