[Federal Register Volume 79, Number 2 (Friday, January 3, 2014)]
[Rules and Regulations]
[Pages 344-346]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-30734]
[[Page 344]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0811; Directorate Identifier 2008-NE-41-AD;
Amendment 39-17715; AD 2013-26-06]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are superseding airworthiness directive (AD) 2010-19-01 for
certain Rolls-Royce Corporation (RRC) AE 3007A series turbofan engines.
AD 2010-19-01 required removing certain high-pressure turbine (HPT)
stage 2 wheels, or performing inspections on them, and reduced their
approved life limits. This new AD clarifies the AE 3007A turbofan
engine model applicability, further reduces the approved life limits of
affected HPT stage 2 wheels, and eliminates the inspections required by
the existing AD. This AD was prompted by additional analysis that
concluded that lower life limits for the affected HPT stage 2 wheels
are necessary. We are issuing this AD to prevent uncontained failure of
the HPT stage 2 wheel, damage to the engine, and damage to the
airplane.
DATES: This AD is effective February 7, 2014.
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: 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-2009-
0811; 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: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010-19-01, Amendment 39-16429 (75 FR 57660,
September 22, 2010), (``AD 2010-19-01''). AD 2010-19-01 applied to the
specified products. The NPRM published in the Federal Register on
August 8, 2013 (78 FR 48339). The NPRM proposed to clarify the AE 3007A
turbofan engine model applicability, further reduce the approved life
limits of affected HPT stage 2 wheels, and eliminate the inspections
required by the existing AD.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
and the FAA's response to each comment.
Request To Clarify Applicability
One commenter indicated that the compliance section may lead the
operator to remove all engines with HPT stage 2 wheels, part number (P/
N) 23074462, while only a few engines are affected. He noted that
compliance paragraphs in previous ADs on HPT stage 2 wheels used tables
to identify affected and non-affected wheels.
We do not agree. The applicability section of this AD states that
the AD applies to RRC AE 3007A, A1, A1/1, A1/2, A1/3, A1P, A1E, and A3
turbofan engines with an installed HPT stage 2 wheel, P/N 23084520 or
P/N 23069438, 23069592, 23074462, 23074644, or 23075345, except for the
HPT stage 2 wheel serial numbers listed in Table 2 through Table 5 of
RRC Alert Service Bulletin (ASB) No. AE 3007A-A-72-414, Revision 1,
dated December 5, 2012. Therefore, as noted in the AD, operators do not
need to remove engines with HPT stage 2 wheels, P/N 23074462 with the
serial numbers listed in Table 2 through Table 5 of this ASB. We did
not change this AD.
Request Not To Reduce Life Limits
One commenter indicated that eddy current inspections (ECIs) or
surface wave ultrasonic test (SWUT) inspections of the HPT stage 2
wheels have proven satisfactory to this point as there have been no
failures of engines in service worldwide. The commenter noted that
reducing the life limit for these HPT stage 2 wheels is not justified.
We do not agree. Per FAA risk guidelines as published in Advisory
Circular (AC) No. 39-8 ``Continued Airworthiness Assessments Of
Powerplant And Auxiliary Power Unit Installations Of Transport Category
Airplanes,'' dated September 8, 2003 (online at http://www.faa.gov/documentLibrary/media/Advisory_Circular/AC39-8.pdf), we do not rely on
recurring inspections to serve as a final corrective action unless
there is no practicable alternative. In this case, analysis and testing
performed on the affected wheels by RRC has shown that the life limit
for the affected wheels must be reduced. We did not change this AD.
Request Not To Issue AD
The same commenter noted that reduced life limits are already
required based on an ASB published by RRC and incorporation of these
life limits in the new RRC Engine Maintenance Manual (EMM), dated
January 20, 2013. Operators have to consider these updates in their own
maintenance programs. Therefore, an AD is not necessary.
We do not agree. Companies cannot mandate that operators follow new
life limits. AD compliance is mandatory. We did not change this AD.
Request To Revise the Cost of Compliance Estimate
The same commenter requested that the FAA include the number of
aircraft affected worldwide in its cost of compliance estimate. He also
indicated that cost of compliance should include an estimated labor
cost of $250 per engine for each HPT stage 2 wheel change.
We do not agree. First, our ADs apply only to U.S. registered or
operated products, not to products registered elsewhere. Therefore,
costs to operators registered elsewhere are speculative.
Second, our cost estimate in this AD is based on the pro-rated cost
of the reduction in life to the wheel. The labor cost of replacing the
wheel is the same as it would be if the life of the wheel had not been
changed. We did not change this AD.
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Request To Continue Inspections and Related Compliance Issues
The same commenter suggested revising the compliance section of
this AD by continuing with ECIs and/or SWUT inspections at the interval
required by AD 2010-19-01 (75 FR 57660, September 22, 2010) or if the
inspections are not performed at the required interval, then (1) the
new life limit published in the RRC EMM, dated January 20, 2013, shall
be considered; (2) at the next engine shop visit or when the life limit
is reached, the affected parts will be changed; and (3) no engine can
be released from an engine shop with life limits that exceed those
published in the RRC EMM, dated January 20, 2013.
The commenter asked that if this change cannot be accepted, then
RRC should be required to lend an engine to the operator free of charge
and change the HPT wheels free of charge.
The commenter also indicated that providing a grace period of 15
cycles in service before removal of the engine for an issue that has
been known and managed for the last 5 years without incident is not
justified.
We do not agree. Repetitive inspection of the affected HPT wheels
is not a replacement for reduction in their life limit. As stated
above, based on FAA risk guidelines as published in AC 39-8, we do not
rely on recurring inspections to serve as a final corrective action
unless there is no practicable alternative. In the case of these
affected wheels, analysis has shown that the life of these wheels must
be reduced. Second, requests for warranty support, i.e., that RRC
provide a free lease engine and free replacement HPT stage 2 wheel are
economic issues between the operator and the original equipment
manufacturer. Third, successful performance of a part has no effect on
the need to remove that part once it has reached its life limit.
However, we are providing a 15-cycle allowance to minimize disruptions
to operators. This grace period is supported by our risk assessment. We
did not change this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD as proposed.
Costs of Compliance
We estimate that this AD affects 18 engines installed on airplanes
of U.S. registry. We also estimate that a replacement HPT stage 2 wheel
costs about $145,524, and that it will 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 $2,619,432.
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 have 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 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 removing airworthiness directive (AD)
2010-19-01, Amendment 39-16429 (75 FR 57660, September 22, 2010) and
adding the following new AD:
2013-26-06 Rolls-Royce Corporation (Formerly Allison Engine
Company): Amendment 39-17715; Docket No. FAA-2009-0811; Directorate
Identifier 2008-NE-41-AD.
(a) Effective Date
This AD is effective February 7, 2014.
(b) Affected ADs
This AD supersedes AD 2010-19-01, Amendment 39-16429 (75 FR
57660, September 22, 2010).
(c) Applicability
This AD applies to the following Rolls-Royce Corporation (RRC)
AE 3007A, A1, A1/1, A1/2, A1/3, A1P, A1E, and A3 turbofan engines:
(1) With an installed high-pressure turbine (HPT) stage 2 wheel,
part number (P/N) 23084520, or
(2) With an installed HPT stage 2 wheel, P/N 23069438, 23069592,
23074462, 23074644, or 23075345, except for the HPT stage 2 wheel
serial numbers listed in Table 2 through Table 5 of RRC Alert
Service Bulletin (ASB) No. AE 3007A-A-72-414, Revision 1, dated
December 5, 2012. Those HPT stage 2 wheels maintain their existing
approved life limits.
(d) Unsafe Condition
This AD was prompted by additional analysis that concluded that
lower life limits for the affected HPT stage 2 wheels are necessary.
We are issuing this AD to prevent uncontained failure of the HPT
stage 2 wheel, 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 HPT stage 2 wheels, P/N 23069438 and P/N 23069592, do
the following:
(i) For HPT stage 2 wheels that have 9,500 cycles since new
(CSN) or more on the effective date of this AD, remove the HPT stage
2 wheel from service within 15 cycles-in-service (CIS) after the
effective date of this AD.
(ii) After the effective date of this AD, do not approve for
return to service any engine with an HPT stage 2 wheel, P/N 23069438
or P/N 23069592, that exceeds the new life limit of 9,500 CSN.
(2) For HPT stage 2 wheels, P/N 23074462, do the following:
(i) For AE 3007A1E turbofan engines with HPT stage 2 wheels
installed that have 7,500
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CSN or more on the effective date of this AD, and for the AE 3007A,
A1, A1/1, A1/2, A1/3, A1P, and A3 turbofan engines with HPT stage 2
wheels installed that have 9,500 CSN or more on the effective date
of this AD, remove the wheel from service within 15 CIS after the
effective date of this AD.
(ii) Thereafter:
(A) Do not approve for return to service any AE 3007A1E turbofan
engine with an HPT stage 2 wheel, P/N 23074462, installed, that
exceeds the new life limit of 7,500 CSN; and
(B) Do not approve for return to service any AE 3007A, A1, A1/1,
A1/2, A1/3, A1P, and A3 turbofan engines with an HPT stage 2 wheel,
P/N 23074462, installed, that exceeds the new life limit of 9,500
CSN.
(C) Throughout the life of the HPT stage 2 wheel, always use the
lowest life limit applicable to any engine model in which the part
was used in service. If life usage records are not sufficient to
identify all engine models in which the part has been flown, the
lowest life applicable to any engine model for which the part is
eligible must be used.
(3) For HPT stage 2 wheels, P/N 23074644 and P/N 23075345, do
the following:
(i) For HPT stage 2 wheels that have 9,500 CSN or more on the
effective date of this AD, remove the HPT stage 2 wheel from service
within 15 CIS after the effective date of this AD.
(ii) Thereafter, do not approve for return to service any engine
with an HPT stage 2 wheel, P/N 23074644 or P/N 23075345, installed,
that exceeds the new life limit of 9,500 CSN.
(4) For HPT stage 2 wheels, P/N 23084520, do the following:
(i) For HPT stage 2 wheels that have 23,000 CSN or more on the
effective date of this AD, remove the HPT stage 2 wheel from service
before the next flight after the effective date of this AD.
(ii) Thereafter, do not approve for return to service any engine
with an HPT stage 2 wheel, P/N 23084520, installed, that exceeds the
new life limit of 23,000 CSN.
(f) Alternative Methods of Compliance
The Manager, Chicago Aircraft Certification Office, may approve
alternative methods of compliance for this AD. Use the procedures 14
CFR 39.19 to make your request.
(g) 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 3007A-A-72-414, Revision 1, dated December 5,
2012, which is not incorporated by reference in this AD, can be
obtained from RRC, using the contact information in paragraph (g)(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.
(h) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on December 17, 2013.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2013-30734 Filed 1-2-14; 8:45 am]
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