Airworthiness Directives; Rolls-Royce Corporation Turboprop and Turboshaft Engines, 5452-5454 [2015-01371]

Download as PDF 5452 * Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations * * WISCONSIN * * * * * * * Southwestern Wisconsin Survey Area Wisconsin: Chippewa Eau Claire La Crosse Monroe Trempealeau Area of Application. Survey area plus: Minnesota: Fillmore Houston Winona Wisconsin: Barron Buffalo Clark Crawford Dunn Florence Forest Jackson Juneau Langlade Lincoln Marathon Marinette Menominee Oneida Pepin Portage Price Richland Rusk Shawano Taylor Vernon Vilas Waupaca Wood * * * * * [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 http:// 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 PO 00000 Frm 00002 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 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 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 http://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 http:// 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 http:// 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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]


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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 http://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]
BILLING CODE 4910-13-P