Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines, 42443-42445 [2017-18910]

Download as PDF Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 2. Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 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) 2015–22–51, Amendment 39–18386 (81 FR 5037, February 1, 2016), and adding the following new AD: ■ 2017–18–13 Agusta S.p.A.: Amendment 39– 19022; Docket No. FAA–2017–0308; Product Identifier 2016–SW–083–AD. (a) Applicability This AD applies to Model A109A and A109A II helicopters with a main rotor blade (blade) part number (P/N) 109–0103–01–7, P/N 109–0103–01–9, or P/N 109–0103–01– 115 that has 500 or more hours time-inservice (TIS) installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a blade. This condition could result in failure of a blade and subsequent loss of control of the helicopter. sradovich on DSK3GMQ082PROD with RULES (c) Affected ADs This AD supersedes AD 2015–22–51, Amendment 39–18386 (81 FR 5037, February 1, 2016). (d) Effective Date This AD becomes effective September 25, 2017. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. VerDate Sep<11>2014 16:18 Sep 07, 2017 Jkt 241001 (f) Required Actions Before further flight, unless already done within the last 5 hours TIS, and thereafter at intervals not to exceed 5 hours TIS: (1) Using a 3X or higher power magnifying glass, visually inspect the top and bottom surface of each blade for a crack in the area between the station at the end of the doublers (station 1550) and the station at the beginning of the abrasion strip (station 3100). (2) If there is a crack, replace the blade before further flight. Replacing the blade with blade P/N 109–0103–01–7, P/N 109–0103– 01–9, or P/N 109–0103–01–115 does not constitute terminating action for the repetitive inspections required by this AD. (g) Special Flight Permits Special flight permits are prohibited. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (i) Additional Information (1) Leonardo Helicopters Alert Bollettino Tecnico No. 109–150, Revision B, dated October 21, 2016, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Leonardo S.p.A. Helicopters, Matteo Ragazzi, Head of Airworthiness, Viale G.Agusta 520, 21017 C.Costa di Samarate (Va) Italy; telephone +39–0331–711756; fax +39–0331– 229046; or at http://www.leonardo company.com/-/bulletins. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N– 321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2016–0213, dated October 26, 2016. You may view the EASA AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2017– 0308. (j) Subject Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blade. Issued in Fort Worth, Texas, on August 30, 2017. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2017–18972 Filed 9–7–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 42443 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0961; Product Identifier 2011–NE–22–AD; Amendment 39– 19023; AD 2017–18–14] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2015–02– 22 for certain Rolls-Royce Corporation (RRC) model 250 turboprop and turboshaft engines. AD 2015–02–22 required repetitive visual inspections and fluorescent-penetrant inspection (FPIs) on certain 3rd-stage and 4th-stage turbine wheels for cracks in the turbine wheel blades. This AD requires repetitive visual inspections and FPIs of 3rd-stage turbine wheels while removing from service 4th-stage turbine wheels. We are also revising the applicability to remove all RRC turboprop engines and add additional turboshaft engines. This AD was prompted by our finding that it is necessary to remove the 4th-stage wheels at the next inspection. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 13, 2017. ADDRESSES: See the FOR FURTHER INFORMATION CONTACT section. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by 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 final rule, 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, FAA, Chicago ACO Branch, Compliance and Airworthiness Division, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: E:\FR\FM\08SER1.SGM 08SER1 42444 Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 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 2015–02–22, Amendment 39–18090 (80 FR 5452, February 2, 2015), (‘‘AD 2015–02–22’’). AD 2015–02–22 applied to certain 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. The NPRM published in the Federal Register on March 29, 2017 (82 FR 15474). The NPRM was prompted by our determination that it is necessary to remove the 4th-stage wheels at the next inspection. The NPRM proposed to require repetitive visual inspections and FPIs of 3rd-stage turbine wheels while removing from service 4th-stage turbine wheels. We are also revising the applicability to remove all RRC turboprop engines and add additional turboshaft engines. We are issuing this AD to prevent failure of the 3rd-stage and 4th-stage turbine wheel blades, damage to the engine, 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 and the FAA’s response to each comment. Request To Remove Certain 3rd Stage Turbine Wheel From AD RRC requested that we remove references in this AD to the 3rd stage turbine wheel, part number (P/N) RR30000236, installed on the RRC 250– C300/A1 and 250–C300/B1 turboshaft engines. RRC indicated that 3rd stage turbine wheels, P/N RR30000236, are not susceptible to cracks. RRC noted that there have been no cracks observed on 3rd stage wheels installed on RRC 250–C300/A1 or 250–C300B/1 engines. We agree. The 3rd stage turbine wheel, P/N RR30000236, installed on RRC 250–C300/A1 and 250–C300/B1 engines does not require inspections. They are subject to less severe operating conditions and are not susceptible to this type of failure. We removed references to the 3rd stage turbine wheel, P/N RR30000236, from this AD. Request To Revise Power Turbine Reference RRC requested that we change references in this AD from ‘‘power turbine’’ to ‘‘turbine.’’ RRC noted that this AD should refer to the entire turbine module rather than just to the power turbine. RRC also commented that the risk analysis for this AD is based on changing the parts anytime the turbine is being serviced, not just the power turbine. Revising the reference in this AD to ‘‘turbine’’ would remove the affected 4th stage turbine wheels from the fleet in a shorter time period since the actions specified in this AD are to be complied with whenever the turbine is at the shop and is dissembled for any reason, or at the next turbine wheel replacement, whichever occurs first. We agree. We changed the reference in the Compliance section of this AD from ‘‘power turbine’’ to ‘‘turbine.’’ RRC also commented that changing the references to ‘‘turbine’’ would allow for removal of the Definition section from this AD. We disagree. The term ‘‘engine shop visit’’ is used as one of the criteria in this AD to determine when an inspection of affected applicable turbine wheels is required. Given that ‘‘engine shop visit’’ may be interpreted in different ways, we provide a definition for this term in this AD. We did not change this AD. Request To Clarify Removal of Blades With Cracks From Service RRC requested that we revise the Compliance section of this AD so that it does not require removal from service all turbine wheels found with cracks. RRC commented that only certain cracks are related to this AD and are a safety concern. We agree. The intent of this AD is to address cracks at the trailing edge of the turbine wheel blades, near the fillet at the rim. The maintenance manuals for these engines allow certain cracks in areas of the turbine wheels not subject to this AD. Engines may still operate safety with turbine wheels that have allowable cracks. We revised paragraph (f)(3) of this AD to refer to cracks found at the trailing edge, near the fillet at the rim, of the turbine blades. Revision to Costs of Compliance We reduced the estimated cost of inspection of 3rd stage wheels from $320,365 to $288,320 since we removed the 3rd stage wheel, P/N RR30000236, from the applicability of this AD. As noted in our previous comment response, these P/N 3rd stage wheels are not subject to the unsafe condition identified in this AD. 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 and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not 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 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Parts cost Inspect 3rd-stage wheels, P/N 23065818 ....... Replace 4th-stage wheel, P/N 23055944 or RR30000240. sradovich on DSK3GMQ082PROD with RULES Action 1 work-hour × $85 per hour = $85 ................. 0 work-hours × $85 per hour = $0 ................. $0 .................. 5,653 (prorated cost of part). Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Sep<11>2014 16:18 Sep 07, 2017 Jkt 241001 rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Cost per product $85 5,653 Cost on U.S. operators $288,320 21,306,157 detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, E:\FR\FM\08SER1.SGM 08SER1 Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. 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 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. sradovich on DSK3GMQ082PROD with RULES 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: ■ VerDate Sep<11>2014 16:18 Sep 07, 2017 Jkt 241001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2015–02–22, Amendment 39–18090 (80 FR 5452, February 2, 2015), and adding the following new AD: ■ 2017–18–14 Rolls-Royce Corporation: Amendment 39–19023; Docket No. FAA–2011–0961; Product Identifier 2011–NE–22–AD. (a) Effective Date This AD is effective October 13, 2017. (b) Affected ADs This AD replaces Airworthiness Directive (AD) 2015–02–22, Amendment 39–18090 (80 FR 5452, February 2, 2015). (c) Applicability This AD applies to Rolls-Royce Corporation (RRC) 250–C20, –C20B, –C20F, –C20J, –C20R, –C20R/1, –C20R/2, –C20R/4, –C20W, –C300/A1, and –C300/B1 turboshaft engines with either a 3rd-stage turbine wheel, part number (P/N) 23065818, or a 4th-stage turbine wheel, P/N 23055944 or RR30000240, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by in-service turbine wheel blade failures that revealed the need for changes to the inspections of certain 3rd-stage turbine wheels and removal from service of certain 4th-stage turbine wheels. We are issuing this AD to prevent failure of the 3rd-stage and 4th-stage turbine wheel blades, damage to the engine, and damage to the aircraft. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 1,775 hours since last visual inspection and fluorescent-penetrant inspection (FPI) or before the next flight after the effective date of this AD, whichever occurs later: (i) Remove 3rd-stage turbine wheels, P/N 23065818, and perform a visual inspection and an FPI on the removed turbine wheels for cracks at the trailing edge of the turbine blades, near the fillet at the rim. (ii) Thereafter, re-inspect the affected turbine wheels every 1,775 hours since last inspection (HSLI). (2) Any time the turbine is disassembled, perform a visual inspection and an FPI on 3rd-stage turbine wheels, P/N 23065818, for cracks at the trailing edge of the turbine blades, near the fillet at the rim. (3) Do not return to service any turbine wheels found to have cracks at the trailing edge, near the fillet at the rim, of the turbine blades. (4) Within 1,775 HSLI, or at the next engine shop visit, whichever occurs later, remove 4th-stage turbine wheels, P/N 23055944, from service. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 42445 (5) Within 2,025 HSLI, or at the next engine shop visit, whichever occurs later, remove 4th-stage turbine wheels, P/N RR30000240, from service. (g) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, FAA, Chicago ACO Branch, Compliance and Airworthiness Division, 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 Branch, send it to the attention of the person identified in paragraph (i) of this AD. (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. (i) Related Information For more information about this AD, contact John Tallarovic, Aerospace Engineer, FAA, Chicago ACO Branch, Compliance and Airworthiness Division, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847–294–8180; fax: 847–294–7834; email: john.m.tallarovic@ faa.gov. (j) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on August 31, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–18910 Filed 9–7–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2016–9593; Airspace Docket No. 16–ACE–12] Amendment of Class E Airspace; Falls City, NE Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action modifies Class E airspace extending upward from 700 feet above the surface at Brenner Field SUMMARY: E:\FR\FM\08SER1.SGM 08SER1

Agencies

[Federal Register Volume 82, Number 173 (Friday, September 8, 2017)]
[Rules and Regulations]
[Pages 42443-42445]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-18910]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0961; Product Identifier 2011-NE-22-AD; Amendment 
39-19023; AD 2017-18-14]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-02-22 for 
certain Rolls-Royce Corporation (RRC) model 250 turboprop and 
turboshaft engines. AD 2015-02-22 required repetitive visual 
inspections and fluorescent-penetrant inspection (FPIs) on certain 3rd-
stage and 4th-stage turbine wheels for cracks in the turbine wheel 
blades. This AD requires repetitive visual inspections and FPIs of 3rd-
stage turbine wheels while removing from service 4th-stage turbine 
wheels. We are also revising the applicability to remove all RRC 
turboprop engines and add additional turboshaft engines. This AD was 
prompted by our finding that it is necessary to remove the 4th-stage 
wheels at the next inspection. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective October 13, 2017.

ADDRESSES: See the FOR FURTHER INFORMATION CONTACT section.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by 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 final rule, 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, 
FAA, Chicago ACO Branch, Compliance and Airworthiness Division, 2300 E. 
Devon Ave., Des Plaines, IL 60018; phone:

[[Page 42444]]

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 2015-02-22, Amendment 39-18090 (80 FR 5452, 
February 2, 2015), (``AD 2015-02-22''). AD 2015-02-22 applied to 
certain 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. The NPRM 
published in the Federal Register on March 29, 2017 (82 FR 15474). The 
NPRM was prompted by our determination that it is necessary to remove 
the 4th-stage wheels at the next inspection. The NPRM proposed to 
require repetitive visual inspections and FPIs of 3rd-stage turbine 
wheels while removing from service 4th-stage turbine wheels. We are 
also revising the applicability to remove all RRC turboprop engines and 
add additional turboshaft engines. We are issuing this AD to prevent 
failure of the 3rd-stage and 4th-stage turbine wheel blades, damage to 
the engine, 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 and 
the FAA's response to each comment.

Request To Remove Certain 3rd Stage Turbine Wheel From AD

    RRC requested that we remove references in this AD to the 3rd stage 
turbine wheel, part number (P/N) RR30000236, installed on the RRC 250-
C300/A1 and 250-C300/B1 turboshaft engines. RRC indicated that 3rd 
stage turbine wheels, P/N RR30000236, are not susceptible to cracks. 
RRC noted that there have been no cracks observed on 3rd stage wheels 
installed on RRC 250-C300/A1 or 250-C300B/1 engines.
    We agree. The 3rd stage turbine wheel, P/N RR30000236, installed on 
RRC 250-C300/A1 and 250-C300/B1 engines does not require inspections. 
They are subject to less severe operating conditions and are not 
susceptible to this type of failure. We removed references to the 3rd 
stage turbine wheel, P/N RR30000236, from this AD.

Request To Revise Power Turbine Reference

    RRC requested that we change references in this AD from ``power 
turbine'' to ``turbine.'' RRC noted that this AD should refer to the 
entire turbine module rather than just to the power turbine. RRC also 
commented that the risk analysis for this AD is based on changing the 
parts anytime the turbine is being serviced, not just the power 
turbine. Revising the reference in this AD to ``turbine'' would remove 
the affected 4th stage turbine wheels from the fleet in a shorter time 
period since the actions specified in this AD are to be complied with 
whenever the turbine is at the shop and is dissembled for any reason, 
or at the next turbine wheel replacement, whichever occurs first.
    We agree. We changed the reference in the Compliance section of 
this AD from ``power turbine'' to ``turbine.''
    RRC also commented that changing the references to ``turbine'' 
would allow for removal of the Definition section from this AD.
    We disagree. The term ``engine shop visit'' is used as one of the 
criteria in this AD to determine when an inspection of affected 
applicable turbine wheels is required. Given that ``engine shop visit'' 
may be interpreted in different ways, we provide a definition for this 
term in this AD. We did not change this AD.

Request To Clarify Removal of Blades With Cracks From Service

    RRC requested that we revise the Compliance section of this AD so 
that it does not require removal from service all turbine wheels found 
with cracks. RRC commented that only certain cracks are related to this 
AD and are a safety concern.
    We agree. The intent of this AD is to address cracks at the 
trailing edge of the turbine wheel blades, near the fillet at the rim. 
The maintenance manuals for these engines allow certain cracks in areas 
of the turbine wheels not subject to this AD. Engines may still operate 
safety with turbine wheels that have allowable cracks. We revised 
paragraph (f)(3) of this AD to refer to cracks found at the trailing 
edge, near the fillet at the rim, of the turbine blades.

Revision to Costs of Compliance

    We reduced the estimated cost of inspection of 3rd stage wheels 
from $320,365 to $288,320 since we removed the 3rd stage wheel, P/N 
RR30000236, from the applicability of this AD. As noted in our previous 
comment response, these P/N 3rd stage wheels are not subject to the 
unsafe condition identified in this AD.

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 and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not 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 
airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
              Action                     Labor cost             Parts cost            product        operators
----------------------------------------------------------------------------------------------------------------
Inspect 3rd-stage wheels, P/N       1 work-hour x $85     $0....................             $85        $288,320
 23065818.                           per hour = $85.
Replace 4th-stage wheel, P/N        0 work-hours x $85    5,653 (pro-rated cost            5,653      21,306,157
 23055944 or RR30000240.             per hour = $0.        of part).
----------------------------------------------------------------------------------------------------------------

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,

[[Page 42445]]

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
appliances to the Manager, Engine and Propeller Standards Branch, 
Policy and Innovation Division.

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 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.

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) 
2015-02-22, Amendment 39-18090 (80 FR 5452, February 2, 2015), and 
adding the following new AD:

2017-18-14 Rolls-Royce Corporation: Amendment 39-19023; Docket No. 
FAA-2011-0961; Product Identifier 2011-NE-22-AD.

(a) Effective Date

    This AD is effective October 13, 2017.

(b) Affected ADs

    This AD replaces Airworthiness Directive (AD) 2015-02-22, 
Amendment 39-18090 (80 FR 5452, February 2, 2015).

(c) Applicability

    This AD applies to Rolls-Royce Corporation (RRC) 250-C20, -C20B, 
-C20F, -C20J, -C20R, -C20R/1, -C20R/2, -C20R/4, -C20W, -C300/A1, and 
-C300/B1 turboshaft engines with either a 3rd-stage turbine wheel, 
part number (P/N) 23065818, or a 4th-stage turbine wheel, P/N 
23055944 or RR30000240, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by in-service turbine wheel blade failures 
that revealed the need for changes to the inspections of certain 
3rd-stage turbine wheels and removal from service of certain 4th-
stage turbine wheels. We are issuing this AD to prevent failure of 
the 3rd-stage and 4th-stage turbine wheel blades, damage to the 
engine, and damage to the aircraft.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 1,775 hours since last visual inspection and 
fluorescent-penetrant inspection (FPI) or before the next flight 
after the effective date of this AD, whichever occurs later:
    (i) Remove 3rd-stage turbine wheels, P/N 23065818, and perform a 
visual inspection and an FPI on the removed turbine wheels for 
cracks at the trailing edge of the turbine blades, near the fillet 
at the rim.
    (ii) Thereafter, re-inspect the affected turbine wheels every 
1,775 hours since last inspection (HSLI).
    (2) Any time the turbine is disassembled, perform a visual 
inspection and an FPI on 3rd-stage turbine wheels, P/N 23065818, for 
cracks at the trailing edge of the turbine blades, near the fillet 
at the rim.
    (3) Do not return to service any turbine wheels found to have 
cracks at the trailing edge, near the fillet at the rim, of the 
turbine blades.
    (4) Within 1,775 HSLI, or at the next engine shop visit, 
whichever occurs later, remove 4th-stage turbine wheels, P/N 
23055944, from service.
    (5) Within 2,025 HSLI, or at the next engine shop visit, 
whichever occurs later, remove 4th-stage turbine wheels, P/N 
RR30000240, from service.

(g) Definition

    For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, FAA, Chicago ACO Branch, Compliance and 
Airworthiness Division, 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 Branch, 
send it to the attention of the person identified in paragraph (i) 
of this AD.
    (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.

(i) Related Information

    For more information about this AD, contact John Tallarovic, 
Aerospace Engineer, FAA, Chicago ACO Branch, Compliance and 
Airworthiness Division, 2300 E. Devon Ave., Des Plaines, IL 60018; 
phone: 847-294-8180; fax: 847-294-7834; email: 
john.m.tallarovic@faa.gov.

(j) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on August 31, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-18910 Filed 9-7-17; 8:45 am]
 BILLING CODE 4910-13-P