82 FR 40681 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 165 (August 28, 2017)

We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent XWB-75, Trent XWB-79, Trent XWB-79B, and Trent XWB-84 turbofan engines. This AD requires inspection of the intermediate-pressure (IP) turbine stage 2 locking plates. This AD was prompted by a report of several IP turbine stage 2 locking plates cracked during module assembly. We are issuing this AD to correct the unsafe condition on these products.

[Federal Register Volume 82, Number 165 (Monday, August 28, 2017)]
[Rules and Regulations]
[Pages 40681-40683]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-18133]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0652; Product Identifier 2017-NE-18-AD; Amendment 
39-18997; AD 2017-17-07]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Rolls-Royce plc (RR) Trent XWB-75, Trent XWB-79, Trent XWB-79B, and 
Trent XWB-84 turbofan engines. This AD requires inspection of the 
intermediate-pressure (IP) turbine stage 2 locking plates. This AD was 
prompted by a report of several IP turbine stage 2 locking plates 
cracked during module assembly. We are issuing this AD to correct the 
unsafe condition on these products.

DATES: This AD becomes effective September 12, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
12, 2017.
    We must receive comments on this AD by October 12, 2017.

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: 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 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. You may view this 
service information at the FAA, Engine and Propeller Standards Branch, 
Policy and Innovation Division, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the FAA, 
call 781-238-7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0652.

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-2017-
0652; 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 AD, the mandatory continuing airworthiness information 
(MCAI), 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, FAA, 
ECO Branch, Compliance and Airworthiness Division, 1200 District 
Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; 
email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2017-0652; Directorate 
Identifier 2017-NE-18-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD 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 
with FAA personnel concerning this AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2017-0088, dated May 16, 2017 (referred to hereinafter as ``the 
MCAI''), to correct an

[[Page 40682]]

unsafe condition for the specified products. The MCAI states:

    During module assembly, cracking was observed on several 
intermediate pressure (IP) turbine stage 2 locking plates from one 
particular supplier. These locking plates form part of the IP 
turbine stage 2 assembly, providing axial retention of the IP 
turbine stage 2 blades onto the disk, and constitute a seal for the 
local air system. These locking plates are pre-bent during 
manufacture and are pressed flat during installation such that they 
fit between grooves in the IP stage 2 disk and blades. There are 16 
locking plates, Part Number (P/N) KH12922 or P/N KH16183, installed 
on an IP turbine stage 2 assembly. It is possible that parts, 
manufactured by this supplier, may have cracked during module 
assembly, without those cracks being detectable prior to release to 
service of an engine. Propagation of cracks during engine operation 
may lead to loss of a locking plate. Missing locking plates will 
allow hot gas ingestion which will locally overheat the blade 
retention features of the disk.
    This condition, if not detected and corrected, could lead to 
accelerated fatigue of the blade retention features of the disk and 
release of one or more IP turbine stage 2 blades, possibly resulting 
in high energy uncontained debris release from the engine, with 
consequent damage to, and reduced control of, the aeroplane.

    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-2017-0652.

Related Service Information Under 1 CFR Part 51

    RR has issued Alert Non-Modification Service Bulletin (NMSB) Trent 
XWB 72-AJ738, dated April 11, 2017. The NMSB describes procedures to 
inspect the IP turbine stage 2 locking plates. 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 AD

    This product has been approved by the aviation authority of EASA, 
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 and service information 
referenced above. We are issuing this AD 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 AD requires inspection of the IP turbine stage 2 locking 
plates.

FAA's Determination of the Effective Date

    No domestic operators use this product. Therefore, we find that 
notice and opportunity for prior public comment are unnecessary and 
that good cause exists for making this amendment effective in less than 
30 days.

Costs of Compliance

    We estimate that this AD affects 0 engine 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
----------------------------------------------------------------------------------------------------------------
Inspection.........................  3 work-hours x $85 per hour              $0            $255              $0
                                      = $255.
----------------------------------------------------------------------------------------------------------------

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.
    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 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    We 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 this AD:
    (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.

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 adding the following new airworthiness 
directive (AD):

2017-17-07 Rolls-Royce plc: Amendment 39-18997; Docket No. FAA-2017-
0652; Product Identifier 2017-NE-18-AD.

(a) Effective Date

    This AD is effective September 12, 2017.

[[Page 40683]]

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) Trent XWB-75, Trent XWB-
79, Trent XWB-79B, and Trent XWB-84 turbofan engines with an engine 
serial number (S/N) listed in Appendix 1 of RR Alert Non-
Modification Service Bulletin (NMSB) Trent XWB 72-AJ738, dated April 
11, 2017, and with intermediate-pressure (IP) turbine stage 2 
locking plates, part number (P/N) KH12922 or KH16183, installed.

(d) Subject

    Joint Aircraft System Component (JASC) 7250, Turbine/Turboprop 
Engine/Turbine Section.

(e) Reason

    This AD was prompted by a report of several IP turbine stage 2 
locking plates cracked during module assembly. We are issuing this 
AD to prevent failure of the IP turbine stage 2 locking plates, 
uncontained release of the IP turbine stage 2 blades, damage to the 
engine, and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Inspect the IP turbine stage 2 locking plates on-wing before 
exceeding 750 engine flight cycles (FCs) since new, or within 100 
engine FCs after the effective date of this AD, whichever occurs 
later. Use the Accomplishment Instructions, paragraph 3.A., of RR 
Alert NMSB Trent XWB 72-AJ738, dated April 11, 2017, to do the 
inspection.
    (2) Thereafter, re-inspect the IP turbine stage 2 locking plates 
at intervals not to exceed 750 engine FCs since the last locking 
plate inspection. Use the Accomplishment Instructions, paragraph 
3.A., of RR Alert NMSB Trent XWB 72-AJ738, dated April 11, 2017, to 
do the inspection.
    (i) If all IP turbine stage 2 locking plates installed on the 
engine have an S/N beginning with 20452, or are not marked with an 
S/N, the repetitive inspection required by paragraph (f)(2) of this 
AD is not required.
    (ii) If one or more IP turbine stage 2 locking plates are 
missing, remove the engine from service within the compliance times 
specified in the Accomplishment Instructions, paragraph 3.A.(3), of 
RR Alert NMSB Trent XWB 72-AJ738, dated April 11, 2017.
    (3) Inspect the IP turbine stage 2 locking plates during the 
next engine shop visit (ESV) after the effective date of this AD.
    (i) Use the Accomplishment Instructions, paragraph 3.B., of RR 
Alert NMSB Trent XWB 72-AJ738, dated April 11, 2017, to do this 
inspection. This in-shop inspection may be substituted for the on-
wing inspection required by paragraphs (f)(1) and (2) of this AD.
    (ii) If one or more IP turbine stage 2 locking plates are 
missing, use the acceptance criteria in the Accomplishment 
Instructions, paragraph 3.B.(3), of RR Alert NMSB Trent XWB 72-AJ738 
dated April 11, 2017, to disposition the engine.

(g) Installation Prohibition

    After the effective date of this AD, do not install an engine 
unless the IP turbine stage 2 locking plates were inspected using 
the Accomplishment Instructions, paragraph 3.A. or 3.B., of RR Alert 
NMSB Trent XWB 72-AJ738, dated April 11, 2017.

(h) Definition

    For the purpose of this AD, an ESV is when the engine is subject 
to a serviceability check and repair, rebuild, or overhaul.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, FAA, ECO Branch, Compliance and Airworthiness 
Division, 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: 
[email protected].
    (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 Robert Green, 
Aerospace Engineer, FAA, ECO Branch, Compliance and Airworthiness 
Division, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7754; fax: 781-238-7199; email: [email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2017-0088, 
dated May 16, 2017, 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-2017-0642.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Rolls-Royce plc (RR) Alert Non-Modification Service Bulletin 
Trent XWB 72-AJ738, dated April 11, 2017.
    (ii) Reserved.
    (3) For RR service information identified in this 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.
    (4) You may view this service information at FAA, Engine and 
Propeller Standards Branch, Policy and Innovation Division, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call 781-238-7125.
    (5) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on August 16, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-18133 Filed 8-25-17; 8:45 am]
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