This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

23737 

Vol. 80, No. 82 

Wednesday, April 29, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0593; Directorate 

Identifier 2015–NE–08–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) RB211–535E4–37, 

RB211–535E4–B–37, and RB211– 

535E4–C–37 turbofan engines. This 

proposed AD was prompted by RR 

updating the life limits for certain highpressure turbine (HPT) disks. This 

proposed AD would require reducing 

the cyclic life limits for certain HPT 

disks, removing those disks that have 

exceeded the new life limit, and 

replacing them with serviceable parts. 

We are proposing this AD to prevent 

failure of the HPT disk, which could 

result in uncontained disk release, 

damage to the engine, and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by June 29, 2015. 

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: Docket Management Facility, 

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 proposed AD, 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://www.aeromanager.com. 

You may view this service information 

at the FAA, Engine & Propeller 

Directorate, 12 New England Executive 

Park, 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–2015– 

0593; 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 proposed 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 

in the ADDRESSES section. Comments 

will be available in the AD docket 

shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238– 

7199; email: wego.wang@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–2015–0593; Directorate Identifier 

2015–NE–08–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 based on 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 with FAA 

personnel concerning this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2014– 

0249R1, dated February 18, 2015 

(referred to hereinafter as ‘‘the MCAI’’), 

to correct an unsafe condition for the 

specified products. The MCAI states: 

An engineering analysis, carried out by RR, 

of the lives of critical parts of the RB211– 

535E4–37 engine, has resulted in reduced 

cyclic life limits for certain high pressure 

(HP) turbine discs. The reduced limits are 

published in the RR RB211–535E4–37 Time 

Limits Manual (TLM): 05–10–01–800–000, 

current Revision dated July 2014. 

Operation of critical parts beyond these 

reduced cyclic life limits may result in part 

failure, possibly resulting in the release of 

high-energy debris, which may cause damage 

to the aeroplane and/or injury to the 

occupants. 

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–2015– 

0593. 

Related Service Information Under 1 

CFR Part 51 

We reviewed RR Non-Modification 

Service Bulletin (NMSB) No. RB.211– 

72–G188, Revision No. 1, dated October 

30, 2013, and RR RB211–535E4–37, 

Time Limits Manual (TLM): 05–10–01– 

800–000, Revision dated July 1, 2014; 

and RR RB211–535E4–37, TLM: 05–00– 

01–800–000, Revision dated July 1, 

2014. The NMSB describes the updated 

lifing analysis of the affected HP turbine 

disks. The TLMs provide revised life 

limits for the affected HP turbine disks. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or see ADDRESSES for 

other ways to access this service 

information. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of the United 

Kingdom, 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 proposing this 

AD because we evaluated all 

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23738 Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / Proposed Rules 

information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

proposed AD would require reducing 

the cyclic life limits for certain HPT 

disks, removing those disks that have 

exceeded the new life limit, and 

replacing them with serviceable parts. 

Costs of Compliance 

We estimate that this proposed AD 

affects 650 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 0 

hours per engine to comply with this 

proposed AD. The average labor rate is 

$85 per hour. Pro-rated cost of required 

parts cost would be about $12,213 per 

engine. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $7,938,450. 

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 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 this 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 adding 

the following new airworthiness 

directive (AD): 

Rolls-Royce plc: Docket No. FAA–2015– 

0593; Directorate Identifier 2015–NE–08–AD. 

(a) Comments Due Date 

We must receive comments by June 29, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc 

(RR), RB211–535E4–37, RB211–535E4–B–37, 

and RB211–535E4–C–37 turbofan engines. 

(d) Reason 

This AD was prompted by RR updating the 

life limits for certain high-pressure turbine 

(HPT) disks. We are issuing this AD to 

prevent failure of the HPT disk, which could 

result in uncontained disk release, damage to 

the engine, and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) After the effective date of this AD, use 

RR RB211–535E4–37 Time Limits Manual 

(TLM): 05–10–01–800–000, Revision dated 

July 1, 2014 (referred to hereafter as ‘the 

TLM’), to determine the new life limits for 

the affected engine models and 

configurations, with the exception of those 

engine models mentioned in paragraph (e)(2) 

of this AD. 

(2) For RR RB211–535E4–B–37 or RB211– 

535E4–C–37 engines with an affected HPT 

disk that was previously installed on an 

RB211–535E4–37 engine operated under 

Flight Plan A, use task 05–00–01–800–000 in 

the TLM to re-calculate equivalent cycles 

since new to obtain the new life limit. 

(3) If an affected engine model has an HPT 

disk installed with P/N UL27681 or 

UL39767, remove the affected HPT disk 

before the accumulated cyclic life exceeds 

either 19,500 flight cycles (FCs) under Flight 

Plan A, or 14,700 FCs under Flight Plan B, 

or within 25 FCs after the effective date of 

this AD, whichever occurs later. 

(4) For all affected engines, other than 

those specified in paragraph (e)(3) in this AD, 

remove each HPT disk before exceeding its 

applicable life limit as specified in the TLM. 

(5) Install an HPT disk eligible for 

installation. 

(f) Definition 

For the purpose of this AD, a part eligible 

for installation is one with a part number 

listed in the TLM with a total accumulated 

cyclic life that is less than the applicable life 

limit specified in the TLM. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, 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 Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238–7199; 

email: wego.wang@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0249R1, dated 

February 18, 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–2015–0593. 

(3) RR Non-Modification Service Bulletin 

No. RB.211–72–G188, Revision No. 1, dated 

October 30, 2013, and RR RB211–535E4–37, 

TLM: 05–10–01–800–000, Revision dated 

July 1, 2014; and RR RB211–535E4–37, TLM: 

05–00–01–800–000, Revision dated July 1, 

2014, which are not incorporated by 

reference in this AD, can be obtained from 

Rolls-Royce plc, using the contact 

information in paragraph (h)(4) of this 

proposed AD. 

(4) For service information identified in 

this proposed 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://

www.aeromanager.com. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

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

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Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / Proposed Rules 23739 

Issued in Burlington, Massachusetts, on 

April 22, 2015. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–09816 Filed 4–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0932; Directorate 

Identifier 2014–NM–205–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–8 

series airplanes. This proposed AD was 

prompted by a report of improperly 

installed outboard stowage bin modules 

in the passenger compartment found 

during maintenance. Further 

investigation revealed that certain 

attachment bracket bushings were 

missing or had moved out of the holes. 

This proposed AD would require 

installing a spacer on the end of each 

quick-release pin that attaches the 

outboard stowage bin module to the 

lateral support tie rods of the main deck 

passenger compartment. We are 

proposing this AD to prevent 

detachment of the quick-release pin, 

which could result in separation of the 

lateral support tie rod and subsequent 

detachment of the module and 

consequent injuries to passengers or 

flightcrew. 

DATES: We must receive comments on 

this proposed AD by June 15, 2015. 

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 Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0932. 

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–2015– 

0932; 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 

regulatory evaluation, any comments 

received, and other information. The 

street 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: 

Stanley Chen, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6585; fax: 

425–917–6590; email: stanley.chen@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–0932; Directorate Identifier 2014– 

NM–205–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 

We have received a report of 

improperly installed outboard stowage 

bin modules in the passenger 

compartment found during 

maintenance. Further investigation 

revealed that certain attachment bracket 

bushings of the outboard stowage bin 

module were missing or had moved out 

of the holes, and pins were installed 

incorrectly. These bushings were 

designed to prevent disengagement of 

the quick release pins; however, 

migration of the bushings deters this. It 

was determined that the interference fit 

of the bushings in the attachment 

brackets was incorrect. Subsequently, 

installation of the quick release pins 

during production has caused bushings 

to migrate or detach. This condition, if 

not corrected, could result in separation 

of the lateral support tie rod, 

detachment of the outboard stowage bin 

module, and consequent injuries to 

passengers or flightcrew. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 747–25– 

3649, dated July 24, 2014. The service 

information describes procedures for 

installing a spacer on the end of each 

quick-release pin that attaches the 

outboard stowage bin module to the 

lateral support tie rods of the main deck 

passenger compartment. Refer to this 

service information for information on 

the procedures and compliance times. 

This service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

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 

accomplishing the actions specified in 

the service information identified 

previously. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee, to enhance the 

AD system. One enhancement was a 

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