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(c) Applicability 

This AD applies to The Boeing Company 

Model 787 series airplanes, certificated in 

any category, powered by Rolls Royce Trent 

1000 engines. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust System. 

(e) Unsafe Condition 

This AD was prompted by reports of 

failures of the inner fixed structure (IFS) 

forward upper fire seal and damage to 

thermal insulation blankets in the forward 

upper area of the thrust reverser (TR). We are 

issuing this AD to prevent failure of the IFS 

forward upper fire seal, which causes the loss 

of seal pressurization and allows fan bypass 

air to enter the engine core compartment. Fan 

bypass air entering the engine core 

compartment could degrade the ability to 

detect and extinguish an engine fire, 

resulting in an uncontrolled fire. 

Furthermore, fan bypass air entering the 

engine core compartment could cause 

damage to the TR insulation blanket, 

resulting in thermal damage to the TR inner 

wall, the subsequent release of engine 

exhaust components, and consequent damage 

to critical areas of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

For Model 787–8 and 787–9 series 

airplanes identified in Boeing Alert Service 

Bulletin B787–81205–SB780033–00, Issue 

001, dated November 1, 2017 (‘‘BASB B787– 

81205–SB780033–00, Issue 001’’): Within 36 

months after the effective date of this AD, do 

all applicable actions identified as ‘‘RC’’ 

(required for compliance) in, and in 

accordance with, the Accomplishment 

Instructions of BASB B787–81205– 

SB780033–00, Issue 001. 

(h) Parts Installation Prohibition 

For Model 787 series airplanes powered by 

Rolls Royce Trent 1000 engines, as of the 

effective date of this AD, no person may 

install a thrust reverser with an IFS forward 

upper fire seal having part number (P/N) 

725Z3171–127 or P/N 725Z3171–128. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or local Flight Standards 

District Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in paragraph (j) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

Branch, FAA, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as RC, the provisions 

of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Tak Kobayashi, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des Moines, 

WA 98198; phone: 206–231–3553; email: 

Takahisa.Kobayashi@faa.gov. 

(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) Boeing Alert Service Bulletin B787– 

81205–SB780033–00, Issue 001, dated 

November 1, 2017. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110 SK57, Seal Beach, CA 90740–5600; 

telephone 562–797–1717; internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(5) You may view this service information 

that is incorporated by reference 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/ibrlocations.html. 

Issued in Des Moines, Washington, on July 

13, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–15535 Filed 7–20–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1237; Product 

Identifier 2017–NE–43–AD; Amendment 39– 

19333; AD 2018–15–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) 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 

engine models. This AD requires certain 

engines susceptible to intermediatepressure turbine (IPT) blade failure not 

be installed on an airplane together with 

other engines with IPT blades of the 

same age. This AD was prompted by 

new operating restrictions for engines 

with IPT blades susceptible to shank 

corrosion and possible blade separation. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 7, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 7, 2018. 

We must receive comments on this 

AD by September 6, 2018. 

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. 


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• 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 final rule, 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.rollsroyce.com/contact/civil_team.jsp; 

internet: https://customers.rollsroyce.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–2017– 

1237. 

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– 

1237; 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 final rule, 

the mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Operations (phone: 800–647– 

5527) is listed above. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kevin M. Clark, Aerospace Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7088; fax: 781–238–7199; 

email: kevin.m.clark@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2018– 

0086, dated April 17, 2018 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

An occurrence was reported where, 

following N2 vibration and multiple 

messages, the flight crew performed an 

engine in-flight shut-down (IFSD) and 

returned to the departure airport, landing 

uneventfully. The post-flight borescope 

inspection of the engine revealed an 

intermediate pressure turbine blade (IPTB) 

missing at the shank. Analysis shows that 

this kind of failure is due to sulphidation 

corrosion cracking. 

This condition, if not detected and 

corrected, could lead to IPTB shank release, 

possibly resulting in an IFSD and consequent 

reduced control of the aeroplane. 

To address this potential unsafe condition, 

RR issued Alert NMSB Trent 1000 72–AJ575 

to provide instructions for engine removal 

from service when any IPTB with a high level 

of sulphidation exposure is identified by 

corrosion fatigue life (CFL) model. 

Consequently, EASA issued AD 2017–0056 

to require removal from service of certain 

engines, to be corrected in shop. 

Since that AD was issued, prompted by 

further occurrences and analyses, it has been 

decided that, to reduce the risk of dual IFSD, 

a new cyclic life limit must be applied to 

certain engines, which determines when an 

engine can no longer be installed on an 

aeroplane in combination with certain other 

engines. RR published the original issue of 

the NMSB to provide de-pairing instructions, 

including the relevant IPTB cyclic limit for 

each engine. Consequently, EASA issued 

Emergency AD 2017–0253–E to require depairing of the affected engines. 

Since that AD was issued, RR issued 

Revision 2 of the NMSB, which removes and 

adds certain ESN from the list of affected 

engines and introduces another IPTB cyclic 

limit. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2017–0253–E, which is superseded, 

amends the Applicability, and requires 

application of the new limit. 

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– 

1237. 

Related Service Information Under 

1 CFR Part 51 

We reviewed RR Alert NonModification Service Bulletin (NMSB) 

Trent 1000–72–AJ992, Revision 1, dated 

January 3, 2018, and Revision 2, dated 

April 16, 2018; and RR Service Bulletin 

(SB) Trent 1000 72–H818, dated 

November 14, 2016. Alert NMSB Trent 

1000–72–AJ992 defines operating 

restrictions for de-pairing certain 

engines before an IPT blade cyclic life. 

Revisions 1 and 2 of this NMSB differ 

by identifying different engine serial 

numbers that are affected by the 

respective NMSBs. RR SB Trent 1000 

72–H818 introduces a new IPT blade 

less susceptible to shank corrosion and 

exempt from this AD. 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 

We reviewed RR NMSB Trent 1000 

72–J442, Revision 1, dated February 21, 

2018; and initial issue, dated September 

21, 2016; and RR NMSB Trent 1000 72– 

J465, Revision 2, dated February 28, 

2018; Revision 1, dated January 10, 

2017; and initial issue, dated December 

22, 2016. RR NMSBs Trent 1000 72– 

J442 and Trent 1000 72–J465 describe 

procedures for refurbishing an engine 

with either serviceable used or new IPT 

blades, and also the cleaning and 

inspection requirements for the reuse of 

IPT blades. 

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 

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 relevant 

information 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 one 

engine from an airplane before both 

engines exceed their respective IPT 

blade operating restrictions. 

FAA’s Justification and Determination 

of the Effective Date 

No domestic operators are affected by 

this regulatory action. Therefore, we 

find good cause that notice and 

opportunity for prior public comment 

are unneccessary. In addition, for the 

reason stated above, we find 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 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite 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 

‘‘Docket No. FAA–2017–1237’’ and 

Product Identifier ‘‘2017–NE–43–AD’’ at 

the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this final rule. We will consider all 

comments received by the closing date 

and may amend this final rule because 

of those comments. 


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We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this final rule. 

Costs of Compliance 

We estimate that this AD affects 0 

engines installed on airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Time-Staggering of selected Trent 1000 engines on B787.48 work-hours × $85 per hour = $4,080 ........ $0 $4,080 $0 

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 

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, 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2018–15–01 Rolls-Royce plc: Amendment 

39–19333; Docket No. FAA–2017–1237; 

Product Identifier 2017–NE–43–AD. 

(a) Effective Date 

This AD is effective August 7, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to 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 engine models with engine 

serial numbers identified in Appendix 1, 

Table 1, of RR Alert Non-Modification 

Service Bulletin (NMSB) TRENT 1000 72– 

AJ992, Revision 1, dated January 3, 2018, or 

Appendix 1, Table 1, of RR Alert NMSB 

TRENT 1000 72–AJ992, Revision 2, dated 

April 16, 2018, except those that have 

incorporated RR Service Bulletin (SB) Trent 

1000 72–H818, dated November 14, 2016. 

(d) Subject 

Joint Aircraft System Component (JASC) 

7250, Turbine Engine, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by operating 

restrictions that have been defined for certain 

engines with intermediate-pressure turbine 

(IPT) blades susceptible to shank corrosion 

and possible blade separation. These 

restrictions define when an engine can no 

longer be installed on an airplane together 

with other engines susceptible to the same 

failure. We are issuing this AD to prevent the 

simultaneous failure of both engines. This 

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 

After the effective date of this AD, for any 

affected engine identified in Appendix 1, 

Table 1, of RR Alert NMSB TRENT 1000 72– 

AJ992, Revision 1, dated January 3, 2018; or 

Appendix 1, Table 1, of RR Alert NMSB 

TRENT 1000 72–AJ992, Revision 2, dated 

April 16, 2018, installed with another 

affected engine, listed in the same table, on 

the same airplane, remove one of the engines 

from the airplane before both engines exceed 

their respective IPT blade cyclic life limit 

identified in Appendix 1, Table 1, of the 

respective NMSB, or within 20 flight cycles, 

whichever occurs later. 

(h) Installation Prohibition 

(1) Engines listed in each group in 

Appendix 1, Table 1, of RR Alert NMSB 

Trent 1000 72–AJ992, Revision 1, dated 

January 3, 2018, or Appendix 1, Table 1, of 

Alert NMSB Trent 1000 72–AJ992, Revision 

2, dated April 16, 2018, are not to be 

installed on an airplane together with an 

engine listed in a different group in the same 

table once they have exceeded their IPT 

blade cyclic life limit identified in Appendix 

1, Table 1 of the respective NMSB. 


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(2) Engines listed in Appendix 1, Table 1, 

of RR Alert NMSB Trent 1000 72–AJ992, 

Revision 1, dated January 3, 2018, or 

Appendix 1, Table 1, of RR Alert NMSB 

Trent 1000 72–AJ992, Revision 2, dated April 

16, 2018, may not be installed on an airplane 

with engines that have IPT blades installed 

in accordance with RR NMSB Trent 1000 72– 

J442, Revision 1, dated February 21, 2018, or 

Initial Issue, dated September 21, 2016; or RR 

NMSB Trent 1000 72–J465, Revision 2, dated 

February 28, 2018, or Revision 1, dated 

January 10, 2017, or Initial Issue, dated 

December 22, 2016. 

(i) Terminating Action 

Modification of an engine in accordance 

with the instructions of RR SB Trent 1000 

72–H818, dated November 14, 2016, 

constitutes terminating action for the 

requirements of this AD for that engine. 

(j) 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 (k)(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Kevin M. Clark, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7088; fax: 781–238–7199; email: 

kevin.m.clark@faa.gov. 

(2) Refer to European Aviation Safety 

Agency (EASA) AD 2018–0086, dated April 

17, 2018, 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–2017–1237. 

(l) 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 NonModification Service Bulletin (NMSB) Trent 

1000–72–AJ992, Revision 1, dated January 3, 

2018. 

(ii) RR Alert NMSB Trent 1000–72–AJ992, 

Revision 2, dated April 16, 2018. 

(iii) RR Service Bulletin Trent 1000 72– 

H818, dated November 14, 2016. 

(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.rollsroyce.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 

that is incorporated by reference 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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

July 17, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–15649 Filed 7–20–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0590; Product 

Identifier 2018–NE–24–AD; Amendment 39– 

19319; AD 2018–13–07] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) Trent 1000–A, 

Trent 1000–C, Trent 1000–D, Trent 

1000–E, Trent 1000–G, and Trent 1000– 

H turbofan engine models. This AD 

requires inspecting the intermediatepressure compressor (IPC) stage 1 rotor 

blades, IPC stage 2 rotor blades, and IPC 

stage 2 dovetail posts, and removing any 

cracked parts from service. This AD was 

prompted by crack findings on the IPC 

rotor blades, which could lead to 

separations resulting in engine failures. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective August 7, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 7, 2018. 

We must receive comments on this 

AD by September 6, 2018. 

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 final rule, 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: corporate.care@

rolls-royce.com; internet: https://

customers.rolls-royce.com/public/ 

rollsroycecare. You may view this 

service information at the FAA, Engine 

& 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–2018–0590. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0590; 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 final rule, 

the mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

Docket Operations (phone: 800–647– 

5527) is listed above. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kevin M. Clark, Aerospace Engineer, 

ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7088; fax: 781–238–7199; 

email: kevin.m.clark@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 


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