[Federal Register Volume 78, Number 77 (Monday, April 22, 2013)]
[Proposed Rules]
[Pages 23692-23694]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-09417]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0351; Directorate Identifier 2009-SW-049-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France 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 AS350B, BA, B1, B2, B3, and D, and
Model AS355E, F, F1, F2, and N helicopters with certain tail rotor (T/
R) blades. This proposed AD would require installing additional rivets
to secure each T/R blade trailing edge tab (tab), and inspecting for
evidence of debonding of the tab after the rivets are installed. This
proposed AD is prompted by reports of T/R blade tab debonding. The
actions specified by this proposed AD are intended to prevent loss of a
T/R blade tab, which could result in excessive vibration and loss of
control of the helicopter.
DATES: We must receive comments on this proposed AD by June 21, 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 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: Gary Roach, 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 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 Direction Generale de l'Aviation Civile (DGAC), which is the
aviation authority for France, has issued DGAC AD No. F-2004-178, dated
November 10, 2004, for the Eurocopter AS 350B, BA, BB, B1, B2, B3, and
D helicopters, fitted with certain T/R blades. DGAC has also issued AD
No. F-2004-176, dated November 10, 2004, for the Eurocopter Model AS
355E, F, F1, F2, and N helicopters with certain T/R blades. DGAC
advises of reports of T/R blade tab debonding, and that the loss of the
tab leads to a significant increase in the aircraft's vibration level.
As a result, the ADs mandate compliance with the manufacturer's service
information to install additional rivets on the tabs.
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, the European Aviation Safety
Agency, which is the Technical Agent for the Member States of the
European Union, has notified us of the unsafe condition described in
the DGAC AD. We are proposing this AD because we evaluated all known
relevant information and determined that an unsafe condition is likely
to
[[Page 23693]]
exist or develop on other products of the same type design.
Related Service Information
We reviewed Eurocopter Alert Service Bulletin (ASB) No. 64.00.05,
Revision 2, dated February 15, 2007, for Model AS350B, BA, BB, B1, B2,
B3, and D helicopters, and ASB No. 64.00.04, Revision 2, dated February
15, 2007, for Model AS355E, F, F1, F2, and N helicopters.
These ASBs specify, within 100 flying hours without exceeding three
months, installing additional rivets on T/R blade tabs and inspecting
each tab for debonding after the rivets have been installed. DGAC
classified these ASBs as mandatory and issued AD No. F-2004-176 and AD
No. F2004-178 to ensure the continued airworthiness of these
helicopters.
Proposed AD Requirements
This proposed AD would require installing additional rivets on each
T/R blade tab and inspecting the tab for debonding. If there is
debonding of the tab, this proposed AD would require replacing the tab
with an airworthy tab before further flight.
Differences Between This Proposed AD and the DGAC AD
This proposed AD does not include the Model AS350 BB because it
does not have an FAA-issued type certificate. This proposed AD requires
compliance within 100 hours TIS. The DGAC ADs require compliance within
100 flying hours ``without exceeding 3 months.''
Costs of Compliance
We estimate that this proposed AD affects 654 helicopters of U.S.
registry and that labor costs average $85 a work-hour. Based on these
estimates, we expect the following costs:
Installing rivets and inspecting for tab debonding would
take one hour for a labor cost of $85. Parts would cost $100 for a
total cost of $185 per helicopter. The cost for the U.S. fleet would
total $120,990.
Replacing the tab with an airworthy tab, if needed, would
take four hours for a total labor cost of $340. Parts would cost $100,
for a total cost of $440 per helicopter.
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;
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]
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2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Europcopter France (Eurocopter): Docket No. FAA-2013-0351;
Directorate Identifier 2009-SW-049-AD.
(a) Applicability
This AD applies to Eurocopter Model AS350B, BA, B1, B2, B3, D,
and AS355E, F, F1, F2, and N helicopters with a tail rotor (T/R)
blade, part number (P/N) 355A12-0040-00, 355A-12-0040-01, 355A12-
0040-02, 355A12-0040-03, 355A-12-0040-04, 355A12-0040-05, 355A-12-
0040-07, 355A-12.0040-08, or 355A12-0040-14, all serial numbers (S/
N); or P/N 355A12-0050-04, 355A12-0050-10, or 355A12-0050-12, with a
S/N 8400 through 9224, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as T/R blade trailing edge
tab (tab) debonding. This condition could result in excessive
vibration of the helicopter and loss of control of the helicopter.
(c) Comments Due Date
Comments are due June 21, 2013.
(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
Within 100 hours time-in-service, install additional rivets on
the trailing edge tab of each T/R blade, according to the following
procedures, referencing Figure 1 of Eurocopter Alert Service
Bulletin (ASB) No. 64.00.05, Revision 2, dated February 15, 2007, or
ASB No. 64.00.04, Revision 2, dated February 15, 2007, whichever is
applicable to your model helicopter:
(1) Lightly sand the area to be drilled, using No. 80 then No.
220 sandpaper.
(2) Locate and drill eight 2.5 mm-diameter holes (T): 4 holes
(T) 12 mm from the existing rivets (E) and on the centerline of the
existing rivets (E), then 4 holes (T) 24 mm from the existing rivets
(E) and on the centerline of the existing rivets (E).
(3) Deburr and clean the area around the drilled holes.
(4) Install 8 rivets (1) on tab (L). Any installation direction
of the rivets is permissible (pressure face or suction face of the
T/R blade).
(5) Inspect the tab for debonding.
(i) If there is no debonding, paint the area.
(ii) If there is debonding, replace the tab.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, Rotorcraft
Directorate, FAA, may approve AMOCs for this AD. Send your proposal
to: Gary Roach, 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 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
[[Page 23694]]
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 AD No. F-2004-176 and AD No. F-2004-178, both dated November
10, 2004.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6410, Tail rotor
blades.
Issued in Fort Worth, Texas, on April 11, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-09417 Filed 4-19-13; 8:45 am]
BILLING CODE 4910-13-P