Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) (Airbus Helicopters) Helicopters, 32881-32883 [2014-13261]
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32881
Proposed Rules
Federal Register
Vol. 79, No. 110
Monday, June 9, 2014
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
[Docket No. FAA–2014–0364; Directorate
Identifier 2013–SW–041–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France) (Airbus Helicopters)
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2013–21–
01 that currently applies to Eurocopter
France Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3, AS350C,
AS350D, AS350D1, AS355E, AS355F,
AS355F1, AS355F2, AS355N, and
AS355NP helicopters. AD 2013–21–01
currently requires certain inspections of
each tail rotor pitch horn assembly
(pitch horn) for a crack and, if there is
a crack, before further flight, replacing
the pitch horn with an airworthy pitch
horn. AD 2013–21–01 also requires a
one-time visual inspection for pitch
horns above certain hours time-inservice (TIS). This NPRM would retain
the requirements of AD 2013–21–01 but
would require a repetitive visual
inspection for all pitch horns regardless
of hours TIS, which requires allowing
the public an opportunity to comment.
These proposed actions are intended to
detect a crack in the pitch horn to
prevent failure of the pitch horn, loss of
the anti-torque function, and subsequent
loss of control of the helicopter.
DATES: We must receive comments on
this proposed AD by August 8, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
ehiers on DSK2VPTVN1PROD with PROPOSALS
SUMMARY:
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15:07 Jun 06, 2014
• 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.
Jkt 232001
You may examine the AD docket on
the Internet at https://
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 Airbus
Helicopters, Inc., 2701 N. Forum Drive,
Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax
(972) 641–3775; or at https://
www.airbushelicopters.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
robert.grant@faa.gov.
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
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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
On October 7, 2013, we issued AD
2013–21–01, Amendment 39–17625 (78
FR 63853, October 25, 2013) for
Eurocopter France (now Airbus
Helicopters) Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3, AS350C,
AS350D, AS350D1, AS355E, AS355F,
AS355F1, AS355F2, AS355N, and
AS355NP helicopters. AD 2013–21–01
requires a one-time visual inspection of
each pitch horn with 135 or more hours
TIS for a crack and, if there is a crack,
before further flight, replacing the pitch
horn with an airworthy pitch horn. It
also requires a dye-penetrant inspection
of any pitch horn before it is installed.
AD 2013–21–01 was prompted by a
report of a crack in the yoke of a pitch
horn and is intended to detect a crack
in the pitch horn to prevent failure of
the pitch horn, loss of the anti-torque
function, and subsequent loss of control
of the helicopter.
AD 2013–21–01 was prompted by AD
No. 2013–0133, dated June 28, 2013,
issued by the European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Union. EASA issued AD No.
2013–0133 to correct an unsafe
condition for Model AS350B, AS350BA,
AS350BB, AS350B1, AS350B2,
AS350B3, AS350D, AS355E, AS355F,
AS355F1, AS355F2, AS355N, and
AS355NP helicopters. EASA advises of
an ongoing investigation of a crack in
the yoke of a pitch horn for which a
cause has not been determined. The
EASA AD requires repetitive visual
inspections of each pitch horn for a
crack and replacing the pitch horn with
a serviceable assembly if a crack is
found. EASA states that its AD is an
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Federal Register / Vol. 79, No. 110 / Monday, June 9, 2014 / Proposed Rules
interim action and further action may
follow.
This NPRM would retain the actions
in AD 2013–12–01 but would require
the visual inspection for all pitch horns
regardless of hours TIS. This NPRM
would also require repeating the visual
inspection every 165 hours TIS. This
NPRM would also change the
requirement for the dye penetration
inspection so that it only applies to
pitch horns that are not new. Also, since
we issued AD 2013–12–01, Eurocopter
France has changed its name to Airbus
Helicopters. This NPRM reflects that
change.
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 the
EASA 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 helicopters of
the same type design.
ehiers on DSK2VPTVN1PROD with PROPOSALS
Related Service Information
We reviewed a Eurocopter (now
Airbus Helicopters) Emergency Alert
Service Bulletin, Revision 1, dated June
25, 2013 (EASB), with four different
numbers. EASB No.05.00.74 is for
Model AS350B, B1, B2, B3, BA, and D;
the non-FAA type certificated Model
AS350BB; and the non-FAA type
certificated military Model AS350L1
helicopters. EASB No. 05.00.49 is for
non-FAA type certificated military
Model AS550A2, C2, C3, and U2
helicopters. EASB No. 05.00.65 is for
Model AS355E, F, F1, F2, N, and NP
helicopters. EASB No. 05.00.44 is for
non-FAA type certificated military
Model AS555AF, AN, SN, UF, and UN
helicopters. Airbus Helicopters has been
informed of a case of a crack on the yoke
of a pitch horn, which may lead to
failure of the pitch horn, resulting in
loss of the anti-torque function. The
EASB specifies a check for cracks on the
yokes of the two pitch horns and
specifies replacing any cracked pitch
horn. The EASB states that it may be
necessary to modify the log card of the
tail rotor blade assembly due to some of
the pitch horn part numbers being
recorded incorrectly.
EASA classified this EASB as
mandatory and issued EASA AD No.
2013–0133, dated June 28, 2013, to
ensure the continued airworthiness of
these helicopters.
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Proposed AD Requirements
This proposed AD would require:
• For parts with 155 or less hours
TIS, before exceeding 165 hours TIS, or
for parts with more than 155 hours TIS,
within 10 hours TIS, visually inspecting
each pitch horn for a crack.
• Thereafter, at intervals not to
exceed 165 hours TIS, visually
inspecting each pitch horn for a crack.
• After each inspection, if there is a
crack, before further flight, replacing the
pitch horn with an airworthy pitch
horn.
• Before installing any pitch horn,
P/N 350A121368, with more than 0
hours TIS, dye penetrant inspecting it
for a crack.
Differences Between the Proposed AD
and the EASA AD
The EASA AD applies to Eurocopter
Model AS350BB that does not have an
FAA type certificate and therefore is not
a part of this proposed AD. The EASA
AD does not apply to Eurocopter Model
AS350C or AS350D1, but this proposed
AD would because those models have
an FAA type certificate and may have
the applicable pitch horn installed. The
proposed AD would require a dyepenetrant inspection before installing a
pitch horn; the EASA AD does not.
Interim Action
We consider this AD to be an interim
action. If final action is later identified,
we might consider further rulemaking
then.
Costs of Compliance
We estimate that this proposed AD
would affect 938 helicopters of U.S.
Registry. We estimate that operators
may incur the following costs in order
to comply with this proposed AD. Labor
costs are estimated at $85 per work
hour. We estimate .1 work hour to
visually inspect a pitch horn for a total
cost of $8.50 per helicopter or $7,973 for
the fleet, per inspection cycle. We
estimate 1 work hour to do a dyepenetrant inspection, for a total cost of
$85 per helicopter. We estimate 1 work
hour to replace a part, if necessary, and
a cost for required parts of $1,946, for
a total cost of $2,031 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,
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2013–21–01, Amendment 39–17625 (78
FR 63853, October 25, 2013), Docket No.
FAA–2013–0878, Directorate Identifier
■
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Federal Register / Vol. 79, No. 110 / Monday, June 9, 2014 / Proposed Rules
2013–SW–033–AD, and adding the
following new AD:
Airbus Helicopters (Previously Eurocopter
France Helicopters) (Airbus
Helicopters): Docket No. FAA–2014–
0364; Directorate Identifier 2013–SW–
041–AD.
(a) Applicability
This AD applies to Airbus Helicopters
Model AS350B, AS350BA, AS350B1,
AS350B2, AS350B3, AS350C, AS350D,
AS350D1, AS355E, AS355F, AS355F1,
AS355F2, AS355N, and AS355NP helicopters
with tail rotor hub pitch horn (pitch horn)
assembly, part number (P/N) 350A121368.01,
350A121368.02, 350A121368.03, or
350A121368.04, with a pitch horn, P/N
350A121368.XX, where XX stands for a twodigit dash number, installed, certificated in
any category. The pitch horn may be marked
with either the pitch horn assembly P/N or
pitch horn P/N.
(b) Unsafe Condition
This AD defines the unsafe condition a
crack in the yoke of a pitch horn. This
condition could result in failure of a pitch
horn, loss of the anti-torque function, and
subsequent loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2013–21–01,
Amendment 39–17625 (78 FR 63853, October
25, 2013).
(d) Comments Due Date
(h) 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 robert.grant@faa.gov.
(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.
(i) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD
No. 2013–0133, dated June 28, 2013. You
may view the EASA AD on the Internet at
https://www.regulations.gov in Docket No.
FAA–2014–0364.
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6400 Tail Rotor.
Issued in Fort Worth, Texas, on May 30,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–13261 Filed 6–6–14; 8:45 am]
BILLING CODE 4910–13–P
We must receive comments by August 8,
2014.
DEPARTMENT OF TRANSPORTATION
(e) 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.
ehiers on DSK2VPTVN1PROD with PROPOSALS
(f) Required Actions
(1) For parts with 155 or less hours timein-service (TIS), before exceeding 165 hours
TIS, or for parts with more than 155 hours
TIS, within 10 hours TIS, and thereafter at
intervals not to exceed 165 hours TIS,
visually inspect each pitch horn for a crack
in the areas shown in Figure 1 of Eurocopter
Emergency Alert Service Bulletin (EASB) No.
05.00.74 or No. 05.00.65, both Revision 1 and
both dated June 25, 2013, as appropriate for
your model helicopter.
(2) If there is a crack, before further flight,
replace the pitch horn with an airworthy
pitch horn.
(3) Do not install a pitch horn, P/N
350A121368 (any dash number), with more
than 0 hours TIS on any helicopter unless it
has passed a dye penetrant inspection for a
crack in the areas shown in Figure 1 of
Eurocopter EASB No. 05.00.74 or No.
05.00.65, both Revision 1 and both dated
June 25, 2013, as appropriate for your model
helicopter.
(g) Special Flight Permits
Special flight permits are prohibited.
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15:07 Jun 06, 2014
Jkt 232001
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2014–0271; Airspace
Docket No. 13–AWP–16]
RIN 2120–AA66
Proposed Modification and
Establishment of Area Navigation
(RNAV) Routes; Western United States
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
modify three RNAV Q-routes and
establish five Q-routes originating in
Oakland Air Route Traffic Control
Center’s (ARTCC) airspace. The routes
would promote operational efficiencies
for users and provide connectivity to
current and proposed RNAV en route
and terminal procedures.
DATES: Comments must be received on
or before July 24, 2014.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, M–
SUMMARY:
PO 00000
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32883
30, 1200 New Jersey Avenue SE., West
Building Ground Floor, Room W12–140,
Washington, DC 20590–0001; telephone:
(202) 366–9826. You must identify FAA
Docket No. FAA–2014–0271 and
Airspace Docket No. 13–AWP–16 at the
beginning of your comments. You may
also submit comments through the
Internet at https://www.regulations.gov.
Paul
Gallant, Airspace Policy and
Regulations Group, Office of Airspace
Services, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA–
2014–0271 and Airspace Docket No. 13–
AWP–16) and be submitted in triplicate
to the Docket Management Facility (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at https://
www.regulations.gov.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to FAA
Docket No. FAA–2014–0271 and
Airspace Docket No. 13–AWP–16.’’ The
postcard will be date/time stamped and
returned to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this action may
be changed in light of comments
received. All comments submitted will
be available for examination in the
public docket both before and after the
closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
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]]>Agencies
[Federal Register Volume 79, Number 110 (Monday, June 9, 2014)]
[Proposed Rules]
[Pages 32881-32883]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-13261]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 79, No. 110 / Monday, June 9, 2014 / Proposed
Rules
[[Page 32881]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0364; Directorate Identifier 2013-SW-041-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters (Previously
Eurocopter France) (Airbus Helicopters) Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede airworthiness directive (AD) 2013-21-
01 that currently applies to Eurocopter France Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F,
AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2013-21-01
currently requires certain inspections of each tail rotor pitch horn
assembly (pitch horn) for a crack and, if there is a crack, before
further flight, replacing the pitch horn with an airworthy pitch horn.
AD 2013-21-01 also requires a one-time visual inspection for pitch
horns above certain hours time-in-service (TIS). This NPRM would retain
the requirements of AD 2013-21-01 but would require a repetitive visual
inspection for all pitch horns regardless of hours TIS, which requires
allowing the public an opportunity to comment. These proposed actions
are intended to detect a crack in the pitch horn to prevent failure of
the pitch horn, loss of the anti-torque function, and subsequent loss
of control of the helicopter.
DATES: We must receive comments on this proposed AD by August 8, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://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 https://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
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052;
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at
https://www.airbushelicopters.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 robert.grant@faa.gov.
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
On October 7, 2013, we issued AD 2013-21-01, Amendment 39-17625 (78
FR 63853, October 25, 2013) for Eurocopter France (now Airbus
Helicopters) Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C,
AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP
helicopters. AD 2013-21-01 requires a one-time visual inspection of
each pitch horn with 135 or more hours TIS for a crack and, if there is
a crack, before further flight, replacing the pitch horn with an
airworthy pitch horn. It also requires a dye-penetrant inspection of
any pitch horn before it is installed. AD 2013-21-01 was prompted by a
report of a crack in the yoke of a pitch horn and is intended to detect
a crack in the pitch horn to prevent failure of the pitch horn, loss of
the anti-torque function, and subsequent loss of control of the
helicopter.
AD 2013-21-01 was prompted by AD No. 2013-0133, dated June 28,
2013, issued by the European Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Union. EASA
issued AD No. 2013-0133 to correct an unsafe condition for Model
AS350B, AS350BA, AS350BB, AS350B1, AS350B2, AS350B3, AS350D, AS355E,
AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. EASA advises
of an ongoing investigation of a crack in the yoke of a pitch horn for
which a cause has not been determined. The EASA AD requires repetitive
visual inspections of each pitch horn for a crack and replacing the
pitch horn with a serviceable assembly if a crack is found. EASA states
that its AD is an
[[Page 32882]]
interim action and further action may follow.
This NPRM would retain the actions in AD 2013-12-01 but would
require the visual inspection for all pitch horns regardless of hours
TIS. This NPRM would also require repeating the visual inspection every
165 hours TIS. This NPRM would also change the requirement for the dye
penetration inspection so that it only applies to pitch horns that are
not new. Also, since we issued AD 2013-12-01, Eurocopter France has
changed its name to Airbus Helicopters. This NPRM reflects that change.
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
the EASA 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 helicopters of the same type design.
Related Service Information
We reviewed a Eurocopter (now Airbus Helicopters) Emergency Alert
Service Bulletin, Revision 1, dated June 25, 2013 (EASB), with four
different numbers. EASB No.05.00.74 is for Model AS350B, B1, B2, B3,
BA, and D; the non-FAA type certificated Model AS350BB; and the non-FAA
type certificated military Model AS350L1 helicopters. EASB No. 05.00.49
is for non-FAA type certificated military Model AS550A2, C2, C3, and U2
helicopters. EASB No. 05.00.65 is for Model AS355E, F, F1, F2, N, and
NP helicopters. EASB No. 05.00.44 is for non-FAA type certificated
military Model AS555AF, AN, SN, UF, and UN helicopters. Airbus
Helicopters has been informed of a case of a crack on the yoke of a
pitch horn, which may lead to failure of the pitch horn, resulting in
loss of the anti-torque function. The EASB specifies a check for cracks
on the yokes of the two pitch horns and specifies replacing any cracked
pitch horn. The EASB states that it may be necessary to modify the log
card of the tail rotor blade assembly due to some of the pitch horn
part numbers being recorded incorrectly.
EASA classified this EASB as mandatory and issued EASA AD No. 2013-
0133, dated June 28, 2013, to ensure the continued airworthiness of
these helicopters.
Proposed AD Requirements
This proposed AD would require:
For parts with 155 or less hours TIS, before exceeding 165
hours TIS, or for parts with more than 155 hours TIS, within 10 hours
TIS, visually inspecting each pitch horn for a crack.
Thereafter, at intervals not to exceed 165 hours TIS,
visually inspecting each pitch horn for a crack.
After each inspection, if there is a crack, before further
flight, replacing the pitch horn with an airworthy pitch horn.
Before installing any pitch horn, P/N 350A121368, with
more than 0 hours TIS, dye penetrant inspecting it for a crack.
Differences Between the Proposed AD and the EASA AD
The EASA AD applies to Eurocopter Model AS350BB that does not have
an FAA type certificate and therefore is not a part of this proposed
AD. The EASA AD does not apply to Eurocopter Model AS350C or AS350D1,
but this proposed AD would because those models have an FAA type
certificate and may have the applicable pitch horn installed. The
proposed AD would require a dye-penetrant inspection before installing
a pitch horn; the EASA AD does not.
Interim Action
We consider this AD to be an interim action. If final action is
later identified, we might consider further rulemaking then.
Costs of Compliance
We estimate that this proposed AD would affect 938 helicopters of
U.S. Registry. We estimate that operators may incur the following costs
in order to comply with this proposed AD. Labor costs are estimated at
$85 per work hour. We estimate .1 work hour to visually inspect a pitch
horn for a total cost of $8.50 per helicopter or $7,973 for the fleet,
per inspection cycle. We estimate 1 work hour to do a dye-penetrant
inspection, for a total cost of $85 per helicopter. We estimate 1 work
hour to replace a part, if necessary, and a cost for required parts of
$1,946, for a total cost of $2,031 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]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2013-21-01, Amendment 39-17625 (78 FR 63853, October 25, 2013), Docket
No. FAA-2013-0878, Directorate Identifier
[[Page 32883]]
2013-SW-033-AD, and adding the following new AD:
Airbus Helicopters (Previously Eurocopter France Helicopters)
(Airbus Helicopters): Docket No. FAA-2014-0364; Directorate
Identifier 2013-SW-041-AD.
(a) Applicability
This AD applies to Airbus Helicopters Model AS350B, AS350BA,
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F,
AS355F1, AS355F2, AS355N, and AS355NP helicopters with tail rotor
hub pitch horn (pitch horn) assembly, part number (P/N)
350A121368.01, 350A121368.02, 350A121368.03, or 350A121368.04, with
a pitch horn, P/N 350A121368.XX, where XX stands for a two-digit
dash number, installed, certificated in any category. The pitch horn
may be marked with either the pitch horn assembly P/N or pitch horn
P/N.
(b) Unsafe Condition
This AD defines the unsafe condition a crack in the yoke of a
pitch horn. This condition could result in failure of a pitch horn,
loss of the anti-torque function, and subsequent loss of control of
the helicopter.
(c) Affected ADs
This AD supersedes AD 2013-21-01, Amendment 39-17625 (78 FR
63853, October 25, 2013).
(d) Comments Due Date
We must receive comments by August 8, 2014.
(e) 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.
(f) Required Actions
(1) For parts with 155 or less hours time-in-service (TIS),
before exceeding 165 hours TIS, or for parts with more than 155
hours TIS, within 10 hours TIS, and thereafter at intervals not to
exceed 165 hours TIS, visually inspect each pitch horn for a crack
in the areas shown in Figure 1 of Eurocopter Emergency Alert Service
Bulletin (EASB) No. 05.00.74 or No. 05.00.65, both Revision 1 and
both dated June 25, 2013, as appropriate for your model helicopter.
(2) If there is a crack, before further flight, replace the
pitch horn with an airworthy pitch horn.
(3) Do not install a pitch horn, P/N 350A121368 (any dash
number), with more than 0 hours TIS on any helicopter unless it has
passed a dye penetrant inspection for a crack in the areas shown in
Figure 1 of Eurocopter EASB No. 05.00.74 or No. 05.00.65, both
Revision 1 and both dated June 25, 2013, as appropriate for your
model helicopter.
(g) Special Flight Permits
Special flight permits are prohibited.
(h) 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
robert.grant@faa.gov.
(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.
(i) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (EASA) AD No. 2013-0133, dated June 28, 2013. You may view
the EASA AD on the Internet at https://www.regulations.gov in Docket
No. FAA-2014-0364.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 6400 Tail Rotor.
Issued in Fort Worth, Texas, on May 30, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-13261 Filed 6-6-14; 8:45 am]
BILLING CODE 4910-13-P
