Airworthiness Directives; Eurocopter France Helicopters, 5247-5249 [2014-01461]
Download as PDF
<![CDATA[
5247
Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations
(2) Step #2—Convert each gross notional
by its derivative adjustment factor to produce
an adjusted gross notional. The derivative
adjustment factor approximates the price
sensitivity for each of the product groups in
order to weight the notional amount by
sensitivity before weighting for maturity.
(i) For cap and floor options, the derivative
adjustment factor is 33 percent. For example,
an interest rate cap with a $1 million
notional amount has an adjusted gross
notional of $330,000 ($1,000,000 × 0.33 +
$330,000).
(ii) For interest rate swaps and Treasury
futures, the derivative adjustment factor is
100 percent. For example, an interest rate
swap with a $1 million notional amount has
an adjusted gross notional of $1,000,000
($1,000,000 × 1.00 = $1,000,000).
(iii) The total adjusted notional for all
derivatives positions is the sum of (i) and (ii)
above.
(3) Step #3—Produce the weighted average
remaining time to maturity (WARM) for all
derivatives positions. (i) For interest rate
caps, interest rate floors, and interest rate
swaps, the remaining maturity is the time left
between the reporting date and the
contracted maturity date, expressed in years
(round up to two decimals);
(ii) For Treasury futures, the remaining
maturity is the underlying deliverable
Treasury note’s maximum maturity (e.g., a
five-year Treasury note future has a five-year
remaining maturity); and
(iii) Determine the WARM using the
adjusted gross notional, as set forth in
subsection (2) of this section, and the
remaining time to maturity as defined for
each product group above in paragraphs
(b)(3)(i) and (ii) of this appendix.
(4) Step #4—Produce the WARMN by
converting the WARM to a percentage and
then multiplying the percentage by the total
adjusted gross notional. (i) Divide the
WARM, as calculated in paragraph (b)(3) of
this appendix, by ten to convert it to a
percentage (e.g., 7.75 WARMN is translated
to 77.5 percent); and
(ii) Multiply the WARM converted to a
percentage, as described in paragraph (c)(4)(i)
of this appendix, by total adjusted gross
notional, described in paragraph (c)(2) of this
appendix.
(5) Compare WARMN calculation to the
WARNM limit for compliance. The total in
step four (4) must be less than the limit in
paragraph (a)(1)(ii) or (a)(2)(ii) of this
appendix, as applicable.
(6) Example calculations for compliance
with this subpart: WARMN. The table below
provides an illustrative example of the
WARMN limit calculations for a sample
Federal credit union that has entry level
authority. The sample Federal credit union
has a net worth of $100 million and total
assets of $1 billion; its notional limit
authority is $65 million (65 percent of net
worth).
TABLE 4—EXAMPLE WARMN LIMIT CALCULATION
Options
Gross Notional (Step #1) .................................................................
Adjustment Factor ............................................................................
Adjusted Notional (Step #2) ............................................................
Weighted Average Remaining Maturity (WARM) (Step #3) ............
Swaps
$50,000,000
100%
$50,000,000
8.50
Total
$5,000,000
100%
$5,000,000
5.00
$155,000,000
............................
$88,000,000
7.74
Weighted Average Remaining Maturity Notional (WARMN) (Step #4):
Notional Limit Authority (65% of net
worth)
Under/(Over) Notional Limit Authority
1 (77.4%
$100,000,000
33%
$33,000,000
7.00
Futures
1 $68,100,000
$65,000,000
($3,100,000)
of Step #3.)
PART 715—SUPERVISORY
COMMITTEE AUDITS AND
VERIFICATIONS
PART 741—REQUIREMENTS FOR
INSURANCE
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
9. The authority citation for part 741
is revised to read as follows:
14 CFR Part 39
Authority: 12 U.S.C. 1757, 1766(a), 1781–
1790, and 1790d; 31 U.S.C. 3717.
[Docket No. FAA–2013–0501; Directorate
Identifier 2011–SW–036–AD; Amendment
39–17732; AD 2014–02–04]
10. Revise § 741.219 to read as
follows:
RIN 2120–AA64
§ 741.219
Airworthiness Directives; Eurocopter
France Helicopters
■
7. The authority citation for part 715
continues to read as follows:
■
Authority: 12 U.S.C. 1757, 1766(a), and
1781–1790; 31 U.S.C. 3717.
■
8. In § 715.5, revise paragraph (a) to
read as follows:
■
emcdonald on DSK67QTVN1PROD with RULES
§ 715.5
Audit of Federal Credit Unions.
(a) Total assets of $500 million or
greater. To fulfill its Supervisory
Committee audit responsibility, a
Federal credit union having total assets
of $500 million or greater, except as
provided in § 703.106(b)(3) of this
chapter, must obtain an annual audit of
its financial statements performed in
accordance with Generally Accepted
Auditing Standards by an independent
person who is licensed to do so by the
State or jurisdiction in which the credit
union is principally located.
*
*
*
*
*
VerDate Mar<15>2010
17:58 Jan 30, 2014
Jkt 232001
Investment requirements.
(a) Any credit union which is insured
pursuant to Title II of the Act must
adhere to the requirements stated in part
703 of this chapter concerning
transacting business with corporate
credit unions.
(b) Any credit union which is insured
pursuant to Title II of the Act must
notify the applicable NCUA Regional
Director or the Director of the Office of
National Examinations and Supervision
in writing at least 30 days before it
begins engaging in derivatives.
[FR Doc. 2014–01703 Filed 1–30–14; 8:45 am]
BILLING CODE 7535–01–P
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model
EC 155B and EC155B1 helicopters. This
AD requires repetitively inspecting the
lower and upper front and rear fittings
(fittings) that attach the upper fin to the
fenestron for a crack and, if there is a
crack, removing all four fittings from
service. This AD also requires, within a
specified time, removing all fittings
from service, and the fittings would not
be eligible to be installed on any
SUMMARY:
E:\FR\FM\31JAR1.SGM
31JAR1
5248
Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations
helicopter. This AD was prompted by
the loss of an upper fin in flight. The
actions of this AD 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: This AD is effective March 7,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of March 7, 2014.
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.
emcdonald on DSK67QTVN1PROD with RULES
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 European
Aviation Safety Agency (EASA) 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 June 11, 2013, at 78 FR 34960, 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
Model EC 155B and EC155B1
helicopters. The NPRM proposed
inspecting certain part-numbered
fittings for a crack and, if there is a
crack, removing the fittings from service
before further flight. Also, the NPRM
proposed removing certain partnumbered fittings from service within
180 hours time-in-service (TIS) and
prohibiting the fittings from being
VerDate Mar<15>2010
17:58 Jan 30, 2014
Jkt 232001
eligible for installation on any
helicopter. The proposed requirements
were intended to detect a crack in the
fittings to prevent loss of the upper fin
and subsequent loss of control of the
helicopter.
The NPRM was prompted by AD No.
2011–0108, dated June 7, 2011, issued
by EASA, which is the Technical Agent
for the Member States of the European
Union, 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
developed modification (MOD) 0754B40
to increase the strength of the fuselagefin 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.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (78 FR 34960, June 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.
Differences Between this AD and the
EASA AD
This AD does 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 requires removing the affected
fittings from service within the
equivalent 180 hours TIS.
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
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.
Costs of Compliance
We estimate that this AD will affect 9
helicopters of U.S. Registry. We estimate
that operators will incur the following
costs in order to comply with this AD
based on an average labor rate of $85 per
work hour. It will take 1 work hour to
inspect the fittings and about 3
inspections before replacement. It will
take 8 work hours to replace the fittings,
and required parts will cost $3,311.
Based on these figures, the total cost
will 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
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;
E:\FR\FM\31JAR1.SGM
31JAR1
Federal Register / Vol. 79, No. 21 / Friday, January 31, 2014 / Rules and Regulations
(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:
(f) 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 initial inspection specified in paragraph
(e)(1) of this AD.
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):
■
2014–02–04 Eurocopter France
Helicopters: Amendment 39–17732; 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.
emcdonald on DSK67QTVN1PROD with RULES
(c) Effective Date
This AD becomes effective March 7, 2014.
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(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 (item c) and rear (item d)
VerDate Mar<15>2010
17:58 Jan 30, 2014
Jkt 232001
upper fitting and each front (item e) and rear
(item f) lower fitting for a crack as depicted
in Detail A of 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.
(g) Special flight permits
Special flight permits will not be issued.
(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
(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
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.
(2) The subject of this AD is addressed in
European Aviation Safety Agency AD No.
2011–0108, dated June 7, 2011, which can be
found in Docket No. FAA–2013–0501 on the
Internet at https://www.regulations.gov.
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
5249
(j) Subject
Joint Aircraft Service Component (JASC)
Code: 5530 Vertical Stabilizer Structure.
(k) 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 Emergency Alert Service
Bulletin No. 05A017, Revision 2, dated
December 9, 2010.
(ii) Reserved.
(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/ibrlocations.html.
Issued in Fort Worth, Texas, on January 16,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2014–01461 Filed 1–30–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0525; Directorate
Identifier 2011–SW–063–AD; Amendment
39–17730; AD 2014–02–02]
RIN 2120–AA64
Airworthiness Directives; Bell
Helicopter Textron Canada Limited
(Bell) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Bell
Model 206L, L–1, L–3, and L–4
helicopters. This AD requires measuring
each main rotor (M/R) blade spar space
to determine whether it is oversized and
reidentifying the M/R blade and
SUMMARY:
E:\FR\FM\31JAR1.SGM
31JAR1
]]>Agencies
[Federal Register Volume 79, Number 21 (Friday, January 31, 2014)]
[Rules and Regulations]
[Pages 5247-5249]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-01461]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0501; Directorate Identifier 2011-SW-036-AD;
Amendment 39-17732; AD 2014-02-04]
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 EC 155B and EC155B1 helicopters.
This AD requires repetitively inspecting the lower and upper front and
rear fittings (fittings) that attach the upper fin to the fenestron for
a crack and, if there is a crack, removing all four fittings from
service. This AD also requires, within a specified time, removing all
fittings from service, and the fittings would not be eligible to be
installed on any
[[Page 5248]]
helicopter. This AD was prompted by the loss of an upper fin in flight.
The actions of this AD 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: This AD is effective March 7, 2014.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of March 7, 2014.
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 European Aviation Safety
Agency (EASA) 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 June 11, 2013, at 78 FR 34960, 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 Model EC 155B and
EC155B1 helicopters. The NPRM proposed inspecting certain part-numbered
fittings for a crack and, if there is a crack, removing the fittings
from service before further flight. Also, the NPRM proposed removing
certain part-numbered fittings from service within 180 hours time-in-
service (TIS) and prohibiting the fittings from being eligible for
installation on any helicopter. The proposed requirements were intended
to detect a crack in the fittings to prevent loss of the upper fin and
subsequent loss of control of the helicopter.
The NPRM was prompted by AD No. 2011-0108, dated June 7, 2011,
issued by EASA, which is the Technical Agent for the Member States of
the European Union, 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 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.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 34960,
June 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.
Differences Between this AD and the EASA AD
This AD does 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 requires
removing the affected fittings from service within the equivalent 180
hours TIS.
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.
Costs of Compliance
We estimate that this AD will affect 9 helicopters of U.S.
Registry. We estimate that operators will incur the following costs in
order to comply with this AD based on an average labor rate of $85 per
work hour. It will take 1 work hour to inspect the fittings and about 3
inspections before replacement. It will take 8 work hours to replace
the fittings, and required parts will cost $3,311. Based on these
figures, the total cost will 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 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;
[[Page 5249]]
(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):
2014-02-04 Eurocopter France Helicopters: Amendment 39-17732;
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) Effective Date
This AD becomes effective March 7, 2014.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(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 (item c) and rear (item d)
upper fitting and each front (item e) and rear (item f) lower
fitting for a crack as depicted in Detail A of 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.
(f) 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 initial inspection specified in paragraph (e)(1) of this AD.
(g) Special flight permits
Special flight permits will not be issued.
(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
(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 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.
(2) The subject of this AD is addressed in European Aviation
Safety Agency AD No. 2011-0108, dated June 7, 2011, which can be
found in Docket No. FAA-2013-0501 on the Internet at https://www.regulations.gov.
(j) Subject
Joint Aircraft Service Component (JASC) Code: 5530 Vertical
Stabilizer Structure.
(k) 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 Emergency Alert Service Bulletin No. 05A017,
Revision 2, dated December 9, 2010.
(ii) Reserved.
(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 January 16, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2014-01461 Filed 1-30-14; 8:45 am]
BILLING CODE 4910-13-P
