[Federal Register Volume 81, Number 8 (Wednesday, January 13, 2016)]
[Rules and Regulations]
[Pages 1492-1494]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-00013]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8695; Directorate Identifier 2015-SW-042-AD; 
Amendment 39-18365; AD 2016-01-06]
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 AB139 and AW139 helicopters. This AD requires 
inspecting each full ice protection system tail rotor slip ring (slip 
ring) for chatter marks, witness marks, or scoring, and determining the 
depth of each mounting hole. Based on the findings from the inspection, 
this AD requires either re-identifying the slip ring or replacing the 
slip ring. This AD is prompted by two incidents of the slip ring body 
separating from the supporting flange due to improper torque. These 
actions are intended to prevent separation of the mounting flange from 
the slip ring body and subsequent loss of control of the helicopter.

DATES: This AD becomes effective January 28, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of January 28, 
2016.
    We must receive comments on this AD by March 14, 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-
8695; 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, any 
incorporated by reference service information, 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 final rule, 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; and Moog Inc., Components Group, Blacksburg 
Operations, 1213 North Main St., Blacksburg, Virginia 24606-3127, 
telephone (540) 552-3011, or at www.moog.com. 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: 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

[[Page 1493]]

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

    We are adopting a new AD for Agusta Model AB139 and AW139 
helicopters with certain slip rings installed. This AD requires 
inspecting each slip ring for chatter marks, witness marks, or scoring. 
Based on the findings from the inspection, the AD requires either re-
identifying the slip ring by marking a letter ``T'' after the serial 
number or replacing the slip ring with a slip ring that is not affected 
by this AD. This AD is prompted by two reports of detached slip ring 
bodies from the supporting flange due to improperly low torque of the 
affected screws during installation. These actions are intended to 
prevent separation of the mounting flange from the slip ring body and 
subsequent loss of control of the helicopter.
    This AD was prompted by AD No. 2015-0155, dated July 28, 2015, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, to correct an unsafe condition for the Agusta Model 
AB139 and AW139 helicopters. EASA advises of two incidents of the 
screws being found loose and broken on two Model AW139 helicopter tail 
rotor slip rings. EASA states that subsequent technical investigation 
revealed that the torque of the screws was improperly low. The slip 
ring manufacturer established that this occurred on the production line 
by improper installation of the affected screws on a number of slip 
rings. EASA advises that this condition, if not detected and corrected, 
could lead to other events of detachment of the slip ring, possibly 
resulting in reduced control of the helicopter.

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

    We reviewed AgustaWestland Bollettino Technico No. 139-404, dated 
December 22, 2014 (BT), including Annex A Moog Service Bulletin SB 14-
02, Revision D, undated (Moog SB). The BT specifies inspecting and 
replacing the slip ring mounting screws and reinstalling the lockwire 
by complying with the Moog SB. The Moog SB advises of insufficient 
torqueing of the screws and incorrect lock wiring used to affix the 
tail rotor mountain plate to the slip ring frame. If the slip ring does 
not pass the inspection, the BT specifies returning the slip ring to 
AgustaWestland, replacing it, and marking the letter ``T'' after the 
serial number of the unit. AgustaWestland states that slip rings 
already marked with a ``T'' after the serial number or ``MOD 1'' marked 
in the manufacturing plate do not have to be inspected. 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 within 25 hours time-in-service:
     Removing each slip ring, lockwire, fastener, and washer.
     Inspecting the wall of the mounting plate hole for a 
chatter mark, witness mark, or scoring. If there is a chatter mark, 
witness mark, or scoring, replacing the slip ring with an airworthy 
slip ring.
     Determining the depth of the mounting plate hole. If the 
depth exceeds the grip length of the screw, replacing the slip ring 
with an airworthy slip ring.
     Re-identifying the slip ring by marking a letter ``T'' 
after the serial number with permanent black pen and applying acrylic 
lacquer (CO81 or equivalent).
    This AD also prohibits installing an affected slip ring on any 
helicopter unless the slip ring has passed the inspections in 
accordance with this AD.

Differences Between This AD and the EASA AD

    This AD requires compliance within 25 hours time-in-service; the 
EASA AD requires compliance within 14 days.

Costs of Compliance

    We estimate that this AD will affect 106 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. We estimate 3 work hours to inspect the slip ring for a cost of 
$255 per helicopter and $27,030 for the fleet. We estimate $56,806 in 
required parts and no additional labor costs to replace a slip ring.

FAA's Justification and Determination of the Effective Date

    Providing an opportunity for public comments before adopting these 
AD requirements would delay implementing the safety actions needed to 
correct this known unsafe condition. Therefore, we found that the risk 
to the flying public justifies waiving notice and comment prior to the 
adoption of this rule because the previously described unsafe condition 
can adversely affect the controllability of the helicopter and the 
required corrective actions must be accomplished within 25 hours TIS. 
These helicopters have a variety of uses including offshore and 
emergency 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;

[[Page 1494]]

    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):

2016-01-06 Agusta S.p.A.: Amendment 39-18365; Docket No. FAA-2015-
8695; Directorate Identifier 2015-SW-042-AD.

(a) Applicability

    This AD applies to Model AB139 and AW139 helicopters, 
certificated in any category, with a Full Icing Protection System 
tail rotor slip ring (slip ring) part number (P/N) 4G6420V00151, P/N 
4G6420V00152, or P/N 4G6420V00153 installed, except a slip ring with 
a letter ``T'' after the serial number or marked with ``MOD 1.''

(b) Unsafe Condition

    This AD defines the unsafe condition as a loose or missing screw 
connecting the mounting flange and the slip ring body. This 
condition could result in separation of the mounting flange from the 
slip ring body and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective January 28, 2016.

 (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:
    (1) Remove each slip ring from the helicopter. Remove each 
lockwire, fastener, and washer by following the Compliance 
Instructions, paragraphs 3 through 5, of Moog Service Bulletin SB 
14-02, Revision D, undated, included as Annex A to Agusta Westland 
Bollettino Tecnico (BT) No. 139-404, dated December 22, 2014, except 
you are not required to discard parts.
    (2) Inspect the wall of the mounting plate hole for a chatter 
mark, witness mark, or scoring. If there is a chatter mark, witness 
mark, or scoring, replace the slip ring with a slip ring that is not 
listed in paragraph (a) of this AD.
    (3) Determine the depth of the mounting plate hole. If the depth 
exceeds the grip length of the screw, replace the slip ring with a 
slip ring that is not listed in paragraph (a) of this AD.
    (4) Re-identify the slip ring by marking a letter ``T'' after 
the serial number with permanent black pen and applying acrylic 
lacquer (CO81 or equivalent).
    (5) Do not install an affected slip ring on any helicopter 
unless the slip ring has passed the inspections in accordance with 
this AD.

(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

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2015-0155, dated July 28, 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-2015-8695.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 3060 Propeller/
Rotor Anti-ice/De-Ice 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) AgustaWestland Bollettino Technico No. 139-404, dated 
December 22, 2014, including Annex A, Moog Service Bulletin SB 14-
02, Revision D, undated.
    (ii) Reserved.
    (3) For service information identified in this AD, contact Moog 
Inc., Components Group, Blacksburg Operations, 1213 North Main St., 
Blacksburg, Virginia 24606-3127, telephone 540/552-3011, or at 
www.moog.com.
    (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.

    Issued in Fort Worth, Texas, on December 28, 2015.
Lance T. Gant,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2016-00013 Filed 1-12-16; 8:45 am]
 BILLING CODE 4910-13-P