[Federal Register Volume 75, Number 183 (Wednesday, September 22, 2010)]
[Rules and Regulations]
[Pages 57660-57664]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-22370]
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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 39-16429; AD 2010-19-01]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation (RRC) AE 3007A
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for RRC AE 3007A series turbofan engines. That AD currently
requires performing an eddy current inspection (ECI) or surface wave
ultrasonic test (SWUT) inspection on each affected high-pressure
turbine (HPT) wheel. This AD requires removing or performing initial
and repetitive ECIs or SWUT inspections on HPT stage 2 wheels for
cracks. This AD also reduces the approved life limits of certain HPT
stage 2 wheels. This AD results from reports of cracked HPT stage 2
wheels. We are issuing this AD to prevent uncontained failure of the
HPT stage 2 wheel and damage to the airplane.
DATES: This AD becomes effective October 27, 2010. The Director of the
Federal Register approved the incorporation by reference of certain
[[Page 57661]]
publications listed in the regulations as of October 27, 2010.
ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce Corporation, P.O. Box 420, Speed Code U15,
Indianapolis, IN 46206-0420, e-mail: royce.com">indy.pubs.services@rolls-royce.com.
The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer,
Chicago Aircraft Certification Office, Small Airplane Directorate, FAA,
2300 E. Devon Ave., Des Plaines, IL 60018; e-mail:
[email protected]; telephone (847) 294-7836; fax (847) 294-7834.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by
superseding AD 2009-08-51, Amendment 39-15905 (74 FR 22091, May 12,
2009), with a proposed AD. The proposed AD applies to RRC AE 3007A
series turbofan engines. We published the proposed AD in the Federal
Register on February 18, 2010 (75 FR 7209). That action proposed to
require:
Removing from service, any engine with certain part number
(P/N) HPT stage 2 wheels that have a cycles-since-new (CSN) specified
in Table 1 of this AD, by the compliance time specified in Table 1 of
this AD; or
Performing an ECI or SWUT inspection on certain P/N HPT
stage 2 wheels that have a CSN specified in Table 1 of this AD by the
compliance time specified in Table 1 of this AD; and
Performing repetitive ECI or SWUT inspections of the HPT
stage 2 wheels within 3,000 cycles-since-last inspection.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
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 street address for
the Docket Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Clarify Repetitive Inspection Paragraph
One commenter asks us to clarify paragraph (i) of the proposed AD,
which states ``Thereafter, within 3,000 cycles since last inspection,
remove the engine from service * * *'' The commenter asks if the last
inspection means those inspections performed to comply with ADs 2008-
19-51, 2008-26-06 and 2009-08-51. The commenter feels paragraph (i) of
the proposed AD is not clear.
We agree. We changed paragraph (i) of this AD to ``Thereafter,
within 3,000 cycles-since-last inspection performed as a result of this
AD or its predecessor ADs (Emergency ADs 2008-19-51, AD 2008-26-06, and
2009-08-51), remove the engine from service * * *
Request To Credit for Work Done to Previous Revisions of the Service
Bulletins
Four commenters ask us to allow credit for initial and repetitive
inspections performed using previous versions of RRC Alert Service
Bulletin (ASB) AE 3007A-A-72-367, Revision 2, dated June 22, 2009,
Service Bulletin (SB) AE 3007A-72-176, Revision 5, dated September 2,
2008; SB AE 3007A-72-215, Revision 2, dated September 28, 2009; SB AE
3007A-72-368, Revision 3, dated May 24, 2010; and SB AE 3007A-72-369,
Revision 2, dated November 5, 2009.
We agree. We added paragraph (g)(6) to allow credit for initial and
repetitive inspections performed using earlier versions of RRC ASB AE
3007A-A-72-367, Revision 2, dated June 22, 2009; SB AE 3007A-72-368,
Revision 3, dated May 24, 2010; and SB AE 3007A-72-369, Revision 2,
dated November 5, 2009. We also changed paragraph (l) of this AD to
state ``For wheels, P/N 23069438 * * * RRC SB AE 3007A-72-176, Revision
5, dated September 2, 2008, or earlier version; or SB AE 3007A-72-215,
Revision 2, dated September 28, 2009, or earlier version, remove the
wheel before exceeding the new, reduced ECLL of 10,000 CSN.''
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 1402 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 2
work-hours per engine to perform both the ECI and SWUT. The average
labor rate is $85 per work-hour. No parts are required for the
inspection. We estimate the prorated life lost per stage 2 wheel is
about $13,177. Based on these figures, we estimate the total cost of
the AD to U.S. operators to be $18,712,494. This estimate is exclusive
of any warranty coverage.
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); and
(3) 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 57662]]
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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 Amendment 39-15905 (74 FR
22091, May 12, 2009), and by adding a new airworthiness directive,
Amendment 39-16429, to read as follows:
2010-19-01 Rolls-Royce Corporation (Formerly Allison Engine
Company): Amendment 39-16429. Docket No. FAA-2009-0811; Directorate
Identifier 2008-NE-41-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
27, 2010.
Affected ADs
(b) This AD supersedes AD 2009-08-51, Amendment 39-15905.
Applicability
(c) This AD applies to Rolls-Royce Corporation (RRC) AE 3007A
series turbofan engines with high-pressure turbine (HPT) stage 2
wheels, part numbers (P/Ns) 23069438, 23069592, 23074462, 23074644,
23075345, or 23084520 installed. These engines are installed on, but
not limited to, Empresa Brasileira de Aeronautica S. A. (EMBRAER)
EMB-135 and EMB-145 airplanes.
Unsafe Condition
(d) This AD results from reports of cracked HPT stage 2 wheels.
We are issuing this AD to prevent uncontained failure of the HPT
stage 2 wheel and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
HPT Stage 2 Wheels Exempted From the Inspection Requirements of This AD
(f) The following engines are exempt from the inspection
requirements of this AD:
(1) All engines with an HPT stage 2 wheel, P/N 23084520.
(2) All engines with an HPT stage 2 wheel, P/N 23075345, that
has a serial number (S/N) specified in Table 1 of this AD, and
(3) All engines with an HPT stage 2 wheel, P/N 23074462, that
has a S/N specified in Table 2 of this AD.
Table 1--HPT Stage 2 Wheel, P/N 23075345 by S/N Excluded From Inspection
Requirements (g) Through (i) of This AD
------------------------------------------------------------------------
------------------------------------------------------------------------
MM507646 MM508211 MM508319
MM508144 MM508221 MM508320
MM508153 MM508241 MM508322
MM508176 MM508248 MM508337
MM508186 MM508251 MM508338
MM508188 MM508264 MM508382
MM508205 MM508305 MM508387
MM508208 MM508311 ......................
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Table 2--HPT Stage 2 Wheel, P/N 23074462 by S/N Excluded From Inspection
Requirements (g) Through (i) of This AD
------------------------------------------------------------------------
------------------------------------------------------------------------
MM504890 MM505025 MM505054
MM504963 MM505034 MM505055
MM504990 MM505041 MM505056
MM504995 MM505045 MM505061
MM505007 MM505046 All `MM' prefix S/Ns
higher than MM505061
MM505017 MM505048 All S/Ns with `MW'
prefix
------------------------------------------------------------------------
Initial Eddy Current Inspection (ECI) or Surface Wave Ultrasonic
Testing (SWUT) Inspection
(g) For engines with an HPT stage 2 wheel, P/Ns 23069438,
23069592, 23074462, 23074644, or 23075345, remove the engine from
service or perform an initial inspection of the wheel by the cycle
limit specified in Table 3 of this AD. Use one of the following
methods for the inspection:
(1) For HPT stage 2 wheels that have S/Ns listed in Table 4 of
this AD, use paragraphs 2.A. through 2.C.(4) of RRC Alert Service
Bulletin (ASB) AE 3007A-A-72-367, Revision 2 dated June 22, 2009, to
inspect the wheel.
(2) For HPT stage 2 wheels that have S/Ns not listed in Table 4
of this AD, use paragraphs 2.A. through 2.C.(4) of RRC ASB AE 3007A-
A-72-367, Revision 2, dated June 22, 2009, or use paragraphs 2.A.
through 2.N. of RRC Service Bulletin (SB) AE 3007A-72-368, Revision
3, dated May 24, 2010; or use 2.A. through 2.V.(4) of RRC SB AE
3007A-72-369, Revision 2, dated November 5, 2009, to perform the
inspections.
Table 3--Compliance Times for Engine Removal or ECI or SWUT Inspection
of the HPT Stage 2 Wheels by Cycles-Since-New
[CSN]
------------------------------------------------------------------------
Remove engine from service or
For HPT stage 2 wheels with the inspect wheel within the
following CSN on the effective date of following cycles-in-service
this AD: (CIS) after the effective date
of this AD:
------------------------------------------------------------------------
(3) 17,500 or more CSN................. Remove engine from service or
inspect before next flight.
(4) 10,000 to 17,499 CSN............... 15 CIS.
(5) 9,999 or fewer CSN................. Before accumulating 10,015 CSN.
------------------------------------------------------------------------
Credit for Previous Inspections
(6) Inspections performed before the effective date of this AD
using earlier versions of RRC ASB AE 3007A-A-72-367 or RRC SB AE
3007A-72-368 or RRC SB AE 3007A-72-369 comply with the requirements
of paragraphs (g)(1) and (g)(2) of this AD.
Table 4--S/Ns of HPT Stage 2 Wheels to be Inspected by SB AE 3007A-72-
367
[ECI Method Only]
------------------------------------------------------------------------
------------------------------------------------------------------------
HPT stage 2 wheels requiring ECI method only
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MM119400 MM183796
MM119480 MM183808
MM119508 MM183831
MM155847 MM228730
MM155907 MM228951
MM155908 MM503748
MM183236 MM504004
MM183362 MM57188
MM183754 MM57440
MM183762 MM57480
------------------------------------------------------------------------
Installation Prohibition
(h) After the effective date of this AD, don't return to
service, any HPT stage 2 wheel that was installed in any RRC AE
3007A series engine that has been removed as a result of the
inspection requirements of this AD, unless the HPT stage 2 wheel was
inspected as specified in RRC ASB AE 3007A-A-72-367, Revision 2,
dated June 22, 2009; or RRC
[[Page 57663]]
SB AE 3007A-72-368, Revision 3, dated May 24, 2010; or RRC SB AE
3007A-72-369, Revision 2, dated November 5, 2009.
Repetitive Inspection
(i) Thereafter, within 3,000 cycles-since-last inspection
performed as a result of this AD or its predecessor ADs (Emergency
ADs 2008-19-51, AD 2008-26-06, and 2009-08-51), remove the engine
from service until an ECI or SWUT inspection is performed on the HPT
stage 2 wheel. Use paragraphs 2.A. through 2.C.(4) of RRC ASB AE
3007A-A-72-367, Revision 2, dated June 22, 2009, or use paragraphs
2.A. through 2.N. of RRC SB AE 3007A-72-368, Revision 3, dated May
24, 2010; or use 2.A. through 2.V.(4) of RRC SB AE 3007A-72-369,
Revision 2, dated November 5, 2009, to inspect the wheel.
New, Reduced Engine Cycle Life Limit and Removal From Service
(j) For HPT stage 2 wheels, P/N 23084520, do the following:
(1) For wheels that have 22,985 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.
(2) Thereafter, remove HPT stage 2 wheels, P/N 23084520, before
exceeding the new, reduced engine cycle life limit (ECLL) of 23,000
CSN.
(k) For HPT stage 2 wheels, P/N 23075345 and 23074644, do the
following:
(1) For wheels that have 19,985 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 unless paragraph (k)(3) of this AD
applies.
(2) Thereafter, remove HPT stage 2 wheels, P/N 23075345 and
23074644, before exceeding the new, reduced ECLL of 20,000 CSN.
(3) For HPT stage 2 wheels, P/N 23075345, that have a S/N listed
in Table 5 of this AD and that have 22,985 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.
(4) Thereafter, for HPT stage 2 wheels, P/N 23075345, that have
a S/N listed in Table 5 of this AD, remove the wheel from service
before exceeding the new, reduced ECLL of 23,000 CSN.
Table 5--S/Ns of HPT Stage 2 Wheel, P/N 23075345, Eligible To Remain in
Service Until 23,000 CSN
------------------------------------------------------------------------
------------------------------------------------------------------------
MM507646 MM508205 MM508251 MM508322
MM508144 MM508208 MM508264 MM508337
MM508153 MM508211 MM508305 MM508338
MM508176 MM508221 MM508311 MM508382
MM508186 MM508241 MM508319 MM508387
MM508188 MM508248 MM508320 ................
------------------------------------------------------------------------
(l) For wheels, P/N 23069438, in engines that have not complied
with RRC SB AE 3007A-72-176, Revision 5, dated September 2, 2008, or
earlier version; or SB AE 3007A-72-215, Revision 2, dated September
28, 2009, or earlier version, remove the wheel before exceeding the
new, reduced ECLL of 10,000 CSN.
(m) For wheels, P/N 23069438, in engines that have complied with
RRC SB AE 3007A-72-176, Revision 5, dated September 2, 2008, or
earlier version; or SB AE 3007A-72-215, Revision 2, dated September
28, 2009, or earlier version; do the following:
(1) For wheels that have 19,985 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.
(2) Thereafter, remove the wheel from service before exceeding
the new, reduced ECLL of 20,000 CSN.
Alternative Methods of Compliance
(n) The Manager, Chicago Aircraft Certification Office, has the
authority to approve alternative methods of compliance for this AD
if requested using the procedures found in 14 CFR 39.19.
Special Flight Permits
(o) Under 14 CFR 39.23, we are limiting the special flight
permits for this AD by restricting the flight to essential flight
crew only.
Related Information
(p) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago
Aircraft Certification Office, Small Airplane Directorate, FAA, 2300
E. Devon Ave., Des Plaines, IL 60018; e-mail:
[email protected]; telephone (847) 294-7836; fax (847) 294-
7834, for more information about this AD.
Material Incorporated by Reference
(q) You must use the service information specified in Table 6 of
this AD to perform the inspections required by this AD. The Director
of the Federal Register approved the incorporation by reference of
the documents listed in Table 6 of this AD in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. You can get a copy from Rolls-Royce
Corporation, P.O. Box 420, Indianapolis, IN 46206; telephone (317)
230-3774; fax (317) 230-8084; e-mail: royce.com">indy.pubs.services@rolls-royce.com. You may review copies at the FAA, New England Region, 12
New England Executive Park, Burlington, MA; or 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.
Table 6--Incorporation by Reference
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Rolls-Royce Corporation Service
Information No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin AE 3007A-A-72- ALL..................... 2 June 22, 2009.
367, Total Pages: 8.
Service Bulletin AE 3007A-72-368, ALL..................... 3 May 24, 2010.
Total Pages: 23.
Service Bulletin AE 3007A-72-369, ALL..................... 2 November 5, 2009.
Total Pages: 22.
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[[Page 57664]]
(Only the transmittal letter for Alert Service Bulletin (ASB) AE
3007A-A-72-367, Revision 2, dated June 22, 2009, identifies this
service bulletin as an ASB; no other page of this document contains
this information.)
Issued in Burlington, Massachusetts, on September 1, 2010.
Robert G. Mann,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-22370 Filed 9-21-10; 8:45 am]
BILLING CODE 4910-13-P