[Federal Register Volume 79, Number 224 (Thursday, November 20, 2014)]
[Rules and Regulations]
[Pages 69039-69041]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-26825]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0472; Directorate Identifier 2013-SW-040-AD; 
Amendment 39-18018; AD 2014-23-02]
RIN 2120-AA64


Airworthiness Directives; Agusta S.p.A. Helicopters (Type 
Certificate Currently Held by AgustaWestland S.p.A.) (Agusta)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. This AD 
requires repetitively performing a magnetic particle inspection of the 
Gleason crown for a crack. This AD was prompted by a report of a crack 
that was found on a Gleason crown, which if not detected, could cause 
damage to or loss of the main rotor drive and subsequent loss of 
control of the helicopter.

DATES: This AD is effective December 26, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of December 26, 
2014.

ADDRESSES: 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-bullettins. You may review the referenced service information 
at the FAA, Office of the Regional Counsel, Southwest Region, 2601 
Meacham Blvd., Room 663, Fort Worth, Texas 76137.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov 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 (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations Office, 
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email <a href="/cdn-cgi/l/email-protection#bac8dbd594dfdecfcacfdddbd4ced3fadcdbdb94ddd5cc"><span class="__cf_email__" data-cfemail="96e4f7f9b8f3f2e3e6e3f1f7f8e2ffd6f0f7f7b8f1f9e0">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    On July 16, 2014, at 79 FR 41462, the Federal Register published 
our notice of proposed rulemaking (NPRM), which proposed to amend 14 
CFR part 39 by adding an AD that would apply to Agusta Model A109E, 
A109K2, A119, and AW119 MKII helicopters with a main transmission, part 
number (P/N) 109-0400-03-103, 109-0400-05-103, and 109-0400-03-109, 
with a Gleason crown, P/N 109-0403-07-103, installed. The NPRM proposed 
to require, for main transmissions with 2,400 or more hours time-in-
service (TIS), performing repetitive magnetic particle inspections of 
the Gleason crown for a crack. If there is a crack, the NPRM proposed 
replacing the Gleason crown assembly before further flight. The NPRM 
also proposed to prohibit installing a Gleason crown, P/N 109-0403-07-
103, or a Gleason crown assembly, P/N 109-0401-27-101 or P/N 109-0401-
27-109, on any helicopter. The proposed requirements were intended to 
detect a crack, which could cause damage to or loss of the main rotor 
drive and subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2013-0118, dated June 3, 2013, 
issued by EASA, which is the Technical Agent

[[Page 69040]]

for the Member States of the European Union, to correct an unsafe 
condition for Agusta Model A109K2, A109E, A119, and AW119MKII 
helicopters. EASA advises that during an overhaul of an A119 main 
transmission, P/N 109-0400-05-103, a crack on the Gleason crown, P/N 
109-0403-07-103, was found. EASA further states that the crack 
originated from the bottom of one of the 40 threaded holes in the 
Gleason crown, and that this part-numbered Gleason crown is also 
installed on Model A109 helicopters. EASA states that this condition, 
if not corrected, could cause damage to or loss of the main rotor drive 
and loss of control of the helicopter. To correct this unsafe 
condition, EASA AD No. 2013-0118 requires repetitive magnetic particle 
inspections of the Gleason crown and, if there is a crack, replacing 
the Gleason crown with a different part-numbered Gleason crown. EASA AD 
No. 2013-0118 also prohibits installing a Gleason crown, P/N 109-0403-
07-103, or a Gleason crown assembly, P/N 109-0401-27-101 or P/N 109-
0401-27-109, on any helicopter, as Gleason crown, P/N 109-0403-07-103, 
is a component of these assemblies.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (79 FR 41462, 
July 16, 2014).

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 and that air 
safety and the public interest require adopting the AD requirements as 
proposed, except for minor editorial changes. These changes are 
consistent with the intent of the proposals in the NPRM (79 FR 41462, 
July 16, 2014) and will not increase the economic burden on any 
operator nor increase the scope of the AD.

Differences Between This AD and the EASA AD

    This AD requires compliance within 200 hours TIS for main 
transmissions with 2,400 or more hours. The EASA AD requires different 
compliance times, depending on the number of flight hours the 
transmission has accumulated.

Related Service Information

    We reviewed Agusta Bollettino Tecnico (BT) No. 109EP-128 for Model 
A109E helicopters, Agusta BT No. 109K-57 for Model A109K2 helicopters, 
and Agusta BT No. 119-058 for Model A119 and AW119MKII helicopters, 
each Revision A and dated May 28, 2013. Each BT describes procedures 
for performing a magnetic particle inspection on the Gleason crown, P/N 
109-0403-07-103, for a crack. If there is a crack, each BT specifies 
replacing the Gleason crown assembly with a Gleason crown assembly, P/N 
109-0401-27-107.
    We also reviewed Agusta BT No. 109EP-126 for Model A109E 
helicopters, Agusta BT No. 109K-56 for Model A109K2 helicopters, and 
Agusta BT No. 119-053 for Model A119 and AW119MKII helicopters, each 
dated December 20, 2012. These BTs contain procedures for upgrading the 
transmission system by replacing the Gleason crown assembly with a 
Gleason crown assembly, P/N 109-0401-27-107.

Costs of Compliance

    We estimate that this AD affects 218 helicopters of U.S. registry. 
We estimate the following costs to comply with this AD. At an average 
labor rate of $85 per hour, magnetic particle inspecting the Gleason 
crown requires about 24 work-hours, for an estimated cost per 
helicopter of $2,040, and a total cost of $444,720 for the U.S. fleet, 
per inspection cycle.
    If required, replacing the Gleason crown assembly requires about 24 
work-hours, and required parts will cost $29,000, for a cost per 
helicopter of $31,040.
    According to the manufacturer, 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 for affected 
individuals. As a result, 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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    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 above, 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):

2014-23-02 Agusta S.p.A. Helicopters (Type Certificate Currently 
Held By AgustaWestland S.p.A.) (Agusta): Amendment 39-18018; Docket 
No. FAA-2014-0472; Directorate Identifier 2013-SW-040-AD.

[[Page 69041]]

(a) Applicability

    This AD applies to Agusta Model A109E, A109K2, A119, and AW119 
MKII helicopters with a main transmission, part number (P/N) 109-
0400-03-103, 109-0400-05-103, or 109-0400-03-109, with a Gleason 
crown, P/N 109-0403-07-103, installed, certificated in any category.

 (b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a Gleason 
crown. This condition could cause damage to or loss of the main 
rotor drive and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective December 26, 2014.

(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) For main transmissions with 2,400 or more hours time-in-
service (TIS), within 200 hours TIS and thereafter at intervals not 
exceeding 1,600 hours TIS, magnetic particle inspect the Gleason 
crown, P/N 109-0403-07-103, for a crack by following the procedures 
in:
    (i) Annex 1 of Agusta Bollettino Tecnico (BT) No. 109EP-128, 
Revision A, dated May 28, 2013, for Model A109E helicopters;
    (ii) Annex 1 of Agusta BT No. 109K-57, Revision A, dated May 28, 
2013, for Model A109K2 helicopters; or
    (iii) Annex 1 of Agusta BT No. 119-058, Revision A, dated May 
28, 2013, for Model A119 and AW119MKII helicopters.
    (2) If there is a crack, before further flight, replace the 
Gleason crown assembly with a Gleason Crown assembly, P/N 109-0401-
27-107. Replacing the Gleason crown assembly with P/N 109-0401-27-
107 is terminating action for the inspection requirements of this 
AD.
    (3) After the effective date of this AD, do not install a 
Gleason crown, P/N 109-0403-07-103, or a Gleason crown assembly, P/N 
109-0401-27-101 or P/N 109-0401-27-109, on any helicopter.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Rao Edupuganti, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email <a href="/cdn-cgi/l/email-protection#0371626c2d666776737664626d776a436562622d646c75"><span class="__cf_email__" data-cfemail="c7b5a6a8e9a2a3b2b7b2a0a6a9b3ae87a1a6a6e9a0a8b1">[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 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. 2013-0118, dated June 3, 2013. You may view the 
EASA AD on the Internet at http://www.regulations.gov in Docket No. 
FAA-2014-0472.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6320: Main Rotor 
Gearbox.

 (i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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 Tecnico No. 109EP-128, Revision A, 
dated May 28, 2013.
    (ii) AgustaWestland Bollettino Tecnico No. 109K-57, Revision A, 
dated May 28, 2013.
    (iii) AgustaWestland Bollettino Tecnico No. 119-058, Revision A, 
dated May 28, 2013.
    (3) For AgustaWestland 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-bullettins.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. 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 October 30, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-26825 Filed 11-19-14; 8:45 am]
BILLING CODE 4910-13-P


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