[4910-13-P] 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2006-25513; Directorate Identifier 99-NE-61-AD; Amendment 39-

18614; AD 2016-17-01] 

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 superseding airworthiness directive (AD) 2006-18-14 for all RollsRoyce Deutschland Ltd & Co KG (RRD) Tay 650-15 and Tay 651-54 turbofan engines. 

AD 2006-18-14 required calculating and re-establishing the cyclic life of stage 1 highpressure turbine (HPT) disks, part number (PIN) JR32013 and PIN JR33838, and stage 1 

low-pressure turbine (LPT) disk, PIN JR323 l 8A. In addition, this AD requires recalculating the cyclic life, and would impose a reduced cyclic life of stage 1 HPT disk, 

PIN JR32013. This AD was prompted by RRD review of the cyclic life limit of parts 

affected by AD 2006-18-14 and the RRD conclusion that the stage 1 HPT disk, PIN 

JR32013, requires further cyclic life limit reduction. We are issuing this AD to prevent 

failure of stage 1 HPT disks, PIN JR32013 and PIN JR33838, and stage 1 LPT disk, PIN 

JR323 l 8A, uncontained disk release and damage to the airplane. 

DATES: This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. The Director of the Federal Register 
approved the incorporation by reference a certain publication listed in this AD as of 

[INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL 

REGISTER]. 

ADDRESSES: For service information identified in this final rule, contact Rolls-Royce 

Deutschland Ltd & Co KG; Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, 

Germany; phone: 49-0-33-7086-1064; fax: 49-0-33-7086-3276. You may view this 

service information at the FAA, Engine & Propeller Directorate, 1200 District A venue, 

Burlington, MA. 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-2006-25513. 

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-2006-25513; 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, 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: Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District A venue, 

Burlington, MA 01803; phone: 781-238-7770; fax: 781-238-7199; email: 

philip .haberlen@faa.gov. 

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SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to 

supersede AD 2006-18-14, Amendment 39-14753 (71 FR 52988, September 8, 2006), 

("AD 2006-18-14"). AD 2006-18-14 applied to the specified products. The NPRM 

published in the Federal Register on March 11, 2016 (81 FR 12841 ). The NPRM 

proposed to require calculating and re-establishing the cyclic life of stage 1 HPT disks, 

PIN JR32013 and PIN JR33838, and stage 1 LPT disk, PIN JR32318A. The NPRM also 

proposed to require removing from service, using a drawdown schedule, those stage 1 

HPT disks and stage 1 LPT disks operated under Tay 650-15 engine flight plan profiles 

A, B, C, or D; or operated under the Tay 651-54 engine datum flight profile, at reduced 

cyclic life limits found in the RRD Time Limits Manual (TLM) T-TA Y-3RR, Chapter 

05, Time Limits, Subject 05-10-01, dated September 15, 2014 and T-TAY-5RR, Chapter 

05-10-01, dated September 15, 2014. 

Comments 

We gave the public the opportunity to participate in developing this AD. We 

considered the comments received. , 

Changes to Related Service Information under 1 CFR Part 51 

We removed Alert Non-Modification Service Bulletin (NMSB) No. TAY-72-

A 1821, Revision 1, dated March 26, 2015 from Related Service Information under 1 CFR 

Part 51, which is not incorporated by reference in this AD. 

We added the RRD TLM T-TAY-3RR, Chapter 05, Time Limits, Subject 05-10-

01, dated September 15, 2014. 

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Request to Change Compliance 

RRD requests that the cyclic life limits for the HPT stage 1 disk, PIN JR33838, 

installed in RRD Tay 650-15 and Tay 651-54 engines to be changed in this AD to match 

the life limits found in the RRD TLM T-T A Y-3RR, Chapter 05, Time Limits, Subject 05-

10-01 , dated September 15, 2014 and the RRD TLM T-TAY-5RR, Chapter 05-10-01 , 

dated September 15, 2014. RRD updated their lifing analysis for the HPT stage 1 disk, 

PIN JR33838 and their new analysis justified an increased cyclic life limit for the HPT 

stage 1 disk, PIN JR33838 installed in the RRD Tay 650-15 and Tay 651-54 engines for 

certain flight profiles. These life increases were reflected in the applicable service 

bulletin and the TLM and the FAA did not have an opportunity to mandate the increase in 

the cyclic life limits via AD until now. The FAA previously addressed the increase in the 

life limits via a global AMOC. 

We agree. The FAA accepts RRD' s new lifing analysis. We changed the cyclic 

life limits in paragraphs (e)(3)(i)(B), (C), and (D) of this AD for the HPT stage 1 disk, 

PIN JR33838, installed in RRD Tay 650-15 engines to 21 ,000 flight cycles since new 

(FCSN), 18,000 FCSN, and 14,250 FCSN for flight profiles B, C, and D, respectively. 

We also changed the cyclic life limit in paragraph (e)(3)(i)(E) of this AD for the HPT 

stage 1 disk, PIN JR33838, installed in RRD Tay 651-54 engines to 14,250 FCSN for any 

flight profile. 

Conclusion 

We reviewed the available data, including the comments received, and determined 

that air safety and the public interest require adopting this AD with the changes described 

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previously. We determined that these changes will not increase the economic burden on 

any operator or increase the scope of this AD. 

Related Service Information under 1 CFR Part 51 

RRD TLM T-TAY-3RR, Chapter 05, Time Limits, Subject 05-10-01, dated 

September 15, 2014, contains information on re-calculating the cyclic 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. 

Other Related Service Information 

RRD TLM T-TAY-5RR, Chapter 05-10-01, dated September 15, 2014 provides 

the new, reduced cyclic life limits for RRD Tay 651-54 engines operated under any 

engine flight plan profile. 

RRD Alert Non-Modification Service Bulletin TAY-72-A1821, Revision 1, dated 

March 26, 2015, provides reduced cyclic life limits for RRD Tay 650-15 and RRD Tay 

651-54 engines operated under various affected flight plan profiles. 

Costs of Compliance 

We estimate that this AD affects 25 engines installed on airplanes of U.S. registry. 

We also estimate that it would take about 0.5 hours per engine to comply with this AD. 

The average labor rate is $85 per hour. The pro-rated life limit reduction cost is about 

$23,053 per engine. Based on these figures, we estimate the cost of this AD on U.S. 

operators to be $577,388. 

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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. 

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, 

(2) Is not a "significant rule" under 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 

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( 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 part 39 of the Federal Aviation Regulations (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 removing airworthiness directive (AD) 2006-18-

14, Amendment 39-14753 (71 FR 52988, September 8, 2006), ("AD 2006-18-14"), and 

adding the following new AD: 

2016-17-01 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce pie): 

Amendment 39-18614; Docket No. FAA-2006-25513; Directorate Identifier 99-NE-61-

AD. 

(a) Effective Date 

This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected ADs 

This AD supersedes AD 2006-18-14. 

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(c) Applicability 

This AD applies to Rolls-Royce Deutschland Ltd & Co (RRD) KG Tay 650-15 

and Tay 651-54 turbofan engines with stage 1 high-pressure turbine (HPT) disks, part 

number (PIN) JR32013 or PIN JR33838 , or stage 1 low-pressure turbine (LPT) disks, PIN 

JR323 l 8A, installed. 

( d) Unsafe Condition 

This AD was prompted by RRD review of the cyclic life limit of parts affected by 

AD 2006-18-14 and the RRD conclusion that the stage 1 HPT disk, PIN JR32013 , 

requires further cyclic life limit reduction. We are issuing this AD to prevent failure of 

stage 1 HPT disks, PIN JR32013 and PIN JR33838, and stage 1 LPT disk, PIN 

JR323 l 8A, which could result in an uncontained engine failure and damage to the 

airplane. 

(e) Compliance 

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

(1) Re-calculate the cyclic life of stage 1 HPT disks, PIN JR32013, as follows: 

(i) If a stage 1 HPT disk, PIN JR32013, was ever operated under a different 

engine flight plan profile than the engine flight plan profile operated on the last flight, or 

was ever installed and operated in a different engine model, do the following: 

(A) Within 30 days after the effective date of this AD, re-calculate the cyclic life 

for each stage 1 HPT disk, PIN JR32013. Use the RRD Time Limits Manual (TLM) TT A Y-3RR, Chapter 05, Time Limits, Subject 05-10-01, Task 05-10-01-800-000, Subtask 

05-10-01-860-036, paragraph l(E) or (l)(F), dated September 15, 2014 to re-calculate the 

cyclic life. 

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(B) Reserved. 

(ii) If you change your flight plan profile or install a stage 1 HPT disk, PIN 

JR32013 or PIN JR33838, or stage 1 LPT disk, PIN JR32318A, into a different engine 

model after the effective date of this AD, re-calculate the cyclic life within 30 days of 

making the change. Use the RRD TLM T-TAY-3RR, Chapter 05, Time Limits, Subject 

05-10-01, Task 05-10-01-800-000, Subtask 05-10-01-860-036, paragraph l(E) or (l)(F), 

dated September 15, 2014 to re-calculate the cyclic life. 

(2) For engines with a stage 1 HPT disk, PIN JR32013, installed, do the 

following: 

(i) Remove from service any stage 1 HPT disk, PIN JR32013, within 100 flight 

cycles after the effective date of this AD or before exceeding the new, reduced cyclic life 

limits specified in paragraphs (e)(2)(i)(A) through (e)(2)(i)(E) of this AD, whichever 

occurs later, as follows: 

(A) For RRD Tay 650-15 engines operated under engine flight plan profile A, the 

new, reduced cyclic life limit is 18,900 flight cycles-since-new (FCSN). 

(B) For RRD Tay 650-15 engines operated under engine flight plan profile B, the 

new, reduced cyclic life limit is 15,500 FCSN. 

(C) For RRD Tay 650-15 engines operated under engine flight plan profile C, the 

new, reduced cyclic life limit is 11,500 FCSN. 

(D) For RRD Tay 650-15 engines operated under engine flight plan profile D, the 

new, reduced cyclic life limit is 9,300 FCSN. 

(E) For RRD Tay 651-54 engines operated under any engine flight plan profile, 

the new, reduced cyclic life limit is 10,873 FCSN. 

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(ii) Reserved. 

(3) For engines with a stage 1 HPT disk, PIN JR33838, or stage 1 LPT disk, PIN 

JR323 l 8A, installed, do the following: 

(i) Remove from service any stage 1 HPT disk, PIN JR33838, or stage 1 LPT 

disk, PIN JR323 l 8A, before exceeding the cyclic life limits specified in paragraphs 

(e)(3)(i)(A) through (e)(3)(i)(E) of this AD, as follows: 

(A) For RRD Tay 650-15 engines operated under engine flight plan profile A, the 

cyclic life limit for stage 1 HPT disk, PIN JR33838, and stage 1 LPT disk, PIN 

JR323 l 8A, is 23,000 FCSN. 

(B) For RRD Tay 650-15 engines operated under engine flight plan profile B, the 

cyclic life limit for stage 1 HPT disk, PIN JR33838, and stage 1 LPT disk, PIN 

JR32318A, is 21,000 FCSN. 

(C) For RRD Tay 650-15 engines operated under engine flight plan profile C, the 

cyclic life limit for stage 1 HPT disk, PIN JR33838, and stage 1 LPT disk, PIN 

JR32318A, is 18,000 FCSN. 

(D) For RRD Tay 650-15 engines operated under engine flight plan profile D, the 

cyclic life limit for stage 1 HPT disk, PIN JR33838, and stage 1 LPT disk, PIN 

JR32318A, is 14,250 FCSN. 

(E) For RRD Tay 651-54 engines operated under any engine flight plan profile, 

the cyclic life limit for stage 1 HPT disk, PIN JR33838, is 14,250 FCSN and the cyclic 

life limit for stage 1 LPT disk, PIN JR32318A, is 20,000 FCSN. 

(ii) Reserved. 

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(f) Installation Prohibition 

After the effective date of this AD, do not install any part identified in paragraph 

( e) of this AD into any engine, or return any engine to service with any part identified in 

paragraph (e) of this AD, installed, if the part exceeds the cyclic life limit specified in 

paragraphs (e)(2) and (e)(3) of this AD. 

(g) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, 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. 

(h) Related Information 

(1) For more information about this AD, contact Philip Haberlen, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781-238-7199; 

email: philip.haberlen@faa.gov. 

(2) Refer to MCAI European Aviation Safety Agency, AD 2015-0056, dated 

March 31, 2015, 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-2006-25513. 

(3) Rolls-Royce Deutschland Ltd & Co KG Alert Non-Modification Service 

Bulletin No. TAY-72-A1821, Revision 1, dated March 26, 2015, which is not 

incorporated by reference in this AD, can be obtained from Rolls-Royce Deutschland Ltd 

& Co KG, using the contact information in paragraph (i)(3) of this AD. 

(4) RRD TLM T-TA Y-5RR, Chapter 05-10-01, dated September 15, 2014. 

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(5) You may view this service information at the FAA, Engine & Propeller 

Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of 

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

(i) 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 Deutschland Ltd & Co KG, Time Limits Manual T-TA Y-3RR, 

Chapter 05, Time Limits, Subject 05-10-01, dated September 15, 2014. 

(ii) Reserved. 

(3) For Rolls-Royce Deutschland Ltd & Co KG service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 

15827 Blankenfelde-Mahlow, Germany; phone: 49-0-33-7086-1064; fax: 

49-0-33-7086-3276. 

( 4) You may view this service information at FAA, Engine & Propeller 

Directorate, 1200 District Avenue, Burlington, MA. 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/ibrlocations.html. 

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Issued in Burlington, Massachusetts, on August 16, 2016. 

Colleen M. D' Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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