Airworthiness Directives; Rolls-Royce Corporation (RRC) AE 3007A Series Turbofan Engines, 57660-57664 [2010-22370]
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57660
Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations
because it addresses an unsafe condition
that is likely to exist or develop on
product(s) identified in this rulemaking
action.
Regulatory Findings
We 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.
Therefore, I certify this AD:
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); 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 an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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:
■
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2010–19–05 Eurocopter France:
Amendment 39–16433 ; Docket No.
FAA–2010–0426; Directorate Identifier
2009–SW–34–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective on October 27, 2010.
erowe on DSK5CLS3C1PROD with RULES
Applicability
(c) This AD applies to Model SA–365N1,
AS–365N2, AS 365 N3, EC 155B, and
EC155B1 helicopters, with a fenestron tail
rotor blade (blade), part number 365A12–
0060–01 or 365A12–0070–00, installed,
certificated in any category.
15:31 Sep 21, 2010
Jkt 220001
Other Information
(g) Alternative Methods of Compliance
(AMOCs): The Manager, Rotorcraft
Directorate, Safety Management Group, Attn:
DOT/FAA Southwest Region, Gary Roach,
ASW–111, Aviation Safety Engineer,
Regulations and Guidance Group, 2601
Meacham Blvd., Fort Worth, Texas 76137,
telephone (817) 222–5130, fax (817) 222–
5961, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
Related Information
(h) European Aviation Safety Agency
MCAI Airworthiness Directive No. 2006–
0099, dated April 24, 2006, contains related
information.
Other Affected ADs
(b) None.
VerDate Mar<15>2010
Actions and Compliance
(e) Required as indicated:
(1) For the Model SA–365N1, AS–365N2,
and AS 365 N3 helicopters, within 50 hours
time-in-service (TIS), unless done previously,
and thereafter at intervals not to exceed 10
hours TIS, inspect each blade of the fenestron
tail rotor to determine whether there has
been any outward slippage (toward the
shroud) of the stainless steel ring that is
around the sleeve of each blade where the
blade enters the fenestron hub as depicted in
Appendix 1 and by following the
Accomplishment Instructions, paragraph
2.B.1., of Eurocopter Alert Service Bulletin
No. 05.00.49, dated March 1, 2006.
(2) For the Model EC 155B or B1
helicopters, within 50 hours time-in-service
(TIS), unless done previously, and thereafter
at intervals not to exceed 15 hours TIS,
inspect each blade of the fenestron tail rotor
to determine whether there has been any
outward slippage (toward the shroud) of the
stainless steel ring that is around the sleeve
of each blade where the blade enters the
fenestron hub as depicted in Appendix 1 and
by following paragraph 2.B.1., of Eurocopter
Alert Service Bulletin No. 05A011, dated
March 1, 2006.
(3) If the stainless steel ring has slipped
outward, before further flight, replace the
blade with an airworthy blade.
Differences Between This AD and the MCAI
AD
(f) We refer to flying hours as hours timein-service. Also, we use ‘‘inspect’’ rather than
‘‘check’’ to describe the action to be taken in
the AD. We use a different initial compliance
time.
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
Reason
(d) The mandatory continuing
airworthiness information (MCAI) AD reports
the separation and loss of a stainless steel
ring (75 mm in diameter) from a blade sleeve
resulting in severe, high-frequency
vibrations, which can lead to damage to the
fenestron blades, loss of yaw control, and
subsequent loss of control of the helicopter.
Joint Aircraft System/Component (JASC)
Code
(i) The JASC Code is 6400: Tail Rotor.
Material Incorporated by Reference
(j) You must use the specified portions of
Eurocopter Alert Service Bulletins No.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
05A011 and No. 05.00.49, both dated March
1, 2006, to do the actions required.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact American Eurocopter
Corporation, 2701 Forum Drive, Grand
Prairie, TX 75053–4005, telephone (800)
232–0323, fax (972) 641–3710, or at https://
www.eurocopter.com.
(3) You may review copies at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Fort Worth,
Texas 76137; 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: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on September
3, 2010.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2010–23098 Filed 9–21–10; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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 highpressure 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
SUMMARY:
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Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations
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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:
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: kyri.zaroyiannis@faa.gov;
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-sincenew (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 https://
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.
VerDate Mar<15>2010
15:31 Sep 21, 2010
Jkt 220001
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
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
57661
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.
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Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations
engines are installed on, but not limited to,
Empresa Brasileira de Aeronautica S. A.
(EMBRAER) EMB–135 and EMB–145
airplanes.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
■
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.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
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
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
MM507646
MM508144
MM508153
MM508176
MM508186
MM508188
MM508205
MM508208
MM508211
MM508221
MM508241
MM508248
MM508251
MM508264
MM508305
MM508311
MM508319
MM508320
MM508322
MM508337
MM508338
MM508382
MM508387
TABLE 2—HPT STAGE 2 WHEEL, P/N
23074462 BY S/N EXCLUDED FROM
INSPECTION
REQUIREMENTS
(g)
THROUGH (i) OF THIS AD
MM504890
MM504963
MM504990
MM504995
MM505007
MM505025
MM505034
MM505041
MM505045
MM505046
MM505017
MM505048
MM505054
MM505055
MM505056
MM505061
All ‘MM’ prefix S/Ns
higher than
MM505061
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]
For HPT stage 2 wheels with the following CSN on the effective date of
this AD:
(3) 17,500 or more CSN ...........................................................................
(4) 10,000 to 17,499 CSN ........................................................................
(5) 9,999 or fewer CSN ............................................................................
Credit for Previous Inspections
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(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.
15:31 Sep 21, 2010
Jkt 220001
Remove engine from service or inspect before next flight.
15 CIS.
Before accumulating 10,015 CSN.
TABLE 4—S/NS OF HPT STAGE 2
WHEELS TO BE INSPECTED BY SB
AE 3007A–72–367
TABLE 4—S/NS OF HPT STAGE 2
WHEELS TO BE INSPECTED BY SB
AE 3007A–72–367—Continued
[ECI Method Only]
[ECI Method Only]
HPT stage 2 wheels requiring ECI method
only
MM119400
MM119480
MM119508
MM155847
MM155907
MM155908
MM183236
MM183362
MM183754
VerDate Mar<15>2010
Remove engine from service or inspect wheel within the following cycles-in-service (CIS) after the effective date of this AD:
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MM183796
MM183808
MM183831
MM228730
MM228951
MM503748
MM504004
MM57188
MM57440
Fmt 4700
Sfmt 4700
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
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New, Reduced Engine Cycle Life Limit and
Removal From Service
SB AE 3007A–72–368, Revision 3, dated May
24, 2010; or RRC SB AE 3007A–72–369,
Revision 2, dated November 5, 2009.
(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
Repetitive Inspection
(i) Thereafter, within 3,000 cycles-sincelast 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.
57663
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
MM508144
MM508153
MM508176
MM508186
MM508188
MM508205
MM508208
MM508211
MM508221
MM508241
MM508248
(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.
MM508251
MM508264
MM508305
MM508311
MM508319
MM508320
MM508322
MM508337
MM508338
MM508382
MM508387
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: kyri.zaroyiannis@faa.gov; 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: indy.pubs.services@rollsroyce.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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
TABLE 6—INCORPORATION BY REFERENCE
Page
Alert Service Bulletin AE 3007A–A–72–367, Total Pages: 8 ........................................
Service Bulletin AE 3007A–72–368, Total Pages: 23 ...................................................
Service Bulletin AE 3007A–72–369, Total Pages: 22 ...................................................
erowe on DSK5CLS3C1PROD with RULES
Rolls-Royce Corporation Service Information No.
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Revision
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Date
June 22, 2009.
May 24, 2010.
November 5, 2009.
57664
Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations
(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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0926; Directorate
Identifier 2010–CE–024–AD; Amendment
39–16435; AD 2010–20–01]
RIN 2120–AA64
Airworthiness Directives; G ROB–
WERKE Model G120A Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by the aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
SUMMARY:
erowe on DSK5CLS3C1PROD with RULES
GROB Aircraft AG has been informed that
flap ribs P/N 120A–1053 and 120A–1054
have been found cracked during regular
maintenance. Structural failure of the ribs
may cause failure of the middle flap support
which may lead to flap asymmetry due to
excessive flap deformation and ultimately
could result in reducing the controllability of
the aeroplane.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
October 12, 2010.
On October 12, 2010, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in this AD.
We must receive comments on this
AD by November 8, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
VerDate Mar<15>2010
15:31 Sep 21, 2010
Jkt 220001
• 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: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; 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 street address for
the Docket Office (telephone (800) 647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Greg
Davison, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4130; fax: (816)
329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued Emergency AD
No.: 2010–0140, dated July 2, 2010
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
GROB Aircraft AG has been informed that
flap ribs P/N 120A–1053 and 120A–1054
have been found cracked during regular
maintenance. Structural failure of the ribs
may cause failure of the middle flap support
which may lead to flap asymmetry due to
excessive flap deformation and ultimately
could result in reducing the controllability of
the aeroplane.
Pending further investigation on the root
source for the cracks, including review of the
original proofs of compliance, temporary
limitations for flap operations were
established until terminating action
development.
EASA AD 2010–0065–E required a
repetitive inspection of the RH and LH flap
ribs. EASA AD 2010–0065–E is superseded
as a terminating action has been developed
by Grob Aircraft AG.
This AD, which supersedes EASA AD
2010–0065–E retaining its requirements,
additionally requires accomplishment of
repair N° 1121–017 and modification N°
1121–018 for aeroplanes on which cracks
have been found or accomplishment of
modification N° 1121–018 only for
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
aeroplanes on which no crack has been
found.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
GROB Aircraft AG has issued Service
Bulletin No. ASB1121–113/1, dated
May 18, 2010; Repair Instruction No.
RI–1121–017, dated April 1, 2010; and
Repair Instruction No. RI–1121–018,
dated May 18, 2010. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of the AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all
information provided by the State of
Design Authority and determined the
unsafe condition exists and is likely to
exist or develop on other products of the
same type design.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might have also required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are described in a
separate paragraph of the AD. These
requirements take precedence over
those copied from the MCAI.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because during regular
maintenance, cracks have been found in
the flap ribs. If not corrected, structural
failure of the ribs may cause failure of
the middle flap support, which could
lead to flap asymmetry, due to excessive
E:\FR\FM\22SER1.SGM
22SER1
]]>Agencies
[Federal Register Volume 75, Number 183 (Wednesday, September 22, 2010)]
[Rules and Regulations]
[Pages 57660-57664]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-22370]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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:
kyri.zaroyiannis@faa.gov; 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 https://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 ......................
------------------------------------------------------------------------
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
------------------------------------------------------------------------
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:
kyri.zaroyiannis@faa.gov; 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:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Table 6--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
[[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
