[Federal Register Volume 79, Number 191 (Thursday, October 2, 2014)]
[Proposed Rules]
[Pages 59461-59463]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-23561]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0462; Directorate Identifier 2014-NE-06-AD]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation Turboprop and
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt 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 proposed 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 proposed AD would reduce the approved
life limits of the affected turbine wheels. This proposed AD would also
require an eddy current inspection (ECI) of certain RRC engines with
affected turbine wheels. We are proposing this AD to prevent
uncontained failure of the turbine wheels, damage to the engine, and
damage to the airplane.
DATES: We must receive comments on this proposed AD by December 1,
2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Rolls-Royce Corporation, 450 South Meridian Street, Mail Code NB-01-06,
Indianapolis, IN 46225, phone: 317-230-1667; email: royce.com">CMSEindyOSD@rolls-royce.com; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
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: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2014-0462;
Directorate Identifier 2014-NE-06-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy
[[Page 59462]]
aspects of this proposed AD. We will consider all comments received by
the closing date and may amend this proposed AD because of those
comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Inspections during the manufacturing process revealed higher than
normal pitting in the bore of certain turbine wheels due to a
permanganate cleaning process. Analysis and subsequent testing by RRC
of these affected turbine wheels indicated that these wheels, because
of the potential for pitting in the wheel bores, could not be operated
safely up to their published life limits. For RRC AE 2100 series
turboprop engines, the affected turbine wheels are identified as 1st
stage gas generator turbine wheels and as 4th stage turbine wheels. For
the RRC AE 3007A and 3007C series turbofan engines, the affected
turbine wheels are identified as high-pressure turbine (HPT) stage 1
and stage 2 wheels. Operation of the affected wheels above the new
lower limits represents an unsafe condition.
We are also proposing an ECI for certain RRC AE 3007A engines with
affected turbine wheels because our risk analysis shows that these
engines are operated in a more stringent environment and therefore
require periodic inspections to ensure these engines are operated
safely.
This condition, if not corrected, could result in uncontained
failure of the turbine wheels, damage to the engine, and damage to the
airplane.
Relevant Service Information
We reviewed RRC Alert Service Bulletin (ASB) No. AE 2100D2-A-72-
085, dated July 25, 2013; RRC ASB No. AE 2100D3-A-72-277, dated July
25, 2013; RRC ASB No. AE 2100P-A-72-019, dated July 25, 2013; RRC ASB
No. AE 3007A-A-72-407, Revision 1, dated August 29, 2014; RRC ASB No.
AE 3007A-A-72-408, Revision 1, dated August 29, 2014; and RRC ASB No.
AE 3007C-A-72-316, dated December 6, 2013. RRC ASB No. AE 3007A-A-72-
408 provides instructions on performing an ECI of affected HPT stage 2
wheels. The other RRC ASBs list the lower approved life limits of the
affected turbine wheels.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require an ECI of certain RRC engines with
affected turbine wheels, and reduce the life limits of the affected
turbine wheels.
Costs of Compliance
We estimate that this proposed AD would affect 664 engines
installed on airplanes of U.S. registry. We also estimate that it would
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 work-hour. We
estimate the pro-rated replacement cost would be $30,688 for a 1st
stage gas generator turbine wheel; $63,693 for an 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 the AD to 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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
(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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
Rolls Royce Corporation (Formerly Allison Engine Company): Docket
No. FAA-2014-0462; Directorate Identifier 2014-NE-06-AD.
(a) Comments Due Date
We must receive comments by December 1, 2014.
(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
[[Page 59463]]
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 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 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 RR ASBs whose wheel life
exceeds the new life limits identified in the RR ASBs:
RRC ASB No. AE 2100D2-A-72-085, dated July 25, 2013;
RRC ASB No. AE 2100D3-A-72-277, dated July 25, 2013;
RRC ASB No. AE 2100P-A-72-019, dated July 25, 2013;
RRC ASB No. AE 3007A-A-72-407, Revision 1, dated August 29,
2014; or
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
(1) 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:
[email protected].
(2) RRC ASB No. AE 2100D2-A-72-085, dated July 25, 2013; RRC ASB
No. AE 2100D3-A-72-277, dated July 25, 2013; RRC ASB No. AE 2100P-A-
72-019, dated July 25, 2013; RRC ASB No. AE 3007A-A-72-407, Revision
1, dated August 29, 2014; RRC ASB No. AE 3007A-A-72-408, Revision 1,
dated August 29, 2014; and RRC ASB No. AE 3007C-A-72-316, dated
December 6, 2013, which are not incorporated by reference in this
AD, can be obtained from RRC using the contact information in
paragraph (i)(3) of this AD.
(3) 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:
royce.com">CMSEindyOSD@rolls-royce.com; Internet: www.rolls-royce.com.
(4) 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.
Issued in Burlington, Massachusetts, on September 25, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2014-23561 Filed 10-1-14; 8:45 am]
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