[Federal Register Volume 78, Number 224 (Wednesday, November 20, 2013)]
[Proposed Rules]
[Pages 69595-69597]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-27634]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0943; Directorate Identifier 2013-SW-001-AD]
RIN 2120-AA64
Airworthiness Directives; AgustaWestland S.p.A. (Type Certificate
Formerly Held by Agusta S.p.A.) (Agusta) Helicopters
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
Agusta Model A109C, A109E, A109K2, and A119 helicopters. This proposed
AD would require recurring visual inspections of the tail rotor (T/R)
blade retaining bolts (bolts) for a crack, corrosion, damage, or
missing cadmium plating in the central part of the bolt. If a crack is
not detected by the initial visual inspection then this proposed AD
would require a liquid penetrant inspection. Replacing a cracked or
damaged bolt would be required before further flight. This proposed AD
is prompted by two reported incidents of cracked bolts. The proposed
actions are intended to detect an unairworthy bolt and prevent failure
of a bolt, release of a T/R blade, and subsequent loss of control of
the helicopter.
DATES: We must receive comments on this proposed AD by January 21,
2014.
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.
[[Page 69596]]
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 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 proposed AD, the foreign
authority's 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 proposed AD, contact
AgustaWestland, Customer Support & Services, Via Per Tornavento 15,
21019 Somma Lombardo (VA) Italy, ATTN: Giovanni Cecchelli; telephone
39-0331-711133; fax 39 0331 711180; 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.
FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222-5110; email [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
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 might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, issued EASA AD No.
2013-0009, dated January 11, 2013, to correct an unsafe condition for
the Agusta Model A109C, A109K2, A109E, and A119 helicopters, all serial
numbers. EASA advises that cracks were reported in bolts, part number
(P/N) 109-8131-09-1, installed on a Model A109K2 and a Model A109E
helicopter. EASA further states that investigations conducted by Agusta
revealed the cracks were in the same area of the bolts and corresponded
with corrosion pits. EASA specified that this condition, if not
detected and corrected, could cause damage to, or loss of, a T/R blade,
possibly resulting in loss of 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 its AD. We are
proposing this AD because we evaluated all known relevant information
and determined that an unsafe condition is likely to exist or develop
on other products of the same type design.
Related Service Information
Agusta issued Bollettino Tecnico (BT) No. 109-135 for Model A109C
helicopters, No. 109EP-125 for Model A109E helicopters, No. 109K-55 for
Model A109K2 helicopters, and No. 119-052 for Model A119 helicopters.
All of the BTs are dated December 19, 2012. The BTs specify to perform
a visual inspection of bolt, P/N 109-8131-09-1, in accordance with the
maintenance manual applicable to the model helicopter for condition,
corrosion, and nicks. The BTs specify replacement of the bolt if there
is any damage, even if minor, or if there is missing cadmium plating in
the central part of the bolt. The BTs state that if a crack is not
revealed from the visual inspection, then to perform a liquid penetrant
inspection. The BTs further specify repeating the visual inspection of
the bolts at intervals specific to the model helicopter. The BTs state
the results of the inspections must be communicated to AgustaWestland.
Proposed AD Requirements
This proposed AD would require a visual inspection of each bolt, P/
N 109-8131-09-1, for a crack, corrosion, a nick, other damage, or
missing cadmium plating in the central part of the bolt. For bolts with
less than 400 hours time-in-service (TIS), the inspection would be
required before exceeding 500 hours TIS. For bolts with 400 or more
hours TIS, the inspection would be required within 100 hours TIS or 2
months, whichever occurs first. If a crack is not detected by the
visual inspection, this proposed AD would require a liquid penetrant
inspection of the bolts in accordance with Annex A of the
manufacturer's service information. Thereafter, this proposed AD would
require repeating the visual inspection. For Model A109C helicopters,
the inspections would be required at intervals not to exceed 300
additional hours TIS or 6 months, whichever occurs first. For Model
A109E, A109K2, and A119 helicopters, the inspections would be required
at intervals not to exceed 200 additional hours TIS or 6 months,
whichever occurs first. If there is a crack, corrosion, damage, or
missing cadmium plating in the central part of the bolt, this proposed
AD would require replacing the bolt with an airworthy bolt before
further flight. This proposed AD would also prohibit installing any
bolt that has accumulated more than 400 hours TIS on any helicopter
unless it has passed the visual and liquid penetrant inspections
proposed in this AD.
Interim Action
We consider this proposed AD to be an interim action. If final
action is later identified, we might consider additional rulemaking.
Costs of Compliance
We estimate that this proposed AD would affect 132 helicopters of
U. S. Registry. We estimate that operators may incur the following
costs in order to comply with this AD. We estimate it would take 2
work-hours to perform the initial visual and liquid penetrant
inspections and 1 work-hour to perform each recurring visual inspection
at an average labor cost of $85 per work-hour. Based on these figures,
it would cost about $170 to perform the initial inspections and about
$85 to perform each recurring visual inspection. A replacement bolt
would cost approximately $1,067; no additional labor cost would be
expected for replacement.
[[Page 69597]]
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 proposed 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, 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 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 proposed 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.
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. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
AgustaWestland S.p.A. (Type Certificate formerly held by Agusta
S.p.A) (Agusta) Helicopters: Docket No. FAA-2013-0943; Directorate
Identifier 2013-SW-001-AD.
(a) Applicability
This AD applies to Agusta Model A109C, A109E, A109K2, and A119
helicopters with a tail rotor blade retaining bolt (bolt), part
number 109-8131-09-1, installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a bolt. This
condition could result in failure of a bolt, release of a tail rotor
blade, and subsequent loss of control of the helicopter.
(c) Comments Due Date
We must receive comments by January 21, 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
For each bolt with less than 400 hours time-in-service (TIS),
before exceeding 500 hours TIS on the bolt, and for each bolt with
400 or more hours TIS, before accumulating an additional 100 hours
TIS or 2 months on the bolt, whichever occurs first:
(1) Visually inspect each bolt for a crack, damage, corrosion, a
nick, or missing cadmium plating in the central part of the bolt.
(i) If there is a crack, corrosion, a nick, any other damage, or
missing cadmium plating in the central part of the bolt, before
further flight, replace the bolt with an airworthy bolt.
(ii) If there is not a crack as a result of the initial visual
inspection as required by paragraph (e)(1) of this AD, liquid-
penetrant inspect the bolt in accordance with Annex A of Agusta
Bollettino Tecnico No. 109-135 for Model A109C helicopters, No.
109EP-125 for Model A109E helicopters, No. 109K-55 for Model A109K2
helicopters, or No. 119-052 for Model A119 helicopters, all dated
December 19, 2012, as applicable to your model helicopter. If there
is a crack, before further flight, replace the bolt with an
airworthy bolt.
(2) Thereafter, for Agusta Model A109C helicopters, repeat the
required actions of paragraph (e)(1) of this AD at intervals not to
exceed 300 additional hours TIS or 6 months, whichever occurs first.
For Agusta Model A109E, A109K2, and A119 helicopters, repeat the
required actions of paragraph (e)(1) of this AD at intervals not to
exceed 200 additional hours TIS or 6 months, whichever occurs first.
(3) Do not install a bolt that has accumulated more than 400
hours TIS on any helicopter unless it has passed the required
actions of paragraph (e)(1) of 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: Robert Grant, Aviation Safety
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort
Worth, Texas 76137; 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. 2013-0009, dated January 11, 2013. You may view
the EASA AD in the AD Docket on the Internet at http://www.regulations.gov.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor.
Issued in Fort Worth, Texas, on October 30, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-27634 Filed 11-19-13; 8:45 am]
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