Federal Register / Vol. 81, No. 163 / Tuesday, August 23, 2016 / Rules and Regulations 57447 

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 Rolls-Royce Deutschland Ltd 

& Co KG (RRD) Tay 650–15 and Tay 

651–54 turbofan engines. AD 2006–18– 

14 required calculating and reestablishing the cyclic life of stage 1 

high-pressure turbine (HPT) disks, part 

number (P/N) JR32013 and P/N 

JR33838, and stage 1 low-pressure 

turbine (LPT) disk, P/N JR32318A. In 

addition, this AD requires re-calculating 

the cyclic life, and would impose a 

reduced cyclic life of stage 1 HPT disk, 

P/N 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, P/N JR32013, requires further 

cyclic life limit reduction. We are 

issuing this AD to prevent failure of 

stage 1 HPT disks, P/N JR32013 and 

P/N JR33838, and stage 1 LPT disk, 

P/N JR32318A, uncontained disk release 

and damage to the airplane. 

DATES: This AD is effective September 

27, 2016. The Director of the Federal 

Register approved the incorporation by 

reference a certain publication listed in 

this AD as of September 27, 2016. 

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 

Avenue, 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 

Avenue, Burlington, MA 01803; phone: 

781–238–7770; fax: 781–238–7199; 

email: philip.haberlen@faa.gov. 

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, P/N JR32013 and 

P/N JR33838, and stage 1 LPT disk, 

P/N 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–TAY–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– 

A1821, 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. 

Request To Change Compliance 

RRD requests that the cyclic life limits 

for the HPT stage 1 disk, P/N 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–TAY–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, 

P/N JR33838 and their new analysis 

justified an increased cyclic life limit for 

the HPT stage 1 disk, P/N 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, P/N 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, P/N 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 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. 


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57448 Federal Register / Vol. 81, No. 163 / Tuesday, August 23, 2016 / Rules and Regulations 

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. 

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 

(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 plc): 

Amendment 39–18614; Docket No. 

FAA–2006–25513; Directorate Identifier 

99–NE–61–AD. 

(a) Effective Date 

This AD is effective September 27, 2016. 

(b) Affected ADs 

This AD supersedes AD 2006–18–14. 

(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 (P/N) JR32013 or P/N JR33838, or 

stage 1 low-pressure turbine (LPT) disks, 

P/N JR32318A, 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, P/N JR32013, requires 

further cyclic life limit reduction. We are 

issuing this AD to prevent failure of stage 1 

HPT disks, P/N JR32013 and P/N JR33838, 

and stage 1 LPT disk, P/N JR32318A, 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, P/N JR32013, as follows: 

(i) If a stage 1 HPT disk, P/N 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, P/N JR32013. Use the RRD 

Time Limits Manual (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 1(E) or (1)(F), dated 

September 15, 2014 to re-calculate the cyclic 

life. 

(B) Reserved. 

(ii) If you change your flight plan profile 

or install a stage 1 HPT disk, P/N JR32013 or 

P/N JR33838, or stage 1 LPT disk, P/N 

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 1(E) or (1)(F), dated 

September 15, 2014 to re-calculate the cyclic 

life. 

(2) For engines with a stage 1 HPT disk, 

P/N JR32013, installed, do the following: 

(i) Remove from service any stage 1 HPT 

disk, P/N 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. 

(ii) Reserved. 

(3) For engines with a stage 1 HPT disk, 

P/N JR33838, or stage 1 LPT disk, P/N 

JR32318A, installed, do the following: 

(i) Remove from service any stage 1 HPT 

disk, P/N JR33838, or stage 1 LPT disk, P/N 

JR32318A, 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, P/N JR33838, 

and stage 1 LPT disk, P/N JR32318A, 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, P/N JR33838, 

and stage 1 LPT disk, P/N JR32318A, is 

21,000 FCSN. 

(C) For RRD Tay 650–15 engines operated 

under engine flight plan profile C, the cyclic 


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Federal Register / Vol. 81, No. 163 / Tuesday, August 23, 2016 / Rules and Regulations 57449 

life limit for stage 1 HPT disk, P/N JR33838, 

and stage 1 LPT disk, P/N 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, P/N JR33838, 

and stage 1 LPT disk, P/N 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, P/N 

JR33838, is 14,250 FCSN and the cyclic life 

limit for stage 1 LPT disk, P/N JR32318A, is 

20,000 FCSN. 

(ii) Reserved. 

(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–TAY–5RR, Chapter 05–10– 

01, dated September 15, 2014. 

(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–TAY–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. 

Issued in Burlington, Massachusetts, on 

August 16, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–20081 Filed 8–22–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–8989; Directorate 

Identifier 2016–CE–025–AD; Amendment 

39–18617; AD 2016–17–04] 

RIN 2120–AA64 

Airworthiness Directives; All Hot Air 

Balloons 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all hot 

air balloons to determine if BALO ́ NY 

KUBI ́Cˇ EK spol. s r.o. Model Kubı ́cˇek 

burners equipped with fuel hoses made 

of ‘‘EGEFLEX’’ material are installed. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by the aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as propane leaks 

found on burners equipped with fuel 

hoses made of EGEFLEX material. We 

are issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective August 29, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 29, 2016. 

We must receive comments on this 

AD by October 7, 2016. 

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. 

• 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 BALO ́ NY KUBI ́Cˇ EK 

spol. s r.o., Jarnı ́ 2a, 614 00 Brno, Czech 

Republic, telephone: +420 545 422 620; 

fax: +420 545 422 621; email: info@

kubicekballons.cz; Internet: http://

www.kubicekballoons.eu. You may view 

this referenced service information at 

the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

locating Docket No. FAA–2016–8989. 

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–2016– 

8989; 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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@

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 AD No. 2016– 

0151, dated July 26, 2016 (referred to 


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