Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21233 

By order of the Board of Governors of the 

Federal Reserve System, March 31, 2016. 

Robert deV. Frierson, 

Secretary of the Board. 

[FR Doc. 2016–07716 Filed 4–8–16; 8:45 am] 

BILLING CODE 6210–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4076; Directorate 

Identifier 2015–NE–30–AD; Amendment 39– 

18483; AD 2016–08–07] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce plc (RR) RB211–22B and 

RB211–524 turbofan engines with lowpressure turbine (LPT) support roller 

bearing, part number (P/N) LK30313 or 

P/N UL29651, installed. This AD 

requires removal of certain LPT support 

roller bearings installed in RR RB211– 

22B and RB211–524 engines. This AD 

was prompted by a report of a breach of 

the turbine casing and release of engine 

debris through a hole in the engine 

nacelle. We are issuing this AD to 

prevent failure of the LPT support roller 

bearing, loss of radial position following 

LPT blade failure, uncontained part 

release, damage to the engine, and 

damage to the airplane. 

DATES: This AD becomes effective May 

16, 2016. 

ADDRESSES: See the FOR FURTHER

INFORMATION CONTACT section. 

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– 

4076; 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 

(MCAI), the 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: 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on December 9, 2015 (80 FR 

76402). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An RB211–524G2–T engine experienced an 

in-service event that resulted in breach of a 

turbine casing and some release of core 

engine debris through a hole in the engine 

nacelle. The investigation of the event 

determined the primary cause to have been 

fracture and release of a Low Pressure (LP) 

turbine stage 2 blade. The blade release 

caused secondary damage to the LP turbine, 

producing significant out-of-balance forces. 

The event engine was fitted with an LP 

turbine support bearing where the roller 

retention cage is constructed from two halves 

that are riveted together. The LP turbine 

imbalance resulted in an overload of the LP 

turbine support bearing and caused 

separation of the riveted, two –piece roller 

retention cage. Radial location of the LP 

turbine shaft was lost, allowing further 

progression of the event that resulted in a 

breach of the IP turbine casing. 

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– 

4076. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Support for the NPRM (80 FR 76402, 

December 9, 2015) 

Boeing concurred with the NPRM. 

Request To Change Compliance 

Orbital ATK and Lockheed Martin 

requested that the compliance time be 

based on LPT blade cycles instead of 

calendar time. Orbital ATK cites 

correspondence with the U.S. RollsRoyce representative who recommends 

a 15,000 cycles-since-new (CSN) 

duration for the LPT blade design life. 

Since there is no calendar time driving 

the unsafe condition, Orbital ATK 

believes this is a good mitigation factor 

for low utilization rate operators. Orbital 

ATK believes that routine borescope 

inspections of the LPT blades and 

removal of the engine prior to reaching 

an LPT blade limit of 15,000 CSN offers 

an equivalent level of safety. 

We partially agree. We agree that the 

failure mode of the bearing support is 

not a time-based dependency. However, 

a compliance time of 24 months is 

specified to allow for a shop visit 

interval. We have determined that 

removal of the LPT support roller 

bearing addresses the unsafe condition. 

Operators with unique circumstances 

may apply for an alternative method of 

compliance using the procedures listed 

in this AD. We did not change this AD. 

Request To Change Costs of Compliance 

Lockheed Martin requested an 

adjustment to the estimated costs of 

compliance. The costs to low utilization 

operators would be significantly 

increased by imposing an unscheduled 

shop visit and/or unscheduled engine 

removal. Another possible contributor 

for increased costs is the lack of an 

approved repair station within the 

United States. 

We partially agree. We disagree that 

no repair stations exist within the U.S. 

that may perform the work required by 

this AD. We agree that this AD may 

drive low utilization operators to the 

shop faster. Operators with unique 

circumstances may apply for an 

alternative method of compliance using 

the procedures listed in this AD. We did 

not change this AD. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 9 

engines installed on airplanes of U.S. 

registry. We also estimate it will take 0 

hours to comply with this AD. 

Removing the LPT support roller 

bearing is required during a shop visit; 

therefore, no additional time is needed 

for removal. Required parts cost about 

$8,184 per engine. The average labor 

rate is $85 per hour. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $73,656. 

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 


jstallworth on DSK7TPTVN1PROD with RULES
21234 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

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 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 this AD: 

(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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2016–08–07 Rolls-Royce plc: Amendment 

39–18483; Docket No. FAA–2015–4076; 

Directorate Identifier 2015–NE–30–AD. 

(a) Effective Date 

This AD becomes effective May 16, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc RB211– 

22B–02, RB211–22B (MOD 72–8700), RB211– 

524B–02, RB211–524B–B–02, RB211–524B2– 

19, RB211–524B2–B–19, RB211–524B3–02, 

RB211–524B4–02, RB211–524B4–D–02, 

RB211–524C2–19, RB211–524C2–B–19, 

RB211–524D4–19, RB211–524D4–B–19, 

RB211–524D4X–19, RB211–524D4X–B–19, 

RB211–524D4–39, RB211–524D4–B–39, 

RB211–524G2–19, RB211–524G3–19, 

RB211–524–G2–T–19, RB211–524G3–T–19, 

RB211–524H–36, RB211–524H2–19, RB211– 

524H–T–36, and RB211–524H2–T–19 

turbofan engines, all serial numbers, with 

low-pressure turbine (LPT) support roller 

bearing, part number (P/N) LK30313 or P/N 

UL29651, installed. 

(d) Reason 

This AD was prompted by a report of a 

breach of the turbine casing and release of 

engine debris through a hole in the engine 

nacelle. We are issuing this AD to prevent 

failure of the LPT support roller bearing, loss 

of radial position following LPT blade 

failure, uncontained part 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. At the next shop visit or within 24 

months after the effective date of this AD, 

whichever occurs first, remove from service 

LPT support roller bearing, P/N LK30313 or 

P/N UL29651, and replace with a part 

eligible for installation. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install an LPT support roller bearing, P/N 

LK30313 or P/N UL29651, onto any engine. 

(g) Definition 

For the purpose of this AD, a ‘‘shop visit’’ 

is defined as induction of an engine into the 

shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance does not constitute an engine 

shop visit. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

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. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0187, dated 

September 9, 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–2015–4076. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

April 4, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–08092 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4112; Directorate 

Identifier 2014–SW–043–AD; Amendment 

39–18471; AD 2016–07–26] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010–23– 

02 for Eurocopter France (now Airbus 

Helicopters) Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. AD 2010–23–02 required 

amending the Limitations section of the 

Rotorcraft Flight Manual (RFM) to limit 

the never-exceed velocity (VNE) to 150 

Knots Indicated Air Speed (KIAS) and 

to add a 1,500 ft/minute rate of descent 

(R/D) limitation beyond 140 KIAS. 

Since we issued AD 2010–23–02, a 

design change designated as 

modification (MOD) 0755B28 improved 

the dynamic behavior of the horizontal 

stabilizer such that AD actions are not 

required. This new AD retains the 

requirements of AD 2010–23–01 and 

revises the applicability to exclude 

helicopters with MOD 0755B28. We are 

issuing this AD to exclude certain 

helicopters from the applicability and 

restrict the VNE on other helicopters to 

prevent failure of the horizontal 

stabilizer and subsequent loss of control 

of the helicopter. 

DATES: This AD is effective May 16, 

2016. 


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