Document ID: FAA-2016-6744-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Rolls-Royce plc Turbofan Engines
Posted Date: 2016-07-26T04:00Z

[Federal Register Volume 81, Number 143 (Tuesday, July 26, 2016)]
[Proposed Rules]
[Pages 48724-48725]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-17160]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 81, No. 143 / Tuesday, July 26, 2016 / 
Proposed Rules  

[[Page 48724]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6744; Directorate Identifier 2016-NE-12-AD]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, 
RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-
Trent 892B-17, and RB211-Trent 895-17 turbofan engines that have not 
incorporated RR modification 72-J195 in production or RR Service 
Bulletin (SB) RB.211-72-J195. This proposed AD was prompted by 
inspection of RR Trent 800 engines returned from service that revealed 
flame erosion and axial cracking on the aft face of the stage 3 disk 
rim of the high-pressure compressor (HPC) stage 1-4 rotor disks shaft. 
This proposed AD would require machining the HPC stage 3 inner shroud, 
inspecting the HPC stage 1-4 rotor disks shaft, and replacing the HPC 
stage 1-4 rotor disks shaft if found defective. We are proposing this 
AD to prevent uncontained failure of the HPC stage 1-4 rotor disks 
shaft, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this NPRM by September 26, 2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.
    For service information identified in this NPRM, contact Rolls-
Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 
8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://customers.rolls-royce.com/public/rollsroycecare. You may view this 
service information at the FAA, Engine & Propeller Directorate, 1200 
District Avenue, 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.gov by searching for and locating Docket No. FAA-2016-
6744; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the mandatory continuing airworthiness 
information (MCAI), the regulatory evaluation, any comments received, 
and other information. The address for the Docket Office (phone: 800-
647-5527) is in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781-
238-7199; email: robert.green@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6744; 
Directorate Identifier 2016-NE-12-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 based on 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 
with FAA personnel concerning this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2016-0078, dated April 20, 2016 (corrected April 27, 2016) (referred 
to hereinafter as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Inspection of Trent 800 engines returned from service revealed 
flame eroded areas and axial cracking on the rear Stage 3 disc of 
the High Pressure Compressor (HPC) Stage 1-4 drum. This is 
considered to be the result of a localised fire originating from an 
excessive rub at the stage 3-4 forward seal fin.
    This condition, if not detected and corrected, could lead to an 
uncontained engine failure and release of high energy debris, 
possibly resulting in damage to the aeroplane and injury to 
occupants.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2016-6744.

Related Service Information Under 1 CFR Part 51

    RR has issued SB RB.211-72-J195, dated February 26, 2016. The SB 
describes procedures to machine the HPC stage 3 inner shroud and to 
inspect the HPC stage 1-4 rotor disks shaft.
    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 and Requirements of This Proposed AD

    This product has been approved by the aviation authority of the 
United Kingdom, and is approved for operation in the United States. 
Pursuant to our bilateral agreement with the European Community, EASA 
has notified us of the unsafe condition described in the MCAI. We are 
proposing this AD

[[Page 48725]]

because we evaluated all information provided by EASA and determined 
the unsafe condition exists and is likely to exist or develop on other 
products of the same type design. This proposed AD would require 
machining the HPC stage 3 inner shroud, inspecting the HPC stage 1-4 
rotor disks shaft, and replacing the HPC stage 1-4 rotor disks shaft if 
found defective.

Costs of Compliance

    We estimate that this proposed AD affects 125 engines installed on 
airplanes of U.S. registry. We estimate it would take 8 hours to comply 
with the inspection required by this proposed AD. Machining the HPC 
stage 3 inner shroud is required during routine overhaul; therefore, no 
additional time is needed for this action. The average labor rate is 
$85 per hour. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $85,000.

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 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 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.

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):

Rolls-Royce plc: Docket No. FAA-2016-6744; Directorate Identifier 
2016-NE-12-AD.

(a) Comments Due Date

    We must receive comments by September 26, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, 
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan 
engines that have not incorporated RR modification 72-J195, in 
production; or RR Service Bulletin RB.211-72-J195, dated February 
26, 2016, in service.

(d) Reason

    This AD was prompted by inspection of RR Trent 800 series 
engines returned from service that revealed flame erosion and axial 
cracking on the aft face of the stage 3 disk rim of the high-
pressure compressor (HPC) stage 1-4 rotor disks shaft. We are 
issuing this AD to prevent uncontained failure of the HPC stage 1-4 
rotor disks shaft, damage to the engine, and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Before exceeding 5,000 duty cycles, since new or since last 
HPC stage 1-4 rotor disks shaft piece-part inspection, whichever 
occurs later, do the following:
    (i) Perform dimensional, fluorescent penetrant, and visual 
inspections of the HPC stage 1-4 rotor disks shaft forward stage 3-4 
seal fin and aft face of the stage 3 disk rim for wear, cracks, and 
flame erosion. Any findings of wear, cracks, or flame erosion 
constitute a failure of the HPC stage 1-4 rotor disks shaft.
    (ii) Machine the HPC stage 3 inner shroud to the dimensions 
shown in Figure 1 of RR Service Bulletin (SB) RB.211-72-J195, dated 
February 26, 2016.
    (2) If the HPC stage 1-4 rotor disks shaft fails the inspections 
required by paragraph (e)(1)(i) of this AD, remove and replace with 
a part eligible for installation before further flight.

(f) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: ANE-AD-AMOC@faa.gov.

(g) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7754; fax: 781-238-7199; email: robert.green@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2016-0078, 
dated April 20, 2016 (corrected April 27, 2016), for more 
information. You may examine the MCAI in the AD docket on the 
Internet at http://www.regulations.gov by searching for and locating 
it in Docket No. FAA-2016-6744.
    (3) RR SB RB.211-72-J195, dated February 26, 2016, can be 
obtained from RR, using the contact information in paragraph (g)(4) 
of this proposed AD.
    (4) For service information identified in this proposed AD, 
contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, 
Derby, England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-
1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://customers.rolls-royce.com/public/rollsroycecare.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on July 13, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-17160 Filed 7-25-16; 8:45 am]
BILLING CODE 4910-13-P