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
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