Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 49575-49577 [2016-17719]
Download as PDF
<![CDATA[
Federal Register / Vol. 81, No. 145 / Thursday, July 28, 2016 / Proposed Rules
of the nose wheel well body structure for any
cracking, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2887, dated December 2, 2015;
except as required by paragraph (j)(2) of this
AD. Do all related investigative and
corrective actions before further flight.
Repeat the detailed inspection thereafter at
the applicable intervals specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2887, dated
December 2, 2015.
Lhorne on DSK30JT082PROD with PROPOSALS
(j) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
747–53A2887, dated December 2, 2015,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(2) If any crack is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 747–53A2887, dated
December 2, 2015, specifies to contact Boeing
for appropriate action, and specifies that
action as ‘‘RC’’ (Required for Compliance):
Before further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (j)(2)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
VerDate Sep<11>2014
14:42 Jul 27, 2016
Jkt 238001
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(l) Related Information
(1) For more information about this AD,
contact Nathan Weigand, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6428; fax: 425–917–6590; email:
Nathan.P.Weigand@faa.gov.
(2) 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 view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on July 21,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–17718 Filed 7–27–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6990; Directorate
Identifier 2016–NE–14–AD]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Turboshaft Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2,
1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2,
1K1, 1S, and 1S1 turboshaft engines.
This proposed AD was prompted by an
anomaly that occurred during the
grinding operation required by
modification TU376, which increases
the clearance between the rear curvic
coupling of the centrifugal impeller and
the fuel injection manifold. This
proposed AD would require removing
the centrifugal impeller and replacing
with a part eligible for installation. We
are proposing this AD to prevent failure
SUMMARY:
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
49575
of the centrifugal impeller, uncontained
centrifugal impeller release, damage to
the engine, and damage to the
helicopter.
DATES: We must receive comments on
this NPRM by September 26, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: 202–493–2251.
For service information identified in
this proposed AD, contact Turbomeca
S.A., 40220 Tarnos, France; phone: 33
(0)5 59 74 40 00; fax: 33 (0)5 59 74 45
15. You may view this service
information at the FAA, Engine &
Propeller Directorate, 1200 District
Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6990; 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
mandatory continuing airworthiness
information (MCAI), the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
in the ADDRESSES section. Comments
will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Philip Haberlen, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7770; fax: 781–238–7199;
email: philip.haberlen@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–6990; Directorate Identifier
2016–NE–14–AD’’ at the beginning of
your comments. We specifically invite
E:\FR\FM\28JYP1.SGM
28JYP1
49576
Federal Register / Vol. 81, No. 145 / Thursday, July 28, 2016 / Proposed Rules
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2016–
0090, dated May 10, 2016 (referred to
hereinafter as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
Turbomeca reported an anomaly that was
generated during the grinding operation
associated to the application of modification
TU376, which increases the clearance
between the rear curvic coupling of the
centrifugal impeller and the fuel injection
manifold.
This condition, if not corrected, could lead
to crack initiation and propagation in the
centrifugal impeller bore area, possibly
resulting in centrifugal impeller failure, with
consequent damage to, and reduced control
of, the helicopter. To address this potential
unsafe condition, the life of the affected
centrifugal impellers was reduced and
Turbomeca published Mandatory Service
Bulletin (MSB) 292 72 0848 to inform
operators about the life reduction and to
provide instructions for the replacement of
the affected centrifugal impellers.
For the reasons described above, this AD
requires replacement of each affected
centrifugal impeller before it exceeds the
applicable reduced life limit.
You may obtain further information
by examining the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6990.
Lhorne on DSK30JT082PROD with PROPOSALS
Related Service Information
Turbomeca S.A. has issued
Mandatory Service Bulletin (MSB) 292
72 0848, Version B, dated April 13,
2016. The MSB describes procedures for
reducing the life limit of the centrifugal
impellers affected by an anomaly that
occurred during the grinding operation
required by modification TU376. This
service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
VerDate Sep<11>2014
14:42 Jul 27, 2016
Jkt 238001
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of France, and is
approved for operation in the United
States. Pursuant to our bilateral
agreement with the European
Community, EASA has notified us of
the unsafe condition described in the
MCAI and service information
referenced above. We are proposing 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
products of the same type design. This
proposed AD would require removal of
the centrifugal impeller from service
before exceeding the reduced life limit
shown in Appendix 1 of EASA AD
2016–0090, dated May 10, 2016, and
replacement with a part eligible for
installation.
Costs of Compliance
We estimate that this proposed AD
affects 3 engines installed on helicopters
of U.S. registry. We also estimate that it
would take about 22 hours per engine to
comply with this proposed AD. The
average labor rate is $85 per hour.
Required parts cost about $96,518 per
engine. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $295,164.
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
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, 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.
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 adding
the following new airworthiness
directive (AD):
■
Turbomeca S.A.: Docket No. FAA–2016–
6990; Directorate Identifier 2016–NE–
14–AD.
(a) Comments Due Date
We must receive comments by September
26, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to certain Arriel 1, 1A,
1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1,
1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines,
with modification TU376 installed.
(d) Reason
This AD was prompted by an anomaly that
occurred during the grinding operation
required by modification TU376, which
increases the clearance between the rear
curvic coupling of the centrifugal impeller
and the fuel injection manifold. We are
issuing this AD to prevent failure of the
centrifugal impeller, uncontained centrifugal
impeller release, damage to the engine, and
damage to the helicopter.
E:\FR\FM\28JYP1.SGM
28JYP1
Federal Register / Vol. 81, No. 145 / Thursday, July 28, 2016 / Proposed Rules
(e) Actions and Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) Remove from service, any centrifugal
impeller listed in Table 1 to paragraph (e) of
this AD, before exceeding the applicable
cycles since new (CSN) and replace with a
49577
centrifugal impeller not listed in Table 1 to
paragraph (e) of this AD.
TABLE 1 TO PARAGRAPH (e)—CENTRIFUGAL IMPELLER CSNS
Part No.
0292254040
0292254040
0292254050
0292254050
0292254050
0292254050
0292254050
0292254050
0292254050
0292254050
0292254050
0292254050
0292254050
0292254050
729225293A
729225293A
729225293A
729225293A
729225293A
729225293A
729225293A
729225293A
729225293A
729225293A
729225293A
Serial No.
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
................................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
...............................................................................
(2) Reserved.
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request. You may email your
request to: ANE-AD-AMOC@faa.gov.
Lhorne on DSK30JT082PROD with PROPOSALS
(1) For more information about this AD,
contact Philip Haberlen, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7770; fax: 781–238–7199; email:
philip.haberlen@faa.gov.
(2) Refer to MCAI, European Aviation
Safety Agency AD 2016–0090, dated May 10,
2016, for more information. You may
examine the MCAI in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2016–6990.
(3) Turbomeca S.A. Mandatory Service
Bulletin (MSB) 292 72 0848, Version B, dated
April 13, 2016, can be obtained from
Turbomeca S.A., using the contact
information in paragraph (g)(4) of this
proposed AD.
(4) For service information identified in
this proposed AD, contact Turbomeca S.A.,
40220 Tarnos, France; phone: 33 (0)5 59 74
40 00; fax: 33 (0)5 59 74 45 15.
(5) You may view this service information
at the FAA, Engine & Propeller Directorate,
1200 District Avenue, Burlington, MA. For
14:42 Jul 27, 2016
Issued in Burlington, Massachusetts, on
July 21, 2016.
Colleen M. D’Alessandro,
Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 2016–17719 Filed 7–27–16; 8:45 am]
BILLING CODE 4910–13–P
(g) Related Information
VerDate Sep<11>2014
44 ................................................................................................
1762FT .......................................................................................
1676CAR ....................................................................................
5333OTT ....................................................................................
5017OTT ....................................................................................
1136CAR ....................................................................................
3655OTT ....................................................................................
1757CAR ....................................................................................
1738CAR ....................................................................................
1149CAR ....................................................................................
2677OTT ....................................................................................
3109OTT ....................................................................................
3496OTT ....................................................................................
2074CAR ....................................................................................
290CAR ......................................................................................
1227FT .......................................................................................
504FB .........................................................................................
2517OTT ....................................................................................
2165OTT ....................................................................................
2194FT .......................................................................................
1331OTT ....................................................................................
1301FT .......................................................................................
1567FT .......................................................................................
783FB .........................................................................................
98OTT ........................................................................................
information on the availability of this
material at the FAA, call 781–238–7125.
(f) Alternative Methods of Compliance
(AMOCs)
Jkt 238001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8180; Directorate
Identifier 2016–NM–083–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model CL–600–2C10
(Regional Jet Series 700, 701, & 702)
airplanes, Model CL–600–2D15
(Regional Jet Series 705) airplanes,
Model CL–600–2D24 (Regional Jet
SUMMARY:
PO 00000
Frm 00022
CSN
Fmt 4702
Sfmt 4702
5,129
11,476
6,281
5,495
5,491
8,734
4,600
7,913
10,640
12,273
11,145
10,662
5,562
7,423
6,326
8,139
4,600
9,732
6,163
11,461
12,513
7,262
6,305
8,307
9,492
Series 900) airplanes, and Model CL–
600–2E25 (Regional Jet Series 1000)
airplanes. This proposed AD was
prompted by a determination that the
protective polyurethane tapes applied to
the upper surfaces of the aluminum and
titanium floor structural members may
not be trimmed properly, and on some
places may overhang the profiles of the
floor structural parts. Subsequent tests
revealed that the overhanging pieces of
tapes that are not bonded to the
structure do not meet the flammability
requirements and may allow fire
propagation below the floor structure.
This proposed AD would require an
inspection of the polyurethane
protective tapes installed on the floor
structure for excess tape or incorrect
tape installation, and corrective actions
if necessary. We are proposing this AD
to detect and correct overhanging pieces
of protective polyurethane tapes, which
are not bonded to the structure and do
not meet the flammability requirements;
this condition may allow fire
propagation below the floor structure.
We must receive comments on
this proposed AD by September 12,
2016.
DATES:
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
ADDRESSES:
E:\FR\FM\28JYP1.SGM
28JYP1
]]>Agencies
[Federal Register Volume 81, Number 145 (Thursday, July 28, 2016)]
[Proposed Rules]
[Pages 49575-49577]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-17719]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6990; Directorate Identifier 2016-NE-14-AD]
RIN 2120-AA64
Airworthiness Directives; Turbomeca S.A. Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2,
1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This proposed AD
was prompted by an anomaly that occurred during the grinding operation
required by modification TU376, which increases the clearance between
the rear curvic coupling of the centrifugal impeller and the fuel
injection manifold. This proposed AD would require removing the
centrifugal impeller and replacing with a part eligible for
installation. We are proposing this AD to prevent failure of the
centrifugal impeller, uncontained centrifugal impeller release, damage
to the engine, and damage to the helicopter.
DATES: We must receive comments on this NPRM by September 26, 2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor,
Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: 202-493-2251.
For service information identified in this proposed AD, contact
Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax:
33 (0)5 59 74 45 15. You may view this service information at the FAA,
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA.
For information on the availability of this material at the FAA, call
781-238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6990; 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 mandatory continuing airworthiness
information (MCAI), the regulatory evaluation, any comments received,
and other information. The address for the Docket Office (phone: 800-
647-5527) is in the ADDRESSES section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Philip Haberlen, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200
District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781-
238-7199; email: philip.haberlen@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6990;
Directorate Identifier 2016-NE-14-AD'' at the beginning of your
comments. We specifically invite
[[Page 49576]]
comments on the overall regulatory, economic, environmental, and energy
aspects of this proposed AD. We will consider all comments received by
the closing date and may amend this proposed AD based on those
comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD 2016-0090, dated May 10, 2016 (referred to hereinafter as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
Turbomeca reported an anomaly that was generated during the
grinding operation associated to the application of modification
TU376, which increases the clearance between the rear curvic
coupling of the centrifugal impeller and the fuel injection
manifold.
This condition, if not corrected, could lead to crack initiation
and propagation in the centrifugal impeller bore area, possibly
resulting in centrifugal impeller failure, with consequent damage
to, and reduced control of, the helicopter. To address this
potential unsafe condition, the life of the affected centrifugal
impellers was reduced and Turbomeca published Mandatory Service
Bulletin (MSB) 292 72 0848 to inform operators about the life
reduction and to provide instructions for the replacement of the
affected centrifugal impellers.
For the reasons described above, this AD requires replacement of
each affected centrifugal impeller before it exceeds the applicable
reduced life limit.
You may obtain further information by examining the MCAI in the AD
docket on the Internet at https://www.regulations.gov by searching for
and locating Docket No. FAA-2016-6990.
Related Service Information
Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) 292 72
0848, Version B, dated April 13, 2016. The MSB describes procedures for
reducing the life limit of the centrifugal impellers affected by an
anomaly that occurred during the grinding operation required by
modification TU376. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of France,
and is approved for operation in the United States. Pursuant to our
bilateral agreement with the European Community, EASA has notified us
of the unsafe condition described in the MCAI and service information
referenced above. We are proposing 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 products of the same type
design. This proposed AD would require removal of the centrifugal
impeller from service before exceeding the reduced life limit shown in
Appendix 1 of EASA AD 2016-0090, dated May 10, 2016, and replacement
with a part eligible for installation.
Costs of Compliance
We estimate that this proposed AD affects 3 engines installed on
helicopters of U.S. registry. We also estimate that it would take about
22 hours per engine to comply with this proposed AD. The average labor
rate is $85 per hour. Required parts cost about $96,518 per engine.
Based on these figures, we estimate the cost of this proposed AD on
U.S. operators to be $295,164.
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 above, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Turbomeca S.A.: Docket No. FAA-2016-6990; Directorate Identifier
2016-NE-14-AD.
(a) Comments Due Date
We must receive comments by September 26, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to certain Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C,
1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines,
with modification TU376 installed.
(d) Reason
This AD was prompted by an anomaly that occurred during the
grinding operation required by modification TU376, which increases
the clearance between the rear curvic coupling of the centrifugal
impeller and the fuel injection manifold. We are issuing this AD to
prevent failure of the centrifugal impeller, uncontained centrifugal
impeller release, damage to the engine, and damage to the
helicopter.
[[Page 49577]]
(e) Actions and Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) Remove from service, any centrifugal impeller listed in
Table 1 to paragraph (e) of this AD, before exceeding the applicable
cycles since new (CSN) and replace with a centrifugal impeller not
listed in Table 1 to paragraph (e) of this AD.
Table 1 to Paragraph (e)--Centrifugal Impeller CSNs
------------------------------------------------------------------------
Part No. Serial No. CSN
------------------------------------------------------------------------
0292254040........................ 44.................. 5,129
0292254040........................ 1762FT.............. 11,476
0292254050........................ 1676CAR............. 6,281
0292254050........................ 5333OTT............. 5,495
0292254050........................ 5017OTT............. 5,491
0292254050........................ 1136CAR............. 8,734
0292254050........................ 3655OTT............. 4,600
0292254050........................ 1757CAR............. 7,913
0292254050........................ 1738CAR............. 10,640
0292254050........................ 1149CAR............. 12,273
0292254050........................ 2677OTT............. 11,145
0292254050........................ 3109OTT............. 10,662
0292254050........................ 3496OTT............. 5,562
0292254050........................ 2074CAR............. 7,423
729225293A........................ 290CAR.............. 6,326
729225293A........................ 1227FT.............. 8,139
729225293A........................ 504FB............... 4,600
729225293A........................ 2517OTT............. 9,732
729225293A........................ 2165OTT............. 6,163
729225293A........................ 2194FT.............. 11,461
729225293A........................ 1331OTT............. 12,513
729225293A........................ 1301FT.............. 7,262
729225293A........................ 1567FT.............. 6,305
729225293A........................ 783FB............... 8,307
729225293A........................ 98OTT............... 9,492
------------------------------------------------------------------------
(2) Reserved.
(f) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: ANE-AD-AMOC@faa.gov.
(g) Related Information
(1) For more information about this AD, contact Philip Haberlen,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803;
phone: 781-238-7770; fax: 781-238-7199; email:
philip.haberlen@faa.gov.
(2) Refer to MCAI, European Aviation Safety Agency AD 2016-0090,
dated May 10, 2016, for more information. You may examine the MCAI
in the AD docket on the Internet at https://www.regulations.gov by
searching for and locating it in Docket No. FAA-2016-6990.
(3) Turbomeca S.A. Mandatory Service Bulletin (MSB) 292 72 0848,
Version B, dated April 13, 2016, can be obtained from Turbomeca
S.A., using the contact information in paragraph (g)(4) of this
proposed AD.
(4) For service information identified in this proposed AD,
contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74
40 00; fax: 33 (0)5 59 74 45 15.
(5) You may view this service information at the FAA, Engine &
Propeller Directorate, 1200 District Avenue, Burlington, MA. For
information on the availability of this material at the FAA, call
781-238-7125.
Issued in Burlington, Massachusetts, on July 21, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2016-17719 Filed 7-27-16; 8:45 am]
BILLING CODE 4910-13-P
