Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 48018-48019 [2015-19321]

Download as PDF 48018 Federal Register / Vol. 80, No. 154 / Tuesday, August 11, 2015 / Rules and Regulations Issued in Renton, Washington, on July 22, 2015. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–19316 Filed 8–10–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0095; Directorate Identifier 2015–NE–01–AD; Amendment 39– 18228; AD 2015–16–03] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211–524B–02, RB211–524B2–19, RB211–524B3–02, RB211–524B4–02, RB211–524B4–D–02, RB211–524C2–19, RB211–524D4–19, RB211–524D4–39, and RB211–524D4X– 19 turbofan engines. This AD requires removing affected high-pressure turbine (HPT) blades. This AD was prompted by several failures of affected HPT blades. We are issuing this AD to prevent failure of the HPT blade, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane. DATES: This AD becomes effective September 15, 2015. SUMMARY: rmajette on DSK2TPTVN1PROD with RULES 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–2015– 0095; 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: Katheryn Malatek, Aerospace Engineer, VerDate Sep<11>2014 15:24 Aug 10, 2015 Jkt 235001 Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238– 7199; email: katheryn.malatek@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 April 29, 2015 (80 FR 23741). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: There were a number of pre-MOD/SB 72– 7730 High Pressure Turbine (HPT) blade failures, with some occurring within a relatively short time. Engineering analysis carried out by RR on those occurrences indicates that certain pre-MOD/SB 72–7730 blades, Part Number (P/N) UL32958 and P/ N UL21691 (hereafter referred to as ‘affected HPT blade’), with an accumulated life of 6500 flight hours (FH) since new or more, have an increased risk of in-service failure. This condition, if not corrected, could lead to HPT blade failure, release of debris and consequent (partial or complete) loss of engine power, possibly resulting in reduced control of the aeroplane. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 23741, April 29, 2015). Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed. Costs of Compliance We estimate that this AD affects 6 engines installed on airplanes of U.S. registry. We also estimate that it will take about 4 hours per engine to comply with this AD. The average labor rate is $85 per hour. Pro-rated cost of required parts is about $250,000 per engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,502,040. 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: PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 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): ■ 2015–16–03 Rolls-Royce plc: Amendment 39–18228; Docket No. FAA–2015–0095; Directorate Identifier 2015–NE–01–AD. (a) Effective Date This AD becomes effective September 15, 2015. E:\FR\FM\11AUR1.SGM 11AUR1 Federal Register / Vol. 80, No. 154 / Tuesday, August 11, 2015 / Rules and Regulations (b) Affected ADs DEPARTMENT OF TRANSPORTATION None. Federal Aviation Administration (c) Applicability This AD applies to all Rolls-Royce plc (RR) RB211–524B–02, RB211–524B2–19, RB211– 524B3–02, RB211–524B4–02, RB211–524B4– D–02, RB211–524C2–19, RB211–524D4–19, RB211–524D4–39, and RB211–524D4X–19 turbofan engines with high-pressure turbine (HPT) blades, part numbers (P/Ns) UL32958 and UL21691, installed. (d) Reason This AD was prompted by several failures of affected HPT blades. We are issuing this AD to prevent failure of the HPT blade, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane. (e) Actions and Compliance (1) Comply with this AD within the compliance times specified, unless already done. (2) After the effective date of this AD, within 2 months or before exceeding 6,500 flight hours since first installation of HPT blades, P/Ns UL32958 and UL21691, on an engine, whichever occurs later, remove all affected HPT blades from service. (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 Katheryn Malatek, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238– 7199; email: katheryn.malatek@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2014–0250, dated November 19, 2014, for more information. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating it in Docket No. FAA–2015–0095. (h) Material Incorporated by Reference rmajette on DSK2TPTVN1PROD with RULES None. Issued in Burlington, Massachusetts, on July 30, 2015. Ann C. Mollica, Acting Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–19321 Filed 8–10–15; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2013–0834; Directorate Identifier 2012–NM–045–AD; Amendment 39–18227; AD 2015–16–02] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directives (AD) 2003–14– 11, AD 2004–11–08, AD 2004–13–25, AD 2004–18–14, AD 2007–05–12, AD 2008–06–07, AD 2009–18–20, AD 2010– 15–02, and AD 2012–04–07 that apply to certain Airbus Model A330 and A340 series airplanes. AD 2003–14–11, AD 2004–11–08, AD 2004–13–25, AD 2004– 18–14, AD 2007–05–12, AD 2008–06– 07, AD 2009–18–20, AD 2010–15–02, and AD 2012–04–07 required revising the maintenance program to incorporate certain maintenance requirements and airworthiness limitations; replacing certain flap rotary actuators; repetitively inspecting elevator servo-controllers and pressure relief valves of the spoiler servo controls; repetitively testing the elevator servo control loops, modifying the elevator servo controls, and repetitively replacing certain retraction brackets of the main landing gear; and revising the airplane flight manual. This new AD requires revising the maintenance program or inspection program to incorporate certain maintenance requirements and airworthiness limitations. This new AD also removes Airbus Model A340–200, –300, –500, and –600 series airplanes from the applicability and adds Airbus Model A330–323 airplanes to the applicability. This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to address the aging effects of aircraft systems. Such aging effects could change the characteristics of those systems, which, in isolation or in combination with one or more other specific failures or events, could result in failure of certain life limited parts, which could reduce the structural integrity of the airplane or reduce the controllability of the airplane. SUMMARY: This AD becomes effective September 15, 2015. DATES: VerDate Sep<11>2014 15:24 Aug 10, 2015 Jkt 235001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 48019 The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 15, 2015. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0834; or in person at the Docket 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. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet https://www.airbus.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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0834. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to revise the following airworthiness directives that applied to certain Airbus Model A330 and A340 series airplanes. • AD 2003–14–11, Amendment 39– 13230 (68 FR 41521, July 14, 2003). • AD 2004–11–08, Amendment 39– 13654 (69 FR 31874, June 8, 2004). • AD 2004–13–25, Amendment 39– 13707 (69 FR 41394, July 9, 2004). • AD 2004–18–14, Amendment 39– 13793 (69 FR 55326, September 14, 2004). • AD 2007–05–12, Amendment 39– 14973 (72 FR 10057, March 7, 2007). • AD 2008–06–07, Amendment 39– 15419 (73 FR 13103, March 12, 2008; corrected April 15, 2008 (73 FR 20367)). • AD 2009–18–20, Amendment 39– 16017 (74 FR 46313, September 9, 2009). • AD 2010–15–02, Amendment 39– 16368 (75 FR 42589, July 22, 2010). • AD 2012–04–07, Amendment 39– 16963 (77 FR 12989, March 5, 2012). E:\FR\FM\11AUR1.SGM 11AUR1

Agencies

[Federal Register Volume 80, Number 154 (Tuesday, August 11, 2015)]
[Rules and Regulations]
[Pages 48018-48019]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-19321]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0095; Directorate Identifier 2015-NE-01-AD; 
Amendment 39-18228; AD 2015-16-03]
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) RB211-524B-02, RB211-524B2-19, RB211-524B3-02, 
RB211-524B4-02, RB211-524B4-D-02, RB211-524C2-19, RB211-524D4-19, 
RB211-524D4-39, and RB211-524D4X-19 turbofan engines. This AD requires 
removing affected high-pressure turbine (HPT) blades. This AD was 
prompted by several failures of affected HPT blades. We are issuing 
this AD to prevent failure of the HPT blade, which could lead to 
failure of one or more engines, loss of thrust control, and damage to 
the airplane.

DATES: This AD becomes effective September 15, 2015.

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-2015-
0095; 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: Katheryn Malatek, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7747; 
fax: 781-238-7199; email: katheryn.malatek@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 April 29, 2015 (80 FR 
23741). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    There were a number of pre-MOD/SB 72-7730 High Pressure Turbine 
(HPT) blade failures, with some occurring within a relatively short 
time. Engineering analysis carried out by RR on those occurrences 
indicates that certain pre-MOD/SB 72-7730 blades, Part Number (P/N) 
UL32958 and P/N UL21691 (hereafter referred to as `affected HPT 
blade'), with an accumulated life of 6500 flight hours (FH) since 
new or more, have an increased risk of in-service failure.
    This condition, if not corrected, could lead to HPT blade 
failure, release of debris and consequent (partial or complete) loss 
of engine power, possibly resulting in reduced control of the 
aeroplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 23741, April 29, 
2015).

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed.

Costs of Compliance

    We estimate that this AD affects 6 engines installed on airplanes 
of U.S. registry. We also estimate that it will take about 4 hours per 
engine to comply with this AD. The average labor rate is $85 per hour. 
Pro-rated cost of required parts is about $250,000 per engine. Based on 
these figures, we estimate the cost of this AD on U.S. operators to be 
$1,502,040.

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 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

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 adding the following new airworthiness 
directive (AD):

2015-16-03 Rolls-Royce plc: Amendment 39-18228; Docket No. FAA-2015-
0095; Directorate Identifier 2015-NE-01-AD.

(a) Effective Date

    This AD becomes effective September 15, 2015.

[[Page 48019]]

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR) RB211-524B-02, 
RB211-524B2-19, RB211-524B3-02, RB211-524B4-02, RB211-524B4-D-02, 
RB211-524C2-19, RB211-524D4-19, RB211-524D4-39, and RB211-524D4X-19 
turbofan engines with high-pressure turbine (HPT) blades, part 
numbers (P/Ns) UL32958 and UL21691, installed.

(d) Reason

    This AD was prompted by several failures of affected HPT blades. 
We are issuing this AD to prevent failure of the HPT blade, which 
could lead to failure of one or more engines, loss of thrust 
control, and damage to the airplane.

(e) Actions and Compliance

    (1) Comply with this AD within the compliance times specified, 
unless already done.
    (2) After the effective date of this AD, within 2 months or 
before exceeding 6,500 flight hours since first installation of HPT 
blades, P/Ns UL32958 and UL21691, on an engine, whichever occurs 
later, remove all affected HPT blades from service.

(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 Katheryn 
Malatek, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: 
katheryn.malatek@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-0250, 
dated November 19, 2014, for more information. You may examine the 
MCAI in the AD docket on the Internet at https://www.regulations.gov 
by searching for and locating it in Docket No. FAA-2015-0095.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on July 30, 2015.
Ann C. Mollica,
Acting Assistant Directorate Manager, Engine & Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2015-19321 Filed 8-10-15; 8:45 am]
 BILLING CODE 4910-13-P
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