Document ID: FAA-2018-0259-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Rolls-Royce Corporation Engines
Posted Date: 2018-04-30T04:00Z

[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]

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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).

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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.
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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