Federal Register / Vol. 82, No. 185 / Tuesday, September 26, 2017 / Rules and Regulations 44713 

(g) Installation Prohibition 

After the effective date of this AD: 

(1) Do not install an engine that is 

equipped with a clutch and has an affected 

gearbox listed in Figure 1 to paragraph (c) of 

this AD; 

(2) Do not install an affected gearbox on an 

engine unless it has passed the inspection 

required by paragraph (f)(2)(iii) of this AD; 

and 

(3) Do not install a clutch on an engine 

previously modified in accordance with the 

requirements of paragraph (f)(2) of this AD or 

already incorporating a dual mass flywheel. 

(h) 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 ECO Branch, send it to 

the attention of the person identified in 

paragraph (i)(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. 

(i) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2017–0034, dated 

February 20, 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–2017–0241. 

(j) 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) Technify Motors GmbH Service Bulletin 

No. SB TMG 125–1020 P1, Initial Issue, dated 

January 27, 2016. 

(ii) Reserved. 

(3) For Technify Motors GmbH service 

information identified in this AD, contact 

Technify Motors GmbH, Platanenstrasse 14, 

D–09356 Sankt Egidien, Germany; phone: 

+49 37204 696 0; fax: +49 37204 696 29125; 

email: info@centurion-engines.com. You may 

view this referenced service information at 

FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(4) 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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 13, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–20419 Filed 9–25–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0140; Product 

Identifier 2017–NE–05–AD; Amendment 39– 

19048; AD 2017–19–18] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) model Tay 620–15 turbofan 

engines. This AD requires reducing the 

maximum approved life limit. This AD 

was prompted by RRD recalculating the 

life limit for certain high-pressure 

compressor (HPC) stage 12 rotor disks. 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD becomes effective 

October 31, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Rolls-Royce Deutschland Ltd & Co KG, 

Eschenweg 11–15827 Dahlewitz, 

Blankenfelde-Mahlow, Germany; phone: 

+49 0 33–7086–1944; fax: +49 0 33– 

7086–3276. 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– 

0140. 

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– 

0140; or in person at the Docket 

Management Facility 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), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

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: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on May 26, 2017 (82 FR 24257). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Based on revised stress analysis and life 

calculation, Rolls-Royce Deutschland (RRD) 

determined new provisional life limits for 

HPC stage 12 rotor disc Part Number (P/N) 

JR18449, reducing the maximum approved 

life limit defined in the Tay 620–15 and Tay 

620–15/20 engine Time Limits Manual 

(TLM), Chapter 05–10–01, Task 05–10–01– 

800–000, currently at revision dated 15 

September 2014. Failure to replace a HPC 

stage 12 rotor disc P/N JR18449, before 

exceeding the thresholds defined by this AD, 

could lead to an uncontained HPC stage 12 

rotor disc failure, possibly resulting in 

damage to, and/or 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– 

0140. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (82 

FR 24257, May 26, 2017) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 


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44714 Federal Register / Vol. 82, No. 185 / Tuesday, September 26, 2017 / Rules and Regulations 

Related Service Information 

RRD has issued Alert NonModification Service Bulletin (NMSB) 

TAY–72–A1813, Revision 1, dated 

January 27, 2017. The Alert NMSB 

provides instructions to determine or recalculate the consumed and remaining 

service life. 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. 

Costs of Compliance 

We estimate that this AD affects 25 

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 

Pro-rated life ................................................... 1 work-hour × $85 per hour = $85 ................. $3,858 $3,943 $98,575 

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 

■ 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): 

2017–19–18 Rolls-Royce Deutschland Ltd & 

Co KG: Amendment 39–19048; Docket 

No. FAA–2017–0140; Product Identifier 

2017–NE–05–AD. 

(a) Effective Date 

This AD becomes effective October 31, 

2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD) model Tay 

620–15 turbofan engines with high-pressure 

compressor (HPC) modules M03100AA, or 

M03100AB, or M03100AC and HPC stage 12 

rotor disk, part number (P/N) JR18449, 

installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

7230, Turbine Engine Compressor Section. 

(e) Reason 

This AD was prompted by RRD 

recalculating the life limit for HPC stage 12 

rotor disk, P/N JR18449. We are issuing this 

AD to prevent failure of the HPC stage 12 

rotor disk, uncontained HPC stage 12 rotor 

disk release, damage to the engine, and 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 30 days after the effective date 

of this AD, determine whether the HPC stage 

12 rotor disk has operated in both flight 

profiles A and B. If the rotor disk was 

operated, or is operating, in both flight 

profiles A and B, re-calculate the consumed 

cyclic life using 16,700 flight cycles (FC) as 

the maximum approved life limit for flight 

profile B. 

(2) After the effective date of this AD, the 

maximum approved life limit for affected 

rotor disks operating in flight profile B is 

16,700 FC. Calculate the consumed cyclic life 

accumulated since new using 16,700 FC as 

the maximum approved life limit for flight 

profile B. 

(3) For those engines operating in flight 

profile B with an HPC stage 12 rotor disk, P/ 

N JR18449, installed, that do not have an 

engine shop visit after the effective date of 

this AD before the re-calculated consumed 

cyclic life of the HPC stage 12 disk exceeds 

16,700 FC, remove the affected rotor disk 

from service before the re-calculated 

consumed cyclic life exceeds the threshold(s) 

defined in Figure 1 to paragraph (g) of this 

AD. 


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Federal Register / Vol. 82, No. 185 / Tuesday, September 26, 2017 / Rules and Regulations 44715 

FIGURE 1 TO PARAGRAPH (g)—REMOVE AFFECTED ROTOR DISKS FROM SERVICE

Recalculated consumed cyclic life on the effective date 

of this AD 

Remove affected rotor disks from service 

(i) less than 15,700 FC ........ Before exceeding 16,700 FC since new 

(ii) 15,700 FC or more, but 

less than 16,700 FC.

Either: 

(A) Within 1,000 FC or 19 months after the effective date of this AD, whichever occurs first; or 

(B) Before exceeding 16,700 FC since new, 

whichever occurs later. 

(iii) 16,700 FC or more ......... Either: 

(A) Within 1,000 FC after the effective date of this AD, or 

(B) Before exceeding 20,000 FC since new, or 

(C) Within 19 months after the effective date of this AD, 

whichever occurs first. 

(h) Installation Prohibition 

After the effective date of this AD, 

installation of a serviceable spare engine or 

release to service of an engine after any shop 

visit, is allowed, provided the installed HPC 

stage 12 rotor disk, P/N JR18449, is a 

serviceable part. 

(i) Definition 

For the purpose of this AD, a serviceable 

part is an HPC stage 12 rotor disk, P/N 

JR18449, that has not exceeded 20,500 FC for 

flight profile A or 16,700 FC for flight profile 

B, as applicable to engine operation. 

(j) 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: 

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 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: 

Robert.Green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2017–0010, dated January 

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–2017–0140. 

(3) RRD Alert Non-Modification Service 

Bulletin TAY–72–A1813, Revision 1, dated 

January 27, 2017, which is not incorporated 

by reference in this AD, can be obtained from 

RRD, using the contact information in 

paragraph (k)(4) of this AD. 

(4) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11–15827 Dahlewitz, 

Blankenfelde-Mahlow, Germany; phone: +49 

0 33–7086–1944; fax: +49 0 33–7086–3276. 

(5) You may view this service information 

at the FAA, Engine and Propeller Standards 

Branch, Policy and Innovation Division, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(l) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

September 13, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–20531 Filed 9–25–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0767; Product 

Identifier 2017–NE–26–AD; Amendment 39– 

19049; AD 2017–19–19] 

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 XWB–75, 

Trent XWB–79, Trent XWB–79B, and 

Trent XWB–84, turbofan engines. This 

AD requires replacement of the lowpressure compressor (LPC) case support 

inboard pins. This AD was prompted by 

LPC case support inboard pins that may 

have reduced integrity due to incorrect 

heat treatment. We are issuing this AD 

to correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

October 11, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publications listed in this 

AD as of October 11, 2017. 

We must receive comments on this 

AD by November 13, 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.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, 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– 

0767. 

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– 

0767; 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 


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