Airworthiness Directives; Eurocopter France Helicopters, 57047-57049 [2013-22295]
Download as PDF
<![CDATA[
57047
Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
TABLE XII—INTERIOR CONTAINER DEFECTS
Categories
Defects
Major
De-tinning in metal container materially affecting usability .....................................................................................
De-tinning in metal container not materially affecting usability ...............................................................................
Black spots in metal container ................................................................................................................................
Enamel missing (when required) in metal container ...............................................................................................
Enamel breakdown in metal container material affecting usability .........................................................................
Enamel breakdown in metal container material not affecting usability ...................................................................
Other defect(s) of the interior of the container (metal, plastic, paper, rigid, etc.) e.g., interior damage, tear,
delamination, missing layer, off-odor, interior blisters, etc. that materially affects usability ...............................
Defect(s) of the interior of the container (metal, plastic, paper, rigid, etc.) e.g., interior damage, tear,
delamination, missing layer, off-odor, interior blisters, etc. that materially affects appearance but not usability
Minor
101
........................
........................
102
103
........................
........................
201
202
........................
........................
203
104
........................
........................
204
TABLE XIII—ACCEPTANCE NUMBERS FOR INTERNAL CONTAINER DEFECTS
Major
Interior Defects
Sample Size (n = number of containers)
Total
Interior Defects
Ac
n—13
n—21
n—29
n—38
n—48
n—60
...............................................................................................................
...............................................................................................................
...............................................................................................................
...............................................................................................................
...............................................................................................................
...............................................................................................................
Dated: September 11, 2013.
Rex A. Barnes,
Associate Administrator, Agricultural
Marketing Service.
[FR Doc. 2013–22574 Filed 9–16–13; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0119; Directorate
Identifier 2011–SW–034–AD; Amendment
39–17541; AD 2013–16–03]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Helicopters
We are adopting a new
airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model
AS350 and AS355 helicopters, to
require inspecting for a crack in the
control lever attachment yokes, and if
needed, replacing the tail rotor gearbox
(TGB). This AD is prompted by
improper casting of TGB casing
assemblies, which may lead to cracking.
A crack in the control lever attachment
yokes could cause a loss of tail rotor
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
16:48 Sep 16, 2013
0
1
1
2
2
2
pitch control, and consequently, loss of
control of the helicopter.
DATES: This AD is effective October 22,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of October 22, 2013.
ADDRESSES: 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 https://
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.
Examining the AD Docket
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
VerDate Mar<15>2010
Re
Jkt 229001
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 AD, the foreign
authority’s AD, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations Office, M–30, West Building
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
Ac
1
2
2
3
3
3
Re
2
3
4
5
6
7
3
4
5
6
7
8
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
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:
Discussion
On February 11, 2013, at 78 FR 9634,
the Federal Register published our
notice of proposed rulemaking (NPRM),
which proposed to amend 14 CFR part
39 to include an AD that would apply
to Eurocopter Model AS350 and AS355
helicopters. The NPRM proposed to
require inspecting for a crack in the
control lever attachment yokes, and if
needed, replacing the TGB. The
proposed requirements were intended to
prevent a crack in the control lever
attachment yokes, which could cause a
loss of tail rotor pitch control, and
consequently, loss of control of the
helicopter.
The NPRM was prompted by AD No.
2011–0104, dated May 27, 2011, issued
by the European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, to correct an unsafe condition
for the Eurocopter Model AS 350 and
AS 355 helicopters. EASA advises that
cracks were found on some TGB casing
E:\FR\FM\17SER1.SGM
17SER1
57048
Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
assemblies when a dye-penetrant
inspection was performed after the
machining of the control lever
attachment yokes. The inspection
followed the repair of the manufacturing
mold. EASA reports that cracks in the
TGB casing assemblies, if not detected
and corrected, could lead to a crack on
the control lever attachment yokes,
which could cause the loss of tail rotor
pitch control and subsequent loss of
control of the helicopter.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(78 FR 9634, February 11, 2013).
mstockstill on DSK4VPTVN1PROD with RULES
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 issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed except the reference to the
Aerospace Material Specification 2647
or equivalent has been removed and we
are now incorporating by reference
procedures for the Fluorescent
Penetrant Inspection. These changes are
consistent with the intent of the
proposals in the NPRM (78 FR 9634,
February 11, 2013) and will not increase
the economic burden on any operator
nor increase the scope of the AD.
Differences Between This AD and the
EASA AD
We require inspecting for a crack in
the attachment yokes of the TGB casing
assemblies within 100 hours time-inservice (TIS). EASA requires that the
inspection be conducted within 26
months or 660 flight hours if the TGB
casing assemblies have less than 550
flight hours and within 110 flight hours
or 13 months if the TGB casing
assemblies have 550 or more flight
hours. We do not include the Model
AS350BB helicopter because it is not
type certificated in the United States,
but we do include models AS350C and
AS350D1.
Related Service Information
Eurocopter issued Alert Service
Bulletin (ASB) No. AS350–65.00.46 for
Model AS350 helicopters and ASB
VerDate Mar<15>2010
16:48 Sep 16, 2013
Jkt 229001
AS355–65.00.22 for AS355 helicopters.
Both ASBs are Revision 0 and dated
May 18, 2011. The ASBs call for nondestructive inspections, such as a dyepenetrant inspection, to check for cracks
in the attachment yokes of the TGB
casing assemblies. If there is a crack, the
ASBs call for replacing the TGB with an
airworthy TGB and returning the
replaced TGB to Eurocopter.
Costs of Compliance
We estimate that this AD affects 693
helicopters of U.S. Registry and that
labor costs average $85 per work-hour.
We estimate that it takes two workhours to inspect TGB casing assemblies
for a cost of $170 per helicopter, and
$117,810 for the U.S. fleet. No parts are
needed. Replacing the TGB requires five
work hours for a labor cost of $425.
Parts cost $37,825 for a total cost of
$38,250 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
helicopters identified in this rulemaking
action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will 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 that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
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
PO 00000
Frm 00016
Fmt 4700
Sfmt 4700
(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 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 adding
the following new airworthiness
directive (AD):
■
2013–16–03 EUROCOPTER FRANCE
HELICOPTERS (EUROCOPTER):
Amendment 39–17541; Docket No.
FAA–2013–0119; Directorate Identifier
2011–SW–034–AD.
(a) Applicability
This AD applies to Eurocopter AS350C, D,
D1, B, BA, B1, B2, and B3; and AS355E, F,
F1, F2, N, and NP helicopters, with a tailrotor
gearbox (TGB) casing assembly, part number
(P/N) 350A33–1090–02 and serial number (S/
N) MA47577, MA47585, MA47587 through
MA47593, MA47597 through MA47600,
MA47602, MA47604, MA47606, MA47610,
MA47613, MA47615, MA47617, MA47619
through MA47624, MA47626, MA47628, or
MA47631 installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the control lever attachment yoke of
the TGB casing assembly, which could result
in loss of tail rotor pitch control and loss of
helicopter control.
(c) Effective Date
This AD becomes effective October 22,
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:
(1) Remove the control lever, as depicted
in Figure 1, item (b), of Eurocopter Alert
Service Bulletin (ASB) No. AS350–65.00.46
E:\FR\FM\17SER1.SGM
17SER1
Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations
or No. AS355–65.00.22, both Revision 0 and
both dated May 18, 2011, as applicable for
your model helicopter.
(2) Strip the paint from the TGB control
lever attachment yokes, as depicted in Figure
2, item (z), of the ASB No. AS350–65.00.46
or No. AS355–65.00.22, as applicable to your
model helicopter.
(3) Perform a Fluorescent Penetrant
Inspection (FPI) in accordance with
paragraph 3.B.2 of ASB No. AS350–65.00.46
or No. AS355–65.00.22, as applicable to your
model helicopter, on the TGB control lever
attachment yokes for a crack. You are only
required to follow the actions defined in this
ASB paragraph pertaining to the FPI.
(4) If a crack exists, before further flight,
replace the TGB with an airworthy TGB.
(5) If there is no crack, clean the inspected
area and apply chemical conversion coating
(Alodine 1200 or equivalent), Epoxy primer,
and top coat paint.
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Fort Worth, Texas, on July 26,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–22295 Filed 9–16–13; 8:45 am]
BILLING CODE 4910–13–P
(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–
5328; 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.
DEPARTMENT OF TRANSPORTATION
(g) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency AD No.
2011–0104, dated May 27, 2011. You may
view the EASA AD at https://
www.regulations.gov by searching for and
locating it in Docket No. FAA–2013–0119.
SUMMARY:
mstockstill on DSK4VPTVN1PROD with RULES
(h) Subject
Joint Aircraft Service Component (JASC)
Code: 6520, Tail Rotor Gearbox.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No.
AS350–65.00.46, Revision 0, dated May 18,
2011.
(ii) Eurocopter Alert Service Bulletin No.
AS355–65.00.22, Revision 0, May 18, 2011.
(3) For Eurocopter 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 https://www.eurocopter.com/
techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
VerDate Mar<15>2010
16:48 Sep 16, 2013
Jkt 229001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0301; Directorate
Identifier 2013–NM–025–AD; Amendment
39–17575; AD 2013–18–02]
RIN 2120–AA64
Airworthiness Directives; the Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 767–200,
–300, –300F, and –400ER series
airplanes. This AD was prompted by
reports of cracked and corroded nuts on
an outboard flap support rib. This AD
requires, for certain airplanes, repetitive
inspections of the cap seal for damaged
sealant on nuts common to certain
outboard flap support ribs, and related
investigative and corrective actions if
necessary. For certain other airplanes,
this AD also requires repetitive
inspections of the cap seal for damaged
sealant on nuts common to certain
outboard flap support ribs, related
investigative and corrective actions if
necessary, and if necessary, a detailed
inspection to determine the nut type
installed in the outboard flap support
rib and corrective actions. This AD also
provides terminating action for the
repetitive inspections under certain
conditions. We are issuing this AD to
detect and correct cracked and corroded
nuts and bolts and the installation of
incorrect nuts on certain outboard flap
support ribs, which could lead to
additional nut and bolt damage in the
joint, result in loss of an outboard flap,
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
57049
and adversely affect continued safe
flight and landing of the airplane.
DATES: This AD is effective October 22,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 22, 2013.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: 425–
917–6577; fax: 425–917–6590; email:
berhane.alazar@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM published in the Federal
Register on April 10, 2013 (78 FR
21276). The NPRM proposed to require,
for certain airplanes, repetitive
inspections of the cap seal for damaged
sealant on nuts common to certain
outboard flap support ribs, related
investigative and corrective actions if
necessary, and replacement of all
fasteners in the support ribs, which
terminates the repetitive inspections.
For certain other airplanes, the NPRM
proposed to require repetitive
E:\FR\FM\17SER1.SGM
17SER1
]]>Agencies
[Federal Register Volume 78, Number 180 (Tuesday, September 17, 2013)]
[Rules and Regulations]
[Pages 57047-57049]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-22295]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0119; Directorate Identifier 2011-SW-034-AD;
Amendment 39-17541; AD 2013-16-03]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model AS350 and AS355 helicopters, to
require inspecting for a crack in the control lever attachment yokes,
and if needed, replacing the tail rotor gearbox (TGB). This AD is
prompted by improper casting of TGB casing assemblies, which may lead
to cracking. A crack in the control lever attachment yokes could cause
a loss of tail rotor pitch control, and consequently, loss of control
of the helicopter.
DATES: This AD is effective October 22, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of October 22,
2013.
ADDRESSES: 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 https://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.
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 AD, the foreign authority's AD,
any incorporated-by-reference service information, the economic
evaluation, any comments received, and other information. The street
address for the Docket Operations Office (phone: 800-647-5527) is U.S.
Department of Transportation, Docket Operations Office, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
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:
Discussion
On February 11, 2013, at 78 FR 9634, the Federal Register published
our notice of proposed rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would apply to Eurocopter Model AS350
and AS355 helicopters. The NPRM proposed to require inspecting for a
crack in the control lever attachment yokes, and if needed, replacing
the TGB. The proposed requirements were intended to prevent a crack in
the control lever attachment yokes, which could cause a loss of tail
rotor pitch control, and consequently, loss of control of the
helicopter.
The NPRM was prompted by AD No. 2011-0104, dated May 27, 2011,
issued by the European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union, to correct
an unsafe condition for the Eurocopter Model AS 350 and AS 355
helicopters. EASA advises that cracks were found on some TGB casing
[[Page 57048]]
assemblies when a dye-penetrant inspection was performed after the
machining of the control lever attachment yokes. The inspection
followed the repair of the manufacturing mold. EASA reports that cracks
in the TGB casing assemblies, if not detected and corrected, could lead
to a crack on the control lever attachment yokes, which could cause the
loss of tail rotor pitch control and subsequent loss of control of the
helicopter.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (78 FR 9634, February
11, 2013).
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 issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed except the reference to the
Aerospace Material Specification 2647 or equivalent has been removed
and we are now incorporating by reference procedures for the
Fluorescent Penetrant Inspection. These changes are consistent with the
intent of the proposals in the NPRM (78 FR 9634, February 11, 2013) and
will not increase the economic burden on any operator nor increase the
scope of the AD.
Differences Between This AD and the EASA AD
We require inspecting for a crack in the attachment yokes of the
TGB casing assemblies within 100 hours time-in-service (TIS). EASA
requires that the inspection be conducted within 26 months or 660
flight hours if the TGB casing assemblies have less than 550 flight
hours and within 110 flight hours or 13 months if the TGB casing
assemblies have 550 or more flight hours. We do not include the Model
AS350BB helicopter because it is not type certificated in the United
States, but we do include models AS350C and AS350D1.
Related Service Information
Eurocopter issued Alert Service Bulletin (ASB) No. AS350-65.00.46
for Model AS350 helicopters and ASB AS355-65.00.22 for AS355
helicopters. Both ASBs are Revision 0 and dated May 18, 2011. The ASBs
call for non-destructive inspections, such as a dye-penetrant
inspection, to check for cracks in the attachment yokes of the TGB
casing assemblies. If there is a crack, the ASBs call for replacing the
TGB with an airworthy TGB and returning the replaced TGB to Eurocopter.
Costs of Compliance
We estimate that this AD affects 693 helicopters of U.S. Registry
and that labor costs average $85 per work-hour. We estimate that it
takes two work-hours to inspect TGB casing assemblies for a cost of
$170 per helicopter, and $117,810 for the U.S. fleet. No parts are
needed. Replacing the TGB requires five work hours for a labor cost of
$425. Parts cost $37,825 for a total cost of $38,250 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 helicopters identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will 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 that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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):
2013-16-03 EUROCOPTER FRANCE HELICOPTERS (EUROCOPTER): Amendment 39-
17541; Docket No. FAA-2013-0119; Directorate Identifier 2011-SW-034-
AD.
(a) Applicability
This AD applies to Eurocopter AS350C, D, D1, B, BA, B1, B2, and
B3; and AS355E, F, F1, F2, N, and NP helicopters, with a tailrotor
gearbox (TGB) casing assembly, part number (P/N) 350A33-1090-02 and
serial number (S/N) MA47577, MA47585, MA47587 through MA47593,
MA47597 through MA47600, MA47602, MA47604, MA47606, MA47610,
MA47613, MA47615, MA47617, MA47619 through MA47624, MA47626,
MA47628, or MA47631 installed, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the control
lever attachment yoke of the TGB casing assembly, which could result
in loss of tail rotor pitch control and loss of helicopter control.
(c) Effective Date
This AD becomes effective October 22, 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:
(1) Remove the control lever, as depicted in Figure 1, item (b),
of Eurocopter Alert Service Bulletin (ASB) No. AS350-65.00.46
[[Page 57049]]
or No. AS355-65.00.22, both Revision 0 and both dated May 18, 2011,
as applicable for your model helicopter.
(2) Strip the paint from the TGB control lever attachment yokes,
as depicted in Figure 2, item (z), of the ASB No. AS350-65.00.46 or
No. AS355-65.00.22, as applicable to your model helicopter.
(3) Perform a Fluorescent Penetrant Inspection (FPI) in
accordance with paragraph 3.B.2 of ASB No. AS350-65.00.46 or No.
AS355-65.00.22, as applicable to your model helicopter, on the TGB
control lever attachment yokes for a crack. You are only required to
follow the actions defined in this ASB paragraph pertaining to the
FPI.
(4) If a crack exists, before further flight, replace the TGB
with an airworthy TGB.
(5) If there is no crack, clean the inspected area and apply
chemical conversion coating (Alodine 1200 or equivalent), Epoxy
primer, and top coat paint.
(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 817-222-5328; 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.
(g) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency AD No. 2011-0104, dated May 27, 2011. You may view the EASA
AD at https://www.regulations.gov by searching for and locating it in
Docket No. FAA-2013-0119.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6520, Tail Rotor
Gearbox.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No. AS350-65.00.46,
Revision 0, dated May 18, 2011.
(ii) Eurocopter Alert Service Bulletin No. AS355-65.00.22,
Revision 0, May 18, 2011.
(3) For Eurocopter 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 https://www.eurocopter.com/techpub.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on July 26, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-22295 Filed 9-16-13; 8:45 am]
BILLING CODE 4910-13-P
