Airworthiness Directives; Pratt & Whitney (PW) JT9D-7R4 Series Turbofan Engines, 20580-20582 [E9-10145]

Download as PDF 20580 Federal Register / Vol. 74, No. 85 / Tuesday, May 5, 2009 / Rules and Regulations List of Subjects in 13 CFR Part 121 Loan programs—business, Disaster assistance loans, Reporting and recordkeeping requirements, Small business. ■ For reasons set forth in the preamble, amend part 121 of title 13 Code of Federal Regulations as follows: PART 121—SMALL BUSINESS SIZE REGULATIONS would have applied if the applicant were a taxable corporation. (iii) Sum the results obtained in paragraphs (b)(2)(i) and (b)(2)(ii) of this section. * * * * * Dated: April 15, 2009. Karen G. Mills, Administrator. [FR Doc. E9–10359 Filed 5–1–09; 11:15 am] BILLING CODE 8025–01–P 1. The authority citation for part 121 continues to read as follows: ■ Authority: 15 U.S.C. 632, 634(b)(6), 636(b), 637, 644, and 662(5); and Pub. L. 105–135, sec. 401 et seq., 111 Stat. 2592. DEPARTMENT OF TRANSPORTATION 2. Amend § 121.301 by revising paragraphs (a) introductory text and (b) to read as follows: 14 CFR Part 39 ■ § 121.301 What size standards are applicable to financial assistance programs? 22:59 May 04, 2009 Jkt 217001 [Docket No. FAA–2006–23742; Directorate Identifier 2005–NE–53–AD; Amendment 39– 15896; AD 2009–10–06] RIN 2120–AA64 (a) For Business Loans (other than for 7(a) Business Loans for the period beginning May 5, 2009 and ending on September 30, 2010) and for Disaster Loans (other than physical disaster loans), an applicant business concern must satisfy two criteria: * * * * * (b) For Development Company programs and, for the period beginning May 5, 2009 and ending on September 30, 2010, for 7(a) Business Loans, an applicant must meet one of the following standards: (1) The same standards applicable under paragraph (a) of this section; or (2) Including its affiliates, tangible net worth not in excess of $8.5 million, and average net income after Federal income taxes (excluding any carry-over losses) for the preceding two completed fiscal years not in excess of $3.0 million. If the applicant is not required by law to pay Federal income taxes at the enterprise level, but is required to pass income through to its shareholders, partners, beneficiaries, or other equitable owners, the applicant’s ‘‘net income after Federal income taxes’’ will be its net income reduced by an amount computed as follows: (i) If the applicant is not required by law to pay State (and local, if any) income taxes at the enterprise level, multiply its net income by the marginal State income tax rate (or by the combined State and local income tax rates, as applicable) that would have applied if it were a taxable corporation. (ii) Multiply the applicant’s net income, less any deduction for State and local income taxes calculated under paragraph (b)(2)(i) of this section, by the marginal Federal income tax rate that VerDate Nov<24>2008 Federal Aviation Administration Airworthiness Directives; Pratt & Whitney (PW) JT9D–7R4 Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for PW JT9D–7R4 series turbofan engines. That AD currently requires removing certain reduced cooling flow 2nd stage high-pressure turbine (HPT) vane assemblies installed in certain 2nd stage HPT vane cluster assemblies. It also requires a visual and a fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal assembly, part number (P/N) 815097. This AD requires a visual and FPI of all P/N 2nd stage HPT air seal assemblies that were used with reduced cooling flow 2nd stage HPT vane assemblies. This AD results from PW identifying additional P/N air seal assemblies that are affected by the unsafe condition. We are issuing this AD to prevent uncontained failure of the 2nd stage HPT air seal assembly, leading to engine in-flight shutdown and damage to the airplane. DATES: This AD becomes effective June 9, 2009. ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565–4503. 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. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov; telephone (781) 238–7758; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by superseding AD 2007–17–21, Amendment 39–15180 (72 FR 48549, August 24, 2007), with a proposed AD. The proposed AD applies to PW JT9D– 7R4 series turbofan engines. We published the proposed AD in the Federal Register on November 9, 2007 (72 FR 63510). That action proposed to require at the next HPT module exposure: • Removing the reduced cooling flow 2nd stage HPT vane assemblies. • Visual and fluorescent penetrant inspections of the 2nd stage HPT air seal assemblies that have operated in an engine with reduced cooling flow 2nd stage HPT vane assemblies. 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. Difficulty Determining Reduced Cooling Flow 2nd Stage HPT Vane Assemblies One commenter, FedEx Express, states since FedEx Express does not track 2nd stage NGVs, it will be difficult to determine if the 2nd stage air seal operated in an engine with reduced cooling flow HPT vane assemblies installed. We don’t agree. There is no requirement to identify 2nd stage air seals which may have operated in the past with reduced cooling flow 2nd stage HPT vane assemblies. This AD requires inspections of 2nd stage air seals if at disassembly, the air seals are found with reduced cooling flow 2nd stage HPT vanes installed. HPT 2nd stage air seals that pass inspection requirements per the engine manual E:\FR\FM\05MYR1.SGM 05MYR1 Federal Register / Vol. 74, No. 85 / Tuesday, May 5, 2009 / Rules and Regulations may be reinstalled. We changed the AD to make this clear. Request to Remove PW Alert Service Bulletin JT9D–7R4–A72–596 From the AD The same commenter states that the NPRM contains a paragraph titled ‘‘Relevant Service Information.’’ The paragraph provides the instructions for modifying the reduced cooling flow vane assemblies. FedEx Express asks ‘‘What is the purpose of the subject paragraph?’’ They ask if the AD will include a reference to PW ASB JT9D– 7R4–A72–96 as a requirement to modify 2nd stage HPT vane assemblies. They ask us to remove the paragraph since it may not be pertinent to the action required by this AD. We partially agree. We agree that incorporating the requirements of PW ASB JT9D–7R4–A72–596, dated September 15, 2005, isn’t a requirement of the AD. However, we include this information in the AD as relevant information to inform operators that a rework procedure for the 2nd stage vanes is available and that parts don’t have to be replaced with new parts. We didn’t change the AD. 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 as proposed. Costs of Compliance We estimate that this AD will affect 85 PW JT9D–7R4 series turbofan engines installed on airplanes U.S. registry. We also estimate that it would take about 65.5 work-hours per engine to perform the required actions, and that the average labor rate is $80 per workhour. Required parts will cost about $5,400 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $904,400. 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 VerDate Nov<24>2008 22:59 May 04, 2009 Jkt 217001 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, Safety. 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: ■ 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 39–15180 (72 FR 48549, August 24, 2007), and by adding a new airworthiness directive, Amendment 39–15896, to read as follows: ■ 2009–10–01 Pratt & Whitney: Amendment 39–15896. Docket No. FAA–2006–23742; Directorate Identifier 2005–NE–53–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 9, 2009. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 20581 Affected ADs (b) This AD supersedes AD 2007–17–21, Amendment 39–15180. Applicability (c) This AD applies to Pratt & Whitney (PW) JT9D–7R4G2, –7R4E1, –7R4E4, and –7R4H1 series turbofan engines. These engines are installed on, but not limited to, Boeing 747–200, –300, 767–200, and Airbus A300–600 and A310–300 series airplanes. Unsafe Condition (d) This AD results from the manufacturer identifying additional part number (P/N) air seal assemblies that are affected by the unsafe condition. We are issuing this AD to prevent uncontained failure of the 2nd stage highpressure turbine (HPT) air seal assembly, leading to engine in-flight shutdown and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed at the next HPT module exposure after the effective date of this AD, unless the actions have already been done. (f) At the next HPT module exposure, remove reduced cooling flow 2nd stage HPT vane assemblies P/Ns: 797282, 796972, 800082, 800072, 803182, 803282, and 822582, installed in 2nd stage HPT vane cluster assemblies: P/Ns 797592, 797372, 799872, 799782, and 822572. (g) For 2nd stage HPT air seals that are installed in engines that had a reduced cooling flow HPT vane assembly removed as specified in (f) of this AD, do the following: (1) Perform a onetime visual inspection of the 2nd stage HPT air seal assembly. Information on the visual inspection can be found in the JT9D–7R4 engine manual, Section 72–51–22, Inspection/Check–01, paragraphs 1.D.(1), 1.D.(4), and 1.D.(6). (2) Perform a fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal assembly for cracks. Information on the FPI can be found in the JT9D–7R4 engine manual, Section 72–51–00, Inspection/Check–03. Definition (h) For the purpose of this AD, we define an HPT module exposure as removing the 1st stage HPT rotor or the 2nd stage HPT rotor from the HPT case. Alternative Methods of Compliance (i) The Manager, Engine 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. Related Information (j) Pratt & Whitney Alert Service Bulletin JT9D–7R4–A72–596, dated September 15, 2005, contains information for modifying the reduced cooling flow 2nd stage HPT vane assemblies. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565–4503, for a copy of this service information. (k) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA E:\FR\FM\05MYR1.SGM 05MYR1 20582 Federal Register / Vol. 74, No. 85 / Tuesday, May 5, 2009 / Rules and Regulations 01803; e-mail: mark.riley@faa.gov; telephone (781) 238–7758; fax (781) 238–7199, for more information about this AD. the Center for Veterinary Medicine, 21 CFR part 510 is amended as follows: Material Incorporated by Reference (l) None. PART 510—NEW ANIMAL DRUGS 1. The authority citation for 21 CFR part 510 continues to read as follows: ■ Issued in Burlington, Massachusetts, on April 23, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–10145 Filed 5–4–09; 8:45 am] Authority: 21 U.S.C. 321, 331, 351, 352, 353, 360b, 371, 379e. 2. In § 510.600 in the table in paragraph (c)(1), remove the entry for ‘‘IVX Animal Health, Inc.’’ and alphabetically add a new entry for ‘‘Teva Animal Health, Inc.’’; and in the table in paragraph (c)(2), revise the entry for ‘‘059130’’ to read as follows: ■ BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration § 510.600 Names, addresses, and drug labeler codes of sponsors of approved applications. 21 CFR Part 510 * [Docket No. FDA–2009–N–0665] * * (c) * * * (1) * * * New Animal Drugs; Change of Sponsor’s Name AGENCY: * Firm name and address Food and Drug Administration, HHS. ACTION: * Final rule. SUMMARY: The Food and Drug Administration (FDA) is amending the animal drug regulations to reflect a change of sponsor’s name from IVX Animal Health, Inc., to Teva Animal Health, Inc. DATES: This rule is effective May 5, 2009. FOR FURTHER INFORMATION CONTACT: David R. Newkirk, Center for Veterinary Medicine (HFV–100), Food and Drug Administration, 7500 Standish Pl., Rockville, MD 20855, 240–276–8307, email: david.newkirk@fda.hhs.gov. SUPPLEMENTARY INFORMATION: IVX Animal Health, Inc., 3915 South 48th Street Ter., St. Joseph, MO 64503, has informed FDA that it has changed its name to Teva Animal Health, Inc. Accordingly, the agency is amending the regulations in 21 CFR 510.600(c) to reflect this change. This rule does not meet the definition of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because it is a rule of ‘‘particular applicability.’’ Therefore, it is not subject to the congressional review requirements in 5 U.S.C. 801–808. List of Subjects in 21 CFR Part 510 22:59 May 04, 2009 Jkt 217001 * 059130 * * * (2) * * * Drug labeler code * 059130 * * * Firm name and address * * * Teva Animal Health, Inc., 3915 South 48th Street Ter., St. Joseph, MO 64503 * * * Dated: April 29, 2009. Steven D. Vaughn, Director, Office of New Animal Drug Evaluation, Center for Veterinary Medicine. [FR Doc. E9–10262 Filed 5–4–09; 8:45 am] BILLING CODE 4160–01–S Final rule. SUMMARY: The Food and Drug Administration (FDA) is amending the animal drug regulations to reflect a change of sponsor’s name from Summit Hill Laboratories to Putney, Inc. DATES: This rule is effective May 5, 2009. FOR FURTHER INFORMATION CONTACT: David R. Newkirk, Center for Veterinary Medicine (HFV–100), Food and Drug Administration, 7500 Standish Pl., Rockville, MD 20855, 240–276–8307, email: david.newkirk@fda.hhs.gov. Summit Hill Laboratories, P.O. Box 535, Navesink, NJ 07752, has informed FDA that it has transferred ownership of, and all rights and interest in, NADA 8–760 for ADRENOMONE (repository corticotropin injection U.S.P.) to Putney, Inc., 400 Congress St., suite 200, Portland, ME 04101. Accordingly, the regulations are amended in 21 CFR 522.480 to reflect this change of sponsorship. This rule does not meet the definition of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because it is a rule of ‘‘particular applicability.’’ Therefore, it is not subject to the congressional review requirements in 5 U.S.C. 801–808. SUPPLEMENTARY INFORMATION: List of Subjects in 21 CFR Part 522 Animal drugs. Therefore, under the Federal Food, Drug, and Cosmetic Act and under authority delegated to the Commissioner of Food and Drugs and redelegated to the Center for Veterinary Medicine, 21 CFR part 522 is amended as follows: ■ PART 522—IMPLANTATION OR INJECTABLE DOSAGE FORM NEW ANIMAL DRUGS 1. The authority citation for 21 CFR part 522 continues to read as follows: ■ DEPARTMENT OF HEALTH AND HUMAN SERVICES Authority: 21 U.S.C. 360b. Food and Drug Administration § 522.480 21 CFR Part 522 ■ Implantation or Injectable Dosage From New Animal Drugs; Change of Sponsor; Repository Corticotropin Injection AGENCY: Food and Drug Administration, HHS. PO 00000 Frm 00024 [Amended] 2. In paragraph (a)(2) of § 522.480, remove ‘‘037990’’ and add in its place ‘‘026637’’. [Docket No. FDA–2009–N–0665] Administrative practice and procedure, Animal drugs, Labeling, Reporting and recordkeeping requirements. ■ Therefore, under the Federal Food, Drug, and Cosmetic Act and under authority delegated to the Commissioner of Food and Drugs and redelegated to VerDate Nov<24>2008 * * * Teva Animal Health, Inc., 3915 South 48th Street Ter., St. Joseph, MO 64503 * * * Drug labeler code ACTION: Dated: April 30, 2009. Steven D. Vaughn, Director, Office of New Animal Drug Evaluation, Center for Veterinary Medicine. [FR Doc. E9–10291 Filed 5–4–09; 8:45 am] BILLING CODE 4160–01–S Fmt 4700 Sfmt 4700 E:\FR\FM\05MYR1.SGM 05MYR1

Agencies

[Federal Register Volume 74, Number 85 (Tuesday, May 5, 2009)]
[Rules and Regulations]
[Pages 20580-20582]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-10145]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23742; Directorate Identifier 2005-NE-53-AD; 
Amendment 39-15896; AD 2009-10-06]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney (PW) JT9D-7R4 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for PW JT9D-7R4 series turbofan engines. That AD currently 
requires removing certain reduced cooling flow 2nd stage high-pressure 
turbine (HPT) vane assemblies installed in certain 2nd stage HPT vane 
cluster assemblies. It also requires a visual and a fluorescent 
penetrant inspection (FPI) of the 2nd stage HPT air seal assembly, part 
number (P/N) 815097. This AD requires a visual and FPI of all P/N 2nd 
stage HPT air seal assemblies that were used with reduced cooling flow 
2nd stage HPT vane assemblies. This AD results from PW identifying 
additional P/N air seal assemblies that are affected by the unsafe 
condition. We are issuing this AD to prevent uncontained failure of the 
2nd stage HPT air seal assembly, leading to engine in-flight shutdown 
and damage to the airplane.

DATES: This AD becomes effective June 9, 2009.

ADDRESSES: You can get the service information identified in this AD 
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-8770; fax (860) 565-4503.
    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: Mark Riley, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
mark.riley@faa.gov; telephone (781) 238-7758; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 2007-17-21, Amendment 39-15180 (72 FR 48549, August 24, 
2007), with a proposed AD. The proposed AD applies to PW JT9D-7R4 
series turbofan engines. We published the proposed AD in the Federal 
Register on November 9, 2007 (72 FR 63510). That action proposed to 
require at the next HPT module exposure:
     Removing the reduced cooling flow 2nd stage HPT vane 
assemblies.
     Visual and fluorescent penetrant inspections of the 2nd 
stage HPT air seal assemblies that have operated in an engine with 
reduced cooling flow 2nd stage HPT vane assemblies.

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.

Difficulty Determining Reduced Cooling Flow 2nd Stage HPT Vane 
Assemblies

    One commenter, FedEx Express, states since FedEx Express does not 
track 2nd stage NGVs, it will be difficult to determine if the 2nd 
stage air seal operated in an engine with reduced cooling flow HPT vane 
assemblies installed.
    We don't agree. There is no requirement to identify 2nd stage air 
seals which may have operated in the past with reduced cooling flow 2nd 
stage HPT vane assemblies. This AD requires inspections of 2nd stage 
air seals if at disassembly, the air seals are found with reduced 
cooling flow 2nd stage HPT vanes installed. HPT 2nd stage air seals 
that pass inspection requirements per the engine manual

[[Page 20581]]

may be reinstalled. We changed the AD to make this clear.

Request to Remove PW Alert Service Bulletin JT9D-7R4-A72-596 From the 
AD

    The same commenter states that the NPRM contains a paragraph titled 
``Relevant Service Information.'' The paragraph provides the 
instructions for modifying the reduced cooling flow vane assemblies. 
FedEx Express asks ``What is the purpose of the subject paragraph?'' 
They ask if the AD will include a reference to PW ASB JT9D-7R4-A72-96 
as a requirement to modify 2nd stage HPT vane assemblies. They ask us 
to remove the paragraph since it may not be pertinent to the action 
required by this AD.
    We partially agree. We agree that incorporating the requirements of 
PW ASB JT9D-7R4-A72-596, dated September 15, 2005, isn't a requirement 
of the AD. However, we include this information in the AD as relevant 
information to inform operators that a rework procedure for the 2nd 
stage vanes is available and that parts don't have to be replaced with 
new parts. We didn't change the AD.

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 as proposed.

Costs of Compliance

    We estimate that this AD will affect 85 PW JT9D-7R4 series turbofan 
engines installed on airplanes U.S. registry. We also estimate that it 
would take about 65.5 work-hours per engine to perform the required 
actions, and that the average labor rate is $80 per work-hour. Required 
parts will cost about $5,400 per engine. Based on these figures, we 
estimate the total cost of the AD to U.S. operators to be $904,400.

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, Safety.

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 39-15180 (72 FR 
48549, August 24, 2007), and by adding a new airworthiness directive, 
Amendment 39-15896, to read as follows:

2009-10-01 Pratt & Whitney: Amendment 39-15896. Docket No. FAA-2006-
23742; Directorate Identifier 2005-NE-53-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 9, 
2009.

Affected ADs

    (b) This AD supersedes AD 2007-17-21, Amendment 39-15180.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT9D-7R4G2, -7R4E1, 
-7R4E4, and -7R4H1 series turbofan engines. These engines are 
installed on, but not limited to, Boeing 747-200, -300, 767-200, and 
Airbus A300-600 and A310-300 series airplanes.

Unsafe Condition

    (d) This AD results from the manufacturer identifying additional 
part number (P/N) air seal assemblies that are affected by the 
unsafe condition. We are issuing this AD to prevent uncontained 
failure of the 2nd stage high-pressure turbine (HPT) air seal 
assembly, leading to engine in-flight shutdown and damage to the 
airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed at the next HPT module exposure after the effective 
date of this AD, unless the actions have already been done.
    (f) At the next HPT module exposure, remove reduced cooling flow 
2nd stage HPT vane assemblies P/Ns: 797282, 796972, 800082, 800072, 
803182, 803282, and 822582, installed in 2nd stage HPT vane cluster 
assemblies: P/Ns 797592, 797372, 799872, 799782, and 822572.
    (g) For 2nd stage HPT air seals that are installed in engines 
that had a reduced cooling flow HPT vane assembly removed as 
specified in (f) of this AD, do the following:
    (1) Perform a onetime visual inspection of the 2nd stage HPT air 
seal assembly. Information on the visual inspection can be found in 
the JT9D-7R4 engine manual, Section 72-51-22, Inspection/Check-01, 
paragraphs 1.D.(1), 1.D.(4), and 1.D.(6). (2) Perform a fluorescent 
penetrant inspection (FPI) of the 2nd stage HPT air seal assembly 
for cracks. Information on the FPI can be found in the JT9D-7R4 
engine manual, Section 72-51-00, Inspection/Check-03.

Definition

    (h) For the purpose of this AD, we define an HPT module exposure 
as removing the 1st stage HPT rotor or the 2nd stage HPT rotor from 
the HPT case.

Alternative Methods of Compliance

    (i) The Manager, Engine 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.

Related Information

    (j) Pratt & Whitney Alert Service Bulletin JT9D-7R4-A72-596, 
dated September 15, 2005, contains information for modifying the 
reduced cooling flow 2nd stage HPT vane assemblies. Contact Pratt & 
Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-
8770; fax (860) 565-4503, for a copy of this service information.
    (k) Contact Mark Riley, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA

[[Page 20582]]

01803; e-mail: mark.riley@faa.gov; telephone (781) 238-7758; fax 
(781) 238-7199, for more information about this AD.

Material Incorporated by Reference

    (l) None.

    Issued in Burlington, Massachusetts, on April 23, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-10145 Filed 5-4-09; 8:45 am]
BILLING CODE 4910-13-P

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