82_FR_40846 82 FR 40681 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines

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)

Page Range40681-40683
FR Document2017-18133

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 Issue 165 (Monday, August 28, 2017) 
[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]
BILLING CODE 4910-13-P

Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40681 (3) Service information identified in this DEPARTMENT OF TRANSPORTATION availability of this material at the FAA, AD that is not incorporated by reference is call 781–238–7125. It is also available available at the addresses specified in Federal Aviation Administration on the Internet at http:// paragraphs (v)(5) and (v)(6) of this AD. www.regulations.gov by searching for (v) Material Incorporated by Reference 14 CFR Part 39 and locating Docket No. FAA–2017– [Docket No. FAA–2017–0652; Product 0652. (1) The Director of the Federal Register approved the incorporation by reference Identifier 2017–NE–18–AD; Amendment 39– Examining the AD Docket 18997; AD 2017–17–07] (IBR) of the service information listed in this You may examine the AD docket on paragraph under 5 U.S.C. 552(a) and 1 CFR RIN 2120–AA64 the Internet at http:// part 51. www.regulations.gov by searching for (2) You must use this service information Airworthiness Directives; Rolls-Royce and locating Docket No. FAA–2017– as applicable to do the actions required by plc Turbofan Engines 0652; or in person at the Docket this AD, unless this AD specifies otherwise. AGENCY: Federal Aviation Operations office between 9 a.m. and 5 (3) The following service information was Administration (FAA), DOT. p.m., Monday through Friday, except approved for IBR on October 2, 2017. ACTION: Final rule; request for Federal holidays. The AD docket (i) Airbus Service Bulletin A320–34–1415, comments. contains this AD, the mandatory Revision 04, dated July 30, 2015. (ii) Airbus Service Bulletin A320–34–1444, continuing airworthiness information SUMMARY: We are adopting a new (MCAI), regulatory evaluation, any Revision 01, dated March 17, 2011. airworthiness directive (AD) for certain comments received, and other (iii) Airbus Service Bulletin A320–34– Rolls-Royce plc (RR) Trent XWB–75, information. The address for the Docket 1564, Revision 01, dated August 26, 2013. Trent XWB–79, Trent XWB–79B, and Office (phone: 800–647–5527) is in the (iv) Airbus Service Bulletin A320–34– 1610, Revision 01, dated July 30, 2015. Trent XWB–84 turbofan engines. This ADDRESSES section. Comments will be (v) Thales Service Bulletin C16291A–34– AD requires inspection of the available in the AD docket shortly after 007, Revision 04, dated October 11, 2012. intermediate-pressure (IP) turbine stage receipt. (vi) Thales Service Bulletin C16291A–34– 2 locking plates. This AD was prompted FOR FURTHER INFORMATION CONTACT: 007, Revision 03, dated April 10, 2012. by a report of several IP turbine stage 2 Robert Green, Aerospace Engineer, FAA, (vii) Thales Service Bulletin C16291A–34– locking plates cracked during module ECO Branch, Compliance and 007, Revision 02, dated December 16, 2011. assembly. We are issuing this AD to Airworthiness Division, 1200 District (viii) Thales Service Bulletin C16291A–34– correct the unsafe condition on these Avenue, Burlington, MA 01803; phone: 007, Revision 01, dated December 03, 2009. products. 781–238–7754; fax: 781–238–7199; (4) The following service information was DATES: This AD becomes effective email: robert.green@faa.gov. approved for IBR on November 6, 2013, September 12, 2017. SUPPLEMENTARY INFORMATION: Amendment 39–17591 (78 FR 60667, October The Director of the Federal Register 2, 2013). approved the incorporation by reference Comments Invited (i) Airbus Mandatory Service Bulletin of a certain publication listed in this AD This AD is a final rule that involves A320–34–1564, including Appendix 01, as of September 12, 2017. requirements affecting flight safety, and dated January 25, 2013. We must receive comments on this we did not precede it by notice and (ii) Reserved. AD by October 12, 2017. opportunity for public comment. We (5) For service information identified in ADDRESSES: You may send comments by invite you to send any written relevant this AD, contact Airbus, Airworthiness any of the following methods: data, views, or arguments about this AD. Office—EIAS, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to Send your comments to an address Bellonte, 31707 Blagnac Cedex, France; http://www.regulations.gov. Follow the listed under the ADDRESSES section. telephone +33 5 61 93 36 96; fax +33 5 61 instructions for submitting comments. Include ‘‘Docket No. FAA–2017–0652; 93 44 51; email account.airworth-eas@ • Mail: U.S. Department of Directorate Identifier 2017–NE–18–AD’’ airbus.com; Internet http://www.airbus.com. Transportation, 1200 New Jersey at the beginning of your comments. We (6) You may view this service information Avenue SE., West Building Ground specifically invite comments on the at the FAA, Transport Standards Branch, Floor, Room W12–140, Washington, DC overall regulatory, economic, 1601 Lind Avenue SW., Renton, WA. For 20590–0001. environmental, and energy aspects of information on the availability of this • Hand Delivery: Deliver to Mail this AD. We will consider all comments material at the FAA, call 425–227–1221. (7) You may view this service information address above between 9 a.m. and 5 received by the closing date and may that is incorporated by reference at the p.m., Monday through Friday, except amend this AD because of those National Archives and Records Federal holidays. comments. Administration (NARA). For information on • Fax: 202–493–2251. We will post all comments we the availability of this material at NARA, call For service information identified in receive, without change, to http:// 202–741–6030, or go to: http:// this AD, contact Rolls-Royce plc, www.regulations.gov, including any www.archives.gov/federal-register/cfr/ibr- Corporate Communications, P.O. Box personal information you provide. We locations.html. 31, Derby, England, DE24 8BJ; phone: will also post a report summarizing each 011–44–1332–242424; fax: 011–44– substantive verbal contact with FAA Issued in Renton, Washington, on August 1332–249936; email: http://www.rolls- personnel concerning this AD. asabaliauskas on DSKBBXCHB2PROD with RULES 2, 2017. royce.com/contact/civil_team.jsp; Jeffrey E. Duven, Internet: https://customers.rolls- Discussion Director, System Oversight Division, Aircraft royce.com/public/rollsroycecare. You The European Aviation Safety Agency Certification Service. may view this service information at the (EASA), which is the Technical Agent [FR Doc. 2017–16860 Filed 8–25–17; 8:45 am] FAA, Engine and Propeller Standards for the Member States of the European BILLING CODE P Branch, Policy and Innovation Division, Community, has issued EASA AD 2017– 1200 District Avenue, Burlington, MA 0088, dated May 16, 2017 (referred to 01803. For information on the hereinafter as ‘‘the MCAI’’), to correct an VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1

40682 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations unsafe condition for the specified with consequent damage to, and reduced agreement with the European products. The MCAI states: control of, the aeroplane. Community, EASA has notified us of During module assembly, cracking was You may obtain further information the unsafe condition described in the observed on several intermediate pressure by examining the MCAI in the AD MCAI and service information (IP) turbine stage 2 locking plates from one docket on the Internet at http:// referenced above. We are issuing this particular supplier. These locking plates form www.regulations.gov by searching for AD because we evaluated all part of the IP turbine stage 2 assembly, and locating Docket No. FAA–2017– information provided by EASA and providing axial retention of the IP turbine determined the unsafe condition exists stage 2 blades onto the disk, and constitute 0652. a seal for the local air system. These locking and is likely to exist or develop on other Related Service Information Under 1 products of the same type design. This plates are pre-bent during manufacture and CFR Part 51 are pressed flat during installation such that AD requires inspection of the IP turbine they fit between grooves in the IP stage 2 disk RR has issued Alert Non-Modification stage 2 locking plates. and blades. There are 16 locking plates, Part Service Bulletin (NMSB) Trent XWB Number (P/N) KH12922 or P/N KH16183, FAA’s Determination of the Effective 72–AJ738, dated April 11, 2017. The Date installed on an IP turbine stage 2 assembly. NMSB describes procedures to inspect It is possible that parts, manufactured by this No domestic operators use this supplier, may have cracked during module the IP turbine stage 2 locking plates. assembly, without those cracks being This service information is reasonably product. Therefore, we find that notice detectable prior to release to service of an available because the interested parties and opportunity for prior public engine. Propagation of cracks during engine have access to it through their normal comment are unnecessary and that good operation may lead to loss of a locking plate. course of business or by the means cause exists for making this amendment Missing locking plates will allow hot gas identified in the ADDRESSES section. effective in less than 30 days. ingestion which will locally overheat the blade retention features of the disk. FAA’s Determination and Requirements Costs of Compliance This condition, if not detected and of This AD We estimate that this AD affects 0 corrected, could lead to accelerated fatigue of the blade retention features of the disk and This product has been approved by engine installed on airplanes of U.S. release of one or more IP turbine stage 2 the aviation authority of EASA, and is registry. blades, possibly resulting in high energy approved for operation in the United We estimate the following costs to uncontained debris release from the engine, States. Pursuant to our bilateral comply with this AD: ESTIMATED COSTS Cost per Cost on Action Labor cost Parts cost product U.S. operators Inspection ................................ 3 work-hours × $85 per hour = $255 ..................................... $0 $255 $0 Authority for This Rulemaking Division, but during this transition under the criteria of the Regulatory period, the Executive Director has Flexibility Act. Title 49 of the United States Code delegated the authority to issue ADs specifies the FAA’s authority to issue List of Subjects in 14 CFR Part 39 applicable to engines, propellers, and rules on aviation safety. Subtitle I, associated appliances to the Manager, Air transportation, Aircraft, Aviation section 106, describes the authority of Engine and Propeller Standards Branch, safety, Incorporation by reference, the FAA Administrator. ‘‘Subtitle VII: Policy and Innovation Division. Safety. Aviation Programs,’’ describes in more detail the scope of the Agency’s Regulatory Findings Adoption of the Amendment authority. We determined that this AD will not We are issuing this rulemaking under have federalism implications under Accordingly, under the authority the authority described in ‘‘Subtitle VII, Executive Order 13132. This AD will delegated to me by the Administrator, Part A, Subpart III, Section 44701: not have a substantial direct effect on the FAA amends 14 CFR part 39 as General requirements.’’ Under that the States, on the relationship between follows: section, Congress charges the FAA with the national government and the States, promoting safe flight of civil aircraft in PART 39—AIRWORTHINESS or on the distribution of power and DIRECTIVES air commerce by prescribing regulations responsibilities among the various for practices, methods, and procedures levels of government. the Administrator finds necessary for For the reasons discussed above, I ■ 1. The authority citation for part 39 safety in air commerce. This regulation certify this AD: continues to read as follows: is within the scope of that authority (1) Is not a ‘‘significant regulatory Authority: 49 U.S.C. 106(g), 40113, 44701. because it addresses an unsafe condition action’’ under Executive Order 12866, that is likely to exist or develop on § 39.13 [Amended] (2) Is not a ‘‘significant rule’’ under products identified in this rulemaking the DOT Regulatory Policies and ■ 2. The FAA amends § 39.13 by adding asabaliauskas on DSKBBXCHB2PROD with RULES action. Procedures (44 FR 11034, February 26, the following new airworthiness This AD is issued in accordance with 1979), directive (AD): authority delegated by the Executive (3) Will not affect intrastate aviation Director, Aircraft Certification Service, 2017–17–07 Rolls-Royce plc: Amendment in Alaska to the extent that it justifies 39–18997; Docket No. FAA–2017–0652; as authorized by FAA Order 8000.51C. making a regulatory distinction, and Product Identifier 2017–NE–18–AD. In accordance with that order, issuance (4) Will not have a significant of ADs is normally a function of the economic impact, positive or negative, (a) Effective Date Compliance and Airworthiness on a substantial number of small entities This AD is effective September 12, 2017. VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1

Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations 40683 (b) Affected ADs paragraph 3.B.(3), of RR Alert NMSB Trent the availability of this material at NARA, call None. XWB 72–AJ738 dated April 11, 2017, to 202–741–6030, or go to: http:// disposition the engine. www.archives.gov/federal-register/cfr/ibr- (c) Applicability locations.html. (g) Installation Prohibition This AD applies to Rolls-Royce plc (RR) Issued in Burlington, Massachusetts, on Trent XWB–75, Trent XWB–79, Trent XWB– After the effective date of this AD, do not August 16, 2017. 79B, and Trent XWB–84 turbofan engines install an engine unless the IP turbine stage 2 locking plates were inspected using the Robert J. Ganley, with an engine serial number (S/N) listed in Appendix 1 of RR Alert Non-Modification Accomplishment Instructions, paragraph 3.A. Manager, Engine and Propeller Standards Service Bulletin (NMSB) Trent XWB 72– or 3.B., of RR Alert NMSB Trent XWB 72– Branch, Aircraft Certification Service. AJ738, dated April 11, 2017, and with AJ738, dated April 11, 2017. [FR Doc. 2017–18133 Filed 8–25–17; 8:45 am] intermediate-pressure (IP) turbine stage 2 (h) Definition BILLING CODE 4910–13–P locking plates, part number (P/N) KH12922 For the purpose of this AD, an ESV is when or KH16183, installed. the engine is subject to a serviceability check (d) Subject and repair, rebuild, or overhaul. DEPARTMENT OF TRANSPORTATION Joint Aircraft System Component (JASC) (i) Alternative Methods of Compliance Federal Aviation Administration 7250, Turbine/Turboprop Engine/Turbine (AMOCs) Section. (1) The Manager, FAA, ECO Branch, 14 CFR Part 39 (e) Reason Compliance and Airworthiness Division, may approve AMOCs for this AD. Use the [Docket No. FAA–2017–0472; Product This AD was prompted by a report of Identifier 2016–NM–148–AD; Amendment several IP turbine stage 2 locking plates procedures found in 14 CFR 39.19 to make your request. You may email your request to: 39–19002; AD 2017–17–12] cracked during module assembly. We are ANE-AD-AMOC@faa.gov. RIN 2120–AA64 issuing this AD to prevent failure of the IP (2) Before using any approved AMOC, turbine stage 2 locking plates, uncontained notify your appropriate principal inspector, Airworthiness Directives; Airbus release of the IP turbine stage 2 blades, or lacking a principal inspector, the manager Airplanes damage to the engine, and damage to the of the local flight standards district office/ airplane. certificate holding district office. AGENCY: Federal Aviation (f) Compliance (j) Related Information Administration (FAA), Department of Comply with this AD within the Transportation (DOT). (1) For more information about this AD, compliance times specified, unless already ACTION: Final rule. contact Robert Green, Aerospace Engineer, done. FAA, ECO Branch, Compliance and (1) Inspect the IP turbine stage 2 locking SUMMARY: We are adopting a new Airworthiness Division, 1200 District plates on-wing before exceeding 750 engine Avenue, Burlington, MA 01803; phone: 781– airworthiness directive (AD) for all flight cycles (FCs) since new, or within 100 238–7754; fax: 781–238–7199; email: Airbus Model A310–203, –221, –222, engine FCs after the effective date of this AD, robert.green@faa.gov. –304, –322, –324, and –325 airplanes. whichever occurs later. Use the (2) Refer to MCAI European Aviation This AD was prompted by an evaluation Accomplishment Instructions, paragraph Safety Agency AD 2017–0088, dated May 16, by the design approval holder indicating 3.A., of RR Alert NMSB Trent XWB 72– 2017, for more information. You may that the wing bottom skin at the main AJ738, dated April 11, 2017, to do the examine the MCAI in the AD docket on the inspection. landing gear (MLG) reinforcing plate is Internet at http://www.regulations.gov by subject to widespread fatigue damage (2) Thereafter, re-inspect the IP turbine searching for and locating it in Docket No. stage 2 locking plates at intervals not to (WFD). This AD requires a modification FAA–2017–0642. exceed 750 engine FCs since the last locking of the wing bottom skin at the MLG plate inspection. Use the Accomplishment (k) Material Incorporated by Reference reinforcing plate. We are issuing this AD Instructions, paragraph 3.A., of RR Alert (1) The Director of the Federal Register to address the unsafe condition on these NMSB Trent XWB 72–AJ738, dated April 11, approved the incorporation by reference products. 2017, to do the inspection. (IBR) of the service information listed in this DATES: This AD is effective October 2, (i) If all IP turbine stage 2 locking plates paragraph under 5 U.S.C. 552(a) and 1 CFR installed on the engine have an S/N 2017. part 51. The Director of the Federal Register beginning with 20452, or are not marked (2) You must use this service information with an S/N, the repetitive inspection as applicable to do the actions required by approved the incorporation by reference required by paragraph (f)(2) of this AD is not this AD, unless the AD specifies otherwise. of a certain publication listed in this AD required. (i) Rolls-Royce plc (RR) Alert Non- as of October 2, 2017. (ii) If one or more IP turbine stage 2 locking Modification Service Bulletin Trent XWB 72– ADDRESSES: For service information plates are missing, remove the engine from AJ738, dated April 11, 2017. identified in this final rule, contact service within the compliance times (ii) Reserved. Airbus SAS, Airworthiness Office— specified in the Accomplishment (3) For RR service information identified in EAW, 1 Rond Point Maurice Bellonte, Instructions, paragraph 3.A.(3), of RR Alert this AD, contact Rolls-Royce plc, Corporate NMSB Trent XWB 72–AJ738, dated April 11, Communications, P.O. Box 31, Derby, 31707 Blagnac Cedex, France; telephone 2017. England, DE24 8BJ; phone: 011–44–1332– +33 5 61 93 36 96; fax +33 5 61 93 44 (3) Inspect the IP turbine stage 2 locking 242424; fax: 011–44–1332–249936; email: 51; email account.airworth-eas@ plates during the next engine shop visit http://www.rolls-royce.com/contact/civil_ airbus.com; Internet http:// (ESV) after the effective date of this AD. team.jsp; Internet: https://customers.rolls- www.airbus.com. You may view this (i) Use the Accomplishment Instructions, royce.com/public/rollsroycecare. referenced service information at the asabaliauskas on DSKBBXCHB2PROD with RULES paragraph 3.B., of RR Alert NMSB Trent (4) You may view this service information FAA, Transport Standards Branch, 1601 XWB 72–AJ738, dated April 11, 2017, to do at FAA, Engine and Propeller Standards Lind Avenue SW., Renton, WA. For this inspection. This in-shop inspection may Branch, Policy and Innovation Division, 1200 information on the availability of this be substituted for the on-wing inspection District Avenue, Burlington, MA 01803. For required by paragraphs (f)(1) and (2) of this information on the availability of this material at the FAA, call 425–227–1221. AD. material at the FAA, call 781–238–7125. It is also available on the Internet at (ii) If one or more IP turbine stage 2 locking (5) You may view this service information http://www.regulations.gov by searching plates are missing, use the acceptance criteria at the National Archives and Records for and locating Docket No. FAA–2017– in the Accomplishment Instructions, Administration (NARA). For information on 0472. VerDate Sep<11>2014 17:58 Aug 25, 2017 Jkt 241001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\28AUR1.SGM 28AUR1


Document Created: 2017-08-28 11:29:48
Document Modified: 2017-08-28 11:29:48
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule; request for comments.
DatesThis AD becomes effective September 12, 2017.
ContactRobert 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]
FR Citation82 FR 40681 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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