[Federal Register Volume 83, Number 166 (Monday, August 27, 2018)]
[Proposed Rules]
[Pages 43561-43563]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-18472]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0737; Product Identifier 2017-SW-096-AD]
RIN 2120-AA64


Airworthiness Directives; Leonardo S.p.A. Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Leonardo S.p.A. (Type Certificate Previously Held by Finmeccanica 
S.p.A., AgustaWestland S.p.A.) Model AW139 helicopters. This proposed 
AD would require inspecting and altering the number 1 driveshaft 
(driveshaft). This proposed AD is prompted by reports of scratches that 
were found on the driveshaft. The actions of this proposed AD are 
intended to prevent an unsafe condition on these products.

DATES: We must receive comments on this proposed AD by October 26, 
2018.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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-
0737; 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 proposed 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 proposed rule, contact 
Leonardo S.p.A. Helicopters, Matteo Ragazzi, Head of Airworthiness, 
Viale G. Agusta 520, 21017 C. Costa di Samarate (Va) Italy; telephone 
+39-0331-711756; fax +39-0331-229046; or at http://www.leonardocompany.com/-/bulletins. 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 <a href="/cdn-cgi/l/email-protection#086c697e616c2660697c6e616d646c486e6969266f677e"><span class="__cf_email__" data-cfemail="e48085928d80ca8c8590828d818880a4828585ca838b92">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    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 might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2017-0011, dated January 25, 
2017, to correct an unsafe condition for certain serial-numbered 
Leonardo S.p.A. (formerly Finmeccanica S.p.A, AgustaWestland S.p.A.) 
Model AW139 helicopters. EASA advises of several helicopters found with 
scratches on the driveshaft part-number (P/N) 3G6510A01132 and that an 
investigation determined only helicopters equipped with rear exhaust 
module assembly P/N 3G7810A00431 and tunnel assembly P/N 3G7130A13431 
are affected. According to EASA, the scratches resulted from 
insufficient clearance between the driveshaft and the rear exhaust 
module and tunnel assemblies. EASA further advises that if not 
corrected, these scratches could lead to a crack in the driveshaft, 
failure of the tail rotor drive system, and subsequent reduced control 
of the helicopter. To prevent this potential unsafe condition, the EASA 
AD requires repetitive inspections of the driveshaft for a crack until 
the exhaust module and tunnel assembly are modified to increase the 
clearance.

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Italy and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Italy, EASA, its technical representative, 
has notified us of the unsafe condition described in its AD. We are 
proposing this AD because we evaluated all known relevant information 
and determined that an unsafe condition is likely to exist or develop 
on other products of the same type design.

Related Service Information Under 1 CFR Part 51

    We reviewed Leonardo Helicopters Bollettino Tecnico No. 139-465, 
Revision A, dated January 25, 2017, which contains procedures for 
visual and eddy-current inspections of the driveshaft. This service 
information also contains procedures for modifying the exhaust module 
and tunnel assemblies.
    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.

Proposed AD Requirements

    This proposed AD would require, within 30 hours time-in-service 
(TIS) and thereafter at intervals not exceeding 100 hours TIS, 
inspecting the driveshaft tube P/N 3G6510A00832 for a scratch and 
indentation. If there is a scratch or indentation, the proposed AD 
would require, before further flight, repairing the driveshaft tube and 
performing a depth check of the repaired area. If the repaired area 
depth is more than 0.2 mm, the proposed AD would require replacing the 
driveshaft tube and altering the rear exhaust module and tunnel 
assembly before further flight. If the depth of the repaired area of 
the tube is 0.2 mm or less, the proposed AD would require, before 
further flight, performing an eddy current inspection of the tube for a 
crack. If there is a crack,

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the proposed AD would require replacing the driveshaft tube and 
altering the rear exhaust module and tunnel assembly before further 
flight.
    This proposed AD would also require, within 300 hours TIS, altering 
the rear exhaust module and tunnel assembly, if not previously done as 
a result of the inspections. Because this proposed AD would also 
require re-identifying the tunnel assembly part number after it is 
altered, this would be terminating action for the repetitive 
inspections.

Costs of Compliance

    We estimate that this proposed AD would affect 55 helicopters of 
U.S. Registry.
    We estimate that operators may incur the following costs in order 
to comply with this AD, based on an average labor rate of $85 per work-
hour. Inspecting, repairing, and eddy-current inspecting the driveshaft 
tube would require about 6 work-hours, and required parts cost would be 
minimal, for a cost of $510 per helicopter and $28,050 for the U.S. 
fleet per inspection cycle. Altering the rear exhaust module and tunnel 
assembly would require about 20 work-hours, and required parts would 
cost $1,500, for a cost of $3,200 per helicopter and $176,000 for the 
U.S. fleet.
    If required, replacing a driveshaft tube would require 1 work-hour, 
and required parts would cost $6,500, for a cost per helicopter of 
$6,585.
    According to Leonardo Helicopter's service information some of the 
costs of this proposed AD may be covered under warranty, thereby 
reducing the cost impact on affected individuals. We do not control 
warranty coverage by Leonardo Helicopters. Accordingly, we have 
included all costs in our cost estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Leonardo S.p.A. (Type Certificate Previously Held by Finmeccanica 
S.p.A, AgustaWestland S.p.A.): Docket No. FAA-2018-0737; Product 
Identifier 2017-SW-096-AD.

(a) Applicability

    This AD applies to Model AW139 helicopters, serial numbers 
31499, 31504, 31507, 31509, 31512, 31518, 31519, 31524, 31529, 
31533, 31535 through 31564, 31567, 31569, 31570, 31589, 41363, 41368 
through 41370, 41372 through 41375, 41378, 41381, and 41384, with a 
tunnel assembly part number 3G7130A13431 installed, certificated in 
any category.

 (b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a tail rotor 
driveshaft, which could result in failure of the tail rotor drive 
system and subsequent loss of control of the helicopter.

 (c) Comments Due Date

    We must receive comments by October 26, 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

    (1) Within 30 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 100 hours TIS, inspect the number 1 
driveshaft tube shaft, P/N 3G6510A00832, for a scratch and 
indentation in the area depicted in Figure 1 of Leonardo Helicopters 
Bollettino Tecnico No. 139-465, Revision A, dated January 25, 2017 
(BT 139-465). If there is a scratch or indentation, before further 
flight:
    (i) Repair the tube shaft in accordance with the Compliance 
Instructions, Part I, paragraphs 7.1 through 7.3, of BT 139-465.
    (ii) Measure the depth of the repaired areas as depicted in 
Figure 2 of BT 139-465.
    (A) If the depth of the reworked area is 0.2 mm (0.079 inch) or 
less, eddy-current inspect the driveshaft for a crack as described 
in the Compliance Instructions, Annex A, of BT 139-465. If there is 
a crack, before further flight, replace the driveshaft, alter the 
rear exhaust module, and alter and re-identify the tunnel assembly 
in accordance with the Compliance Instructions, Part II, paragraphs 
7 through 12, of BT 139-465.
    (B) If the depth of the reworked area is more than 0.2 mm (0.079 
inch), before further flight, replace the driveshaft, alter the rear 
exhaust module, and alter and re-identify the tunnel assembly in 
accordance with the Compliance Instructions, Part II, paragraphs 7 
through 12, of BT 139-465.
    (2) Within 300 hours TIS, unless already accomplished as 
required by paragraph (e)(1)(ii) of this AD, alter the rear exhaust 
module and alter and re-identify the tunnel assembly in accordance 
with the Compliance Instructions, Part II, paragraphs 7 through 12, 
of BT 139-465.

 (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 <a href="/cdn-cgi/l/email-protection#83baaec2d0d4aec5d7d4aec2ceccc0aed1e6f2f6e6f0f7f0c3e5e2e2ade4ecf5"><span class="__cf_email__" data-cfemail="caf3e78b999de78c9e9de78b878589e798afbbbfafb9beb98aacababe4ada5bc">[email protected]</span></a>.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, we suggest that

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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 (EASA) AD No. 2017-0011, dated January 25, 2017. You may view 
the EASA AD on the internet at http://www.regulations.gov in the AD 
Docket.

 (i) Subject

    Joint Aircraft Service Component (JASC) Code: 6510 Tail Rotor 
Driveshaft.


    Issued in Fort Worth, Texas, on August 10, 2018.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2018-18472 Filed 8-24-18; 8:45 am]
 BILLING CODE 4910-13-P


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