Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 18629 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–07235 Filed 4–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1202; Directorate 

Identifier 2012–NE–38–AD; Amendment 39– 

17816; AD 2014–07–02] 

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) 2012–26– 

14 for all Rolls-Royce Deutschland Ltd 

& Co KG (RRD) BR700–715A1–30, 

BR700–715B1–30, and BR700–715C1– 

30 turbofan engines. AD 2012–26–14 

required removal from service of certain 

high-pressure (HP) compressor stages 1 

to 6 rotor disc assemblies before 

exceeding certain thresholds. This AD 

requires removal from service at those 

same thresholds but restricts the 

applicability to engines exposed to 

silver-plated nuts, and removes the 

terminating action statement required 

by AD 2012–26–14. This AD was 

prompted by RRD development of a new 

silver-free nut that, if installed with a 

new HP compressor stages 1 to 6 rotor 

disc assembly, would correct the unsafe 

condition identified in AD 2012–26–14. 

We are issuing this AD to prevent 

failure of the HP compressor stages 1 to 

6 rotor disc assembly, which could lead 

to an uncontained engine failure and 

damage to the airplane. 

DATES: This AD is effective May 8, 2014. 

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–2012– 

1202; 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: 

Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7154; fax: (781) 238– 

7199; email: robert.c.morlath@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–26–14, 

Amendment 39–17309 (78 FR 2195, 

January 10, 2013), (‘‘AD 2012–26–14’’). 

AD 2012–26–14 applied to the specified 

products. The NPRM published in the 

Federal Register on November 19, 2013 

(78 FR 69316). The NPRM proposed to 

continue to require removal from 

service of certain HP compressor stages 

1 to 6 rotor disc assemblies before 

exceeding certain thresholds. The 

NPRM also proposed to restrict the 

applicability to engines exposed to 

silver-plated nuts, and to remove the 

terminating action statement required 

by AD 2012–26–14. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Include a Mandatory 

Terminating Action 

RRD requested that we include the 

installation of a new HP compressor 

stages 1 to 6 rotor disc assembly with 

silver-free nuts, part number (P/N) 

U755872, as a necessary terminating 

action to the parts removal requirements 

of this AD, because this would eliminate 

the unsafe condition caused by silver 

nut corrosion. 

We disagree. The flight cycle limits 

imposed by this AD on engines 

operating with silver-plated nuts 

provide an acceptable level of safety. 

Requiring operators to purchase a new 

HP compressor stages 1 to 6 rotor disc 

assembly and new silver-free nuts 

would be an undue economic burden. If 

an operator chooses to install a new HP 

compressor stages 1 to 6 rotor disc 

assembly and silver-free nuts, P/N 

U755872, this AD would no longer 

apply to that engine. We did not change 

this AD. 

Request To Require the Replacement of 

Affected P/Ns at Listed Intervals 

RRD requested that instead of 

requiring a one-time replacement of the 

HP compressor stages 1 to 6 rotor disc 

assembly installed with silver-plated 

nuts, we require replacement of the 

P/Ns at intervals published in European 

Aviation Safety Agency (EASA) AD 

2012–0230, Initial Issue, dated October 

30, 2012. 

We disagree. Our proposed AD did 

not require a one-time replacement. 

This AD requires, for any HP 

compressor stages 1 to 6 rotor disc 

assembly that has ever been installed 

with silver-plated nuts, replacement at 

the cyclic limits stated in paragraphs 

(e)(1) and (e)(2) of this AD, which are 

equivalent to the cyclic limits stated in 

EASA AD 2012–0230, Initial Issue, 

dated October 30, 2012. We did not 

change this AD. 

Request To Update Service Information 

References to the Most Recent Versions 

RRD requested that we update 

references to service bulletins (SBs) to 

the most recent versions. 

We disagree. We do not reference any 

SBs 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 the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 255 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 20 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Prorated parts life 

will cost about $13,500 per engine. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$3,876,000. 

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 


pmangrum on DSK3VPTVN1PROD with RULES
18630 Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 

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) 

2012–26–14, Amendment 39–17309 (78 

FR 2195, January 10, 2013) and adding 

the following new AD: 

2014–07–02 Rolls-Royce Deutschland Ltd & 

Co KG (Type Certificate previously held 

by Rolls-Royce Deutschland GmbH and 

BMW Rolls-Royce Aero Engines): 

Amendment 39–17816; Docket No. 

FAA–2012–1202; Directorate Identifier 

2012–NE–38–AD. 

(a) Effective Date 

This AD is effective May 8, 2014. 

(b) Affected ADs 

This AD supersedes AD 2012–26–14, 

Amendment 39–17309 (78 FR 2195, January 

10, 2013). 

(c) Applicability 

This AD applies to all Rolls-Royce 

Deutschland Ltd & Co KG (RRD) BR700– 

715A1–30, BR700–715B1–30, and BR700– 

715C1–30 turbofan engines with highpressure (HP) compressor stages 1 to 6 rotor 

disc assemblies that were ever installed using 

nuts, part number (P/N) AS44862 or P/N 

AS64367. 

(d) Unsafe Condition 

This AD was prompted by a report of silver 

chloride-induced stress corrosion cracking of 

the HP compressor stages 1 to 6 rotor disc 

assembly. We are issuing this AD to prevent 

failure of the HP compressor stages 1 to 6 

rotor disc assembly, which could lead to an 

uncontained engine failure and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For BR700–715A1–30 turbofan engines 

operated under the Hawaiian Flight Mission 

only, remove the HP compressor stages 1 to 

6 rotor disc assembly from service before 

exceeding 16,000 flight cycles since new 

(CSN) or before further flight after the 

effective date of this AD, whichever occurs 

later. 

(2) For BR700–715A1–30, BR700–715B1– 

30, and BR700–715C1–30 turbofan engines 

(all flight missions except Hawaiian Flight 

Mission), remove the HP compressor stages 1 

to 6 rotor disc assembly from service before 

exceeding 14,000 flight CSN or before further 

flight after the effective date of this AD, 

whichever occurs later. 

(f) Prohibition Statement 

After the effective date of this AD, do not 

install an HP compressor stages 1 to 6 rotor 

disk assembly into an engine, or an engine 

with an HP compressor stage 1 to 6 rotor disk 

assembly onto an aircraft, if the HP 

compressor stages 1 to 6 rotor disk assembly 

has ever been operated with nuts, P/N 

AS44862 or P/N AS64367, and has more CSN 

than specified in the applicable portion of 

the compliance section of this AD. 

(g) Definition 

For the purpose of this AD, flight cycles are 

defined as the total flight CSN on the HP 

compressor stages 1 to 6 rotor disc assembly, 

without any pro-rated calculations applied 

for different flight missions. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7154; fax: (781) 238–7199; 

email: robert.c.morlath@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2012–0230, Initial Issue, 

dated October 30, 2012, for more 

information. You may examine the MCAI in 

the AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2012-1202-0005. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

March 27, 2014. 

Robert J. Ganley, 

Acting Assistant Directorate Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–07444 Filed 4–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Occupational Safety and Health 

Administration 

29 CFR Part 1985 

[Docket Number: OSHA–2011–0540] 

RIN 1218–AC58 

Procedures for Handling Retaliation 

Complaints Under the Employee 

Protection Provision of the Consumer 

Financial Protection Act of 2010 

AGENCY: Occupational Safety and Health 

Administration, Labor. 

ACTION: Interim Final Rule; request for 

comments. 

SUMMARY: This document provides the 

interim final text of regulations 

governing the employee protection (or 

whistleblower) provisions of the 

Consumer Financial Protection Act of 

2010, Section 1057 of the Dodd-Frank 

Wall Street Reform and Consumer 

Protection Act of 2010 (CFPA). This rule 

establishes procedures and time frames 

for the handling of retaliation 

complaints under CFPA, including 

procedures and time frames for 

employee complaints to the 

Occupational Safety and Health 

Administration (OSHA), investigations 

by OSHA, appeals of OSHA 

determinations to an administrative law 

judge (ALJ) for a hearing de novo, 

hearings by ALJs, review of ALJ 

decisions by the Administrative Review 

Board (ARB) (acting on behalf of the 

Secretary of Labor) and judicial review 

of the Secretary’s final decision. 

DATES: This interim final rule is 

effective on April 3, 2014. Comments 

and additional materials must be 


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