Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines, 18629-18630 [2014-07444]

Download as PDF Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 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 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: 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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. pmangrum on DSK3VPTVN1PROD with RULES SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 VerDate Mar<15>2010 13:29 Apr 02, 2014 Jkt 232001 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. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 18629 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 E:\FR\FM\03APR1.SGM 03APR1 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: pmangrum on DSK3VPTVN1PROD with RULES ■ 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. VerDate Mar<15>2010 13:29 Apr 02, 2014 Jkt 232001 (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 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 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 https:// 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 Occupational Safety and Health Administration, Labor. ACTION: Interim Final Rule; request for comments. AGENCY: 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 SUMMARY: E:\FR\FM\03APR1.SGM 03APR1

Agencies

[Federal Register Volume 79, Number 64 (Thursday, April 3, 2014)]
[Rules and Regulations]
[Pages 18629-18630]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-07444]


-----------------------------------------------------------------------

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 https://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

[[Page 18630]]

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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 high-pressure (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 https://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
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