68284 Federal Register / Vol. 80, No. 213 / Wednesday, November 4, 2015 / Proposed Rules 

levels sufficient to power the aircraft 

system. The Instructions for Continued 

Airworthiness must also contain 

procedures for the maintenance of 

replacement batteries in spares storage 

to prevent the installation of batteries 

that have degraded charge retention 

ability or other damage due to 

prolonged storage at a low state of 

charge. Replacement batteries must be 

of the same manufacturer and part 

number as approved by the FAA. 

Note 2: The term ‘‘sufficiently 

charged’’ means that the battery will 

retain enough of a charge, expressed in 

ampere-hours, to ensure that the battery 

cells will not be damaged. A battery cell 

may be damaged by lowering the charge 

below a point where there is a reduction 

in the ability to charge and retain a full 

charge. This reduction would be greater 

than the reduction that may result from 

normal operational degradation. 

(11) In showing compliance with the 

proposed special conditions herein, 

paragraphs (e)(1) through (e)(8), and the 

RTCA document, Minimum Operational 

Performance Standards for Rechargeable 

Lithium Battery Systems, DO–311, may 

be used. The list of planned DO–311 

tests should be documented in the 

certification or compliance plan and 

agreed to by the CACO. Alternate 

methods of compliance other than DO– 

311 tests must be coordinated with the 

directorate and CACO. 

Issued in Kansas City, Missouri, on 

October 28, 2015. 

Robert Busto, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–28125 Filed 11–3–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3778; Directorate 

Identifier 2015–NE–27–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 a review 

of operational data that determined 

certain RR RB211–535E4–37 engines 

have been operated to a more severe 

flight profile than is consistent with the 

flight profile used to establish the cyclic 

life limits for the rotating parts. This 

proposed AD would require 

recalculating the cyclic life for certain 

engine life-limited rotating parts and 

removing those parts that have exceeded 

their cyclic life limit within specified 

compliance times. We are proposing 

this AD to prevent failure of life-limited 

rotating parts, which could result in 

uncontained parts release, damage to 

the engine, and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by December 4, 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, 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://

customers.rolls-royce.com/public/

rollsroycecare. 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– 

3778; 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: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238– 

7199; email: robert.green@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–2015–3778; Directorate Identifier 

2015–NE–27–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 2015– 

0148, dated July 23, 2015 (corrected July 

24, 2015), referred to hereinafter as ‘‘the 

MCAI’’, to correct an unsafe condition 

for the specified products. The MCAI 

states: 

A review of operational flight data has 

revealed that some RB211–535 engines may 

have been operated beyond the flight profile 

(FP) assumed by the operator when 

establishing the operational limits (life 

limits) within which the corresponding 

critical parts are allowed to remain installed. 

This condition, if not corrected, may lead 

to critical part failure, possibly resulting in 

release of high energy debris, damage to the 

aeroplane and/or injury to the occupants. 

To preclude failure of an engine lifelimited part, the MCAI specifies, and 

this proposed AD would require, 

recalculating the cyclic life for certain 

parts, and removing from service those 

parts that have exceeded their cyclic life 

limit within specified compliance times. 

This proposed AD would establish a 

new default Flight Profile G for RB211– 

535E4–37 engine life-limited parts. If, 

however, operators meet the 

requirements of Appendix 6 of RR Alert 

Non-Modification Service Bulletin 

(NMSB) No. RB.211–72–AH972, 

Revision 3, dated August 28, 2015, they 

may operate to Flight Profile A or B. 

You may obtain further information by 

examining the MCAI in the AD docket 


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Federal Register / Vol. 80, No. 213 / Wednesday, November 4, 2015 / Proposed Rules 68285 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3778. 

Related Service Information Under 1 

CFR Part 51 

RR has issued Alert NMSB No. 

RB.211–72–AH972, Revision 3, dated 

August 28, 2015. The NMSB describes 

a new flight profile, the consumed 

cyclic life corrections for prior operation 

of affected parts, and the removal from 

service recommendations for parts that 

have exceeded their cyclic life limit. 

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 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 

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 

recalculation of the remaining cyclic life 

for the affected engine life-limited parts 

and removal from service of parts that 

exceed their cyclic life limit. 

Costs of Compliance 

We estimate that this proposed AD 

affects 107 engines installed on 

airplanes of U.S. registry. Pro-rated cost 

of the lost cyclic life as a result of the 

corrections would be about $25,417,324. 

We estimate it will take 1 hour to 

recalculate the consumed cyclic life and 

revise the engine records. The average 

labor rate is $85 per hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $25,426,419. 

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– 

3778; Directorate Identifier 2015–NE– 

27–AD. 

(a) Comments Due Date 

We must receive comments by December 4, 

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 a review of 

operational data that determined that certain 

RR RB211–535E4–37 engines have been 

operated to a more severe flight profile than 

is consistent with the flight profile used to 

establish the cyclic life limits for the rotating 

parts. We are issuing this AD to prevent 

failure of life-limited rotating parts, which 

could result in uncontained parts 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. Within 21 days after the effective date 

of this AD: 

(1) For RR RB211–535E4–37 engines, 

establish a new flight profile, Flight Profile 

G, as the new default profile for flight 

operations and new part lives for life-limited 

parts. 

(i) Use Appendix 6 of RR Alert NonModification Service Bulletin (NMSB) No. 

RB.211–72–AH972, Revision 3, dated August 

28, 2015, to define Flight Profile G. 

(ii) Use the definition of Flight Profile G in 

Appendix 6 and the maximum approved 

cyclic lives in Appendix 2 of RR Alert NMSB 

No. RB.211–72–AH972, Revision 3, dated 

August 28, 2015, to identify the new lives for 

life-limited parts. 

(iii) If operators meet the requirements of 

Appendix 6 of RR Alert NMSB No. RB.211– 

72–AH972, Revision 3, dated August 28, 

2015, they may operate to Flight Profile A or 

B. 

(2) For all RB211–535E4–37, RB211– 

535E4–B–37, and RB211–535E4–C–37 

engines, determine if any part identified by 

part number and serial number in Appendix 

4 of RR Alert NMSB No. RB.211–72–AH972, 

Revision 3, dated August 28, 2015, is 

installed on the engine. 

(i) Do not return to service any engine with 

a part identified in paragraph (e)(2) of this 

AD after the part reaches the ‘‘Compliance 

Time’’ date or cycles, whichever occurs first, 

as specified in Appendix 4 of RR Alert NMSB 

No. RB.211–72–AH972, Revision 3, dated 

August 28, 2015. 

(ii) For each part identified in paragraph 

(e)(2) of this AD without a ‘‘Compliance 

Time’’ that has a lifing correction identified, 

apply the lifing correction for each part using 

the ‘‘Additional Life Consumed Flight 

Cycles’’ specified in Appendix 4 of RR Alert 

NMSB No. RB.211–72–AH972, Revision 3, 

dated August 28, 2015. 

(3) For RB211–535E4–37 engines operated 

to Flight Profile G with parts listed in 

Appendix 4 of RR Alert NMSB No. RB.211– 

72–AH972, Revision 3, dated August 28, 

2015, do the following: 


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68286 Federal Register / Vol. 80, No. 213 / Wednesday, November 4, 2015 / Proposed Rules 

(i) Re-calculate the consumed cyclic life of 

the low-pressure (LP) compressor shaft, LP 

turbine shaft, LP turbine disk Stage 2, 

intermediate-pressure compressor rotor shaft 

Stage 1 to 6, high-pressure (HP) compressor 

rotor disk Stage 1 and 2, HP compressor rear 

rotor shaft assembly, and HP turbine disk as 

follows. 

(ii) Determine the Flight Profile G cycles in 

service (CIS). Count all CIS accumulated 

since April 1, 2015, inclusive. 

(iii) Use the Flight Profile G cycles in 

service from paragraph (e)(3)(ii) of this AD, 

the maximum approved lives in Appendix 2 

of RR Alert NMSB No. RB.211–72–AH972, 

Revision 3, dated August 28, 2015, and 

Figure 1 to paragraph (e) of this AD to 

calculate the new consumed cyclic lives. 

(f) 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. 

(g) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, 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 2015–0148, dated July 23, 

2015 (Corrected July 24, 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–2015–3778. 

(3) RR Alert NMSB No. RB.211–72–AH972, 

Revision 3, dated August 28, 2015, and Task 

05–00–01–800–000, ‘‘Recording and Control 

of the Lives of Parts’’, dated July 1, 2015, of 

the RR RB211–535E4 Time Limits Manual 

(TLM), publication reference T–211(535)– 

6RR, Revision 49, dated July 1, 2015, can be 

obtained from RR using the contact 

information in paragraph (g)(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://

customers.rolls-royce.com/public/

rollsroycecare. 

(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. 

Issued in Burlington, Massachusetts, on 

October 28, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28080 Filed 11–3–15; 8:45 am] 

BILLING CODE 4910–13–P 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Part 300 

[Release No. SIPA–173; File No. SIPC–2015– 

01] 

Securities Investor Protection 

Corporation 

AGENCY: Securities and Exchange 

Commission. 

ACTION: Proposed rule. 

SUMMARY: The Securities Investor 

Protection Corporation (‘‘SIPC’’) filed 

proposed rules with the Securities and 

Exchange Commission (‘‘Commission’’). 

SIPC proposes to adopt the SIPC Series 

600 Rules, entitled ‘‘Rules Relating to 

Supplemental Report of SIPC 

Membership,’’ in accordance with 

paragraph (e)(4) of Rule 17a–5 under the 

Securities Exchange Act of 1934 

(‘‘Exchange Act’’). The Commission is 

publishing the proposed rules for public 

comment. Because SIPC rules have the 

force and effect as if promulgated by the 


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