Airworthiness Directives; Rolls-Royce Corporation Turboprop and Turboshaft Engines, 5452-5454 [2015-01371]
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Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations
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[FR Doc. 2015–01938 Filed 1–30–15; 8:45 am]
BILLING CODE 6325–39–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0961; Directorate
Identifier 2011–NE–22–AD; Amendment 39–
18090; AD 2015–02–22]
wreier-aviles on DSK5TPTVN1PROD with RULES
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation Turboprop and Turboshaft
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2012–14–
06 for certain Rolls-Royce Corporation
SUMMARY:
VerDate Sep<11>2014
15:25 Jan 30, 2015
Jkt 235001
(RRC) 250–C20, –C20B, and –C20R/2
turboshaft engines. AD 2012–14–06
required a one-time visual inspection
and fluorescent-penetrant inspection
(FPI) on certain 3rd-stage and 4th-stage
turbine wheels for cracks in the turbine
blades. This new AD replaces the onetime visual inspection and FPI with
repetitive visual inspections and FPIs.
This AD also adds certain engine
models to the applicability. This AD
was prompted by the determination that
the one-time inspections required by AD
2012–14–06 should be changed to
repetitive inspections. We are issuing
this AD to prevent failure of 3rd-stage
and 4th-stage turbine wheel blades,
which could cause engine failure and
damage to the aircraft.
DATES: This AD is effective March 9,
2015.
ADDRESSES: For service information
identified in this AD, contact RollsRoyce Corporation, 450 South Meridian
Street, Indianapolis, IN 46225–1103;
phone: 888–255–4766 or 317–230–2720;
email: helicoptercustsupp@rollsroyce.com; Internet: www.rollsroyce.com. You may view this service
information at the FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, 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.govby searching for
and locating Docket No. FAA–2011–
0961; 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: John
Tallarovic, Aerospace Engineer, Chicago
Aircraft Certification Office, FAA, 2300
E. Devon Ave., Des Plaines, IL 60018;
phone: 847–294–8180; fax: 847–294–
7834; email: john.m.tallarovic@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–14–06,
Amendment 39–17120 (77 FR 40479,
July 10, 2012), (‘‘AD 2012–14–06’’). AD
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Fmt 4700
Sfmt 4700
2012–14–06 applied to certain RRC
250–C20, –C20B, and –C20R/2
turboshaft engines. The NPRM
published in the Federal Register on
October 2, 2014 (79 FR 59463). The
NPRM was prompted by determination
that the one-time inspections required
by AD 2012–14–06 should be changed
to repetitive inspections. The NPRM
proposed to replace the one-time visual
inspection and FPI with repetitive
visual inspections and FPIs, and also to
require a visual inspection and FPI after
any engine hot start. The NPRM also
proposed to add certain engine models
to the applicability. We are issuing this
AD to prevent failure of 3rd-stage and
4th-stage turbine wheel blades, which
could cause engine failure and damage
to the aircraft.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 59463,
October 2, 2014) and the FAA’s
response to each comment.
Request To Remove a Certain Proposed
Inspection Requirement
RRC requested that we remove the
requirement to inspect the 3rd-stage and
4th-stage turbine wheels after a hot start
because they are already prohibited
from further use after a hot start by the
maintenance instructions.
We agree. Maintenance instructions
clearly direct replacement of 3rd-stage
and 4th-stage turbine wheels following
a hot start. We removed from this AD
the requirement to perform a visual
inspection and an FPI on the affected
turbine wheels after any hot start.
Request To Limit Applicability
RRC requested that we restrict
applicability of the AD to only those
affected engines that are installed on
MD helicopters because the majority of
failures have occurred on MD
helicopters.
We disagree. Failures have occurred
in installations on other than MD
helicopters. Also, the FAA cannot
ensure that parts once used on MD
helicopters have not been subsequently
installed on other engines or helicopter
models. We did not change this AD.
Request To Delete a Certain Reference
RRC requested that we remove, from
the Actions Since AD 2012–14–06 Was
Published paragraph, reference to 3rdstage turbine wheel failures by replacing
the words ‘‘3rd-stage and’’ with the
words ‘‘two additional’’ because
additional failures only occurred in 4thstage turbine wheels.
E:\FR\FM\02FER1.SGM
02FER1
Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations
We agree. The new failures since AD
2012–14–06 was published were in 4thstage turbine wheels. However, the
paragraph, Actions Since AD 2012–14–
06 was Published, which appeared in
the NPRM (October 2, 2014 79 FR
59463), does not appear in this final
rule. We did not change this AD.
Request To Revise a Certain Paragraph
RRC requested that we add the word
‘‘potential’’ before the word ‘‘failures’’
in the Actions Since AD 2012–14–06
Was Published paragraph.
We agree. However, the paragraph,
Actions Since AD 2012–14–06 Was
Published, which appeared in the
NPRM (October 2, 2014 79 FR 59463),
does not appear in this final rule. We
did not change this AD.
Request To Revise the Costs of
Compliance
Request To Revise the Labor Rate
RRC requested that we change, in the
Costs of Compliance paragraph, the
labor rate from $85 per hour to $116 per
hour.
We disagree. The rate of $85 per hour
is provided by the FAA Office of
Aviation Policy and Plans for us to use
when estimating the labor costs of
complying with AD requirements. We
did not change this AD.
Request To Revise the Costs of
Compliance
RRC requested that we add the word
‘‘initial’’ before the stated cost in the
Costs of Compliance paragraph.
We partially agree. We did not insert
the word ‘‘initial’’, but we clarified that
our estimate of costs of compliance are
for one inspection, whether initial or
recurring.
wreier-aviles on DSK5TPTVN1PROD with RULES
Request To Revise a Definition
RRC requested that we change our
definition of a hot start.
We partially agree. We agree with the
suggested changes because they clarify
the definition of a hot start. However, in
our reply to a prior comment, we agreed
to remove the inspection requirements
associated with a hot start. Therefore,
we have deleted all requirements in this
AD to conduct inspections after hot
starts, and have deleted the Definition
paragraph.
15:25 Jan 30, 2015
Jkt 235001
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM (79 FR
59463, October 2, 2014) for correcting
the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 59463,
October 2, 2014).
We also determined that these
changes will not significantly increase
the economic burden on any operator or
increase the scope of this AD.
Costs of Compliance
RRC requested that we change, in the
Costs of Compliance paragraph, the
estimated time to conduct the
inspection from one hour to two hours.
We agree. We changed our estimate in
this AD to reflect two hours of labor to
conduct the inspection.
VerDate Sep<11>2014
Conclusion
We estimate that this AD affects 3,769
engines installed on aircraft of U.S.
registry. We also estimate that it will
take about 2 hours per engine to comply
with the inspection requirement of this
AD. The average labor rate is $85 per
hour. Based on these figures, we
estimate the cost of this AD on U.S.
operators for one inspection to be
$640,730.
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.
5453
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, 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.
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
removing Airworthiness Directive (AD)
2012–14–06, Amendment 39–17120 (77
FR 40479, July 10, 2012), and adding the
following new AD:
■
2015–02–22 Rolls-Royce Corporation:
Amendment 39–18090; Docket No.
FAA–2011–0961; Directorate Identifier
2011–NE–22–AD.
(a) Effective Date
This AD is effective March 9, 2015.
(b) Affected ADs
This AD supersedes AD 2012–14–06,
Amendment 39–17120 (77 FR 40479, July 10,
2012).
Regulatory Findings
(c) Applicability
This AD applies to Rolls-Royce
Corporation (RRC) 250–B17, –B17B, –B17C,
–B17D, –B17E, –B17F, –B17F/1, –B17F/2
turboprop engines; and 250–C20, –C20B,
–C20F, –C20J, –C20R, –C20R/1, –C20R/2,
–C20R/4, –C20S, and –C20W turboshaft
engines; with either a 3rd-stage turbine
wheel, part number (P/N) 23065818, or a 4thstage turbine wheel, P/N 23055944, installed.
We have determined that 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.
(d) Unsafe Condition
This AD was prompted by investigations
that revealed that not all 3rd-stage and 4thstage turbine wheel blade failures were
identified by the one-time inspections
required by AD 2012–14–06, Amendment
39–17120 (77 FR 40479, July 10, 2012). We
determined that to address the unsafe
condition, repetitive inspections are
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E:\FR\FM\02FER1.SGM
02FER1
5454
Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations
required, triggered by hours since last
inspection (HSLI). We are issuing this AD to
prevent failure of 3rd-stage and 4th-stage
turbine wheel blades, which could cause
engine failure and damage to the aircraft.
DEPARTMENT OF TRANSPORTATION
(e) Compliance
[Docket No. FAA–2015–0049; Directorate
Identifier 2014–SW–037–AD; Amendment
39–18096; AD 2015–02–27]
Comply with this AD within the
compliance times specified, unless already
done. After the effective date of this AD:
(1) Within 1,750 HSLI, remove the affected
turbine wheels and perform a visual
inspection and a fluorescent-penetrant
inspection (FPI) on the removed turbine
wheels for cracks at the trailing edge of the
turbine blades near the fillet at the rim.
(2) Any time the power turbine is
disassembled, perform a visual inspection
and an FPI on the affected turbine wheels for
cracks at the trailing edge of the turbine
blades, near the fillet at the rim.
(3) Thereafter, re-inspect every 1,750 HSLI.
(4) Do not return to service any turbine
wheels that have cracks detected.
(f) Alternative Methods of Compliance
(AMOCs)
The Manager, Chicago Aircraft
Certification Office, may approve AMOCs for
this AD. Use the procedures found in 14 CFR
39.19 to make your request.
(g) Related Information
(1) For more information about this AD,
contact John Tallarovic, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA,
2300 E. Devon Ave., Des Plaines, IL 60018;
phone: 847–294–8180; fax: 847–294–7834;
email: john.m.tallarovic@faa.gov.
(2) RRC Alert Commercial Engine Bulletin
(CEB) No. CEB–A–1407, Revision 3, dated
May 19, 2014, and Alert CEB No. CEB–A–72–
4098, Revision 3, dated May 19, 2014
(combined into one document), which are
not incorporated by reference in this AD, can
be obtained from RRC, using the contact
information in paragraph (g)(3) of this AD.
(3) For service information identified in
this AD, contact Rolls-Royce Corporation
Customer Support, 450 South Meridian
Street, Indianapolis, IN 46225–1103; phone:
888–255–4766 or 317–230–2720; email:
helicoptercustsupp@rolls-royce.com;
Internet: www.rolls-royce.com.
(4) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA 01803. For information on the
availability of this material at the FAA, call
781–238–7125.
(h) Material Incorporated by Reference
wreier-aviles on DSK5TPTVN1PROD with RULES
None.
Issued in Burlington, Massachusetts, on
January 20, 2015.
Colleen M. D’Alessandro,
Assistant Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2015–01371 Filed 1–30–15; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
15:25 Jan 30, 2015
Jkt 235001
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Previously Eurocopter
France) Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–19–
19 for certain Eurocopter France Model
AS332C, AS332L, AS332L1, AS332L2,
and EC225LP helicopters. AD 2013–19–
19 required replacing certain serialnumbered main gearbox (MGB) bevel
gear vertical shafts and inspecting and
replacing, if necessary, each MGB bevel
gear vertical shaft (shaft). This new AD
requires the same actions as AD 2013–
19–19 but corrects an error in the term
used to identify an inspection
qualification and updates the type
certificate holder’s name. This AD is
prompted by two incidents of
emergency ditching after warning
indications of loss of MGB oil pressure.
These actions are intended to detect a
cracked shaft, which could result in loss
of MGB oil pressure, loss of the MGB
lubrication system, and subsequent loss
of control of the helicopter.
DATES: This AD is effective February 17,
2015.
We must receive comments on this
AD by April 3, 2015.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
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, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
For service information identified in
this AD, contact Airbus Helicopters,
Inc., 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641–
0000 or (800) 232–0323; fax (972) 641–
3775; or at https://
www.airbushelicopters.com/techpub.
You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
James Blyn, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
james.blyn@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, explain the reason for any
recommended change, and include
supporting data. To ensure the docket
does not contain duplicate comments,
commenters should send only one copy
of written comments, or if comments are
filed electronically, commenters should
submit them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
Examining the AD Docket
Discussion
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
On September 9, 2013, we issued AD
2013–19–19 (78 FR 60188, October 1,
2013), which required replacing certain
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E:\FR\FM\02FER1.SGM
02FER1
Agencies
[Federal Register Volume 80, Number 21 (Monday, February 2, 2015)]
[Rules and Regulations]
[Pages 5452-5454]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01371]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0961; Directorate Identifier 2011-NE-22-AD;
Amendment 39-18090; AD 2015-02-22]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation Turboprop and
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directive (AD) 2012-14-06 for
certain Rolls-Royce Corporation (RRC) 250-C20, -C20B, and -C20R/2
turboshaft engines. AD 2012-14-06 required a one-time visual inspection
and fluorescent-penetrant inspection (FPI) on certain 3rd-stage and
4th-stage turbine wheels for cracks in the turbine blades. This new AD
replaces the one-time visual inspection and FPI with repetitive visual
inspections and FPIs. This AD also adds certain engine models to the
applicability. This AD was prompted by the determination that the one-
time inspections required by AD 2012-14-06 should be changed to
repetitive inspections. We are issuing this AD to prevent failure of
3rd-stage and 4th-stage turbine wheel blades, which could cause engine
failure and damage to the aircraft.
DATES: This AD is effective March 9, 2015.
ADDRESSES: For service information identified in this AD, contact
Rolls-Royce Corporation, 450 South Meridian Street, Indianapolis, IN
46225-1103; phone: 888-255-4766 or 317-230-2720; email:
royce.com">helicoptercustsupp@rolls-royce.com; Internet: www.rolls-royce.com. You
may view this service information at the FAA, Engine & Propeller
Directorate, 12 New England Executive Park, 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.govby searching for and locating Docket No. FAA-2011-
0961; 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: John Tallarovic, Aerospace Engineer,
Chicago Aircraft Certification Office, FAA, 2300 E. Devon Ave., Des
Plaines, IL 60018; phone: 847-294-8180; fax: 847-294-7834; email:
john.m.tallarovic@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-14-06, Amendment 39-17120 (77 FR 40479,
July 10, 2012), (``AD 2012-14-06''). AD 2012-14-06 applied to certain
RRC 250-C20, -C20B, and -C20R/2 turboshaft engines. The NPRM published
in the Federal Register on October 2, 2014 (79 FR 59463). The NPRM was
prompted by determination that the one-time inspections required by AD
2012-14-06 should be changed to repetitive inspections. The NPRM
proposed to replace the one-time visual inspection and FPI with
repetitive visual inspections and FPIs, and also to require a visual
inspection and FPI after any engine hot start. The NPRM also proposed
to add certain engine models to the applicability. We are issuing this
AD to prevent failure of 3rd-stage and 4th-stage turbine wheel blades,
which could cause engine failure and damage to the aircraft.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (79
FR 59463, October 2, 2014) and the FAA's response to each comment.
Request To Remove a Certain Proposed Inspection Requirement
RRC requested that we remove the requirement to inspect the 3rd-
stage and 4th-stage turbine wheels after a hot start because they are
already prohibited from further use after a hot start by the
maintenance instructions.
We agree. Maintenance instructions clearly direct replacement of
3rd-stage and 4th-stage turbine wheels following a hot start. We
removed from this AD the requirement to perform a visual inspection and
an FPI on the affected turbine wheels after any hot start.
Request To Limit Applicability
RRC requested that we restrict applicability of the AD to only
those affected engines that are installed on MD helicopters because the
majority of failures have occurred on MD helicopters.
We disagree. Failures have occurred in installations on other than
MD helicopters. Also, the FAA cannot ensure that parts once used on MD
helicopters have not been subsequently installed on other engines or
helicopter models. We did not change this AD.
Request To Delete a Certain Reference
RRC requested that we remove, from the Actions Since AD 2012-14-06
Was Published paragraph, reference to 3rd-stage turbine wheel failures
by replacing the words ``3rd-stage and'' with the words ``two
additional'' because additional failures only occurred in 4th-stage
turbine wheels.
[[Page 5453]]
We agree. The new failures since AD 2012-14-06 was published were
in 4th-stage turbine wheels. However, the paragraph, Actions Since AD
2012-14-06 was Published, which appeared in the NPRM (October 2, 2014
79 FR 59463), does not appear in this final rule. We did not change
this AD.
Request To Revise a Certain Paragraph
RRC requested that we add the word ``potential'' before the word
``failures'' in the Actions Since AD 2012-14-06 Was Published
paragraph.
We agree. However, the paragraph, Actions Since AD 2012-14-06 Was
Published, which appeared in the NPRM (October 2, 2014 79 FR 59463),
does not appear in this final rule. We did not change this AD.
Request To Revise the Costs of Compliance
RRC requested that we change, in the Costs of Compliance paragraph,
the estimated time to conduct the inspection from one hour to two
hours.
We agree. We changed our estimate in this AD to reflect two hours
of labor to conduct the inspection.
Request To Revise the Labor Rate
RRC requested that we change, in the Costs of Compliance paragraph,
the labor rate from $85 per hour to $116 per hour.
We disagree. The rate of $85 per hour is provided by the FAA Office
of Aviation Policy and Plans for us to use when estimating the labor
costs of complying with AD requirements. We did not change this AD.
Request To Revise the Costs of Compliance
RRC requested that we add the word ``initial'' before the stated
cost in the Costs of Compliance paragraph.
We partially agree. We did not insert the word ``initial'', but we
clarified that our estimate of costs of compliance are for one
inspection, whether initial or recurring.
Request To Revise a Definition
RRC requested that we change our definition of a hot start.
We partially agree. We agree with the suggested changes because
they clarify the definition of a hot start. However, in our reply to a
prior comment, we agreed to remove the inspection requirements
associated with a hot start. Therefore, we have deleted all
requirements in this AD to conduct inspections after hot starts, and
have deleted the Definition paragraph.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously. We have determined that
these minor changes:
Are consistent with the intent that was proposed in the
NPRM (79 FR 59463, October 2, 2014) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 59463, October 2, 2014).
We also determined that these changes will not significantly
increase the economic burden on any operator or increase the scope of
this AD.
Costs of Compliance
We estimate that this AD affects 3,769 engines installed on
aircraft of U.S. registry. We also estimate that it will take about 2
hours per engine to comply with the inspection requirement of this AD.
The average labor rate is $85 per hour. Based on these figures, we
estimate the cost of this AD on U.S. operators for one inspection to be
$640,730.
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 have determined that 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, 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.
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 removing Airworthiness Directive (AD)
2012-14-06, Amendment 39-17120 (77 FR 40479, July 10, 2012), and adding
the following new AD:
2015-02-22 Rolls-Royce Corporation: Amendment 39-18090; Docket No.
FAA-2011-0961; Directorate Identifier 2011-NE-22-AD.
(a) Effective Date
This AD is effective March 9, 2015.
(b) Affected ADs
This AD supersedes AD 2012-14-06, Amendment 39-17120 (77 FR
40479, July 10, 2012).
(c) Applicability
This AD applies to Rolls-Royce Corporation (RRC) 250-B17, -B17B,
-B17C, -B17D, -B17E, -B17F, -B17F/1, -B17F/2 turboprop engines; and
250-C20, -C20B, -C20F, -C20J, -C20R, -C20R/1, -C20R/2, -C20R/4, -
C20S, and -C20W turboshaft engines; with either a 3rd-stage turbine
wheel, part number (P/N) 23065818, or a 4th-stage turbine wheel, P/N
23055944, installed.
(d) Unsafe Condition
This AD was prompted by investigations that revealed that not
all 3rd-stage and 4th-stage turbine wheel blade failures were
identified by the one-time inspections required by AD 2012-14-06,
Amendment 39-17120 (77 FR 40479, July 10, 2012). We determined that
to address the unsafe condition, repetitive inspections are
[[Page 5454]]
required, triggered by hours since last inspection (HSLI). We are
issuing this AD to prevent failure of 3rd-stage and 4th-stage
turbine wheel blades, which could cause engine failure and damage to
the aircraft.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done. After the effective date of this AD:
(1) Within 1,750 HSLI, remove the affected turbine wheels and
perform a visual inspection and a fluorescent-penetrant inspection
(FPI) on the removed turbine wheels for cracks at the trailing edge
of the turbine blades near the fillet at the rim.
(2) Any time the power turbine is disassembled, perform a visual
inspection and an FPI on the affected turbine wheels for cracks at
the trailing edge of the turbine blades, near the fillet at the rim.
(3) Thereafter, re-inspect every 1,750 HSLI.
(4) Do not return to service any turbine wheels that have cracks
detected.
(f) Alternative Methods of Compliance (AMOCs)
The Manager, Chicago Aircraft Certification Office, may approve
AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make
your request.
(g) Related Information
(1) For more information about this AD, contact John Tallarovic,
Aerospace Engineer, Chicago Aircraft Certification Office, FAA, 2300
E. Devon Ave., Des Plaines, IL 60018; phone: 847-294-8180; fax: 847-
294-7834; email: john.m.tallarovic@faa.gov.
(2) RRC Alert Commercial Engine Bulletin (CEB) No. CEB-A-1407,
Revision 3, dated May 19, 2014, and Alert CEB No. CEB-A-72-4098,
Revision 3, dated May 19, 2014 (combined into one document), which
are not incorporated by reference in this AD, can be obtained from
RRC, using the contact information in paragraph (g)(3) of this AD.
(3) For service information identified in this AD, contact
Rolls-Royce Corporation Customer Support, 450 South Meridian Street,
Indianapolis, IN 46225-1103; phone: 888-255-4766 or 317-230-2720;
email: royce.com">helicoptercustsupp@rolls-royce.com; Internet: www.rolls-
royce.com.
(4) You may view this service information at the FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803. For information on the availability of this material at the
FAA, call 781-238-7125.
(h) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on January 20, 2015.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2015-01371 Filed 1-30-15; 8:45 am]
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