80 FR 48018 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 154 (August 11, 2015)

Page Range48018-48019
FR Document2015-19321

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.

Federal Register, Volume 80 Issue 154 (Tuesday, August 11, 2015)
[Federal Register Volume 80, Number 154 (Tuesday, August 11, 2015)]
[Rules and Regulations]
[Pages 48018-48019]
From the Federal Register Online  [www.thefederalregister.org]
[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.

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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 http://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: [email protected].

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: [email protected].

(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: 
[email protected].
    (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 http://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


80_FR_48172
Current View
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD becomes effective September 15, 2015.
ContactKatheryn 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: [email protected]
FR Citation80 FR 48018 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

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