Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 12841 

telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2011–0207, dated October 20, 2011. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA-2016–4278. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2900: Hydraulic Power. 

Issued in Fort Worth, Texas, on March 3, 

2016. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–05368 Filed 3–10–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25513; Directorate 

Identifier 99–NE–61–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2006–18– 

14 that applies to all Rolls-Royce 

Deutschland Ltd & Co KG (RRD) Tay 

650–15 and Tay 651–54 turbofan 

engines. AD 2006–18–14 requires 

calculating and re-establishing 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. This proposed AD would 

require re-calculating the cyclic life, and 

would impose a reduced cyclic life, of 

stage 1 HPT disk, P/N JR32013. We are 

proposing 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. 

DATES: We must receive comments on 

this proposed AD by May 10, 2016. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11, Dahlewitz, 15827 BlankenfeldeMahlow, 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. 

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 proposed 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 in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–25513; Directorate Identifier 

99–NE–61–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

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 proposed AD. 

Discussion 

On August 30, 2006, we issued AD 

2006–18–14, Amendment 39–14753 (71 

FR 52988, September 8, 2006), for all 

RRD Tay 650–15 and Tay 651–54 

turbofan engines. AD 2006–18–14 

requires 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, that have 

been exposed to different engine flight 

plan profiles. AD 2006–18–14 also 

requires 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. AD 

2006–18–14 resulted from RRD 

updating their low-cycle-fatigue 

analysis for stage 1 HPT disks and stage 

1 LPT disks and reducing their cyclic 

life limits. We issued AD 2006–18–14 to 

prevent cracks leading to turbine disk 

failure, which could result in an 

uncontained engine failure and damage 

to the airplane. 

Actions Since AD 2006–18–14 Was 

Issued 

Since we issued AD 2006–18–14, RRD 

reviewed the cyclic life limit of parts 

affected by AD 2006–18–14; RRD 

concluded that the stage 1 HPT disk, P/ 

N JR32013, requires further cyclic life 

limit reduction. RRD did not further 

reduce the cyclic life limit of stage 1 

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

disk, P/N JR32318A. Accordingly, the 

cyclic life limits of stage 1 HPT disk, P/ 

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

JR32318A, as imposed by AD 2006–18– 

14, remain unchanged in this proposed 

AD. 

Since AD 2006–18–14 was issued, the 

European Aviation Safety Agency 

(EASA) issued AD 2015–0056, dated 

March 31, 2015 to reduce the cyclic life 

limits of the stage 1 HPT disk, P/N 

JR32013. 


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Related Service Information Under 1 

CFR Part 51 

RRD has issued Alert NonModification Service Bulletin (NMSB) 

No. TAY–72–A1821, Revision 1 dated 

March 26, 2015. The Alert NMSB 

describes procedures to re-calculate the 

consumed cyclic life of stage 1 HPT 

disk, P/N JR32013. 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 of this NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require recalculating and re-establishing the 

cyclic life of stage 1 HPT disk, P/N 

JR32013. This proposed AD would also 

require removing from service those 

stage 1 HPT disks, P/N JR32013, 

depending on engine flight plan profiles 

and engine models, at certain reduced 

cyclic life limits, using a drawdown 

schedule. 

Costs of Compliance 

We estimate that this proposed 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 proposed 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 proposed 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 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Rolls-Royce Deutschland Ltd & Co KG 

(formerly Rolls-Royce plc): Docket No. 

FAA–2006–25513; Directorate Identifier 

99–NE–61–AD. 

(a) Comments Due Date 

We must receive comments by May 10, 

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 reducing 

the cyclic life limit for certain stage 1 HPT 

disks, P/N JR32013. We are issuing this AD 

to prevent cracks leading to turbine disk 

failure, 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, and/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, using 

paragraphs 3.A.(1)(b)(1) through 3.A.(1)(b)(4) 

of the Accomplishment Instructions of RRD 

Alert Non-Modification Service Bulletin 

(NMSB) No. TAY–72–A1821, Revision 1, 

dated March 26, 2015. 

(B) Reserved. 

(ii) If you change your flight plan profile 

and/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 of the part(s) as described in 

paragraph (e)(1)(i)(A) of this AD within 30 

days of making the change. 

(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 


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Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 12843 

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, 

is 20,000 FCSN; and the cyclic life limit for 

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 

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

is 14,700 FCSN; and the cyclic life limit for 

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, 

is 11,000 FCSN; and the cyclic life limit for 

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 12,600 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 can be obtained from Rolls-Royce 

Deutschland Ltd & Co KG, using the contact 

information in paragraph (h)(4) of this AD. 

(4) For 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. 

(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. 

Issued in Burlington, Massachusetts, on 

February 26, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–05463 Filed 3–10–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0219; Directorate 

Identifier 2010–NE–14–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2010–11– 

10 that applies to all Turbomeca S.A., 

Astazou XIV B and XIV H turboshaft 

engines. AD 2010–11–10 requires 

inspection of certain third stage turbine 

wheels and removal of any damaged 

wheel. This AD was prompted by a 

report of a third stage turbine wheel 

crack detected during engine overhaul. 

This proposed AD would expand the 

population and frequency of repetitive 

inspections. We are proposing this AD 

to prevent uncontained failure of the 

third stage turbine wheel, which could 

result in damage to the engine and 

damage to the helicopter. 

DATES: We must receive comments on 

this proposed AD by May 10, 2016. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: (33) 

05 59 74 40 00; fax: (33) 05 59 74 45 15. 

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. 

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–2010– 

0219; 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 proposed 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 in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Contact Brian Kierstead, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA 

01803; phone: 781–238–7772, fax: 781– 

238–7199; email: brian.kierstead@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0219; Directorate Identifier 

2010–NE–14–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

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 proposed AD. 

Discussion 

On May 19, 2010, we issued AD 

2010–11–10, Amendment 39–16315 (75 

FR 30270, June 1, 2010), (‘‘AD 2010–11– 

10’’), for all Turbomeca S.A., Astazou 

XIV B and XIV H turboshaft engines. AD 

2010–11–10 requires inspection of 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS