[Federal Register Volume 77, Number 35 (Wednesday, February 22, 2012)]
[Rules and Regulations]
[Pages 10355-10356]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-3863]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0755; Directorate Identifier 2010-NE-12-AD;
Amendment 39-16956; AD 2012-04-01]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc (RR) RB211-Trent 800
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding an existing airworthiness directive (AD)
for all RR RB211-Trent 800 series turbofan engines. That AD currently
requires removal from service of certain critical engine parts based on
reduced life limits. This new AD reduces the life limits of additional
critical engine parts. This AD was prompted by RR reducing the life
limits of additional critical engine parts. We are issuing this AD to
prevent the failure of critical rotating parts, which could result in
uncontained failure of the engine and damage to the airplane.
DATES: This AD is effective March 28, 2012.
ADDRESSES: For service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England,
DE248BJ; phone: 011-44-1332-242424; fax: 011-44-1332-245418 or email
from http://www.rolls-royce.com/contact/civil_team.jsp, or download
the publication from https://www.aeromanager.com. You may review copies
of the referenced service information at the FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA. For
information on the availability of this material at the FAA, call 781-
238-7125.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; 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 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: Alan Strom, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; phone: 781-238-7143; fax:
781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede airworthiness directive (AD) 2003-16-
18, amendment 39-13271 (68 FR 49344, August 18, 2003). That AD applies
to the specified products. That SNPRM published in the Federal Register
on November 7, 2011 (76 FR 68663). The original NPRM (75 FR 45560,
August 3, 2010) proposed to revise the Trent 800 Time limits Manual
(TLM) of the Trent 800 engine maintenance manuals (EMMs). The SNPRM
proposed to prohibit installation of one certain critical part and to
increase the life of another critical part whose lives were previously
reduced by that existing AD.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the SNPRM (76 FR 68663, November 7,
2011).
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed.
Costs of Compliance
Based on the service information, we estimate that this AD affects
about 16 RB211-Trent 800 series turbofan engines of U.S. registry. The
average labor rate is $85 per work-hour, but no labor cost is
associated with this AD because discs are replaced at scheduled
maintenance intervals. Prorated cost of parts cost about $45,000 per
engine. Based on these figures, we estimate the cost of the AD on U.S.
operators to be $720,000.
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:
[[Page 10356]]
``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
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, 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 removing airworthiness directive (AD)
2003-16-18, Amendment 39-13271 (68 FR 49344, August 18, 2003) and
adding the following new AD:
2012-04-01 Rolls-Royce plc: Amendment 39-16956; Docket No. FAA-2010-
0755; Directorate Identifier 2010-NE-12-AD.
(a) Effective Date
This AD is effective March 28, 2012.
(b) Affected ADs
This AD supersedes AD 2003-16-18, Amendment 39-13271 (68 FR
49344, August 18, 2003).
(c) Applicability
This AD applies to Rolls-Royce plc (RR) RB211-Trent 895-17, 892-
17, 892B-17, 884-17, 884B-17, 877-17, and 875-17 turbofan engines.
(d) Unsafe Condition
This AD was prompted by RR reporting changes to the lives of
certain life-limited rotating parts. We are issuing this AD to
prevent the failure of critical rotating parts, which could result
in uncontained failure of the engine and damage to the airplane.
(e) Actions and Compliance
Compliance is required within 30 days after the effective date
of this AD, unless already done.
(1) After the effective date of this AD, remove from service the
parts listed in Table 1 of this AD before exceeding the new life
limit indicated:
Table 1--Reduced Part Lives
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Life in Life in cycles
Part nomenclature Part No. (P/N) standard duty using the HEAVY
cycles profile
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(i) Intermediate-pressure (IP) Compressor Rotor Shaft........ FK24100 8,140 8,140
(ii) IP Compressor Rotor Shaft............................... FK24496 8,860 8,180
(iii) High-pressure (HP) Compressor Stage 1 to 4 Rotor Discs FK24009 4,560 4,460
Shaft.......................................................
(iv) HP Compressor Stage 1 to 4 Rotor Discs Shaft............ FK26167 6,340 6,000
(v) HP Compressor Stage 1 to 4 Rotor Discs Shaft............. FK32580 8,550 6,850
(vi) HP Compressor Stage 1 to 4 Rotor Discs Shaft............ FW11590 8,550 6,850
(vii) HP Compressor Stage 1 to 4 Rotor Discs Shaft........... FW61622 8,550 6,850
(viii) HP Compressor Stage 5 and 6 Discs and Cone............ FK25230 5,000 5,000
(ix) HP Compressor Stage 5 and 6 Discs and Cone.............. FK27899 5,000 5,000
(x) IP Turbine Rotor Disc.................................... FK21117 11,610 10,400
(xi) IP Turbine Rotor Disc................................... FK33083 0 0
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(f) Installation Prohibition
After the effective date of this AD, do not install any IP
turbine rotor discs, P/N FK33083, into any engine.
(g) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
to this AD. Use the procedures found in 14 CFR 39.19 to make your
request.
(h) Related Information
(1) You may find additional information on calculating Standard
Duty Cycles and/or using HEAVY Profile Cycles, in RR Time Limits
Manual 05-00-01-800-801, Recording and Control of the Lives of
Parts.
(2) For more information about this AD, contact Alan Strom,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7143; fax: 781-238-7199; email:
[email protected].
(3) Refer to European Aviation Safety Agency Airworthiness
Directive 2007-0003R1, dated January 15, 2009, and RR Alert Service
Bulletin No. RB.211-72-AE935, Revision 7, dated January 19, 2009,
for related information.
(4) For service information identified in this AD, contact
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, DE24
8BJ, United Kingdom; phone: 011-44-1332-242424; fax: 011-44-1332-
249936; email from http://www.rolls-royce.com/contact/civil_team.jsp; or Web: https://www.aeromanager.com.
(i) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on February 10, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2012-3863 Filed 2-21-12; 8:45 am]
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