[Federal Register Volume 80, Number 23 (Wednesday, February 4, 2015)]
[Rules and Regulations]
[Pages 5909-5911]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-01282]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0462; Directorate Identifier 2014-NE-06; Amendment 
39-18075; AD 2015-02-08]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation Turboprop and 
Turbofan Engines (Type Certificate Previously Held by Allison Engine 
Company)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Rolls-Royce Corporation (RRC) AE 2100 series turboprop engines and AE 
3007A and 3007C series turbofan engines. This AD was prompted by 
reports of pitting in the wheel bores and subsequent RRC analysis that 
concluded that lower life limits are needed for the affected turbine 
wheels. This AD requires a reduction for the approved life limits of 
the affected turbine wheels. This AD also requires an eddy current 
inspection (ECI) of certain RRC engines with affected turbine wheels. 
We are issuing this AD to prevent uncontained failure of the turbine 
wheels, damage to the engine, and damage to the airplane.

DATES: This AD is effective March 11, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 11, 
2015.

ADDRESSES: For service information identified in this AD, contact 
Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB-01-06, 
Indianapolis, IN 46225; phone: 317-230-1667; email: <a href="/cdn-cgi/l/email-protection#26656b75634f48425f6975626654494a4a550b1a47064e5443401b" http: royce.com">royce.com</a>">CMSEindyOSD@rolls-royce.com</a>; Internet: www.rolls-royce.com. You may view this 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 by searching for and locating Docket No. FAA-2014-
0462, 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: Kyri Zaroyiannis, Aerospace Engineer, 
Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 
2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847-294-7836; fax: 
847-294-7834; email: <a href="/cdn-cgi/l/email-protection#cca7b5bea5e2b6adbea3b5a5ada2a2a5bf8caaadade2aba3ba"><span class="__cf_email__" data-cfemail="f79c8e859ed98d9685988e9e9699999e84b7919696d9909881">[email protected]</span></a>.

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 certain RRC AE 2100 series 
turboprop engines and AE 3007A and 3007C series turbofan engines. The 
NPRM published in the Federal Register on October 2, 2014 (79 FR

[[Page 5910]]

59461). The NPRM was prompted by reports of pitting in the wheel bores 
and subsequent RRC analysis that concluded that lower life limits are 
needed for the affected turbine wheels. The NPRM proposed to require 
reducing the approved life limits of the affected turbine wheels and 
performing an ECI of certain RRC engines with affected turbine wheels. 
We are issuing this AD to prevent uncontained failure of the turbine 
wheels, damage to the engine, and damage to the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. An anonymous 
commenter supported the NPRM (79 FR 59461, October 2, 2014).

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes, e.g., verb 
tense changes and word changes appropriate to a final rule. We have 
determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 59461, October 2, 2014) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 59461, October 2, 2014).

Related Service Information

    We reviewed:
    <bullet> Rolls-Royce (RR) Alert Service Bulletin (ASB) No. AE 
2100D2-A-72-085, dated July 25, 2013.
    <bullet> RR ASB No. AE 2100D3-A-72-277, dated July 25, 2013.
    <bullet> RR ASB No. AE 2100P-A-72-019, dated July 25, 2013.
    <bullet> RR ASB No. AE 3007A-A-72-407, Revision 1, dated August 29, 
2014.
    <bullet> RR ASB No. AE 3007A-A-72-408, Revision 1, dated August 29, 
2014.
    <bullet> RR ASB No. AE 3007C-A-72-316, dated December 6, 2013.
    These service bulletins describe procedures for inspecting high-
pressure turbine (HPT) stage 2 wheels and identify life-limit reduction 
for all affected HPT wheels. You can find this information at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0462.

Costs of Compliance

    We estimate that this AD will affect 664 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
hour to perform an ECI in the bore of the turbine wheel for affected 
engines. The average labor rate is $85 per hour. We estimate the pro-
rated replacement cost would be $30,688 for a 1st stage gas generator 
turbine wheel; $63,693 for a HPT stage 1 wheel; $13,941 for an HPT 
stage 2 wheel; and $13,186 for a 4th stage turbine wheel. We also 
estimate that these parts would be replaced during an engine shop visit 
at no additional labor cost. Based on these figures, we estimate the 
total cost of this AD on U.S. operators to be $11,317,969.

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

    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 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):

2015-02-08 Roll-Royce Corporation (Type Certificate previously held 
by Allison Engine Company): Amendment 39-18075; Docket No. FAA-2014-
0462; Directorate Identifier 2014-NE-06-AD.

(a) Effective Date

    This AD is effective March 11, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce Corporation (RRC) AE 2100D2, 
2100D2A, 2100D3, and 2100P turboprop engines and AE 3007A1, A1/1, 
A1/3, A1E, A1P, A2, A3, C, C1, and C2 turbofan engines:
    (1) With an installed 1st stage gas generator turbine wheel, 
part number (P/N) 23079946, 23088906, or 23089692, all serial 
numbers (S/Ns) listed in Table 2 and Table 3 of RRC Alert Service 
Bulletin (ASB) No. AE 2100D2-A-72-085, dated July 25, 2013; and in 
Table 2 and Table 3 of RRC ASB No. AE 2100D3-A-72-277, dated July 
25, 2013.
    (2) With an installed high-pressure turbine (HPT) stage 1 or HPT 
stage 2 wheel, P/N 23079946, 23088906, 23088784, 23084520, 23084781, 
23088817, or 23088818, all S/Ns listed in Table 1 through Table 7 of 
RRC ASB No. AE 3007A-A-72-407, Revision 1, dated August 29, 2014, 
except those S/Ns excluded by Table 1, Table 2, Table 4, and Table 5 
of RRC ASB No. AE 3007A-A-72-407, Revision 1, dated August 29, 2014.
    (3) With an installed HPT stage 2 wheel, P/N 23084520 or 
23088818, all S/Ns listed in Table 1 and Table 2 of RRC ASB No. AE 
3007C-A-72-316, dated December 6, 2013, except those S/Ns excluded 
by Table 1 of RRC ASB No. AE 3007C-A-72-316, dated December 6, 2013.
    (4) With an installed 4th stage turbine wheel, P/N 23083536, all 
S/Ns listed in Table 2 of RRC ASB No. AE 2100P-A-72-019, dated July 
25, 2013.

(d) Unsafe Condition

    This AD was prompted by reports of pitting in the wheel bores 
and subsequent RRC analysis that concluded that lower life

[[Page 5911]]

limits are needed for the affected turbine wheels. We are issuing 
this AD to prevent uncontained failure of the turbine wheels, damage 
to the engine, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) For all RRC AE 3007A1, A1/1, A1/3, A1E, A1P, and A3 series 
engines with an HPT stage 2 wheel P/N and S/N identified in RRC ASB 
No. AE 3007A-A-72-408, Revision 1, dated August 29, 2014, at each 
shop visit after the effective date of this AD, eddy current inspect 
the bore of the affected HPT stage 2 wheels. Use RRC ASB No. AE 
3007A-A-72-408, Revision 1, August 29, 2014, to do the inspection. 
Do not return to service any wheel that fails the inspection 
required by this AD.
    (2) Thirty days after the effective date of this AD, do not 
return to service any engine that has a turbine wheel with a P/N and 
an S/N listed in any of the following RRC ASBs whose wheel life 
exceeds the new life limits identified in the following RRC ASBs:
    (i) RRC ASB No. AE 2100D2-A-72-085, dated July 25, 2013;
    (ii) RRC ASB No. AE 2100D3-A-72-277, dated July 25, 2013;
    (iii) RRC ASB No. AE 2100P-A-72-019, dated July 25, 2013;
    (iv) RRC ASB No. AE 3007A-A-72-407, Revision 1, dated August 29, 
2014; or
    (v) RRC ASB No. AE 3007C-A-72-316, dated December 6, 2013.

(f) Installation Prohibition

    Thirty days after the effective date of this AD, do not install 
an affected wheel, as identified in paragraph (c) of this AD, into 
any RRC AE 3007C2 engine.

(g) Definition

    For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges, except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance is not an 
engine shop visit.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Chicago Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 
to make your request.

(i) Related Information

    For more information about this AD, contact Kyri Zaroyiannis, 
Aerospace Engineer, Chicago Aircraft Certification Office, Small 
Airplane Directorate, FAA, 2300 E. Devon Ave., Des Plaines, IL 
60018; phone: 847-294-7836; fax: 847-294-7834; email: 
<a href="/cdn-cgi/l/email-protection#d6bdafa4bff8acb7a4b9afbfb7b8b8bfa596b0b7b7f8b1b9a0"><span class="__cf_email__" data-cfemail="2f44565d4601554e5d4056464e4141465c6f494e4e01484059">[email protected]</span></a>.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Rolls-Royce Alert Service Bulletin (ASB) No. AE 2100D2-A-72-
085, dated July 25, 2013.
    (ii) Rolls-Royce ASB No. AE 2100D3-A-72-277, dated July 25, 
2013.
    (iii) Rolls-Royce ASB No. AE 2100P-A-72-019, dated July 25, 
2013.
    (iv) Rolls-Royce ASB No. AE 3007A-A-72-407, Revision 1, dated 
August 29, 2014.
    (v) Rolls-Royce ASB No. AE 3007A-A-72-408, Revision 1, dated 
August 29, 2014.
    (vi) Rolls-Royce ASB No. AE 3007C-A-72-316, dated December 6, 
2013.
    (3) For RRC service information identified in this AD, contact 
Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB-01-
06, Indianapolis, IN 46225; phone: 317-230-1667; email: 
<a href="/cdn-cgi/l/email-protection#e9aaa4baac80878d90a6baada99b8685859ac4d588c9819b8c8fd4" http: royce.com">royce.com</a>">CMSEindyOSD@rolls-royce.com</a>; Internet: www.rolls-royce.com.
    (4) You may view this service information at 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.
    (5) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on January 13, 2015.
Thomas A. Boudreau,
Acting Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-01282 Filed 2-3-15; 8:45 am]
BILLING CODE 4910-13-P


</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>