[Federal Register Volume 80, Number 236 (Wednesday, December 9, 2015)]
[Rules and Regulations]
[Pages 76381-76383]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30973]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3783; Directorate Identifier 2015-SW-027-AD; 
Amendment 39-18342; AD 2015-25-04]
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 A109A and A109A II helicopters. This AD requires 
inspecting the slider assembly pitch control (slider) for play and 
replacing the slider if the play exceeds certain limits. This AD is 
prompted by a report of excessive slider play and wear that was 
detected during a scheduled inspection of a Model A109A II helicopter. 
These actions are intended to detect and prevent excessive wear and 
play on a slider, which could lead to loss of tail rotor pitch control 
and consequently loss of helicopter control.

DATES: This AD becomes effective December 24, 2015.
    We must receive comments on this AD by February 8, 2016.

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-2015-
3783; or in person at the Docket Operations Office 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 the Docket Operations Office (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 AD, contact 
AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 
Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-
664757; fax 39-0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may review the referenced service information 
at the FAA, Office of the Regional Counsel, Southwest Region, Room 6N-
321, 10101 Hillwood Pkwy, Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Martin R. Crane, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, 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 EASA AD No. 2015-0097, dated June 1, 2015, 
to correct an unsafe condition for Agusta Model A109A and A109A II 
helicopters. EASA advises that during a scheduled 100-flight-hour 
inspection on a Model A109A II helicopter, unusual play was detected on 
a part number (P/N) 109-0130-11-7 slider. Further investigation 
revealed excessive wear of the slider broaching at the point of contact 
with the tail rotor shaft. However, the cause of the excessive play and 
wear has not been determined.
    This condition, if not detected and corrected, could lead to 
reduced control of the helicopter, EASA advises. EASA consequently 
requires repetitive inspections of slider P/N 109-0130-11-7 more 
frequently than those performed at the 100-flight-hour inspection and 
corrective actions depending on the findings. EASA advises that its AD 
is an interim measure and further AD action may follow.

[[Page 76382]]

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

    We reviewed AgustaWestland Bollettino Tecnico No. 109-149, dated 
May 29, 2015, for Model A109A and A109A II helicopters. The bulletin 
states that during a 100-flight-hour inspection of a Model A109A II 
helicopter, ``anomalous'' play was found on a P/N 109-0130-11-7 slider. 
After the slider was removed and inspected, extended, unusual wear of 
the broaching in the point of contact with the tail rotor shaft was 
found. Agusta states that the investigation is ongoing, but as a 
precautionary measure it is reducing the slider inspection intervals 
from 100 flight hours to 25 flight hours.

AD Requirements

    This AD requires, within 25 hours time-in-service (TIS) and 
thereafter at intervals not to exceed 25 hours TIS, inspecting the 
slider for play. If there is any play that exceeds 2.3 millimeters 
(0.09 inch), this AD requires replacing the slider with an airworthy 
slider before further flight.

Interim Action

    We consider this AD to be an interim action. The design approval 
holder has not determined the cause of the unsafe condition identified 
in this AD. If a cause is determined and actions developed to address 
the cause, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this AD will affect 36 helicopters of U.S. 
Registry and that labor costs average $85 a work-hour. Based on these 
estimates, we expect the following costs:
     Inspecting the slider for play requires 1 work-hour for a 
labor cost of $85 per helicopter and $3060 for the U.S. fleet.
     Replacing the slider requires 10 work-hours and $4068 in 
parts for a total cost of $4918 per helicopter.
    According to Agusta'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 Agusta. 
Accordingly, we have included all costs in our cost estimate.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments prior to adopting 
these AD requirements would delay implementing the safety actions 
needed to correct this known unsafe condition. Therefore, we find that 
the risk to the flying public justifies waiving notice and comment 
prior to the adoption of this rule because the unsafe condition can 
adversely affect control of the helicopter and the required corrective 
actions must be accomplished within 25 hours TIS. These helicopters 
have a variety of uses, including search-and-rescue and medical 
flights, and are expected to accumulate 25 hours TIS within a few 
weeks.
    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we determined that notice and opportunity for 
public comment before issuing this AD are impracticable and contrary to 
the public interest and 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):

2015-25-04 Agusta S.p.A.: Amendment 39-18342; Docket No. FAA-2015-
3783; Directorate Identifier 2015-SW-027-AD.

(a) Applicability

    This AD applies to Agusta S.p.A. (Agusta) Model A109A and A109A 
II helicopters with a slider assembly pitch control (slider) part 
number 109-0130-11-7 installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as excessive wear and play 
on a slider. This condition could result in loss of tail rotor pitch 
control and consequently loss of helicopter control.

(c) Effective Date

    This AD becomes effective December 24, 2015.

(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 25 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 25 hours

[[Page 76383]]

TIS, inspect the slider for play. If there is play greater than 2.3 
millimeters (0.09 inch), replace the slider with an airworthy slider 
before further flight.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Martin R. Crane, Aviation Safety 
Engineer, Safety Management Group, Rotorcraft Directorate, 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

    (1) AgustaWestland Bollettino Tecnico No. 109-149, dated May 29, 
2015, which is not incorporated by reference, contains additional 
information about the subject of this AD. For service information 
identified in this AD, contact AgustaWestland, Product Support 
Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, 
ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39-0331-
664680; or at http://www.agustawestland.com/technical-bulletins. You 
may review a copy of the service information at the FAA, Office of 
the Regional Counsel, Southwest Region, Room 6N-321, 10101 Hillwood 
Pkwy, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2015-0097, dated June 1, 2015. You may 
view the EASA AD on the Internet at http://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2015-3783.

(h) Subject

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

    Issued in Fort Worth, Texas, on December 2, 2015.
James A. Grigg,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2015-30973 Filed 12-8-15; 8:45 am]
 BILLING CODE 4910-13-P