[Federal Register Volume 83, Number 139 (Thursday, July 19, 2018)]
[Rules and Regulations]
[Pages 34029-34031]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-15303]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0091; Product Identifier 2017-SW-054-AD; Amendment 
39-19334; AD 2018-15-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for Airbus 
Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS355E, 
AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD 
requires inspecting the tail rotor (TR) pitch rod. This AD is prompted 
by a report of several cases of damaged TR pitch rod ball joints. The 
actions of this AD are intended to correct an unsafe condition on these 
helicopters.

DATES: This AD becomes effective August 3, 2018.
    We must receive comments on this AD by September 17, 2018.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0091; 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 (EASA) AD, the economic 
evaluation, any comments received, and other information. The street 
address for Docket Operations (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.
    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 
http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You may review the referenced service information at 
the FAA, Office of the Regional Counsel, Southwest Region, 10101 
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: David Hatfield, 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:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments prior to it becoming effective. However, we 
invite you to participate in this rulemaking by submitting written 
comments, data, or views. We also invite comments relating to the 
economic, environmental, energy, or federalism impacts that resulted 
from adopting this AD. The most helpful comments reference a specific 
portion of the AD, explain the reason for any recommended change, and 
include supporting data. To ensure the docket does not contain 
duplicate comments, commenters should send only one copy of written 
comments, or if comments are filed electronically, commenters should 
submit them only one time. We will file in the docket all comments that 
we receive, as well as a report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking during the 
comment period. We will consider all the comments we receive and may 
conduct additional rulemaking based on those comments.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued Emergency AD No. 2017-0020-E, dated February 
7, 2017, to correct an unsafe condition for Airbus Helicopters Model AS 
350 B, AS 350 BA, AS 350 BB, AS 350 B1, AS 350 B2, AS 350 B3, AS 355 E, 
AS 355 F, AS 355 F1, AS 355 F2, AS 355 N and AS 355 NP helicopters with 
modification (MOD) 075601 or MOD 076602 installed. EASA advises of 
several reports of damaged horn-side TR pitch rod elastomeric ball 
joints, and of an on-going investigation to determine the cause of the 
damage. EASA states that this condition could result in loss of control 
of the helicopter. To address this unsafe condition, the EASA AD 
requires repetitive inspections of the TR pitch rod. While the 
inspections are contained in the Airworthiness Limitations Section of 
the helicopter maintenance manual, the EASA AD reduces the interval 
from 50 flight hours to 10 flight hours.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
France and are approved for operation in the United States. Pursuant to 
our bilateral agreement with France, EASA, its technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other helicopters of these same 
type designs.

Related Service Information

    We reviewed Airbus Helicopters Emergency Alert Service Bulletin 
(EASB) No. 05.00.86 for Model AS350-series helicopters and EASB No. 
05.00.75 for Model AS355-series helicopters, both Revision 1 and both 
dated February 6, 2017. This service information contains procedures 
for inspecting the TR pitch change rod elastomeric ball joint for 
damage.

AD Requirements

    This AD requires, for helicopters with a TR pitch change rod 
elastomeric ball joint installed, within 10 hours time-in-service (TIS) 
and thereafter at intervals not exceeding 10 hours TIS, inspecting each 
face of the TR pitch rod blade side ball joint for debonding, 
extrusion, and a crack. If there is debonding, extrusion, or a crack 
with a circumference of 90 degrees or more, this AD requires replacing 
the TR pitch rod before further flight. Airbus Helicopters identifies 
the installation of a TR pitch change rod elastomeric ball joint as MOD 
075601 or MOD 076602.

Differences Between This AD and the EASA AD

    The EASA AD applies to Airbus Helicopters Model AS 350 BB 
helicopters. This AD does not as that model is not type-certificated in 
the U.S.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified,

[[Page 34030]]

we might consider further rulemaking then.

Costs of Compliance

    We estimate that this AD affects 896 helicopters of U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD. At an average labor rate of $85 per hour, 
inspecting the TR pitch rod ball joint requires 0.5 hour, for a cost of 
$43 per helicopter and $38,528 for the U.S. fleet, per inspection 
cycle.
    If required, replacing a TR pitch rod requires one work-hour and 
required parts cost $3,174, for a cost per helicopter of $3,259.

FAA's Justification and Determination of the Effective Date

    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 waiving notice and comment prior to adoption of this rule 
because the inspections required by this AD must be accomplished within 
10 hours TIS and thereafter every 10 hours TIS. Therefore, we find good 
cause that notice and opportunity for prior public comment are 
impracticable. In addition, for the reason stated above, we find that 
good cause exists for making this amendment effective in less than 30 
days.

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.
    We are 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

    We 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, I certify that this AD:

    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska to the extent that 
it justifies making a regulatory distinction; and
    4. 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD and placed it in the AD docket.

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):

2018-15-02 Airbus Helicopters: Amendment 39-19334; Docket No. FAA-
2018-0091; Product Identifier 2017-SW-054-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS350B, AS350B1, 
AS350B2, AS350B3, AS350BA, AS355E, AS355F, AS355F1, AS355F2, AS355N, 
and AS355NP helicopters, certificated in any category, with a tail 
rotor (TR) pitch change rod elastomeric ball joint installed.
    Note 1 to paragraph (a): Airbus Helicopters modification (MOD) 
075601 and MOD 076602 consist of replacing the TR pitch change rod 
with an elastomeric ball joint rod.

(b) Unsafe Condition

    This AD defines the unsafe condition as a damaged elastomeric 
ball joint on the TR pitch change rod. This condition could result 
in failure of the TR pitch change rod and subsequent loss of control 
of the helicopter.

(c) Effective Date

    This AD becomes effective August 3, 2018.

(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 10 hours time-in-service (TIS) and thereafter at 
intervals not exceeding 10 hours TIS:
    (1) Manually induce a flapping movement in the TR blade until 
the pitch change rod rotates a minimum of 10 degrees.
    (2) Inspect both faces of the blade side of the ball joint 
elastomer for debonding, extrusion, and cracks. If there is a crack 
or any debonding or extrusion with a circumference of 90 or more 
degrees, before further flight, replace the pitch change rod.

(f) Special Flight Permits

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
David Hatfield, Aviation Safety Engineer, Safety Management Section, 
Rotorcraft Standards Branch, FAA, 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, we suggest 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

    (1) Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. 05.00.86 and EASB No. 05.00.75, both Revision 1 and both dated 
February 6, 2017, which are not incorporated by reference, contain 
additional information about the subject of this AD. 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 http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. 
You may review a copy of the service information at the FAA, Office 
of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 
6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) Emergency AD No. 2017-0020-E, dated February 7, 
2017. You may view the EASA Emergency AD on the internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2018-0091.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6720 Tail Rotor 
Control System.


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    Issued in Fort Worth, Texas, on July 6, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2018-15303 Filed 7-18-18; 8:45 am]
 BILLING CODE 4910-13-P