Document ID: FAA-2018-0170-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Agusta S.p.A. Helicopters
Posted Date: 2018-04-11T04:00Z

[Federal Register Volume 83, Number 70 (Wednesday, April 11, 2018)]
[Rules and Regulations]
[Pages 15495-15498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07285]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0170; Product Identifier 2017-SW-091-AD; Amendment 
39-19239; AD 2018-07-08]
RIN 2120-AA64

Airworthiness Directives; Agusta S.p.A. 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 Agusta 
S.p.A. (Agusta) Model A109E, A109K2, A109S, AW109SP, A119, and AW119 
MKII helicopters. This AD reduces the life limit of and requires 
inspecting a tail rotor blade retention bolt (bolt). This AD is 
prompted by the discovery of a cracked bolt. The actions of this AD are 
intended to address an unsafe condition on these products.

DATES: This AD becomes effective April 26, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of April 26, 2018.
    We must receive comments on this AD by June 11, 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-
0170; 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, any 
incorporated-by-reference service information, 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 
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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0170.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior 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

[[Page 15496]]

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. 2016-0173-E, dated August 
24, 2016, to correct an unsafe condition for Leonardo S.p.A. (formerly 
Agusta) Model A109E, A109K2, A109LUH, A109S, A119, AW109SP, and 
AW119MKII helicopters. EASA advises of a crack found in a bolt, part 
number (P/N) 709-0160-57-101, during a pre-flight inspection of a Model 
A109E helicopter. This part-numbered bolt is also installed on Model 
A109K2, A109LUH, A109S, A119, AW109SP, and AW119MKII helicopters. 
Subsequent investigation did not identify the cause of the crack. EASA 
advises that this condition, if not detected and corrected, could lead 
to failure of the tail rotor, possibly resulting in loss of control of 
the helicopter. As a precautionary measure pending the completion of 
the investigation and to address the unsafe condition, the EASA AD 
requires reducing the life limit of and repetitively inspecting the 
bolts. The EASA AD is considered an interim action and further AD 
action may follow.
    Accordingly, this AD requires reducing the life limit of bolt P/N 
709-0160-57-101 to 800 hours time-in-service (TIS) or 3,200 landings, 
depending on the model helicopter on which the bolt is installed. This 
AD also requires, within 25 hours TIS, inspecting each bolt for a crack 
using a 10X or higher power magnifying glass, both before and after 
cleaning and degreasing the bolts. Additional inspections of the bolts 
at longer intervals may also be necessary. We plan to publish a notice 
of proposed rulemaking to give the public an opportunity to comment on 
those long-term requirements.
    The FAA is in the process of updating Agusta's name change to 
Leonardo Helicopters on its FAA type certificate. Because this name 
change is not yet effective, this AD specifies Agusta.

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 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 Under 1 CFR Part 51

    Leonardo Helicopters has issued Mandatory Bollettino Tecnico (BT) 
No. 109EP-149 for Model A109E helicopters, Mandatory BT No. 109K-72 for 
Model A109K2 helicopters, Mandatory BT No. 109S-072 for Model A109S 
helicopters, Mandatory BT No. 109SP-105 for Model AW109SP helicopters, 
and Mandatory BT No. 119-080 for Model A119 and AW119 MKII helicopters, 
all dated August 19, 2016. This service information specifies reducing 
the life limit of bolt P/N 709-0160-57-101 and repetitively inspecting 
the bolts for cracks.
    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 requires, before further flight, removing from service any 
bolt P/N 709-0160-57-101 that has reached or exceeded its new life 
limit. Thereafter, this AD requires removing from service any bolt P/N 
709-0160-57-101 before it reaches its new life limit.
    This AD also requires, within 25 hours time-in-service, inspecting 
each bolt for a crack using a 10X or higher power magnifying glass, 
both before and after cleaning and degreasing the bolts, and replacing 
a cracked bolt before further flight.

Differences Between This AD and the EASA AD

    The EASA AD applies to Model A109LUH helicopters. This AD does not 
because the Model A109LUH does not have an FAA type certificate. The 
EASA AD does not specify life limits for bolt P/N 709-0160-57-101 that 
has been interchanged between model helicopter installations, while 
this AD does. The EASA AD requires repeating the visual inspection 
every 200 hours, while this AD does not, as this time interval would 
allow for sufficient time for notice and comment.

Interim Action

    We consider this AD to be an interim action. The design approval 
holder is currently developing a modification that will address the 
unsafe condition identified in this AD. Once this modification is 
developed, approved, and available, we might consider additional 
rulemaking.

Costs of Compliance

    We estimate that this AD affects 234 helicopters of U.S. Registry. 
We estimate that operators may incur the following costs in order to 
comply with this AD. Labor costs are estimated at $85 per work-hour.
    Removing a bolt that has reached its new life limit will take about 
2 work-hours for a cost of $170 per bolt. Inspecting the bolts will 
take about 4 work-hours for an estimated cost of $340 per helicopter 
and $79,560 for the U.S. fleet. Replacing a bolt will take negligible 
additional labor time and parts will cost about $500.
    According to Leonardo Helicopter's service information, some of the 
costs of this AD may be covered under warranty, thereby reducing the 
cost impact on affected individuals. We do not control warranty 
coverage by Leonardo Helicopter. Accordingly, we have included all 
costs in our cost estimate.

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 some of the required corrective actions must be completed 
before further flight. Therefore, we find good cause that notice and 
opportunity for prior public comment are impracticable.
    In addition, for the reasons 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

[[Page 15497]]

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):

2018-07-08 Agusta S.p.A.: Amendment 39-19239; Docket No. FAA-2018-
0170; Product Identifier 2017-SW-091-AD.

(a) Applicability

    This AD applies to Model A109E, A109K2, A109S, AW109SP, A119, 
and AW119 MKII helicopters, certificated in any category, with a 
tail rotor blade retention bolt (bolt) part number (P/N) 709-0160-
57-101 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a bolt. This 
condition could result in failure of the tail rotor and loss of 
control of the helicopter.

(c) Effective Date

    This AD becomes effective April 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) Before further flight:
    (i) For Model A109E and A109K2 helicopters, remove from service 
any bolt P/N 709-0160-57-101 that has 800 or more hours time-in-
service (TIS). If the hours TIS is unknown, remove the bolt from 
service. Thereafter, remove from service any bolt P/N 709-0160-57-
101 before accumulating 800 hours TIS.
    (ii) For Model A109S, AW109SP, A119, and AW119 MKII helicopters, 
remove from service any bolt P/N 709-0160-57-101 that has 3,200 or 
more landings. If the number of landings is unknown, remove the bolt 
from service. Thereafter, remove from service any bolt P/N 709-0160-
57-101 before accumulating 3,200 landings. For purposes of this AD, 
a landing is counted anytime a helicopter lifts off into the air and 
then lands again regardless of the duration of the landing and 
regardless of whether the engine is shutdown.
    (iii) Remove from service any bolt P/N 709-0160-57-101 that has 
been interchanged between different model helicopters listed in 
paragraphs (e)(1)(i) and (e)(1)(ii) of this AD that has 800 or more 
hours TIS or 3,200 or more landings. If the hours TIS or number of 
landings is unknown, remove the bolt from service. Thereafter, 
remove from service any bolt P/N 709-0160-57-101 that has been 
interchanged between different model helicopters listed in 
paragraphs (e)(1)(i) and (e)(1)(ii) of this AD before accumulating 
800 hours TIS or 3,200 landings, whichever occurs first.
    (2) Within 25 hours TIS, remove each bolt P/N 709-0160-57-101. 
Prior to cleaning, using a 10X or higher power magnifying glass, 
visually inspect the bolt for a crack in the area depicted in Figure 
1 of Leonardo Helicopters Mandatory Bollettino Tecnico Nos. 109EP-
149, 109K-72, 109S-072, 109SP-105, or 119-080, all dated August 19, 
2016 (BT Nos. 109EP-149, 109K-72, 109S-072, 109SP-105, or 119-080), 
as applicable to your model helicopter.
    (i) If there is a crack, replace the bolt before further flight.
    (ii) If there are no cracks, clean and degrease the inspection 
area of the bolt with solvent, and using a 10X or higher power 
magnifying glass, visually inspect the bolt for a crack in the area 
depicted in Figure 1 of BT Nos. 109EP-149, 109K-72, 109S-072, 109SP-
105, or 119-080, as applicable to your model helicopter. If there is 
a crack, replace the bolt before further flight.

(f) 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: 
Matt Fuller, Senior 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.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) Emergency AD No. 2016-0173-E, dated August 24, 2016. 
You may view the EASA AD on the internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2018-0170.

(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) Leonardo Helicopters Mandatory Bollettino Tecnico No. 109EP-
149, dated August 19, 2016.
    (ii) Leonardo Helicopters Mandatory Bollettino Tecnico No. 109K-
72, dated August 19, 2016.
    (iii) Leonardo Helicopters Mandatory Bollettino Tecnico No. 
109S-072, dated August 19, 2016.
    (iv) Leonardo Helicopters Mandatory Bollettino Tecnico No. 
109SP-105, dated August 19, 2016.
    (v) Leonardo Helicopters Mandatory Bollettino Tecnico No. 119-
080, dated August 19, 2016.
    (3) For Leonardo Helicopters service information identified in 
this AD, 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.
    (4) You may view this service information at 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, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

[[Page 15498]]

    Issued in Fort Worth, Texas, on April 3, 2018.
Scott A. Horn,
Deputy Director for Regulatory Operations, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2018-07285 Filed 4-10-18; 8:45 am]
 BILLING CODE 4910-13-P