Airworthiness Directives; Rolls-Royce Corporation Engines, 18751-18753 [2018-09012]

Download as PDF Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Proposed Rules December 21, 2010) (‘‘AD 2010–26–05’’) and AD 2014–03–12, Amendment 39–17749 (79 FR 11693, March 3, 2014) (‘‘AD 2014–03– 12’’). (c) Applicability This AD applies to all Dassault Aviation Model FALCON 2000 airplanes, certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 05, Time limits/maintenance checks. (e) Reason This AD was prompted by manufacturer revisions to the airplane maintenance manual (AMM) that introduce new or more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to prevent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. nshattuck on DSK9F9SC42PROD with PROPOSALS (g) Revision of Maintenance or Inspection Program Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the information specified in Chapter 5–40, Airworthiness Limitations, Revision 19, dated November 2017, of Chapter 5, Maintenance Planning Document, of the Dassault Falcon 2000 Maintenance Manual. The initial compliance times for doing the tasks are at the time specified in Chapter 5– 40, Airworthiness Limitations, Revision 19, dated November 2017, of Chapter 5, Maintenance Planning Document, of the Dassault Falcon 2000 Maintenance Manual, or within 90 days after the effective date of this AD, whichever occurs later; except as required by paragraphs (g)(1) through (g)(3) of this AD. The term ‘‘LDG’’ in the ‘‘First Inspection’’ column of any table in Chapter 5–40, Airworthiness Limitations, Revision 19, dated November 2017, means total airplane landings. The term ‘‘FH’’ in the ‘‘First Inspection’’ column of any table in Chapter 5–40, Airworthiness Limitations, Revision 19, dated November 2017, means total flight hours. The term ‘‘FC’’ in the ‘‘First Inspection’’ column of any table in Chapter 5–40, Airworthiness Limitations, Revision 19, dated November 2017, means total flight cycles. (1) For Task 30–11–09–350–801 identified in the service information specified in the introductory text of paragraph (g) of this AD, the initial compliance time is the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) At the earlier of the times specified in paragraphs (g)(1)(i)(A) and (g)(1)(i)(B) of this AD. (A) Prior to the accumulation of 2,400 total flight hours or 2,000 total flight cycles, whichever occurs first. (B) Within 2,400 flight hours or 2,000 flight cycles after April 7, 2014 (the effective date of AD 2014–03–12), whichever occurs first. VerDate Sep<11>2014 15:05 Apr 27, 2018 Jkt 244001 (ii) Within 30 days after April 7, 2014 (the effective date of AD 2014–03–12). (2) For Task 52–20–00–610–801–01 identified in the service information specified in the introductory text of paragraph (g) of this AD, the initial compliance time is within 24 months after April 7, 2014 (the effective date of AD 2014– 03–12). (3) The limited service life of part number F2MA721512100 is 3,750 total flight cycles on the part or 6 years since the manufacturing date of the part, whichever occurs first. (h) No Alternative Actions or Intervals After the maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections), or intervals, may be used unless the actions, or intervals, are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. (i) Terminating Actions for Other ADs (1) Accomplishing the actions required by this AD terminates all of the requirements of AD 2014–03–12. (2) Accomplishment of the actions required by paragraph (g) of this AD terminates the requirements of paragraph (g) of AD 2010– 26–05 for all Dassault Aviation Model FALCON 2000 airplanes. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Dassault Aviation’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0236, dated November 30, 2017, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 18751 by searching for and locating Docket No. FAA–2018–0306. (2) For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3226. (3) For service information identified in this AD, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; internet http:// www.dassaultfalcon.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on April 19, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–08757 Filed 4–27–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0259; Product Identifier 2018–NE–09–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for RollsRoyce Corporation (RRC) AE 2100D2A and AE 2100D3 model turboprop engines and AE 3007A2 model turbofan engines. This proposed AD was prompted by the possibility of a lowcycle fatigue failure on certain turbine wheels. This proposed AD would require removing the affected turbine wheels at the next engine shop visit or before reaching the new reduced life limit, whichever occurs first, and replacing them with parts eligible for installation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 14, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\30APP1.SGM 30APP1 18752 Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Proposed Rules • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Rolls-Royce Corporation, 450 South Meridian Street, Indianapolis, IN 46225; phone: 317– 230–3774. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238– 7759. 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–2018– 0259; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer, Chicago ACO Branch, FAA, 2300 E Devon Ave., Des Plaines, IL 60018; phone: 847–294–7836; fax: 847–294– 7834; email: kyri.zaroyiannis@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0259; Product Identifier 2018– NE–09–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We were prompted to issue this NPRM based upon a report of the discovery of steel inclusion in the production process at an RRC forging supplier. Ultrasonic inspection at the forging supplier revealed steel impurities could be introduced into turbine wheels during forging. Analysis and testing by RRC of these wheels indicated that, because of imperfections, these turbine wheels could not be operated safely up to their published life limits. The affected turbine wheels include 1st-stage gas generator turbine wheels, installed on AE 2100D2A and AE 2100D3 model turboprop engines, and 1st-stage high-pressure turbine (HPT) wheels, installed on AE 3007A2 turbofan engines. This condition, if not addressed, could result in uncontained turbine wheel release, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed RRC Alert Service Bulletin (ASB) AE 2100D2–A–72–090, Revision 1, dated July 11, 2014, and RRC ASB AE 2100D3–A–72–286, Revision 1, dated July 11, 2014 (one document, referred to herein as ‘‘RRC ASB AE 2100D2–A–72–090/AE 2100D3–A–72–286’’), and RRC ASB AE 3007A–A–72–419, Revision 2, dated December 4, 2017. RRC ASB AE 2100D2–A–72–090/AE 2100D3–A–72– 286 provides removal and replacement instructions and a new life limit for the affected 1st-stage gas generator turbine wheels installed on RRC AE 2100D2A and AE 2100D3 model turboprop engines. ASB AE 3007A–A–72–419 provides removal and replacement instructions and a new life limit for 1ststage HPT wheels installed on RRC AE 3007A2 model turbofan engines. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD requires the removal and replacement of the affected turbine wheels at the next engine shop visit or before reaching their new life limit, whichever occurs first. Costs of Compliance We estimate that this proposed AD affects nine engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Replace turbine wheels .................................. nshattuck on DSK9F9SC42PROD with PROPOSALS Action 0 work-hours × $85 per hour = $0 ................. 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. VerDate Sep<11>2014 15:05 Apr 27, 2018 Jkt 244001 Parts cost 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 $160,829 Cost per product $160,829 Cost on U.S. operators $1,447,461 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. E:\FR\FM\30APP1.SGM 30APP1 Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Proposed Rules Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Roll-Royce Corporation (Type Certificate previously held by Allison Engine Company): Docket No. FAA–2018–0259; Product Identifier 2018–NE–09–AD. (a) Comments Due Date We must receive comments by June 14, 2018. nshattuck on DSK9F9SC42PROD with PROPOSALS (b) Affected ADs None. (c) Applicability This AD applies to: (1) Rolls-Royce Corporation (RRC) AE 2100D2A turboprop engines with 1st-stage gas generator turbine wheels, part number (P/N) 23089692, with serial numbers (S/Ns) MW65898 or MW68310, installed. (2) RRC AE 2100D3 turboprop engines with 1st-stage gas generator turbine wheels, P/N 23088906, with S/Ns MW65895, MW65896, VerDate Sep<11>2014 15:05 Apr 27, 2018 Jkt 244001 MW65900, MW65901, MW65903, MW68305, MW68306, MW68307, MW68312, MW68314, MW68316, MW68318, or MW68319 installed. (3) RRC AE 3007A2 turbofan engines with 1st-stage high-pressure turbine (HPT) wheels, P/N 23088906, with S/Ns MW65894, MW68303, or MW68315 installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine section. (e) Unsafe Condition This AD was prompted by the possibility of steel inclusions in the turbine wheel forging. We are proposing this AD to prevent a low-cycle fatigue failure of a 1st-stage gas generator turbine wheel or 1st-stage HPT wheel. The unsafe condition, if not addressed, could result in uncontained turbine wheel release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Remove the affected 1st-stage gas generator turbine wheel and replace with a part eligible for installation at the next engine shop visit or before exceeding the life limit of 4,800 engine cycles, whichever occurs first, in accordance with the Accomplishment Instructions, Paragraph 2, of RRC Alert Service Bulletin (ASB) AE 2100D2–A–72–090, Revision 1, dated July 11, 2014, and RRC ASB AE 2100D3–A–72–286, Revision 1, dated July 11, 2014 (one document). (2) Remove the affected 1st-stage HPT wheel and replace with a part eligible for installation at the next engine shop visit or before exceeding the life limit of 5,600 engine cycles, whichever occurs first, in accordance with the Accomplishment Instructions, Paragraph 2, of RRC ASB AE 3007A–A–72– 419, Revision 2, dated December 4, 2017. (h) 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 is not an engine shop visit. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Chicago ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j)(1) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 18753 of the local flight standards district office/ certificate holding district office. (j) Related Information (1) For more information about this AD, contact Kyri Zaroyiannis, Aerospace Engineer, Chicago ACO Branch, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847–294–7836; fax: 847–294–7834; email: kyri.zaroyiannis@faa.gov. (2) For service information identified in this AD, contact Rolls-Royce Corporation, 450 South Meridian Street, Indianapolis, IN 46225; phone: 317–230–3774. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7759. Issued in Burlington, MA, on April 25, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–09012 Filed 4–27–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0359; Product Identifier 2018–NM–040–AD] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Dassault Aviation Model MYSTERE– FALCON 900 airplanes. This proposed AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. This proposed AD would require revising the maintenance or inspection program, as applicable, to incorporate new and more restrictive maintenance requirements and airworthiness limitations. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 14, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. SUMMARY: E:\FR\FM\30APP1.SGM 30APP1

Agencies

[Federal Register Volume 83, Number 83 (Monday, April 30, 2018)]
[Proposed Rules]
[Pages 18751-18753]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09012]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0259; Product Identifier 2018-NE-09-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Rolls-Royce Corporation (RRC) AE 2100D2A and AE 2100D3 model turboprop 
engines and AE 3007A2 model turbofan engines. This proposed AD was 
prompted by the possibility of a low-cycle fatigue failure on certain 
turbine wheels. This proposed AD would require removing the affected 
turbine wheels at the next engine shop visit or before reaching the new 
reduced life limit, whichever occurs first, and replacing them with 
parts eligible for installation. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 14, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 18752]]

     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Rolls-
Royce Corporation, 450 South Meridian Street, Indianapolis, IN 46225; 
phone: 317-230-3774. You may view this service information at the FAA, 
Engine and Propeller Standards Branch, 1200 District Avenue, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call 781-238-7759.

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-2018-
0259; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer, 
Chicago ACO Branch, FAA, 2300 E Devon Ave., Des Plaines, IL 60018; 
phone: 847-294-7836; fax: 847-294-7834; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0259; 
Product Identifier 2018-NE-09-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    We were prompted to issue this NPRM based upon a report of the 
discovery of steel inclusion in the production process at an RRC 
forging supplier. Ultrasonic inspection at the forging supplier 
revealed steel impurities could be introduced into turbine wheels 
during forging. Analysis and testing by RRC of these wheels indicated 
that, because of imperfections, these turbine wheels could not be 
operated safely up to their published life limits. The affected turbine 
wheels include 1st-stage gas generator turbine wheels, installed on AE 
2100D2A and AE 2100D3 model turboprop engines, and 1st-stage high-
pressure turbine (HPT) wheels, installed on AE 3007A2 turbofan engines.
    This condition, if not addressed, could result in uncontained 
turbine wheel release, damage to the engine, and damage to the 
airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed RRC Alert Service Bulletin (ASB) AE 2100D2-A-72-090, 
Revision 1, dated July 11, 2014, and RRC ASB AE 2100D3-A-72-286, 
Revision 1, dated July 11, 2014 (one document, referred to herein as 
``RRC ASB AE 2100D2-A-72-090/AE 2100D3-A-72-286''), and RRC ASB AE 
3007A-A-72-419, Revision 2, dated December 4, 2017. RRC ASB AE 2100D2-
A-72-090/AE 2100D3-A-72-286 provides removal and replacement 
instructions and a new life limit for the affected 1st-stage gas 
generator turbine wheels installed on RRC AE 2100D2A and AE 2100D3 
model turboprop engines. ASB AE 3007A-A-72-419 provides removal and 
replacement instructions and a new life limit for 1st-stage HPT wheels 
installed on RRC AE 3007A2 model turbofan engines. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD requires the removal and replacement of the 
affected turbine wheels at the next engine shop visit or before 
reaching their new life limit, whichever occurs first.

Costs of Compliance

    We estimate that this proposed AD affects nine engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace turbine wheels................  0 work-hours x $85 per          $160,829        $160,829      $1,447,461
                                         hour = $0.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 18753]]

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

 Roll-Royce Corporation (Type Certificate previously held by Allison 
Engine Company): Docket No. FAA-2018-0259; Product Identifier 2018-
NE-09-AD.

(a) Comments Due Date

    We must receive comments by June 14, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to:
    (1) Rolls-Royce Corporation (RRC) AE 2100D2A turboprop engines 
with 1st-stage gas generator turbine wheels, part number (P/N) 
23089692, with serial numbers (S/Ns) MW65898 or MW68310, installed.
    (2) RRC AE 2100D3 turboprop engines with 1st-stage gas generator 
turbine wheels, P/N 23088906, with S/Ns MW65895, MW65896, MW65900, 
MW65901, MW65903, MW68305, MW68306, MW68307, MW68312, MW68314, 
MW68316, MW68318, or MW68319 installed.
    (3) RRC AE 3007A2 turbofan engines with 1st-stage high-pressure 
turbine (HPT) wheels, P/N 23088906, with S/Ns MW65894, MW68303, or 
MW68315 installed.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by the possibility of steel inclusions in 
the turbine wheel forging. We are proposing this AD to prevent a 
low-cycle fatigue failure of a 1st-stage gas generator turbine wheel 
or 1st-stage HPT wheel. The unsafe condition, if not addressed, 
could result in uncontained turbine wheel release, damage to the 
engine, and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Remove the affected 1st-stage gas generator turbine wheel 
and replace with a part eligible for installation at the next engine 
shop visit or before exceeding the life limit of 4,800 engine 
cycles, whichever occurs first, in accordance with the 
Accomplishment Instructions, Paragraph 2, of RRC Alert Service 
Bulletin (ASB) AE 2100D2-A-72-090, Revision 1, dated July 11, 2014, 
and RRC ASB AE 2100D3-A-72-286, Revision 1, dated July 11, 2014 (one 
document).
    (2) Remove the affected 1st-stage HPT wheel and replace with a 
part eligible for installation at the next engine shop visit or 
before exceeding the life limit of 5,600 engine cycles, whichever 
occurs first, in accordance with the Accomplishment Instructions, 
Paragraph 2, of RRC ASB AE 3007A-A-72-419, Revision 2, dated 
December 4, 2017.

(h) 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 is not an 
engine shop visit.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Chicago ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (j)(1) 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.

(j) Related Information

    (1) For more information about this AD, contact Kyri 
Zaroyiannis, Aerospace Engineer, Chicago ACO Branch, FAA, 2300 E. 
Devon Ave., Des Plaines, IL 60018; phone: 847-294-7836; fax: 847-
294-7834; email: [email protected].
    (2) For service information identified in this AD, contact 
Rolls-Royce Corporation, 450 South Meridian Street, Indianapolis, IN 
46225; phone: 317-230-3774. You may view this service information at 
the FAA, Engine and Propeller Standards Branch, 1200 District 
Avenue, Burlington, MA. For information on the availability of this 
material at the FAA, call 781-238-7759.

    Issued in Burlington, MA, on April 25, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-09012 Filed 4-27-18; 8:45 am]
 BILLING CODE 4910-13-P