AD 2012-04-01

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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 <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>, or download 
the publication from <a href="https://www.aeromanager.com">https://www.aeromanager.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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: <a href="/cdn-cgi/l/email-protection#355459545b1b4641475a58755354541b525a43"><span class="__cf_email__" data-cfemail="6c0d000d02421f181e03012c0a0d0d420b031a">[email&#160;protected]</span></a>.

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
----------------------------------------------------------------------------------------------------------------
                                                                                    Life in       Life in cycles
                      Part nomenclature                         Part No. (P/N)   standard duty   using the HEAVY
                                                                                     cycles          profile
----------------------------------------------------------------------------------------------------------------
(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
----------------------------------------------------------------------------------------------------------------

(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: 
<a href="/cdn-cgi/l/email-protection#5e3f323f30702d2a2c31331e383f3f70393128"><span class="__cf_email__" data-cfemail="4f2e232e21613c3b3d20220f292e2e61282039">[email&#160;protected]</span></a>.
    (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 <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>; or Web: <a href="https://www.aeromanager.com">https://www.aeromanager.com</a>.

(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]
BILLING CODE 4910-13-P