Document ID: FAA-2019-0693-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce Deutschland Ltd and Co KG (Type Certificate previously held by Rolls-Royce plc) Turbofan Engines
Posted Date: 2019-10-15T04:00Z

[Federal Register Volume 84, Number 199 (Tuesday, October 15, 2019)]
[Rules and Regulations]
[Pages 55041-55044]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-22323]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0693; Product Identifier 2017-NE-43-AD; Amendment 
39-19758; AD 2019-20-05]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
(Type Certificate Previously Held by Rolls-Royce plc) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding airworthiness directive (AD) 2018-15-01 
for certain Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 
1000-D, Trent 1000-E, Trent 1000-G, Trent 1000-H, Trent 1000-A2, Trent 
1000-C2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, 
Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model turbofan engines. 
AD 2018-15-01 required certain engines susceptible to intermediate-
pressure turbine (IPT) blade failure not be installed on an airplane 
together with other engines with IPT blades of the same cyclic life. 
This AD requires removal of the IPT blade set at lower cyclic life 
limits and replacing it with a blade set eligible for installation. 
This AD also expands the applicability to include additional Trent 1000 
turbofan engine models. This AD was prompted by the determination that 
certain IPT blades are susceptible to shank corrosion which leads to 
cracking and possible blade separation. The FAA is issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective October 30, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 30, 
2019.
    The FAA must receive any comments on this AD by November 29, 2019.

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.
     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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    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, 
1200 District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call 781-238-7759. It is also 
available on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2019-0693.

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-2019-
0693; 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 AD, the mandatory continuing airworthiness information (MCAI), 
regulatory evaluation, any comments received, and other information. 
The street address for Docket Operations is listed above. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Martin Adler, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7088; fax: 781-238-7157; email: martin.adler@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued AD 2018-15-01, Amendment 39-19333 (83 FR 34755, July 
23, 2018), (``AD 2018-15-01''), for certain RR Trent 1000-A, Trent 
1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, Trent 1000-H, Trent 
1000-A2, Trent 1000-C2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, 
Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model 
turbofan engines. AD 2018-15-01 prohibited the installation of engines 
susceptible to IPT blade failure on an airplane together with other 
engines with IPT blades of the same cyclic life. AD 2018-15-01 resulted 
from new operating restrictions

[[Page 55042]]

for engines with IPT blades susceptible to shank corrosion and possible 
blade separation. The FAA issued AD 2018-15-01 to prevent the 
simultaneous failure of both engines.

Actions Since AD 2018-15-01 Was Issued

    Since the FAA issued AD 2018-15-01, RR determined that unless new 
IPT blades are installed in accordance with RR Service Bulletin (SB) 
Trent 1000 72-H818, dated November 14, 2016, or RR SB Trent 1000 72-
J559, dated November 27, 2017, each engine must remain subject to 
specific maintenance intervals to minimize the risk of IPT blade 
release. Both SBs introduced new IPT blades not subject to this AD. RR 
SB Trent 1000 72-J559 also applies to additional RRD Trent 1000 engines 
(Trent 1000 TEN engine standard). RR subsequently transferred its FAA 
type certificate for the subject model engines to Rolls-Royce 
Deutschland Ltd & Co KG (RRD).
    Also, since the FAA issued AD 2018-15-01, the European Union 
Aviation Safety Agency (EASA) issued EASA AD No. 2019-0135, dated June 
11, 2019 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or the ``MCAI''). The MCAI states:
    Occurrences were reported of IPTB [IPT blade] shank cracking. 
Analysis shows that this kind of failure is due to sulphidation 
corrosion.
    This condition, if not corrected, could lead to IPTB shank release, 
possibly resulting in engine in-flight shut-down (IFSD) and consequent 
reduced control of the aeroplane.
    Prompted by these events, Rolls-Royce identified engines with a 
high level of sulphidation exposure using a corrosion fatigue life 
(CFL) model. Consequently, EASA issued AD 2017-0056 to require removal 
from service of certain engines, to be corrected in shop. In addition, 
to reduce the risk of dual IFSD, it was decided to introduce a new 
cyclic life limit to certain engines, determining when an engine can no 
longer be installed on an aeroplane in combination with certain other 
engines. Consequently, EASA issued Emergency AD 2017-0253-E, AD 2018-
0086, and finally AD 2018-0139, each next AD superseding the previous 
one, to require de-pairing of the affected engines.
    After EASA AD 2018-0139 was issued, prompted by further analyses of 
data provided by operators, Rolls-Royce developed an updated service 
management approach to minimise the risk of IPTB release and issued the 
NMSB, identifying those ESN at highest risk, and providing the 
corresponding cyclic limits for in-shop IPTB replacement. Consequently, 
EASA issued AD 2018-0257, superseding EASA AD 2017-0056 and AD 2018-
0139, to require removal from service of certain engines, to be 
corrected in shop. That AD also required, for engines having SUM IPTB 
installed, the introduction of IPTB cyclic limits. Finally, that AD 
retained the optional terminating action as previously provided by EASA 
AD 2018-0139.
    Since that AD was issued, it was determined that, unless mod/SB 72-
H818 or mod/SB 72-J559 is embodied, each engine must remain subject to 
service management to minimise the risk of IPTB release. Rolls-Royce 
mod/SB 72-J559 applies to the Trent 1000 TEN engine standard, 
introducing IPTB P/N KH71526 and additional IPTB coating.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2018-0257, which is superseded, expands the 
Applicability by including Trent 1000 TEN engine models, and including 
reference to the NMSB, as defined in this AD.
    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-2019-0693.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed RR Alert Non-Modification Service Bulletin (NMSB) 
Trent 1000 72-AK186, Revision 2, dated April 16, 2019. This service 
information establishes cyclic life limits for IPT blades and specifies 
removing RRD Trent 1000 engines with IPT blades that have a cyclic life 
exceeding the new cyclic life limits.
    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.

Other Related Service Information

    The FAA reviewed RR NMSB Trent 1000 72-J442, Revision 3, dated 
October 8, 2018, and RR NMSB Trent 1000 72-J465, Revision 4, dated 
October 8, 2018. These NMSBs both describe procedures, as applicable to 
different sets of RRD Trent 1000 model turbofan engines, for cleaning 
and inspecting affected IPT blades so that they are suitable for reuse.
    The FAA also reviewed RR SB Trent 1000 72-H818, dated November 14, 
2016, and RR SB Trent 1000 72-J559, dated November 27, 2017. RR SB 
Trent 1000 72-H818 introduced a new IPT blade that is less susceptible 
to shank corrosion. RR SB Trent 1000 72-J559 introduced a new IPT blade 
with additional blade coating and applies to additional Trent 1000 
engines (Trent 1000 TEN engine standard).

FAA's Determination

    This product has been approved by EASA, and is approved for 
operation in the United States. Pursuant to our bilateral agreement 
with the European Union, EASA has notified us of the unsafe condition 
described in the MCAI and service information referenced above. The FAA 
is issuing this AD because it evaluated all the relevant information 
provided by EASA and determined the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design.

AD Requirements

    This AD requires removal of the IPT blade set at lower cyclic life 
limits and its replacement with a blade set eligible for installation 
for affected RRD Trent 1000 model turbofan engines.

FAA's Justification and Determination of the Effective Date

    No domestic operators use this product. Therefore, the FAA finds 
that notice and opportunity for prior public comment are unnecessary. 
In addition, for this same reason, the FAA finds that good cause exists 
for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and the FAA did not provide you with notice and an opportunity 
to provide your comments before it becomes effective. However, the FAA 
invites you to send any written data, views, or arguments about this 
final rule. Send your comments to an address listed under the ADDRESSES 
section. Include the docket number FAA-2019-0693 and product identifier 
2017-NE-43-AD at the beginning of your comments. The FAA specifically 
invites comments on the overall regulatory, economic, environmental, 
and energy aspects of this final rule. The FAA will consider all 
comments received by the closing date and may amend this final rule 
because of those comments.
    The FAA will post all comments received, without change, to http://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this final rule.

[[Page 55043]]

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 0 engines installed on 
airplanes of U.S. registry.
    In the event an affected engine becomes installed on a U.S.-
registered product, the FAA estimates the following costs to comply 
with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace IPT blades.................  48 work-hours x $85 per            $100,000        $104,080              $0
                                      hour = $4,080.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is 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

    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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866, and
    (2) Will not affect intrastate aviation in Alaska.

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 part 39 of the Federal Aviation 
Regulations (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 removing airworthiness directive (AD) 
2018-15-01, Amendment 39-19333 (83 FR 34755, July 23, 2018), and adding 
the following new AD:

2019-20-05 Rolls-Royce Deutschland Ltd & Co KG (Type Certificate 
previously held by Rolls-Royce plc) Turbofan Engines: Amendment 39-
19758; Docket No. FAA-2019-0693; Product Identifier 2017-NE-43-AD.

(a) Effective Date

    This AD is effective October 30, 2019.

 (b) Affected ADs

    This AD replaces AD 2018-15-01, Amendment 39-19333 (83 FR 34755, 
July 23, 2018).

 (c) Applicability

    This AD applies to Rolls-Royce Deutschland Ltd. & Co KG (Type 
Certificate previously held by Rolls-Royce plc) (RRD) Trent 1000-A, 
Trent 1000-A2, Trent 1000-AE, Trent 1000-AE2, Trent 1000-AE3, Trent 
1000-C, Trent 1000-C2, Trent 1000-CE, Trent 1000-CE2, Trent 1000-
CE3, Trent 1000-D, Trent 1000-D2, Trent 1000-D3, Trent 1000-E, Trent 
1000-E2, Trent 1000-G, Trent 1000-G2, Trent 1000-G3, Trent 1000-H, 
Trent 1000-H2, Trent 1000-H3, Trent 1000-J2, Trent 1000-J3, Trent 
1000-K2, Trent 1000-K3, Trent 1000-L2, Trent 1000-L3, Trent 1000-M3, 
Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3 and Trent 1000-R3 model 
turbofan engines, with an engine serial number (ESN) listed in 
Appendix 1, 2, or 3 of Rolls-Royce plc (RR) Alert Non-Modification 
Service Bulletin (NMSB) Trent 1000 72-AK186, Revision 2, dated April 
16, 2019, except those engines that have incorporated the 
modifications in RR Service Bulletin (SB) Trent 1000 72-H818, dated 
November 14, 2016, or RR SB Trent 1000 72-J559, dated November 27, 
2017.

 (d) Subject

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

 (e) Unsafe Condition

    This AD was prompted by the determination that certain 
intermediate-pressure turbine (IPT) blades are susceptible to shank 
corrosion which leads to cracking and possible blade separation. The 
FAA is issuing this AD to prevent the simultaneous failure of both 
engines installed on an airplane, during flight. The unsafe 
condition, if not addressed, could result in a dual engine in-flight 
shutdown and loss of the airplane.

 (f) Compliance

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

 (g) Required Actions

    (1) For engines with an ESN listed in Appendix 1 of RR Alert 
NMSB Trent 1000 72-AK186, Revision 2, dated April 16, 2019 (``RR 
Alert NMSB Trent 1000 72-AK186''), prior to reaching the blade cycle 
life limit listed in Appendix 1 of RR Alert NMSB Trent 1000 72-
AK186, or within 30 days of the effective date of this AD, whichever 
occurs later, remove the IPT blade set and replace with an IPT blade 
set eligible for installation.
    (2) For engines with an ESN listed in Appendix 2 of RR Alert 
NMSB Trent 1000 72-AK186:
    (i) If the engine is in an engine shop visit on the effective 
date of this AD, remove the IPT blade set and replace with an IPT 
blade set eligible for installation prior to returning the engine to 
service; or

[[Page 55044]]

    (ii) If the engine is not in an engine shop visit on the 
effective date of this AD and the IPT blade set was not replaced 
during the previous engine shop visit, remove the IPT blade set and 
replace with an IPT blade set eligible for installation within 30 
days of the effective date of this AD.
    (3) For engines that have replaced the IPT blade set per RR NMSB 
Trent 1000 72-J442, Revision 3, dated October 8, 2018, or RR NMSB 
Trent 1000 72-J465, Revision 4, dated October 8, 2018, as 
applicable, remove and replace those blades prior to reaching the 
``Permitted Cycles of operation since installation in accordance 
with NMSB 72-J442 or 72-J465'' listed in Appendix 3 of RR Alert NMSB 
Trent 1000 72-AK186, as applicable for each ESN, or within 30 days 
of the effective date of this AD, whichever occurs later.

    Note 1 to paragraph (g): An IPT blade set eligible for 
installation is a full set of new IPT blades, or a full set of 
blades that have been inspected per RR NMSB Trent 1000 72-J442, 
Revision 3, dated October 8, 2018, or RR NMSB Trent 1000 72-J465 
Revision 4, October 8, 2018, as applicable by engine model.

 (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 case flanges, except that 
the separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

 (i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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. You may email your 
request to: ANE-AD-AMOC@faa.gov.
    (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 Martin Adler, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7088; fax: 781-238-7157; email: 
martin.adler@faa.gov.
    (2) Refer to European Union Aviation Safety Agency (EASA) AD 
2019-0135, dated June 11, 2019, for more information. You may 
examine the EASA AD in the AD docket on the internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2019-0693.

 (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 1000 72-AK186, Revision 2, dated April 16, 2019.
    (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, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (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, email: fedreg.legal@nara.gov, 
or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on October 3, 2019.
Robert J. Ganley,
Manager, Engine & Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-22323 Filed 10-11-19; 8:45 am]
 BILLING CODE 4910-13-P