[Federal Register Volume 78, Number 112 (Tuesday, June 11, 2013)]
[Proposed Rules]
[Pages 34960-34962]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-13799]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0501; Directorate Identifier 2011-SW-036-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model 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
Eurocopter France (Eurocopter) Model EC 155B and EC155B1 helicopters.
This proposed AD would require repetitively inspecting the lower and
upper front and rear fittings (fittings) that attach the upper fin to
the fenestron for a crack. If there is a crack, this AD would require
removing all four fittings from service. This proposed AD would also
require, within a specified time, removing all fittings from service,
and the fittings would not be eligible to be installed on any
helicopter. This AD is prompted by the loss of an upper fin in flight.
The proposed actions are intended to detect a crack in the fittings to
prevent loss of the upper fin and subsequent loss of control of the
helicopter.
DATES: We must receive comments on this proposed AD by August 12, 2013.
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 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 economic
evaluation, any comments received, and other information. The street
address for the Docket Operations
[[Page 34961]]
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
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775;
or at http://www.eurocopter.com/techpub. 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, has issued EASA AD
No. 2011-0108, dated June 7, 2011, to correct an unsafe condition for
Eurocopter Model EC 155B and EC155B1 helicopters. EASA advises of an
in-flight loss of a fin on a Model EC155B1 helicopter. According to
EASA, a crack in the fittings attaching the upper fin to the fenestron
(tail rotor assembly) was discovered during an investigation. As a
result, EASA issued an emergency AD to mandate repetitive inspections
of the upper fin attachment fittings. EASA states that Eurocopter has
now developed modification (MOD) 0754B40 to increase the strength of
the fuselage-fin junction fittings by installing two reinforced single-
piece fittings to replace the affected fittings, which is terminating
action for the repetitive inspection requirements. EASA subsequently
issued AD No. 2011-0108, which superseded its emergency AD, to require
installation of MOD 0754B40 and to retain the repetitive inspection
requirements until the MOD is installed.
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, 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
Eurocopter has issued Emergency Alert Service Bulletin No. 05A017,
Revision 2, dated December 9, 2010, which specifies repetitively
inspecting the fittings for a crack and replacing each fitting if there
is a crack. Eurocopter has also issued Service Bulletin No. 53-029,
Revision 1, dated March 10, 2011, which specifies replacing the
fittings with reinforced fittings in accordance with MOD 0754B40.
Proposed AD Requirements
This proposed AD would require repetitively inspecting certain
part-numbered fittings for a crack, and if there is a crack, removing
the fittings from service before further flight. Also, within 180 hours
time-in-service (TIS), this AD proposes removing certain part-numbered
fittings from service. Replacing the fittings with airworthy fittings
not listed in the applicability paragraph of this proposed AD would be
terminating action for the requirements of this AD. The affected
fittings would not eligible to be installed on any helicopter.
Differences Between This Proposed AD and the EASA AD
This AD would not require replacing the upper fin to fenestron
fittings with reinforced fittings in accordance with MOD 0754B40 within
6 calendar months as stated in the EASA AD but rather would require
removing the affected fittings from service within the equivalent 180
hours TIS.
Costs of Compliance
We estimate that this proposed AD would affect 9 helicopters of
U.S. Registry. We estimate that operators would incur the following
costs in order to comply with this AD, based on an average labor rate
of $85 per work hour. It would take 1 work hour to inspect the fittings
and about 3 inspections would occur before replacement. It would take 8
work hours to replace the fittings and required parts would cost
$3,311. Based on these figures, the total cost would be $4,246 per
helicopter and $38,214 for the U.S. fleet.
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, I certify this proposed regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
[[Page 34962]]
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):
Eurocopter France: Docket No. FAA-2013-0501; Directorate Identifier
2011-SW-036-AD.
(a) Applicability
This AD applies to Model EC 155B and EC155B1 helicopters with
lower front fitting part number (P/N) 365A23-4240-01, upper front
fitting P/N 365A23-4242-01, lower rear fitting P/N 365A23-4241-01,
or upper rear fitting P/N 365A23-4243-01 (fittings) installed,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a fitting.
This condition could result in loss of the upper fin during flight
and subsequent loss of control of the helicopter.
(c) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time.
(d) Required Actions
(1) Within 15 hours time-in-service (TIS) and thereafter at
intervals not to exceed 55 hours TIS:
(i) Using an appropriate light source and a 10x or higher power
magnifying glass, inspect each front (c) and rear (d) upper fitting
and each front (e) and rear (f) lower fitting for a crack as
depicted in Figure 1 of Eurocopter Emergency Alert Service Bulletin
No. 05A017, Revision 2, dated December 9, 2010 (ASB). Inspect the
hatched area as depicted in Details B, C, and D of Figure 2 of the
ASB. A high-resolution (more than 2 million pixels) digital camera
or dye-penetrant inspection may be used to facilitate the crack
inspection.
(ii) If there is a crack in any fitting, before further flight,
remove all four fittings from service.
(2) Within 180 hours TIS, remove the fittings from service.
(3) Do not install lower front fitting P/N 365A23-4240-01, upper
front fitting P/N 365A23-4242-01, lower rear fitting P/N 365A23-
4241-01, and upper rear fitting P/N 365A23-4243-01 on any
helicopter.
(e) Credit for Actions Previously Completed
Inspections accomplished before the effective date of this AD in
accordance with the procedures specified in Eurocopter Emergency
Alert Service Bulletin No. 05A017, Revision 2, dated December 9,
2010; Revision 1, dated January 27, 2010; and Revision 0, dated
September 28, 2007, are considered acceptable for compliance with
the inspection specified in paragraph (d)(1) of this AD.
(f) Special flight permits
Special flight permits will not be issued.
(g) 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.
(h) Additional Information
(1) Eurocopter Service Bulletin No. 53-029, Revision 1, dated
March 10, 2011, which is not incorporated by reference, contains
additional information about the subject of this AD. For service
information identified in this AD, contact American Eurocopter
Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone
(972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.eurocopter.com/techpub. 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.
(2) The subject of this AD is addressed in European Aviation
Safety Agency AD No. 2011-0108, dated June 7, 2011.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 5530 Vertical
Stabilizer Structure.
Issued in Fort Worth, Texas, on June 3, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-13799 Filed 6-10-13; 8:45 am]
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