Document ID: FAA-2014-0472-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Agusta S.p.A Helicopters (Type Certificate Currently Held by AgustaWestland S.p.A.) (Agusta)
Posted Date: 2014-07-16T04:00Z

[Federal Register Volume 79, Number 136 (Wednesday, July 16, 2014)]
[Proposed Rules]
[Pages 41462-41464]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-16683]

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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]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. 
This proposed AD was prompted by a report of a crack that was found on 
a Gleason crown. This proposed AD would require repetitively performing 
a magnetic particle inspection of the Gleason crown for a crack. We are 
proposing this AD to detect a crack, which could cause damage to or 
loss of the main rotor drive and subsequent loss of control of the 
helicopter.

DATES: We must receive comments on this proposed AD by September 2, 
2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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 Management Facility 
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 regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Office (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

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 rao.edupuganti@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2014-0472; 
Directorate Identifier 2013-SW-040-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD No. 2013-0118, dated June 3, 2013, 
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, part number (P/N) 109-0400-05-103, a crack on 
the Gleason crown, P/N 109-0403-07-103, was found. EASA further states 
that an investigation by Agusta revealed 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.

Relevant 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

[[Page 41463]]

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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Proposed AD Requirements

    This proposed AD would require, for helicopters with a main 
transmission, P/N 109-0400-03-109, with 2,400 or more hours time-in-
service (TIS), performing a magnetic particle inspection of the Gleason 
crown, P/N 109-0403-07-103, within 200 hours TIS, and thereafter at 
intervals not exceeding 1,600 hours TIS. If there is a crack, this 
proposed AD would require replacing the Gleason crown assembly with a 
different part-numbered assembly before further flight. The proposed AD 
would also prohibit installing on any helicopter 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.

Differences Between This Proposed AD and the EASA AD

    This proposed 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.

Costs of Compliance

    We estimate that this proposed AD affects 218 helicopters of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD. At an average labor rate of $85 per hour, magnetic particle 
inspecting the Gleason crown would require 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 would require 
about 24 work-hours, and required parts would cost $29,000, for a cost 
per helicopter of $31,040.
    According to the manufacturer, 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 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 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 above, 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, 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.

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. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

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

(a) Comments Due Date

    We must receive comments by September 2, 2014.

(b) 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, and 109-0400-03-109, with a Gleason 
crown P/N 109-0403-07-103 installed, certificated in any category.

(c) 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.

(d) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(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

[[Page 41464]]

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, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your 
request to your principal inspector or local Flight Standards 
District Office, as appropriate. If sending information directly to 
the manager of the ACO, send it to the attention of the person 
identified in paragraph (g) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(g) Related Information

    (1) For more information about this AD, 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 rao.edupuganti@faa.gov.
    (2) For service information identified in this proposed 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.
    (3) 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 System Component Code: 6320: Main Rotor Gearbox.

    Issued in Fort Worth, Texas, on July 9, 2014.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-16683 Filed 7-15-14; 8:45 am]
BILLING CODE 4910-13-P