[Federal Register Volume 79, Number 136 (Wednesday, July 16, 2014)]
[Proposed Rules]
[Pages 41462-41464]
From the Federal Register Online via the Government Publishing 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 [email protected].
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 [email protected].
(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]
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