Airworthiness Directives; Rolls-Royce Corporation (RRC) AE 3007A Series Turbofan Engines, 78927-78929 [E8-30051]
Download as PDF
Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations
Moreover, it is likely that Surrey County
is the origin of only a negligible share
of the United Kingdom’s exports of
ruminant and swine products to the
United States, given the relatively small
size of that county’s ruminant and
swine inventories. As reported by the
United Kingdom’s Department for
Environment, Food, and Rural Affairs,
only 0.6 percent of England’s cattle, 0.2
percent of its swine, 0.4 percent of its
sheep, and 1.4 percent of its goats were
located in Surrey County in June 2007.4
Under these circumstances, the
Administrator of the Animal and Plant
Health Inspection Service has
determined that this action will not
have a significant economic impact on
a substantial number of small entities.
List of Subjects in 9 CFR Part 94
Animal diseases, Imports, Livestock,
Meat and meat products, Milk, Poultry
and poultry products, Reporting and
recordkeeping requirements.
Accordingly, the interim rule
amending 9 CFR part 94 that was
published at 73 FR 5424–5426 on
January 30, 2008, is adopted as a final
rule with the following changes:
■
pwalker on PROD1PC71 with RULES
Authority: 7 U.S.C. 450, 7701–7772, 7781–
7786, and 8301–8317; 21 U.S.C. 136 and
136a; 31 U.S.C. 9701; 7 CFR 2.22, 2.80, and
371.4.
§ 94.1
[Amended]
2. In § 94.1, paragraph (a)(2) is
amended by removing the words
‘‘(except for Surrey County, England)’’.
■
[Amended]
3. In § 94.11, paragraph (a) is amended
by removing the words ‘‘(except for
Surrey County, England)’’.
■
This is a substantive rule that relieves
restrictions and, pursuant to the
provisions of 5 U.S.C. 553, may be made
effective less than 30 days after
publication in the Federal Register.
This rule restores Surrey County,
England, to the list of regions of the
world that are considered free of
rinderpest and FMD, and to the list of
regions of the world considered free of
rinderpest and FMD but subject to
additional importation restrictions
because of those regions’ proximity to or
trading relationships with FMD-affected
regions. We have determined that
approximately 2 weeks are needed to
ensure that APHIS and the Department
of Homeland Security, Bureau of
Customs and Border Protection,
personnel at ports of entry receive
official notice of this change in the
regulations. Therefore, the
Administrator of the Animal and Plant
Health Inspection Service has
determined that this rule should be
effective 15 days after publication in the
Federal Register.
4 Department for Environment, Food, and Rural
Affairs (DEFRA), UK. June 2007 Agricultural and
Horticultural Survey—England. https://
www.defra.gov.uk/esg/work_htm/publications/cs/
farmstats_web/2_SURVEY_DATA_SEARCH/
COMPLETE_DATASETS/PSM/RegCountUA_07.xls.
19:28 Dec 23, 2008
1. The authority citation for part 94
continues to read as follows:
■
§ 94.11
Effective Date
VerDate Aug<31>2005
PART 94—RINDERPEST, FOOT-ANDMOUTH DISEASE, FOWL PEST (FOWL
PLAGUE), EXOTIC NEWCASTLE
DISEASE, AFRICAN SWINE FEVER,
CLASSICAL SWINE FEVER, AND
BOVINE SPONGIFORM
ENCEPHALOPATHY: PROHIBITED
AND RESTRICTED IMPORTATIONS
Jkt 217001
Done in Washington, DC, this 16th day of
December 2008.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
[FR Doc. E8–30724 Filed 12–23–08; 8:45 am]
BILLING CODE 3410–34–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0975; Directorate
Identifier 2008–NE–29–AD; Amendment 39–
15772; AD 2008–26–06]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Corporation (RRC) AE 3007A Series
Turbofan Engines
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is superseding
emergency airworthiness directive (AD)
2008–19–51 that we sent previously to
all known U.S. owners and operators of
RRC AE 3007A series turbofan engines.
That AD requires performing initial and
repetitive eddy current inspections
(ECIs) on the high-pressure turbine
(HPT) stage 2 wheel for cracks. This AD
continues to require those same
inspections, but revises the compliance
schedule for the initial inspection and
specifies the affected HPT stage 2
wheels by part number (P/N). This AD
results from reports of cracked HPT
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
78927
stage 2 wheels. We are issuing this AD
to detect cracks in the HPT stage 2
wheel, which could result in a possible
uncontained failure of the HPT stage 2
wheel and damage to the airplane.
DATES: Effective January 8, 2009.
We must receive any comments on
this AD by February 23, 2009.
ADDRESSES: Use one of the following
addresses to comment on this AD.
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
Contact Rolls-Royce Corporation, P.O.
Box 420, Speed Code U15, Indianapolis,
IN 46206–0420, e-mail:
indy.pubs.services@rolls-royce.com, for
the service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Kyri
Zaroyiannis, Aerospace Engineer,
Chicago Aircraft Certification Office,
Small Airplane Directorate, FAA, 2300
E. Devon Ave., Des Plaines, IL 60018; email: kyri.zaroyiannis@faa.gov;
telephone (847) 294–7836; fax (847)
294–7834.
SUPPLEMENTARY INFORMATION: On
September 8, 2008, we issued
emergency AD 2008–19–51, that applies
to RRC AE 3007A series turbofan
engines. That AD requires performing
initial and repetitive ECIs on HPT stage
2 wheels that have accumulated 6,500
or more cycles-since-new (CSN). That
AD resulted from reports of HPT stage
2 wheels that had cracks in the bores of
the wheels. This condition, if not
corrected, could result in a possible
uncontained failure of the HPT stage 2
wheel, which could cause damage to the
airplane.
Actions Since AD 2008–19–51 Was
Issued
Since we issued that AD, we have
determined that the cracks in the HPT
stage 2 wheel bores are caused by a
thermally-induced high stress in the
disk bore which was not identified at
the time of the original certification. We
performed a new risk assessment for
cracking in the bore of the HPT stage 2
wheel using the FAA methodology
guidelines in FAA Advisory Circular
39.8 and the results of the inspections
from AD 2008–19–51. The risk
E:\FR\FM\24DER1.SGM
24DER1
78928
Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations
assessment takes into account physical
characteristics about the cracks that
were not available when we issued AD
2008–19–51. This risk assessment, in
combination with a sufficient number of
early inspections relative to the existing
AD, shows that the risk profile is not
rapidly increasing, which was a concern
when we issued AD 2008–19–51. Using
this new information, we determined
we could change the compliance
requirements for the ECI while still
maintaining a level of safety consistent
with the intent of the original AD. We
changed the new compliance schedule
to an interval of 150 cycles-in-service
(CIS) between wheel populations. The
intervals for the wheel populations are
based on CSN and they vary because of
the current distribution of the affected
wheels throughout the fleet. This
distribution results in a compliance
schedule that inspects the fleet from the
highest time, highest risk wheels to the
lowest time, lowest risk wheels, and
allows us to control the overall risk
consistent with the intent of the original
AD.
We determined that a requirement to
perform the ECI by a certain CIS is by
itself sufficient to maintain the level of
safety consistent with the intent of the
original AD. Because of that
determination, we no longer prohibit
installing any engine that has an HPT
stage 2 wheel with more than 6,500 CSN
unless the wheel was inspected. Instead,
we modified that requirement to apply
only to HPT stage 2 wheels removed
from service as a result of complying
with this AD.
Finally, we specify the P/Ns for the
affected HPT stage 2 wheels to ensure
proper identification.
pwalker on PROD1PC71 with RULES
Relevant Service Information
We have reviewed and approved the
technical contents of RRC Alert Service
Bulletin (ASB) AE 3007A–A–72–367,
dated September 5, 2008. That ASB
describes procedures for ECI of the HPT
stage 2 wheel on AE 3007A series
engines.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other RRC AE 3007A series turbofan
engines of the same type design. We are
issuing this AD to detect cracks in the
HPT stage 2 wheel, which could result
in a possible uncontained failure of the
HPT stage 2 wheel and damage to the
airplane. This AD requires:
• Removing from service any engine
with certain P/N HPT stage 2 wheels by
the compliance time specified in Table
1 of this AD; and
VerDate Aug<31>2005
19:28 Dec 23, 2008
Jkt 217001
• Performing an ECI on any HPT stage
2 wheel in any engine that was removed
from service as a requirement of this AD
before returning that HPT stage 2 wheel
to service.
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in less than 30
days.
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.
Interim Action
These actions are interim actions and
we may take further rulemaking actions
in the future.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2008–0975; Directorate Identifier
2008–NE–29–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of the Web site, anyone
can find and read the comments in any
of our dockets, including, if provided,
the name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78).
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 the same as the mail
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
Authority for This Rulemaking
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 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 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, Safety.
Adoption of the Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration amends part 39
of the Federal Aviation Regulations (14
CFR part 39) as follows:
E:\FR\FM\24DER1.SGM
24DER1
Federal Register / Vol. 73, No. 248 / Wednesday, December 24, 2008 / Rules and Regulations
Installation Prohibition
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 adding
a new airworthiness directive,
Amendment 39–15772, to read as
follows:
■
2008–26–06 Rolls-Royce Corporation
(Formerly Allison Engine Company):
Amendment 39–15772. Docket No.
FAA–2008–0975; Directorate Identifier
2008–NE–29–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 8, 2009.
DEPARTMENT OF TRANSPORTATION
(g) 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 removed as a result of paragraph (f)
of this AD, unless the HPT stage 2 wheel was
inspected as specified in RRC Alert Service
Bulletin (ASB) AE 3007A-A–72–367, dated
September 5, 2008.
Alternative Methods of Compliance
(h) 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.
(i) Alternative Methods of Compliance
(AMOCs) currently approved for AD 2008–
19–51 will remain in effect until the effective
date for this AD. After that date the AMOCs
will expire.
Special Flight Permits
Affected ADs
(b) This AD supersedes emergency AD
2008–19–51.
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)
23065892, 23069116, 23069438, 23069592,
23074462, 23074644, 23075345, 23084520, or
23084781, 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 detect cracks in the HPT stage 2 wheel,
which could result in a possible 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.
Removing Engines From Service
(f) For engines with an HPT stage 2 wheel,
P/Ns 23065892, 23069116, 23069438,
23069592, 23074462, 23074644, 23075345,
23084520, or 23084781, remove the engine
from service by the cycles-in-service (CIS)
specified in Table 1 of this AD.
(j) Under 14 CFR part 39.23, we are
limiting the special flight permits for this AD
by restricting the flight to essential flight
crew only.
Related Information
(k) 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.
(l) Rolls-Royce Corporation ASB AE
3007A-A–72–367, dated September 5, 2008,
contains information on performing ECIs on
HPT stage 2 wheels. Contact Rolls-Royce
Corporation, P.O. Box 420, Speed Code U15,
Indianapolis, IN 46206–0420; e-mail:
indy.pubs.services@rolls-royce.com, for a
copy of this service information.
Material Incorporated by Reference
(m) None.
Issued in Burlington, Massachusetts, on
December 12, 2008.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E8–30051 Filed 12–23–08; 8:45 am]
BILLING CODE 4910–13–P
TABLE 1—COMPLIANCE TIMES FOR
ENGINE REMOVAL FOR ECI OF THE
HPT STAGE 2 WHEELS
pwalker on PROD1PC71 with RULES
If the HPT stage 2
wheel has accumulated on the effective
date of this AD:
16,200 cycles-sincenew (CSN) or more.
15,800 to 16,199 CSN
15,500 to 15,799 CSN
VerDate Aug<31>2005
Then remove the engine from service:
Within 150 CIS.
Within 300 CIS.
Within 450 CIS.
19:28 Dec 23, 2008
Jkt 217001
PO 00000
Frm 00013
Fmt 4700
78929
Sfmt 4700
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1138; Directorate
Identifier 2008–CE–059–AD; Amendment
39–15778; AD 2008–26–12]
RIN 2120–AA64
Airworthiness Directives; Aircraft
Industries a.s. (Type Certificate G60EU
´ ´
previously held by LETECKE ZAVODY
a.s. and LET Aeronautical Works)
Model L 23 Super Blanik Sailplane
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
This Airworthiness Directive (AD) is
prompted by the discovery on L 23 SUPER–
BLANIK sailplanes of cracks in zones where
the front and aft control levers attach the
connecting rod designated as ‘‘control
bridge’’ on the relevant Illustrated Parts
Catalogues (IPC). If left uncorrected cracks
could propagate and lead to the breakage of
the connecting rod with subsequent loss of
control of the sailplane.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
January 28, 2009.
On January 28, 2009, the Director of
the Federal Register approves the
incorporation by reference of certain
publications listed in this AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at
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: 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:
E:\FR\FM\24DER1.SGM
24DER1
Agencies
[Federal Register Volume 73, Number 248 (Wednesday, December 24, 2008)]
[Rules and Regulations]
[Pages 78927-78929]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-30051]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0975; Directorate Identifier 2008-NE-29-AD;
Amendment 39-15772; AD 2008-26-06]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Corporation (RRC) AE 3007A
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding emergency airworthiness directive (AD)
2008-19-51 that we sent previously to all known U.S. owners and
operators of RRC AE 3007A series turbofan engines. That AD requires
performing initial and repetitive eddy current inspections (ECIs) on
the high-pressure turbine (HPT) stage 2 wheel for cracks. This AD
continues to require those same inspections, but revises the compliance
schedule for the initial inspection and specifies the affected HPT
stage 2 wheels by part number (P/N). This AD results from reports of
cracked HPT stage 2 wheels. We are issuing this AD to detect cracks in
the HPT stage 2 wheel, which could result in a possible uncontained
failure of the HPT stage 2 wheel and damage to the airplane.
DATES: Effective January 8, 2009.
We must receive any comments on this AD by February 23, 2009.
ADDRESSES: Use one of the following addresses to comment on this AD.
Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact Rolls-Royce Corporation, P.O. Box 420, Speed Code U15,
Indianapolis, IN 46206-0420, e-mail: indy.pubs.services@rolls-
royce.com, for the service information identified in this AD.
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: On September 8, 2008, we issued emergency AD
2008-19-51, that applies to RRC AE 3007A series turbofan engines. That
AD requires performing initial and repetitive ECIs on HPT stage 2
wheels that have accumulated 6,500 or more cycles-since-new (CSN). That
AD resulted from reports of HPT stage 2 wheels that had cracks in the
bores of the wheels. This condition, if not corrected, could result in
a possible uncontained failure of the HPT stage 2 wheel, which could
cause damage to the airplane.
Actions Since AD 2008-19-51 Was Issued
Since we issued that AD, we have determined that the cracks in the
HPT stage 2 wheel bores are caused by a thermally-induced high stress
in the disk bore which was not identified at the time of the original
certification. We performed a new risk assessment for cracking in the
bore of the HPT stage 2 wheel using the FAA methodology guidelines in
FAA Advisory Circular 39.8 and the results of the inspections from AD
2008-19-51. The risk
[[Page 78928]]
assessment takes into account physical characteristics about the cracks
that were not available when we issued AD 2008-19-51. This risk
assessment, in combination with a sufficient number of early
inspections relative to the existing AD, shows that the risk profile is
not rapidly increasing, which was a concern when we issued AD 2008-19-
51. Using this new information, we determined we could change the
compliance requirements for the ECI while still maintaining a level of
safety consistent with the intent of the original AD. We changed the
new compliance schedule to an interval of 150 cycles-in-service (CIS)
between wheel populations. The intervals for the wheel populations are
based on CSN and they vary because of the current distribution of the
affected wheels throughout the fleet. This distribution results in a
compliance schedule that inspects the fleet from the highest time,
highest risk wheels to the lowest time, lowest risk wheels, and allows
us to control the overall risk consistent with the intent of the
original AD.
We determined that a requirement to perform the ECI by a certain
CIS is by itself sufficient to maintain the level of safety consistent
with the intent of the original AD. Because of that determination, we
no longer prohibit installing any engine that has an HPT stage 2 wheel
with more than 6,500 CSN unless the wheel was inspected. Instead, we
modified that requirement to apply only to HPT stage 2 wheels removed
from service as a result of complying with this AD.
Finally, we specify the P/Ns for the affected HPT stage 2 wheels to
ensure proper identification.
Relevant Service Information
We have reviewed and approved the technical contents of RRC Alert
Service Bulletin (ASB) AE 3007A-A-72-367, dated September 5, 2008. That
ASB describes procedures for ECI of the HPT stage 2 wheel on AE 3007A
series engines.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other RRC AE 3007A series turbofan engines of the same type
design. We are issuing this AD to detect cracks in the HPT stage 2
wheel, which could result in a possible uncontained failure of the HPT
stage 2 wheel and damage to the airplane. This AD requires:
Removing from service any engine with certain P/N HPT
stage 2 wheels by the compliance time specified in Table 1 of this AD;
and
Performing an ECI on any HPT stage 2 wheel in any engine
that was removed from service as a requirement of this AD before
returning that HPT stage 2 wheel to service.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Interim Action
These actions are interim actions and we may take further
rulemaking actions in the future.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2008-0975;
Directorate Identifier 2008-NE-29-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
with FAA personnel concerning this AD. Using the search function of the
Web site, anyone can find and read the comments in any of our dockets,
including, if provided, the name of the individual who sent the comment
(or signed the comment on behalf of an association, business, labor
union, etc.). You may review the DOT's complete Privacy Act Statement
in the Federal Register published on April 11, 2000 (65 FR 19477-78).
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 the same as
the mail address provided in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
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 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 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, Safety.
Adoption of the Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
[[Page 78929]]
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding a new airworthiness directive,
Amendment 39-15772, to read as follows:
2008-26-06 Rolls-Royce Corporation (Formerly Allison Engine
Company): Amendment 39-15772. Docket No. FAA-2008-0975; Directorate
Identifier 2008-NE-29-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
8, 2009.
Affected ADs
(b) This AD supersedes emergency AD 2008-19-51.
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) 23065892, 23069116, 23069438, 23069592,
23074462, 23074644, 23075345, 23084520, or 23084781, 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 detect cracks in the HPT stage 2 wheel,
which could result in a possible 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.
Removing Engines From Service
(f) For engines with an HPT stage 2 wheel, P/Ns 23065892,
23069116, 23069438, 23069592, 23074462, 23074644, 23075345,
23084520, or 23084781, remove the engine from service by the cycles-
in-service (CIS) specified in Table 1 of this AD.
Table 1--Compliance Times for Engine Removal for ECI of the HPT Stage 2
Wheels
------------------------------------------------------------------------
If the HPT stage 2 wheel has accumulated Then remove the engine from
on the effective date of this AD: service:
------------------------------------------------------------------------
16,200 cycles-since-new (CSN) or more..... Within 150 CIS.
15,800 to 16,199 CSN...................... Within 300 CIS.
15,500 to 15,799 CSN...................... Within 450 CIS.
------------------------------------------------------------------------
Installation Prohibition
(g) 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 removed as a result of paragraph (f) of this AD,
unless the HPT stage 2 wheel was inspected as specified in RRC Alert
Service Bulletin (ASB) AE 3007A-A-72-367, dated September 5, 2008.
Alternative Methods of Compliance
(h) 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.
(i) Alternative Methods of Compliance (AMOCs) currently approved
for AD 2008-19-51 will remain in effect until the effective date for
this AD. After that date the AMOCs will expire.
Special Flight Permits
(j) Under 14 CFR part 39.23, we are limiting the special flight
permits for this AD by restricting the flight to essential flight
crew only.
Related Information
(k) 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.
(l) Rolls-Royce Corporation ASB AE 3007A-A-72-367, dated
September 5, 2008, contains information on performing ECIs on HPT
stage 2 wheels. Contact Rolls-Royce Corporation, P.O. Box 420, Speed
Code U15, Indianapolis, IN 46206-0420; e-mail:
indy.pubs.services@rolls-royce.com, for a copy of this service
information.
Material Incorporated by Reference
(m) None.
Issued in Burlington, Massachusetts, on December 12, 2008.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E8-30051 Filed 12-23-08; 8:45 am]
BILLING CODE 4910-13-P